Navair Navy F-8E Flight Manual Download

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Summary of Contents for Navy F-8E

Page 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...

Page 2: ...nsert these pages into basic publication Destroy superseded pages NAVAIR 01 45HHD 1 NATOPS FLIGHT MANUAL NAVY MODEL F SD F SE AIRCRAFT ISSUED BY AUTHORITY OF THE CHIEF OF NAVAL OPERATIONS AND UNDER TH...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

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

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

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

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

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

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

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

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

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

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

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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_...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

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

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

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

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

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

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

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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_ ___ ___...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

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

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

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

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 303: ...7 I Ii t...

Page 304: ...i...

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