Home

PILOT'S FLIGHT OPERATING INSTRUCTIONS

1. 53 Take off Climb and Landing Chart 38 54 Flight Operations Instruction Charts P 38H 55 58 Flight Operations Instruction Charts P 38 and 58 59 62 RESTRICTED RESTRICTED Section No 01 75 1 F 5B is SIMILAR 38 EXCEPT NO GUNS ARE INSTALLED The Airplane RESTRICTED ili 3442 10 ON 041 030 Mes aac eh me ET Figure 2 Three Quarter Rear View of Complete Airplane 9315141534 Al Section Paragraph 1 2 RESTRICTED No 01 75FF 1 SECTION the same as the fighters but all armament is replaced by cameras 2 ENGINE AND PROPELLER CONTROL a THROTTLE AND SUPERCHARGER CONTROL 1 The throttle is mechanically connected to the supercharger regulator so that control of the super charger as a separate operation has been eliminated 2 Operation of the throttle control figure 4 2 the same as a conventional throttle except that the engine response is sluggish in the 2 3 to WIDE OPEN range This sluggish response is due to the time required for the superchargers to reach their new speed b MIXTURE CONTROLS 1 The mixture controls figure 4 6 have four positions FULL RICH AUTO RICH AUTO LEAN and CUTOFF Operate as
2. 4 8 Heating and 7 9 Electrical System 7 05 mM 11 Miscellaneous mC L u TEE IE 9 SECTION 1 PILOT OPERATING INSTRUCTIONS PH GRE 1558001689488 etr RRR 72 21 2 Before Entering the Cockpit 00 21 3 On Entering the Cockpit rsen enr eere rens 22 4 Fuel System Management rrr onn eren rer reina Raten 23 5 Starting Engines 24 Di NGABA 759 7 24 7 Emergency 24 8 Engine and Accessories Operation Ground 24 9 Taxiing Instructions E ux 9 11 Engine Failure During 1 00 26 12 11858 rep eae ene nie 26 13 General Flying Characteristics eene eene 26 14 MERANA SPAM P PENGEN GA SEMANGAT 27 LTE 0 27 16 Acrobatics 27 17 Diving irren 27 19 Approach and Landing PRIN dibus 28 20 Stopping of Engines i HISO KN A PAIR ET EECHER 29 21 Before Leaving Cockpit
3. 29 22 Tieing Deen 29 RESTRICTED RESTRICTED 01 75FF 1 SECTION FLIGHT OPERATING DATA Paragraph Page E EE EEN 2 and Altimeter Correction Table rr meses 31 Engine 711817 Chart 38 aana war 32 Specific Engine Flight Chart 38 and 58 33 SECTION IV EMERGENCY OPERATING INSTRUCTIONS 1 Hydraulic Failure sus 2 Landing with Wheels nnne noma 36 Landing on Water IDHEP b anren 36 4 Elecirical ass Kan 36 Engine eon M 36 Icing ConGitions E 37 7 Emergency O 37 SECTION V OPERATIONAL EQUIPMENT ls ees 39 2 Operation of the Oxygen Equipment 5 esee anara aa rrr nara 42 GE Che 9 9 9 0 43 4 Operation of 4 Automatic Pilot esee 46 5 Operation of the Camera 46 APPENDIX I Glossary of Nomenclature 5 58 49 APPENDIX II FLIGHT OPERATING CHARTS TABLES CURVES AND DIAGRAMS 1 Flight Planning REENEN a Take off Climb and Landing Chart 38
4. 01 75 1 2 The override switches figure 6 13 may operated to fully OPEN or fully CLOSE the flaps in the event that the regulators fail to maintain the above temperatures It 15 not possible to set the coolant flap to any position except full OPEN or full CLOSE when using the override switches If hydraulic pressure fails completely the flaps will assume a faired mid posi f OIL TEMPERATURE CONTROLS 1 temperature is automatically regulated be tween 75 flaps closed and 95 C flaps open 167 to 203 F with the oil cooler flap switches fig ure 6 17 set to AUTOMATIC 2 The cooler flap switches have four posi tions AUTOMATIC OFF OPEN and CLOSE They may be operated to place and hold the flaps in any position in the event the regulators fail to maintain the above temperatures The pilot is protected from U 5 30 German 312 and Jap 303 7 7 caliber fire originating within the colored area Figure 3 Armor Protection Section Paragraph 2 2 PROPELLER SELECTOR SWITCHES figure 4 5 have four positions a AUTO CONSTANT SPEED The propel ler governors are in operation and engine speed will be maintained as set on the propeller pitch levers figure 4 4 b FIXED PITCH Propeller pitch is fixed engine speed depends upon power and airplane speed INC RPM Propeller pitch decreases
5. Coolant From Engine Vent to Atmosphere Coolant From Tank Breather Lines Coolant to Engines Temperature Regulator Lines Hydraulic Lines Coolant reservoir Vent to atmosphere Coolant outlet from engine Coolant inlet to engine Automatic temperature regulator Coolant radiator exit hydraulic cylinder Coolant radiators SAW Figure 16 Coolant System Diagram RESTRICTED 17 Section 1 RESTRICTED 01 75FF 1 pim d a j 1 m Hg Vacuum Air Pressure 42 2 Hg Vacuum Filtered Air Atmospheric Pressure b Suction System vacuum regulator Gyro horizon 3 Backfire reltef valve Air filter outlet to atmosphere Directional gyro separator Turn and bank indicator Vacuum pumps Turn and bank vacuum regulator Oil return to engine 18 RESTRICTED Section Figure 18 19 RESTRICTED No 01 75FF 1 Heat bypass shutoff valve Windshield defroster tube Cockpit heat control Exhaust Manifold Cockpit Heat Lines Flexible hatch defroster tube Foot heat shutoff valve Armament Heat Lines Gun or camera heat control Figure 18 Heating System Diagram RESTRICTED Section Il Paragraph 1 2 corresponds to 28 50 gear down Under these tail heavy conditions full down elevator
6. WEIGHT SEA AT 3 000 FT AT SEA LEVEL 3 000 FT 6 000 FT SEA LEVEL 3 000 FT AT 6 000 FT LBS Grouno TO CLEAR GROUND TO GROUND CLEAR cur Grouno GROUND TO 0 RUN 50 OBJ RUN 50 OBJ RUN 50 OBJ RUN SO 081 50 OBJ 50 OBJ Bed 1350 20 1460 750 1440 990 1820 uut 1000 8600 1240 1060 580 1380 200 650 320 Bn 24 700 260 950 2150 1200 2235 1490 2590 d350 2440 1700 2970 22 1740 ano 1800 1140 2160 1020 1960 1300 2400 1310 610 1360 780 1630 706 1500 900 1830 var 370 020 1270 1250 2290 1380 188 250 2700 1120 2180 1380 2540 1290 2000 1620 2820 2140 19 500 770 1630 970 2080 900 1930 1170 2290 420 1110 560 1480 510 1270 7220 1640 NOTE INCREASE DISTANCE 10 FOR EACH 10 C ABOVE O C 11 FOR EACH 20 ABOVE 32 F ENGINE LIMITS FOR TAKE OFF 3000 RPM amp 54 IN HG COMBAT MISSIONS USE 3000 WM FERRY MISSIONS USE 2300 amp 34 GROSS L TO 5 FI AUT 10 000 rr 15 000 rr art AT 25 000H AU AT 35 000 Fr att WEIGHT 5 BEST TIME FUEL ume FUE CHANGE IN LBS 1 GAS FT MIN FROM S L F
7. 7 Disconnect the destructor plug as soon as the airplane lands in friendly territory f BC 608 CONTACTOR Provisions have been made for the installation of this unit when in British squadrons or when operating in conjunction with British airplanes 1 Before take off turn the contactor heater switch ON wind the clock and synchronize it with the control clock by sctting the clock switch figure 24 3 to RUN at the given signal 2 Turn the command transmitter ON 3 Turn the contactor switch figure 24 1 to IN a Automatic transmission takes place during the 15 seconds the clock hand is between the 12 00 and the 3 00 o clock position Normal transmission and reception is not possible during this time Six position switch Emergency switch ON OFF switch Protection plug to prevent short circuit with safety belt 7 5 Headset jack Al 6 Destructor buttons 7 G band switches GER RESTRICTED No 01 75 1 e SCR 695 A RADIO 1 Before take off insert the destructor plug the radio located just forward of and accessible through the baggage compartment door on the right boom The destructor plug socket is on the right side set apart from the group of three sockets on the left side of the radio DANGER Do not insert the destructor plug if the red warning lights located over the radio set in the boom are lighted Make sure that the warning light system has been
8. Indicated Air Speed L Ras Auto Rich 2 98 GAS IMP GALS FOR WARM UP Manifold Presaure In 1 Auto Lean 5 TAKE OFF AND CLIMB o 5 000 reer ALTITUDE M RETURN FUEL FLOWS TO EX Fall Teele USE FUEL FROM TANKS IN THE FOLLOWING ORDER bi sa TO SPECIFIC ENGINE FLIGHT CHART FOR ADDITIONAL ENGINE OPERATION DATA 0010 ZS EXTERNAL LOAD ITEMS DEAD PROPELLER FEATHERED FLIGHT OPERATION INSTRUCTION CHART pe b amp m m m 8 xipueddy except in emergency Columns 11 IV amp V toward the right pro gressively give increase in range at sacrifice in speed Manifold Pressure Gallons Per Hour G P H ore approximate maximum valves for reference 0 For quick reference take off and military power data are listed in the upper left corner of chart NO RESERVE FUEL ALLOWANCE MAX RANGE RANGE IM AIR MILES 3442 10 ON 04 0308 LES Auto Rich _ LAS Indicated Spoed MP Manifold Pressure U 5 G F H 5 Gallons Hour INSTRUCTIONS FOR USING CHART Select figure in fuel column equal to or less than total amount of fuel in airplane Move horizontally to the right or left and select a figure equal to or greater than the air miles to be flown Vertically below and opposite desired cruising altitude r
9. NOTE It may be necessary to operate the electric fuel pumps for a short while if the engine driven pumps do not build up pressure immediately CAUTION Due to the fire hazard electric fuel pumps must not be operated unless the mixture 18 in or unless the engine is running 24 RESTRICTED Section Paragraph 8 10 to ease wheel back at about 70 mph then at 90 100 lift the airplane into the air NOTE The top hatch must be locked in place and the side windows should be cranked figure 10 2 14 8 closed with the ratchets figure 10 3 14 7 on Open side windows will cause buffet ing of the tail section TO AIRPORT 10 MILES TRICYCLE GEAR WILL NEVER GET OFF BY ITSELF eee TRY LIFTING THE NOSE 70 a Propeller pitch levers figure 4 4 INC RPM full forward b Propeller selector switches figure 4 5 AUTO CONSTANT SPEED c Mixture figure 4 6 AUTO RICH d Tank selector valves figure 10 7 and 10 8 RE SERVE ON preferred e Wing flaps UP and lever figure 5 2 CLOSED Up to 15 flaps may be used for short take off run f Controls free Generator switch es figure 6 16 ON b Intercooler flaps figure 6 12 OPEN if in stalled i Electric fuel pumps figure 10 4 ON j Rudder elevator and aileron tabs ZERO k Hatch locked in place and side windows CLOSED 1 Hold brakes open throttles to 46 Hg 3000 rpm Release brakes keep manifold press
10. SA Ed BE CAREFUL WHERE YOU DROP YOUR TANKS 9 If the left engine has failed and consequently the generator stopped take action indicated under ELECTRICAL FAILURE Section IV paragraph 4 This is not applicable to F 5B airplanes which have a generator on each engine RESTRICTED Section V Paragraph 1 SECTION V NOTE The T and R positions are provided for use on installations employing a separate radio oper ator Transmission 15 impossible with the switch in the R position reception 15 impossible with the switch in the T position The lock lever figure 5 8 spring loads the selector switch to the R position and prevents operation in the REM position 7 To stop the equipment push the OFF button 39 figure 5 5 NOTE This radio is not equipped with a volume con trol Some installations may have a remote volume control installed service which 1 be located on the junction box on the right hand side of the cockpit over the hydraulic hand pump RESTRICTED 01 75 1 1 RADIO These airplanes may be equipped with SCR 522 command set as shown in figure 5 or an SCR 274N com mand set illustrated in figure 22 An SCR 695 A radio and a Detrola model 438 beacon receiver are installed when the airplane leaves the factory Provisions for the BC 608 contactor are installed at the factory and the unit may be installed in the field b OPERATION OF THE SCR 522 RAD
11. FE 4 FI MHH LIMITIN ACCELERATION 1 SPEED IN M P H INDICATED OUTSIDE OF ABOVE LIMITS BUFFETING AND DIVE TENDENCY MAY BE EXPECTED IF EX PERIENCED REDUCE ACCELERATION OR SPEED Figure 21 Dive Placard 17 DIVING NOTE MANIFOLD PRESSURE MUST BE KEPT 20 HG OR ABOVE DURING DIVES TO PREVENT POSSIBLE MALFUNCTION ING OR MISSING OF ENGINES WHEN THROTTLES ARE OPENED AFTER THE PULLOUT FROM THE DIVE a The diving speed ts restricted as indicated on the placard figure 21 a copy of which ts posted in the cockpit of each airplane As the airplane approaches the critical speed it becomes rapidly nose heavy and starts to buffet as if it were about to stall If this condi RESTRICTED 01 75FF 1 3 Re adjust the throttles 4 Mixture figure 4 6 AUTO LEAN if per missible d The turbo superchargers in this airplane are con trolled by the same levers which operate the throttles Turbo overspeed is indicated by the warning lights figure 7 12 Rated turbo speed is 24 000 rpm and overspeed turbo speed is 26 400 rpm allowed for 5 minutes The warning lights start to flicker at 25 600 turbo rpm and burn continuously at 26 400 turbo rpm Operation within the flickering range is permissible only during war emergencies and the throttles must be re tarded when the flicker changes to continuous burning e P 38 and F 5B airplanes intercooler flaps should be open for take off and cl
12. OG 10123 35 33006 731137 9255214 AJEA sseddq ujais s 033 Sutpue 5901 paya uaya juo uado sarea 22 12430 ur 1 0210 ouo U MOH 321 SMOTTY AJEA pue PAP 60117060100001 L OL A35 6I 8l 91 61 15 Cl 11 OI 1233 1 UTEJp 10419521 g1aydsoune 01 342 041402 011102 1898 100p 838 401011 4 o dn 1833 ul YING YIOT UMOP Ipu uorsuarx2 01 7 133 SurpurT 1349 01102 Jo 211155 uo Surpuedap 07 IO 1 sdeg 840165 4015 deg 7 No 01 75 1 Section RESTRICTED Section RESTRICTED No 01 75 1 Automatic temperature regulator 2 Line to oil pressure gage 3 Oil Tank capacity 13 U S gal 11 Imperial gal gt Supercharger regulator Vents to atmopshere from engine cooling radiators ZE to engine Main Lines Line to Pressure Gage Breather Lines Vent Lines Supercharger Regulator Oil Line Figure 15 Oil System Diagram 16 RESTRICTED RESTRICTED Section No 01 75 1
13. carriage AMERICAN Accumulator hydraulic Aur filter Airfoil Antenna Battery electrical Ceiling Check valve Command set radio Course direction with respect to true north Critical speed Cylinder hydraulic Drift Empennage Flare signal Gage fuel Gasoline gas fuel Generator Ground electrical Gyro horizon Heading Indicated air speed ias Landing gear 49 RESTRICTED Appendix ll RESTRICTED T 01 75 1 APPENDIX II Diagrams Range in Air Miles section of the FLIGHT OPERA TION INSTRUCTION CHART 3 Select a figure in the fuel column equal to or the next entry less than the available amount of fuel in the airplane as determined in paragraph 2 a 2 above Move horizontally to the right or left and select a figure equal to or the next entry greater than the air miles with no wind to be flown Operating values contained in the column number in which this figure appears represent the highest cruising speed possible at the range desired however the airplane may be oper ated in accordance with values contained under OPER ATING DATA in any column of a higher number with the flight plan being completed at a sacrifice of speed but at an increase in fuel economy 4 Using the same column number selected by application of instructions contained in the preceding paragraph read the gallons per hour given at the alti tude to be flown and divide this figure
14. ill IN amp toward the right pro or less than total amount of fuel in airplane Move horizontally to the right gressively give increase in range at sacrifice in speed C Manifold Pressure UN TAKE OFF 3000 54 or left and select a figure equal to greater than the air miles to be M P Galloms Per Hour G P H are approximate maximum volves for 3000 5 162 flown Vertically below and opposite desired cruising altitude read op reference ID For quick reference take off and military power data listed timum cruising conditions NOTES Avoid continuous cruising Column in the upper left corner of chart wena in V 1710 89 RH 9 NO RESERVE FUEL ALLOWANCE RANGE RANGE IR AIR MILES an RANGE IM AIR MILES MAX CONT POWER KAMBI IM AIR MILES STATUTE NAUTICAL STATUTE NAUTICAL STATUTE NAUTICAL 51 12 000 ats 8000 sdt avai 1110 970 1920 1670 2640 2290 1010 880 _ 1750 1520 2380 2070 810 790 1570 1370 2130 1850 810 710 1400 1220 1880 1630 710 620 1230 1070 1610 1420 610 530 080 920 510 450 880 770 Hun 30 710 620 310 270 180 OPER ATING DATA AS REM MPH TURE Ll 31 AL A ML 31 D 1 INDICATED ALTITUDE CORRECTED FOR FREE AIR TEMPERATURE 1 5
15. 1570 980 2140 810 1360 7160 1530 1070 2240 700 1500 900 1830 1260 2820 1070 500 1570 320 830 420 1110 1629 370 1020 508 760 1856 1400 2590 3110 2170 3980 1476 2690 1720 323 1170 1580 2970 2070 2700 4720 1060 2520 1700 1120 2160 1380 2640 3460 1290 200 1620 2140 1570 1910 1220 2650 170 16 30 370 2060 1300 2760 900 1830 1170 1550 212 _ 1026 20 VA 150 E _ 20 1110 560 14 0 800 2050 510 1270 22 190 2340 NOTE INCREASE DISTANCE 0 FOR EACH 10 ABOVE O C FOR EACH 20 ABOVE 32 ENGINE LIMITS FOR TAKE OFF 3000 54 IN HG CLIMB DATA FERRY MISSIONS USE 2300 RPM A 3 10000 FT ALT Web TYPE OF LIT e _3500 25000 Hat 35000 CLIMB TIME FUEL TIME FUEL BEST BEST FUEL CHANGE IN LBS FROM S L FROM S L FT MIN FROM S L FROM Si LAS FT MIN FROM S L FROM S L FT MIN FROM S L FROM S L 3210 155 2500 de COMBAT 185 2800 2 160 2600 ay ass 71 ta 90 160 1300 200 38 1100 185 806 COMBAT 185 5 55 0200 7 5 c0 19 600 FERRY HOO 18 70 155 RO NOTE INCREASED ELAPSED CLIMBING TIME 5 FOR EACH 10 C ABOVE C FREE AIR TEMPERATURE 5 FOR EACH 20 ABOVE 32 FUEL INCLUD
16. 20 Check fuel quantity figure 7 16 21 PUSH button figure 7 12 to test turbo warn ing lights 22 Carburetor air filters figure 4 8 or behind pilot s seat AS REQUIRED NOTE The use of carburetor air filters reduces the critical altitude and range of the airplane and should be avoided in clear air 23 Set clock and altimeter b SPECIAL CHECK FOR NIGHT FLYING Test operate 1 Landing lights figure 6 7 Not more than 5 seconds for test 2 Recognition lights figure 5 13 Not more than 30 seconds on ground 3 Cockpit lights figure 6 11 4 Fluorescent lights figure 6 5 5 Position lights figure 6 6 6 Spot light figure 4 1 4 FUEL SYSTEM MANAGEMENT a NORMAL USE 1 Warm up take off and fly for the first 15 min utes on RESERVE tanks This is to allow space in the reserve tanks for the vapor return from the carburetors Switch both engines to the Jett drop tank until almost RESTRICTED 23 RESTRICTED No 01 75FF 1 1 Return the mixture control to CUTOFF if the gine does not continue to run 1 STOP THE ENGINE IF OIL PRESSURE DOES NOT REGISTER WITHIN 30 SECONDS k Start the right hand engine in the same manner Turn generator switch figure 6 16 ON m Lock the primer pump DOWN 4 Battery switch figure 6 15 ON before discon necting the battery cart NOTE If battery power is not sufhcient for starting use the inertia starter hand crank
17. 24 oblique right __ p e obique lett Pilot I certify that the above cameras have been installed in aircraft No under my supervision this date Magazine taken up five 5 exposures and are ready for use Photographer Photographer 48 RESTRICTED Appendix BRITISH Weak mixture Port Flatten out Dinghy Boost pressure Mooring guy Picketing rings Crankcase sump Centre section plane Outer plane Rod aerial Radio track beacon Starboard Filter Tail plane Fin Engine speed indicator revolution counter Take off run Valve Cock Tare All up weight Windscreen Main plane RESTRICTED No 01 75FF 1 APPENDIX GLOSSARY OF NOMENCLATURE S A BRITISH AMERICAN Lean mixture Left Level off Life raft Manifold pressure Mooring line Mooring rings Oil pan Panel center wing Panel outboard Radio mast Radio range beacon Right Screen oil Stabilizer horizontal Stabilizer vertical Tachometer Take off distance Tube radio Valve fuel or oil Weight empty Weight gross Windshield Wing BRITISH Pressure reservoir Air cleaner Aerofoil Aerial Electrical accumulator Cloud height Non return valve Pilot controller set Track angle Stalling speed Jack hydraulic Drift angle Tail unit Signal star signal projecticle Fuel contents gauge Petrol or fuel Dynamo Earth Artificial horizon Course Air speed indicator reading Alighting gear under
18. 3 to 7 0 megacycles 7 0 to 9 1 megacycles Receiver Frequencies 190 to 550 kilocycles 3to 6 megacycles 6to 9 1 megacycles Figure 22 SCR 274N Radio Controls i RO a me METTE Main power switch receivers 4 y Tel plug in B jack CHE it Radio range filter switch zu Headset jack 10 Emission selector switch 11 Main power switch transmitter 12 Transmitter selector switch 13 Microphone jack stowed 14 Headset extension cord jack stowed 6 15 Transmitter key 1 a 2 Headset selector switches 3 Surface controls lock I us 4 4 Recognition light switch box aras 5 Volume controls 6 Tuning cranks m d 8 9 The receivers may be tuned in flight the transmitters are pre tuned to the proper frequency on the ground 1 Receiving a Plug the headphones into the jack JK 26 figure 22 14 which is in turn plugged into the bot tom of the filter box figure 22 9 b Determine the frequency to be used and turn the main power switch figure 22 1 for that receiver to 40 RESTRICTED Section V Paragraph 1 qum 9 REMOVE T Contactor in out switch Clock winding knob Clock stop run switch Clock indicator AWN figure 23 6 should be obtained from the Communica tions Officer 6 To stop the equipment turn all switches OFF
19. 5 FLIGHT OPERATION INSTRUCTION CHART P 38J AND F 5B EXTERNAL LOAD ee 6 e Ee seess amp OR RA m ai SINGLE ENGINE OPERATION O EAP BROPELL R MASA Jade EE SES akar EXTERNAL TANK SUPPORTS ONLY BLOWER peng pagan a well a 3000 se Jar as 32 _ 151 1710 89 RH AND 1710 91 LH mE NO WIND ALTERNATE CRUISING CONDITIONS NO RESERVE FUEL ALLOWANCE RANGE IN AIR MILES INSTRUCTIONS FOR USING CHART Select figure in fuel column equal to except emergency B Columns 11 111 IV amp toward the right pro or less than total amount of fuel in airplane Move horizontally to the right gressively give increase in range at sacrifice in speed Manifold Pressure or left and select a figure equal to or greater than the air miles to be Gallons Per Hour G P H are approximate maximum values for flown Vertically below and opposite desired cruising altitude read op reference D For quick reference take off and military power data are listed timum cruising conditions NOTES A Avoid continuous cruising in Column in the upper left corner of chart TURE i M INDICATED ALTITUDE CORRECTED FOR FREE AIR TEMPERATURE A Indicat
20. 9 oe Ted ET 09 YULI 3412524 YUE WOT aded ainssaid jan dumnd Zururmd 301403 durd oni 7 GI 5 T x x 1648 0101 ang 8138 sun uonn rp janj usatip sursuy 4 011 142 169 SZE JO 1 9 yes 97 sor apqgddoadqq JUJA 3412524 HINS pu YUL 09944194 528558 jenadwj LL e3 6 SADECE TUBA MURI SA E 10123 98 IY v6 ANY 6 383619914 OL A35 Figure 9A Simplified Fuel System Diagram Ad Saur 3U3A Yue ong noy 124 44 saur 70 91155214 Jang 5207 1 unig IUIdUy SQUTT 2158214 1204 58011 jang TO LR SYSTEM No 01 75FF 1 RESTRICTED T O Section 3452 10 ON 01 0312191539 Landing gear control valve System pressure regulator Hydraulic pressure accumulator Vent to atmosphere Main reservoir drain Emergency hand pump To flap system see figure 13 Main hydraulic reservoir Engine driven pump Hydraulic fluid filter To landing gear see figure 13 Ta 8 d 10 11 To coolant flaps see figure 16 Hydraulic pressure gage Ground test connection Check valve To right h
21. CHART 5 P 38J EXTERNAL LOAD ITEMS N ISO GALLON TANKS 8 INSTRUCTIONS FOR USING CHART Select figure fuel column equal to except in emergency B Columns IV amp V toward the right pro E or less than tatal amount of tuel in airplane Move horizontally to the right gressively give increase in range ot sacrifice in speed Manifold Pressure or left and select a figure equal to or greater than the air miles to be M P Gallons Per Hour G P H are approximate maximum values for flown Vertically below and opposite desired cruising altitude read op reference D For quick reference take off ond military power data ore listed timum cruising conditions NOTES A Avoid continuous cruising in Column in the upper left corner of chart NO RESERVE FUEL ALLOWANCE LAE M E MAX RANGE TAKE OFF d 830 790 1070 950 00 9 2 2 m E T d 2200 7000 18300 1 2300 243 KL 183 950 228 1600 2250 31 te 1900 291 a 1600 2200 247 3 35 LRS 22 15000 2 L INDICATED ALTITUDE CORRECTED FOR FREE AIR TEMPERATURE LAS Indicated Air Speed E ALLOw 50 ut GALS _IMP GALS FOR WARM UP M P Manifold Prexure In TAKE OFF AND CLIMB el 1 _ FEET ALTITUDE U 5 G P H U 5 Gollom Per Hour N RETURN FUEL FLOWS TO TAN SERVES 1 E USE FUEL FROM TANKS IN THE FOLLOWING ORDE kis
22. FOR ADDITIONAL ENGINE DATA RED FIGURES ARE PRELIMINARY SUBJECT TO REVISON AFTER FLIGHT CHECK SPEC le LAS MIX Trp 1512 TR TURE lt 2912181538 55 xipueddy 1336410 ON 041 003 38 EXTERNAL LOAD ITEMS 75 0800 except in emergency Columns 11 IN amp toward the right pro gressively give increase in range sacrifice in speed Manifold Pressure M P Gallons Per are approximate maximum volver for reference D For quick reference take off and military power dato are listed in the upper left corner of chart RESERVE FUEL ALLOWANCE Iv RANGE IN AIR MILES STATUTE MI Ee Hg POUNDS LAS M TURE FLIGHT OPERATION INSTRUCTION CHART e e e B WE eg ag m W s b s Swiss sn X a Bo BB spe ps Wo INSTRUCTIONS FOR USING CHART Select figure in fuel column equal to or less than total amount of fuel in airplane Move horizontally to the right or left and select a figure equal to greater than the air miles to be flown Vertically below ond opposite desired cruising altitude read op timum cruising conditions NOTES Avoid contimvous cruising in Column RANGE IN MILES STAT
23. Flaps 100 extended 2 150 mph 2 AIRSPEED AND ALTIMETER CORRECTION Airplane Airplane Calibrated A S LA Sa Gear L A S Gear and and Flaps Flaps DOWN Sea Level 110 L130 100 125 90 4 115 4 70 100 50 60 0 0 80 110 130 70 160 230 210 290 260 360 325 450 340 400 540 Includes Installation Errors only Does not include Instrument Errors as obtained by the C 1 Field Test Set RESTRICTED 994295 1 343452 10 ON 04 10312131533 AIRPLANE MODELS SPECIFIC ENGINE ENGINE MODELS 38 __ FLIGHT CHART TIBOR 0 NORMAL RATED geg Lg H Ett 0 5 08 im m md elu nos didi 80 9 08 MIN SPECIFIC V S QT HR FUEL oiL COOLANT 0 0 TM MAX PERMISSIBLE DIVING RPM 3120 18 50 IN 18 50 IN 96 COND IT10N ALLOWABLE 011 CONSUMPTION _12 55 uo 104 85 IDLING OIL GRADE S 1120 1120 SUPERCHARGER TYPE EXHAUST ORIVEN TURBINE FUEL GRADE OCTANE ape MANIFOLD CRITICAL ALTITUDE _ ITICAL ALTITUDE MIXTURE FUEL FLOW IMUM ING i TH CONDITION PRESSURE BLOWER CONTROL 8005 WITH KAM NO RAM POSITION INUTES AUTO WAR AUTO DURING WAR vum CARS EAR m III NO LIMIT
24. MAX MUM CRUISE pu SEA LEVEL MINIMUM SPECIFIC INO LIMIT CONSUMPTION 20000 30000 REMARKS NEVER EXCEED THE FOLLOWING MANIFOLD PRESSURES ALTITUDE AT THE ALTITUDES SHOWN REGAROLESS OF ENGINE RPM UP 15 000 AIRPLANES WITH TYPE B 13 SUPERCHARGERS So AIRPLANES WITH TYPE B 33 SUPERCHARGERS 30 000 35 000 40 000 23 30 j 29 K 35 0 NORMAL RATED 26000 AUTO pep RICH AUTO GE 9315141534 1 446 10 ON OL 93415141533 99295 MAXIMUM DURATION MINUTES ENGINE MODELS FUEL FLOW GAL HR ENG MIXTURE CONTROL POSITION SPECIFIC ENGINE FLIGHT CHART amp BON W BP ee 9 P d E d PB s s USE LOW BLOWER BELOW 4 ps gg m m es ep gp m kh ps UP 25000 38000 6O so a lt 55 11 TARY POWER OR LESS AIRPLANE MODELS FORM 5 512 U Lu 00 lt 8 DEC 18 1942 CONDITION PRESSURE PRESSURE LB SQ IN 18 39 IN MANIFOLD PRESSURE BOOST OPERATING CONDITION 1425 MAXIMUM CONTINUOUS MINIMUM SPECIFIC CONSUMPTION ALTITUDE WAR EMERGENCY POWER MAXIMUM CRUISE 312141534 Section IV Paragraph 1 a Check coolant override
25. TAKE OFF IF LANDING IS NOT COMPLETED 1 Open throttles to take off stop and after pro peller rpm has stabilized push propeller pitch control forward to take off position CAUTION Pull the airplane up in a climb sufficient to stay below 150 mph indicated airspeed until the flaps are retracted 2 Retract flaps and proceed in take off tech nique as outlined in paragraph Section II paragraph 9 RESTRICTED 29 Section Ill Paragraph 1 2 Maximum allowable airspeed indicated Flaps 50 extended Landing light extended 140 mph 300 gal droppable tanks installed 250 mph Subtract from altimeter reading 31 400 4 430 L420 380 300 190 0 50000 270 4 265 4 250 4 190 4 130 0 230 330 430 550 20000 200 195 4 179 140 20 0 160 250 379 400 2500 620 730 Add to altimeter reading RESTRICTED No 01 75 1 Condition TABLE ALTIMETER INSTALLATION ERRORS Feet Gear and Flaps UP 10000 x 7 g IM 2 1 A d l 1 EV pt Hi 1 1 AIRSPEED LIMITATIONS Condition Maximum allowable airspeed indicated DIRE Lu one kee EE ER cmm m oi See Placard Section 11 paragraph 17 Landing gear extended TT 175 mph
26. be attempted at altitudes below 10 000 feet 2 BEFORE ENTERING THE COCKPIT Check the loading of the airplane with the ap plicable weight and balance chart in Appendix II Determine the approximate take off weight and the center of gravity position WARNING Dangerous instability exists when the center of gravity 15 aft of 32 mac 32 gear up RESTRICTED 21 RESTRICTED 01 75 1 Figure 20 Hatch Controls Extertor hatch release Left latch release Left latch handle locked position Emergency hatch release Glare shield 6 Right latch handle unlocked position Cockpit heat control 8 Right latch release 9 Exterior hatch release V d 4 Propeller pitch control figure 4 4 INC RPM Full forward 7 Propeller selector switches figure 4 5 AUTO CONSTANT SPEED 8 PUSH propeller circuit breakers figure 4 9 9 Propeller feathering switches figure 4 13 NORMAL 10 Mixture figure 4 6 CUTOFF 11 cooler flap switches figure 6 17 AUTO MATIC 12 Generator switch figure 6 16 OFF until engines are started 13 Battery switch hgure 6 15 OFF if battery cart is used ON if cart is not used 14 Coolant flap override switches figure 6 13 OFF 15 Intercooler flaps figure 6 12 CLOSED If installed 16 Check gunsight light figure 6 10 operation and adjust the seat so that the sight reflection is easily vis
27. breathing d Failure of the automatic supply will be indi cated by failure of the flow indicator figure 25 1 re adjustment of the mask does not restore the flow turn the emergency knob figure 25 4 and the auto mix lever OFF This will supply a constant stream of oxygen to the mask regardless of the breathing re quirements RESTRICTED Section V Paragraph 2 MN 26Y RADIO COMPASS This radio compass may be temporarily installed in airplanes serial 42 67702 and up when they leave the factory The compass is intended for use during the ferry flights and may be removed in combat zones 1 GENERAL a The master control switch marked OFF COMP REC ANT and REC LOOP controls all radio compass equipment functions other chan tuning and adjustment of signal level b The COMP setting is used for obtaining com munications reception visual on course indication of homing and bearings The REC ANT setting is used for communi cation and aural radio range reception d The REC LOOP setting 15 used for obtaining communications reception during conditions of severe rain and snow static aural radio range reception aural null bearings and aural null homing from communica tion stations e The OFF setting opens all current consuming circuits thus rendering the equipment inoperative f The azimuth control warning light operates at all times when the equipment is in use except when the a
28. checked and is in proper working order 2 After take off set the ON OFF switch figure 23 3 to 3 Set the six position switch figure 23 1 to the position specified by the Communications Officer in Charge In the absence of specific information set to 172 4 Set the band switches figure 23 7 as directed by the Communications Officer 5 Details concerning the use of the EMER GENCY switch figure 23 2 and destructor buttons RESTRICTED 41 RESTRICTED No 01 75 1 2 OPERATION OF THE OXYGEN EQUIPMENT a 400 to 450 lb sq in is full pressure in the three bottles This supply is sufficient to last approximately 1234 hours at 15000 feet 9 hours at 20000 feet 7 hours at 25000 feet or 614 hours at 30000 feet if properly used b Fit the demand type mask snugly to the face and test the fit by pinching the tube and sucking lightly The mask should collapse Clip the mask tube to the clothing allowing for all necessary head movement without pulling the mask away from the face WARNING It must be remembered that the suction of breathing is used to open the oxygen valve and that any leakage in the mask will cause this valve to become inoperative and will stop the flow of oxygen c Check the auto mix lever figure 25 3 and the emergency knob figure 25 4 OFF Under these conditions a correct oxygen air mixture will be sup plied ai altitude as required by normal
29. en gine speed increases d DEC RPM Propeller pitch increases gine speed decreases 3 PROPELLER CIRCUIT BREAKERS Open and the propeller pitch changing mechanism 15 inopera tive when the current required to operate the propellers becomes too high When the circuit breakers open the buttons figure 4 9 pop up disclosing a red and white band on the buttons They may be reset by pushing the buttons after allowing approximately 15 seconds for the switches to cool Only the black portion of the buttons is visible when the circuit breakers are properly set 4 FEATHERING SWITCHES figure 4 13 turn the propellers to their minimum drag position 5 WARNING LIGHTS figure 4 7 are installed on P 38H only They indicate when the propeller cir cuits are not properly set for take off and landing 1 when the circuit breakers are open or the selector switches are not set to AUTO CONSTANT SPEED These lights however do not warn of an improperly set propeller pitch control 6 VERNIER KNOB figure 4 18 provides for fine adjustment of the right hand propeller pitch con trol when synchronizing the engines 7 FRICTION CONTROL figure 4 19 may be adjusted to prevent the throttles and propeller pitch con trols from vibrating out of position 4 CARBURETOR AIR FILTER CONTROLS 1 This control 15 located behind the pilot seat on early airplanes On airplanes serial 42 67702 and up this control is located on th
30. into the number of gallons available for cruising as determined in para graph 2 above This will give the calculated flight dura tion in hours which can then be converted into hours and minutes and deducted from the desired arrival time at destination in order to obtain the take off time with out consideration for wind To allow for wind deter mine the calculated ground speed by dividing the flight duration in hours into the range selected in paragraph 3 and calculate a new corrected ground speed with the aid of a navigator s triangle of velocities 5 The airplane and engine operating values listed below Operating Data in any column except 1 are calculated to give constant miles per gallon at any altitude listed Therefore the airplane may be operated at any altitude and at the corresponding set of values given so long as they are in the same column listing the range desired ht h Dee 1 FLIGHT PLANNING The following outline may be used as a guide to assist personnel in the use of the FLIGHT OPERATION IN STRUCTION CHART for flight planning purposes a If the flight plan calls for a continuous flight where the desired cruising power and air speed are reasonably constant after take off and climb to 5 000 feet the fuel required and flight time may be computed as a single section flight 1 Within the limits of the airplane the fuel re quired and flying time for a given mission depend large ly
31. re quiring changes in power speed or gross load in ac cordance with GR WT increments shown in the series of FLIGHT OPERATION INSTRUCTION CHARTS provided the total flight should be broken down into a Series of individual short flights each com puted as outlined in paragraph in its entirety and then added together to make up the total flight and its re quirements CAUTION Ranges listed in column I under Cont Power are correct only at the altitude given in footnote 1 6 The flight plan may be readily changed at any time enroute and the chart will show the balance of range at various cruising powers by following the In structions for Using Chart printed on each page 7 In using the FLIGHT OPERATION IN STRUCTION CHARTS set the propeller pitch control WHAT WAS THAT 52 RESTRICTED 3 6 10 ON 01 0312141534 I AIRPLANE MODELS m ENGINE MODELS TAKE OFF CLIMB amp LANDING CHART a eg e e ge s ge P BP P bh 8 B b B 4 B B ee b Hee w m e au w gg pe geg e e B P B a pr 5 a B a m mama wow B B oW P eh ee es a TAKE OFF DISTANCE in reen HARD SURFACE RUNWAY SOD TURF RUNWAY GROSS
32. switches figure 6 13 OFF 5 Flap control figure 5 2 MANEUVER DOWN c Source selector valve handle figure 14 4 UP This 15 the normal position d Operate the hand pump figure 14 2 until the desired flap extension is obtained 2 If the above system fails to extend the flaps leave the control at DOWN while extending the land ing gear Oil from the return side of the landing gear cylinders may fill the system enough to cause the flaps Operate EMERGENCY OPERATION OF THE LANDING GEAR 1 Operate the hand pump figure 14 2 with all controls in the normal position for gear extension Check Coolant override switch OFF NOTE Nose gear door must open and nose gear must unlock before any pressure may flow to the main gear door cylinders RESTRICTED No 01 75 1 1 HYDRAULIC FAILURE a If the gear does not extend when the lever is put down return the lever to UP and attempt to extend the flaps using the auxiliary system NOTE The auxiliary system should be used for flap extension because in some cases there may not be sutficient fluid to extend both gear and flaps and the gear may be extended with the emer gency system fluid CAUTION If one engine has failed in addition to the hydraulic system failure remember that the airplane cannot maintain level flight on one engine with gear and flaps extended Under these conditions it may be desirable to land with flaps UP
33. to retract the gear on the ground due to engine failure at take off it may be released by ro tating the landing gear control release knob figure 4 33 in a counter clockwise direction The landing gear position is indicated on the instrument panel figure 7 19 A warning horn and light figure 4 17 are pro vided which operate when either throttle is closed if the gear is not down and locked P 38 and F 5B airplanes are not equipped with the warning horn 6 FLAP CONTROL See figure 13 a Flap action is controlled by the lever figure 5 2 on the right hand side of the cockpit and flap position is indicated on the instrument panel figure 7 19 When the lever is placed to UP or DOWN the flaps will auto 4 RESTRICTED Section RESTRICTED No O1 75FF 1 Recogniuon light switches Detrola receiver tuning knob Detrola receiver volume control Pilot s relief tube Rudder trim tab control Rudder pedal adjustment lever 1 5 14 15 16 17 18 Frequency selector push buttons Selector lock lever Selector switch Surface controls lock stowed Recognition light keying switch Cockpit light 7 8 9 10 11 12 Figure 5 Cockpit Right hand Side RESTRICTED Aileron tab control Flap control lever Cockpit heat control Surface controls lock guide angle Radio OFF push button Indicator light dimming lever ms I4 Section RESTRICTED No 01 75
34. upon the speed desired With all other factors re maining equal in an airplane speed is obtained at a sacrifice of range and range is obtained at a sacrifice of speed The speed is usually determined after considering the urgency of the flight plotted against the range re quired The time of take off is adjusted so as to have the flight arrive at its destination at the predetermined time Fuel should be used in the following sequence 1 Reserve tanks for first 15 minutes 2 External tanks 3 Main tanks 4 Reserve tanks 2 Select the FLIGHT OPERATION INSTRUC TION CHART corresponding to the weight and ex ternal load items of the airplane Locate the largest fig ure entered under gph gallons per hour in column 1 on the lower half of the chart Multiply this figure by the number and or fraction of hours desired for reserve fuel Add the resulting figure to the number of gallons set forth in footnote No 2 and subtract the total from the amount of fuel in the airplane prior to starting the engines The figure obtained as a result of this compu tation will represent the amount of gasoline available and applicable for flight planning purposes on the RESTRICTED 51 RESTRICTED Appendix 01 75 1 to give the desired rpm and open the throttle to give the desired indicated air speed Use the manifold pressure only as an approximate value for reference b If the original flight plan calls for a mission
35. 0 feet Above 25000 feet turbo supercharger overspeed is 26 RESTRICTED Section Paragraph 13 17 d The stall should be practiced so the pilot may know the feel of the controls near the stall and the indicated stalling speed of the airplane 15 SPINS Deliberate spinning 15 prohibited because the spin tends to flatten out after two or three turns When this occurs the controls are forced back and engine power must be used to help get the wheel forward Before flattening out normal recovery may be made without power Recovery is made by easing the wheel forward and applying full opposite rudder 16 ACROBATICS Although such maneuvers as loops Immelmanns and rolls are permitted with this airplane the pilot is cautioned to exercise extreme care in acrobatic maneu vers which require a downward recovery In general acrobatics should be attempted at altitudes below 10000 feet until the pilot becomes familiar with the speed at which the airplane can gain and lose altitude DIVE il HER bm E HH Lagi Ch be Mop E LLLILLIAL IL EE 4 or BT 43882 We mug EID ana EZ Lo da 1 1 1 HEH CH tahoe ganpang 1185352215 HL LO ANEN HP 11111111111 11 1111 D i ES E HHH
36. 1 Su ur AT FESr Set ig 16 115 1147 1 Ignition master switch 11 Cockpit light rheostat 2 dilution switches 2 Intercooler flap switches P 38 and F 5B 3 Starter switch Circuit not in use on 38 4 Engage switch 13 Coolant flap override switches 5 Fluorescent light switch 14 Pitot heat switch 6 Position light switches 15 Battery switch 7 Landing light switches left hand 16 Generator switch only on P 33 and 5 8 Voltmeter 9 Inverter switch P 38H 10 Gun sight light rheostat 17 Oil cooler flap switches 15 Ignition switch 19 Inverter warning light P 38H Figure 6 Main Switch Box RESTRICTED Section Paragraph 8 9 the switch es ON the lights extend and turn on P 38H airplanes with the switches OFF the lights turn off but remain extended On 38 and F 5B airplanes with the switch OFF the lights remain ON and the lights remain extended Never fly above 140 MPH un less the landing light switches are in the RETRACT position 2 RECOGNITION LIGHTS One or two white upward and three red green and amber down ward lights are controlled by switches on the right hand side of the cockpit To operate turn the selector switches figure 5 13 to STEADY or turn the selector switches to KEY and press the keying switch button figure 5 11 CAUTION It 15 possible to burn the plastic lenses of the down
37. 70 260 250 240 230 225 215 205 195 190 355 345 335 325 315 310 300 290 280 270 260 250 240 230 225 215 205 380 370 360 350 340 330 320 310 300 290 280 270 260 250 240 230 220 To determine intervalometer setting 1 Find airplanes altimeter reading in left hand side of table 2 Follow down to first indicated airspeed higher than airplane s airspeed 3 Follow across horizontal to intervalometer setting below distance above the ground Time intervals marked are too short for runaway operation with K 17 camera Time intervals marked 1 are too short for runaway operation with K 18 camera Figure 30 Intervalometer Setting 60 Over Lap PHOTOGRAPHIC DATA SHEET A PHOTOGRAPHIC DATA SHEET B C Diaphragm setting o o ooo l Dark slide removed 2 Weather conditions 2 Cameras properly secured in airplane 3 Altitude true 3 Shutter tested 4 Exposures made 4 Shutter speed Set properly 5 Approximate time A Filter used 6 Area covered 6 Lens tight 7 Magazine properly seated 8 Camera operations checked on Intervalometer and on Manual Switches 9 lights and warning lights checked 10 Daylight loading trailer wound off supply spool 11 Lamera windows clean 12 Cameras used A Camera Serial No B Magazine Serial No a 6 vertical b 24 vertical 12 vertical d 6 oblique righe e G oblique left f
38. All dittances average and iubject to considerable variation because af differences in pilot technique load C G ete REO FIGURES HAVE NOT SEEM FLIGHT CHECKED 9315141534 ES xipueddy 13454 10 ON 041 93121415384 AIRPLANE MODELS ENGINE MODELS 38 TAKE OFF CLIMB 8 LANDING CHART 17 0 89 RH 4 m TAKE OFF DISTANCE IN FEET SOD TURF RUNWAY HARD SURFACE RUNWAY GROSS SOFT SURFACE RUNWAY WEIGHT AT SEA LEVEL AT 6 000 FT AT SEA LEVEL AT 3 000 FT AT 6 000 3 000 FT 6 000 FT IN LBS TO CLEAR TO CLEAR GROUND TO CLEAR GROUND TO GROUND TO CLEAR GROUND TO CLEAR TO CLEAN GROUND GROUND TO CLEAR 50 OBJ 50 OBJ PUN RUN 50 OBJ RUN 50 OBJ RUN 50 OBJ 50 OBJ RUN 50 QBJ RUN 50 1850 2010 1 90 3 1100 DOEN 1990 262 1010 2255 700 2870 1300 850 1620 1087 2040 1350 1650 1140 2110 Ze 140 90 226 1300 2330 960 870 1230 740 1550 MEL 10 800 1280 ep LEUL 1060 SAC 1390 309 1790 290 Fut Junt 0 200 865 320 Ga LOAC 240 TOO an 980 PANG 1280 jt Ux 7254 LES 4908 2235 1490 97 1920 139 Duo 1706 2979 2250 384 2080 1400 2720 300 1 ROO 110 2160 1500 28130 1020 1960 1300 2400 1760 0
39. ES WARM UP AND TAKE OFF ALLOWANCE LANDING DISTANCE Feer FIRM DRY SOD WET OR SLIPPERY SEA LEVEL 3 000 AT SEA LEVEL 3 000 FT 6 000 FT AT SEA LEVEL 3 000 FT 6 000 FT IN LBS TO CLEAR GROUND TO CLEAR GROUND TO CLEAR GROUND TO CLEAR GROUND TO CLEAR GROUND TO CLEAR GROUND cua rouno TO Citar GROUND TO GROUND 50 ROLL 50 OBJ 50 50 OLJ ROLL 50 OBJ ROLL 50 OBJ ROLL 50 OBJ ROLL 50 083 ROLL k 50 De ROLL 13 500 2510 1920 1440 1580 2860 1470 2900 1610 3170 1760 4520 E 15 500 2800 1480 1620 3360 2970 1850 3250 1820 3550 1990 5100 378 4130 610 NOTE FOR GROUND TEMPERATURES ABOVE 35 C 95 F INCREASE APPROACH 1 5 10 AND ALLOW 20 INCREASE IN GROUND ROLL REMARKS FOR COMBAT CLIMB USE 3000 RPM AND 54 IN HG 25 000 FT THEN GRADUALLY REDUCE SAWANG PRESS TO 45 5 IN HG AT 30 000 FT AND TO 37 IN HG 35 000 1 5 Indicated Air NOTE dutances arg amp aroge ond te contiderable varigtions becouse of diflerences in pilot technique load CG etc vS 0312131533 1 448710 ON O 1 03131801538 xipueddy EXTERNAL LOAD ITEMS TANK SUPPORTS ONLY POU
40. IO 1 Plug the headphones and microphones into the jack figure 14 5 2 Check the generator switch figure 6 16 and the battery switch figure 6 15 3 Set the selector switch figure 5 9 to REM The T and R positions of this switch are not to be used 4 Push the A C or D button figure 5 7 de pending on which pre tuned frequency is to be used and wait about one minute for warm up Lights beside each button indicate which button has been pushed The lever figure 5 G beside the OFF button may be used to dim the indicator lights 5 Press the microphone button in the center of the control wheel and speak slowly and clearly 6 Release the microphone button to receive RESTRICTED RESTRICTED No 01 75 1 MCW or to CW depending on the type of reception desired For normal reception set the range selector switch figure 22 8 to BOTH To receive radio range without voice interference set the selector switch to RANGE To eliminate radio range interference from a station broadcasting range and voice signals on the same frequency set the selector switch to VOICE 4 Note which jack A or the TEL plug figure 22 7 is in and turn the headset selector switch figure 22 2 of the receiver being used to the corres ponding position A or B e Adjust the volume figure 22 5 to obtain a light frying noise and tune in the desired station using the crank figure 22 6 NOTE Two
41. NDS except im emergency Columns 11 amp V toward the right pro gressively give increase in range at sacrifice in speed Manifold Pressura NPL Gallons Per Hour approximate maximum valves for reference 0 For quick reference take off and military power data listed m the upper left corner of chart NO RESERVE FUEL ALLOWANCE RANGE RANGE IN AIR MILES _ NAUTICA 720 670 350 280 218 1 5 Indicated Air Speed A R Auto Rich M P Manifold Pressure 1 la Auto Lean US GPAH U 5 Gallons Per Hour FT Full Throttle 5 1 Saa Laval SHEETS INSTRUCTIONS FOR USING CHART Select figure in fuel column equal to or less than total amount of fuel in airplane Move horizontally to the right or left and select figure equal to or greater than the air miles to be flown Vertically below and opposite desired cruising altitude read op fimum cruising conditions NOTES A Avoid continuous cruising in RANGE IM AIR MILES 930 770 E at IM Hg FLIGHT OPERATION INSTRUCTION CHART INDICATED ALTITUDE CORRECTED FOR FREE AIR TEMPERATURE 40 0 6 5 __ IMP GALS FOR WARM UP TAKE OFF AND CLIMB TOD 000 FEET ALTITUDE RETURN FUEL FLOWS USE FUEL FROM TANKS IN THE FOLLOWING ORDER TO SPECIFIC ENGINE FLIGHT CHART
42. ON OF THE CAMERA EQUIPMENT F 5B only a the cameras are installed in the fuselage nose which is divided into three camera compartments The forward compartment accomodates one 6 K 17 chart camera The center compartment will accomodate two 6 K 17 chart cameras or one 12 or 24 K 17 recon naissance camera The aft compartment accommodates two 24 K 17 or one 24 K 18 reconnaissance cameras b CAMERA OPERATION for pilot 1 Before take off the pilot should determine which cameras are installed and that the airplane is properly balanced THIS IS IMPORTANT see Sec tion II paragraph 2a Section V Paragraph 4 5 i i Emergency hatch release T A 2 Gun sight dark glass 3 Bullet proof glass 4 Reflecting glass GL Se 5 Glare shield LEA Later airplanes will be rearranged with the bullet proof glass forming the front windshield surface and a new type gunsight operating on the same principle mounted on the glass 4 OPERATION OF THE A 4 AUTOMATIC PILOT F 5B only a During warm up 1 Check vacuum figure 7 10 4 or 5 Hg 2 Check auto pilot oil pressure figure 28 10 125 16 59 in 3 Uncage the bank and climb unit figure 27 5 4 Match the directional gyro cards and uncage the directional gyro figure 27 6 5 Turn the automatic pilot control valve figure 27 10 ON 6 Turn the course setting knob figure 27 4 the elevator trim knob fi
43. P 38H only Carburetor air filcer control airplane 42 67702 and up control not used on earlier airplanes Propeller circuit breaker buttons Gun charger handle lenition Switches Cannon trigger button Machine gun button on forward side of wheel RESTRICTED 9 10 11 12 RESTRICTED No O1 75FF 1 matically stop at their end position The lever should be returned to CLOSED as soon as the end position 15 reached The control will not go to the down position until the trigger on the lever is lifted through the notch just forward of the closed position NOTE When using maneuvering flaps the flap lever must be left in the maneuver position If it 15 moved even slightly forward and then returned to maneuver the flaps will extend completely This condition is corrected on airplanes 42 66750 and up 7 HYDRAULIC SYSTEM See figure 11 a Normal system pressure figure 7 11 is between 1200 and 1350 16 59 in See Section IV paragraph 1 for emergency operation in case of failure of the system There are three separate systems of operation for the hydraulic equipment in this airplane 1 The normal system operates all the hydraulic equipment except brakes using power from the engine driven pumps and fluid from the TOP half of the main hydraulic reservoir 2 The auxiliary system operates the same equip ment and uses the same lines as the normal system It functions exactly like the nor
44. RESTRICTED NO 01 75FF 1 DIST 4 5 7 8 FILE BEGH PILOT S FLIGHT OPERATING INSTRUCTIONS FOR ARMY MODELS P 38H Series 38 5 and F 5B 1 NOTE This Technical Order replaces 01 75FF 1 dated June 25 1943 This publication shall not be carried in aircraft on combat missions or when there is reasonable chance of its falling into the hands of the enemy NOTICE This document contains information affecting the National Defense of the United States within the meaning of the Espionage Act 50 8 and 32 as amended Its transmission ar the revelation of its con tents in any manner to unauthorized person is prohibited by law MARSHALL WHITE CHICAGO SEPTEMBER 25 1943 RESTRICTED 01 75 1 Published by authority of the Commanding General Army Forces THIS PUBLICATION MAY BE USED BY PERSONNEL RENDERING SERVICE TO THE UNITED STATES OR ITS ALLIES Paragraph 5 4 of Army Regulation 380 5 relative to the handling of in Government work but will not be communicated to the public or to the restricted printed matter ts quoted below press except by authorized military public relations agencies d Dissemination of restricted matter The information contained in This permits the issue of restricted publications to civilian contract and restricted documents and the essential characteristics of restricted material other accredited schools engaged in training pe
45. UTE NAUTICAL in 1120 1020 1850 930 830 730 P k lead 630 530 430 330 240 OPERATING DATA mm 2300 200 SPEC 8 DEC 18 1982 er M 195 AL 295 kk 195 1 4 5 Indicated Air Speed MP Manifold Pressure US GPH U Gallons Par Hour LE Auto Rich A L Auto Lean F T Full Throttle L Sas Level 2300 935 A L 230 ah 240 246 245 2300 32 133 32 128 32 115 INDICATED ALTITUDE CORRECTED FOR FREE AIR TEMPERATURE ALLOW GALS IMP GALS FOR WARM UP TAKE OFF AND CLIME 5 000 ALTITUDE RETURN FUEL FLOWS TO USE FUEL FROM TANKS IN THE FOLLOWING ORDE REE TO SPECIFIC ENGINE FLIGHT CHART FOR ADDITIONAL ENGINE OPERATION DATA RED FIGURES ARE PRELIMINARY SUBJECT TO REVISION AFTER FLIGHT CHECK 03121031 1 449 10 ON 1 0313181538 Xipueddy FLIGHT OPERATI IN TI CHART EXTERNAL LOAD ITEMS 300 GALLON TANKS d Se PF Po o Ba pp ag ag B ar s 58 DEC 18 1952 SPEC ee eee ee POUNDS MIXTURE DURATION u s POSITION POSITION 1 MIM G P H INSTRUCTIONS FOR USING CHART Select figure in fuel column equal to except in emergency B Columns 11
46. Y MIN FROM 54 FROM S L LA S FT MIN FROM S L FROM S L 54 NOTE INCREASED ELAPSED CLIMBING TIME 5 FOR EACH 10 d ABOVE D d FREE AIR TEMPERATURE 2 Ki FOR EACH 20 ABOVE 32 2 FUEL INCLUDES WARM UP AND TAKE OFF ALLOWANCE LANDING DISTANCE ow Feet _ GROSS HARD DRY SURFACE _ _ DRY SOD WET OR SLIPPERY WEIGHT AT SEA LEVEL 3 000 AT SEA LEVEL AT 3 000 FT SEA LEVEL 3 000 6000 FT T 5 rocas GROUND GROUND TO GROUND GROUND TO CLEAR CLEAR GRO CLEAR GROUND TOCLEAR GROUND TO CLEAR GROUND CLEAR 1 UN LBS 50 08 5008 e d Df gert oui 50708 seou ROLL 50008 ROLL 0 OBJ 13 500 100 2830 2730 1440 3000 1590 2680 1470 2000 1610 3170 1760 3330 ugio 3620 suo 15 500 105 2800 1820 3360 1790 2979 1550 3250 1820 3560 1990 5560 4130 451 0 NOTE FOR GROUND TEMPERATURES ABOVE 35 C 95 F INCREASE APPROACH 5 10 AND ALLOW 20 INCREASE IN GROUND ROLL ALT TUBE Heel 2 REMARKS COMBAT CLIMB USE 3000 RPM AND 54 IN 20 000 FEET REDUCE MANIFOLD PRES SURE AS FOLLOWS ABOVE 20 000 FEET STILL USING 3000 RPM WITH B 13 SUPERCHARGERS WITH TYPE 8 33 SUPERCHARGERS LA Indicated Air Speed NOTE
47. aggage compartment when the airplane leaves the factory 1 If extreme conditions are encountered ropes may be tied around the tail end of each boom and se cured to some solid anchor point RESTRICTED T O No 01 75FF 1 CROSS WIND LANDING 1 Same as the normal landing The tricycle gear reduces danger from landing in a reasonably strong cross wind If the drift seems excessive the up wind wing may be lowered until just before contact rh A Na m Z 124 Sas Hy 17 IF HEDA LANDED AT 85 INSTEAD OF 120 4 SINGLE ENGINE LANDING 1 The main differences between the single en gine landing and two engine landing are that the air plane can not maintain altitude in flying on one engine with both flaps and the landing gear fully extended and that directional control is impossible below 120 mph with one engine operating at more than 45 Hg and 3000 rpm Keep the airspeed above 120 mph until the landing is absolutely assured 2 Put the gear down first 3 When in a good position for a normal ap proach put the flaps only 1 down 4 Crank the rudder tabs back to zero and reg ulate the gliding angle by using the remaining flap travel and power from the live engine 5 When the approach is assured close the throttle put the flaps all the way down and proceed with a normal landing e
48. alues for flown Vertically below and opposite desired cruising altitude read op reference D For quick reference take off and military power dato ars listed timum cruising conditions NOTES Avoid continuous cruising in Column in the upper left corner of chart NO WIND ALTERNATE CRUISING CONDITIONS NO RESERVE FUEL ALLOWANCE MAX CONT POWER RANGE IN AIR MILES STATUTE 1 A 680 e Ow EN mm J p A Tu 0 3 d 2 1 1 2 H a d 1 BH B 1 A r 1 d 3 1 OPERATING DATA Tat am 30000 1800 50 1600 2100 264 AL 37 500 9 L 28 66 3000 1500 2050 266 2 Op 0 6 1600 INDICATED ALTITUDE CORRECTED FOR FREE AIR TEMPERATURE lA X Air Saeed alow DU US GALS IMP GALS FOR WARM UP M P Monifold Prowure In Hg TAKE OFF AND CLIMB 5000 ALTITUDE 0 5 6 5 Gallon Per How RETURN FUEL FLOWS TO RESERVES ONT T Full Thiol SERVE 5 TES RESERVES TOn DER USE FUEL FROM TANKS IN THE FOLLOWING ORDE os Weh FEIS TO SPECIFIC ENGIME PLIGHT CHART FOR ADOITIOMAL EMOIME OPERATION DATA A L Auto Lean RED FIGURES ARE PRELIMINARY SUBJECT TO REVISION AFTER FLIGHT CHECK 0312143153 65 E gt MODEL 5 FLIGHT OPERATION INSTRUCTION
49. and engine pump Flap control valve aes NE tes Pump Pressure Return ro Reservoir Pump Suction System Pressure Tank Drain or Vent cl 9315141534 RESTRICTED section No 01 75 1 FUSELAGE Main landing gear wheel and brake Yo left hand gear Brake cylinders Hydraulic fluid reservoirs Figure 12 Brake System Diagram RESTRICTED 13 Section RESTRICTED No 01 75 1 Landing Gear and Flap Hydraulic System Diagram E g 5 e M 2 2 8 8 5 gt ka e aD Ze 5 LA K sw 2 e OG VI ren kd So o c c ul 9 u uu BH A a o 4 O O ui 14 RESTRICTED 15 RESTRICTED 9 Radio jack Right hand window crank 8 e Gel La E QJ K E Ve c o 4 yeh a c Sal Emergency bypass valve Source selector valve Radio jack stowed position 1 Seat adjustment release handle Window ratchet 2 Hand pump handle 3 4 5 110410591 21 n EJpAt 831 0018031083 403871307323 duind pure 4 0337 uonisod
50. aps and gear down there appears to be a slight tendency for onc wing to drop however there is no tendency to spin Under these conditions the nose drops slightly and as the speed increases the wing will come up RESTRICTED 27 RESTRICTED No O1 75FF 1 strument dials are coated with phosphorescent paint This will enable the eyes to become accustomed to the darkness The instrument glare shield should be installed for all night flying 6 When more light is needed cockpit lights figure 6 11 may be turned on or the spotlight figure 4 1 may be focused on any point where local light is de sired and adjusted to the required brilliancy Position lights are turned on by a switch figure _6 6 the main switch d Landing lights figure 6 7 may be used for take off and landing They should not however be extended at any time when the airspeed is greater than 140 mph e Recognition lights may be used as required 19 APPROACH AND LANDING a The landing technique is similar to that for a con ventional landing geared airplane and the landing attitude is about the same i e main wheels first tail lightly down slightly down NOTE Extreme tail low landings possible only with flaps UP may cause the fins to strike the run way 1 With the gear DOWN and flaps at MANEU VER start the approach at 120 mph indicated airspeed When the approach is assured put the flaps all the way down come
51. ary power data ars listed timum cruising conditions NOTES A Avoid continuous cruising in Column in the upper left corner of chart NO RESERVE FUEL ALLOWANCE RANGE RANGE IN AIR MILES STATUTE NAUTICAL FLIGHT 1 90 1450 1830 1670 OPERATING D 2600 234 253 30000 245 R 2350 250 is 34 136 30000 2200 2600 240 A R 5000 2200 206 A L au 1143 2150 1 au 127 25000 2600 248 253 20000 Bi 2300 215 A au 143 2050 206 ni 10 20000 2500 2600 255 2600 260 2600 265 A R 1506 1506 1500 ra 183 CO CO 14 La 1 2600 270 2300 2 2050 5 33 1600 2600 275 2300 239 A L 34 7143 2000 33 1500 18 2600 279 2300 3 141 1350 32 1800 L INDICATED ALTITUDE CORRECTED FOR FREE AIR TEMPERATURE LAS Indicated Air Speed 5 60 GAS IMF GALS FOR WARM UP M P Manifold Preuure In e TAKE OFF AND CLIMB 0 2000 ALTITUDE N RETURN FUEL FLOWS TO TAN 7 ETE FON Tiis D USE FUEL FROM TANKS IN THE FOLLOWING ORDE SERVES 15 MINUTES DROP TANKS MAINS RESERVES 8 Auto Rich REFER TO SPECIFIC ENGIME FLIGHT CHART FOR ADDITIONAL ENGINE OPERATION DATA La Auto Lean RED FIGURES ARE PRELIMINARY SUBJECT TO REVISIOM AFTER FLIGHT CHECK 00 00 9 xipueddy 1316410 ON 04 0315131534 MODEL
52. at REFER TO SPECIFIC ENGINE ALIGHT CHART FOR ADDITIONAL ENGINE OF ERATION DATA La Auto Lean RED FIGURES ARE PRELIMINARY SUBJECT TO REVISION AFTER FLIGHT CHECK 09 0312181538 3444 10 ON 0318 MODEL S FLIGHT OPERATION INSTRUCTION CHART B 6 B B ek o4 YT POR b amp s sp amp B EXTERNAL LOAD ITEMS 26UU Lo OB 4 amp wo OP A PBod4 od ep amp PB amp POUNDS prom TTT TURN ee Dsg d 4 B W W a d EB B Ro B OR 4 4 ok 4 4 m o God EINE POSITION MOS CM rn MM EES MILITARY 3000 5 POWER INSTRUCTIONS FOR USING CHART Select figure fuel column equal to except in emergency Columns IV amp V toward the right pro less than total amount of fuel in airplane Move horizontally to the right gressively give increase in range at sacrifice in speed Manifold Pressure or left and select o figure equal to or grecter than the air miles to be Gallons Per Hour G P H are approximate maximum values for flown Vertically below and opposite desired cruising altitude read op reference D For quick reference take off and milit
53. b EMERGENCY OPERATION OF FLAPS 1 If the engine pumps fail to extend the flaps it may be possible to get them down by operating the hand pump RESTRICTED RESTRICTED No 01 75FF 1 the air Release bombs or drop tanks and the top hatch and push down both side windows Leave the shoulder harness on to prevent the shock of landing from throw ing the head forward into the bullet proof glass 1 Since much flatter approach be made with power on the landing should be made before the fuel has competely run out 2 Wind and surface conditions should be noted so that the approach may be made along the swell and as near into the wind as possible c Make contact with landing gear UP water land ings with gear down are invariably fatal flaps DOWN and at an atrspeed slightly above the stalling point d After coming to rest release the safety belts and swim clear of the airplane before tt sinks 4 ELECTRICAL FAILURE Electrical failure may be indicated by a zero read ing on the voltmeter figure 6 8 and the ammeter figure 7 13 and by rapidly diminishing battery pow er the first indication of a low battery will be given by failure of the propeller governors to hold the proper rom When the above conditions are noticed 1 Set the propeller selector switches to FIXED PITCH 2 Set the oil cooler flap switches to MANUAL 3 Restrict the use of all lights and radio 4 If possible tu
54. canopy Oil cooler radiators P 38H behind and above the pilot s left shoulder Cartridges 7 Oil tank are located nearby 8 Carburetor filter 9 Carburetor air intercooler MAP CASE is located behind the pilot s right 0 10 Airspeed pitot shoulder 11 Battery compartment door 2 Oxygen bottles d EMERGENCY RATIONS if any will be carried 13 Radio equipment Sear 14 Baggage compartment door in the baggage compartment 15 Recognition radio e INCENDIARY GRENADE is stowed behind the Soe bee seat of airplanes serial 42 66702 and up When a forced 8 Turbo supercharger ma P 19 cooler radiators landing is made in enemy territory the airplane may P 38 and 5 be destroyed by throwing the grenade at the airplane 20 Carburetor air intercooler from a safe distance RESTRICTED uonu eg 1336410 ON 01 2310191538 Diagram 9 Fuel System 01 0312181539 11 RESTRICTED 8 Electric fuel pump switches 3 1 7 Righe hand tank selector valve Left hand tank selector valve 5 6 Window crank ratchet handle Spotlight in alternate position Left window crank Shoulder harness release Cross feed switch Figure 10 Fuel System Controls 1 2 55017 701118137181 urua 01 009111118 dJO01391nqJr C 93
55. cross the back Before applying the front tape run a stout cord along the edge of the window frame just ahead of the cardboard and attach the tape over the cord Tie a loop in the cord so as to cause it to en circle the tape Tie the other end of the cord to the nose wheel strut and take up all possible slack This is repeated for the other windows as required Retraction of the nose wheel will pull off the front tapes and per mit the cardboard covers to blow away 4 A piece of tape should be put over any in operative blinker lights for the pilot s information 5 The photographer should fill out photographic data sheet A before the airplane takes off RESTRICTED No 01 75 1 2 OPERATE CAMERAS Set camera diaphragm control figure 28 4 as required Bright medium or cloudy b Turn camera switches figure 28 6 7 or 8 ON for each group of cameras to be used NOTE Camera heat figure 4 23 should be adjusted to maintain approximately 5 C 40 F on the camera compartment temperature indicator figure 28 1 Some airplanes may be equipped in service with prestone electric fan heaters which will be operated through a switch and rheostat in the cockpit c FOR INTERVALOMETER OPERATION 1 Determine time interval from the INTER VALOMETER SETTING table figure 30 2 Set the intervalometer hand to the selected time interval Push and turn knob figure 28 11 to set hand 3 Set the ca
56. ction Il Paragraph 4 8 sible to operate either engine from any tank When pro longed single engine flight makes it necessary to use fuel from the dead engine side or when operating both engines from one drop tank operate as follows a Set tank selector valve to the tank to supply fuel b Turn crossfeed switch figure 10 5 to CROSSFEED c Turn other tank selector valve OFF 5 STARTING ENGINES NOTE Engine fire extinguishers are NOT installed in this airplane Strict adherence to the following instructions as to mixture control positions will reduce the possibility of fire If fire does occur cut off mixture control electric fuel pump and ignition to that engine a With ignition OFF turn the engines over by hand two or three revolutions if they have been idle for more than three hours b Check operation of electric fuel pumps figure 10 4 Pressure 15 to 16 1 54 in with engines not oper ating Turn pumps OFF c Prime the left engine 2 to 4 strokes NOTE Push primer handle figure 4 36 down and turn 90 to unlock d Ignition master switch figure 6 1 ON e Left ignition figure 4 11 BOTH f Hold the starter switch figure 6 3 to LH left hand until the inertia starter has reached maximum rpm g Engage switch figure 6 4 to LH still holding starter switch to LH and prime as necessary b s soon as the engine definitely fires place the mixture control figure 4 6 to AUTO RICH
57. e engine control stand fig ure 4 8 The filters are to be used whenever dusty air conditions dictate but since they reduce the critical altitude of the engines and reduce the maximum range obtainable they should be used only when necessary e COOLANT TEMPERATURE CONTROLS 1 Coolant temperature is automatically regulated between 101 C flaps closed and 121 C flaps open 214 to 250 F with the coolant flap override switches set to OFF 2 RESTRICTED Section Arm safe switch Arming indicator light Safe indicator light Bomb or tank release button Spare indicator lights Spotlight alternate position socket Cockpit ventilator control Gun sight dark glass stowage Landing gear control handle Landing gear control release Oxygen pressure gage Elevator tab control Engine primer 24 25 26 27 28 30 51 32 33 34 39 30 RESTRICTED No 01 75FF 1 Propeller feathering switches Parking brake handle Microphone button under left thumb on 38 and F 5B Gun charging selector knob Landing gear warning light Propeller pitch vernier knob Friction control Bomb or tank selector switches Bomb or tank indicator lights Cockpit light or camera compartment heat control 20 Spotlight normal position Throttles Surface controls lock clip Propeller pitch controls Propeller selector switches Mixture controls Propeller warning lights
58. ead timum cruising conditions NOTES Avoid continuous cruising in Column ALTERNATE CRUISING CONDITIONS RAMGE IM AIR MILES 85 w o o n ze a Ww W pe pe SPEC 8 DEC 18 1942 I P BLOWER MIXTURE DURATION HG I POSITION POSITION 1710 89 8 MAX CONT POWER RAMGE IM AIR MILES 001015 ppm LAS MIK INDICATED ALTITUDE CORRECTED FOR FREE AIR TEMPERATURE GALS FOR WARM UP TAKE OFF AND CLIMB RETURN FUEL FLOWS TANK SSS USE FUEL FROM TANKS IN THE FOLLOWING ORDE ENEE TO SPECIFIC ENGINE FLIGHT CHART FOR ADDITIONAL ENGINE OPERATION DATA SINGLE ENGINE OPERATION RED FIGURES ARE PRELIMINARY SUBJECT TO REVISION AFTER FLIGHT CHECK 3354 10 ON O1 9315131533 xipueddy MODEL 5 FLIGHT OPERATION INSTRUCTION CHART EXTERNAL LOAD ITEMS EXTERNAL TANK SUPPORTS ONLY POUNDS INSTRUCTIONS FOR USING CHART Select figure in fuel column equal to except in emergency Columns IV amp V toward the right pro or less than total amount of fuel in airplane Move horizontally to the right gressively give increase in range at sacrifica in speed IC Manifold Pressure or left and select a figure equal to greater than the air miles to be Gallons Hour are approximate maximum v
59. ed Air Speed L ALLOW 0 5 GALS IMP GALS FOR WARM UP M P Manifold in 6 TAKE OFF AND CLIMB TO FEET ALTITUDE U 9 P M V 5 Galon Hour RETURN FUEL FLOWS T 7 D USE FUEL FROM TANKS IN THE FOLLOWING ORDER NGINE THEN DEAD ENGINE MAINS RESERVES Muto Rich EFE TO SPECIFIC ENGINE FLIGHT CHART POE ADDITIONAL ENGINE OPERATION DATA A La Auto Lean RED FIGURES ARE PRELIMINARY SUBJECT TO REVISION AFTER FLIGHT CHECK 29 033
60. fter the engines stop turning b If the oil temperature is above 40 104 F up on completion of the diluting process the engine should be shut down and allowed to cool until the oil temper ature is below 40 The engine should then be restarted and the same diluting process repeated This will avoid the possibility of evaporation due to the high tem perature nullifying the effect of the first dilution c If oil dilution is not necessary set the mixture con trols to CUTOFF at 1200 rpm d After the engines stop turning turn the ignition switches figure 6 18 6 1 OFF and leave the mixture in CUTOFF 21 BEFORE LEAVING THE COCKPIT Turn all switches and valves OFF b Lock the controls 1 To set surface controls lock figure 5 10 put rudders in neutral push the right end of the lock ing tube forward of the guide angle figure 5 4 and place the left end of the locking tube in the clip pro vided figure 4 3 Strap control wheel to center of surface control lock c Set the parking brake 1 Apply the toe brakes pull the parking brake handle figure 4 14 out and release the toe brakes NOTE Do not set the parking brake while the brake drums are hot 22 TIEING DOWN This airplane is secured by ropes which are passed through tie down lugs on each landing gear shock strut and tied to stakes firmly anchored to the ground Stakes and ropes are provided in the mooring kit which is stowed in the b
61. gure 27 9 and the aileron trim knob figure 27 7 to check operation of the units 46 RESTRICTED Section Paragraph 5 3 Runaway operation may also be obtained setting the controls for manual operation and holding the trigger down 1 The pilot should fill out photographic data sheet B on completion of each photographic flight GROUND OPERATION for photographer 1 Owing to the limited space the dark slides must be removed before installation of the magazines With this in mind do not roll the entire daylight load ing leader onto the take up spool until after the mag azine is installed The leader may then be wound up in checking the operation of the camera controls 2 Set the reversing switch located on the control box in the camera compartment and arrange cams in the control box so that cameras will fire in the desired order Usually the adjustment will be made so that 24 cameras fire at the beginning of each time interval 12 cameras fire at the beginning of intervals 1 3 5 etc and 6 cameras fire at every fourth interval 1 5 9 etc 3 The camera windows may have to be protected from spray from the nose wheel when taking off from muddy wet or oily runways The following expedient has been found satisfactory Cut a piece of cardboard to the size of the visible glass area Attach this over the glass with two pieces of masking tape one across the front side and one a
62. h it forward c Strike the charging selector with the heel of the hand NOTE Never attempt to move the charging selector unless the charging handle is in the full for ward position d Charge the other three machine guns 11 the same manner 2 Turn the armament switch on control column to COMBAT 3 Push the machine gun button or the cannon button figure 4 12 to fire the guns Machine gun button is on reverse side of wheel from cannon button shown a If it is desired to use the camera without the guns set the armament switch to CAMERA and operate either the gun or cannon button NOTE Turn gun heat figure 4 23 ON whenever the outside air temperature is below freezing RESTRICTED 43 Section V RESTRICTED No 1 75 1 l Rate control ground adjustment only 6 Directional gyro caging knob 2 Speed valves 7 Aileron trim knob 3 Course setting knob indicator 8 Miniature airplane control 9 Elevator trim knob 4 Course setang knob 2 10 Gyropiloc shutoff valve 5 Artificial horizon caging knob 44 RESTRICTED RESTRICTED Section V No 01 75 1 a BLINKER 7 00 ONTGIN FLOW Camera compartment temperature indicator e Exposure counters Blinker light box Diaphragm setting control Camera master switch Chart camera switch Reconnaissance camera switch Alternate reconnai
63. he ground but before the safe single engine speed 120 mph has been reached close both throttles and LAND STRAIGHT AHEAD Retract the gear if you are running out of air port c If one engine fails after reaching the safe speed of 120 mph and after the gear has started up 1 Reduce power enough to regain control then apply power gradually and hold enough rudder to pre vent the airplane from skidding Raise the wing on the dead engine side to assist in preventing the skid 2 Release drop tanks or bombs if circumstances dictate 3 Trim rudder tabs 4 Feather the dead engine s propeller NOTE Do not apply so much power that the airplane cannot be held straight with the rudder 45 Hg at 3000 rpm should be enough to accelerate the airplane to a good single engine climbing speed of 165 mph 5 Set the mixture on the dead engine to CUT OFF 6 Turn OFF electric fuel pump of dead engine 7 Circle the field and land Make all turns with the dead engine on the outside of the turn See Section II paragraph 19 4 for single engine landing 12 CLIMB Mixture figure 4 6 AUTO RICH b Intercooler flaps figure 6 12 OPEN If installed c Refer to the climb chart in Appendix II for the best climbing speeds at different weights powers and altitudes 160 mph is the average best climbing speed at sea level d On P 38H airplanes carburetor air temperature is critical in a high power climb between 15000 and 2500
64. ible 17 Inverter switch figure 6 9 or compass switch on main switch box ON Section ll Paragraph 3 1 To open the top hatch turn the two releases figure 20 1 and 20 9 on the top of the windshield and rotate the hatch backward 3 ON ENTERING THE COCKPIT 4 CHECK FOR ALL FLIGHTS 1 Crossfeed switch figure 10 4 OFF 2 Tank selector valves figure 10 7 10 8 SERVE ON 3 Oxygen pressure figure 4 34 400 to 450 Ib sq in 4 Turn the bomb selector switches figure 4 20 ON and the arming switch figure 4 24 to SAFE so that tanks or bombs may be dropped quickly in the event of engine failure at take off 5 Throttles figure 4 2 1 10 OPEN I Flush type handhold 2 Up tock release 3 Down lock release 4 Ladder lever 5 Ladder Figure 19 Access Ladder 22 RESTRICTED Section ll Paragraph 3 4 dry then shift to right drop tank Hourly fuel con sumption may be determined from the charts in Ap pendix II no fuel gage is installed in the drop tanks Switch both selector valves to MAIN ON Do not drop external tanks unless necessary for increased range or engaging in combat Burn out main tanks and switch back to RESERVE for the remainder of the flight NOTE Never exceed 250 mph with 300 gallon drop tanks installed 2 When flying above 12000 feet altitude it may be necessary to operate the electric fuel pumps figure 10 4 to maintain the required 14 to 18 lb sq in f
65. icated at 20 000 feet the airplane will become nose heavy and start to buffet Or if a pullout of over 4 5 G s is made at 300 mph and 20 000 feet the same condition will be evident 4 When the above conditions are noticed THE FOLLOWING ACTION SHOULD BE TAKEN IM MEDIATELY 1 In accelerated maneuvers dive pullouts or steep turns buffeting may be stopped by reducing the acceleration 2 In steady dives at high speed buffeting may be stopped by reducing the airplane speed and pulling out using minimum acceleration Any acceleration will tend to increase the buffeting a Throttles CLOSED b Use the elevator tab figure 4 35 if neces to assist recovery WARNING Elevator tab must be used with care in order to prevent an extreme tail heavy condition after the buffeting stops 18 NIGHT FLYING a Very little light need be used for normal cruising flight Fluorescent lights figure 6 5 should be dimmed down until the instruments are barely visible all in 28 RESTRICTED Section Il Paragraph 20 22 20 STOPPING OF ENGINES cold weather 0 C or 32 F start is anticipat ed the oil system should be diluted before stopping the engines Idle the engines until oil temperature is below 70 158 F adjust the throttles to approximately 1000 rpm hold the oil dilution switches figure 6 2 ON for 4 minutes pull the mixture controls figure 4 6 to CUTOFF and release the oil dilution switches a
66. imb and nearly closed at all other times Carburetor air temperature should not be allowed to exceed 45 C 113 F P 38H airplanes are not equipped with intercooler flaps f Flight operations should be planned from the Flight Operations Instructions Charts in Appendix II When using these charts make sure that the chart being used is applicable to the airplane Charts are clearly marked to indicate the airplane model the weight and the external load items carried If the weight or external load is to be changed during the flight charts should be used with this in mind 2 The airplane 15 stable at all normal speeds be comes slightly nose heavy when flaps and landing gear are extended Release of droppable fuel tanks causes no noticeable change Two engine cruising below 170 mph indicated is not recommended as the airplane requires more attention and range 1 not increased by flying be low this speed 14 STALLS a With power OFF the airplane stalls at the follow ing indicated speeds at the gross weight noted 15000 Ib 1700018 19000 Ib Flaps and gear UP 94 mph 100 mph 105 mph and gear DOWN 69 mph 74mph 78 mph b As stalling speed is approached the center section stalls first with noticeable shaking of the airplane and the ailerons stay unstalled and effective In either power on or power off stalls with flaps and landing gear up the airplane mushes straight forward in a well controlled stall With fl
67. indicated in Section II and in the cruising charts in Appendix II c PROPELLER CONTROLS Conventional electric propeller controls are installed 1 PROPELLER PITCH CONTROL LEVERS figure 4 4 select the desired engine rpm for automatic constant speed propeller operation 1 GENERAL The P 38H 38 and F 5B airplanes are twin boomed single seater monoplanes manufactured by the Lockheed Aircraft Corporation and are powered by one V 1710 89 right hand rotating and one V 1710 91 left hand rotating Allison engine P 38H and P 38 are fighter airplanes The 5 is a photographic air plane The engines drive three bladed constant speed full feathering Curtiss electric propellers Hydraulically operated landing gear flaps brakes and coolant shut ters are provided The approximate overall dimensions are as follows Length asawang na teen 37 feet 10 inches HEGDE EE 9 feet 934 inches niece deceptis 0 6 52 feet 0 inches b FUEL OIL AND COOLANT Fuel Specification AN VV F 781 Amendment No 5 or better Octane 100 Oil Specification AN VV O 446A Grade 1120 for cold weather operation use grade 1100A with oil dilution if necessary Coolant Specification AN E 2 Ethylene Glycol c The armament 15 mounted n the nose of the fuse lage and armor protection is provided as shown in figure 3 Photographic airplanes are protected by armor RESTRICTED 1 RESTRICTED
68. mal system except the hand hydraulic pump furnishes the power and the fluid comes from the BOTTOM of the main hydraulic reser voir When using the auxiliary system the hand pump source selector valve figure 14 4 is UP and the bypass valve figure 14 3 is OPEN NOTE It will be impossible to build up pressure with the hand pump unless the coolant override switches are OFF This is due to a fixed bleed in the system when the switches are in the override position Section Paragraph 3 7 3 FUEL SYSTEM See figure 9 Fuel pressure figure 7 4 normally 14 to 18 15 54 in is supplied by one engine driven pump and one electric pump for each engine The electric pumps figure 10 4 should be turned ON during take off and landing and at altitude usually above 12000 feet if the fuel pressure drops below 14 Ib sq in b FUEL QUANTITY GAGES figure 7 16 indi cate for the four wing tanks only The quantity in the droppable tanks must be estimated from the time of flight and the hourly fuel consumption as indicated in the charts in Appendix 4 OIL SYSTEM See figure 15 RETRACTABLE LANDING GEAR CONTROL See figure 13 a The landing gear lever figure 4 32 controls the extension and retraction of all three wheels A lock on the lever prevents its being moved out of the DOWN pesition when the airplane is or the ground when the left main shock strut is compressed If this lock fails or if it is necessary
69. mera control switch figure 28 9 to 4 Turn camera master switch figure 28 5 ON An exposure will be made immediately 5 Amber lights flash when exposure is made Green lights indicate when film is winding The white light gives a three second warning before exposure 6 To take an extra picture at any instant throw the control switch to RUNAWAY and immedi ately return it to INTERVALOMETER 4 FOR MANUAL CONTROL 1 Set camera control switch to MANDAL 2 Turn camera master switch ON 3 Pull the camera control trigger on the control wheel to make an exposure e FOR RUNAWAY OPERATION 1 Set camera control switch to RUNAWAY 2 Turn camera master switch ON NOTE Because the time to wind varies slightly for each camera exposures will not be made simul taneously during runaway operation Pictures will therefore not be suitable for stereoscopic viewing RESTRICTED 47 Section V RESTRICTED No 01 75 1 AIRPLANE S AIRSPEED INDICATOR READING MPH INTERVALOMETER SETTING SEC Airplane s Altimeter Reading 1 000 Ft Altimeter Set 29 92 Hg Altitude Above Ground 1 000 Ft 14 16 18 26 38 9 285 275 270 260 250 245 235 230 220 210 200 190 180 175 170 160 155 2 2 3 3 4 4 51 St 6 Ot 61 64 9 9 9 310 300 290 280 275 265 260 250 240 230 220 215 205 195 185 180 17011 2 2 37 3 5 4 St 61 ot Sf Sf 9 330 320 310 300 295 285 280 2
70. nd off 9 ELECTRICAL SYSTEM The 24 volt electrical system is powered gen erator on the left engine and a battery in the left boom F 5B camera airplanes have a generator on each engine controlled by separate switches located near the am meters and a battery in the nose compartment The battery switch figure 6 15 cuts out the battery leaving the rest of the system operating on the generator The generator switch figure 6 16 cuts out the generator allowing the system to draw from the battery only The ignition master switch figure 6 1 has no effect upon the electrical system but cuts out the ignition to both engines b LIGHTS 1 LANDING LIGHT is located under the left wing both wings on P 38H and controlled by switch es figure 6 7 on the main switch box With RESTRICTED 7 RESTRICTED 01 75 1 lever and make sure that the seat is firmly locked the new position Normally the seat will be adjusted to the height which will make the reflection of the gun sight light easily visible c SHOULDER HARNESS should be worn at all times It will be impossible to lean forward unless the harness lever figure 10 6 on the left side of the pilot s seat is raised The harness lock will re engage as soon as an upright position 159 resumed d PILOT S RELIEF TUBE figure 5 16 Section Paragraph 10 10 PILOT COMFORT RUDDER PEDAL ADJUSTMENT is obtained by pushing or pulling
71. nsight fig ure 29 2 To drop bombs set the arming switch fig ure 4 24 to safe set the bomb selector switch figure 4 20 to ON for the bomb to be dropped and while flying at not more than 400 mph and not more than 30 from the horizontal with flaps UP press the release button figure 4 27 RESTRICTED T O No 01 75FF T e With the auto mix and the emergency controls both turned OFF pure oxygen will be supplied as required by normal breathing This setting however is wasteful of oxygen and should be used only in an emergency or when denitrogenizing for high altitude flight has been accomplished f The supply warning light figure 25 2 indicates when the pressure drops below approximately 100 Ib sq in Pressure is indicated on the oxygen pressure gage hgure 4 34 3 OPERATION OF THE ARMAMENT 4 The airplanes are equipped with four 50 caliber machine guns and one 20 mm cannon Space 15 vided for carrying 500 rounds of ammunition for each 50 caliber gun and 150 rounds for the 20 mm cannon small motion picture camera operates with the guns to record results 1 Before take off check that machine guns and cannon have been charged P 38H only is equipped with a machine gun charger which may be operated 1n flight as follows a Pull the charging selector figure 4 16 out and turn to the gun to be charged b Pull the charging handle figure 4 10 all the way back and then pus
72. or an external energizer 6 ENGINE WARM UP Keep the rpm under 1400 until the oil temperature reaches 40 105 or shows a definite increase 10 C 18 F and the oil pressure is steady below 75 Ib sq in b Make a radio check with the control tower or another airplane while the engines are warming 7 EMERGENCY TAKE OFF 4 When necessary take off may be made without the normal engine and accessories ground tests provided that the oil pressure is steady below 85 16 54 in and that the oil temperature has shown a definite increase at least 10 C 18 F since starting Use the oil dilu tion system to reduce the oil pressure if necessary b Overdilution is likely to result from diluting the oil in a cold engine If dilution is necessary during warm up oil pressure should be carefully watched dur ing the remainder of warm up and take off to insure that overdilution has not occurred 8 ENGINE AND ACCESSORIES OPERATION GROUND TEST 4 Extend and retract the flaps figure 5 2 to check the hydraulic system 15 to 20 seconds is normal ex tension time at 1400 rpm 25 seconds if one engine pump is dead b Normal fuel pressure figure 7 4 14 to 18 16 59 in Idling 10 Ib sq in Check for normal pressure with electric fuel pumps OFF c Increase rpm to 2300 1 Check propeller pitch control levers figure 4 4 DEC RPM then INC RPM full forward 2 Check propeller selector switches figure 4 5 Se
73. or three receivers may be turned on simul taneously by following the instructions con tained in paragraphs 4 and above for each receiver 2 Transmitting a Select the desired frequency with the trans mitter selector switch figure 22 12 b Plug the microphone into the jack JK 48 figure 22 13 which is plugged into the bottom of the transmitter control box c Turn the main power switch figure 22 11 ON and allow 15 seconds for the transmitter to warm up d Turn the emission selector figure 22 10 to CW MCW or TONE as desired e If MCW was selected press the microphone button in the center of the control wheel and talk slowly and clearly f CW or is selected operate the key figure 22 15 d DETROLA MODEL 438 BEACON RECEIVER This receiver is in addition to the SCR 522 or the SCR 274N radio when the airplane leaves the factory If it is still installed 1 Plug headphones into the jack figure 14 5 which is plugged into the face of the radio panel 2 Turn the volume control figure 5 15 up un til the background noise is heard 3 Tune to the desired frequency with the tuning knob figure 5 14 4 Frequencies covered are 200 to 400 kilocycles Section V Paragraph 1 c OPERATION OF THE SCR 274N RADIO There are three separate receivers and there may be any two of four available transmitters installed Transmitter Frequencies 3 104 megacycles 4 0 to 5 3 megacycles 5
74. orcing them with the wheels Remind the ground crew to check for broken locks and warped doors while the emergency system 1s being serviced Imm YOU HAVE AN EMERGENCY EXTENSION SYSTEM WHY NOT LEARN TOUSE IT 7 2 LANDING WITH WHEELS RETRACTED a When a belly landing is necessary it should be made without external tanks Use to full flaps NOTE When belly landing is due to apparent hydraultc failure unless forced down by lack of fuel or approaching darkness don t give up until all methods of gear extension have been thoroughly and exhaustively tried b Make a normal approach at 8 or 10 mph over the stalling speed and set the airplane on the ground slight ly before the stall is reached Jj LANDING ON WATER DITCHING Unless the water is very smooth it will probably be more desirable to bail out of the airplane chan to try to land it on the water b If a water landing is necessary preparations for abandoning the airplane should be made while still in 36 RESTRICTED Section IV Paragraph 6 7 unfeather a propeller in flight 1 Prepare the engine for normal starting ex cept set the propeller pitch control to DEC RPM and do not prime 2 Turn the feathering switch figure 4 13 ro NORMAL CAUTION When practicing single engine flight always shut down the right engine so that the gener ator will remain in operation Make all re start ing preparations immediately so tha
75. over the fence at 110 mph flare off to about 80 mph and wait for contact 2 If for some reason the flaps won t come down bring it in a little faster and allow for more flare off and a flatter gliding angle b NORMAL LANDING 1 Tank selector valves figure 10 7 10 8 to MAIN or RESERVE whichever contains the most fuel 2 Mixture controls figure 4 6 AUTO RICH 3 Propeller pitch levers figure 4 4 to about 2600 rpm position 4 Electric fuel pumps figure 10 4 ON 5 Landing gear figure 4 32 DOWN not over 175 mph 6 Pump the toe brake pedals a few times to in sure that brakes are working 7 Wing flaps figure 5 2 DOWN not over 150 mph NOTE Lift the trigger through the quadrant notch to place lever to DOWN 8 Intercooler flaps figure 6 12 CLOSED If installed 9 Flaps UP before taxiing Section Paragraph 18 19 tion is allowed to develop the nose heavy condition will become more pronounced and it will be very dif ficult to pull out b The speed at which this phenomenon occurs de pends upon the altitude and the acceleration or G s which is being applied in a pullout Figure 21 shows the placard consisting of three curves of indicated airspeed plotted against acceleration and indicates the safe range at the altitudes shown on each curve We DON T DIVE WITH NG MANEUVERING ASW FLAPS EXTENDED O For example If a straight dive is made in excess of 370 mph ind
76. rn the battery switch OFF until electrical power is necded 5 If it necessary to land with the propeller selector switches MANUAL the following setting should be made to insure that sufficient power will be available and that the engines will not overspeed in the event of a mislanding Make this adjustment possible while there still sufficent battery power to operate the propellers a Altitudc Not over 5000 feet above the atr port b Adjust the throttles and propeller selector switches to obtain 2600 rpm and 25 Hy manifold pressure at an approximate airspeed of 180 mph in level flight 5 ENGINE FAILURE 4 lhe airplane flies well on onc engine Using nor mal rated power it will climb to about 26 500 feet and can be flown at more than 255 mph true speed in level flight at 20 000 feet Section IV Paragraph 2 5 2 If after considerable pumping no reading is given on the position indicator figure 7 19 operate the emergency system as follows a Source selector valve handle figure 14 4 break safety wire and push DOWN b Bypass valve figure 14 3 break safety wire and CLOSE tightly On later airplanes separate control of the bypass valve will be eliminated by in corporating it into the source selector valve If bypass valve is not present disregard operation b c Check landing gear control DOWN and operate the hand pump NOTE This system opens the gear doors by f
77. rsonnel for Government may be given to person known to be in the service of the United States work to civilian concerns contracting for overhaul and repair of aircraft and to persons of undoubted loyalty and discretion who are cooperating or aircraft accessories and to similar commercial organizations LIST OF REVISED PAGES ISSUED NOTE A heavy black vertical line to the left of the text on revised pages indicates the extent of the revision This line is omitted where more than 50 percent of the page is revised This issue contains no revisions ADDITIONAL COPIES of this publication may be secured on Requisition AAF Form 102 as prescribed in AAF Regulations 15 102 Submit requisitions to Commanding General Air Service Command Patterson Field Fairfield Ohio Also see T O No 00 25 3 for details on distribution of Technical Orders Requests from Naval activities shall be submitted to Chief of che Bureau of Aeronautics Navy Deparcment Washington D C A RESTRICTED RESTRICTED No 01 75FF 1 CONTENTS SECTION I DESCRIPTION Paragraph Page 1 General sonsa M 1 2 Engine and Propeller Control Dom 4 p c 13 ESO OEES 0 Les ERR RR EEN 4 5 Retractable Landing Gear Control 4 6 Flap Control O 4 7 Hydraulic System
78. s f Refer to the Specific Engine Flight Chart in Sec tion III for power time limitations g Refer to the Climb Chart in Appendix II for rate of climb Note correction to be made during hot weather 13 GENERAL FLYING CHARACTERISTICS a Due to the counter rotating propellers there is no noticeable torque effect in any two engine flying with this airplane Rudder and aileron trim tab settings do not require adjustment due to changes in speed and powet b TO INCREASE POWER IN FLIGHT 1 Mixture figure 4 6 AUTO RICH if maxi mum cruising power is to be exceeded see Specific Engine Flight Chart in Section III 2 Propeller pitch controls figure 4 4 to the new rpm 3 Throttles figure 4 2 to the new manifold pressure c TO DECREASE POWER IN FLIGHT 1 Throttles figure 4 2 to the new manifold pressure 2 Propeller pitch controls figure 4 4 to the new rpm Section Paragraph 10 13 NOTE It is important that the gear be retracted im mediately after the airplane is off the ground so that the flight may be safely continued in the event of engine failure after take off o Reduce power to 43 Hg 2600 rpm after clearing all obstacles 11 ENGINE FAILURE DURING TAKE OFF If one engine fails before leaving the ground close both throttles immediately and apply full brakes If it is going to be impossible to stop on the airport retract the gear and slide in b If one engine fails after leaving t
79. ssance camera switch Camera control switch Gyropilot oil pressure indicator Intervalometer setting knob Figure 28 Camera Controls RESTRICTED RESTRICTED O1 75FF 1 7 CHECK AUTOMATIC PILOT CONTROL VALVE OFF BEFORE TAKE OFF b TO ENGAGE AUTOMATIC PILOT IN FLIGHT 1 Trim the airplane for hands off flight 2 Set the directional gyro lower card to agree with the compass and rotate the course setting knob until the upper and lower cards coincide 3 Uncage the directional gyro 4 Turn the elevator and aileron trim knobs to zero 5 Turn the automatic pilot control valve ON 6 Adjust the course setting knob and the trim knobs to hold the airplane in straight and level flight 7 Adjust the speed valves figure 27 2 to obtain the proper rate of control 8 Disengage automatic pilot every 15 minutes in flight to reset the directional gyro with the compass and retrim the airplane for hands off flight 9 Make small directional changes flat turns by turning the course setting knob slowly to the new heading 10 Make faster turns by setting the airplane in a bank with aileron trim knob caging the directional gyro and rotating the course setting knob until the ball bank indicator 1 centered CAUTION The operating limits are 55 in a climb or dive and 90 in a bank Both gyros should be caged during any maneuvers which might exceed these limits 5 OPERATI
80. t the engine may be started quickly if the left engine should fail during the practice 3 Hold the propeller selector switch figure 4 5 to INC RPM until the engine is turning 600 to 800 rpm then place it to AUTO CONSTANT SPEED Place mixture contro to AUTO RICH and engine should start 4 Warm up the engines before operating at full power 6 ICING CONDITIONS Pitot heat figure 6 14 ON b The formation of carburetor ice 15 unlikely in this airplane due to the injection type carburetors and the heating effect of the turbo superchargers It is possible however that ice could form while flying at low powers in a humid atmosphere If icing conditions are present during a landing approach move the throttles occasionally to prevent 1ce from freezing them in a closed position Put gear down flaps 14 down and make the approach under partial power d carburetor ice forms in cruising flight it may be removed by increasing the power boldly and putting the airplane into a steep climb Intercooler shutters on P 38 and F 5B airplanes only should be closed as far as possible without exceeding the maximum 45 carburetor air temperature e Ice formation on the windshield may be removed by turning the cockpit heat ON and directing the flex ible heater tube to the desired point on the glass 7 EMERGENCY EXIT Recommended Slow down as much as possible below 200 mph and trim the airplane in an approx ima
81. tch on the main switch box labeled COMPASS ON OFF No warning light is installed RESTRICTED No 01 75 1 3 The emergency system operates from a separate reservoir and through separate lines using the hand pump for power THE ONLY PURPOSE OF THIS SYSTEM IS TO EXTEND THE LANDING GEAR IN CASE OF COMPLETE FAILURE OF THE OTHER TWO SYSTEMS When using the emergency system the hand pump source selector valve figure 14 4 is DOWN and the bypass valve figure 14 3 is CLOSED Later airplanes have the bypass valve incorporated in the source selector valve c Brakes are not connected to the main hydraulic system No emergency braking system is provided See figure 12 for brake system diagram 8 HEATING AND VENTILATION See figure 18 4 COCKPIT HEAT is supplied by an intensifier tube in the right engine exhaust and controlled by knob figure 5 3 on the right windshield support Heat out lets are arranged to supply warm air to the windshield and removable hatch The foot heat outlet may be closed off by operating the heat control figure 18 5 on the floor under the right foot b VENTILATING AIR enters from the left wing fuselage fillet The rate of flow may be varied by rotat ing the ventilator figure 4 30 as desired c ARMAMENT OR CAMERA COMPARTMENT HEAT 1 supplied by an intensifier tube in the left en gine exhaust The heat control figure 4 23 on the left windshield support is used to turn the heat on a
82. tely level attitude heading towards an unpopulated area if possible Pull the handle figure 20 4 to release the top hatch crank or push side window down crawl out and slide off the wing head first b Alternate If control is still available turn the airplane upside down and unhook the safety belt RESTRICTED No 01 75 1 b When one engine fails 15 shut down 1 Reduce the power from the live engine if necessary to maintain directional control 2 Close the throttle figure 4 2 of the dead engine 3 Propeller pitch figure 4 4 control DEC RPM 4 Mixture figure 4 6 IDLE CUTOFF 5 Feather the dead engine s propeller figure 4 13 6 Ignition figure 6 18 OFF 7 Open throttle enough to silence the landing gear warning horn NOTE IN AN EXTREME EMERGENCY FEATH ER THE PROPELLER FIRST 8 Use as little power as necessary from the good engine and refer to the single engine cruising chart in Appendix Il if range is important For maximum single engine range with droppable tanks installed fly the airplane as low as safety permits and at the lowest pow er which will maintain an airspeed of approximately 160 mph Use fuel from the tank on the live engine side first and drop each tank as soon as it is empty After both tanks have been dropped refer to the single engine cruising chart in Appendix II to obtain the range available with fuel remaining in the wing tanks Fur
83. the small lever figure 5 18 on the outboard corner of each pedal and moving the pedals to suit Care must be taken to insure that both pedals are adjusted equally b SEAT ADJUSTMENT 15 obtained by lifting the small lever figure 14 1 on the right side of the seat and raising or lowering the seat as required Release the 12 Turbo overspeed warning lights 13 Ammeter 14 lachometers 15 Coolant temperature indicator 16 Fuel quantity gages 17 Clock 18 Combination oll pressure and temperature gages fuel pressure indicator not connected 19 Flap and Janding Gear position indicator 20 Space for 008 Contactor 21 Carburetor air temperature indteator 1 Directional gyro 2 Gyro horizon 3 Compass indicator 4 Fuel pressure gages 5 Altimeter Airspeed indicator Turn and bank indicator 8 Rate of climb indicator Manifold pressure pages 10 Suction gaye 11 Hydraulic pressure gave Figure 7 Instrument Panel 8 RESTRICTED RESTRICTED Section No O1 75FF 1 Paragraph 11 38 and F 5B Figure 8 Airplane Content Diagram 11 MISCELLANEOUS ME 50 caliber machine guns FIRST AID KIT 15 located behind the pilot s seat 2 20 mm cannon 1 E al 3 Antenna mast on the right hand side i feel katik 7 Di ES 5 Coolant tank b VERY PISTOL is carried in the top of the
84. uel pressure 3 To release droppable fuel tanks a Flaps and gear UP Tank selector valves figure 10 7 10 8 to MAIN or RESERVE c Arming switches figure 4 24 to ARM or SAFE d Selector switches figure 4 20 ON for tank s to be dropped e Press the release button figure 4 27 while flying at an angle not greater than 30 from the hori zontal f Full fuel tanks may be dropped without dan ger at airspeeds up to 400 mph Empty 150 gallon tanks should be dropped only while flying at an airspeed of 160 mph or less WARNING EMPTY 500 GALLON TANKS ARE TO BE DROPPED ONLY IN AN EMERGENCY as the tanks may hit the airplane when released Consequently it is necessary to slow the air plane down to 120 mph with gear and flaps up to avoid serious damage b LONG RANGE FERRY FLIGHT 1 Whenever flying with droppable tanks it is advisable to operate both engines from the LEFT drop tank until empty then shift both engines to the right drop tank If necessary the left tank may be dropped as soon as it is empty and will then be carried only half as far as if each engine were operated from its own tank c CROSS FEED OPERATION 1 The two fuel systems are connected by an elec trically operated crossfeed valve which makes it pos RESTRICTED T O No 01 75FF 1 18 Contactor heater ON if contactor is to be used during the flight 19 Armament switch on control column or con trol wheel OFF
85. ure below 54 Hg CAUTION Be prepared to reduce power immediately to prevent uncontrollable yaw and roll in case of engine failure on take off Landing gear UP as soon as practical after leaving the ground RESTRICTED T O No 01 75FF 1 DEC RPM then INC RPM then return to AUTO CON STANT SPEED Note that propeller warning lights on P 38H only glow when selector switches are out of AUTO CONSTANT SPEED 3 Check magnetos Maximum normal drop 100 rpm on going from both to either magneto Engine must run smoothly on eitber magneto 4 With the generator switch es ON check the voltmeter figure 6 8 for approximately 28 volts and the ammeter figure 7 13 for charge On 5 air planes check voltage at both generators by turning the voltmeter selector switch to L then R 5 Check intercooler flaps OPEN if installed and check operation of superchargers by opening throt tles individually to take off power see specific engine chart in Section NOTE Do not operate at this power for more than 2 or 3 seconds while standing still 9 TAXIING INSTRUCTIONS The airplane taxis easily use differential throttle con trol for turning and save the brakes There is no danger of nose over or ground loop should it become necessary to turn sharply or to apply full brakes Forward visibility is good ui WATCH WHERE YOU RE GOING WHEN TAXIING 10 Roll a few feet straight do
86. ward recognition lights by operating them for more than thirty seconds while on the ground Make all ground operation as short as possible 3 POSITION LIGHTS controlled switches figure 6 6 on the main switch box Bright dim and off positions are provided 4 COCKPIT LIGHTS figures 5 12 aud 4 22 are controlled by a rheostat figure 6 11 on the main switch box and a switch on the lights themselves 5 FLUORESCENT INSTRUMENT LIGHTS are mounted on the forward side of the control column and turned on by a switch figure 6 5 on the main switch box Light intensity is regulated by twisting the ends of the lighting unit 6 SPOTLIGHT figure 4 1 is normally on the left windshield support An alternate position figure 10 1 15 provided over the fuel tank selector valves The spotlight switches are located on the light and the beam may be focused by sliding the screw head forward and aft in 115 slot INVERTER On P 38H airplanes the inverter is turned on by the switch figure 6 9 under the flap lever It supplies 400 cycle alternating current which is used to operate the fluorescent lights and the remote indicating compass warning light figure 6 19 glows when the inverter is not operating The operation of this light indicates failure of the inverter and consequent failure of the compass and fluorescent lights 1 On P 38J and F 5B airplanes the inverter operates only the compass and is turned on by a swi
87. will be required to prevent stalling the plane if the speed is allowed to drop below 90 mph indicated with flaps down power on and gear up NOTE Tail heavy conditions may be relieved by low ering the landing gear 6 Check that the cannon and machine guns have been charged and chat the radio transmitters have been tuned to the proper frequencies Access to the airplane ts by means of the retractable ladder on the rear of the fuselage figure 19 5 Push the up lock release figure 19 2 and raise the handle figure 19 4 to a vertical position Force the handle down until the ladder locks in the position shown retract the ladder push the down lock release figure 19 3 and pull the handle straight up until the ladder stows in place then swing the handle forward flush with the tuselage contour and press firmly into place A flush hinged handhold figure 19 1 15 built into the left side of the fuselage RESTRICTED T O No 01 75FF 1 1 FLIGHT RESTRICTIONS MANEUVERS PROHIBITED 1 Snap rolls and intentional spins 2 Continuous inverted flight 3 Do not exceed the airspeed or accelerations given on the DIVE LIMITS placard which is posted in the cockpit of each airplane Do not exceed 3 5 Ge n gative acceleration 4 Do not exceed 250 mph with 300 gallon drop tanks installed b Extreme care must be taken during acrobatic maneuvers which require a downward recovery Acro batics should not
88. wn the runway so that the nose wheel will be in line when power is applied Max imum performance take offs require holding the airplane with brakes at the end of the runway until engine power reaches the desired setting Because of the tricycle gear there is no tendency for the airplane to take off by itself no feeling of lightness as take off speed is reached Start RESTRICTED 25 RESTRICTED 01 75 1 critical Excessive temperatures will cause detonation and very rough engine operation resulting in loss of power and probable engine damage 1 On 38 and F 5B airplanes with intercooler flaps OPEN the manifold pressure is limited by the rating of the engine up to 25000 feet Above 25000 feet turbo supercharger overspeed is again critical The following maximum manifold pressures are to be used for war emergency only Never exceed 60 Hg Above 25000 feet these limits indicate the approxi mate values at which the turbo warning lights should burn in a climb In level flight it should be possible to carry the manifold pressures shown below to slightly higher altitudes Altitude P 38H P 38 and F 5B Feet 13 turbo B 33 turbo B 33 turbo up to 15000 60 60 60 20000 55 55 60 25000 45 48 60 30000 35 40 50 35000 30 35 41 40000 20 30 33 Early 38 1 are equipped with type 13 turbos P 38H airplanes above serial 42 66727 and 38 and F 5B airplanes are equipped with type B 33 turbo
89. zimuth control is set at zero g The azimuth crank is used to rotate the loop antenna Antenna position is indicated on the azimuth indicator 5 The left right indicator indicates whether the station 15 the right or left of the centerline of the airplane only when the azimuth indicator is turned to zero An azimuth indicator warning light indicates whenever the azimuth indicator is not on zero 2 OPERATION OF THE MN 26Y RADIO COMPASS a Turn the main switch ON and set the band selector switch to the frequency range desired 6 Tune to the desired station and adjust the volume audio control Set the C W switch to ON for code reception OFF for voice reception Set the master switch according to the oper ation to be conducted 1 Oxygen flowmeter 2 Oxygen pressure warning light 3 Auto mix lever 4 Emergency knob 42 Section V Paragraph 3 Oxygen Lines Refill Lines Oxygen bottles Check valves Refill connection Demand type oxygen regulator Oxygen flowmeter Oxygen pressute page MAY Row OM Pressure warning light sight is turned ON by the rheostat figure 6 10 which adjusts the intensity of 4 The optical gun the reflection on the glass behind the windshield Adjust the seat vertically until the sight reflection is easily visible 5 When flying in bright sunlight place the dark glass figure 4 31 in position over the gu

PILOT'S FLIGHT OPERATING INSTRUCTIONS

Contents

Download Pdf Manuals

Related Search

Related Contents