Navair Navy F-8E Скачать руководство пользователя | Manualshive

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Содержание Navy F-8E

Страница 1: ...UBLICATION SUPERSEDES NAVWEPS 01 45HHD 1 DATED 1 APRIL 1964 CHANGED 1 SEPTEMBER 1964 WHICH SHOULD BE REMOVED FROM THE FIL ES AND DESTROYED ISSUED BY AUTHORITY OF THE CHIIiF OF NAVAL OPERATIONS AND UND...

Страница 2: ...nsert these pages into basic publication Destroy superseded pages NAVAIR 01 45HHD 1 NATOPS FLIGHT MANUAL NAVY MODEL F SD F SE AIRCRAFT ISSUED BY AUTHORITY OF THE CHIEF OF NAVAL OPERATIONS AND UNDER TH...

Страница 3: ...66 104C 1 Dec 1966 8 15 Jul 1966 1040 1 Dec 1966 10 15 Jan 1967 105 15 Jul 1965 11 J5 Jul 1965 107 15 Jul 1965 14 15 Jul 1966 112 15 Jul 1966 18_ 15 Jul 1966 113 15 Jui 1966 19 15 Jul 1966 115 15 Jul...

Страница 4: ...7 178 15 Jul 1966 229 15 Jan 1967 179 15 Jul 1966 230 15 Jan 1967 180 15 Jul 1966 231 15 Jan 1967 181 15 Jul 1965 232 15 Jan 1967 183 15 Jul 1966 233 15 Jan 1967 184 15 Jul 1966 234 15 Jan 1967 185 15...

Страница 5: ...l 1966 246L 15 Jan 1967 262 15 Jul 1966 246M 15 Jan 1967 263 15 Jul 1966 246N 15 Jan 1967 264 15 Jul 1966 246P 15 Jan 1967 265 15 Jul 1966 246Q 15 Jan 1967 266 15 Jul 1966 246R 15 Jan 1967 267 15 Jul...

Страница 6: ...ing progressive profession it is both desirable and necessary that new ideas and new techniques be expeditiously evaluated and incorporated if proven to be sound To this end Type Fleet Air Group Air W...

Страница 7: ...E PAGES PURPOSE AFFECTED 1 through 5 Previously incorporated or cancelled 6 9 26 63 Ou Scanding Adds supersonic towing procedures and limits 5 6 64 Outstanding Adds procedures for air pickup 7 of dan...

Страница 8: ...ight Procedures_ _ Pari 2 Flight Characteristics Section V EMERGENCY PROCEDURES 165 Pari 1 Ground Emergencies Pari 2 Takeoff Emergencies Pari 3 Inflight Emergencies Pari 4 Landing Emergencies Section...

Страница 9: ...ents and operating limitations Part 1 provides a general description of the aircraft console and instru ment board illustrations and a description of the engine and afterburner Pare 2 describes aircra...

Страница 10: ...n the same manner as the NATOPS Flight Manual Cbanges to them are concurrent with and dated the same as the NATOPS Flight Manuals Changed 15 July 1966 UP DATING THE MANUAL To ensure that the manual co...

Страница 11: ...robe illuminating light for in flight refueling at night Provides for photographing radarscope dis plays Installs provisions for usc of an external pressure gage to monitOr wing fuel tank trapped air...

Страница 12: ...tion seat installation in the aircraft Adds GARO guns automatic ranging only mode of radar operation Permits emergency replies to be transmitted when a mode 3 interrogation is received with IFF master...

Страница 13: ...NAVAIR 01 45HHD 1 F 80 F 8E Figure I J viii Changed 15 July 1966...

Страница 14: ...____________________________________________________________________________ 46 Fuel System _ ____________________________________________________________ 47 Inflight Refueling _______________________...

Страница 15: ...AIRCRAFT OPERATING LIMITATIONS Introduction _ _ __ __ _ ________ ______________________________ 98 Instrument Markings ____________ 98 Airspeed Limitations _ _______ ___________ 98 Power Control Hydra...

Страница 16: ...__________________________________141 4 in_ Incidence at mean aerodynamic chord _ _ _____ _______ _____ ____ _ ____ _________ _______________ _______ __ _ 10 Sweepback of 4 chord line_________________...

Страница 17: ...mera Fire Control Radar Antenna External Electrical Power Recepticle TACAN Antenna Speed Brake Forward Transfer Fuel Cell Radio Altimeter Receiver Transmitter and Antenna Inllight Refueling Probe Figu...

Страница 18: ...ngine pressure ratio indicator 8 Tachometer 22 Fuel transfer switch 36 Nose trim indicator 23 Fuel transfer pump caution light 37 Armament panel 9 AngIe oF attack indicator 24 Clock 38 Oil cooler door...

Страница 19: ...el dump switch 22 Fuel transfer switch 23 Fuel transfer pump caution light 24 Clock 25 UHF preset channel indicator 26 Oxygen warning light 27 Transfer fuel quantity indicator 28 Hydraulic pressure in...

Страница 20: ...hand switch panel 14 Engine master switch 15 Yaw stabilization switch 16 Emergency pitch trim handle 17 Yaw stabilization light 18 Roll stabilization light 19 Autopilot master switch 20 Autopilot hea...

Страница 21: ...aster switch 15 Yaw stabilization switch 16 Emergency pitch trim handle 17 Yaw stabilization light 18 Roll stabilization light 19 Autopilot master switch 20 Autopilot heading hold disable switch 21 Em...

Страница 22: ...conditioning panel 9 Autopilot control panel 10 TACAN panel 11 Exterior lights control panel 11 A Interior lights control panel 12 Armament panel dimming knob 13 Cockp it emergency air ventilation kno...

Страница 23: ...terior lights control panel Armament panel dimming knob NAVAIR 01 45HHD l 13 14 15 16 17 18 19 20 21 22 23 24 Cockpit emergency air ventilation knob W ingfold controls Approach light hook bypass switc...

Страница 24: ...ne oil pressure indicator II figure 1 3 Eogine oil hydraulic pressure warning light 25 figure 1 3 Engine pressure ratio indicator 7 figure 1 3 Exhaust temperature indicator 45 figu re 1 3 Fuel flow in...

Страница 25: ...ntrif ugal booster stage and separate gear stages for the engine and afterburner The pump mounts a transfer valve which routes afterburner fuel to an internal recirculating line when the afterburner i...

Страница 26: ...ansfer Valve From Main Fuel Cell Engine Fuel Shutoff Valve Pump Transfer Valve I J dj i 1 Engine Fuel Normal Flow Engine Fuel Manifold Figure 1 6 I i I i Engine Fuel Emergency Flow _ i M il Afterburne...

Страница 27: ...m air from the engine intake passes through the radiator and overboard A pressure ratio switch automatically opens the oil cooler door to relieve ram air pressure in the intake duct unless a missile i...

Страница 28: ...persist and exhaust temperature does not return to normal following a stall land as soon as practical Continued engine operation with unstable engine con ditions is dangerous AFTERBURNER OPERATION Af...

Страница 29: ...nozzle actuator control to direct engine compressor bleed air to the eight exhaust nozzle flap actuators The actuators are mechanically linked to the exhaust nozzle flaps and hold the flaps open 16 du...

Страница 30: ...ss of all air conditioning and pressurization functions The temperature of the air entering the cockpit is controlled by mixing hot air from the temperature control bypass valve with cold air from the...

Страница 31: ...ature knob 8 figure 1 12 Cockpit pressure altimeter 3 figure 1 12 Cockpit emergency ventilation knob 4 figure 1 12 Manual override switch 9 figure 1 12 Antiexposure coverall ventilation switch decaled...

Страница 32: ...mp e rature Controller eNI Ram Air Volve t Aircraft before BuNo ______ _I Air 150672 Without ASC 4 17 have on external inlet connection for the anti exposure covera ll and a diffe rent anti exposure...

Страница 33: ...NAVWEPS 01 45HHD l I 20...

Страница 34: ...efogger switch 6 Rain removal switch 7 Cockpit pressure switch 8 Temperature knob 9 Manual override switch 10 G valve 11 G valve button llA Anti exposure coverall ventilation switch 12 Anti exposure c...

Страница 35: ...as altitude is gained If the rain removal system has not been oper ated for several flights oil accumulation in the system may result in oil being blown on the windscreen when the system is first act...

Страница 36: ...Units Pointer a t or lower edge of approa ch index marke r NAVAIR 01 45HHD l TRANSDUCER Section I Systems 0 00 APPROACH INDICATOR INDEXER LIGHTS Approach speed more than 5 knots SLOW Angle of attack...

Страница 37: ...per sequence Also observe the airspeed indicator to verify that the recommended angle of attack corresponds to the correct approach airspeed The approach is flown by coordinating throttle and stick mo...

Страница 38: ...retard the throttie below approxi mately 75 rpm Upon touchdown compression of the mai n landing gear shock Strut actuates the deck compress switch to cause the system to disengage autO matically leavi...

Страница 39: ...rapid which could result In compressor stall and engine flameout 1 Aircraft LANDING CONFIGURATION 2 Throttle friction wheel MINIMUM FRICfION 3 Fuel control switch NORMAL 4 Cockpit emergency ventilatio...

Страница 40: ...re and with loss of hydraulic pressure by a mechanical uplock latch The hook is held extended by overcenter locking gear linkage which is connected to a spring loaded linkage unlock ing cylinder Appro...

Страница 41: ...eking the selected heading When the bank controller is actuated to select an angle of bank greater than 50 and the aircraft responds the heading hold function will automatically disengage then re enga...

Страница 42: ...pitch reference altitude signals amplifier attitude hold when altitude to make cwe on hold d engaged I ROLL CONTROL HEADING SYNCHRONIZER I Sense deviations from engagement reference direction signal...

Страница 43: ...T CONTROLS 30 1 Autopilot master switch 2 Heading hold disable switch 3 Autopilot engage light 4 Pitch trim knob 5 Roll tri n knob 6 En9age disengage switch 7 Bank control knob 8 Altitude hold engage...

Страница 44: ...itude up I to 70 right Or left and at rates of climb or dive up to 2 000 feet per minute Heading hold is engaged any time normal mode is selected and wing position is within 5 of level unless the head...

Страница 45: ...as desired Disengage at completion of letdown CLIMB Trim Airplane for climb Engage Autopilot Maintain Mach No with Pitch Trim Bank Controller as required for Turns Yaw Trim as required DESCENT See DES...

Страница 46: ...handles Pulled out to full length of lanyard fires canopy actuator to release canopy locks and open canopy EJECTION SEAT DESCRIPTION The ejection system utilizes either the Martin Baker MK F5 or MK F...

Страница 47: ...I Section I Systems CANOPY 34 I NAVWEPS Ol 45HHD l Figure 1 19...

Страница 48: ...22 for a list of pilot s equip ment that may be used with the Martin Baker seat EMERGENCY RELEASE FROM THE SEAT In landing emergencies in ditching and in the event of the automatic release failing to...

Страница 49: ...i ng haneli e o i J Leg r estraint lines A 1 Link Line 2 Drogue pa rachute withdrawal line 2A Top latc h mechanism 3 Emer gency release h llillotine 4 Drogue 6 l l n 5 Drogue gun Ir ip rod 6 Canopy in...

Страница 50: ...move upward the drogue gun firing mechanism and timed release mechanism trip rods are pulled free and both mechanisms are armed F the drogue gun is fired after 1 second delay O 5 second delay MK F5 se...

Страница 51: ...of the pilot and seat two friction fastenings sticker tabs briefly restrain the pilot in the seat after harness release occurs Seat and occupant stabilized and de celerated by drogues At 1 75 seconds...

Страница 52: ...and exposure coverall and type Z 4 anti g suit 2 Type A13 A face mask 3 Type APH 5 helmet 4 Mini Reg hose 5 MK 3C flotation vest 6 Oxygen hose P 4932010 3 or IS Pirewe1 FOR USE IN MARTIN BAKER EJECTIO...

Страница 53: ...rectifier which supplies power to the dc ELECTRICAL SUPPLY SYSTEM CONTROLS Nomenclature Main generator indicator 24 figure 1 5 Master generator switch 23 figure 1 5 Emergency generator switch 7 figure...

Страница 54: ...Main fuel q uanti ty O xygen quantity Pitol heal TACAN radia Tail position light Transfer fuel quantity Yaw trim and stabilization Ex ternal AC Power Aircraft AC Power Aircraft DC Pow er Figure 1 23 S...

Страница 55: ...ator warning light Engine cranking control Integrated electronics package ADF radio IFF radar identification UHF command radio Jettison missile MA l compass Speedbroke TACAN radio Yow trim and stabili...

Страница 56: ...ce Refer to ANGLE OF ATTACK INDICAT ING this section for information concerning sequence of approach light op ration An exterior light master control circuit is provided with a switch located above th...

Страница 57: ...ting in illumination of the fire warning light The system is comprised of the warning light detection control assembly and heat sensing elements Electrical power is provided by the emergency de bus Th...

Страница 58: ...linkage from the wing to the aileron power control hydraulic slider valves and the flap segment inboard of the ailerons Aileron droop and lap action provide increased lift and stability when the wing...

Страница 59: ...d indicated Mach number readings of 0 4 to 2 5 An airspeed correction card provides calibrated ai r speed data Conventional picot tube anti icing is pro vided 46 RATE Of CLIMB INDICATOR T his indicato...

Страница 60: ...central point fueling for selection of different types of fuel loads or for defueling POWER OFF is the Hight position PRESS DUMP relieves wing tank pressure and shuts off transfer fuel pumps to dis co...

Страница 61: ...uel Boost Forward Transfer Cell And Regulator For Increa sed Compressor Dumping Pressure Bleed AjlQ Y r To gli ti _ l Fuseloge orjtf i Cells Ram Air _ _ Dump Valve Fuel Quantity Probe Typ Forward Tran...

Страница 62: ...ssurization and venting maintain a constant pres sure in the fuel cells and cell cavities during climbs dives fueling defueling and fuel transfer Air pres sure is used to transfer wing tank fuel Press...

Страница 63: ...Section I NAVAIR 01 45HHD l I 48 B Changed 15 July 1966...

Страница 64: ...ward transfer cell empties first the aft transfer cells empty second and the wing tank empties last The aircraft then consumes main cell fuel until landing During transfer from the aft cells there wil...

Страница 65: ...ed nose down attitudes and when there are approximately 1 500 pounds re maining in the transfer system in certain other flight profiles But in no case shall it read below 2 200 pounds before the trans...

Страница 66: ...ced in CABIN DUMP wing tank fuel dumping may be accomplished at a reduced rate under pressure supplied by the wing tank emergency ram air scoop INFLIGHT REFUELING DESCRIPTION Note The inflight refueli...

Страница 67: ...ling probe switch in the IN position will reenergize the transfer system and reposition the fuel valves for normal opera tion retract the probe and close the fairing door IHold the switch IN for 5 sec...

Страница 68: ...tity indicator Main fuel quantity indicator Missile release indicatOr Oil cooler door indicator Pressure ratio indicator Standby compass Pri71UJry lights Airspeed Mach number indicator Instrument boar...

Страница 69: ...anel relocated to rear of right console after AFC 490 Parts I and II o o o 00 00 0 0 00 00 o I Chart board light switch 2 Emergency flood light switch 3 Approach indexer dimming knob 4 Flight instrume...

Страница 70: ...ation The armament system is dearmed when the landing gear handle is down and the approach lights are energized when the gear is extended LANDING GEAR CONTROLS NomctlcltJture Landing gear handle 23 fi...

Страница 71: ...y Hydrauli Return 00 Utility Hydrauli Pressu 1 To left Hand Main Gear landing Gear Indicators 7 Emergency Air Control Volve 8 Deleted 9 Door Cylinder 10 Main Gear Door 11 Main Gear Cylinder 12 Down lo...

Страница 72: ...r following loss of utility hydraulic pres sure However the pneumatic system also can be effec tive in extending the gear in some cases where utility hydraulic pressure remains but has proven ineffect...

Страница 73: ...k 6 h om 7 Emergency Air Control Valve 8 Deleted 9 Door Cylinder 10 Main Gear Door 11 Main Gear Cylinder cc a Pneumatic Supply To Opposite Side 12 Down Lock Indicator Microswitch 13 Bypass Valve To le...

Страница 74: ...ation NORMAL OPERATION Slaved Method 1 Power failure indicator flag NOT SHOWING 2 Mode selector switch AFTER 2 MINUTE WARMUP PLACE IN SLAVED MA l COMPASS CONTROLS Nomenclature Compass setting knob 7 f...

Страница 75: ...moves in correct direction and is centered 1 Power failure flag NOT SHOWING 2 Mode selector switch FREE N LAT or FREE S LAT After 2 minute warmup set selector to hemi sphere in which you are flying 3...

Страница 76: ...d at the begin ning of the film at some time before initiating the radar or IR intercept Using a grease pencil write the desired information on the transparent tider that comes with the camera set or...

Страница 77: ...ilm magazine door S Film magazine door latches 6 Velcro tape connector stowage 7 FilmMremaining light 8 Camera on light 9 Camera erector assembly 10 Camera electrical connector 11 Test switch 12 Inten...

Страница 78: ...the power switch in ON before closing the door The switch can be returned to OFF after the door has been closed The door will not close if the magazine has been installed improperly Note Make sure by...

Страница 79: ...r stop engagement the full nose gear steering range is not available with the wing down Unpowered 360 nosewheel swivelling is available w hen the steering system is not actuated The system is energize...

Страница 80: ...is attached to the structure of the aircraft so as to activate the oxygen bottle automatically upon ejection IOxygen controls and indicators are illustrated in figure 1 34 2 System quantity CHECKED No...

Страница 81: ...ioning properly Following servicing in which the bottle has been filled the light will sometimes illuminate intermittently S Oxygen connections CH ECKeD 64 Complete or intermittent loss of radio commu...

Страница 82: ...systems The only difference in operation of the two systems is that the aileron spoilers and the yaw stabilization system operate only off the PC 2 system while roll stabilization operates only off th...

Страница 83: ...oiler Circuit Port CONTROL SURFACE IN MOVEMENT DOWN Control Stick Moved To Left 66 Emergency Pump Hydraulic Filler Reservoir Emergency Pressure Indicating Sw itch Pressure Pump Emergency Transmitter q...

Страница 84: ...Air Valve ressure e Ie a ve fig 1 29 2 To Gun Circuit fig 8 2 Eme rgency Power Package and Actuating Cylinder cu in To Wing Incidence and Landing Droop Emerge ncy Air Valve fig 1 44 Air Bottle Pneumat...

Страница 85: ...nutes before continuing Primary ac and dc bus power is connected to the modified UHF receiver transmitter IFF receiver trans mitter and an ADF electronic control amplifier in the electronic package th...

Страница 86: ...nd release Channel is correctly preset if index line assumes a vertical position Rotate sensitivity trim knob clockwise until a background noise is heard then slowly rotate COMMAND RADIO CONTROLS Chan...

Страница 87: ...elector switch DESIRED CHANNEL To stop operation The ANIARA 25 direction finder group operates in conjunction with the UHF command radio set ADF signals are received by the main receiver of the com ma...

Страница 88: ...witch OUT Note AN APX 6B should be energized master switch in NORM LOW or STDBY during every flight to minimi e the possibility of packag failure due to moisture condensation Function I p switch 4 fig...

Страница 89: ...NAVWEPS Ol 45HHD l Section I Systems IFF RADAR CONTROlS 1 Code selector dials 2 Master switch 3 Mode switches 4 li P switch Figure 1 38 73 I...

Страница 90: ...the dropout mask below the 0 scale mark WARNING I Radio altimeter indications become erroneous at airspeeds over 300 KIAS Aircraft bank angles of more than 300 will cause the pointer to become erratic...

Страница 91: ...low 90 second warmup_ 2_ Channel selector knobs DESIRED CHANNEL 3 Volume control MIDPOINT OF RANGE When operating in the air to air mode if more than one aircraft in a formation is If either REC or T...

Страница 92: ...50 000 feet to prevent damage to equipment as a result of arcing SPEED BRAKE DESCRIPTION The system is illustrated in figure 1 4l The speed brake is operated by utility hydraulic pres sure and can be...

Страница 93: ...e automatically closes and is inoperative until electrical power from the emergency power package is connected emergency generator switch in ON During ground operations a safety circuit pre vents open...

Страница 94: ...l stabilization warning light 18 figure 1 4 Rudder neutral trim light 1 figure 1 3 Rudder trim knob 28 figure 1 4 Yaw stabilization switch 13 figure 1 4 Yaw stabilization warning light 15 figure 1 4 P...

Страница 95: ...ate gyros as stick position changes 1 Roll trim and damping operates electrically from emergency buses and hydraulically from PC No 1 system 2 A monitor system maintains a constant check of 1 011 actu...

Страница 96: ...rom acceler ometer trim poten tiometer and aileron position potentiometer to yaw actuator Rudder trim potentiometer left hand console signals am that sur Aileron position potentiometer sig nals amplif...

Страница 97: ...h amplifier transmits normal and emergency trim signals to pitch trim actuator Also processes auto pilot correction and damping signals and transmits them to actuator _lIIIh Normal Trim Signals _ Emer...

Страница 98: ...atically effected by raising or lowering the wing WING INCIDENCE CHANGE CLEAN CONDITION Overridable Clean Condition Stops 9 12 Engaged Available Aileron Throw 15 Up and 15 Down Roll Damper In and Roll...

Страница 99: ...NG CONTROLS NomencLzture Cruise droop switch throttle grip Leading edge droop indicator 40 figure 1 3 Wing downlock handle 5 figure 1 4 Wing incidence release switch 8 figure 1 4 Wing incidence handle...

Страница 100: ...Valve 7 Restrictor Arrow denotes free flo w 8 Seque nce Val ve 9 Pressure Relief Val ve 10 Restrictor Relief Valve 11 Check Val ve 84 Figure 1 44 From land Droop Uplock Switches From Pneumatic Supply...

Страница 101: ...LOCK To raise the wing and extend the droop pneumatically 1 Wing downlock handle UNLOCK 2 Wing incidence handle DN 3 Emergency droop and wing incidence guard RAISE 4 Wing incidence release switch DEPR...

Страница 102: ...r 1 Pneumatic Supply Linkage Emergency Exhaust Air Accumulator Air NAVWEPS 01 4SHHD l Utility Hydraulic Return Preuure Relief Valve Pressure Shutoff Valve Check Valve Arrow denotes Free Flow Valve Fro...

Страница 103: ...000 psi for tbe operation of tbe utility hydraulic circuits Hydraulic pressure failure will be indicated I by illumination of the engine oil hydraulic pressure warning light 29 figure 1 3 I Illuminat...

Страница 104: ...ised or lowered W hen the wings are folded red warning liags figure 1 48 are extended mechanically and tbe lock safety latches are released At the same time a selector valve is mechanically posi tione...

Страница 105: ...ngs are NOT LOCKED in tho spread position if the warning flags are visible Check both left and right Do not clear tho airplane for flight if any warning flag is visible Red Wingfold Warning Flag Red W...

Страница 106: ...I Section I Systems NAVWEPS 01 45HHD 1 WINGFOlD SAFETY INSPECTION PORTS 90 LATCHED Forward Port UNLATCHED Forward Port Figure 1 49 LEFT WING TYPICAL LATCHED Aft Port UNLATCHED Aft Port InU I_...

Страница 107: ...e link snaps The throttle catapult handle on the left hand console permits the throttle lever to be held in full forward position during catapult acceleration without locking the throttle lever REAR V...

Страница 108: ...indicate approx imately 1 to 1Y2 psi during fueling if wing tank fueling and vent systems are functioning properly Should the gage reading exceed I Y2 psi stop fueling immediately 92 If the aircratt...

Страница 109: ...1749 grade A type I or type II liquid oxygen only Liquid oxygen boils at 183 C 297 4 F Keep oxygen away from oil grease or other combustible materials Ensure ade quate ventilation UTILITY HYDRAULIC SY...

Страница 110: ...raft gross weight 30 000 pounds or greater 265 psi land carrier or FMLP HANDLING EXTERNAL ELECTRICAL POWER REQUIREMENTS 115 volt 400 cycle 3 phase ac ENGINE STARTER REQUIREMENTS Set to low pressure ra...

Страница 111: ...ering deflection 1 0 RIGHT 0 LEFT 4 Wing tip radius 30 FEET I Cloo onco fo 180 turn is 65 FEET APPROXIMATE GROUND CLEARANCES A _ Wing tip wing down 5 FEET 6 INCHES fwlng up I 3 FEET 6 INCHES I Dutllip...

Страница 112: ..._t tr_ _ _ 1_ _ __ 120dbto 1 40db Ear protection re quired U se caution 50 t f n exposure time 0 50 r 4 _ _ f 100 r _t _ r _ 1_ _ r _ 1_ _t 150 r i t r f 1 t t t 200 r r _t 1_ _ 1_ _ _t 2 5 0 250 200...

Страница 113: ...u 59K 105 F Jet wake will shift with wind Remove 112K all objects under the aircraft that may cause damage if blown by the Jet wake 155 F Rocks and dirt can be blown as far as 206K 1 mile by afterburn...

Страница 114: ...Extended 550 KIAS With wing down and leading edge landing droop extended pneumatically 300 KIAS With leading edge droop unlocked barberpole indication _ _ 300 KIAS 98 For extension of emergency power...

Страница 115: ...level idle rpm HYDRAULIC PRESSURE Transfer pump shou ld h urned olT U IP proxim m ly 1 000 Ihs lid n mainin l pro idin L the tr lnsf r fm 1 pump elU tion li z ht is illuminatl 1 slI Hlily 800 to 3 200...

Страница 116: ...st be main tained in the main fuel system to prevent flameout under the operating conditions stated Level flight____________________Military thrust 150 pounds Maximum thrust 300 pounds Best glide rati...

Страница 117: ...ATION Engines should not normally be operated beyond the specified time limitations for maximum thrust and military thrust however if this becomes necessary for a particular mission the engine should...

Страница 118: ...engine suc tion creates a low pressure area in the inlet duct causing air to flow from the compartments into the inlet duct There are certain flight conditions for which the engine suction exactly mat...

Страница 119: ...NEVi FllUiT i i NTENCB 1 0 PARAGRAPH AFrER IE IGHr TliliULAT IONS 4 ROLL IN FH LD ul HE TED L iNDING l lES rRIC rIOl lS lli iUIRE fRaT l lili LANJi ING TOUCHOO liN l lUST BE AT LlCA H 500 BEET FR011 T...

Страница 120: ...rget launcher and the Aero 43 tow reel can be carried to the following limits 104 Maximum permissible airspeed____________________500 KIAS Maximum permissible acceleration range__Og to 4 0 g Maximum p...

Страница 121: ...winders Pack 107 2101bs Ibs each each Note 2 3651bs 6701bs 1 1781bs 1 4831bs 1 577 Ibs 1 8821bs 1 797 Ibs 2 102 lbs 2 5621bs 2 8571bs Note4 2 799 lbs 3 104 lbs Note 5 Note 5 1 791 Ibs 1 096 Ibs Note 4...

Страница 122: ...57 Ibs each Note 4 Four MK 24 Mod 2A 3 Parachute Flares 27 Ibs each Note 5 Attached to the Aero 7A l _Ejector Bomb Rack tAttached to the AIA37B l Multiple Bomb Rack Loaded in the Aero 8A l Practice Bo...

Страница 123: ...r to ensure that all F 8 pilots are properly indoctrinated thoroughly briefed and adequately prepared to fly the aircraft certain specific courses must be standardized An outline of those courses and...

Страница 124: ...eapons System Tactical Handbook Tactics publications Rules of engagement 3 Instrument flight planning cross country navigation Flight planning Rest computer Current OPNAV Instruction P3710 series 106...

Страница 125: ...ths 12 months If these requirements are not met familiarization phase requirements with the exception of NAMT I must be completed Training requirements checkout procedures evalua tion procedures and w...

Страница 126: ...n the piloc cype commanders are auchorized co grant a waiver 14 Survival kit 15 Operacional equipment appropriace co climace or the area 108 16 Navigation packet 17 Pocket checklist Survival equipment...

Страница 127: ..._ ____ ___ ____ _________ _ _ _________ _____________________________ _ _ ____ ___ _ _ _ ____________ _ ___________ _ ____________ 131 Touch and Go Landing _ _________________ _________________ ___ __...

Страница 128: ...ing area Control agency Time on station or over target WEAPONS Loading Safety Arming dearming Duds Special routes with ordnance aboard Minimum pull out altitude Jettison area Tow escort COMMUNICATIONS...

Страница 129: ...ll pilots will assemble for a debriefing and critique It will be conducted or supervised by the flight leader and will cover the following Interrogation by an intelligence officer if applicable Genera...

Страница 130: ...e missing only when the two missing fasteners are separated by two installed fasteners The first and last fastener in any row must be installed No fastener may be missing from the leading edge of any...

Страница 131: ..._______ NO LEAKS RIGHT WING Check general condition NO FLUID LEAKS Access doors and panels ___ SECURED Leading edge NO DAMAGE OR HYDRAULI C LEAKS Wing hinge pins_ __ ___ LOCKED PANELS SPREAD AND LOCK...

Страница 132: ...45HHD l Shore Based Procedures COCKPIT ENTRY 114 e zRelea Buttons To open top step press lower release button To extend lower step press re lease mechanism and pull step __ Step Extension SSE Right F...

Страница 133: ...ensure proper attachment 13 Emergency oxygen bottle pressure Emergency oxygen bottle lanyard secured to structure lan yard quick disconnect locked and lanyard not foul d on seat or cockpit floor 14 Pu...

Страница 134: ...e Based Procedures EJECTION SYSTEM INSPECTION I Guillotine Parachute Trap Door 116 ithdrawal Line Drogue Gun Trip Rod t i i NAVAIR 01 45HHD 1 See Detail C i 1I 6376Z Z 3 Z N E Figure 3 3 Sheef 2J Chan...

Страница 135: ...II Shore Based Procedures UEcnON SYSTEM INSPECnON Pin 1 i Q Pin 1 Face Curtain Pin 2 Ejection Gun Pin 3 Drogue Gun Changed 15 July 1966 0 Pin 4 Guillotine Firing Mechanism SAFETY PIN PROPERLY INSTALLE...

Страница 136: ...not crank the engine until a positive down indication is received for all landing gear 6 Main fuel shutoff valve CHECK Give the plane captain the drinking ignal When he is at the starboard wheel well...

Страница 137: ...lly no engine warmup period is required After the engine has stabilized at idle the throttle may be advanced to full power At ambient temperatures below 35 C 31 F operate engine at idle for 2 to 5 min...

Страница 138: ...test switch PRESS Main and transfer fuel quantity indicators drop to zero and return to original readings when released 6 Hydraulic pressures CHECKED WARNING LIGHT OFF All pressure gages read 3 000 20...

Страница 139: ...g to that of the stick pitch trim knob Place hands outside the cockpit and have the plane captain check the wing well for leaks damage or foreign objects Changed 15 July 1966 With Wing Up 7 Angle of a...

Страница 140: ...e pins are locked 20 Canopy CLOSE LOCK STOW HANDLE 122 Turn cockpit pressurization and defog off Pull canopy down and hold with left hand Actuate canopy locking handle full aft then full forward makin...

Страница 141: ...and 3 5 TakeoH Checklist The takeoff checklist will be completed prior to take off Figure 3 6 presents the short cockpit mounted checklist 1 Fuel CHECKED Check for proper quantity in the main and tran...

Страница 142: ...10 0 2 53 11 1 2 52 12 2 2 51 13 3 2 50 14 4 2 48 15 6 2 47 16 7 2 46 17 8 2 45 18 9 2 44 20 0 2 43 21 1 2 42 22 2 2 41 23 3 2 40 24 4 2 39 25 6 2 38 26 7 2 37 27 8 2 36 28 9 2 35 30 0 2 34 31 1 2 33...

Страница 143: ...UP Cruise droop switch DOWN Throttle Military Release brakes Nose gear steering used In Initial ground roll Gear UP Airspeed 170 1 80 KIAS Altitude 200 FEET Wing ON Oownlock handle LOCK I Start nose u...

Страница 144: ...the handle cannot be placed in LOCK or the wing wheels droop light remains on recycle the wing Do not exceed 220 KIAS until the wing is down and locked Wing transition will require very little stick...

Страница 145: ...ching of the aircraft conduct the normal preflight start and poststart checks If practicable conduct radio checks with the controlling agencies and the other aircraft of the flight Check radar opera t...

Страница 146: ...t the hook warning light is out B Hook bypass swirch AS REQUIRED For unarrested landings place the hook bypass switch in FIELD CO prevent approach lights from flashing due to retracted hook 9 Continuo...

Страница 147: ...f the angle of cttack indicator BREAK q Section III Shore Based Procedures 1NfTlA1 APPROAOI TralfK patIem 01_ 250 to 350 K1AS Cru dn op _ 250 minimum to 350 KIAS Ex ondocI speed brab en roqui ed Ainpo...

Страница 148: ...Maintain normal approach speed and line up so that touchdown will be on the upwind side of the runway 130 Just before touchdown align the aircraft with the runway by using rudder Maintain a wing low a...

Страница 149: ...Aircraft lined up with the runway or simulated carrier centerline At the point where the meatball is first observed dur ing the turn to final approach the difference between Changed 15 July 1965 a Rog...

Страница 150: ...will signal engine cut after gear downlocks have been installed and wheel chocks are in place 2 Master generator switch OFF 132 Place switch off by the time the engine deceler ates to 45 rpm 3 Engine...

Страница 151: ...he rendezvous to assure separation Cross under and to the outside of Changed 15 July 1966 the leader s turn When in formation fly a position further aft and more stepped down to compensate for a lack...

Страница 152: ...mergency flood lights chartboard lights and extension lights may be used as desired Changed 15 July 1966 ENGINE START Engines will normally be started 10 minutes before launch time Perform the system...

Страница 153: ...in a turn or listing During all catapult hookups personnel designated as checkers will visually inspect the aircraft to ensure that it is suitable for flight The inspection includes but is not limite...

Страница 154: ...ignal the catapult officer by plac ing the exterior lights master switch to ON Changed 15 July 1966 Carrier Based Procedures Be prepared to establish a wings level climbing atti tude on instruments A...

Страница 155: ...tors for 13 units angle of attack and proper airspeed Check cockpit emergency ventilation port closed before using 136 angle of attack indications Fly a racetrack pattern with the 1800 position approx...

Страница 156: ...I I J u 0 Q Q 0 I u c t f y Q w W 0 c U z 0 z 0 0 0 co co 0 8 Ii 0 C 0 c 0 ii O i _ v z o _M Z 0 1 SlON I S v 1 Changed 15 July 1966 NAVAIR 01 45HHD 1 1 1 1 1 i I i1JI 1 I I If 1 I f 1 i Seclion 11 Ca...

Страница 157: ...IN WAVE OFF Avoid a close in wave off whenever possible How ever if it becomes necessary move the throttle smartly to MRT or CRT and maintain optimum angle of attack 138 Do not overrotate Maintain a...

Страница 158: ...hen the cut signal is received Always control canopy opening rate by holding the rails with both hands Install the lan yard before opening the canopy since wind across the deck makes it difficult to d...

Страница 159: ..._____________ _________________________________ ________ 150 Ventral Fins ___ Speed Brake ____ _ ___ 151 151 Cruise Droop _ _ ____ _____ _ _ _ ___ ________ ____ __ _ _______________ _ _ __ 151 Emergen...

Страница 160: ...ean and dirty configurations FAM flights will be planned so that approximately 2 000 pounds of fuel remain upon return to the home field Fuel remaining checks will be given by stating main fuel quanti...

Страница 161: ...es of 8 to 10 feet Maintain vertical and lateral separation and cross under the leader s flight path When proper horizontal separation is obtained on the opposite side of the leader move vertically un...

Страница 162: ...root and fuse lage 2 Number 4 man line up canopies to balance formation 5 Feet Wingtip Separation 5 to 8 Feet Stepdown ECHELON PARADE o 144 5 Feet Wingtip Separation 5 to 8 Feet Stepdown Figure 4 2 1...

Страница 163: ...ht Procedures INSTRUMENT PARADE 3 to 5 Feet Wingtip Separation 5 to 8 Feet Stepdown J Figure 4 3 Bearing is maintained by flying on line with trailing edge of wing DIAMOND PARADE 1 5 Feet Wingtip Sepa...

Страница 164: ...VWEPS 01 45HHD l Flight Procedures PA DE AND IL CHASE COLUMN 146 PARADE COLUMN TAIL CHASE COLUMN d Ji Match lead aircraft s wing and stepdown to avoid excessive turbulence 4 i I No Le I ae Than j 50 F...

Страница 165: ...pproximately 20 Feet t Balanced A t i l I u 0 I i t I iT f j I I I f I li Y I I I e Approximately 20 Feet I t n l 1 Wingman flies on bearing made by leading edge of wing 2 Section leader flies on bear...

Страница 166: ...will permit safe ejection Establish radio contact and determine the indicated airspeed altitude and Hight path of the aircraft to be joined Place all lights on bright and the anticol lision lights on...

Страница 167: ...minutes ensure Changed 15 July 1966 that the hose is depressurized then top off just prior to disconnect Aircraft with Airframe Change No 449 are subject to the following limitation when refueling fro...

Страница 168: ...e and the amber light goes out call contact Note At high closure rates hose whip will occa sionally follow engagement If engagement does not occur reduce power and move slightly to starboard of normal...

Страница 169: ...d spoilers unit hori zontal tail and rudder are fully powered through dual power control systems in order to overcome the high airloads encountered in high speed Bight Artificial feel is provided by s...

Страница 170: ...either power control system However yaw stabili zation and aileron rudder interconnect are lost with PC 2 inoperative With loss of PC 2 acceleration restrictions governing loss of yaw stabilization ap...

Страница 171: ...alities With stabilization systems operative the Crusader is a smooth effective and competitive flying 152 and fighting machine throughout its flight envelope Without stabilization it still may be flo...

Страница 172: ...EAN CONFIGURATION SUBSONIC The aircraft normally spends mOst of its flight time in the subsonic region and has quite conventional Changed 15 July 1965 characteristics there The afterburner gives it ex...

Страница 173: ...t low altitudes the vibration is higher and reaches a modetate peak level around 47 KIAS At higher or lower speeds the vibration level is light but even under these conditions the instrument board and...

Страница 174: ...altitudes or low airspeeds For this reason make large speed changes at low altitudes or at low speeds in normal autopilot mode only Flight Characteristics While operating in the altitude hold mode acc...

Страница 175: ...t engaged in the normal mode differs from operation of the pitch system The roll trim knob is not effective in making roll attitude changes because the heading hold function 156 opposes such changes i...

Страница 176: ...STALLS Stalls in Pullou ts or Turning Flight Accelerated stalls will occur whenever excessive aft Changed 15 July 1965 stick is used for maneuvering at subsonic speeds such as in pullouts or turning...

Страница 177: ...40 120 1 2 1 4 1 6 1 8 2 0 ACCELERATION g Power oil stalling speeds a re based on oper ation with the engine idling Stalling speeds with the engine windmilling are essentially the same as presented fo...

Страница 178: ...ove moderate buffet levels RECOVERY PROCEDURE Upon first signs that the stall point has been reached or upon recognition from the roll behavior of the airplane that a stall is imminent the following r...

Страница 179: ...of the third turn However it is not violent nor does it affect ability of the pilot to select 160 and apply proper recovery controls T he recovery does nOt appear to be lengthened or otherwise change...

Страница 180: ...d rudder and push stick 2 to 3 inches forward of neutral WARNING I Full lateral stick deBection must be applied since as little as inch les than full deflec tion may add one additional turn to the rec...

Страница 181: ...leasing the stick will not cause the airplane to enter any other type of maneuver or to fall or spin any faster There are no restrictions with respect to extending leading edge to landing droop during...

Страница 182: ...full aft stick and full lateral stick opposite to the applied rudder with spin EXAMPLE Control Right Spin Left Spin Rudder Full left Full right Stick Full aft and full Full aft and full right left 7 A...

Страница 183: ...NCIES Engine Malfunctions Airsrarring Afterburner Malfunctions ____ ___ _ _ ______ __ _ _____ ___ ___ ____ _ _ ______ ______________ _____ __ Fuel System Malfunctions _______________ _________________...

Страница 184: ...Position __ _ _ _ _ _ __ _ 195 Landing with Damaged Landing Gear Hook _ _ 198 Landing with Wing Down _ _ _ __ _ __ _ _ 199 Field Arrestments _ _ _ ____ _ _ _ _ __ _ 200 Barricade Arrestment _______ _...

Страница 185: ...moved Manipulate handle to obtain momentary brak ing action Push handle full forward to release brakes Differential braking is unobcainable If necessary shut down the engine to aid stop ping 2 Perfor...

Страница 186: ...ions EMERGENCY ENTRANCE Refer to figure 5 1 for the procedure to be followed when entering the cockpit under emergency condi EMERGENCY EGRESS Begin egress procedure immediately after aircraft comes to...

Страница 187: ...LY CAREFUL NOT TO INJURE THE PILOT WHEN FORCING ENTRY TO THE COCKPIT BE EXTREMELY CAREFUL NOT TO PULL THE EJECTION SEAT FACE CURTAIN OR THE SEAT SECONDARY FIRING HANDLE WHEN FORCING ENTRY TO THE COCKP...

Страница 188: ...ing gear DOWN 170 Landing gear handle WHLS DOWN If this step and step 7 cannot both be per formed in the time available due to reqnire ment for gear handle to be in WHLS UP position for jettisoning th...

Страница 189: ...e out if windmilling rpm is greater than 10 A relight is highly prob able b Alai ll filet exhaustion may also have the same symptoms as a boost pump failure but the main fuel quantity indication and f...

Страница 190: ...d fuel flol drops to zero iIlmed ie te l r e otivate ignihan and engage the e ppro 1 ch power conpensator APe t Tho APe must be engaged prior to loss of main gener ator power as tho Al C is energized...

Страница 191: ...f the engine fails to respond to throttle movement in either normal or manual fuel there is a possibility that control may be regained by engaging the APC At tempt to engage the APC wirh the fuel cont...

Страница 192: ...ue to produce thrust for a period of approximately 4 seconds at MRT to 24 seconds at IDLE 112 Fly proper glideslope approach This approach allows safe ejection prior to reaching 1 500 feet from the en...

Страница 193: ...AS NOT EXCEEDING 1 000 FPM SINK Eng ine master switch OfF APPROACH USE SPEED BRAKE IF EXCEEDING 175 KIA5 00 NOT REPOSITION BRAKE ARER ENGINE FLAMEOUT Stobs OFF BELOW 17S KIAS AfTER ___ENGINE FLAMES OU...

Страница 194: ...When se lecting power SOurce after extending EPP master generator switch must be placed in OFF before emergency generator switch placed in ON or LAND to prevent complete loss of electrical power Chang...

Страница 195: ...rine under EJECTION AND BAILOUT Do not attempt bailout ditching or dead engine approach un less the ejection seat malfunctions If dead landing is to be made fo11ow the procedure under DEAD ENGINE LAND...

Страница 196: ...A due to failure of exhaust nozzle to close Fuel vapor coming out of tailpipe Inflight Emergencies Procedures L Attempt to cycle afterburner If attempt to relight fails or cOluJiJiOtI remains uncorrec...

Страница 197: ...ing light with transfer fuel remaining may indicate failure of wing to transfer fuel 176 low transfer rates are indicated by higher than expected quantity of transfer fuel remaining Main fuel quantity...

Страница 198: ...id using afterburner except in emergency 2 Land as soon as practical ELECTRICAL SYSTEM MALFUNCTIONS MAIN GENERATOR FAILURE Indications Barberpole in main generator indicator Loss of all electrical pow...

Страница 199: ...ry OUt the EMERGENCY DE PRESSURIZATION procedure If primary ac bus power is lost the cockpir air conditioning temperature will go full colJ temperature control bypass valve will fully close Fog in the...

Страница 200: ...bserve Right restrictions Maximum airspeed 600 KIAS or 0 92 IMN whichever is less Maximum permissible airspeed with either stab out in landing condition 180 KIAS Maximum acceleration PC lout 4 0 g PC...

Страница 201: ...artempts ro raise wing will be un successful c Wing incidence handle DN Fai lure to place the ing incidence handle in DN before the emergency droop and wing incidence guard is raised will result in ch...

Страница 202: ...URE OF ROLL TRIM AND STAB SYSTEM Indications Inability to trim Roll stab warning ligbt illuminated Loss of autopilot functions Procedures 1 Roll stab switcb OFF RESET then ON If wamitlg light remains...

Страница 203: ...ons should be con irmed If fire ot positively im icated 3 Return to base using minimum power If enp p fire does exist 4 Shut down engine or eject 182 If fire exists shutting down the engine is a reaso...

Страница 204: ...ort door resulting in Changed 15 J uly 1966 erroneous angle of atta k indications and faulty operation of the approach power compensator system 4 Canopy JETIISON I F REQUIRED If unable to control cock...

Страница 205: ...en quantity Activate emergency oxygen bottle Green apple PULL LANYARD If mask breathing mask with miniature regu lators continues to be difficult after pulling the lanyard remove mask 6 Descend below...

Страница 206: ...egun after power loss a minimum of 210 KIAS and a maximum of 230 KlAS wing up or down is required During landing approach airspeed will nor mally he approximately 150 KlAS at the 180 Changed 15 July 1...

Страница 207: ...CENT FT MIN b UiM 1 For 90 bank add 200 feet to teerain clearance required 3 Normnl ejcction capability based on for wings level n Two second reaction time 2 For inverted flight add 400 fect to terrai...

Страница 208: ...cted weight LAND Wing Down 180 to Knols Gear Up 160 120 Knots See Nole 3 150 KNOTS 2 Bosed on complete power foilure Includes 2 second rcoelion lime 3 Minimum e jection speed with zero rate of sink gr...

Страница 209: ...0 Sink Role Effect See Note 2 Landing 180 Knots Gear Up 150 Knot Wave Off J 1 000 to 2 000 Lb I l DOO 10 2 000 Lbs Fuel 130 Knots 500 Feet 1 Performance based on maximum ope rational ejected weight 2...

Страница 210: ...me 2 Curves are based on wings level bank attitude and appropriate angle of attack 3 Terrain clearance required is based on 5 OOQ foot terrain and is conservative for lower terrain 4 Example At 600 kn...

Страница 211: ...ease handle before ejection 1 Sit erect in seat buttocks against backrest head Pull face curtain out and downward in one finnly against headrest spine straight thighs firm continuous motion Canopy wil...

Страница 212: ...Inflight WARNING II1II Do not release the face curtain after it has been pulled If one hand must be freed to a id ejection grip face curtain tightly with other hand r to pr event curtain from blowing...

Страница 213: ...hancUe Remove the oxygen mask hefore landing or at any time br eathing becomes difficult This action provides better visibilit y and r educes the possibility of suffocation follow ing injury or deplet...

Страница 214: ...ed by the primary dc bus Procedures If EPP supplyi g electrical power Emergency generator switch ON FOR JETI JSONJNG To jet iso Sidewinders from dual or si gle pylons 1 Landing gear handle WHLS UP lnf...

Страница 215: ...urate only in 1 g flight FLIGHT CONDITION ANGLE OF ATTACK UNITS Takeoff Scan wing down 9 0 Winglocked by _____ _ __ ____ _ _ _______ _ _ _______ 14 0 MRT Climb cruise droop out to 10 000 feeL_ ___ ___...

Страница 216: ...ormal landing approach using optimum approach angle of attack 2 Assure minimum sink rate on touchdown 3 Throttle off at touchdown Changed 15 July 1966 4 Engine master switch OFF 5 Master generator swi...

Страница 217: ...e gear up or trailing Short field arcestment tt Barricade arrestment with aU wires on deck and hook down Nose gear caoted Normal landing Turn generator switch off just Normal arrested landing prior to...

Страница 218: ...Wing down landing aher malfunction Long ield arrestm ent Approach s peed 0 wing down landi ng Corresponding precautionar approach shore 16units 160 175 KIAS Utility h ydraulic failure Short field a rr...

Страница 219: ...lan normal or arrested landing Just before t01lchdown 2 Master generator switch OFF With generator switch off nose gear is free to caster GEAR INDICATOR BARBERPOLE Field or Carrier Procedure Treat as...

Страница 220: ...pproach power compensator during the approach The compensater would produce an excessively fast approach if operated with the wing down because it bases the throttle setting on optimum angle of attack...

Страница 221: ...rly enough for full excension Normal excension time is approximately 8 seconds 3 Ensure engagement before loss of directional control Touch down as close to the arresting gear as necessary to ensure c...

Страница 222: ...wing in the down position will attain a nose high attitude at touchdown Changed 15 July 1966 Landing Emergencies speed Normally he wing will he up only during takeoff or landing Lowering the wing unde...

Страница 223: ...for the EPP based on adequate power control system hydraulic pressure Figure 5 8 GLIDE Wing DOWN Gear UP leading edge CRUISE DROOP Airspeed 220 KIAS ThroHle OFF Engine master switch OFF Emergency pow...

Страница 224: ...sity surrounding terrain weath er runway length and other associated factors For maximum stopping effect shut down engine on touchdown 3 Final approach point I 500 feet from runway end 175 KIAS 150 fe...

Страница 225: ...____________ 207 Prior to Descent _____________________________________________________________________ 207 Penetrations _______________________________________________________________________________...

Страница 226: ...ions provide the necessary training Variations of these maneuvers can be performed but those discussed are considered minimal for indoctrination Use a 206 routine scan pattern and practice maneuvers t...

Страница 227: ...nsi tion cannot safely be made below the overcast Changed 15 July 1966 If a formation section makes individual takeoffs accomplish a prebriefed rendezvous either before entering the weather or after r...

Страница 228: ...nt conditions use of the UHF ADF for penetration should be considered an emergency 208 measure When the ARC27A UHF radio is used for direction information voice communication is lost When used for voi...

Страница 229: ...pattern is not feasible the wingman will rejoin you for another approach If leading a section approach to a section landing the leader will not pass the lead Each aircraft will land and roll out in t...

Страница 230: ...1 I I i r 1 1 l I 1 4 Ii 1 I o 1 1 y J z o w Z w 0 zo _N x u t 0 0 t w z o l l l Zl l eLi zZ to U NAVWEPS 01 45HHD l 1 I I I I I f 1 I 1 I 1 I 1 I y I z _ I I E t2 I g I N I on eN Z N I i I 12 _ g I...

Страница 231: ...ation Airspeed 1SO to 160 KIAS _ n ll_ Airspeeds based on 1 000 to 2 000 pounds of fu el remaining All turns are standard rate _ l evel decelerating tum Airspeed 135 to 145 KIAS 13 units Cruise droop...

Страница 232: ...ain on windscreen gives the illusion of being high Use landing techniques described for landing on ice 212 SNOW During flight in snow follow the procedures recom mended for flight under icing conditio...

Страница 233: ...l switch MANUAL Changed 15 July 1966 3 Throttle Advance slowly to RonA rpm Monitor EGT 4 Fuel control switch NORMAL GROUND TESTS If the engine has cooled to an ambient temperature of 35 C 31 F or belo...

Страница 234: ...duction ___________________________________________________________________________________________________ 217 Radio Communications _________________________________________________ 217 Hand Signals...

Страница 235: ...lize bailout oxygen The console oxygen fitting does not have an automatic disconnect therefore do not eject with oxygen hose plugged into this fitting Changed 15 July 1966 RADIO PROCEDURES 1 During fo...

Страница 236: ...pm 8 EMERGENCY PITCH TRIM IN Plane captain forms T with hands at wa ist level and roises hands smart ly In th at position Piiol raises pllch trim handle 11 RUDDER AILERON INTERCONNECT Plane captain mo...

Страница 237: ...PER CHECK With opened right hand strike clenched left fist held near stomach two sharp blows Pilot executes damper check HOOK DOWN Right fist thumb extended dow n ward Into hori zontal palm of Ie I ha...

Страница 238: ...ith Ignore my last signal an eraSing motion in front of external lights face with palm turned fOl ward Employ fingers held vertically Numerals as indicated A nod of the head I under to indicate desire...

Страница 239: ...es assumes lead them 2 Wingman places lights on 3 Wingman places lights on DIM and assumes lead DIM and assumes lead 3 Wingman shines flashlight at leader then on his hard hat Leader pats seH on head...

Страница 240: ...Single letter R or K in 1 Wingman cross under to 1 Execute forearm vertically with clen code given by external lights right or left echelon or in ched fist or single wing dip direction of wing dips 2...

Страница 241: ...on channel indicated by finger ceiving frequency and switch by finger numbers indicating numbers to channel indicated by orig frequency inator Dial in manually if necessary r Vertical hand with finger...

Страница 242: ...y UHF ADF is up or 3 Thumbs up or nod I down understand Two fingers pointed toward Repeat then execute eyes meaning IFF SIF Sig nals followed by 1 CUT 1 Turn IFF SIF to STAND BY 2 3 digit numerals 2 S...

Страница 243: ...als 3 Followed by thumbs down 3 I am unable to fire 3 Nod head I understand Signal 63762 7 12N B figure 7 6 AIRCRAFT AND ENGINE OPERATION SIGNALS Signal Meaninp Response Day Night I Raise fist with th...

Страница 244: ...if 1 Cone moved aft 1 By receiver extend 1 Drogue extends proper 2 Cone moved forward drogue ly 2 By receiver retract 2 Drogue retracts fully drogue and air turbine feathers Make hand into cupshape t...

Страница 245: ...r craft nearest suitable field Point to pUot and give Flash series of dots with Are you having difficulty Thumbs up I am all right series of thumb down move exterior lights Thumbs down 1 am having men...

Страница 246: ...a Hold until arming crew b Thumbs down all personnel and equipment clear of arming clear of area b RetUrn to line b Aircraft is down for ordinance DEARMING 3 Dearming supervisor Same Pilot Check all a...

Страница 247: ...al lights Extend speedbrakes commen Execute when leader extends thumb in pinching motion cing approach speedbrakes I Rotary moyement of clenched 2 dashes w external lights Extend wheels anci full flap...

Страница 248: ...lage Scores System Wing Stores System Before AFC 488 Wing Stores System After AFC 488 Fuze Function Control AN AWW l System Stores Weight and Compatibility Misfires _____ _ __ Stores Jettisoning ___ E...

Страница 249: ...ised later The fire control system sight unit has an antitumbling circuit to prevent the sight gyro from tumbling duc iog violent maneuvers When the sight gyro pipper reaches maximum deflection the an...

Страница 250: ...83 CONTROL RADAR SET C 2695 APQ 83 ADAPTER COMPUTER MK 20 MOD 3 Changed 15 January 1967 SYNCHRONIZER SN 253 IAPQ 83 GYROSCOPE ASSEMBLY CN 529 IAPQ 83 RADAR HAND CONTROL SIGHT UNIT CONTROL BOX RANGE U...

Страница 251: ...OMPUTER Range Current Elevation Offset Constant MK 101 MOD 0 Elevation Current Foe Range aDd Azimuth Current Bias Range VDC Computer Alert VDC Gyro Caging 28 Volt DC ARMAMENT RANGE UNIT Switch MK 26 M...

Страница 252: ...Section VIII AN AWG 4 System FIRE CONTROL SYSTEM CONTROLS Range Azimuth Indicator F 8D Aircraft Changed 15 January 1967 L t i I I I r Figure B 3 She et I Range A zimuth Indicator F 8E AircrQft 63762 4...

Страница 253: ...e with armament selector switch in GUNS STBY applies power to maintain radar and IR operation in standby condition NOR places radar and IR setS in operation in search mode HO places radar set in opera...

Страница 254: ...rror reflects the p ipper image on its optical path Precession of the gyro with relation to the sight unit housi ng displaces the pipper on the reflector plate The pipper indicates the direction the g...

Страница 255: ...enser Mirror Condenser System Housing Lamp Fixed Reticle Lamp Housing Cable Adaptor Assembly figure 8 4 Socket Reflector Plate Obiective Lens Instrument Dryer MK 5 Mod 0 Front Reflector Plate Terminal...

Страница 256: ...of the system Ic accepts data on rhe attack conditions makes rhe complitations for firing g uns and causes rhe sight unit CO generate the required lead angle T he computer solves nonlinear algebraic...

Страница 257: ...ad effecc to pull the pipper far beyond the desired posi tion for in dicating the correct point of aim Because of this the kinematic lead is purposely decreased so that the com bination of kinematic l...

Страница 258: ...AWG 4 System EFFECT OF THE ACCELEROMETER Required Gravity Drop 50 Milsl Required Kinematic Lead Complolted Gravity Drop 50 Miisl Down Computed Kinematic Lead Accelerometer Output 63762 8 9 10 66 Figur...

Страница 259: ...d of the slide and tube assembly secures the guns to the front mount The quick release pin used to clamp the retaining ring is itself safetied with a pin to ensure that the quick release pin does not...

Страница 260: ...ition Boxes Feed Chutes Ammunition Box Gun and Adapter Assembly Expended Case and Link Compartment Limiting Resistors and Interlock Bypass Relays Feeder Pressure r Reducer LJ i Gun Charger r _ I I Air...

Страница 261: ...dor Switches 234 o 00 o o o o o o o o 00 o o o o o o o o o o F BE Aircraft with AFC 488 On a ircraft without AFC 488 panel same cJo cept no MER TER STORES position on select jeHison switch o o o o o o...

Страница 262: ...ON upper guns trigger circuit completed to guns trigger switch Missile tones available Forward ONt upper guns trigger circuit completed to guns trigger switch Gun firing tones available missile tones...

Страница 263: ...236 of guns are fired by separate pulse trains our of time with each other to provide desynchronized firing of upper and lower guns 0 of the interlock bypass relays arc connected in parallel with the...

Страница 264: ...Fwd Vent Armament Control Panel Pressure Regulator and Relief Valve From Secondary AC Bus Energized to charge guns t Holds aft door open until fwd door closes j Holds fwd door closed until aft door op...

Страница 265: ...gas mech anism which starts the breechblock rearward after a round has been fired The gas mechanism which unlocks the breechblock and starts it rearward immediately after a round has been fired derive...

Страница 266: ...o switch ON 2 Sight fixed lamp switch AS DESIRED 3 Sight dimming knob INTERMEDIATE POSITION 4 Fire control power switches ON 5 Range switch FIXED 6 Fixed range dial AT ESTIMATED FIRING RANGE 7 Guns se...

Страница 267: ...ROLS 240 o o o o o o o o o o o o 00 o o o o o o o o o 00 o o o o f 8E Aircraft with AfC 488 On aircraft without AFC 488 panel same except no MER TER STORES position on Iclect jenison switch o o o o o...

Страница 268: ...uit Clockwise toward HIGH increases volume of missilt audio signal UPI E H Simultaneously launches left and right hand upper missiles in an unarmed unguided condition b providing tiring power to missi...

Страница 269: ...computer group from LOW to HI GH ON Jettisons stores selected by armament selector switch with landing gcar handle in the W H lS UP posicion OFF decncrgizcs jettison system ON With landing gcar retra...

Страница 270: ...Bomb Container PBC These racks attach to a basic ejector rack Aero 7A or Aero 7A l in each w ing pylon Sing le ordnance can also be attached to the Aero 7A or Aero 7A l ejector racks For a current lis...

Страница 271: ...E ZUNI ROCKET LAUNCHER AND LAU 7 A Firing Pin No 1 Umbilical 244 Gas Receiver Firing Pin No 2 Tube No 2 Fuselage Zuni Firemode Switch See Figure 8 16 figure 8 12 Lau 33 A or Lau 35 A Airborne Rocket L...

Страница 272: ...WING PYLON 641 and 642 t 639 and 640 PANEL NO 638 63 640 641 642 643 Refer to figure 8 16 for pylon mounte d ormoment swi tches w hich are adjacent 10 Ihe circuit breaker panels AERO 7A 1 EJECTOR BOM...

Страница 273: ...for opening the hooks Release of the individual bombs during flight is accomplished by the firing of a Mk 17 Mod 0 separation cartridge in each bo lb rack Firing of the cartridge actuates an overcente...

Страница 274: ...VAIR 01 45HHD 1 Section VIII Wing Stores System MULTIPLE BOMB RACK ASSEMBLY Changed 15 January 1967 Release Mode Selector Switch ISee Figure 8 161 Sway Brace Pads 63 7 62 6 16 1 0 66 Figure 8 14 246A...

Страница 275: ...65 12 inches 21 6 inches 14 2 inches 87 pounds 28 volts 6 14 or 30 inches 6 Bombs Carried 6 MK 76 3 MK 89 6 MK 106 ____ 2 3 1 5 1 AIA37B 3 Practice Multiple Bomb Rack 5 Sway Brace 2 Wing Pylon 3 Elec...

Страница 276: ...ARD te o o AI A37B Multiple 80mb Rock i Eji r t C rj W lAu ta A Zuni launcher C1lJ l cJ22 AIA37B 3 Practico Multiple Bomb Rock eel l u U J _ Aero SA Practice Bomb Container o it M o Switth also oppeor...

Страница 277: ...ZUNI rockets with one press of the Stores release bUHon There is a 95 millisecond imcrval between rocket firings Inoperative SINCLE for Iring or dropping Slores from seleClcd wing pylon onl Either or...

Страница 278: ...d to selcct the bomb drop sequem e Prov ides for selective release of practice bombs from the practice multiple bomb rllck Before flight the selector switch must be set at position number o ne when ca...

Страница 279: ...s System WING STORES SYSTEM COCKPIT CONTROLS r BE 246 F F BE Aircraft with AFC 488 On aircraft without AFC 488 panel some except no MER TER STORES position on select jeHison switch 63762 8 S I 12 66 F...

Страница 280: ...he AERO 7A 1 ejector bomb rack including any multiple racks or launchers I ER TER STORES placing the switch in this position with the landing gear handle in W I ILS U P and the pylon ME RI TER mode sw...

Страница 281: ...ns for jettisoning the rockets If a no fire occurs a second attempt may be made to fire the rocket Normal Operation 1 Armament select switch WING R or WING L cor responding to wing station to be actua...

Страница 282: ...lc I WZS LH and RH Single 2 TMRS LH and RJ I Single 2 TMRS LH and RH Dual 3 FS LH and RH Safe 3 FS LH and RH Safe Ripple I WZS LH and RH Ripple I WZS LH and RH Ripple 2 TMRS LH and RH Single 2 TMRS L...

Страница 283: ...he wing pylon stores When single bombs are loaded the circuit fires the ejector cartridge which energizes the ejector mech anism in the AERO 7A 1 ejector rack to eject the 246K bomb When multiple bomb...

Страница 284: ...configuration to connect the ejectOr rack to the wing pylon electrical circuits CV21 20n07 11 and 18 adapter harnesses are installed in the wing pylon for the multiple bomb configuration to connect th...

Страница 285: ...LH and RH 2 RMS _ SINGLE LH and RH 3 FS ELECf or MECH 3 FS ELECf or MECH 1 TMRS _ SINGLE LH and 1 TMRS DUAL LH and RH 2 RMS DUAL LH and RH 2 RMS _ DUAL LH and RH 3 FS _ ELECf or MECH 3 FS _ ELECf or M...

Страница 286: ...Changed 15 January 1967 Pylons are preset for simultaneous release by preset ting both triple multiple rack firemode switches to DUAL The armament selector switch on the armament panel is set to WING...

Страница 287: ...MULTIPLE EJECTOR RACK MER ___ Rocket Harness Assembly Individual Rack Assembly Ejector Unit 6 Places Suspension Lug Attoch Points Typical Adjustable Sway Braco TypicQI TER Electrical TER Controls See...

Страница 288: ...rI Single Rid Pocks I Single Firing WING l Land R Pylon Select WING tJJ _ Single Bombs Switches in DUAL R for single release option t Simultaneous Release SINGLE or RIPPLE Land R Pylon See Note 3 Swi...

Страница 289: ...fect after AFC 488 2 When a MER TER station is left empty the stores hanger must be open and the mechanical fuzing switch on the armament control panel placed in the NOSE position Otherwise automatic...

Страница 290: ...the fuzing voltage is indicated when the HV DC check lamp lights T he selected fuzing voltage is applied to the bomb fuze at the selected station when bomb release is initiated by Changed 15 January...

Страница 291: ...Tbe oscillator operates in conjunction with the fuz ing amplifier power supply to provide rf signals re quired in cbarging rf dc bomb fuzes Eighteen different arming and detonation time delay options...

Страница 292: ...ircuit by placing the maSter armament switch in OFF To fire guns or additional missiles return the switch to ON the misfired missile firing cir cuit will not rearm For a misfired Side winder missile O...

Страница 293: ...ator switch in ON or LAND The master armament switch need not be placed in ON for salvo or selective jettisoning 246V AUTION 1 Jettisoning of Aero 6A and 6A l rocket packs is not recommended Jettisoni...

Страница 294: ...ation When the chalf select switch is placed in FWD or AFT the chaff release switch 1 figure 8 22 is armed to release chaff Each time the chaff release switch is depressed one package wiII fire from t...

Страница 295: ...I Section VIII ECM NAVAIR 01 45HHD l CHAFF SYSTEM CONTROLS PROGRAMMER PANEL 246 X CHAFF CONTROL PANEL r7 Figure 8 22 Sheet 11 63762 6 20 0 66 Changed 15 January 1967...

Страница 296: ...for manual operation and arms autofice button and chaff release switch Momentarily depressed initiates programmed chaff dispensing Indicates number of chaff packages remaining in forward and afr dispe...

Страница 297: ...bay vent door circuit 236 gun charging circuit 236 gun firin g 237 gun system arrangements 2 33 gunner y system 232 gunnery system controls 234 NAVAIR 01 45HHD l INDEX jettisoning 193 missiles from F...

Страница 298: ...1 chaff dispenser 246X chaff system controls 246X Emergencies see specific emergency Emergency power package Right characteristics 152 Engine 11 compressor stalls 15 cooling fl ow limitations 102 dead...

Страница 299: ...246J carrying equipment 239 cockpit controls 239 240 fuselage mounted Zuni rockets 239 Sidewinder missile system 239 Fuze function control ANIAWW 1 system 2465 circuit breakers 246T description 2465 f...

Страница 300: ...aircraft before AFC 488 193 Multiple bomb rack preflight check 246M N NATOPS evaluation report form 270 Navigation equipment direction finder ADF group AN ARA 25 71 MA l compass 57 TACAN 75 Night fly...

Страница 301: ...246U jettisoning missiles from F 8E with AFC 488 246W jettisoning missiles wing stores from F 8E before AFC 488 246V Stores weight and compatibility 246U Stuck throttle in normal range 172 in afterbu...

Страница 302: ...W ing fails to transfcr fuel 177 tank fuel dumping 51 193 Wing stores system ahec AFC 488 193 W ing cwo position 82 normal operation 85 wing and leading edge schematic 84 278 NAVAIR 01 45HHD 1 Wingfo...

Страница 303: ...7 I Ii t...

Страница 304: ...i...

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