Douglas A-4M Flight Manual Download | Manualshive

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Summary of Contents for A-4M

Page 1: ...SUPERSEDES PRELIMINARY PUBLICATION NAVAIR OI 40AVM 1 DATED I AUGUST 1970 A D I i L i I 7 1 I eel to special export controls to fore ign governments nls thereof may be made 1 prior approval of NAVAIRSY...

Page 2: ...art material for preflight planning and application of the prescribed operating procedures will result in optimum effectiveness of the aircraft Part 5 ENDURANCE Fouled Deck Endurance Maximum Endurance...

Page 3: ...at a ltitude to speed of sound at sea leveL CAO standard day Aliernating current Automatic direction finding Altitude Degrees Centigrade Calibrated a irspeed LAS cOITected for position rror CC nter o...

Page 4: ...quires a method of data presentation that can reflect a var iable external configur ation This method is called the Drag Count Index System In the Drag Count Index System each ilem of the ex ter nal s...

Page 5: ...4 1 RACK PYLONS ON STATION1l3 75 lANDS 128 TWO JOe GALLON AERO lO EXTERNAL FUEL TANKS EMPTYl_____ 398 ARMORP LATE__ ___ __ ____ __ 101 TOTAL OPERATINGWEIGHT EMPTY _ _ _ 12 437 l J REFER TO NAVAIR Ol 4...

Page 6: ...RO 20A I 1 2239 199 H Fin Fl U EMPTy 2 IOO Gi L F uel Tank AEBO 7A I 2960 240 Ft LL iEJ l PTy 2 300 GA L Hefueling AEHO 7A I 2765 725 Store FrLLI EM PTy 2 GTC POO AERO 20A I 7A I SA5 4i7 Mounted f L L...

Page 7: ...y at a par ticular a ltitude True airspeed is related to equivalent airspeed by the following KTAS KEAS x 1 fU The quantity 1 fli may be found in figures 11 3 and 11 5 Part 1 To convert calibrated air...

Page 8: ...1 00 0 0 0 70 00 0 60 600 Z z u c Ii 0 50 0 0 0 20 f jl 3i 60 KNOTS PRESSURE ALTITUDE 25 000 FEET 1 T R U E M A C H N U M B R 01 84 TRUE AIRSPEED DAY 517 I cuo 100 00 00 CAUSIAUD AIRSPEED KNOTS Figur...

Page 9: ...ALTITUDE CHART _80 60 0 _20 0 20 TEMPERATURE DEGREES CENTIGRADE TEMPERATURE DEGREES FAHRENHEIT 40 _140_120 _100_80 _60 _40 20 0 20 40 60 0 100 120 40 65 70 75 0 as 90 95 1 00 1 05 1 10 1 15 TEMPERATUR...

Page 10: ...8 17 6 40 56 2 7 19 4 48 54 4 6 21 2 47 52 6 5 23 0 46 50 8 4 24 8 45 49 0 3 26 6 44 4 7 2 2 28 4 43 45 4 1 30 2 42 43 6 0 32 0 41 41 8 1 33 8 40 40 0 2 35 6 39 38 2 3 37 4 38 36 4 4 39 2 37 34 6 5 4...

Page 11: ...54 1 520G 36 511 33 no I 5480 3 1 493 37 2SG I S762 40 474 40 852 1 6052 42 4 5 44 419 1 6349 4 1 13 47 98 1 66501 10 417 1 551 1 6968 4 39V 55 117 I 7291 50 379 58 6 13 1 7623 52 361 62 24 9 I One in...

Page 12: ...4 2 6892 2 7540 2 8216 2 8903 2 960 3 0326 3 1063 3 18 19 3 2593 3 3386 3 4198 3 S029 3 5881 3 6754 56 500 69 700 0 7534 0 7525 0 751D 0 7 519 l Onc in of H 70 732 lb pe r sq rt 0 4912 Ib per sq in OA...

Page 13: ...ents an ar ea in which the minimum acceptable thrust to weight ratio may be encountered resulting in marginal climbout capability or the sale tire limit speed of 175 knots ground speed may be ex ceede...

Page 14: ...J1 8 the aircraft is climbing out with MILITARY thrust with the assist of ground effect multiple carl iage stores are carried on wing 11 18 stations and wing flaps are set ilt the half flaps position...

Page 15: ...owing reasons 1 USing a time interval from brake release is onsidered to be too inaccurate 2 Using airspeed as a reference for JATO firing would not be possible since generally JATO firing occurs at a...

Page 16: ...at which engine failure pernlits stopping the aircraft on a run S way of specified length F igures 11 12 and 11 14 1 present this data for engine failure during a militar y thrust takeoff without JATO...

Page 17: ...this critical s tage of the takeoff abort it is recommended that flaps be II left in the pOSition selected for takeoff Figure 11 13 is without drag chute deployed and figu re 11 15 is with drag chute...

Page 18: ...AL 180 NOSEUP TRIM NO JATO DATA AS OF 1 DECEMBER 1970 DATA BASIS FLIGHT TEST INAVY TTrrMn rnc r rJ I 1 j 0 I _t t AK EOFF AlRSP Efl 1 t r 1 IMOM rJiJt 6 F WI 1GHT 1 AT IE LIMITED BV SAfE L y f1 E SPEE...

Page 19: ...4 SOOt pdU DS If itt t tf t 1 r I 2 I r 23 i w r h 22 I 11 4 r j t 21 1 l t 20 1 19 r r I t 1 rt t t 1 T lTtHt f 1 rs Ip iI iI I 1 b p t I I I fO ff 1 I t I I 18 NOTE 17 20 WHEN USING C l1 e ll _1 CAT...

Page 20: ...The d 1 1a are based on the climb speed schedule shown in fig ure 11 16 SAMPLE PROBLEM Climb Speed Schedule For figure 11 16 A Cruise altitude B Drag index C Climb speed at cruise altitude D Initial...

Page 21: ...und of fuel are presented in figure 11 20 The d t ar e presented as a function of gross weight and drag Index SAMPLE PROBLEM Combat Ceiling and Optimum Cruise Altitude For figure 11 20 11 32 CRUISE AL...

Page 22: ...3 0 20 Q 8 c 10 Q NAVAffi Ol 40AVM l CLIMB SPEED SCHEDULE MILITARY THRUST DATA AS OF 1 DECEMBER 1970 DATA BASIS ESTIMATED f r I o 200 250 300 350 00 50 CALIBRATED AIRSPEED _ KNOTS Figure 11 16 Climb S...

Page 23: ...ODEL A 4M FUEl USED ENGINE J52 P 40 26 24 w Q Q Z 22 0 8 w 20 w 18 w 16 Z 14 12 w z w 8 g o oif __ __ I L I I I I I I I I o 20 10 o 11 34 l J TEMPERATURE C Figure 11 17 Climb Fuel ALTITUDE 1000 Fl o 5...

Page 24: ...S2 P 408 DATA AS Of 1 DECEMBER 1970 DATA BASIS ESTIMATED 0 8 z 11 0 0 o 810 18 Z 11 z w J1 E t m C O lOER 1 10 10 0 6 TEMPERATURE _ C 1 1 L T _ l 1tt f 7 001 I I r 150 LL 71 tr A Ni D O Y OPTIMUM l r...

Page 25: ...MILITARY THRUST CLIMB TIME TO CLIMB 1 oJ DATA AS OF 1 DECEMBER 1970 DATA BASIS ESTIMATED p P 1 0 1 Ud llO STAND q DAY OPTIMUM qRU SE I LI ALTITUDE T DR o it Y J v 11 Ht V jib r I r T t f l ALTITUDE T...

Page 26: ...L A 4M ENGINE J52 P 408 DATA AS OF 1 DECEMBER 1970 DATA BASIS ESTIMATED Fi friH f_ FPM I e r F I m 1 L t i j ff 4 h l 12 14 16 20 GROSS WEIGHT 1000 POUNDS t _ 1 I I t 1 Htfl n dj it LffilI f t Illtl F...

Page 27: ...nfigu ration consists of four empty wing pylons plus guns with a total drag index of 33 Climb speeds and air speeds for maximum range are included in the chart as well as letdown ins tructions The tim...

Page 28: ...l O 0 0 9 l8 0 00 o 66 O 2 1 O 7 1 O 1 6 0 017 O S 3 O 2 O 16 O l53 0 927 O iI I9 O 70 0 40 O laS 0 93 0 910 O I O I 0 962 0 9 1 0 919 O 9 II 73 0 994 0 963 o n 0 9 1 O 41 0 995 O 9 9 O ISO O l O I 0...

Page 29: ...5 000 Feet Bange Hange Optimum 35 000 Optimum Optimum Altitl lde Feet Altitude AltItude Feet NMI NMI Feet 40 000 5 J8 571 40 000 40 000 452 m 40 000 40 000 403 420 40 000 40 000 353 368 40 000 40 000...

Page 30: ...eed Military Thrust CruIS Speed KCAS Mach No KCAS 340 275 340 270 340 265 140 260 140 255 0 764 250 0 764 240 0 764 225 0 764 210 0 76 1 200 If You AI at 10 000 Fu t Hange Optimum Optimum Altitude Alt...

Page 31: ...00 ao ooo W OOO ao ooo 30 000 25 000 20 000 0 000 Optimum Altitude Fpet 30 000 30 000 30 000 30 000 1O 000 30 000 1O 000 30 000 25 000 Ha nge at 10 000 FeN J 18 13 1 115 82 40 33 HrUlg e at 30 000 Fce...

Page 32: ...R O l 40AVM l LONG RANGE CRUISE MACH NUMBER AND EPR MODEL A 4M DATA AS OF 15 OCTOBER 1971 ENGINE J52 p 40a DATA BASIS ESTIMATED 3 4 2 c Z o 2 22 o I w I w 12 11 44 Figure 11 25 Long Range Cruise Mach...

Page 33: ...RANGE CRUISE ALTITUDE AT DRAG INDEX o 00 PRESSURE ALTITUDE 1000 F1 o 5 10 15 20 25 30 35 40 SPECIFIC RANGE Section Xl Part 4 ICAO STANDARD TEMP _ C 15 0 5 1 4 8 14 7 24 6 34 5 44 4 54 3 56 S 0 _ NAUTI...

Page 34: ...SE Maximum Range Cruise charts shown in figures 11 27 11 28 and 11 29 present the necessary m ission planning data to set up maximum range cruise schedules for a constant cru ise altitude To I usc the...

Page 35: ...ction XI Part 4 DATA AS OF 15 OCTOBER 1971 DATA BASIS ESTIMATED OPTIMUM CRUISE ALTITUDE AT DRAG INDEX w z I il m 0 100 00 w Z i 1 w I 80 70 60 SO 40 30 _ 0 0 011 So I IV vb lIrIC sr 1V I 0 I II II l 5...

Page 36: ...RESSURE ICAO ALTITUDE STANDARD 1000 FT TEMP C I I I I I OPTIMUM CRUISE ALTITUDE AT DRAG INDEX o I y1 oo 200 0 5 10 15 20 25 30 35 40 SPECIFIC RANGE 15 0 5 1 4 14 7 24 6 34 5 44 4 54 3 56 5 NAUTICAL MI...

Page 37: ...IR Ol 40AVM l MAXIMUM RANGE CRUISE fUEL Section Xl Part 4 MODEL A 4M ENGINE J 52 P 408 DATA AS OF 15 OCTOBER 1971 DATA BASIS ESTIMATED o 1000 2000 3000 4000 5000 7000 FUEL FLOW POUNDS PER HOUR Figure...

Page 38: ...w J Time 28 a m n tl SO SAMPLE MAXIMUM RANGE CRUISE TIME AND SPEED FA1 1S6 Maximum Range Cruise Nautical Miles per Pound of Fu el For figure 11 2 8 K Average gross weight 18 000 II L Cruise altitude...

Page 39: ...ng W range cruise To usc the Nauticall Iiles PCI Pound of Fue l charts the average gross weight pressure altitude cruise Mach number drag index and ambient air lemperalure must be known It is then pos...

Page 40: ...ED 10 __ 20 s MACH NUMBER FOR MAXIMUM RANGE CRUISE AT DRAG INDEX o 100 200 30 WEIGHT amb 1000 POUN ___ 70 __ r ll 80 f lh I 1 t 1 2 3 4 5 6 7 9 10 2 3 4 5 6 7 S 13 9 Q Z o TRUE MACH NUMBER 26 24 22 20...

Page 41: ...XI Part 4 NAUTICAL MILES PER POUND OF FUEL MODEL A 4M ENGINE J52 P 408 DATA AS OF 15 OCTOBER 1971 DATA BASIS ESTIMATED j 8 J w Z J U w 11 t 12 L j t I ttB l b r 13 f 9 8 7 6 s 4 3 t i f 2 F igur e 11...

Page 42: ...ER POUND OF FUEL MODEL A 4M ENGINE JS2 P 408 DATA AS OF 1S OCTOBER 1971 DATA BASIS ESTIMATED 5 SS MACH NUMBER 2 v o 4 3 2 40 30 20 10 o S 10 20 c 30 Z iii 40 IE 50 60 70 80 11 54 3 4 5 6 7 8 9 FA1 173...

Page 43: ...Part 4 NAUTICAL MILES PER POUND OF FUEL MODEL A 4M ENGINE J52 P 408 DATA AS OF 15 OCTOBER 1971 DATA BASIS ESTIMATED 2 3 4 Nl 25 45 65 5 GENERALIZED FUEL FLOW PARAMETER 7 UNCORRECTED FOR RNII Figure 11...

Page 44: ...AND 85 70 60 50 40 30 DATA AS OF 15 OCTOBER 1971 DATA BASIS ESTIMATED PRESSURE ICAO ALTITUDE STANDARD 1000 FT TEMP _ C 0 15 0 5 5 1 10 4 B 15 14 7 20 24 6 25 34 5 30 44 4 3 54 3 40 56 5 45 56 5 50 45...

Page 45: ...1S u Z 10 OS 0 NAVAIR Ol 40AVM l NAUTICAL MILES PER POUND OF FUEL MODEL A 4M ENGINE JS2 P 408 100 DATA AS OF 15 OCTOBER 1971 DATA BASIS ESTIMATED 200 300 400 SOO 600 TRUE AIRSPEED KNOTS Figure 11 30...

Page 46: ...ch number IN Reynolds number index RNI 11 58 NAVAlR 01 40AVM l 6225 0 75 100 8820 FlI l I O _44 40C 30 000 ft 0 75 0 503 SAMPLE NAUTICAL MILES PER POUND OF FUEl Nauticol Miles per Pound of Fu el For f...

Page 47: ...ruise Mach number W Pressure altitude X Ambient air temperature Y Nautical miles pel pound of fuel NAVAlR 01 40AVM l FA 1 162 6 41 0 75 30 000 ft _44 40C 0 114 SAMPLE NAUTICAL MILES PER POUND OF FUEl...

Page 48: ...NAUTICAL MILES PER POUND OF FUEl NAVAlR Ol 40AVM l SAMPLE PROBLEM O 174 Engine Pressure Ratio for Cruise 2550 Ib hr For figure 11 31 F Total thrust required a amb 8820lb G True Mach number O 75 d H En...

Page 49: ...RATIO FOR CRUISE Sectior XI Part 4 MODn A 4M ENGINE JS2 P 408 DATA AS OF 15 OCTOBER 1971 DATA BASIS ESTIMATED t 1 0 1 2 1 4 1 6 1 8 2 0 2 2 2 4 2 6 2 8 3 0 3 2 3 4 3 6 ENGINE PRESSURE RATIO T IP T 0 F...

Page 50: ...peeds and airspeeds for maximum endurance are included in the chart together with letdown instructions The time at which letdown should be initiated is given in terms of fuel on board and r epresents...

Page 51: ...ptimum Fcct ltHudc Altitude Feel AILilUdc Altitude Minutcs Minutes t l Ct Alinutcs Minutes Fl et 2300 OJ 35 000 i7 35 000 1900 7S 0 3 i 000 81 S 35 000 1700 70 35 000 73 73 35 000 1500 62 1 Li OOO 65...

Page 52: ...You Arc at 30 000 Fect 35 000 eel 10 000 Feet Endurance Endurance Endurance Endurance Endurance at Optimum Optimum at 35 000 at OpUmum Optimum at 40 000 at OptinlUm Optimum Altitude Altitude Feet Alt...

Page 53: ...l l 1 000 100 1 1 10 000 10 10 10 uoo If You Arc It 20 000 FcC If you Are at lO OOO feCI I Endurance Enduranec EndUl ancc f ntiul lncc a t 20 000 at 0 timum Optimum al 30 000 at 0pllmum Optimum Feet A...

Page 54: ...NGINE JS2 P 408 NAVAIR O l 40AVM l Section XI Part 5 MAXIMUM ENDURANCE SPEED DATA AS OF 15 DECEMBER 1971 DATA 8ASIS ESTIMATED 26 o z 2 0 L 20 z W 18 o 16 M 100 150 200 250 300 350 400 450 500 CALIBRAT...

Page 55: ...rees r 1 1711 IL Loiter pressur e altitude 25 000 It 1M Temperatu re deviation rrom ICAO standard Ambient temper ature 24 50C 10oC SAMPLE PROBLEM IN Drag index 100 IP Loiter pr essur e altitude 25 000...

Page 56: ...r DEVIATION FROM O t re i PTl r T Z 2S ICAO STANDARD Lu W C I 20 SO I I 11 I t I II t H I 1 14 i 1 1 PRESSURE ICAO l rlf ALTITUDE STANDARD I L L 1000 FT rEMP C J a u 15 0 1k 5 5 1 _ l 10 4 1f f 15 14...

Page 57: ...sea level are presented as a function of gross weight and drag index All data is based on an ICAO standard atmospher e The method of presenting data for fuel distance and time is identical Therefore...

Page 58: ...I MODEL A 4M ENGINE JS2 P 408 0 12 150 125 100 Q Z 0 75 w SO r 2S 0 11 80 NAVAJR 01 40AVM l DESCENT FUEL IDLE THRUST GEAR UP FLAPS UP SPEEDBRAKES RETRACTED L t DATA AS Of 1 DECEMBER 1970 DATA BASIS ES...

Page 59: ...L A 4M DATA AS OF 1 DECEMBER 1970 ENGINE JS2 P 408 DATA BASIS ESTIMATED o l DRAG INDEX 0 100 200 12 185 175 5 l ll o t J L DESCENT SPEED SCHEDULE KCAS GROSS WEIGHT 1000 POUNDS 14 18 20 22 200 215 225...

Page 60: ...ill 0 I II 25 20 w 15 E I w 10 E 5 0 11 82 MODEL A 4M ENGINE JS2 P 408 0 NAVAIR Ol 40AVM l DE5CENT TIME IDLE THRUST GEAR UP FLAPS UP SPEEDBRAKES RETRACTED DATA AS OF 1 DECEMBER 1970 DATA BASIS ESTIMAT...

Page 61: ...urning radius is the use of a dime on an ONe l 1 000 000 or a quarter on a PC J 500 000 SAMPLE PROBLEM Turning Radius For rtgurc 11 4 7 From ManeU erabUity Sample Problem ure J1 48 Mach Number Normal...

Page 62: ...RADIUS 400 300 200 100 5 50 10 1 0 5 1 2 DISTANCE TRAVElED IN TURN 11000 FEET NAUTICAL MILES 150 100 5 4 3 2 1 0 5 30 20 10 5 4 3 2 1 0 4 3 2 1 TURN RADIUS 11000 FEET NAUTICAL MILES 10 1 02 1 05 20 1...

Page 63: ...0 3 NAVAIR Ol 40AVM l Section XI Part 9 MANEUVERABILITY MILITARY THRUST SEA LEVEL STANDARD DAY I I I GEAR UP DATA AS OF 1 DECEMBER 1970 DATA BASIS ESTIMATED tT T r fTTC r S U u liMIT 1 1 f t J 0 4 0 5...

Page 64: ...RY THRUST 10 000 FEET STANDARD DAY GEAR UP MODEl A 4M DATA AS OF 1 DECEMBER 1970 ENGINE JS2 P 408 DATA BASIS ESTIMATED 90 80 70 c Z 0 60 iii 50 0 X 40 0 u c 30 0 0 20 Z 10 o 0 2 0 3 0 4 0 5 0 6 0 7 0...

Page 65: ...48 sheet 1 Altitude Gross weight A Mach number B Drag index C Normal load factor x gross weight Gross weight Nor mal load factor at zero longitudinlll acceiel a tion Sea level 18 000 lb O 75 50 69 00...

Page 66: ...49 as a function of 11 98 and 10 000 feel Military th rust fuel flow is pre sented in fib ure 11 50 as a fUllction of pressure altitude and Mach nu mber SAMPLE PROBLEM Maximum Mach Numbe r For figu r...

Page 67: ...A 4M ENGINE J52 P 40fl DATA AS OF 1 DECEMBER 1970 DATA BASIS ESTIMATED U r issu 0 Hl t L 1 f 4 I I r j TI L lJ l H o 40 I o 40 G dss WEIG J noo0jJ 6tl L 1 111 h if 12 t 718 vV it c r r j 80 120 DRAG...

Page 68: ...12 8 MODEL A 4M ENGINE JS2 P 408 o 40 60 80 NAVAIR 01 40AVM 1 MILITARY FUEL FLOW ICAO STANDARD ATMOSPHERE DATA AS OF 1 DECEMBER 1970 DATA BASIS ESTIMATED 100 120 140 160 180 FUEL FLOW POUNDS PER MINU...

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