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CONTINUED

NAVAIR 01-F14AAP-1B

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47

d. ALQ-167 can radiate (TARPS).

e. BOL chaff can dispense.

IN FLIGHT

For most systems, failure of both the left and right
weight-on-wheels switches is required to cause the
systems to revert to the on-deck mode. Should such
failures occur, the following anomalies can result:

INDICATIONS:

1

a. Approach indexers are inoperative.

b. APC will not engage.

c. Outboard spoiler module inoperative (flaps

up).

d. Nozzles full open (gear down, throttles IDLE).

e. Ground-roll spoiler braking (throttles IDLE).

f. Radar will not scan.

g. Autopilot cannot be engaged.

h. BOL chaff will not dispense.

i. At high altitude, ground cooling fans may

overspeed and shut down, causing smoke in
cockpit.

j. RATS will be enabled airborne with the hook

handle down or the hook out of the stowed
position.

With RATS enabled airborne, military
power provides 20 to 25 percent less
thrust than normal, resulting in less
than optimum waveoff and bolter
performance.

Change 1

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Содержание F-14B

Страница 1: ...AND THEIR CONTRACTORS 1 JUNE 1992 DESTRUCTION NOTICE FOR UNCLASSIFIED LIMITED DOCUMENTS DESTROY BY ANY METHOD THAT WILL PREVENT DISCLOSURE OF CONTENTS OR RECONSTRUCTION OF THE DOCUMENT EJECT GROUND E...

Страница 2: ...RDS 311 EMERGENCY FIELD ARRESTMENT GUIDE 168 169 LANDING APPROACH AIRSPEED 14 UNITS SINGLE ENGINE 183 LANDING APPROACH AIRSPEED 15 UNITS 255 LANDING DISTANCE GROUND ROLL FLAPS DOWN 257 258 FLAPS UP 25...

Страница 3: ...erred to Commanding Officer Naval Air Technical Data and Engineering Command Naval Air Station North Island Bldg 90 Distribution P O Box 357031 San Diego CA 92135 7031 DESTRUCTION NOTICE For unclassif...

Страница 4: ...January 2004 TOTAL NUMBER OF PAGES IN THIS PUBLICATION IS 339 CONSISTING OF THE FOLLOWING Page No Issue Front Cover 0 Inside Front Cover 3 Title 3 A B C 3 1 2 3 3 thru 7 0 8 3 9 10 blank 0 11 1 12 th...

Страница 5: ...3 205 206 blank 3 207 208 blank 0 Page No Issue 209 thru 213 0 214 2 215 216 0 217 2 218 thru 221 0 222 thru 224 1 224a 224b 1 225 1 226 0 227 3 228 thru 235 0 236 2 237 238 0 239 2 240 3 241 0 242 2...

Страница 6: ...Changes have been incorporated into this Change Revision INTERIM CHANGE NUMBER S REMARKS PURPOSE 31 Modifies the L and or R Fuel Press Light s and Warning Tone Emergency Procedure and Adds Fuel Imbal...

Страница 7: ...AN 04 REF D IS F 14D FLIGHT MANUAL NFM 01 F14AAD 1 DTD 15 APR 02 WITH CHANGE 2 DTD 15 JAN 04 REF E IS F 14B POCKET CHECKLIST PCL 01 F14AAP 1B DTD 01 AUG 01 WITH CHANGE 3 DTD 15 JAN 04 REF F IS F 14B F...

Страница 8: ...OLLOWS A PAGE 123 TITLE 1 DELETE WARNING TONE 2 ADD 10 SEC WARNING TONE B PAGE 123 LINE 3 AFTER STEP 2 1 DELETE AND WARNING TONE 2 ADD NA C PAGE 124 LINE 1 1 DELETE AND THE WARNING TONE 2 ADD NA D PAG...

Страница 9: ...M 757 433 5147 EMAIL MILLERKA AT VF101 NAVY MIL B NAVAIR POCS 1 LT MIKE DOXEY F 14ABD CLASS DESK TEL DSN 757 7021 OR COMM 301 757 7021 EMAIL MICHAEL DOXEY AT NAVY MIL 2 LCDR JR NASH 4 0P NATOPS OFFICE...

Страница 10: ......

Страница 11: ...UAL NFM 01 F14AAD 1 DTD 15 APR 02 WITH CHANGE 2 DTD 15 JAN 04 REF E IS F 14B POCKET CHECKLIST PCL 01 F14AAP 1B DTD 01 AUG 01 WITH CHANGE 3 DTD 15 JAN 04 REF F IS F 14B FLIGHT MANUAL NFM 01 F14AAP 1 DT...

Страница 12: ...ISTING WARNING PARAGRAPH TO READ INDICATION OF FUEL BALANCING SHOULD APPEAR WITHIN 3 MINUTES OF SELECTING THE HIGH FUSELAGE TAPE SIDE F 1 DELETE ENTIRE WARNING THAT BEGINS WITH AIRCRAFT ATTITUDE WILL...

Страница 13: ...AB OPERATION IS NOT RECOMMENDED WITH A FUEL IMBALANCE OR WITH INDICATIONS OF VENTING FUEL B 1 DELETE NA 2 ADD INSERT NOTE PARAGRAPH BEFORE THE EXISTING NOTE PARAGRAPH AT THE BEGINNING OF THE PROCEDURE...

Страница 14: ...L 1 DELETE NA 2 ADD INSERT WARNING PARAGRAPH IMMEDIATELY FOLLOWING NEW STEP 4 TO READ VENTING FUEL IN CONJUNCTION WITH AN UNCONTROLLABLE FUEL SPLIT IS INDICATIVE OF A MOTIVE FLOW FAILURE AND CAN RESUL...

Страница 15: ...NG OF THE AFT LT FUEL SYSTEM AND SUBSEQUENT FUEL VENTING TO PREVENT THIS THE FEED SWITCH SHOULD BE RETURNED TO NORM BEFORE THE AFT LT TAPE REACHES 6 200 POUNDS OVERFILLING IS INDICATED BY A QUANTITY O...

Страница 16: ...F PRACTICAL OBTAIN A VISUAL INSPECTION FOR VENTING FUEL DO NOT DELAY EXECUTION OF EMERGENCY PROCEDURES FOR VISUAL INSPECTION E 1 DELETE NA 2 ADD INSERT NOTE PARAGRAPH AFTER PRECEEDING INSERTED NOTE PA...

Страница 17: ...DURE PAGE 14 20 7 CHANGE REF G F 14A PCL FUEL CHAPTER PAGE 98 AS FOLLOWS A 1 DELETE STATEMENTS UNDER FIRST WARNING DURING AB OPERATIONS NORM SHALL BE SELECTED FWD OR AFT COULD DEPLETE THE SUMP TANKS 2...

Страница 18: ...REPLACE WITH 3 FUEL FEED SWITCH AS REQUIRED AND LAND AS SOON AS PRACTICABLE J 1 DELETE NA 2 ADD INSERT STATEMENT IMMEDIATELY PRIOR TO STEP 4 TO READ IF FUEL VENTING EXISTS AND OR FUEL IMBALANCE EXCEE...

Страница 19: ...2 ADD NA G 1 DELETE NA 2 ADD MOVE FIRST NOTE PARAGRAPH OF EXISTING PROCEDURE THAT BEGINS WITH A HIGH QUANTITY TO A POSITION IMMEDIATELY FOLLOWING THE SECOND ADDED NOTE PARAGRAPH BETWEEN STEPS 2 AND 3...

Страница 20: ...CDR JR NASH 4 0P NATOPS OFFICER TEL DSN 995 2052 OR COMM 301 995 2052 EMAIL JAMES NASH AT NAVY MIL 3 KRISTIN SWIFT 4 0P NATOPS CHIEF ENGINEER TEL DSN 995 4193 OR COMM 301 995 4193 EMAIL KRISTIN SWIFT...

Страница 21: ...AP 1B F 14B AIRCRAFT PILOT S POCKET CHECKLIST INTERIM CHANGE 32 33 REPLACEMENT PAGES 1 Replacement pages for Interim Change Numbers 32 33 to the F 14B PCL NAVAIR 01 F14AAP 1B dated 15 Jan 2004 are att...

Страница 22: ......

Страница 23: ...HECK 77 COOLING AIR LIGHT 14 CROSSBLEED AIRSTART 53 D DFCS POWER ON RESET POR 80 DOUBLE GENERATOR FAILURE 31 E ECS MALFUNCTIONS 9 ECS LEAK ELIMINATION OF SMOKE AND FUMES 11 EJECT EGRESS 25 EJECTION 25...

Страница 24: ...HT 96 RUDDER AUTH LIGHT 100 RUDDER HARDOVER 100 RUNAWAY STABILIZER TRIM 98 S SINGLE ENGINE OPERATIONS 171 SINGLE ENGINE TAKEOFF 173 SINGLE ENGINE LDG PRI MODE 173 SINGLE ENGINE LDG SEC MODE 176 SMOKE...

Страница 25: ...Yaw SAS and all ARI functions 1 Ensure ROLL and YAW STAB AUG switches ON 2 MASTER RESET 3 See page 96 Autopilot or reference failure 1 MASTER RESET AUX FIRE EXT Low extinguisher agent pressure Report...

Страница 26: ...tch OFF COOLING AIR IN FLIGHT Indication of possible bleed duct failure for ward of the pressure pri mary heat exchanger and 400 F modulating valve 1 AIR SOURCE OFF 2 Assume ECS malfunc tion See page...

Страница 27: ...overheat condition in engine nacelle 1 Throttle IDLE 2 AIR SOURCE OFF 3 See page 71 Flap position disparity with commanded position or asymmetric procedures 1 Airspeed below 225 KIAS 2 See page 92 Usa...

Страница 28: ...2 3 Pull cb s and leave out if light remains on Computer malfunction or ramp mispositioning 1 Avoid abrupt throttle movements 2 Decelerate below 1 2 IMN 3 See page 62 Icing condition exists inlet or e...

Страница 29: ...enge oil temp 1 On deck increase fuel flow 2 Airborne see page 66 L or R oil press 11 psi 1 Throttle IDLE 2 See page 67 Qty 2 liters 1 Inform pilot 2 See page 20 Indicates inoperative pitch channel or...

Страница 30: ...E FLAME OUT procedures page 48 TARPS ECS Overtemp in TARPS pod 1 TARP sensors OFF 2 SYSTEM switch OFF 3 See page 18 TRANS RECT Lack of dc output from either or both T R Check bus tie Left T R Master T...

Страница 31: ...PERATURE CONTROL MALFUNCTION 16 COOLING AIR LIGHT 14 IN FLIGHT 15 ON DECK 14 COCKPIT OVER PRESSURIZATION ON DECK 16 ECS LEAK ELIMINATION OF SMOKE AND FUMES 11 DIRECT INDICATIONS OF ECS MALFUNCTION 11...

Страница 32: ...NAVAIR 01 F14AAP 1B 10 16...

Страница 33: ...out the 400 F manifold system DIRECT INDICATIONS OF ECS MALFUNCTION a BLEED DUCT caution light or FIRE warning light b Smoke or fumes in cockpit c Heat emanating from behind aft right comer of RIO co...

Страница 34: ...00 Feet b Cabin PRESS switch DUMP 3 RAM AIR INCR Note RAM air door may take up to 50 sec onds to fully open 4 Airspeed Below 300 KIAS 0 8 IMN 5 Nonessential electrical equipment Secure 6 CANOPY DEFOG...

Страница 35: ...ontrolled bleed air to circulate and the loss of normal cabin dump capability Mini mize low speed less than 0 25 IMN and ground operations as the heat exchanger cooling fan will be inop erative and EC...

Страница 36: ...open the cabin regulator valve for maximum ECS air flow If smoke or fumes are not elimi nated it is most probable that smoke fumes are being regenerated by an ECS air leak As a last resort jettison th...

Страница 37: ...ols If associated with any other direct or indirect indication of ECS malfunction 2 Perform ECS Leak Elimination of Smoke and Fumes procedure If not associated with any other direct or indirect indica...

Страница 38: ...e above 110 F from entering air craft After ram air flow is stabilized air speed may be increased as required for flightcrew comfort or to increase flow to electronic equipment 3 VENT AIRFLOW OFF 4 AI...

Страница 39: ...IN PRESS switch Cycle AWG 9 COND LIGHT ILLUMINATED AND OR PUMP PHASE CIRCUIT BREAKERS POPPED OR AWG 9 PM ACRONYM 1 LIQ COOLING switch OFF 2 WCS switch OFF 3 ANT SVO HYD PH A B C IF2 IF4 IF6 cb s Pull...

Страница 40: ...2D1 e RECON HTR PWR PH C 2F1 f RECON POD 1F4 g RECON POD CONTR 8F7 h RECON POD DC PWR NO 2 8F1 i RECON POD DC PWR NO 1 8F2 4 Ask for visual check of pod by wingman 5 Land as soon as practicable MSL C...

Страница 41: ...Check 2 If possible descend cabin altitude to less than 10 000 feet With mask removed loss of cabin pres sure above 10 000 feet MSL can rapidly cause hypoxia 3 If not possible to descend actuate emerg...

Страница 42: ...of cabin pres sure above 10 000 feet MSL can rapidly cause hypoxia 5 OXYGEN switch OFF Before landing 6 OXYGEN switch and masks ON CANOPY LIGHT OR CANOPY LOSS 1 Canopy handle BOOST CLOSE canopy remai...

Страница 43: ...ticable WSHLD HOT LIGHT 1 WSHLD AIR OFF If light remains illuminated 2 Reduce airspeed to less than 300 KIAS or 0 8 IMN 3 AIR SOURCE OFF below 35 000 feet Note If light remains illuminated after air s...

Страница 44: ...NAVAIR 01 F14AAP 1B 22 28 EJECT EGRESS...

Страница 45: ...NAVAIR 01 F14AAP 1B 23 29 EJECT EGRESS Index CONTROLLED EJECTION 25 GROUND EGRESS WITHOUT PARACHUTE AND SURVIVAL KIT 27 MANUAL BAILOUT 26 23 24 blank...

Страница 46: ...NAVAIR 01 F14AAP 1B 24 30...

Страница 47: ...2 Warn other crewmember 3 EJECT CMD lever Select RIO 4 IFF SIF EMERG 7700 RIO 5 Position report Transmit 6 Check altimeter 7 Assume proper eject position a Head pressed back against headrest b Chin sl...

Страница 48: ...endant leg injury Proper body position is a critical factor in preventing ejection injuries Minimum ejection altitudes are de pendent upon dive angle airspeed and angle of bank MANUAL BAILOUT Manual b...

Страница 49: ...e discon nected from ejection seat 7 Release stick 8 Roll forward and push free of aircraft GROUND EGRESS WITHOUT PARACHUTE AND SURVIVAL KIT 1 Kneel aircraft if possible 2 Canopy Open or Jettison 3 Pa...

Страница 50: ...NAVAIR 01 F14AAP 1B 28 34 ELECT...

Страница 51: ...BUSES NO 2 34 FAILURE OF BOTH TRANSFORMER RECTIFIERS EQUIPMENT INOPERATIVE LIST 36 L OR R GEN LIGHT 31 L OR R GEN AND TRANS RECT LIGHTS 31 TOTAL ELECTRICAL FAILURE 37 WEIGHT ON OFF WHEELS SWITCH MALF...

Страница 52: ...NAVAIR 01 F14AAP 1B 30 36...

Страница 53: ...IDG or GCU L OR R GEN AND TRANS RECT LIGHTS 1 Generator affected generator switch OFF RESET Then NORM 2 If L GEN and TRANS RECT light remains illuminated select EMERG GEN on MASTER TEST panel 3 Land...

Страница 54: ...t illumination of caution lights If the 5 kVA mode is regained a MASTER RE SET will be required to regain SAS spoiler authority stop and ARI functions Note DFCS synchronization can take up to 2 second...

Страница 55: ...Group Engine Stall Tone Engine Stall Overtemp Warning Fire Detection Fire Extinguishing Flap Slat Position Ind Floodlights Fuel Quantity Indicator Hydraulic Pressure Indication Flight and Combined ICS...

Страница 56: ...ghts Cockpit Temperature Control Control Surface Position Indicator Tail Rudder and Spoilers CSDC ECM Navigational Aids IFF Interrogator and Transmitter Eject Command Indicator Electronic Cooling Emer...

Страница 57: ...MDIG Display Panel Nose Landing Gear Kneeling Nosewheel Steering Oxygen Quantity Indicators Probe Anti Ice AOA Total Temperature Pilot Radar Beacon Servo pneumatic Altimeter Speedbrakes Spoiler Contro...

Страница 58: ...OR EGI ELECTRONIC COOLING EMERG GENERATOR CONTROL FEMS FUZE FUNCTION CONTROL GROUND POWER GROUND TEST GUN ARMED POWER GUN CLEAR POWER GUN CONTROL POWER GYRO POWER IFF AIR TO AIR INTEGRATED TRIM INTERR...

Страница 59: ...in pitch and yaw and severely degraded roll control with flaps extended Perform controllability check Note The standby attitude gyro is capable of providing reliable attitude infor mation within 6 for...

Страница 60: ...engine operation without elec trical power supplied by either the gen erators or external power may cause 20 mm ammunition detonation be cause of excessive heat in the gun ammunition drum CAUTION Do...

Страница 61: ...uld be conducted to VFR condi tions for landing WEIGHT ON OFF WHEELS SWITCH MALFUNCTION ON DECK INDICATIONS 1 WOW acronym is displayed 2 Approach indexer is illuminated 3 Nozzles may be partially clos...

Страница 62: ...r right weight on off wheels switches to the in flight mode can cause loss of engine ejector air to the engine oil IDGs and hydraulic heat exchangers causing thermal discon nect and or heat damage to...

Страница 63: ...e c Outboard spoiler module inoperative flaps up d Nozzles full open gear down throttles IDLE e Ground roll spoiler braking throttles IDLE f Radar will not scan g Autopilot cannot be engaged h BOL cha...

Страница 64: ...ight on off wheels switch is suspected because of loss of thrust and lift caused by nozzles open ing and spoilers deploying 1 Throttles Any position except IDLE 2 ANTI SKID SPOILER BK switch OFF 3 Lan...

Страница 65: ...et after touchdown to enable ground roll braking antiskid nozzles open at idle and nosewheel steering D Circuit breakers must be reset simultaneously within 0 1 sec once on deck or a secondary fault m...

Страница 66: ...NAVAIR 01 F14AAP 1B 44 50 ENG...

Страница 67: ...O SECONDARY MODE RESULTS 56 EXHAUST NOZZLE FAILED 59 NO NOZZLE RESPONSE TO THROTTLE MOVEMENT 59 INLET ICE LIGHT 65 L OR R OIL HOT LIGHT 66 OIL PRESS LIGHT AND OR ABNORMAL OIL PRESSURE 67 RATS OPERATIO...

Страница 68: ...NAVAIR 01 F14AAP 1B 46 52...

Страница 69: ...rical power during an engine start with the RPM below forty percent Air flow will be cut off and fuel will continue to be scheduled to the engine with the igni tors firing causing a rapid and severe r...

Страница 70: ...ALVE light remains out Crossbleed airstarts may not be available to the affected engine after a START VALVE light illuminates because of possible overspeed damage If airborne 3 ENG START RE1 cb Pull I...

Страница 71: ...Engines should be exercised at 10 000 feet in cruise and then at approach speeds one at a time to ensure stall free performance is avail able for landing If engine performance is abnormal set power a...

Страница 72: ...cycle the emergency gen erator switch through OFF RESET to NORM to regain lost engine instruments D With existing ejection seat design limitations the decision to exceed 350 KIAS rests with the aircr...

Страница 73: ...E SELECT switch PRI When PRI mode is restored 8 Maintain constant subsonic airspeed in level flight 9 Affected L or R AICS LF2 left LG2 right cb Cycle If WING SWEEP advisory light is illumi nated cycl...

Страница 74: ...AND FASTER ENGINE ACCELERATION THE OPTIMUM RESTART RPM IS 15 OR GREATER RESTARTS FROM 10 RPM ARE SUCCESSFUL BUT AC CELERATE VERY SLOWLY AND ENGINE LIGHT OFF IS HARDER TO DETECT IF THE WINDMILL RESTAR...

Страница 75: ...e ON 7 Throttle bad engine IDLE Immediately Note The quickest light offs are achieved with throttle to IDLE at less than 10 per cent Light offs can take as long as 45 seconds If hung start 8 Throttle...

Страница 76: ...1 LE1 and WG SWP DR NO 2 MANUV FLAP LE2 cb s are pulled ENGINE OVERSPEED N2 107 7 PERCENT RPM 1 Throttle affected engine IDLE If overspeed continues 2 ENG MODE SELECT switch SEC Verify ENG SEC light...

Страница 77: ...e Engine Cruise Operations page 181 5 Land as soon as practicable ENGINE TRANSFER TO SEC MODE CAUTION In SEC mode idle lockup protection is lost Decelerate below 1 1 IMN before retarding throttle to i...

Страница 78: ...ICS LF2 left LG2 right cb Cycle If engine remains in SEC 12 3 ENG MODE SELECT switch SEC 4 Avoid abrupt throttle movements 5 Land as soon as practicable CAUTION Landing in SEC mode may increase landin...

Страница 79: ...7 65 to 116 percent basic engine thrust available 8 Main engine ignition continuously energized 9 No Idle lockup protection 10 IGV fixed full open higher windmill airspeed 11 RATS inoperative UNCOMMAN...

Страница 80: ...LE1 and WG SWP DR NO 2 MANUV FLAP LE2 cb s are pulled 3 Affected L or R AICS LF2 left LG2 right cb Cycle UNCOMMANDED ENGINE ACCELERATION ON DECK 1 Paddle switch Depress Hold 2 Throttle s As Desired 3...

Страница 81: ...ective 1 ENG MODE SELECT switches SEC If dual engine uncommanded acceleration associated with CADC failure normal primary mode may be re gained by selecting PRI mode with gear handle down If engine st...

Страница 82: ...selection of SEC mode In event of engine rollback PRI mode must be reselected above 59 per cent rpm or flameout will occur and an airstart will not be possible 3 ENG MODE SELECT SEC 4 Obtain visual i...

Страница 83: ...lax aft pressure on throttles 5 While forcing throttles apart laterally a Pull throttles straight aft to MIL detent b Move inboard and aft 6 Do not reselect afterburner If right throttle will not reta...

Страница 84: ...light when the LDG GEAR handle is UP If RAMPS light remains illuminated 4 Throttle bad engine 80 percent or less 5 If WING SWEEP advisory light is illuminated Wing sweep drive cb s Pull LE1 and LE2 If...

Страница 85: ...fected INLET RAMPS switch AUTO 8 Land as soon as practicable If INLET light only illuminated attempt AICS programmer reset 123 4 Decelerate below 0 5 IMN 5 If WING SWEEP advisory light is illuminated...

Страница 86: ...T RAMPS switch AUTO If INLET light remains illuminated 123456 7 Affected L or R AICS cb Pull LF2 left or LG2 right Note Pulling the AICS cb while airborne may illuminate the FCS CAUTION and ARI DGR li...

Страница 87: ...conditions 2 ENG PROBE ANTI ICE switch AUTO OFF Ice may form on inlet and ramp sur faces without any other visual indica tions which may cause compressor stalls and or FOD CAUTION The formation of ic...

Страница 88: ...radation Note On deck light may be caused by under servicing or by excessive temperature on deck Normally advancing throttles out of IDLE will extinguish light 1 Oil pressure Check 2 Throttle affected...

Страница 89: ...Refer to Single Engine Cruise Operations If shutdown is not feasible 1 2 Rpm Set minimum Rpm 3 Avoid high g or large throttle movements 4 Land as soon as possible RATS OPERATION IN FLIGHT 1 Tailhook...

Страница 90: ...sink rate CAUTION Circuit breaker 7C2 must be in prior to hook transition Avoid icing conditions and rain with 7C2 pulled Note D If RATS secures when the hook is raised with no other weight on wheels...

Страница 91: ...NAVAIR 01 F14AAP 1B 69 75 FIRE Index ELECTRICAL FIRE 73 ENGINE FIRE ON THE GROUND 72 L OR R FIRE LIGHT AND OR FIRE IN FLIGHT 71 69 70 blank...

Страница 92: ...NAVAIR 01 F14AAP 1B 70 76...

Страница 93: ...ilable on the emergency generator 3 MASTER TEST FIRE DET TEST If light remains on FIRE DET TEST fails or there are sec ondary indications 4 FUEL SHUT OFF handle affected engine Pull 5 Throttle affecte...

Страница 94: ...TION switch Check OFF CAUTION Excessive windmilling of engine with oil system failure may increase com bustion smoking blue white and re sult in greater difficulty extinguishing causing further damage...

Страница 95: ...eak Elimination of Smoke and Fumes procedure CAUTION An electrical fire may affect the CADC and AICS system causing random movements of the wings and ramps If conditions permit 3 EMERG generator switc...

Страница 96: ...sible CAUTION Do not operate engines on the ground without electrical power Ground cooling fans are shut off causing hot bleed air to cook off oil and hydro carbons in the ECS ducting resulting in smo...

Страница 97: ...80 FLAP AND SLAT ASYMMETRY 90 FLAP LIGHT 92 AFTER LANDING TAKEOFF FLAP TRANSITION OR REILLUMINATION AFTER ABOVE PROCEDURES 93 FLAP HANDLE DOWN AND FLAPS DOWN 93 FLAP HANDLE DOWN AND FLAPS NOT FULLY EX...

Страница 98: ...TRIM 98 SPOILERS CAUTION LIGHT SPOILER MALFUNCTION SPOILER STUCK UP 85 STAB AUG TRANSIENTS 98 UNCOMMANDED ROLL AND OR YAW 83 UNSCHEDULED WING SWEEP 107 UPRIGHT DEPARTURE FLAT SPIN 104 WINGS SWEEP LIGH...

Страница 99: ...not raise flaps until recovered If during flap slat transition follow uncom manded roll yaw procedures A controllability check requires the total attention and awareness of the aircrew The aircrew mus...

Страница 100: ...flaps are lowered do so incrementally and be alert for flap slat asymmetry 6 If maneuver flaps are used for landing approach WG SWP DR NO 1 and PULL WG SWP DR NO 2 LE1 and LE2 MANUV FLAP cb s Note Fai...

Страница 101: ...le full ground roll braking authority 13 If directional control is in question a A shorebased arrested landing should be flown to touchdown at or just prior to the ar resting gear b Use LSO if possibl...

Страница 102: ...S and or spoiler control inputs following an air borne POR If a dual failure has been declared that will not clear with a MASTER RESET performing a power on reset POR to clear the failure can result i...

Страница 103: ...RI SAS OUT light due to ROLL and YAW STAB switches OFF If the system continues to display any DFCS related caution lights following MASTER RESET this could be indicative of a recurring flight control...

Страница 104: ...STAB AUG switches ON If any uncommanded SAS control inputs 6 Affected STAB AUG switch OFF If uncommanded roll SAS inputs are observed following a POR reselection of the SPOILER CONTR cb s can result...

Страница 105: ...ownwing engine MAX THRUST if required 5 Master Reset Button Depress Note DFCS synchronization can take up to 2 seconds following a power interrupt If the Master Reset button is depressed during the sy...

Страница 106: ...er e Structural damage 10 Slow fly aircraft to determine controllability at 10 000 feet AGL minimum BINDING JAMMED FLIGHT CONTROLS ON THE GROUND 1 Hold light pressure against binding restriction to fa...

Страница 107: ...line is not considered a mechanical failure Note Use lateral stick as primary control and rudder only as needed to main tain balanced flight Subsequent depression of the MAS TER RESET pushbutton will...

Страница 108: ...fac tory with flaps down Note Any single fully deflected failed up spoiler is controllable even with flaps down and ROLL SAS off if the remain ing spoilers are operating With multi ple failures aircra...

Страница 109: ...power on reset in an at tempt to regain at least one spoiler set See DFCS POR procedures page 80 If controllability satisfactory 5 Perform maneuver flap slat or no flap straight in approach at or abo...

Страница 110: ...n removed Therefore it should be considered only as a last resort 1234 5 SPOILER CONTR cb for affected pair Pull 7G9 for INBD 8C5 for OUTBD If uncontrollable roll or no improvement in controllability...

Страница 111: ...ydraulic failure rendering the inboard spoilers inop erative can result in asymmetric spoil er float such that the aircraft may not be flyable at normal approach airspeeds CAUTION If outboard spoilers...

Страница 112: ...procedures take precedence if appropriate Other wise perform the procedures below 1 FLAP SLAT CONTR SHUTOFF cb Check in RE2 Lack of asymmetry protection RE2 cb out may cause uncommanded roll and or ya...

Страница 113: ...cb Pull Failure to complete step 7 before the subsequent steps can result in large uncommanded pitch trim changes because of auxiliary flap movement Pulling circuit breaker RE2 removes flap slat asym...

Страница 114: ...been corrected flaps and slatsdid not respond to above procedure or lat eral control problems exist land using minimum safe speed AOA if landing is elected FLAP LIGHT NOT AFTER LANDING TAKEOFF FLAP TR...

Страница 115: ...FLAP light remains illuminated refer to Flap and Slat Asymmetry procedures FLAP HANDLE UP AND FLAPS INDICATING FULL UP 1 Flaps Cycle If FLAP handle or flaps will not respond or FLAP light remains illu...

Страница 116: ...If light remains illuminated The DFCS has lost redundancy but has not lost any authority The DFCS is potentially one failure away from losing authority and may degrade to ROLL SAS OFF or YAW SAS OFF c...

Страница 117: ...operative the degra dation in the roll axis may be severe and a careful slow flight should be conducted to determine whether a CV approach should be attempted Refer to spoiler failure procedure Note T...

Страница 118: ...l ARI SAS OUT LIGHT WITH ROLL DGR YAW DGR OR ARI DGR LIGHT 1 Ensure ROLL and YAW STAB AUG switches ON 2 MASTER RESET pushbutton Depress If lights remain illuminated 3 Leave STAB AUG switches ON to tak...

Страница 119: ...landings with total yaw SAS failure require increased attention to control of directional oscillations especially in turbulence and or dur ing lineup corrections Rudder pedal shakers inop if YAW B fai...

Страница 120: ...ed under fol lowing conditions a Runaway nose down FLAPS UP b Runaway nose up FLAPS DOWN 5 Straight in approach STAB AUG TRANSIENTS 1 MASTER RESET pushbutton Depress 2 Airspeed Decelerate below 400 KI...

Страница 121: ...ht will illuminate 3 Restrict lateral control inputs above 400 KIAS 0 9 IMN to one quarter throw CAUTION Above 400 KIAS 0 9 IMN there is a danger of torsional overstress to the fuselage with large lat...

Страница 122: ...nd differential braking is required com ing out of the arresting gear RUDDER HARDOVER A rudder hardover will result in a single fully de flected over 30 degrees pegged on cockpit indica tor inboard or...

Страница 123: ...tions during throttle and control move ments Undesirable airspeed in crease may occur due to differential thrust Airspeed control may also be influenced by flap position and pilot workload Specificall...

Страница 124: ...ly mo nitored Recommend using gear up flaps down single engine BINGO char ts Fuel imbalance may occur during prolonged flight with higher demands on one engine Use feed switch to mini mize fuel split...

Страница 125: ...departing the landing area runway Note Ensure familiarity with landing con siderations of controllability check procedures Simulation indicated that bank angle control was enhanced by leading lateral...

Страница 126: ...nly opposing throttle for waveoff bolter CAUTION If rudder pedal authority is restricted nosewheel steering should not be en gaged upon landing rollout UPRIGHT DEPARTURE FLAT SPIN 1 Stick Forward Neut...

Страница 127: ...command eject Ejection guidelines are not meant to prohibit earlier canopy jettison and or ejection If insufficient altitude exists to recover from departed flight the flightcrew should not hesitate t...

Страница 128: ...ing below 10 000 feet AGL 6 Eject RIO command eject CAUTION Dual compressor stalls overtempera tures should be expected in an in verted spin Note If pedal adjustment and or pilot posi tioning because...

Страница 129: ...ss 2 Check spider detent engaged 3 MASTER RESET Depress wait 15 seconds to determine system status If advisory and warning lights illuminate again 4 WING SWEEP DRIVE NO 1 and WG SWP DR NO 2 MANUV FLAP...

Страница 130: ...NAVAIR 01 F14AAP 1B 106b 114...

Страница 131: ...al damage 2 Airspeed Decelerate to 0 6 IMN or Less in 1g Nonmaneuvering Flight 3 Emergency WING SWEEP handle FULL FWD If wings do not move full forward 4 Emergency WING SWEEP handle Match With Actual...

Страница 132: ...wing sweep commands prior to performing steps 1 through 8 Limit maneuvering envelope to 350 KIAS and 1 5g s 1 Leave wings and flaps as set 2 Altitude Climb Remain Above 10 000 feet AGL 3 Airspeed 250...

Страница 133: ...for Landing procedure 8 Perform preliminary controllability check as fol lows a Trim away from forward wing opposite stick force to ensure that maximum spoiler deflection is available b Assess spoiler...

Страница 134: ...for Landing procedure If aircraft controllability is safe for landing perform Asymmetric Wing Sweep Acceptable for Landing procedure ASYMMETRIC WING SWEEP ACCEPTABLE FOR LANDING Establish final landin...

Страница 135: ...ion during flap exten sion An uncommanded but control lable roll transient because of the spoiler gearing change will also occur Upon observing either event retract the flaps to just less than 25_ the...

Страница 136: ...c cur Precise AOA control and smooth lateral control inputs are required Note Indicated AOA is subject to a 1 to 2 unit sideslip induced error Verify proper AOA at zero sideslip 2 Emergency WING SWEEP...

Страница 137: ...rrested or normal landing CAUTION Avoid rapid lateral stick inputs since significant pitch roll coupling may re sult in roll ratcheting pitching motion and lateral PIO tendency an excessive descent ra...

Страница 138: ...rudder at the beginning of the approach and held to touch down Lateral stick force increases as sideslip is reduced Method of approach is pilot s option In the event of bolter or go around as airspeed...

Страница 139: ...UX FLAP FLAP CONTR 7G3 cb In Note At any point during the following procedures if wing sweep symme try is regained at aft wing sweep position and runway length approach speed permit aircrew may elect...

Страница 140: ...s forward of right wing a Airspeed 300 KIAS b Emergency WING SWEEP handle 68 c Emergency WING SWEEP handle 20 d AUX FLAP FLAP CONTR cb 7G3 Pull e Repeat preliminary landing controllability check step...

Страница 141: ...liminary landing controllability check step 9 on page 79 If left wing is jammed and spoilers are operational 1 a Emergency WING SWEEP handle 20o b AUX FLAP FLAP CONTR cb 7G3 Pull c Repeat preliminary...

Страница 142: ...LANDING APPROACH AIRSPEEDS 15 UNITS AOA MAIN FLAPS SLATS EXTENDED AUXILIARY FLAPS RETRACTED FLAPS UP APPROACH AIRSPEED 14 UNITS AOA FLAPS SLATS RETRACTED DATE AUGUST 1986 DATA BASIS FLIGHT TEST ASYMME...

Страница 143: ...safe Mach b Autopilot c Idle lockup function of AFTC d Wing sweep indicator e Cockpit cooling less than Mach 0 25 f HUD display takeoff and landing g Servo altimeter Note D Erroneous Mach inputs to AF...

Страница 144: ...NAVAIR 01 F14AAP 1B 120 128 FUEL...

Страница 145: ...126a FUEL TRANSFER FAILURES 124b WINGS ACCEPT FUEL WITH SWITCH IN FUS EXTD POSITION 126 WINGS DO NOT ACCEPT FUEL WITH SWITCH IN ALL EXTD POSITION 126 L AND OR R FUEL PRESS LIGHT S ON 123 L OR R FUEL...

Страница 146: ...NAVAIR 01 F14AAP 1B 122 130...

Страница 147: ...ettings or less 6 Land as soon as possible D Illumination of both lights and the warning tone may be indicative of a total motive flow failure Zero or negative g flight should be avoided D Complete lo...

Страница 148: ...ncrease on the inoperative side or a 100 to 300 PPM decrease on the operative side above expected burn rate according to indicated fuel flow 6 FUEL PRESS ADVSY CB PULL 7F1 Note Pulling the FUEL PRESS...

Страница 149: ...ld result in fuel migration to the inoperative side If fuel migration occurs after selecting AFT or FWD on the FEED SWITCH as indicated by a 100 to 300 PPM increase on the inoperative side immediately...

Страница 150: ...ble transfer Note Fuel management panel will be inop erative if FUEL MGT PLN cb RC1 is out 1 Fuel Management Panel cb Check in RC1 If wing fuel does not transfer 2 WING EXT TRANS switch ORIDE If one w...

Страница 151: ...WING EXT TRANS ORIDE If fuel continues to transfer improperly or does not transfer 3 In flight refueling probe All Extend Then Retract 4 Apply cyclic positive or negative g s 5 AIR SOURCE pushbutton O...

Страница 152: ...of descent landings minimum sink rate are authorized Note CSDC flycatcher 71 00031 displays free airstream temperature if first digit is an even number the temperature is above freezing WINGS DO NOT A...

Страница 153: ...ntly be necessary useable fuel will be limited to only what is available on the operating side FUEL LEAK 1 Land as soon as possible CAUTION Use of afterburner with fuel leak should be limited to emerg...

Страница 154: ...e operation subsequently be necessary useable fuel will be limited to only what is available on the operating side Note Enough time should be allowed for quantity tapes feeds to develop split so that...

Страница 155: ...IGHT FEED GROUPS 1 Both throttles MIL power or less 2 FEED SWITCH select high fuselage tape side Note D If practical obtain a visual inspec tion for venting fuel Do not delay execution of emergency pr...

Страница 156: ...balance If this occurs as indicated by an imbalance increase of 100 to 300 PPM immediately return the FEED SWITCH to NORM If fuel venting exists and or fuel imbalance exceeds 2 000 pounds 4 FUEL FEED...

Страница 157: ...URE 144 BOTH COMBINED AND FLIGHT PRESSURE ZERO 139 COMBINED PRESSURE APPROXIMATELY 2 400 TO 2 600 PSI 131 COMBINED PRESSURE ZERO 133 FLIGHT PRESSURE APPROXIMATELY 2 400 TO 2 600 PSI 136a FLIGHT PRESSU...

Страница 158: ...NAVAIR 01 F14AAP 1B 130 140...

Страница 159: ...witch BIDI OFF 1 HYD ISOL switch FLT Note Monitor AUX BRAKE PRESSURE gauge Tap wheelbrakes to seat priority valve if pressure is decreasing 2 In flight REFUEL PROBE switch EXTD In carrier environment...

Страница 160: ...ay illuminate the FCS CAUTION and ARI DGR lights Above about 600 KIAS the PITCH SAS and ROLL DGR lights will also be illuminated These should clear with a MASTER RESET following a pro grammer reset 6...

Страница 161: ...ternal fuel will not transfer with refuel probe switch in ALL EXTD If probe extension required select FUS EXTD to enable transfer 4 Wing sweep Set at 20_ 5 EMERG FLT HYD LOW If the INLET RAMPS switch...

Страница 162: ...to AUTO LOW mode once module is selected on HIGH or LOW with operating flight hydraulic system When operated in conjunc tion with zero combined pressure some backup module fluid will be expelled by th...

Страница 163: ...will not illuminate if the remaining system fails Note Complete loss of combined hydraulic pressure will result in the following caution lights due to the loss of a single channel SAS actuator functio...

Страница 164: ...n return line m Auxiliary flaps n Nosewheel steering o Gun drive 6 LDG GEAR handle EMERG DN 7 HOOK EMERG DN 8 AUX FLAP FLAP CONTR cb Pull 7G3 9 Flaps no auxiliary flaps available DN 10 Brake accumulat...

Страница 165: ...LIGHT PRESSURE APPROXIMATELY 2 400 TO 2 600 PSI If hammering cavitation is experi enced in the hydraulic system compo nent rupture is imminent Turn the hydraulic transfer pump switch BIDI OFF 1 Wing s...

Страница 166: ...NAVAIR 01 F14AAP 1B 136b 148...

Страница 167: ...pro grammer reset 4 R INLET RAMP switch AUTO 5 EMERG FLT HYD switch HIGH on final committed to land CAUTION Monitor remaining hydraulic system pressure since the MASTER CAUTION and HYD PRESS lights wi...

Страница 168: ...af ter complete loss of pressure Trapped fluid may be the only thing holding the affected ramp in position CAUTION Monitor remaining hydraulic system pressure since the MASTER CAUTION and HYD PRESS li...

Страница 169: ...andle restowed 4 EMERG FLT HYD switch HIGH on final committed to land 5 Land as soon as possible Note Arrested landing will require emergency hook extension BOTH COMBINED AND FLIGHT PRESSURE ZERO 1 EM...

Страница 170: ...ected to float causing uncomfortable lateral stick requirements for level flight Do not trim out lateral forces 3 Reduce airspeed to below 250 KIAS if practicable Note Airspeeds less than 250 KIAS whi...

Страница 171: ...uver flaps Extend 6 EMERG FLT HYD switch HIGH prior to moving to pre contact 7 Avoid abrupt control inputs during contact Any abrupt control input to effect engagement can rate limit the stabil izers...

Страница 172: ...G DN 11 Maneuver flaps Extend with thumbwheel 12 Maneuver flap cb Pull LE2 13 HOOK handle EMERG DN 14 Brake accumulator Check Established on final committed to land 15 EMERG FLT HYD switch HIGH Aggres...

Страница 173: ...of the module The LOW mode should be selected as soon as practicable following a waveoff or bolter and the HIGH mode reselected on the subse quent approach 16 If wings are at 20_ Fly straight in appr...

Страница 174: ...module in the high mode may result in failure of the module 1 FLT HYD BACKUP PH A B C 2A1 2C1 2E1 cb s In 2 Land as soon as possible LOW BRAKE ACCUMULATOR PRESSURE IN FLIGHT 1 HYD ISOL T O LDG If pres...

Страница 175: ...NAVAIR 01 F14AAP 1B 145 157 If accumulator cannot be recharged 4 Make arrested landing as soon as practicable 5 Parking brake Pull to lock wheels 145 LAND LAND GEAR...

Страница 176: ...NAVAIR 01 F14AAP 1B 146 158 LAND LAND GEAR...

Страница 177: ...7 LANDING GEAR EMERGENCY LOWERING 155 LANDING GEAR INDICATES SAFE GEAR DOWN TRANSITION LIGHT ILLUMINATED 154 LANDING GEAR INDICATES UNSAFE GEAR DOWN TRANSITION LIGHT ILLUMINATED 151 LANDING GEAR INDIC...

Страница 178: ...NAVAIR 01 F14AAP 1B 148 160...

Страница 179: ...draulic pressure Check 3 If less than 3 000 psi refer to combined hydrau lic failure procedures LANDING GEAR INDICATES UNSAFE GEAR UP OR TRANSITION LIGHT ILLUMINATED 1 LDG GEAR handle DN If safe gear...

Страница 180: ...nes and to the tower or LSO by one main gear hanging no ticeably lower than the other When ei ther of these situations occurs landing procedures for a stub MLG mount must be followed 4 Land as soon as...

Страница 181: ...ual check 2 Landing gear Cycle If condition still exists 3 Obtain visual check if possible 4 Make normal landing LANDING GEAR INDICATES UNSAFE GEAR DOWN TRANSITION LIGHT ILLUMINATED 1 Obtain visual ch...

Страница 182: ...exists that the downlock actuator has failed and the gear may not be locked in the down position 2 LDG GEAR handle Cycle If still unsafe 3 Increase airspeed to 280 KIAS pull positive g s and yaw airc...

Страница 183: ...the doors attempt to close as indicated by an un safe main mount or visual inspection Note Use of the above procedure should be done at the intended point of landing or within range of an acceptable d...

Страница 184: ...aircraft has stopped Do not attempt to tow aircraft by the nosegear until the gear is secured in the down position Nose landing gear ground safety pin installation will not prevent nose gear collapse...

Страница 185: ...fer to Landing Gear Malfunction Guide If launch bar is down or visual inspection is not available 3 Remove arresting cables for field landing 4 Remove crossdeck pendant Nos 1 and 4 for CV landing LAND...

Страница 186: ...in flight check if possible 9 Refer to Landing Gear Malfunction Emergency Landing Guide on page 167 ARRESTING HOOK EMERGENCY DOWN 1 HOOK handle DN 2 HOOK handle Pull Then Rotate Note Pull handle aft a...

Страница 187: ...o extend spoilers on touchdown due to a momentary miscompare of the weight on wheels switches BARRICADE ARRESTMENT 1 External stores Jettison except AIM 7 and AIM 54 on fuselage stations if wing is at...

Страница 188: ...Barricade stanchions may obscure the meatball Upon engaging the barricade 6 Throttles OFF 7 Evacuate aircraft as soon as practicable Weight limits are Wings at 20_ 51 800 Lb max Wings 20_ 35_ 46 000 L...

Страница 189: ...e 4 HOOK DN CAUTION After lowering hook nosewheel steer ing will be automatically centered and will remain centered until nosewheel steering is cycled 5 External lights ON 6 Notify ground or tower 7 B...

Страница 190: ...flight visual check if possible 2 ANTI SKID SPOILER BK SPOILER BK OFF for CV 3 HOOK DN 4 Make carrier or short field fly in arrested land ing as soon as practicable 5 HYD ISOL switch T O LND on final...

Страница 191: ...controllable Note If outboard spoilers are needed for ground roll braking FLAP handle must be lowered at least 5 on landing rollout 3 Fly landing pattern slightly wider than normal or make straight in...

Страница 192: ...ches Wing drop and increased sink rate may occur at 16 5 to 17 5 units AOA Aircrew should expect hot brakes following high speed landings Ap plication of the parking brake could cause the brake assemb...

Страница 193: ...F14AAP 1B 162a 175 ALL DRAG INDEXES 0_ FLAP GEAR DOWN DATE 1 MAY 1980 FUEL GRAD JP 5 JP 8 JP 4 DATA BASIS FLIGHT FUEL DENSITY 6 8 TEST 6 7 6 5 lb gal LANDING APPROACH AIRSPEED 15 UNITS Change 2 162a 1...

Страница 194: ...NAVAIR 01 F14AAP 1B 162b 176...

Страница 195: ...l Wing Sweep Position Tape CAUTION Closely monitor wingsweep move ment when attempting to match handle with wingsweep position If abnormal movement is noticed immediately return handle to previous pos...

Страница 196: ...ings aft of 50 and to evaluate handling stall characteristics and waveoff performance Refer to emergency field arrestment guide for maximum engagement speed if field arrestment is desired Refer to lan...

Страница 197: ...f hung ordnance exceeds 1000 pounds 2 Wing sweep Set at 25_ if 2 000 Pounds Hung Aft Set at 30_ if 2 000 Pounds Hung Aft 3 Perform transition to gear down configuration in straight and level flight 4...

Страница 198: ...de for maximum engagement speed page 169 If arresting gear is not available 10 If field arrestment is not available spoiler brake BOTH Expect a significant nose pitchup dur ing landing rollout as spoi...

Страница 199: ...ND IF TANKS INSTALLE D 1 2 8 11 PILOT OPTION EJECT OR ARREST 6 8 10 11 12 PILOT OPTION EJECT OR LAND 6 8 10 11 MAINS ONE OR BOTH STUB MOUNT HYPER EXTENDED WHEEL COCKED LAND 1 2 4 8 11 NO AR RESTED LAN...

Страница 200: ...ross deck pendant 50 000 pound weight setting and 1 200 foot runout No information available regarding applicability to other configurations D Maximum engaging speed limited by arresting gear capacity...

Страница 201: ...NAVAIR 01 F14AAP 1B 169 183 EMERGENCY FIELD ARRESTMENT GUIDE SHEET 2 169 SE...

Страница 202: ...NAVAIR 01 F14AAP 1B 170 184 SE...

Страница 203: ...1B 171 185 SINGLE ENGINE OPERATIONS Index SINGLE ENGINE CRUISE OPERATIONS 181 SINGLE ENGINE FAILURE FIELD CATAPULT LAUNCH WAVEOFF 173 SINGLE ENGINE LANDING PRI MODE 173 SINGLE ENGINE LANDING SEC MODE...

Страница 204: ...NAVAIR 01 F14AAP 1B 172 186...

Страница 205: ...th throttles As Required for Positive Rate of Climb 4 Landing gear UP 5 Jettison If Required If banner tow 6 Hook DN 7 If unable to control aircraft Eject 8 Establish 10 unit AOA climb 9 Climb to safe...

Страница 206: ...permitting and full rudder authority RUDDER AUTH light out 4 Wing sweep Set at 20_ EMER If hammering cavitation is experi enced in the hydraulic system compo nent rupture is imminent Turn the hy drau...

Страница 207: ...o do not re turn to auto low mode once module is selected on If module is shut off after operation commences it may not restart 14 For landing pattern use 12 units AOA for pattern airspeed and do not...

Страница 208: ...high sink rate condi tions Use of full AB provides an increase in climb performance Up to full rudder may be required to counter AB asymmetric thrust yawing moment during waveoff or bolter Do not exce...

Страница 209: ...ured for landing 4 Perform constant airspeed climb 5 knots at 10 units AOA landing gear up maneuvering flaps down if possible above 2 000 feet Minimum climb required in 30 seconds is as follows CHANGE...

Страница 210: ...performance criteria are not passed and all options are exhausted stores jettisoned minimum gross weight and divert not possible eject under controlled conditions If configured for landing 123 4 Thro...

Страница 211: ...edbrakes RET on final approach 11 LDG GEAR handle DN 12 Hook As Required 13 Check SAS ON Shore based landings should be con ducted with flaps up If conditions warrant a full flap landing conduct a per...

Страница 212: ...le of bank Extreme caution must be exercised when performing turns into a dead engine Decaying airspeed increasing AOA can rapidly result in a situation where there is not enough rudder authority to r...

Страница 213: ...WING EXT TRANS switch auto matically returns to AUTO if the REFUEL PROBE switch is placed to ALL EXTEND DUMP is selected or there is 2 000 pounds remaining in the low side The WING EXT TRANS switch c...

Страница 214: ...that the sump tank interconnect valve is not open Fuel available is limited to the quantity on the operating engine side If the fuselage fuel quantity on the inoperative engine side begins to decrease...

Страница 215: ...NAVAIR 01 F14AAP 1B 183 197 2 TO...

Страница 216: ...NAVAIR 01 F14AAP 1B 184 198 TO...

Страница 217: ...AVAIR 01 F14AAP 1B 185 199 TAKEOFF Index ABORTED TAKEOFF 187 BLOWN TIRE DURING TAKEOFF 188 TAKEOFF ABORTED OR AFTER LANDING TOUCHDOWN 188 TAKEOFF CONTINUED OR AFTER LANDING GO AROUND 188 185 186 blank...

Страница 218: ...NAVAIR 01 F14AAP 1B 186 200...

Страница 219: ...ght engine OFF if required CAUTION Aircrew should expect hot brakes following heavy gross weight high speed aborts Application of the park ing brake could cause the brake assembly to fail and result i...

Страница 220: ...n order to center rudder pedals Aircraft should have ground locks installed and engine secured before moving aircraft TAKEOFF CONTINUED OR AFTER LANDING GO AROUND 1 Throttles As Required 2 Landing gea...

Страница 221: ...ne 195 Gear Up Flaps Down 48 000 Single Engine 196 Gear Down Flaps Up 48 000 Single Engine 197 Gear Down Flaps Down 48 000 Single Engine 198 Gear Up Flaps Up Wings 68_ 48 000 Two Engines 199 Gear Up F...

Страница 222: ...NAVAIR 01 F14AAP 1B 190 206...

Страница 223: ...RPOSE PYLON 1 8 3 3 AIM 54 ADAPTOR LAUNCHER 1B 8B 3 3 AIM 7 ADAPTOR LAUNCHER 1B 8B 2 2 AIM 9 ADAPTOR LAUNCHER 1 8 1 1 AIM 9 LAUNCHER 1A 8A BRU 32 ADU 703A A 3 4 5 6 2 BRU 42 ITER 3 4 5 6 6 MK 76 3 BOM...

Страница 224: ...C 301 MODIFIED BOATTAIL ADD 10 COUNTS TO DRAG INDEX DRAG INDEX OF ZERO REFERS TO FAIRED AIM 7 CAVITIES WEAPONS DRAG COUNT ____________ RAILS LAUNCHERS DRAG COUNT ____________ EXTERNAL FUEL DRAG COUNT...

Страница 225: ...MK 76 3 BOMBS 75 MK 82 BSU 33 NTP 527 TP 540 MK 82 BSU 86 NTP 566 TP 579 MK 83 CONICAL NTP 971 TP 987 MK 83 BSU 85 NTP 1 006 TP 1 022 MK 84 CONICAL NTP 1 970 TP 1 989 GBU 10 2 083 GBU 16 1 100 MK 20...

Страница 226: ...NAVAIR 01 F14AAP 1B 190d 210...

Страница 227: ...55 46 27 205 2990 3400 264 46 43 DRAG 40 73 15 000 49 30 17 205 2710 3040 264 32 32 DR 20 73 8000 44 15 8 205 2390 2600 264 18 19 00 200 72 43 000 73 120 79 201 4610 5420 256 112 94 X 100 150 72 39 0...

Страница 228: ...27 12 148 4170 5490 182 48 40 DRAG 40 40 17 000 175 18 7 148 3570 4670 182 35 31 DR 20 195 7000 185 7 3 148 2860 3610 180 19 18 00 200 40 27 000 43 31 14 147 8250 12 070 188 134 112 X 100 150 40 28 00...

Страница 229: ...00 47 32 17 191 3520 4210 33 50 44 DRAG 40 43 13 000 40 18 10 191 3090 3680 33 36 34 DR 20 225 4000 210 6 3 191 2590 2980 32 20 19 00 200 56 35 000 61 58 35 189 5910 7350 33 123 100 X 100 150 56 35 00...

Страница 230: ...160 23 9 140 4460 6130 164 49 40 DRAG 40 195 14 000 160 14 5 140 3760 5200 164 35 32 DR 20 195 7000 160 7 2 140 2950 3880 162 19 18 00 200 40 25 000 40 26 11 138 9160 14 220 170 138 115 X 100 150 40 2...

Страница 231: ...2 50 DRAG 40 43 9000 41 16 8 194 2710 3110 242 36 36 DR 20 43 4000 40 7 4 194 2370 2600 242 19 19 00 200 42 21 000 50 38 21 192 5240 6780 244 152 139 X 100 150 42 21 000 50 38 21 192 4500 5680 244 117...

Страница 232: ...166 56 54 DRAG 40 180 6000 165 6 4 146 3700 4310 164 38 36 DR 20 180 3000 165 3 2 146 2870 3200 164 20 19 00 200 175 7000 165 7 5 144 10 630 13 910 170 183 180 X 100 150 175 7000 165 7 5 144 8420 10...

Страница 233: ...52 DRAG 40 205 8000 205 11 5 186 3060 3780 206 37 37 DR 20 205 2000 205 3 1 186 2550 2970 206 19 20 00 200 40 17 000 41 22 12 185 6820 9800 206 162 148 X 100 150 40 17 000 41 22 12 185 5670 7900 206 1...

Страница 234: ...54 DRAG 40 160 7000 160 7 4 138 3850 4570 156 38 37 DR 20 160 3000 160 3 2 138 2950 3340 156 19 19 00 200 155 5000 155 5 3 137 11 590 15 670 162 190 186 X 100 150 155 6000 155 6 4 137 9040 11 960 160...

Страница 235: ...5 AG IN 60 81 28 000 78 38 263 3110 47 44 DRAG 40 81 21 000 61 27 263 2800 47 32 DR 20 81 11 000 55 13 263 2450 47 18 00 200 78 36 000 82 47 255 5400 46 123 X 100 150 78 36 000 82 47 255 4620 46 94 DE...

Страница 236: ...8 3310 45 54 DRAG 40 51 9000 53 10 228 2900 45 38 DR 20 51 5000 49 5 228 2470 45 20 00 200 48 14 000 59 14 219 6630 46 172 X 100 150 48 14 000 59 14 219 5490 46 130 DEX 1 100 48 13 000 57 13 219 4370...

Страница 237: ...58 45 28 215 3010 3420 268 46 42 DRAG 40 73 15 000 51 30 18 215 2730 3050 268 34 31 DR 20 73 8000 45 15 9 215 2400 2600 268 19 18 00 200 72 40 000 72 102 68 210 4750 5600 262 115 99 X 100 150 72 39 0...

Страница 238: ...5 11 155 4300 5680 192 49 42 DRAG 40 40 15 000 180 16 7 155 3650 4790 190 36 32 DR 20 195 6000 180 6 2 155 2890 3640 190 19 19 00 200 40 25 000 43 28 13 154 8570 12 840 194 139 119 X 100 150 40 26 000...

Страница 239: ...00 48 30 17 201 3600 4300 49 52 44 DRAG 40 42 11 000 41 15 8 201 3140 3750 42 37 34 DR 20 225 4000 225 6 3 201 2610 2990 37 20 20 00 200 56 33 000 61 52 32 199 6200 7750 34 128 106 X 100 150 56 33 000...

Страница 240: ...65 22 9 147 4600 6310 172 50 42 DRAG 40 200 13 000 165 13 5 147 3840 5310 172 36 32 DR 20 200 6000 165 6 2 147 2990 3920 170 20 18 00 200 40 23 000 40 24 10 145 9720 15 120 178 144 122 X 100 150 40 24...

Страница 241: ...81 27 000 80 36 276 3170 49 44 DRAG 40 81 20 000 69 25 276 2840 49 32 DR 20 81 10 000 57 12 276 2470 49 18 00 200 78 34 000 83 43 268 5680 48 130 X 100 150 78 34 000 82 43 268 4820 48 100 DEX 1 100 78...

Страница 242: ...718 99 61 202 6990 8710 X 100 500 0 718 97 65 202 8160 10 340 DEX 600 0 718 96 64 202 9360 11 970 G IND 700 0 718 102 62 202 10 590 13 660 AG I 800 0 718 100 61 202 11 830 15 380 DRA 900 0 718 99 65 2...

Страница 243: ...81 27 000 80 36 276 3170 49 44 DRAG 40 81 20 000 69 25 276 2840 49 32 DR 20 81 10 000 57 12 276 2470 49 18 00 200 78 34 000 83 43 268 5680 48 130 X 100 150 78 34 000 82 43 268 4820 48 100 DEX 1 100 78...

Страница 244: ...NAVAIR 01 F14AAP 1B 206 220...

Страница 245: ...scent 241 Prestart Pilot 217 Prestart RIO 221 Takeoff Checklist 239 Taxi Pilot 238 Taxi RIO 238 Ejection Seat Inspection 210 Hot Refueling Procedures 246 Hot Switch Procedures 247 In Flight Refueling...

Страница 246: ...NAVAIR 01 F14AAP 1B 208 222...

Страница 247: ...ions assigned alternate missions 5 External assets call signs 6 Weather a Base en route target area divert b Water air temperature sea state 7 Ordnance and stores carried preflight restrictions on use...

Страница 248: ...kit and para chute will remain attached to the aircrew via lap belts and koch fittings 5 Face curtain automatic release linkage Disconnected 6 System initiator Connected and Pin Removed 7 Time release...

Страница 249: ...f harness sear rods Connected 23 Rocket motor initiator sear and Pin Removed Connected 24 Drogue gun trip rod Connected and Pin Removed 25 Rocket motor initiator sear extraction lanyard Attached 26 Pa...

Страница 250: ...full forward position will pre vent ejection by means of the lower ejection handle 39 Emergency oxygen supply bottle Full Indication 1 800 Psi in black 40 Emergency oxygen actuator Connected Stowed 4...

Страница 251: ...Set 4 Tone VOLUME CONTROLS Set 5 TACAN function selector OFF 6 ICS panel Set 7 STAB AUG switches OFF 8 UHF function selector OFF 9 Wing sweep mode switch MANUAL 10 Emergency wing sweep handle Correspo...

Страница 252: ...h to TO LDG 25 NOSE STRUT switch OFF 26 Parking brake Pull 27 Radar altimeter OFF 28 Altimeter Set 29 Left and right FUEL SHUT OFF handles IN 30 ACM switch OFF guard down 31 MASTER ARM switch OFF guar...

Страница 253: ...of excessive heat in the gun ammunition drum 46 EMERG generator switch NORM guard down 47 Air condition controls Set a TEMP mode selector switch AUTO b TEMP thumbwheel control As Desired 5 to 7 midra...

Страница 254: ...6 SYS TEST SYS PWR ground check panel Closed 7 T CPS switches OFF 8 KY 28 or KY 58 P OFF 9 ICS panel Set 10 CDNU OFF 11 VHF UHF MODE selector OFF 12 LIQ COOLING switch OFF 13 EJECT CMD lever Set Deter...

Страница 255: ...32 RADAR BEACON switch OFF 33 RADAR BEACON MODE switch Single or Double 34 POWER SYS TEST switch OFF 35 DATA ADF switch OFF PRESTART PILOT 1 External electrical power ON 2 If wings are not in OV SWP a...

Страница 256: ...sequent illumination after slight adjustment of either fire warning light during lights test is indicative of a weak ened fire light retaining clip and or current flow impediments at the bulb contact...

Страница 257: ...s status of the emer gency stores jettison circuit cannot be deter mined Under some lighting conditions it may be difficult to determine when the light is illuminated Ensure that the light goes off wh...

Страница 258: ...transitioning fore and aft Note If CLOSE does not close the canopy depress the grip latch release and push handle out board and forward into BOOST If it is neces sary to use BOOST the handle shall be...

Страница 259: ...y Check 6 Lights Check 7 LTS test Check 8 Ejection seats Armed 9 CANOPY handle CLOSE Alert pilot 10 Acknowledge Ready To Start ENGINE START PILOT The RIO must monitor pilot procedures and plane captai...

Страница 260: ...ing crossbleed start attempts select the operating engine for air source and return to BOTH ENG after rpm stabilizes at idle or above 1 ENG CRANK switch L left engine 2 ENG CRANK switch OFF 3 ENG CRAN...

Страница 261: ...y return to the OFF position by 50 percent rpm during start ensure the ENG CRANK switch is off prior to 60 percent rpm to prevent starter overspeed If the START VALVE caution light illumi nates after...

Страница 262: ...sing ab normally increasing the supply engine to 80 precent rpm may yield a normal start tem perature Note D Advancing the R throttle from OFF to IDLE automatically actuates the ignition system An imm...

Страница 263: ...mum f FLT HYD PRESS 3 000 Psi 11 External power Disconnect Ground engine operation without electrical power supplied by either the generators or external power may cause 20 mm ammunition detonation be...

Страница 264: ...5 seconds immedi ately set HYD TRANSFER PUMP switch to SHUTOFF 14 HYD TRANSFER PUMP switch SHUTOFF 15 Repeat steps 6 through 10 for left engine 16 Starter air Disconnect 17 AIR SOURCE switch L ENG R...

Страница 265: ...FAIL group will indicate IMU 4 MASTER TEST switch OFF 5 MASTER RESET pushbutton Depress Verify DFCS caution lights extinguished STAB AUG switches should not disengage 6 Advise RIO that test and checks...

Страница 266: ...y SEC mode closes exhaust nozzles increasing exhaust nozzle jet wake hazard Note Performing AFTC check during OBC inhibits AICS ramps from programming Ramps must be reset before another OBC can be per...

Страница 267: ...HZ TAIL AUTH caution light goes out and OVER flag appears on wing sweep indicator Move handle to full aft OV SW and stow 10 WING SWEEP MODE switch AUTO 11 WING SWEEP DRIVE NO 1 and WG SW DR NO 2 MANUV...

Страница 268: ...MASTER TEST switch OBC 19 AUTOPILOT switch ENGAGE CAUTION OBC commencement with autopilot engaged and nose down trim may result in a force link disconnect when the stick hits forward stick stop durin...

Страница 269: ...r of these areas 21 Speedbrake switch EXT then RET 22 REFUEL PROBE switch ALL EXT then RET 23 WSHLD AIR switch Cycle 24 MASTER TEST switch OBC OFF 25 WING EXT TRANS switch OFF 26 Trim Checked and set...

Страница 270: ...light controls Cycle Observe the following a Pitch control 36 TEU to 9 TED horizontal tail 33 to 12 without ITS b Lateral control 24 total differential tail c Directional control 30 rudder d Longitudi...

Страница 271: ...TEST switch DFCS BIT IBIT RUN coordinate with RIO and plane captain 40 DCP Verify record codes FAIL FLT IBIT 41 DCP Clear codes FAIL FLT 42 Flaps and slats UP 43 Maneuver flaps Down 44 WING SWEEP MOD...

Страница 272: ...56 Tacan BIT 57 ARA 63 BIT 58 HUD VIDEO BIT 59 Altimeter SET RESET mode 60 Compass Check 61 Flight instruments Check POSTSTART RIO Note The RIO will ensure that the EMERG GEN check is completed before...

Страница 273: ...luminated for cooldown period maximum of 17 minutes 13 TACAN EGI select switch EGI 14 RADAR WARNING RCVR panel Set 15 DECM knob STBY a When STBY light goes out select HOLD 3 SEC then ACT for OBC 16 IF...

Страница 274: ...h VERT c FILM switch RUN Observe exposure interval of 1 0 second and frame camera green light illuminated check camera frame counter for proper operation d FILM switch OFF e FRAME switch OFF 22 T PAN...

Страница 275: ...heck camera frame counter for proper operation d FILM switch OFF e PAN switch OFF 25 T IR sensor check Note Before IRLS system check observe IR NR light is out following cooldown and BIT Observe film...

Страница 276: ...s completed a PTID NAV mode INS b Program restart Depress c STBY READY lights OFF 39 DEST data Verify 40 BRG DIST to destination Check 41 OWN A C groundspeed Check 42 MAG VAR Check 43 KY 28 58 As Requ...

Страница 277: ...ure to notify CV OPS may result in dam age to the ship s arresting gear or aircraft tail hook assembly structure 2 Nosewheel steering Cycle Off Then On Failure to cycle nosewheel steering following ho...

Страница 278: ...the hydraulic transfer pump BIDI fails while taxiing with the left engine secured 1 Parking brake Release 2 Nosewheel steering Check 3 Brakes Check 4 Turn and slip indicator Check 5 Ordnance Safe TAXI...

Страница 279: ...FULL BINGO SET 3 CANOPY CLOSED LOCKS ENGAGED LIGHT OUT STRIPES ALIGNED HANDLE IN CLOSE POSITION CLOSED LOCKS ENGAGED LIGHT OUT SEAL INFLATED HANDLE IN CLOSE POSITION 4 SEAT ARMED TOP AND BOTTOM COMMA...

Страница 280: ...S visually checked AS REQUIRED 13 SPOILERS AND ANTISKID SPOILER MODULE ON SPOILER BRAKES SELECTED field SPOILER MODULE ON SPOILER BRAKES OFF CV 14 TRIM 0 0 0 field AS REQUIRED CV 15 HARNESS LOCKED LOC...

Страница 281: ...age resulting in inadvertent AIM 9 sepa ration from the aircraft during an arrested landing PRELAND AND DESCENT 1 HOOK HOOK BYPASS As Desired 2 Exterior lights As Desired 3 Compass BDHI Check With Mag...

Страница 282: ...ause damage 16 WEAPON SELECT Cycle to GUN Then OFF If HOT TRIG light illuminates with MASTER ARM switch OFF or CI PSU acronym was displayed during in flight OBC perform step 17 17 STA 1 8 AIM 9 REL PW...

Страница 283: ...switch OFF 23 T FILM switch OFF CAUTION Before selecting system switch to OFF delay 15 seconds for sensor shutdown IR door to close and mount to drive to vertical 24 T CPS system switch OFF LANDING C...

Страница 284: ...EP handle OV SW 6 Avionics OFF 7 DCP Verify record codes FAIL FLT IBIT 8 Right throttle OFF 9 HYD TRANSFER PUMP switch SHUTOFF after BIDI check 10 Ejection seats SAFE coordinate with RIO 11 Ordnance D...

Страница 285: ...ink OFF 6 DECM switch OFF 7 CDNU RECORD BLENDED GPS FREE INERTIAL POS Record RNAV page data after aircraft parked 8 NAV MODE switch OFF Requires 10 seconds to restore history data prior to removal of...

Страница 286: ...5 Parking brake Pull CAUTION If heavy braking is used during landing or taxi ing followed by application of the parking brake normal brake operation may not be available following release of the parki...

Страница 287: ...LOT 5 Flightcrew Remain strapped in HOT SWITCH PROCEDURES 1 Parking brake Pull 2 HYD TRANSFER PUMP switch NORMAL 3 WCS switch OFF 4 IR TV power switch OFF 5 RECORD switch OFF 6 T CPS system switch OFF...

Страница 288: ...power to TARPS pod 25 T CPS system switch RDY IN FLIGHT REFUELING CHECKLIST The in flight refueling checklist shall be completed before plug in 1 WCS switch STBY 2 Arming switches Safe 3 DUMP switch O...

Страница 289: ...0 59 1790 2465 3455 20 58 000 150 140 90 2000 2305 3285 120 2400 2780 3970 20 1315 1835 2605 59 1455 2030 2880 40 90 1635 2305 3285 120 1970 2780 3970 20 2650 3615 4995 59 2900 3940 5450 0 90 3225 443...

Страница 290: ...3170 4665 20 58 000 152 142 90 2505 3640 5435 120 3100 4565 7010 20 1620 2365 3510 59 1800 2620 3900 40 90 2055 3020 4565 120 2555 3805 5910 20 3245 4630 6785 59 3555 5060 7440 0 90 4030 5820 8755 12...

Страница 291: ...795 59 1510 2140 3090 20 58 000 132 122 90 1710 2420 3520 120 2060 2975 4365 20 1080 1555 2270 59 1200 1730 2525 40 90 1365 1960 2890 120 1655 2420 3600 20 2340 3270 4690 59 2550 3570 5125 0 90 2860 4...

Страница 292: ...8 0 MAXIMUM ENDURANCE ALL DRAG INDEXES ALL ALTITUDES 10 0 IDLE 250 KNOTS MAXIMUM RANGE 9 0 10 0 GEAR AND FLAPS EXTENSION SAFE GEAR EXTENSION FLAPS UP AT 280 KNOTS SAFE FLAP EXTENSION GEAR DN AT 225 KN...

Страница 293: ...O S 50 0 73 IMN 51 000 13 000 205 25 32 000 210 82 30 000 220 136 29 000 225 186 29 000 230 232 73 IMN T 250 KIAS 0 56 000 11 000 210 23 30 000 220 75 29 000 230 125 27 000 235 172 27 000 235 213 0 7...

Страница 294: ...1 000 210 180 11 000 215 217 S 50 0 43 IMN 51 000 500 210 25 4 000 210 75 10 000 215 122 9 000 220 165 9 000 225 199 250 KIAS 0 56 000 500 215 23 2 000 215 69 8 000 220 112 7 000 225 152 7 000 235 183...

Страница 295: ...MERGENCY OPERATION WING SWEEP LESS THAN OR EQUAL TO 50_ AIRSPEED CORRECTION TO BE ADDED TO DLC STOWED APPROACH SPEED WING SWEEP _ AUXILIARY FLAPS RETRACTED KIAS ALL FLAPS SLATS RETRACTED KIAS SLAT RET...

Страница 296: ...ERGENCY OPERATION WING SPEED GREATER THAN 50_ AIRSPEED CORRECTION TO BE ADDED TO DCL STOWED APPROACH SPEED WING SWEEP _ 15 UNITS AOA KIAS 17 UNITS AOA KIAS 51 55 45 60 58 48 68 60 50 LANDING APPROACH...

Страница 297: ...VEL 120 2485 2170 1915 1700 1520 20 2355 2050 1805 1600 1425 59 2545 2230 1965 1750 1570 4000 45 000 126 90 2695 2370 2095 1870 1680 120 2845 2505 2225 1990 1790 20 2735 2405 2130 1905 1710 59 2955 26...

Страница 298: ...LEVEL 120 3050 2700 2410 2160 1955 20 2895 2560 2275 2040 1840 59 3130 2775 2480 2230 2020 4000 55 000 141 90 3315 2950 2645 2390 2165 120 3495 3120 2805 2535 2305 20 3365 2995 2690 2426 2200 59 3635...

Страница 299: ...EVEL 120 3485 3105 2780 2510 2275 20 3305 2935 2625 2385 2140 59 3570 31 5 2860 2585 2350 4000 45 000 148 90 3780 3385 3050 2760 2515 120 3985 3780 3230 2930 2675 20 3840 3440 3100 2810 2555 59 4145 3...

Страница 300: ...0 LEVEL 120 4295 3865 5500 3180 2910 20 3990 3585 3235 2940 2680 59 4475 4035 3655 3330 3050 4000 55 000 164 90 4985 4510 4095 3740 3430 120 5485 4975 4530 4145 3810 20 5105 4620 4205 3840 3525 59 586...

Страница 301: ...291 Circuit Breaker Alphanumeric Index 263 Crosswind Chart Inside Back Cover Dc Essential No 1 Circuit Breaker Panel Right Side Panel No 6 283 Dc Essential No 2 Circuit Breaker Panel Right Aft Panel N...

Страница 302: ...NAVAIR 01 F14AAP 1B 332...

Страница 303: ...L 2I5 AICS L HTR 7E2 AICS L LKUP PWR EMER GEN TEST 6A6 AICS L RAMP STOW LG2 AICS R 2I8 AICS R HTR 7E1 AICS R LKUP PWR ANTI SKID 6A5 AICS R RAMP STOW 8A4 AIM 54 MSL 8G4 AIM 7 L BATT ARM 8G3 AIM 7 R BAT...

Страница 304: ...N AWW 4 PH A 1C4 AN AWW 4 PH B 1B6 AN AWW 4 PH C 3C3 ANGLE OF ATTK IND AC 7E3 ANGLE OF ATTACK IND DC 4F5 ANL ATTK TOTAL TEMP HTR 7C1 ANN PANEL PWR 7F3 ANN PILOT PANEL AUX PWR TR ADVSY 8C2 ANN PNL DDI...

Страница 305: ...OT AC 8B7 AUTO THROT DC 7G3 AUX FLAP FLAP CONTR 6B7 AWG 15 DC 5B5 AWG 15 PH A NO 1 5B4 AWG 15 PH A NO 2 5D5 AWG 15 PH B NO 1 5D4 AWG 15 PH B NO 2 5F5 AWG 15 PH C NO 1 5F4 AWG 15 PH C NO 2 3D3 BARO ALT...

Страница 306: ...B7 CSDC PH A 4B2 CSDC PH B 4B5 CSDC PH C 6B5 DC ESS NO 1 FDR 7A2 DC ESS NO 2 BUS FDR 7G7 DC L TEST RUDDER TRIM 8D1 DC R TEST AMC BIT 1I1 DDI AC 8C2 DDI ANN PNL DIM CONTR 8G6 DDI DC ASW 27 7B1 DFCS BUS...

Страница 307: ...7G10 EXT LT CONTR 8D2 FEMS COUNTING ACCEL 7C4 FIRE L DET LT 6C5 FIRE L EXT 7C3 FIRE R DET LT 6C4 FIRE R EXT 7G3 FLAP CONTR AUX FLAP 3E3 FLAP IND TAIL RUDDER RE2 FLAP SLAT CONTR SHUT OFF LD1 FLT CONTR...

Страница 308: ...B3 GUN CLR GUN CONTR PWR DC 2H5 GUN CONTR PWR AC 8B3 GUN CONTR PWR DC GUN CLR 8I3 GYRO PWR 1B1 HSD ECMD PH A 1B4 HSD ECMD PH B 1B7 HSD ECMD PH C 8C4 HUD CAMERA DC 1F1 HUD CAMERA PH A 1D4 HUD CAMERA PH...

Страница 309: ...2 INTRF BLANKER 8I1 INTRPT FREE DC BUS FDR NO 1 8C6 INTRPT FREE DC BUS FDR NO 2 6E3 JETT 1 6E2 JETT 2 7D7 JULIET 28 LF2 L AICS 2I5 L AICS HTR 7E2 L AICS LKUP PWR EMER GEN TEST 6A6 L AICS RAMP STOW 8G4...

Страница 310: ...ER ARM 8H5 MASTER TEST 8H3 MECH FUZING STA 1 8 8H2 MECH FUZING STA 3 4 8H1 MECH FUZING STA 5 6 7G5 MLG HANDLE RLY NO 1 7G4 MLG HANDLE RLY NO 2 6F5 MLG SAFETY RLY NO 1 6F4 MLG SAFETY RLY NO 2 8D3 MONIT...

Страница 311: ...OLL TRIM L PH B TEST 4E5 P ROLL TRIM L PH C TEST RA2 P ROLL TRIM SPD BK ENABLE 3E6 PH A L TEST P ROLL TRIM 2H1 PH A R TEST 4E2 PH B L TEST P ROLL TRIM 2H4 PH B R TEST 4E5 PH C L TEST P ROLL TRIM 2H8 P...

Страница 312: ...RECON HTR PWR PH C 1F4 RECON POD 8F7 RECON POD CONTR 8F1 RECON POD DC PWR NO 2 8F2 RECON POD DC PWR NO 1 7A5 R ENG AFT CONT EXHAUST NOZZLE 5A3 R ENG BACK UP IGN 3C2 R ENG N2 TACH 4D6 R ENG OIL PRESS...

Страница 313: ...H A 1H5 SOL PWR SUP PH B 1H7 SOL PWR SUP PH C RA2 SPD BK P ROLL TRIM ENABLE 7G11 SPOILER CONTR HYD PUMP 7G9 SPOILER CONTR INBD 8C5 SPOILER CONTR OUTBD 7G1 SPOILER POS IND GND ROLL BRAKING 8E4 STA 1 AI...

Страница 314: ...TA 8 REL PWR A 6E4 STA 8 REL PWR B 8E3 STA 8A AIM 9 PWR 2I7 STA 8A AIM 9 PWR PH B 8E2 STA 8B AIM 9 PWR 2I9 STA 8B AIM 9 PWR PH C 7F8 STARTER VALVE LT THRUST LIM 5A5 STBY ATTD IND PH A 5C5 STBY ATTD IN...

Страница 315: ...EP DRIVE NO 1 7C2 WSHD AIR ANTI ICE HK CONTR 8B2 WSHLD DEFOG CONTR 1A5 XFMR RECT L MAIN 2E3 XFMR RECT R MAIN 7B6 YAW A DC 7B5 YAW B DC LC1 YAW A AC LC3 YAW B AC LB3 YAW M ROLL A 3F7 26 VAC BUS FDR 1B2...

Страница 316: ...NAVAIR 01 F14AAP 1B 276 300 276 Change 3...

Страница 317: ...NAVAIR 01 F14AAP 1B 277 293 AC LEFT MAIN CIRCUIT BREAKER PANEL LEFT AFT PANEL NO 1 UPPER SEGMENT...

Страница 318: ...NAVAIR 01 F14AAP 1B 278 294 AC LEFT MAIN CIRCUIT BREAKER PANEL LEFT AFT PANEL NO 1 LOWER SEGMENT...

Страница 319: ...NAVAIR 01 F14AAP 1B 279 295 AC RIGHT MAIN CIRCUIT BREAKER PANEL LEFT AFT PANEL NO 2...

Страница 320: ...NAVAIR 01 F14AAP 1B 280 296 AC ESSENTIAL NO 2 PHASE A CIRCUIT BREAKER PANEL LEFT PANEL NO 3...

Страница 321: ...NAVAIR 01 F14AAP 1B 281 297 AC ESSENTIAL NO 2 PHASE B AND C CIRCUIT BREAKER PANEL LEFT PANEL NO 4...

Страница 322: ...NAVAIR 01 F14AAP 1B 282 298 AC ESSENTIAL NO 1 CIRCUIT BREAKER PANEL RIGHT SIDE PANEL NO 5 282 Change 2...

Страница 323: ...NAVAIR 01 F14AAP 1B 283 299 DC ESSENTIAL NO 1 CIRCUIT BREAKER PANEL RIGHT SIDE PANEL NO 6...

Страница 324: ...NAVAIR 01 F14AAP 1B 284 300 DC ESSENTIAL NO 2 CIRCUIT BREAKER PANEL RIGHT AFT PANEL NO 7 UPPER SEGMENT 284 Change 2...

Страница 325: ...NAVAIR 01 F14AAP 1B 285 301 DC ESSENTIAL NO 2 CIRCUIT BREAKER PANEL RIGHT AFT PANEL NO 7 LOWER SEGMENT...

Страница 326: ...NAVAIR 01 F14AAP 1B 286 302 DC MAIN CIRCUIT BREAKER PANEL RIGHT AFT PANEL NO 8 UPPER SEGMENT...

Страница 327: ...NAVAIR 01 F14AAP 1B 287 303 DC MAIN CIRCUIT BREAKER PANEL RIGHT AFT PANEL NO 8 LOWER SEGMENT...

Страница 328: ...e maximum refueling rate is approximately 500 gallons per minute at a pressure of 50 psi Nominal and minimum pressure is approximately 15 psi and maximum pressure is 50 psi Ensure that both the fuelin...

Страница 329: ...p is necessary it shall not be defueled into storage tanks containing JP 5 ENGINE OIL For normal servicing sight gauge on the oil storage tank is the primary indicator as to whether servicing is requi...

Страница 330: ...gauge must be checked no sooner than 5 minutes and no later than 60 minutes after shutdown HYDRAULIC SYSTEMS Hydraulic servicing is required on the flight and combined sys tems outboard spoiler backu...

Страница 331: ...NAVAIR 01 F14AAP 1B 291 307 AIRCRAFT SERVICING LOCATIONS...

Страница 332: ...XYGEN BOTTLE NITROGEN BB N 411C TYPE I GRADE A NONE NONE NONE USE CLEAN OIL FREE FILTERED DRY AIR IF NITROGEN IS NOT AVAILABLE LIQUID COOLANT COOLANT 25 25R MONSANTO CHEMICAL CO CHEVRON FLO COOL 180 C...

Страница 333: ...0 PSI AT 70 F ARRESTING HOOK DASHPOT 800 10 PSI MAIN GEAR SHOCK STRUTS 2 980 PSI NOSEGEAR SHOCK STRUT 1300 PSI WINDSHIELD AIR 75 PSI NOTE DRY NITROGEN SPECIFICATION BB N 411C TYPE 1 GRADE A IS PREFERR...

Страница 334: ...NAVAIR 01 F14AAP 1B 294 310 AIRCRAFT SERVICING DATA SHEET 3...

Страница 335: ...NAVAIR 01 F14AAP 1B 295 311 AIRCRAFT SERVICING DATA SHEET 4...

Страница 336: ...NAVAIR 01 F14AAP 1B 296 312 AIRCRAFT SERVICING DATA SHEET 5 296 Change 2...

Страница 337: ...NAVAIR 01 F14AAP 1B 297 313 AIRCRAFT SERVICING DATA SHEET 6...

Страница 338: ...NAVAIR 01 F14AAP 1B 298 314 AIRCRAFT SERVICING DATA SHEET 7...

Страница 339: ...NAVAIR 01 F14AAP 1B 299 315 AIRCRAFT SERVICING DATA SHEET 8 299 300 blank...

Страница 340: ...NAVAIR 01 F14AAP 1B 300 316...

Страница 341: ...uminated proceed to the next card Likewise if the ARI DGR caution light is not illuminated proceed to the next card Proceed until one of the lights is recognized Then identify the matching set of caut...

Страница 342: ...FLIGHT FAULT MATRIX MISC LIGHTS CARD 9 of 10 DFCS IN FLIGHT FAULT MATRIX NO LIGHTS CARD 10 of 10 Abbreviations used in these cards ARI automatic rudder interconnect functions listed below LSRI latera...

Страница 343: ...oll SAS basic OB spoilers inop Authority stops inop DLC Autopilot inop DCP inop 1 DCP inop YC codes blanked FCS CAUTION PS RS YS UA 1 Yaw rate 2F 1 Roll SAS ARI SR inop Yaw SAS ARI SR inop PQVM inop 1...

Страница 344: ...er failure degrade 1 RC RS PA or UA 1 Roll Rate 2F1 2 Lateral stick position 2F 5 1 Roll SAS ARI inop Yaw SAS basic 2 Roll SAS ARI SR inop Yaw SAS basic Spoilers inop 1 RGY 2 RCP ARI SAS OUT ARI DGR R...

Страница 345: ...I half authority gain doubled 1 YSA ARI DGR ROLL DGR PITCH SAS FCS CAUTION PS PA or UA 1 Mach 1F 600 kts AICS cross check 1 Pitch SAS inop Roll SAS degrade low gain ARI degrade fixed Mach gains 1 MACL...

Страница 346: ...C inop 3 ARI degrade fixed Mach gains Autopilot Mach trim inop YAW DGR after maneuvering WRS LSXC inop 4 5 Equivalent of AOA Mach 1F 1 AD01 2 AD04 3 AD01 04 4 AOAL MACL AICX 5 AOAR MACR AICX PA 1 AOA...

Страница 347: ...S CONFIG FAILURE CAUSE S FUNCTIONALITY DEGRADED DCP FLT CODE S PITCH SAS FCS CAUTION PC PS RA RS PA or UA 1 PITCH A computer fault 1 5 1 Pitch SAS half auth IB spoilers inop DLC Auto pilot inop ARI DG...

Страница 348: ...on 1F 2 Roll rate 1F 1 No effect one failure away from loss of roll SAS ARI spoilers 2 No effect one failure away from loss of roll SAS ARI 1 RCP 2 RGY YS PA or UA 1 Rudder pedal position 1F 2 Yaw rat...

Страница 349: ...AD05 HZ TAIL AUTH PA or UA 1 Lateral authority actuator fault 2 28 VDC lateral authority fault 3 Lateral authority schedule fault 1 3 Lateral authority stops inop 1 HZTA 2 HT28 2 AD07 RUDDER AUTH PA o...

Страница 350: ...flaps up 1 WSP PA or UA 1 AHRS valid fault w INS invalid 1 1 AHRS inop Autopilot ACLS inop w IMU failure 1 AHR PA or UA 1 Emergency disengage to pitch roll computer fault 1 1 Emergency paddle off capa...

Страница 351: ...m followed by IBIT DFCS DN or SW status may be further resolved by the DOWN DN SOP WAIVER SW NOTES see below Aircraft UP DOWN status regarding other systems shall be considered independent of DFCS IBI...

Страница 352: ...fault A3 1x IMU failure LAT I O Lateral accelerometer fault X9 1x Redundancy 2x Yaw SAS ARI LDG O Main landing gear handle discrete fault D0 1x Redundancy 2x Default UA control laws MACL O Left AICS M...

Страница 353: ...ncy will initialize SAR 5 Note the time Lat Long and winds 6 Monitor guard When contact is established with SAR Helo switch to SAR primary 282 8 7 Warn non participating A C to stay clear 8 Leave freq...

Страница 354: ...NAVAIR 01 F14AAP 1B 314 Change 2 330...

Страница 355: ...VELOCITY ARC FROM INTERSECTION OF WIND ANGLE AND VELOCITY DETERMINE HEADWIND COMPONENT BY PROJECTING HORIZONTALLY TO LEFT DETERMINE CROSSWIND COMPONENT BY DROPPING VERTICALLY TO BASELINE UNTIL FURTHER...

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