This PDF can be searched for text using keys "Control+F" there are Bookmarks for major sections of NATOPS manual Use the F4 key to hide/show bookmarksThe two front pages have been made from the actual front & back covers which do not have the A4G photos - used here to illustrate that it is an A4G NATOPS manual NAVAIR01-40A\lC-1 NATOPS

FlightManual NAVY MODEL A-4E/F AIRCRAFT THISPUBLICATIONCANCELSANDSUPERSEDESNAVAIR 01-40AVC-tDATED 1 FEBRUARY1964. CHANGED 1 FEBRUARY1968ANDNAVAIR 01-40AVE-1 DATED15FEBRUARY1967. CHANGED1 FEBRUARY1968. THISPUBLICATIONISINCOMPLETEWITHOUT A-4/TA-4TACTICALMANUAL(NAVAIR01-40AV-1T) ISSUEDBYAUTHORITY OF THECHIEF OF NAVAL OPERATIONS ANDUN'DERDIRECTIONOF THENAVALAIRSYSTEMSCOMMAND This PDF is an exact copy of how pages appeared when the manual was in use - specific extra pages have been added for the A-4G and by the RAN Fleet Air Arm also (these pages are at the beginning)VF-805 & VC-724 Sqdns Royal Australian Navy Fleet Air ArmThe actual 'punch' holes for ring binding of actual manual pages have been retained to also illustrate the 'facing' pages of the manual (with some RAN FAA quirks at beginning~ . _,IIl NAVAIR01-40AVF-1 Supplement to NATOPS Flight Manual NAVY MODEL A-4E/F International Model A-4G AIRCRAFT THISPUBLICATIONSUPPLEMENTSNAVAIR01-40AVC-1 DATED15NOVEMBER1968,CHANGED15NOVEMBER1970, ANDSUPERSEDESNAVAIR01-40AVF-1DATED1 MARCH1968 THISPUBLICATIONISINCOMPLETEWITHOUT CONFIDENTIALSUPPLEMENTNAVAIR01-40AVF-1A,OR A-4/ TA-4TACTICALMANUALNAVAIR01-40AV-1T ISSUEDBYAUTHORITYOFTHECHIEFOFNAVALOPERATIONS ANDUNDERTHEDIRECTIONOFTHECOMMANDER, NAVALAIRSYSTEMSCOMMAND 15 June 1971 A NAVAIR01-40AVF-l Reproductionfornon-militaryuseoftheinformationorillustrationscontainedinthispublicationis notpermittedwithoutspecificapprovaloftheCommander,NavalAirSystemsCommand. LISTOFEFFECTIVEPAGES INSERTLATESTCHANGEDPAGES.DESTROYSUPERSEDEDPAGES. NOTE:The portion of thetextaffectedby the current change isindicated by avertical line in the outer margins of the page. TOTALNUMBEROFPAGESINTHISPUBLICATIONIS49,CONSISTINGOFTHEFOLLOWING: Page No.Issue Title..15June1971 A....15June1971 Flyleaf1.... ,15June1971 Flyleaf 2Blank.15June1971 115June1971 *ii....... 15November1970 iii- v.. ..15June1971 *vi......15July1969 viiBlank.15June1971 1-015June1971 1-115June1971 1-2 Blank15June1971 1-315June1971 *1-4.15November1968 1-lOA Blank15June1971 1-10B........15June1971 1-11- 1-1215June1971 1-43- 1-4415June1971 1-83- 1-84...15June1971 1-93.15June1971 *1-94..... 15November1968 *3-7..... 15November1970 3-815June1971 8-1- 8-515June1971 8-6Blank15June1971 Index1-Index3. *Index 4. Index5. *Index 6-Index 7. Index8. Index13. *Index14. Index15. 15June1971 15November1970 ...15June1971 15November1970 ...15June1971 .....15June1971 ..15November1970 Index16Blank.. FO-O 15June1971 15June1971 15June1971 FO-2 FO-5 15June1971 15June1971 Page No.IssuePage No.Issue *Asteriskindicates back-uppagesaddedfrombasicNATOPSFlightManualNAVAIR01-40AVC-l Section I NAVAIR01-40AVF-l Figure1-1.ModelA-4G Aircraft (viiblank)/1-0 NAVAIR01-40AVF-1 Section I Part 1 PART1 GENERALDESCRIPTION DESCRIPTION TheNavyModelA-4G Skyhawk(figure 1-1) is a . single-place rilOnoplanewith amodified delta-planform wingmanufactured by theDouglasAircraft Company,Aircraft Division,Long Beach,California. The aircraft is powered byaP&WAJ52-P-SA gas turbine engine producing asea levelstatic thrust rating Of9300 pounds.DeSigned as ahigh performance,attack aircraft,it mounts two20mmgunsinternally,carries avariety of externalstores,and is capable ofoperating from either acarrier or ashore base.Thetotal operating weight ofthe aircraft is 11,350 poundswhich includes aISO-pound pilot,oil,trapped fueland oil,liquid oxygen,centerline pylon,gun installation (less ammunition),AWW-lfusingsystem,inboard and outboard wing pylons,and twoempty300-gallon external fueltanks. 1-3 ,'. Superintendent, AircraftMaintenance S y d n ~ y . .\ AmendmentListNo.(RAN)S-tot & Repair, AP(RAN)NA01-40AVC-1 February,1973. INSTRUCTIONSHEET NATOPS FLIGHTMANUAL NAVYMODELSA-4E/FAIRCRAFT INSERTIONOFLEAVES 1.RemoveanddestroyexistingListofSupplementsandinsertnewListof SupplementstoAL.S. 2.InsertRANSupplementnumber6tofacepage1-93Sect.IPart2. 3.RecordincorporationofAmendmendmentListintheALRecordCertificateand destroythisInstructionSheet. REF:(AS/720/73)4803 ~ ";, t{ AL(RAN)5,Feb.73.AP(RAN)NAOl-40AVC-1 ROYALAUSTRALIANNAVY , LISTOFSUPPLEMENTS Sect/PageAffectedSupplement Sect.V,Page5-361 Sect. IPt.4,Page1-1332 Sect. IPt.4,Page1-1313 Sect.IVPt.2,Page4-224 Sect.!Pt.4,Page1-1295 Sect. IPt.2,Page1-936 r''I.': AL(RAN) 5,Feb.73. .. AP(RAN)NAOl-40AVC-1 ROYALAUSTRALIANNAVY . ' SUPPLEMENT6 , TO NAOl-40AVC-l,SECTION1,PART2,PAGE1-93 INTRODUCTION 1.ThisSupplementispromulgatedtodescribeRANSkyhawkbannertowedtarget pilotoperatingproceduresandflightlimitations. BRIEFDESCRIPTIONOFEQUIPMENT 2.Thestandard30'x6'bannerisusedtoprovideasuitableair-to-air gunnerytargetforSkyhawkarmamenttraining.Thebannerisofpol)'thenemesh, andissecuredtoaspreaderbar,fittedwithacounterweightononeendtokeep thebannerinaverticalpositionwhilstairborne.Thebanneristowedfroma specially-designedplatform,securedinthesamemannerasageneralstoretothe Aero7Acentrelinerack-pylon.ThebannermaybeelectricallyreleaSedfromthe platform,ortheplatformandtwoexplosivelyjettisonedinanemergency,using thenormalarmamentcircuitsandswitches.Thebanneristowedbehindthe aircraftusingaspecially-manufactured,plastic-sheathed1200ftsteelcable, andincorporatesswivelfittingsandaweaklinkshearpin.Threelargenylon websof100ftlengthsecurethecabletothebannerspreaderbar. OPERATINGPROCEDURES Preflight 3.(a) (b) (c) Pre-taxi Ensuretowingplatformhasbeenfittedtoaircraft,andarmamentpre-flightprocedureshavebeensignedforintheTA-100. Duringpre-flightexteriorinspection,checksecurityofplatformon centrelinerack,andplatformmembersandJ-hookreleaseunitfor obviousdamage. Calculatetakeoffdistanceasdescribedinpara.llofthisSupplement. 4.(a)Checkallarmamentswitchesaresafeandoff,andselectstation"3"or or"ALL"onemergencyselectswitchasappropriatefortakeoff. (b)Checkcentrelineracksafe.typinremovedwithotherpins. Pre-takeoff 5.(a)Afterbannerhandlingparty havestreamedbannerandtowline,andATC entryclearancereceived,taxidowncentrelinewithnosewheelslightly toonesideoftowlinetominimisewearonsame.Aircraftwillbe marshalledovertowlineend.Keepbrakesonandengineatidlewhile towlineisconnectedtoplatform.Tension-upasdirectedby marshaller. ,...........

r .. :or:

ALtRAN)5,Feb.73.AP(RAN)NAOl-40AVC-l (b) (c) In-flight 7.(a) (b) (c) Takeoffshouldbemadewithtakeoffflapset,andusingtakeoffspeed foractualgrossweightlisted inNATOPStakeoffcharts. Usestandardrun-upandbrakereleaseprocedures;correctanyinitial noseswingwithsteeringand/ordifferentialbraking; expectaslightlysloweraccelerationthanwithcleanaircraft. Justbeforecalculatedt8leoffspeed,movestickback,androtate aircrafttolift-off onspeed.Immediatelyadoptasteepclimbing attitude(approximately12-13deg.nose-up).Whencomfortably airborne,retractwheelsandflapsinnormalmanner. NOTE:Takeoffplanningdataiscontainedinpara11. Theaircraftmustbeoperatedwithinthelimitationslaiddownin para10. FlightplanningandfuelrequirementscanbecalculatedusingNatops SectionXIperformancedatachartsanddatacontainedinpara12of thisSupplement.' Aircrafthandlingqualitiesduringbannertowingoperationsare unchangedwithrespecttocleanaircraftbehaviour,providedthe prescribedbannertowinglimitationsarenotexceeded.Apparent directionalstabilityisincreased.Mildlongitudinalvibrationsmay occurduringflight,thisphenomenabeingmoreapparentduringhigher speedoperationsorflightthroughturbulence.Longi tudina1trim dataiscontainedinpara13ofthisSupplement. Normalreleaseoperations 8.(a)ObtaindroppointanddirectionfromATConreturnfromexercise;plan adescendingstraightinapproach,tobeat350ftAGLand160KIAS atdroppoint.ReleasewillnormallybecalledbyAirwatch,and_ shouldnormallybemadeinthecleanaircraftconfiguration. (b)Priortorelease,placearmamentswitchesinfollowingconfiguration:-(1)FunctionselectswitchtoBOMBS&GMARM. (2)Station3switchtoREADY. (3)ArmamentmasterswitchtoON. (c)Forrelease,depressbombreleasebutton.

9.(a) (b) releaseoperations If bannerfailsto(asindicatedbylongitudinalvibrationand callbyAirwatch),planflightpatternforsecondreleaseattempt, recyclearmamentswitche$aslistedinpara8(b),recheckcorrect switchpositions,andattemptfurtherrelease. Aftersecondreleaseattempt,positionaircraftforfurtherattempt andplaceswitchesliste.dinpara8(b)tosafe.PlaceEmergency SelectorSwitchtoNo."3"position. YES! the RAN put the holes on the wrong side of these additional pages 10 I!>Feb.73.APCRAN)NAOl-40AVC-1 9.(c)Atreleasepoint,pullEmergencystoresReleaseHandle. platformcompleteshouldbeexplosivelyjettisoned. Bannerand (d)Ifasecondattemptatemergencyjettisonprocedureisunsuccessful, flytheaircraftoveraclearareaouttosea,andincreasespeedto 450-500KIAS.Releaseshouldbefeltasamarkedlongitudinal vibrationwhentheweaklinkshearpinfailswithinthisairspeed range. WARNING: NOTE: (1)Releaseofthebanneratairfieldsshouldonly becarriedoutoverATC-approvedandvisually clearareas.Releasesmustbemadeinstraight andlevelflightwithallowancemadeforcross-windsduringperiodofbannerdrop. (2)Transitstoandfromthecoastshouldbemadeat amaximumairspeedof250KIAS,andover uninhabitedareas. Normalreleasecannotbemadeafterfailureofmain generator,orduringemergencygeneratoroperation. Limitations 10.(a)Maximumspeed- 280KIAS/0.6IMN (b)Maximumspeed(overland)- 250KIAS/0.6IMN (c) (d) (e) (f) (g) (h) (i) (j) (k) Recommendedmaximumspeedduringfiringpractice- 250KIAS Maximumspeedforfullpowerclimb- 250KIAS Maximumspeedforspeedbrakeoperations- 250KIAS Maximumloadfactors- +2g/0g Maximumbankangles(flapup):-(1)0to10unitsAOA- 60 (2)10to15unitsAOA- 450 (3)15to20unitsAOA- 300 Maximumbankangle(flapdown)- 300 MaximumAOA(wingslevel)- 20UNITS Turnreversals- maybemadewithinrolllimitsforagiven configurationusingmoderaterollrates. Maximumtakeoffcrosswind- 10kt (1)Maximumsideslip- 5deg (m)Hookuse- nottobeloweredwhilstairborne,exceptineme!gencies. FLIGHTPLANNINGDATA Takeoff 11.Ca)UsingSectionXIChart11-10.(A-4(,';)or11-8 _(1'A-4(j),calculate. takeoff airspeedusingactual'aircraftgrossweight. Feb. 73.Ap(RAN)NAOI-40AVC-l 11.(b)Foraircraftgroundrolldistance,usegiventemperature,pressure a1 ti tude,headwil;ldandrunwaygradientfigures,butadd1850lbto actualgrossweightforgivengrossweight. (c)Toaircraftgroundrolldistance,add1940ft(toallowforstreamed bannerandadditionalbannergroundroll)toobtaintotalrequired runwaydistancetobannerliftoff. NOTE: WARNING: Thisassumesbannerisstreamedatedgeofrunway downwindthreshold. (1)Thesefiguresrefertodryrunwayconditions. Extradragcausedbywetbannerandwateron runwaywouldincreasetakeoffdistance. (2)Itmustbeborneinmindthatthelast850ft ofrunwaywillbeunavailableduetofouling ofbanneronupwindriggedarrestinggear, atNASNowra. Climb,CruiseandDescent 12.Forallairborneflightplanningdata,addadragindexof160forbanner andassociatedequipment,tothenormalexternaldrag1ndexofthetowaircraft, andutilizeperformance. datachartsinSectionXIof,'Natops. CentreofGravity 13.(a)Bannerplatform(39lb)isfittedatanarmof228ins.givinga momentof8.892lbin/lOOO(i.e.approximateC.G.changeof0.1%MAC forward) . (b)ApparentC.G.changetrimeffectduetooffsetbannerdraglinewhilst airborneisasfollows:-@ 160KIAS- 1deg.extranoseuptrimrequired. @ 250KIAS- ~deg.extranoseuptrimrequired. Verticaldropof banner 14.@160KIAS- 120ft. @ 250KIAS- 80ft. S.A.M.R. SYDNEY. February,1973. REFERENCE:AHAFTUFLIGHTTESTREPORTF6/72 NAVAIR 01-40AVF-1 Supplement to NATOPS Flight Manual NAVY MODEL A-4EJF International Model A-4G AIRCRAFT THISPUBLICATIONSlIPPLEMENTSNAVAIR01-40AVC-1 DATED15NOVEMBER1968,CHANGED15NOVEMBER1970, ANDSUPERSEDESNAVAIR01-40AVF-1DATED1 MARCH1'968 THISPUBLICATIONISINCOMPLETEWITHOUT CONFIDENTIALSUPPLEMENTNAVAIR01-40AVF-1A,OR A-4/TA-4 TACTICALMANUALNAVAIR01-40AV-1T ....~ ISSUEDBYAUTHORITYOF THECHIEFOFNAVALOPERATIONS ANDUNDERTHEDIRECTIONOF THECOMMANDER, NAVAL AIRSYSTEMSCOMMAND AL(RAN)2,Nov69 AP(RAN)IiA01-40AVC-1 15Nov68Changed 15August1910 RoyalAU.stralianl'Jav"r . I__.:.,s; SECTIonsAFFEC'}llDD SectionV,Page5-36 Horizontal TrimMalfunctionMod. 3 Section1,Pt.4Pa.{;e1-133 Fig.1-57Revisedli!;1:,L t foroilgauge. Sect:,.on1,P"t.4,Page1-131 Maximuml)ermissa.blecentreof gravi tyrangeforthD cleanaircraft SectionIV,Pt.2,Pace;4-22 DumpWarningLight,Inflight RefuellingCentrolConsole Supplementllo. 1 2 3 4 .AP( RAN )HA01-40AVO-01 TorDcorclthoincoX'T)Orationoran Listin thisSi(71aca.insttheAL( RAN) ]Jo.andinscrt date DEPARTMENT OFTHENAVY OFFICEOFTHECHIEF OF NAVALOPERATIONS WASHINGTON,D. C.-20350 LETTER OFPROMULGATION 1March 1968 1.TheNavalAirTraining andOperating ProceduresStandardization Program (N ATOPS) isapositive approach towards improving combatreadinessand achieving asubstantial reduction in theaircraft accident rate.Standardization,based on professional knowledgeandexperience,providesthebasisfordevelopment ofan efficient andsoundoperational procedure.Thestandardization program is not planned tostifle individual initiative but rather,toaidtheCommanding Officer in increasing hisunit'scombat potential withoutreducing hiscommand prestige or responsibility. 2.Thismanual standardizesgroundand flightproceduresbut doesnot include tactical doctrine.Compliancewiththestipulatedmanual procedure ismandatory exceptasauthorized herein.Inorder toremain effective,NATOPSmustbe dynamicandstimulateratherthan suppress individual thinking.Sinceaviation is acontinuingprogressive profession,it is bothdesirable and necessarythat new ideasandnewtechniquesbeexpeditiouslyevaluated and incorporated if proven to besound.TothisendType/Fleet/AirGroup/Air Wing/SquadronCommandersand subordinatesare obligated,authorizedanddirected tomodifyprocedurescon-tainedherein,in accordance withOPNAVInstruction 3510.9 seriesandapplicable directives,forthepurposeofassessing newideas,in apractical way,prior to initiatingrecommendationsforpermanentchanges.Thismanual is prepared and kept current bytheusers inorder toachievemaximumreadinessand safetyin the most efficient andeconomicalmanner.Shouldconflictexist betweenthetraining andoperating proceduresfoundin thismanualandthosefoundin other publications,thismanual willgovern. 3.Checklistsandotherpertinent extractsfromthispublication necessarytonor-mal operationsand training shouldbemadeandmaybecarried in Naval Aircraft foruse therein.It is forbiddentomakecopiesof thisentire publication ormajor portionsthereof withoutspecificauthorityof theChief ofNavalOperations. NAVAIROl-40AVF-l INTERIMCHANGESUMMARY The followingInterimChangeshave been canceled or previously incorporated in thismanual: INTERIM CHANGE NUMBER(S) INTERIM CHANGE NUMBER INTERIM CHANGE NUMBER REMARKS/PURPOSE The followingInterim Changeshave been incorporated in thisChange;nevision: REMARKS/PURPOSE Interim ChangesOutstanding- Tobemaintained bythecustodian of thismanual: ORIGINATOR;l>ATEPAGES (or DATE/I'IMEGROUP)AFFECTEDREMARKS/PURPOSE FlyleafIj(Flyleaf 2blank) NAVAIROl-40AVF-l AIRCRAFTCHANGESUMMARY TheA-4aircraft have beenmodified bymany field changeswhichaffectoperation oftheaircraft and equipment.Throughout thismanual,fieldchanges arereferred tobyAircraft ServiceChange(ASC)or AirframeChange(AFC)number,oneor theotherof whichis assigned totherequired modification. Followingis alist ofASC'S/AFC'Sthat applytothis ASCor AFCNo.Description manual.Thechangeis brieflydescribed and,where applicable,information is given forvisualdeter-mination ofincorporation.Since all ASC'S/AFC'S referred toonthispagemaynot be incorporated into aparticular aircraft,thepilot must check withthe maintenancedepartment todetermine whichchanges havebeeninstalled in theaircraft. VisualIdentification IntroductionNAVAIR01-40AVC-l AFCNo.DescriptionVisual Identification 327Eight-DayClockInstPanel i 331ImprovedAirBleed SystemforAirTurbineNone TransferPump 333-1LAWS,InstallationWiring Mod. 343-1,CommunicationsEquipmentRHConsole -II 344EmergencyBombReleaseSelector SwitchArmamentPanel 345WarningLightPress-to-Test CircuitInstPanel 353GunsightMountRigidityandLightDimming CircuitInstPanel 356IFFMODE4FailureLightRHGlareshield 359EscapacIZero-ZeroEscapeSystemCockpit 360-1UpperAvionicsCompartmentLHGlareshield 376FullShrike SystemEarlyA-4EArmamentPanel 382ExhaustSmokeAbatementLHWedgeConsole 386ShrikeImprovedDisplaySystem(SIDS)ArmamentPanel 387RadarControlConsoleLHConsole 394,SupplementECMWiring/ControlMod. -I,-II, -III, -VI 395ImprovedWalleyeDisplayInstPanel 400J52-P-8AEngineInstallationCockpitPlacard 418-IIAN/ ALEChaff DispenserLHGlareshield 423DisableLAWSUnreliabilityTone withWiringMod. APR-27Installed 428InstrumentPanelLightingControlWiring/ControlMod. 429NosewheelSteeringThrottleQuad. 430CockpitLandingChecklistPanelLHInstPanel 442WingLiftSpoilersThrottleQuad. 451Gunsight,AdjustmentKnobAssemblyCenterGlareshield 451-1InterchangeAngle-of-AttackIndexerand AccelerometerInstrumentPanel 456Angle-of-AttackIndexerAboveGlareshield 464AXC-666AirDataComputerWiringWiringMod. 473AN/APN-154(V)RadarBeaconLHConsole iiChanged15November1970 SECTION I SECTION II SECTIONIII SECTION IV SECTIONV SECTIONVI SECTIONVII SECTIONVIII SECTIONIX SECTIONX SECTIONXI NAVAIROl-40AVF-l TABLEOFCONTENTS THEAIRCRAFT.................................... . Part1 Part2 Part3 Part 4 GeneralDescription........................... . Systen1s................................... . AircraftServicing............................ . OperatingLimitations......................... . INDOCTRINA TION................................... . NORMALPROCEDURES............................... . Part1 Part2 Part3 Part 4 Part5 Briefing/Debriefing ............................ . MissionPlanning............................. . Shore-BasedProcedures ........................ . Carrier-BasedProcedures...................... . HotRefuelingProcedures........................ . FLIGHTCHARACTERISTICS ANDFLIGHTPROCEDURES........ . Part1 Part2 FlightCharacteristics .......................... . FlightProcedures............................ . EMERGENCYPROCEDURES............................ . ALL-WEATHEROPERATION........................... . COMMUNICATIONSPROCEDURES......................... ARMAMENTSYSTEM ................................. FLIGHTCREWCOORDINATION......................... . NATOPSEVALUATION PERFORMANCEDATA Part1 Part2 Part3 Part 4 Part5 Part6 Part 7 Part 8 Part9 General Takeoff Climb Range Endurance .................................. . AirRefueling............................... . Descent................................... . Landing................................... . CombatPerformance.......................... . Introduction Page 1-1 1-3 1-13 1-97 1-129 2-1 3-1 3-1 3-3 3-3 3-23 3-29 4-1 4-1 4-17 5-1 6-1 7-1 8-1 9-1 10-1 11-1 11-2 11-17 11-33 11-41 11-57 11-63 11-71 11-75 11-81 Part10MissionPlanning..............................11-89 Parts2Athru9A- same as.2thru -9........................11-97 NATOPSFLIGHTMANUALGLOSSARY ..................................... ,Glossary-l ALPHABETICALINDEX...............................................Index-l FOLDOUTILLUSTRATIONS.............................................FO-O iii ForewordNAVAIR01-40AVF-1 FOREWORD SCOPE TheNATOPSFlight Manualis issued bytheauthority oftheChiefofNavalOperationsand underthedirec-tionofCommander,NavalAir SystemsCommand in conjunction with theNavalAirTraining and Operating Procedures Standardization(NATOPS)Program. Thismanualcontainsinformation on all aircraft systems,performancedata,and operating proce-duresrequired forsafe and effective operations. However,it isnot asubstitute forsound judgement. Compoundemergencies,available facilities,adverse weather or terrain,or considerationsaffectingthe livesand propertyofothersmayrequiremodifica-tionofthe procedures contained herein.Read this manual fromcover tocover.It's yourresponsibility tohave acomplete knowledgeofitscontents. APPLICABLEPUBLICATIONS The followingapplicablepublicationscomplement thismanual: NAVAIR01-40AVC-1(basicA-4E/FNATOPS flightmanual) NAVAIR01-40AVF-1B(checklist) NAVAIR01-40AV-1T(tacticalmanual) NA VAIR01-40AV-I T(A)(supplement) NAVAIR01-40AV-1TB(tactical pocket guide) NA VAIR01-40AVC -1-6(functionalchecklist) HOWTOGETCOPIES AutomaticDistribution Toreceive futurechangesandrevisionstothis manualautomatically,aunit must beestablished ontheautomaticdistribution list maintained bythe NavalAirTechnicalServicesFacility (NATSF).To becomeestablished on thelist or tochangedistribu-tionrequirements,aunit must submit NAVWEPS Form5605fitoNATSF,700RobbinsAve., Philadelphia,Pa.19111,listing thismanualand iv allotherNAVAIRpublicationsrequired.For addi-tionalinstructionsrefertoBUWEPSINST5605.4 series and NAVSUPPublication 2002. AdditionalCopies Additionalcopiesofthismanualand changesthereto may be procured bysubmittingFormDD1348to NPFCPhiladelphia in accordance withNAVSUP Publication2002,SectionVIII,Part C. UPDATINGTHEMANUAL Toensure that themanualcontainsthelatest proce-dures and information,NATOPSreviewconferences are held in accordance with OPNAVINST3510.11 series. CHANGERECOMMENDATIONS Recommended changestothismanualor other NATOPSpublicationsmay besubmitted byanyone in accordance withOPNAVINST3510.9series. Routinechangerecommendationsaresubmitted directly totheModelManager onOPNAVForm 3500-22shownon thenext page.The addressof theModelManager ofthis aircraft is: Commanding Officer VA-127 NASLemoore,California93245 Attn:NATOPSEvaluator Changerecommendationsofan URGENTnature (safety offlight,etc.,)should besubmitted directly tothe NATOPSAdvisoryGroupMember in thechain ofcommand bypriority message. YOURRESPONSIBILITY NATOPSFlight Manualsare keptcurrent through an activemanualchangeprogram.Anycorrections, NAVAIROl-40AVF-lForeword additions,or constructive suggestions for improve-ment ofits content should besubmitted byroutine or urgent changerecommendation,as appropriate,at once. NATOPSFLIGHTMANUALINTERIMCHANGES FlightManual InterimChanges are changes or cor-rectionstothe NATOPSFlight Manualspromulgated byCNOor NAVAIRSYSCOM.InterimChangesare issued either as printed pages,or as anaval message.The InterimChange Summary pageis provided as arecord ofallinterim changes.Upon receipt of achange or revision,thecustodian of the manualshould check theupdated Interim Change Summarytoascertain that alloutstanding interim changeshave been either incorporated or canceled; thosenotincorporated shall berecorded as out-standing in thesection provided. CHANGESYMBOLS Revised text is indicated by ablack verticalline in either margin ofthepage,adjacent totheaffected text,likethe oneprinted next tothis paragraph. The changesymbolidentifiesthe additionofeither newinformation,achanged procedure,thecorrec-tion ofan error,or arephrasing oftheprevious material. WARNINGS,CAUTIONS,ANDNOTES The followingdefinitionsapplyto"WARNINGS," "CAUTIONS, "and"NOTES" foundthrough the manual. Anoperating procedure,practice,or con-dition,etc.,which mayresult in injury or death,if notcarefully observed or followed. Anoperating procedure,practice,or con-dition,etc.,which,if notstrictly observed, maydamageeqUipment. NOTE Anoperating procedure,practice,or condi-tion,etc.,which is essentialtoemphasize. WORDING The concept ofword usage and intended meaning which has been adhered to in preparing thisManual is as follows: "Shall"hasbeen used only when application of a procedure is mandatory. "Should"has been used only whenapplicationofa procedure isrecommended. "May"and "need not"have been used onlywhen application ofaprocedure is optional. "Will"hasbeen used onlyto indicate futurity,never to indicate anydegreeofrequirement forapplication ofaprocedure. v IntroductionNAV AIROl-40AVC-l NATOPSITACTICALCHANGERECOMMENOATION OPNAVFORM3500/22(5-69)0107-722-2002DATE TOBEFILLEDINBYORIGINATORANDFORWARDEDTOMOOELM.ANAGER F ROM(originator) Unit TO(ModelM3nager) Unit CompleteNameofManual/ChecklistRevisionDateChangeDateSection/CIi.pterParagraph Recom'TIendation(bespecific) Justification ", Ii ~ ~ ~ \ ~ ~ ~----------------o OttClt.. COIIT ..,UGIlMCIt Signature IRank AddressofUnitorCommand TO8EFILLEDINBYMODELMANAGER(IeturntoOri,in.tor) TO"[F[.EHCE (a)YourChan,eReco endationDated D Yourchan,ereco endationdated____________ ieecknowled,ed.Itwillbeheldforactionoftha raVle_conferenceplannedfor ____~ - - - - - - - - - - - - - - - - - - - - - - - - t obaheldat ___________________________ c=JYourchaA,ereco endetioni.recla ifiedURGENTandforwardedforappro.alto ______________________ _______________________ bylOyDTG _______________ /SIMODELMANAGER. vi Changed15July 1969 . ~........'.'" "",f;.'; .. k, i, ~ ~'f":?"'T.-Jr', AL(RAH)6,May.73 . , CAMERADESCRIPTION ROYALAUSTRALIANNAVY SUPPLEMENTNo.7 TO AP(RAN)NA01-40AVC-1SEC.1PT.2 MINIPANRECONNAISSANCECAMERA. AP(RAN)NA01-40AVC-1 1.ThePerkinElmerModel2-18Minipanaerialreconnaissancecameraisa compact,lightweight,35mmpanoramiccameraproducingfourframesof6.12in. lengtheachsecond.ItcanbeusedintheSkyhawkinstallationineitherfore andaft(longitudinal)orspanwise(lateral)modes.Highshutterspeedsare madepossiblebyuseofcontinuouslymovingfilmwitharotatinginclined mirrorandlenssystem.Thescanningslitlocatednearthefilmplaneis coupledtotherotatingmirrorandmovesacrossthefilmplaneintheopposite directiontofilmmotion.Theelectricaldrivemotoriscoupledmechanically toacapstanassemblyandtake-upassemblybymylarbelts.Thecapstanassembly iscoupledtothescanningassemblyinthesamemanner;thismethodof transmissioncompensatesforvariationsinspeedduetoslippagesuchthatthe photographyisnotdegraded. 2.Leadingparticularsare:-Lens ScanAngle FrameRate PictureSize Resolution ShutterSpeeds Aperture FilmCapacity Size Weight PowerRequirement 50mm,F/2.3,2infoca1length 340 x1800 4framespersec.,fixed 6.12in.x1.12in.with0.25in.betweenframes Minimum75lines/mmonaxis,using1/1500sec. atf.2.8on3400PanatomicXfilmdevelopedfor 5min.in019developerat680F. 1/500, 1/3000, 1/750,1/1000,1/1500,1/2000, 1/4000sec.(Manualpreset) F2.3,2.8,4.0,5.6,8.0,11.0,16.0,22.0 (Iriscontrol,manualpreset) 100ft.standardbasedaylightfi 1m.240ft. thinbasedaylightfilm.(BasedonKodak No.10spool) 8.5x8.84x7.81ins. 111b.(Filmandwindowfitted) 28VoltD.C.30Watts ''''_\'"____ ,./.t''..J"'i': :i::., i ,t., CAMERAINSTALLATION 3.Thecameraisfittedtoamodifiedaftenginebayaccessdoor,withthe windowandlowersectionprotrudingthroughthedoorcut-out.Electricalpower forthecameraistakenfromthe28v.d.c.JATOfiringcircuit. CONTROLSANDINDICATORS 4.Controlofthecameraisviatwoswitchesandanassociatedindicator light. s.A switchlabelledMINIPANMASTERislocatedontheJATOcontrolbox, .putboardofthethrottlequadrant.Thisswitchapplies28voltd.c.powerto thecameracircuitwhenselectedtothe'on'position.Indicationthatpoweris suppliedtothecircuitisprovidedbyan -amberlight,MINI PANREADY,mounted adjacentto-theMINIPANMASTERswitch.Thelightilluminateswhenpoweris appliedtothecircuit. 6.Theoperatingpushbuttonismountedonthethrottleleverbelowthe handgrip.Thisbuttonisspringloadedto"theoffpositionandthecameraruns whenthebuttonisdepressed. RefertoA4/TA4TACTICALMANUAL,NAVAIR orcameraoperatingprocedures. CAUTION "0 8.Attemperaturesabove90F,filmstartstodeteriorate.Ifapossibility ,existsthatthetemperatureintheenginebaywillexceed900Fforextended periods,thecamerashouldberemovedtoacoolerenvironment. 9.Itispossibleforthecamerawindow,tobeobscuredbysmearsof oiland hydraulicfluid,andthecameramayingestthesefluidscausingdamagetothe cameraanddegradationoftheBeforeoperatingaircraftfittedwith Minipan,theaftenginecompartmentandundersideofthe aheadofthe camerashouldbecheckedashavingbeenthoroughlycleanedandthatnoexcess fluidispresent. S.A.M.R. SYDNEY. May,1973. --- 72 AP(RAN)NA01-40AVC-1 ... ROYALAUSTRALIANNAVY SUPPLEMENTNo.5 lL NA01-40AVC-1,SECTION1,PART4.PAGE1-129 INTRODUCTION 1.ThissupplementspBcifiestheprocedurestobeadoptedwhencatapult launchingSkyhawkaircraftfittedwithexternalfueltanks. REQUIREMENT 2.Aeitispossiblethatlossofcontrolmayresultfromcatapult. launchingSkyhawkaircraftwithpartiallyfilledexternalfueltanksthis methodofvaryingaircraftlaunchweightisnottobeused. Ifexternalfueltanksarecarriedtheyareeithertobefulland unpressurisedorempty.Ifaircraftlaunchweighthastobevariedwhen carryingexternalfuel,internalfueltanksaretobepartiallyfilled. SUPPLEMENTSUPERSEDESSKYHAWKS.F.I.1/70 (N.O.L.1362/1/725thMAY'72refers) l,.. A.M.R. UST1972 "\..--, ... AL(RAN) T,Jul. 73. INTRODUCTION ROYALAUSTRALIANNAVY SUPPLEMENTNo.8 TO NAOI-40AVC-l 15November1968 Changed15November1970 NAOl-40AVC-l,SECTION3,PAGE3 - 2 2 ~ ,PARA.V 1.Thissupplementdeletestherequirementfortimingtheenginerundown. REQUIREMENT 2.Para.Vafterlanding,ofPage3-22Q,deletesub-paragranhA.4inits entirety. S.A.M.R. SYDNEY. -; . .. .. :,,;;;;t;;,AL (RAN)1,>Jul. 73. ......

INTRODUCTION ROYALAUSTRALIANNAVY SUPPLEMENTNo.9 TO NAOI-40AVC-l 15November1968 Changed15November1970 NAOl-40AVC-1,SECTION3,PAGE3-19,ITEM12 1.Thissupplementdeletestherequirementfortimingtheenginerundown. REQUIREMENT 2.Item12ofPage.3-19delete"TimeEngineRundown". S.A.M.R. SYDNEY. 1973. II .: ..y; NAVAIR01-40AVF-l Section I SECTIONI THEAIRCRAFT TABLEOFCONTENTS Part 1GENERALDESCRIPTION.. Description 2SYSTEMS. Engine ... OilSystem FuelSystem. ElectricalSystem FireDetectionSystem HydraulicSystems ... FlightControlSystem LandingGearSystem. WingFlaps ..... . NosewheelSteering.. WingSpoilers. Speedbrakes.... . WingSlats..... . VortexGenerators. ArrestingHook.. . WheelBrakes... . CockpitEnclosure. Escapac1EjectionSeatSystem.. Zero- ZeroEscapeSeatSystem.. Escapac1C-3EjectionSeatSystem OxygenSystem.............. . FlightInstruments .......... . CommunicationsandAssociated ElectronicEquipment(A-4E) .... Communicationsand Associated ElectronicEquipment(A-4F) ... . NavigationEquipment ........ . AXC-666AirDataComputer ....... . AutomaticFlightControl System(AFCS).............. . LightingEquipment........... . AirConditioningandPressurization Systenl............... . AntiblackoutSystem ..... . Anti-IcingSystem...... . RainRemovalSystem .... . Page 1-3 1-3 1-13 1-13 1-17 1-17 1-24 1-26 1-26 1-27 1-29 1-30 1-30 1-31 1-31 1-32 1-32 1-32 1-33 1-33 1-34 1-35 1-36 1-40 1-42 1-48 1-51 1-53 1-56 1-76 1-83 1-86 1-89 1-89 1-90 Part RainRepellentSystem.. AirRefueling(TankerSystem) .. Jet-AssistedTakeoffSystem ... BannerTowingSystemEquipment MiscellaneousEquipment.. 3AIRCRAFT SERVICING General ....... . PressureFueling HotRefueling... . GravityFueling .. . FuelControlFuelSelector. EngineExhaustSmokeAbatement SystemServicing ............ . EngineOilSystemServicing....... . ConstantSpeedDrive(CSD)Servicing .. HydraulicSystemServicing ..... RainRepellentSystemServicing LiquidOxygenSystemServicing. ExternalPowerApplication. ForwardTowingProvisions TiedownProvisions ..... . DangerAreas .... TurningRadii.......... 4OPERATINGLIMITATIONS. Introduction.......... . EngineLimitations..... . EngineOperatingLimits .. . Maneuvers ........... . AirspeedLimitations .... . Centerof GravityLimitations. GrossWeightLimitations .... AsymmetricLoadLimitations. AutomaticFlightControlSystem Limitations............ . AFCSPerformanceandPower Page 1-90 1-91 1-92 1-93 1-93 1-97 1-97 1-97 1-103 1-103 1-104 1-106 1-106 1-107 1-109 1-112A 1-114 1-118 1-119 1-121 1-122 1-122 1-129 1-129 1-129 1-129 1-130 1-131 1-131 1-131 1-135 1-135 Limitations.............1- 135 AccelerationLimitations....1-135 PressurizedWingTankLimitations...1-139 1-1/ (1-2blank) 1.Air refueling probe 2.Radome 3.Pitot tube 4.Total temperature sensor 5.Brake fluidlevel window 6.Thermal radiation closure 7.ANIARC-51A(UHF)radio antenna 8.ECMpod 9.Normal cockpit entry handle 10.External canopy-jettison handle 11.Approach lights 12.Catapult hook NAVAm01-40AVE-1 KEYTOFIGURE1-4 20.Nosecompartment accessdoor 21.Oil tank 22.Fuselage fueltank fillercap 23.Cockpitcanopy air bungee cylinder 24.Nosesection electronicequipment compartment Section I Part 1 25.ANIAPG-53Bradartransmitterandreceiver group 26.Emergency generator 27.Fuselage fueltank 28.Airrefueling probelight 29.Catapult hook 30.Wing tank fillercap 13.External power receptacle and access door31.Slat 14.Oil tank pressure fillercap32.Barricade engagement detent 15.Taxi light33.Vortex generators 16.Angle-of-attack vaneandtransducer34.Integral wing fueltank 17.T ACAN(V)antenna35.Arresting hook 18.Staticorifice36.JATO igniter terminal 19.ANIARA-50(UHF-ADF) antenna cover37.JATO mounting hooks 38.Speedbrake 1-7 I Section I Part 1 1-8 NAVAffiOl-40AVF-1 Figure1-5.General Arrangement - Cockpit 1. 2. 3. 4. 5. 6. 7. 8. 9. 10. 11. 12. 13. 14. 15. 16. NAVAIR01-40AVF-1 KEY TOFIGURE1-5 Shoulderharness control handle17.Glareshield Leftconsole(figure1-6)18.FIRE warning light Catapult handgrip19.OBSTwarninglight JA TO firingbutton20.Instrument panel(figure1-7) Emergency landing gear releasehandle21.Utility floodlight Compasscorrectioncard22.Eyeball diffuser Compass deviationcard23.Standbycompass deviationcard Rain repellent button24.Arresting hookhandle Landing gear handle25.Emergency generatorreleasehandle Lowaltitude warning system light(LAWS)26.Canopyjettison handle WHEE LSwarning light27.Whitefloodlightscontrol Angle-of-attack indexer28.Rightconsole(figure1-8 ) Gunsight29.Harness releasehandle Elapsed-timeclock30.Alternateejection handle Standpycompass31.Controlstick Rear viewmirror SectionI Part 1 1-9 I Section I Part 1 1-10 NAVAffi 01-40AVE-1 1.WHEELS ANDFLAPSPOSITIONINDICATORPANEL 2.BLANKPANEL .3.BLAN K PANEL 4.THROTTLEPANEL 5.ENGINECONTROLPANEL 6.BLANK PANEL 7.AUTOPILOTCONTROLPANEL 8.BLANKPANEL 9.OXYGENANDANTI-GPANEL 10.ANTI-EXPOSURESUITCONTROLPANEL 11.EMERGENCY SPEEDBRAKECONTROL 12.CANOPYCONTROLHANDLE 13.MANUALFUELSHUTOFF CONTROLLEVER 14.SMOKEABATEMENTSWITCH 15.FLAPHANDLE 16.SPOILERARMSWITCH 17. JATOJETT IS ONSWITCH 18.NOSEWHEELSTEERINGSWITCH 19. JATOARMSWITCH Figure1-6.Cockpit- TypicalLeftConsole HHl-9-A Changed1February1968 SectionI Part 1 (1-10A blank)/1-10B NAVAffi01-40AVF-1 ZZl-3-A Figure 1-6.General Arrangement - Cockpit 1. i 2. 3. 4. 5. i 6. 7. 8. 9. 10. i 11. 12. 13. 14. 15. I 16. 17. Shoulder harness control handle Left console (figureFO-2) Catapult handgrip Emergency landing gearrelease handle Compasscorrection card NAVAIR01-40AVF-1 KEY TOFIGURE1-6 18.Glareshield 19.FIREwarning light 20.OBSTwarning light 21.Instrument panel(figureFO-2) 22.Utility floodlight Section I Part 1 Airspeed correction card23.NORMAL,COMBATlighting controlswitch Rainrepellent button24.Eyeballdiffuser -Landinggear handle25.AUDIOBYPASSswitch Lowaltitudewarning system light (LAWS)26.Standbycompassdeviationcard WHEELSwarning light27.Arresting hookhandle Instrument panel floodlight28.Emergency generatorrelease handle Angle-of-attack indexer29.Canopyjettison handle Gunsight30.White floodlightscontrol Elapsed-time clock 31.Right console(figureFO-2) Standbycompass 32.Harnessrelease handle Glareshield warning lights:WHEELS,*LABS, LAWS,OBST,*IFF,and FIRE(BuNo.155051, 33.Alternateejection handle 155052,155055,155060-155063,and 155069) Rear viewmirror34.Controlstick i *Inoperative;press-to-test only. 1-11 i ~ ~ I' SectionI Part1 Enpne ThruM FuHlace FuelingProbe Alr Refuellne Store IntalreDuets Upper AvionicsCompartment AFCS Radar Video IP.936/AXQ NavigationComputer LABS CP-741/A OXygenSystem Fuel Gaging Fuselage Wine DropTanks FuselaceFuel Cen Capacity ElevatorPowered AlleronPowered Stabilizer Trim 121/4-Degrees Noseup I-Degree Nosedown Bomb Racks RocketEjection Seat Nosewbeel Steertne Spoilers Drag Chute Communications Radar Identification(IFF) APCASN-54 DopplerAPN-153(V) TACAN A-4E J52-P-8A J52-P-8A 8,500' 9,300' Yes Yes Separated Some Yes AN/APG-53A AN/APG-53B Some ASN-19A (Early A-4E) ASN-41 AN/AlB-3 AN/AlB-3A Yes 10Liter 1 Probe 6Probe Yes 1600Lb Yes Tandem Yes 5 Escapac1 Stencel Mod No No No AN/ARC-27A APX-6B Yes Some ARN-21B (Early A-4E) ARN-52(V) NAVAffi01-40AVF-l A-4FTA-4FA-4GTA-4G J52-P-8A J52-P-8A J52-P-8AJ52-P-8A J52-P-8A 9,300' 8,5001 9,300'9,3001 9,3001 YesYesYesYes YesYesYesYes SeparatedSeparatedSeparatedSeparated YesNoNoNo YesYesYesYes AN/APG-53AAN/APG-53A AN/APG-53AAN/APG-53A AN/APG-53BAN/APG-53B SomeSomeNoNo ASN-41ASN-41ASN-41ASN-41 AN/AJB-3AAN/AJB-3ANoNo YesYesYesNo 10 Liter10Liter10Liter10Liter 1 Probe1 Probe1 Probe1 Probe 6Probe6Probe6Probe6Probe YesYesYesYes 1600Lb700 Lb1600Lb700Lb YesYesYesYes TandemTandemTandemTandem YesYesYesYes 5555 EscapacEscapacEscapacEscapac lC-3lC-3lC-3lC-3 YesYesYesYes YesYesYesYes NoNoNoNo AN/ARC-51AAN/ARC-51AAN/ARC-51AAN/ARC-51A AN/ARR-69AN/ARR-69AN/ARR-69AN/ARR-69 APX-64 (V)APX-64(V)APX-64 (V)APX-64(V) YesYesNoNo YesYes"YesYes ARN-52(V)ARN-52 (V)ARN-52 (V)ARN-52(V) AnFARA-25 I.BUNO,155051,155052, ARA-50ARA-50ARA-50ARA-50 155055,155060-155063,and155069 Figure1-7.MainDifferences 1-12 TA-4JA-4KTA-4K J52-P-6AJ52-P-8AJ52-P-8A 8,50019,30019,30011 YesYesYes YesYesYes SeparatedSeparatedSeparated NoYesNo YesYesYes AN/APG-53AAN/APG-53AAN/APG-53A NoNoNo ASN-41ASN-41ASN-41 NoNoNo NoNoNo 10 Liter10Liter10Liter 1 Probe1 Probe1 Probe 6Probe6Probe6 Probe YesYesYes 700Lb1600Lb700Lb YesYesYes TandemTandemTandem YesYesYes 555 EscapacEscapacEscapac lC-3lC-3lC-3 YesYesYes YesYesYes NoYesYes AN/ARC-51AAN/ARC-51A AN/ARC-51AAN/ARC-U5AN/ARC-115 AN/ARR-69(VHF)(VHF) AN/ARR-69AN/ARR-69 APX-64(V)APX-72 (V)APX-72 (V) Provisions NoNo Only YesYesYes ARN-52(V)ARN-52 (V)ARN-52(V) ARA-50ARA-50ARA-50 NAVAIR01-40AVF-1Section I Part 2 altitudeof1000 feet.On the left ofthecenter of the instrument is awindowcontaining tworotating counters;the inner counterregisters altitude in thousandsoffeet,whiletheouterregisters in ten thousandsoffeet.When the altimeter pointer makes 12revolutions,for instance,theouter counter will indicate1,and the innercounter willindicate2,thus showing that the aircraft is at an altitudeof12,000 feet abovesea level.Barometric pressure setting, in millibars,isdisplayed in awindowontheright side of the altimeter face.The knobon thelower left corner of the instrument case is used tocorrect for variations in sea levelbarometricpressure. RadarAltimeter ~TheAN/APN-141radar altimeter (figureFO-2) employsthepulseradar techniqueto furnish accurate instantaneous altitude information to thepilot from0 to5000 feetterrain clearance.Aircraft height is determined bymeasuring theelapsed transit time of aradar pulse,which isconverted directly toaltitude in feet and displayed on thecockpit indicator.The indicatordialfaceis marked in 10-foot increments upto200feet,50-foot increments from200to600 feet,100-foot increments from600to2000 feet,and 500-foot increments from2000to5000feet.A con-trol knobonthe frontoftheindicator controls power to the indicator and is used forsetting thelow-limit indexer.. Thecontrol knobalso provides forpreflight and in-flight test oftheequipment with apush-to-test typecontrol knobfeature.RefertoLOWALTI-TUDEWARNINGSYSTEM(LAWS)forinformation regarding lowlimit indexer.AnOFF flagonthe indicator faceappears whensignalstrength becomes inadequateto providereliable altitudeinformation, whenpowertothesystem is lost,or whenthesystem is turned OFF. LeavetheAN/APN-141radar altimeter in theOFFpositionuntilpower is applied to the aircraft andreturn equipmenttoOFF beforepowerisremoved. NOTE At altitudesabove5000 feetterrain clear-ance,theOFF flag willappear and the pointer willmove behindthemasked portion ofthe indicator dial.Thepointer will resumenormaloperation whentheaircraft descendsbelow5000 feet. Theradar altimeter operatesnormallyduring50-degree anglesofclimb or diveand 30-degree angles ofbank,right or left.Beyond thesepOints,the indications ontheradar altimeter become unreliable but willresume normal operation when theaircraft returns tonormal flight. LowAltitudeWarningSystem(LAWS) Thelow altitudewarningsystemis used towarnthe pilot ofimpendingdangerduetolowaltitude.The warningsystem consistsoftwowarninglights and an aural warningtoneheard inthepilot'sheadset that operates inconjunction withtheAN/APN-141radar altimeter.Onewarninglightislocated underthe glareshield(figure1-6),and theother,whichistheI radarlowlimit warninglight,islocated adjacentto theradar altimeter(figureFO-2).WhentheAN/ APN -141radar altimeter indicator pOinterdrops below thepreset low-limitindexer altitudesetting, both warninglightscomeonandtheaural warning toneisactivated for2seconds.Thewarningtoneis an alternating 700- to1700-cpstonewith arepetition rate of2cps.Inaddition,areliability warningsig-nalsoundsfor2secondswhentheradar altimeter acquiresor losesitslock-on.Thereliability warn-ingsignalhasthesamefrequencyrangebut arepeti-tionrate of8cps. ANI AJB-3AAll-AttitudeIndicator Anall-attitudeindicator for theAN/AJB-3Asystem is located ontheinstrument panel(figureFO-2).The~ indicator providesthe pilot with apictorial presenta-tion oftheaircraft's pitch,roll,heading,and turn-and-slip.Aircraft attitudereferencesignals are supplied totheindicator byelectrical connection with theremote mountedmaster reference platform. Pitch,roll,and heading areshownbytheorientation oftheall-attitudesphere with theminiaturerefer-enceaircraft attached to theinstrument face.A bank inclinometer and anelectrically powered rate-of-turn pointerlocated belowthespherecomplete theindicator presentation.Thehorizon is shown as awhitelinedividingthetopand bottomhalvesofthe sphere.Theupperhalf,symbolizing sky,is indi-cated byalight grey area abovethehorizon line; thelower half,symbolizing earth,is indicated bya dullblack area belowthehorizon line.Thesphere isgraduated every5degreesin azimuth onthe horizon line and every30degrees in azimuth in the upperand lower portionsofthesphere.Thesphere isgraduated every10 degreesofclimb and dive. Thesphereis freetomoveafull360degrees in pitch,roll,or heading without obstruction.Roll indices are located onthetopand bottomofthe indicator. A verticaldisplacement pointer,vertical and hori-zontaldirector pointers,vertical and horizontal director warning flags,and averticaldisplacement warning flagare incorporated in theinstrument but are not used.Allflagsand pointers are biased out 1-43 Section I Part 2 NAVAIROl-40AVF-l ofsight at the end ofthe60-second start period.The OFF flagdisappearsat theend ofthe 60-second start period andshould notreappear untilthesystem is turned off.Appearance oftheOFF flag after the 60-second start period indicates apower failure in thesystem.Amaximumof90secondsmaybe required forgyroerection and amplifier warmup. WARNING 1__-Donotrelyon indicator,includingrate-of-turn pOinter,if OFF flagis visible. It is possible toreceiveerroneous indications ongyro indicator withoutOFF flagshowing. Theturn-and-slip indicators are located belowthe C'J sphere and are an integralpart ofthe all-attitude ~indicator.A one-needle widthdeflection ofthe turn 1-44 indicator willresult in astandard rate,2-minute, 360-degree turn.Fulldeflection(two-needle widths) results in a1-minute,360-degree turn.Theturn indicator is electrically driven and willoperateon emergency generator. A pitch trim knob,located on the lowerright corner oftheindicator,with an indexmark at its 10o'clock poSition,controls thesphere pitch setting inrelation tothereference aircraft.Adjustment can bemade from10 degreesnoseupto5degreesnosedown. Theindicator is calibrated todisplay,at anypitch angle,the true aircraft attitude(Armament Datum Line)in relation to thesurface oftheearth,with pitch trim knobaligned totheindex mark.It is recommended that thepitch trim knobalwaysbe aligned totheindex mark before flight andbe left in that position throughout the flight.Thiswillenable thepilot toalwaysknowhistrue attitudeinrelation to thesurfaceoftheearth regardlessoftheman-euverperformed. NAVAIR01-40AVE-1Section I Part 2 LIQUIDOXYGENDURATION 10 LITERSYSTEM DATAASOF:1 February1962 DATABASIS:SpecificationMIL-I-19326(Wep} CABIN PRESSURE ALTITUDE -FEET-108 40,000UP60.648.5 35,00037.029.6 30,00027.221.8 25,00020.416.4 20,00016.012.8 15,00012.810.2 10,00010.08.0 5,0008.46.6 SEALEVEL7.05.6 REMARKS: (1)Basedon800litersof gaseousoxygen perliter ofliquidoxygen. (2)Dataassumetheuseof a properlyfittedmask. HOURSREMAINING GAGEREADING (LITERS) 6421 36.424.212.04.8 22.214.87.43.6 16.410.85.42.8 12.48.24.02.0 9.66.43.21.6 7.65.22.61.2 6.04.02.01.0 5.03.21.60.8 4.22.81.40.6 HHl-22 Figure1-16.LiquidOxygenDuration DURINGFLIGHT Oxygenquantityshouldbechecked periodically during flight. NOTE Separationoftheoxygen hosecouplings will beimmediatelyapparentasoxygenflowand radiocommunication willcease. FLIGHTINSTRUMENTS Theairspeed indicator,vertical speedindicator,and altimeterare connected tothepitot-staticsystem. Theattitudegyro,standbyattitudegyro,bearing-distance-headingindicator(BDID),angle--of-attack-system,andradaraltimeter areelectrically operated.Theeight-dayclock and accelerometer are independentofothersystemsinoperation. AIRSPEED INDICA TOR Acombinationairspeed indicatorandMachmeter (figure1-7)islocated on theinstrument panel.The airspeedportion of thedial is fixedin position,and is calibrated from80to650knots.TheMachmeter scaleis arotating disc,marked from0.50 to2.9, turningbeneath theairspeed dial.Onlyaportion of thedisccan beseen through acutoutin theairspeed dial.Airspeed and corresponding Machnumber are indicatedsimultaneously byasingleneedlepOinter. OntheMachnumberdiscis amovableindexwhichis used toset aMachreferencebydepressing andturn-ingaset knobon thelowerleftcorner oftheinstru-mentcase.Ontheedgeoftheairspeed dial isan airspeed indexpOinter,whichis adjustable througha rangeof80to145 knotsmerely by turning theset knob. VERTICALSPEED INDICATOR A vertical speed indicator(figure1-7)islocated on theinstrumentpanel.Theindicatorshowstherate ofascentordescentof theaircraft.Theupper half oftheindicatorfaceisgraduated in500-foot units from0to6000feet with100-footscaledivisions from0to1000feet.The upper halfoftheinstrument indicatesrateof climb in thousandsoffeetpermin-ute.Thelower halfoftheindicator faceis identical to theupper half except that it indicatesrateof descent.Thevertical speed indicator is connected to thestaticpressuresystemoftheaircraft andmea-sures thechangeinatmospheriCpressure asthe aircraft climbsor descends. ALTIMETER Thepressure altimeter(figure1-7)indicates the altitudeoftheaircraft abovesea level toaheight of 1-47 SectionI Part 2 NAVAIR01-40AVF-1 50, 000 feet.The dial faceis marked inincrements of11feet;eachcompleterevolution ofthe pOinter indicates achangein altitudeof1000 feet.Onthe left of thecenter of theinstrument is awindowcon-taining tworotating counters; theinnercounter regis-ters altitude inthousandsof feet,whiletheouter registers in ten thousandsof feet.Whenthealtimeter pointermakes12revolutions,forinstance,theouter counter will indicate1,and theinner counter will indicate2,thusshowing that theaircraft is at an altitude of12, 000 feet abovesea level.Barometric pressure setting,in millibars,is displayedin awin-dowontherightSide of thealtimeter face.The knob onthelowerleft corner oftheinstrument case is usedtocorrect forvariationsinsea level barometric pressure. RADAR ALTIMETER TheANIAPN-141radar altimeter(figure1-7) employsthepulse radartechniquetofurnish accurate instantaneous altitudeinformation to the pilot from0 to5000 feet terrain clearance.Aircraft height is determinedbymeasuring theelapsed transit time of aradar pulse,whichis converted directly toaltitude in feet anddisplayed on thecockpit indicator.The indicator dial faceis markedin10-foot increments upto200 feet,50-foot increments from200to600 feet,100-foot increments from600to2000 feet,and 500-foot increments from2000to5000 feet.Acon-trol knob onthe front of theindicatorcontrols power to the indicator andis used forsetting thelow-limit indexer.Thecontro Iknob also provides for preflight andin-flight test of theeqUipmentwith apush-to-test typecontrol knob feature.RefertoLOWALTI-TUDEWARNINGSYSTEM(LAWS)forinformation regarding lowlimit indexer.AnOFF flagonthe indicator faceappears whensignal strength becomes inadequatetoprovidereliable altitudeinformation, whenpowertothesystemis lost,or whenthesystem is turnedOFF. 1-48 LeavetheANIAPN-141radar altimeterin theOFF position until power is appliedto theaircraft andreturn equipment toOFF before powerisremoved. NOTE Ataltitudesabove5000 feet terrain clearance, theOFF flagwill appear andthe pOinterwill movebehindthemasked portion oftheindi-cator dial.The pOinterwillresumenormal operation whentheaircraft descendsbelow 5000 feet. Theradar altimeter operates normally during 50-degree anglesofclimb or dive and30-degree angles ofbank,right orleft.Beyondthese pOints,the indi-cationsontheradar altimeter become unreliable but will resume normal operation whentheaircraft returns to normal flight. LOW ALTITUDEWARNINGSYSTEM(LAWS) Thelow altitude warningsystemis usedtowarn the pilot ofimpending danger duetolow altitude.The warning system consists oftwowarninglightsand an aural warning toneheardinthe pilot'sheadset that operates inconjunctionwiththeANIAPN-141radar altimeter.Onewarning lightislocatedunderthe left Sideoftheglare shield(figure1-5),andtheother, which is theradarlowlimit warninglight,islocated adjacent to theradar altimeter(figure1-7).When theANIAPN-141radar altimeterindicator needle dropsbelow thepreset low-limit indexer altitudeset-ting,bothwarning lightscomeonandtheaural warn-ing toneis activated for2seconds.The warning tone is analternating 700- to1700-cpstonewith arepe-titionrate of2cps.In addition,areliability warn-ing Signal sounds for2secondswhentheradar altimeter acquires or losesitslock-on.Therelia-bility warning signal hasthesame frequency range but arepetition rate of8cps. AN/AJB-3A ALL-ATTITUDEINDICATOR Anall-attitudeindicator fortheANIAJB-3A system islocatedontheinstrument panel(figure1-7).The indicator providesthepilot withapictorial presenta-tion oftheaircraft's pitch,roll,heading,and turn-and -slip.Aircraft attitudereferenceSignals are suppliedtotheindicator by electrical connection with theremote mountedmasterreference platform. Pitch,roll,andheading are shownbytheorientation oftheall-attitudesphere with theminiaturereference aircraft attachedtotheinstrument face.Abank inclinometerandan electrically poweredrate-of-burn pOinterlocatedbelowthesphere complete theindi-cator presentation.Thehorizonis shown as awhite line dividing thetop andbottomhalves ofthesphere. Theupperhalf,symbolizing sky,is indicatedby a lightgrey area abovethehorizonline;thelowerhalf, symbolizing earth,is indicatedby adull black area below thehorizonline.Thesphere is graduated every5 degreesinazimuth on thehorizon lineand every30 degreesin azimuth in the upper andlower NAVAIR01-40AVF-1Section I Part 2 portions ofthe sphere.Thesphere isgraduated every 10 degreesofclimb and dive.The sphere is freetomoveafull360 degreesinpitch,roll,or heading withoutobstruction.Rollindices arelocated onthetopandbottomoftheindicator. A vertical displacement pOinter,vertical andhori-zontal director pOinters,vertical andhorizontal directorwarning flags,andavertical displacement warning flag are incorporated in theinstrument but are not used.All flagsandpointers are biased out ofsight at theendofthe60-secondstart period.The OFF flag disappears at theendofthe60-secondstart period andshould not reappear until thesystemis turnedoff.Appearance oftheOFF flag afterthe60-secondstart period indicates apower failureinthe system.Amaximumof90secondsmay berequired forgyroerection andamplifierwarmup. Donot rely onindicator,including rate-of-turn pOinter,ifOFF flagis visible. It is possibletoreceiveerroneous indications ongyroindicator withoutOFF flag showing. Theturn-and-slip indicators arelocatedbelowthe sphereandare an integral part oftheall-attitude indicator.A one-needle width deflectionoftheturn 1-48A J NAVAIROl-40AVF-lSection I Part 2 TODISENGAGEAFCS The pilotmaydisengagetheAFCS by oneofthe followingactions: 1.Pressing controlstick AP button. 2.Placing thestandbyswitch in OFF position. 3.Placing both theengageand thestability augmentationswitches in their OFF positions. 4.Depressing thePUSHTO SYNCbutton on thecompasscontroller. 5.Movingthe SETHDGswitch onthecompass controller. 6.Placing theaileron trim NORM/EMER switch in EMER position.Intheevent theswitch-over fromautomatictrim to manualtrim malfunc-tions,or upondisengagement,theEMER position givesanadditionalswitchover and willdisengage the AFCS. 7.Movingthehorizontalstabilizer manual override lever onthe left console willmanually overcome malfunction oftheautomatic pitch trimmer. NOTE Upto4secondsofoverride lever actuation may be required before disengagement occurs. 8.Pulling theemergency generatorrelease handle. LIGHTINGEQUIPMENT InteriorLights The interior lighting system includes all instrument lights,console lights,and cockpit floodlights.A light is mounted in each instrument lens(except the oilpressuregage)to provideequalillumination over theentire faceoftheinstrument.Two floodlights are mounted oneachsideofthegunsight beneath the glareshield toprovide auxiliary or emergency light-ing oftheinstrument panel.A white kneeboard floodlightincorporating ared filter is mounted on thegunsightsupport ontheright-handside topro-vide lighting forthepilot's kneeboard.Six red floodlightsare installed toprovide auxiliary or emergency console lighting.Four white floodlights are provided for auxiliarycockpit lighting foruse with the thermalradiation closure.Instrument and console lights and thered floodlightsare operative onemergency generator. Interior LightsControlPanel An interior lights (INT LTS) control panel (figure 1-23) mounted ontheright console,containsswitches for theoperation of all interior lightsexcept the four high-intensity white floodlights.Tworotary switches, marked INSTandCONSOL ESare turned clockwise fromOFF to turn on theinstrument lights and con-sole lights,respectively.Additimal turning in a clockwisedirection toward the BRIGHTpOSition increases the intensity ofthelight. Aircraft reworked per A-4 Interim AFC428havea two-position interior lighting interrupter switch installed.Theswitch (labeled NORMALandCOM-BAT)is located ontheright-hand gunsight support adjacent to the pilot's kneeboard light (figure1-23). WhentheNORMAL,COMBATswitch is in NORMAL pOSition,instrument panel and console lights are controlled normally bythe lightscontrolswitches onthe interior lightscontrol panel.Whenthe instru-ment paneland console lights are on normally, plaCing theswitch in COMBATposition willcut off allconsole and instrument panel lightsexcept thoseI forthe all-attitude indicator,accelerometer,air-speed indicator,vertical velocity indicator,altim-eter,BDHI,and eight-day clock. NOTE When the INSTlightsswitch is in anyposi-tionother than OFF,the ladder lights are dimmed fornight operations and maynot be visible in daylight. A toggleswitch labeled FLOOD,with three pOSitions, BRIGHT,DIM,and MEDIUM,controlsthe intensity ofthered floodlightsafter theCONSOLESswitch is turned fromtheOFF position.The pilot's kneeboard floodlighthasaseparateintensity control onthecase. The fourhigh-intensity whitefloodlights,two forthe instrument panel and one foreach console,havea common control installed abovetheright-hand con-sole on the fuselageskin.Clockwiserotation from theOFF pOSitionturnsthe floodlightsondimly and furtherclockwiserotation increases the intensity. ExteriorLights The exterior lightssystem includesposition lights, fuselagewing lights,air refueling probe light,an approach light,and ataxilight.Asemiflush,white, high-intensity gasdischarge and low-intensity fila-ment fuselagewing light is located under theleading edgeofeach Wing.Theaircraft has two flashingred anticollision beacons,onemounted onthetopofthe fuselageand theother mounted on the left main landing gear strut fairing.Theangle-of-attack approach lightsare mounted in the leading edgeof theleft wing(figure1-24).Thetaxilight is installed ontheright-hand main landinggeardoor. The air refueling probe light is located ontheright-hand intakeduct forward outboard lip(figure1-24). Wingtip,tail,and fuselagelightsare actually double lights,as both filament and gasdischargetypesare 1-83 Section I Part 2 1-84 NAVAffi01-40AVF-1 A REDFLOODLIGHTS B WHITEFLOODLIGHTS CPILOT'sKNEEBOARD o NORMAL,COMBATSWITCH INTERIORLIGHT CONTROLPANEL \I SPARELAMPS RECEPTACLE \ Figure 1-23.InteriorLights ZZl-8 NAVAIR01-40AVF-lSection I Part 2 JA TO ARMINGSWITCH The JATO armingswitch is atwo-position lever-lock toggleswitch labeled ARMED andOFF.To place theswitch intheARMED position,thespring-loaded toggle lever must be lifted.This arms the JATO firingcircuit byenergizing theJATO firing buttonon thecatapult handgripand thejettison cir-cuit tothejettison switch. JA TO ARMEDINDICA TORLIGHT A JATO armed indicator light onthecontrolpanel comesonwhenthearmingswitch is energized.The press-to-test featureofthislight teststhe bulb. JA TOJETTISONSWITCH The JATOjettison switch on thecontrolpanelis a guarded,momentary-controltoggleswitch,spring-loaded totheSAFEposition.In theJATO JETT position theswitch energizesasolenoid-controlled hydraulicselector valvewhichdirectshydraulic pressure totheJATOmountinghookactuatingcylin-ders.Themounting hooksare actuated torelease both JATO bottlesSimultaneously. WhenJATO bottlesare installed,operation oftheemergencyspeedbrakecontrolwill forcetheJATO bottlesofftheaircraft resulting in airframe damage. NOTE Aninterlock in thespeedbrakeelectrical circuit preventsnormaloperation ofspeed-brakeswith JATO bottlesattached.Besure thespeedbrakeswitch onthethrottle is in theCLOSED position prior tojettisioning the JATObottles;otherwise,uponrelease ofthe JATObottlesthespeedbrakes willopen. JATOFIRINGBUTTON TheJATO firingbutton(figures1-5and1-6),located at theend ofthecatapult handgripenergizesarelay whichcompletesthecircuit tothefiringmechanism. Refertosection XI,PerformanceData,foraddi-tionalinformation ontakeoff airspeeds with JATO anddistancesat which the JATO bottlesare fired. I WARNING' To prevent possible JATOsystem accidents, theJATO armingswitch inthecockpit shall beatOFF and ano-voltagetest shall be madeat theaircraft igniter terminals prior toattaching the JATO igniter leadstothe bottles. BANNERTOWINGSYSTEMEQUIPMENT Bannertowingsystemequipment consistsofabanner target,towline,banner towing platformassembly, andrelease unit assembly.Thebanner towingplat-formassemblysuspends fromtheAero 7 A-Iejector rackontheaircraft centerlinestation (figure8-2). Targets Standard Navyor AirForce 71/2x40 feet or 6x30 feetbannertargetsmaybeutilized. Towline Recommended towlineconfiguration is1950 feetof 7/16-inchnylontowlineattachedto50feetof7/32-inch armored cable leader.Thearmored cable leader isrequired at the towplaneend ofthetowline toprevent burn through which willoccur if an all nylontowlineis used. AircraftTowlineAttachment For detailon thebanner towingsystem installation ontheAero7 A-I centerlineejectorrack refer to NAVAIR01-40AVF-2. Refertosection VIIIofthissupplement fortowline/ target release andbannertowing platformassembly jettison procedures. MISCELLANEOUSEQUIPMENT ThermalRadiationClosure Athermalradiationclosuremaybeinstalled onthe canopystructure foruseonmissionsrequiring pilot protectionfromtheheatandlightproducedby nuclearexplosions. Theclosureconsistsoffixed fiberglasspanelsand a manuallyactuated segmented telescopinghood(buggy top)attached tothecanopy.Theglareshield installa-tionincludes light seals and an extension ontheaft end.Whenthecanopy isclosed,the fixedpanelon thecanopymatchestheglareshield in contour and 1-93 Section I Part 2 NAVAIR01-40AVC-1 formsaglare shield extension.Thebuggytop pivots downandformsalight seal with thefixedpanelcom-pletely sealing the pilot withinathermal protective covering.Attached to theforwardsegment of the buggytop are right andleft handholdsforopening and clOSingasrequired.Theright handholdcontains a latchingmechanism forlocking thebuggytopin the open(stowed)position.TwodetentreadypOSitions hold thebuggy toppartially open forforwardvisibil-ity.This affordsthepilot partial protection in the eventof asurprise burst andshortens thetime required to gofromthereadyposition tofullyclosed. Buggytop shouldstayindetented positierA-4 AFC 353-11) is bypassed allowingmaximumpower to thegunsight reticle light controlrheostat.With theswitch in the NIGHTposition,power is directed through thegun-sight light resistor circuit,resulting in lower light intensity variancecontrolled by thereticle light controlrheostat. Aircraft reworked perA-4 AFC388haveconcentric light intensity control knobsonthegunsight lighting controlpanel.Theinner knurled knob,within the gunsight light control knob,is labeled CMPTR LT and controlsthe intensity of theCP-741/A computer LOCK ONand INRANGEdisplay lights.Thecom-Iputerdisplay lights are mounted onthe uppergun-sight assembly forpilot convenience.Althoughthe CMPTR LT control knobdoesnothaveadirect func-tion in gunsight light control,it enables the pilot to adjust theintenSity of thedisplay lightsat themost comfortable level forgunsight vision. BannerTowingSystem The banner towingsystem utilizestheaircraft weaponnormalreleasesystem andtheAero7 A-1 centerline ejectorrack in conjunction with the banner towing platform assembly and therelease unit assembly (figure 8-2). Thebanner towingassembly is suspended fromtheAero7 A-1ejectorrack.Release ofthe banner towtarget is accomplished with the aircraft weapon normalrelease system as follows: 1.MASTER arm switch.........ON 2.STATIONSselect switch 3.Functionselectorswitch 3READY BOMBS& GMARM 4.Bombrelease button........DEPRESS Thebanner towing platform assembly can bejetti-soned bymeansoftheaircraft emergencyrelease system. 1.Emergencyselect (EMER SEL) switch............. .STATION3 2.Emergencystores (EMER BOMB)release handle......PULL 8-5/(8-6blank) NAVAIR0l-40AVE-1Sectionvm TABLE8-2.EJECTION VELOCITIES Recommended CP-741/A Store WeightEjectionVelocityEject Velocity Rack(lb)(fps)(fps) MER/TER-7All*5 PMBR/MBRAll00 Aero-7A-12503535 (1MK1 MOD250029.530 andMK2 MOD0 Cartridges)75025.525 100022.720 200016.515 Aero-20A-12502425 50019.520 75015.415 100012.510 *TheMER/TER-7ejectionvelocitynormal tofuselagereference planevaries withrack station and store weight.Thisvarianceis from4.3 fpsto9.3 fps.Byusing anaverage5 fps(switch moduleejec-tionvelocitiesareset in5-fpsincrementsfrom0 to45fps).setting themaximumsystem error dueto theejection velocity will beless than5 mils. bereset in flight.Parameters which are set into the weapon control panel fordive-tossbombing are: 1.ATTACK MODEswitchto TOSSor STIK. 2.Ballisticselectorswitchtothemodulecorres-pondingto theordnanceto bereleased. 3.BURSTheight appropriatetotheordnance/ fUZing/targetcombination. 4.TARGET heightabovemean sea level. 5.D-VALUEasdetermined from worksheet. Settingsin steps4and5are used onlyinBAROmode tossbombing andperformno functionduring RADAR modeattacks.However,radarmalfunctionor failure to achievelock-on isanever-present possibility.If noradarranging information is provided to theC P-741/A computer,theCP-741/A computer will auto-matically usethevaluesset into theweaponcontrol panel tocomputeaBAROsolution.Therefore,pilots should set into these controlsthebest availablein-formationforan alternativeBAROmodeattack in casetheradar doesnot functionasplanned. Thepreflight procedureforpreparing theAN/APG-53Bradarto functionin itsair-to-groundmodeis describedinSection 1. Turnonthegunsight,set it at the desired brilliance, conductoptical boresight,check andensurethat the sight drum is set at 0milssight depression. Ifmultiplereleases are planned,the AWE-1cockpit intervalometershould be set up forstick bombing. (RIPPLEmodeand interval.)TheC P-7 41/Asends outthefirstreleasesignal and theintervalometer sendsout all additional releases.Therelease signal (aural tone)fromthecomputer continuesuntil the last bombisreleased.In STEP mode,toneceases when bomb buttonisreleased. AFTER ENGINESTART TurntheRadarModeSelector Switch to STANDBY. Allowat least 3minutesforequipment warmup prior toselecting anoperatingmodeof theradar. THEDELIVERY Thearmament switchesareset up as follows: 1.AWE-lQUANTITY, INTERVAL AND MODE ..SELECTED 2.NOSE/TAIL ARM or AWW-1..........SELECTED 8-33 Section VIIINAVAIR01-40AVF-1 3.MIL Setting......ZERO 4.CP-741/A Weapon ControlPanel........SET 5.Radar........A/G 6.station Selector Switch.............DESIRED STATIONS 7.Function Selector Switch............BOMBS&GMARM 8.Master Armament Switch.............ON NOTE H(INT)AAC444is not incorporated in AWE-1, positionmaster arm switch toON beforeturn-ing AWE-1on. Maneuver theaircraft to bewithin thecapability envelopeofthecomputer bombingsystemat time of pullup(figures8-11and 8-12).Maxi.mumslant rangeis 22,500 feet,or amaximumaltitudeof 15,000 feet in theBAROmode. Afterensuring that theINRANGElight is illumi-nated,the pilotmay initiatehisrelease at any time hedesires.Torelease thebombs,put thepipper on the target,depress the bombrelease button,and establish a2- to6-g pullup.It is notnecessary to flyagscheduleduring thepullup.However,a higher gduring pullup willprovideamorerapid releaseand reducethedownrangetravel oftheair-craft.These factorswilltend toimprove the accuracy ofdelivery.Therefore,fly themaneuver at thehighest gload that is comfortable.The bomb release tonewillcome on whenthe bombrelease button is depressed and gooffwhen thelast bomb selected is automaticallyreleased.H astepmode oftheAWE-1is used,the tonewillgooffat bomb button release. Whenrepeatedpassesare planned,astraight and level leg ofat least 1minutewillpermit precession of theAJB-3A Gyrotobecorrected. The CP-741/A bombingsystemdoesnotprovide corrections fortheeffects of theexistingwind.Either of twoapproachescan be used tocorrect forthese 2.Track thetarget with thepipper.Crosswind effectswillrequire the upwind winglow tokeep the pipper on target in coordinated flight.Depress the bomb button whilemaintainingthe pipper ontarget and pull up in theplane perpendicular totheplaneof thewingsat thetime ofpickle.Thismaneuvercor-rects forone-half oftheeffects ofcrosswind.To correct also fortheeffectsofrangewind,keep the pipper vertically aligned with thetarget butoffset theaimpointalongtherun-in track into therange wind component. Large impact errors can beexpected whenmaking repeated runsin theBAROmodeat low diveangles. Vertical gyroprecession willresultin slantrange error input tothecomputer. For best accuracy,a2- to4-second tracking timeis recommended.Therecommended tracking timeis notmandatory butwill improveaccuracy.Thetwo most importantitemsare(1)"In-Range"light illumination anj(2)steady pipper tracking. Accuracy is seriously degraded ifbombrelease button isdepressedwhilepipperissweepingthroughthe target. Donotreleasebombsif the"In-Range" light is notilluminated.This lightindicates the computerhasabombingsolution.Release atslantrangesnear10, 000 feetwithoutan "In-Range"lightcanresult in impact errors up to3000 feet. NOTE Theinformation in table8-3willallow addi-tionaluseoftheMK76series and theMK76 weapon adapter modules until specific mod-ulesareavailable. STATIONLOADING RefertoConfidential SupplementNAVAIR01-40AVC-1A or A-4/TA-4TacticalManual,NAVAIR 01-40AV-IT. effects:MISSILE,AIR-TO-GROUND 1.Offset theaim point intothewindadistance that willcompensate fortheeffects ofthewindat releasealtitude. 8-34 Refer toConfidential SupplementNAVAIR0l-40AVC-lA,Confidential SupplementNAV AIROl-40AVF-lA, or A-4/TA-4Tactical-Manual,NAVAIR0l-40AV-1T. NAVAIROl-40AVF-lIndex Abbreviations to Altitude ALPHABETICALINDEX A Abbreviations,Symbolsand Definitions..... . AbortingaSection Takeoff................ AbortingTakeoff.............. AccelerationLimitations ...... AFCS speedenvelope......... versusgross weights....... Accelerometer................. ACPowerDistribution........ emergency................. normal ...... ADF /UHFCircling Rendezvous ..... ADF /UHFRunning Rendezvous.............. AFCSModes............ . altitudehold.............. attitudehold................. controlstick steering(CSS)..... . groundcontrol bombing .......... heading hold........... preselect heading ........ . stability augmentation ..... . AFCSPerformance andPower Limitations .......... . AFCSSpeedEnvelope........ . Ailerons............. . control .... . rolls..... . trimrunaway trimsystem..... . AIMSTransponderIdEmtification System ..................... AirConditioning................ . cabin pressureswitch ......... cabin temperaturecontrol........ . cockpit fogandsnowsuppression... . cockpit pressurization chart...... controlpanel............. defrost ................... andpressurization system ........ . temperaturecontrol failure....... windshield defrost switch........ . Aircraft,the ................... airframe majorcomponents ....... . AN/ ALE-29Achaff dispensing system ................... . catapult malfunction,or........ cockpit,A-4Egeneralarrangement. cockpit,generalarrangement. description................ . dimensions,principal ......... andengineoperation signals.... . generalarrangements ......... . main differences............ . modelA-4G........... . operatinglimitations........ . servicing................ . systems................. . towlineattachment.......... . PageNo. TextIllus 11-2 5-4 5-3 1-135 1-45 1-25 1-25 1-25 4-20 4-20 1-79 1-79 1-79 1-79 1-80 1-79 1-79 1-79 1-135 4-1 1-27 4-5 5-36 1-27 1-53 1-86 1-86 1-88 1-89 1-86 1-89 1-86 5-39 1-88 1-1 3-28A 1-3 1-4 1-129 1-97 1-13 1-93 1-138 1-137 1-138 1-88 1-87 1-5 1-10 1-8 I-lOB 7-14 1-6 1-12 1-0 Air Refueling............ banner towtarget operation.... beforetakeoff.......... charts................... control panel ............ drogueextension,' .......... drogueposition indicator ... drogueswitch....... droptank transfer during.. .. flight procedures - refueling training and refresher....... fuelconsumption oftankerduring.. fueltransfer switch............ . gallonsdelivered counter...... . hosejettison switch...... jettisoning the fuelingstore.. light switch ......... masterswitch ..... mission refueling ...... night flyingprocedures... . normaloperation....... . pilot technique ....... receiver system ship-tank switch signals ...... . store ....... store dumplight store failure........ . storelimits ......... tankerfuelavailablefortransfer.... tankerfueltransfer time ........ . tankeroperation....... . tankersafety precautions tanker speedenvelope .... tankersystem............. Airspeed andaltitudecorrection forposition error.................. altitude,mach numbercorrection for position error computerair data...... . conversion........... . corrections indicator............ . limitations........... . operating flightstrength diagram Airstart ............ . AJB/AJB-3AFailures Altimeter..... . corrections .. . radar ....... . Altitude airspeedcorrection forposition error ................. . airspeed,mach numbercorrection forpositionerror...... . chart,density................ . PageNo. TextIllus 4-22, 11-63, 11-131 4-29 4-22 11-63 1-91 4-22 1-91 1-92 1-92 4-27 11-65 1-92 1-91 1-92 4-23 1-92 1-91 4-28 4-28 4-22 4-26 1-92 1-92 1-91 1-91 5-39 4-26 11-64 11-64 4-26 11-63 1-91 1-56 11-4 1-42 1-131 5-9 5-38 1-42 11-5 1-43 11-69, 11-135 7-14 11-67, 11-133 11-68, 11-134 4-24 11-66, 11-132 11-14 11-13 11-8 1-136 1-136 11-14 11-13 11-9 Index1 Index ANIAJB-3A toBraking chart,ICAOstandard .. ANIAJB-3All-Attitude Indicator ANIAJB-3AAll-Attitude Indicator. ANIAPA-89Coder(SIF). ANIAPG-53A RadarSystem air-to-ground mode.. components ... controls...... emergencyoperation and malfunctions ground procedure. indicator(scope).. in-flight procedure .. operating modes ... ANIAPG-53B Radar System . ANIAPN-153 (V)Radar Navigation Set (Doppler)....... AN/APN-154(V)Radar Beacon ... C44191 APN-154(V)ControlPanel . ANIAPR-25(V)Homingand Warning System .... ANIAPX-6BTransponder(IFF) ANIARC-51AUHFRadioCommunication System .... audioisolationamplifier c-65551ARC-51Aradio set control panel ...... electronic equipment ANIAPX-64(V)(IFF)Radar Identification System .... ANIARR-69(UHF)Auxiliary Receiver System.. ANIASN-19ANavigationComputer Set controls...... flightsgreater than1000 miles . in-flight .... operational procedure . ANIASN-41Navigation Computer System ... ANIASN-41Navigation Computer Set...... air massmode .. controls..... dopplermode .. memory mode .. operational procedure Angle-of-Attack System .. approach light .. approach light arresting hook bypass....... external approach light . indexer lights . indicator.. relationship.. AntennaLocations. Antiblackout System... AntiexposureSuit Ventilation . AntifoggingCompound..: Anti-Icing System .... control ... engine... pilot andangle-of-attack vane Approach carrier-controlled(CCA) high precautionaryIflameout ..... light system - angle-of-attack lowprecautionary.. low-visibility ApproachPower Compensator precautionary. Index2 NAVAffiOl-40AVF-l Page No. Text 1-43 1-44 1-50 lllus 11-11 1-651-66 1-72 1-65 1-65 1-75 1-73 1-68 1-73 1-68 1-751-74 1-631-64 1-64A 1-64A 1-51, 1-53 1-50 1-51 1-52A 1-52A 1-52B 1-52A 1-52 1-561-57 1-56A 1-59 1-58 1-58 1-59 1-60 1-60 1-60 1-60 1-62 1-46 1-48 1-48 1-46 1-46 1-61 1-47 4-144-15 1-89 1-94 6-8 1-89 1-89 1-89 1-90 3-27 6-7 4-14A 5-42 1-52A 5-43 1-47 5-47 typical ground-controlled... Armament.......... controls....... controls...... control stick switches .... equipment ...... gunsight ......... gunsight reticle light control.... panel .............. signals...... systems.... Arming and Safing Signals... Arrangement,A-4ECockpit.. Arrangement,A-4GCockpit... Arrangements,General . Arrested Landing andExit Fromthe Landing Area......... Arresting Hook...... AsymmetricLoadLimitations. catapult launches with asymmetric loadscrosswindsvsexcess endspeed required...... wing station nomogram.... Audio Isolation Amplifier..... AutomaticFlight Control System AutomaticFlightControl System(AFCS)....... aileron trimnorm-emergency switch............... aircraft structural protection.. altitudeswitch ...... control stick ........ control stick disengage.. direction findingequipment. engageswitch..... heading select switch... lateral hydraulic disengage limitations......... modes......... normalin-flight operation.... panel........... preflight procedure.. .... preflight text panel......... safety features ............. stability augmentationswitch . standby switch ..... ~... temporaryoverpower . AXC-666AirData Computer.... B Bailout .......... BannerTowingPlatform andRelease Assembly Banner Towing System......... aircraft towline attachment......... eqUipment ...... failure.............. operation............. targets ........... towline ..... Barricade Strap Detents.... Bearing-Distance-Heading Indicator(BDHI) ........ BingoEndurance...... BingoRange............ Brake Reservoir Servicing BrakesFailure DuringTaxi... Brakes,Hot........... Braking Techniques..... PageNo. Text 7-13 8-1 8-2 8-3 8-1 8-4 8-4 8-1 8-1 3-26 1-32 1-135 1-48 1-76 1-78 1-80 1-78 1-78 1-80 1-55 1-76 1-76 1-80 1-135 1-79 1-82 1-76 1-80 1-78 1-80 1-78 1-76 1-80 1-56 5-32 8-5 1-93 1-93 5-40 4-29 1-93 1-93 1-32 1-45 1-112 5-2A 5-3 3-16 lllus 6-5 7-13 7-16 1-8 1-10B 1-6 1-137 1-134 1-77 8-5 11-60 11-27 11-48 11-115 1-113 Briefing .......... air intelligenceand special instructions ........ communications ......... emergencies..... mission......... navigationand flight planning.. safety precautions..... weapons.......... weather...... BullpupAdaptiveControl(ARN-77). C C-1457/ ARR-40Receiver ControlPanel.... C4419/APN-154(V)ControlPanel.. C-6280(P) APX Transponder Set ControlPanel........ Canopy controls...... jettison handle ..... jettisoning exterior...... jettisoning interior ..... jettison safety pins ........ lossof ....... Carrier barricade engagement ........ based procedures ........ controlled approach(CCA) dayoperations.. ...... fieldlanding practice(FCLP) . emergency signals.. landing pattern,typical.. night operations.... procedures.......... qualification,andFCLP.... sectionCCA.... wave off bolter pattern... CatapultLaunches....... aircraft or catapult malfunction. enginefailureduring. optimumtrimsettings ...... technique....... with asymmetricloadscrosswindsvs excessendspeed required.... Center-of-GravityLimitations.. Centigrade/Fahrenheit Conversion CheckFlight Procedures, Functional......... after landing ........ approach andlanding.. flightcontrol disconnect procedures..... inflight......;......... pretakeoff........... Checklist preflight .......... pretakeoff .... poststart........ takeoff........... Chugsand Stalls... Climb.. :...... combat ceiling andoptimum cruisealtitude ...... distance .. NAVAIROl-40AVF-l Index Briefing to Communications PageNo. Text 3-1 3-2 3-2 3-2 3-1 3-2 3-2 3-2 3-2 8-1 1-53 1-64A 1-54 1-33 1-33 1-34 1-33 1-34 5-39 5-50 3-23 3-27 3-23 3-19 3-28 3-26 3-27 2-3 3-27 3-28 3-23, 3-26, 3-28C 3-24 5-5 3-24 3-24 1-131 3-22 3-22Q 3-22Q 3-22N 3-22B 3-22 3-3 3-11 3-10 3-8B 4-17, 11-33, 11-107 lllus 3-25 1-137 11-10 3-13 11-3411-39, 11-112 11-37, 11-110 fuel............. speed schedule....... time ............ Clock,Eight-Day ........... Clock,Elapsed-Time.......... Cockpit A-4E generalarrangement. A-4G generalarrangement... canopy............ canopy controls.......... exterior canopyjettisoning..... interior canopyjettisoning ....... enclosure.............. fogand suppression........ pressurization ............ typical left,instrument,and right panels,A-4E ...... typicalleft,instrument,and right panels,A-4G ...... ColdWeatherOperations ..... beforeentering theaircraft..... before starting engine ...... before takeoff........... descent.......... during flight..... .... landing .............. onentering theaircraft...... shutdown and postflight ...... starting and warmup ground check. takeoff ........... taxiing.......... Combat Performance......... maneuverability ......... maximummach number ........ military fuelflow .......... turning radius............... Communications ........... aircraft and engineoperation.... air refueling........... armament ............... arming anddearming signals.... electronic communicationsand navigation............. emergency signals between aircraft flightsignals between aircraft penetrationinstrument approach (noradio)............. formation signals .......... generalsignals............. night tactical signals ....... postflight ground crew to pilot signals radio........... signalsbetween aircraft and surface ships................ starting and posts tart signals ... surface shipone-letter code.... takeoff,changing lead,leaving formation,breakup,andlanding .. visual .............. Communicationsand Associated ElectronicEquipment(A-4E)...... AN/ALE-29Achaff control ... audioisolation amplifier ..... radaridentification equipment Page No. Text 1-46 1-46 1-33 1-33 1-34 1-33 1-33 1-89 1-88 6-9 6-10 6-10 6-11 6-11 6-11 6-11 6-10 6-12 6-10 6-11 6-10 11-81, 11-147 11-82 11-82 11-81 7-1 7-2 7-1 7-2 7-2 7-1 1-48 1-51 1-48 1-50 Illus 11-36, 11-109 11-35, 11-108 11-38, 11-111 1-8 I-lOB F0-1 F0-2 11-85, 11-149 11-87, 11-151 11-88, 11-152 11-84, 11-148 7-14 7-14 7-13 7-16 7-11 7-15 7-15 7-9 7-3 7-17 7-4 7-8 Index 3 Index CommunicationstoEjection security equipment........... . UHFradio.................. . CommunicationsandAssociatedElec-tronicEquipment(A-4F)......... ANI ARC-51AUHFradio communicationsystem........ . ANI ARR-69(UHF)auxiliaryreceiver system ................... . C-1457 I ARR-40receivercontrol panel.................... . radaridentificationequipment.... sec uri tyequipment ............ . CompassController ............. freegyrooperation............ slavedoperation............... CompassSystemFailure .......... ConditionsRequiringFunctional CheckFlights.............. Constant SpeedDriveFilling....... . Constant SpeedDrive(CSD) servicing............ daily inspection......... filling...... ControlStickSwitches... Controls aileron ....... autopilotoverridebutton.... canopy ............... elevator................ emergency speedbrake........ engine.................. andequipment........ flight............... flightsystems failure..... fuel................ fuelselector.......... malfunctionsfuel........... panel,air conditioning.............. panel,engine......... pitch................. roll............... seat sensor .................. stick............... stick steering engage transients during auto trim....... stick steering feel......... stick trim switch.... yaw............. Correction forPosition Error airspeed and altitude ......... airspeed,altitude,mach number........... machnumber........ Crosswindlanding........... Cruise................ climb.......... control ........... descent................ enginepressure ratio for fuelmaximumrange .... long range........ maximumrange .... maximumrange-time and speed ............ , Index4 NAVAIR01-40AVC-1 PageNo. Textlllus 1-49 1-49 1-51 1-51 1-52A 1-52B 1-52B 1-52B 1-53 1-54 1-54 5-35 3-21 1-109 1-107 1-107 1-1081-109 1-30A 1-27 1-78 1-33 1-28 1-32 1-14 1-41 4-1 5-36 1-14 1-104 5-7 1-86 1-14 4-13 4-13 1-37 1-78 1-78 4-13 4-13 1-78 4-13 11-14 11-13 11-15 3-18 4-2, 4-18 4-17 4-17 4-18 11-56, 11-123 11-51, 11-118 11-4111-49, 11-116 11-42 11-50, 11-117 D Danger Areas................ Day Operations....... aircraft or catapult malfunction.......... approach............... arrested landing.......... arrested landing andexitfromthe landing area.............. bolter.............. catapultlaunches........... landing pattern.. ..... :...... postlanding procedures........ . poststart.............. preflight SA TScatapultlaunches...... taxi.............. technique.......... typical carrier-landing pattern wave off................. DCPowerDistribution......... armament bus........... armamentsafety disable switch.................... Debriefing.................. Definitions,Abbreviations, andSymbols.......... Defrost................. Density AltitudeChart.. ......... Descent............ cold weather............ distance.............. fuel maximumrange ......... time................ Differences,Main.............. Dimensions,Principal.... Ditching................... DiveRecovery Chart....... Diving................ DME,Lossof ............... Downedl LostPlaneProcedures..... Drag CountIndex System....... Drag Indexes............ E Ejection.................. automatic barometric parachute actuator........ controlled.............. functionalcomponents.... harness-release actuator ...... immediate.......... seat ...................... . seat attachments............. . seat controls .............. seat stabilization system(DART)... PageNo. TextIllus 1-1221-124 3-23, 3-28 3-28A 3-28B 3-28B 3-26 3-28 3-23 3-24, 3-28B 3-26 3-23, 3-28 3-23, 3-28 3-28 3-23, 3-28 3-28A 3-28B 1-25 1-26 1-26 3-2 11-2 1-89 11-71, 11-137 6-11 11-71 11-74, 11-140 5-58 4-9 5-35 5-40 11-3 5-12 1-36 5-13 1-36 1-36 5-32 3-6 1-37 1-37 1-40 3-25 11-9 11-73, 11-139 11-72, 11-138 1-12 1-4 4-11 11-6 Changed15November1970 seat,zero-zero . sequence ........ sequence.......... sequence - ESCAPAC1and lC-3ejection seats .. terrain clearance forsafe Electrical System ..... acpowerdistribution...... dcpowerdistribution...... emergency generator...... external power switch....... failure...... fire............ fusepanels.............. main generator.............. . Electrical System - A-4G......... . ElectronicCommunications NavigationSignals...... ElectronicEquipment ........ ElevatorControl.... Elevators............ EmergencyProcedures ... '. A-4E/F fieldarrestment data .............. abnormalstarts ......... aborting asection takeoff.... aborting takeoff ........ acpower............ aileron trimrunaway..... air conditioning temperature control failure ...... air refueling store failure..... AJB-AJB-3A failures.......... . bailout ........ banner towtarget failure... blowntireontakeoff ....... carrier barricade engagement .. brakes failureduring taxi.... compasssystem failure ....... ditching................. ejection............ ejection sequence - ESCAPAC1 andlC-3ejection seats ..... electrical fire............ electrical systemfailure ........ enginefailure..... enginefailureafter takeoff.... enginefailureduring catapulting............... enginefailureduring takeoff ............ enginefire.......... enginefireduring start .. enginemalfunctions..... entrance .......... exit........... fire............ flightcontroldisconnect.. flightcontrolssystems failure.................. . flightrelight regions .......... fuelcontrol malfunctions . fuelsystemfailure ....... fueltransfer........... generator .......... generator bypassswitch..... generator releasehandle ... ground .............. NAVAIROl-40AVF-lIndex Electrical toEndurance Page No. TextIllus 5-18 1-35, 1-40, 5-13 5-15 5-15 5-20 1-24 1-25 1-25 1-25 1-25 5-34 5-11 1-26 1-25 F0-5 7-11 1-52 1-28 4-2 5-1 5-49 5-2 5-4 5-3 1-25 5-36 5-39 5-39 5-38 5-32 5-40 5-4 5-50 5-2A 5-35 5-58 5-12 5-15 5-11 5-34 5-8 5-5 5-5 5-5 5-9 5-2A 5-6 5-585-59 5-'57 5-9 5-6 5-36 5-10 5-7 5-37 1-18 1-25 1-25 1-25 5-2 high precautionary/flameout approach............. horizontalstabilizer runaway trim........... hot brakes ........... hydraulicsystems failure... inflight ............... JATO bottlesfailure ..... landing ............. . landing withlanding gear malfunctions.. landing at high gross weights ....... landing gear system... landing - other failures..... landing - useof emergency field arresting gear . ~..... landings with landing gear malfunctions.. landings,forced........... lossofcanopy .... lossof DME..... lost-downed plane procedures...... lowprecautionary approach.. maximumglide......... . night(or IFR)............. no-radio pattern entry andlanding (VFR) ................ oxygen system/mask failure ...... . oxygensupply......... oxygen bottleservicing ... pitot-staticsystemfailure. precautionary approaches..... retraction safetysolenoid inoperative...... rudder trimrunaway... runawaynosedowntrim .. signals betweenaircraft.. signals,carrier....... . smokeor fumes ...... . speedbrakecontrol ...... speedbrakefailure...... . spoiler malfunction.... . starts,abnormal ......... structural failureor damage.............. summary of flameout action .. systemsfailures... . TACANfailure .......... . takeoff ............ terrain clearance forsafe ejection............ . unsafegear-upindication... wingor accessory section fire ............ wing fire ............... zero-zero ejectionseat - O-knot trajectory ................ zero-zero ejectionseat - 600-knot trajectory ............. zero-zero ejection seat sequence... Endurance ........ . bingo..... fouleddeck. maximum... maximumfuel...... PageNo. TextIllus 5-43 5-36 5-3 5-33 5-6A 5-5 5-42 5-51 5-56 1-30 5-51 5-48 5-52 5-57 5-39 5-35 5-40 5-47 5-11 5-42 5-42 5-38 1-41, 1-141 1-1161-117 5-39 5-42 5-5 5-36 5-5 7-15 3-28 5-12 1-32 5-37 5-37 5-2 5-32 5-14 5-33 5-35 5-3 5-20 5-6 5-2A 5-11 5-18 5-19 5-17 11-57, 11-125 11-60, 11-127 11-5711-59, 11-126 11-57 11-62, 11-129 Index5 Index EnginetoFlight maximumspeed ......... Engine................ . and aircraft operation. airstart........... air temperature switch APecontrol panel APepowerswitch.......... APestatus light .............. approach powercompensator.. compressor airbleed system control panel......... exhaust gastemperature and enginespeed......... exhaust gas temperature(EGT) indicator.............. exhaust smokeabatementsystem exhaust smokeabatementsystem -pressure filling.......... exhaustsmokeabatement system servicing failure......... failureaftertakeoff failureduring catapulting.... failureduring takeoff... fire......... fuelcontrol.... fuelflowmeter. fuelpump..... fuelsystem.... ground operation.. groundstarting preliminary preparations idlecheck curve .. ignition.... instruments ..... limitations..... low-altitudeair start.... malfunctions........... oilsystempressure filling. engineoilsystem - pressure filling........... oilsystemquantitycheck... oilsystcmservicing .. operating limits ......... . operation............. operation and aircraft Signals. pressureratio forcruise .. pressure ratioindicator.. starter......... . tachometer.... throttle .......... . EngineMalfunctions... . abnormal oilpressure. chugsandstalls ..... . overtemping....... . fuel-boostpumpfailure. fuelcontrolmalfunctions .. fuelpump.......... . lossof thrust........ . low-altitudeloss of thrust/ flameout......... low oilquantity....... . RPM/EGTmalfunctions. throttlelinkagefailure..... . Entrance,Emergency.......... ESCAPAC1EjectionScat S.\'stem preflight ................... . Index6 NAVAffi01-40AVC-1 Page No. TextIllus 11-61, 11-61, 11-128 11-128 1-13, 1-89 7-14 5-9 1-14A 1-14A 1-14A 1-HA 1-14A 1-13 1-14 1-129 1-14B 1-15 1-107 1-107 1-106 5-8 5-5 5-5 5-5 5-9 1-14 1-14B 1-14 1-13 3-10 1-120 3-9 1-13 1-14B1-133 1-129 5-8 5-6 1-107 1-108 1-106 1-106 1-129 1-14B 7-14 11-56, 11-123 1-14B 1-13 1-14B 1-14 5-6 5-8 5-6 5-7 5-7 5-7 5-8 5-7 5-7 5-8 5-6 5-7 5-585-59 1-:)4 :1-6 ESCAPAClA-lEjection Seat with Dart SystemPreflight ESCAPAClC-3Ejection Seat,A-4F ESCAPAClC-3Ejection Seat System. A-4Erocket ejectionseat....... ejection sequence ........... functioncomponents........ . preflight ................ . Exhaust GasTemperatureandEngine Speed.................... . Exit,Emergency ............... ExteriorInspection............. ExteriorLights......... . ExternalPowerApplication. ExternalPower Switch..... F Fahrenheit/CentigradeConversion FieldArrestment Data........... FieldCarrierLandingPractice(FCLP). Figure-8 Pattern .... . Fire.................. . detectionsystem....... . electrical........... eliminationofsmokeorfumes.. engine................... . smokeor fumes ............. . warning light - nootherindications or fire................. . warninglight - otherindications offire................. wing.................... . wing or accessorysection..... . FlameoutAction,Summaryof.. FlightCharacteristics ......... . onAFCS............... . angle-or-attackrelationship ... . divechart.... . flightcontrol s.............. . flight withcxternalstorcs. lcvel.................... . maneuveringflight..... . rollbackonrollattitudehold. spincharacteristics...... . stalls ................ . transonicmach......... . wing downphenomena onheading hold ......... . FlightControl......... . ailerons...... . aileroncontrol.. . aileron trimsystem automatic(AFCS) elevator control elevators..... . failure................ . horizontalstabilizer trimsystem hydrauli cmanualbleedval ve hydraulicpowerdisconnect hydraulicquick-disconnent panel.. . hydraulic reservoirsig