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Navair F-14B Emergency Procedure Tabs

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CIRCUIT BREAKERS
EMERGENCY PROCEDURE TABS
NAVAIR 01-F14AAP-1B
POCKET CHECKLIST
AIRCRAFT
DISTRIBUTION STATEMENT C — DISTRIBUTION
AUTHORIZED TO U.S. GOVERNMENT AGENCIES
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.
ISSUED BY AUTHORITY OF THE CHIEF OF
NAVAL OPERATIONS AND UNDER THE
DIRECTION OF THE COMMANDER,
NAVAL AIR SYSTEMS COMMAND.
REFERENCE DATA
NATOPS
F-14B
01 AUGUST 2001
BINGO
ECS LEAKS
COCKPIT/OXYGEN
COOLANT/CANOPY
CONTROLLED
MANUAL
GROUND EGRESS
GENERATOR
ELECTRICAL
TRANS/RECT
WOW
AICS/AIRSTART
NOZZLE/START VALVE
OIL/THROTTLE
INFLIGHT
ON DECK
ELECTRICAL
FLAPS
FLAPS
FLIGHT
SPOILERS
SPOILERS
CONTROL
WINGSWEEP
WINGSWEEP
SAS
SAS
DUMP
LEAK
PRESSURE
TRANSFER
COMBINED
FLIGHT
HYDRAULICS
BRAKES
ARRESTMENT
LANDING GEAR/
BRAKES
BLOWN TIRE
LAUNCH BAR
TAKEOFF
SINGLE ENGINE
LANDING
CRUISE/FUEL
MIGRATION
ABORT
BLOWN TIRE
ECS
EJECT/
EGRESS
ENGINE
FIRE
FLIGHT
CONTROL
FUEL
LANDING
OPS
TAKEOFF

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  • Page 1 CIRCUIT BREAKERS REFERENCE DATA BINGO ECS LEAKS EMERGENCY PROCEDURE TABS COCKPIT/OXYGEN COOLANT/CANOPY NAVAIR 01-F14AAP-1B CONTROLLED NATOPS EJECT/ MANUAL EGRESS POCKET CHECKLIST GROUND EGRESS GENERATOR F-14B ELECTRICAL TRANS/RECT AIRCRAFT AICS/AIRSTART ENGINE NOZZLE/START VALVE OIL/THROTTLE INFLIGHT FIRE ON DECK ELECTRICAL DISTRIBUTION STATEMENT C — DISTRIBUTION AUTHORIZED TO U.S.
  • Page 2 NAVAIR 01-F14AAP-1B MISCELLANEOUS DATA INDEX ADMIN BRIEF ......... .
  • Page 3 NAVAIR 01-F14AAP-1B NATOPS POCKET CHECKLIST F-14B AIRCRAFT DISTRIBUTION STATEMENT C — Distribution authorized to U.S. Government agencies and their contractors to protect publications required for official use or for administrative or operational purposes only (1 June 1992). Other requests for...
  • Page 4 NAVAIR 01-F14AAP-1B NAVAIR 01-F14AAP-1B Reproduction for nonmilitary use of the information or illustrations con- tained in this publication is not permitted without specific approval of the Commander, Naval Air Systems Command. The policy for use of classified publications is established for the Navy and Marine Corps in OPNAVINST 5510-1 series.
  • Page 5 NAVAIR 01-F14AAP-1B LIST OF EFFECTIVE PAGES (continued) Page No. Issue Page No. Issue 209 thru 213 ... . 129/(130 blank) ......
  • Page 6 NAVAIR 01-F14AAP-1B INTERIM CHANGE SUMMARY The following Interim Changes have been cancelled or previously incorporated into this manual. INTERIM CHANGE NUMBER(S) REMARKS/PURPOSE 1 thru 30 Incorporated The following Interim Changes have been incorporated into this Change/Revision. INTERIM CHANGE NUMBER(S) REMARKS/PURPOSE...
  • Page 7 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, DTD 01 AUG 01 WITH CHANGE 3 DTD 15 JAN 04. REF G IS F-14A POCKET CHECKLIST (PCL) 01-F14AAA-1B, DTD 15 MAY 03 WITH CHANGE 1 DTD 15 JAN 04.
  • Page 8 D. CHAPTER 14, PAGE 14-18, SECOND COLUMN, SECOND NOTE PARAGRAPH, LINE 1: (1) DELETE: AND (2) ADD: AND/OR 5. CHANGE REF E (F-14B PCL) AS FOLLOWS: A. PAGE 123, TITLE: (1) DELETE: WARNING TONE. (2) ADD: 10 SEC WARNING TONE.
  • Page 9 9. POINTS OF CONTACT: A. F-14ABD NATOPS PROGRAM MANAGER, LT KYLE MILLER, TEL DSN 433-5147, OR COMM (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 OFFICER, TEL DSN 995-2052, OR COMM (301)995-2052, EMAIL: JAMES.NASH(AT)NAVY.MIL...
  • Page 11 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, DTD 01 AUG 01 WITH CHANGE 3 DTD 15 JAN 04. REF G IS F-14A POCKET CHECKLIST (PCL) 01-F14AAA-1B, DTD 15 MAY 03 WITH CHANGE 1 DTD 15 JAN 04.
  • Page 12 I. (1) DELETE: EXISTING STEP 3. (2) ADD (REPLACE WITH): "3. FUEL FEED SWITCH - AS REQUIRED AND LAND AS SOON AS PRACTICABLE." J. (1) DELETE: NA NAVAIR 212005Z JUL04 Page 2 of 11 A1-F14AAA-1 IC 150 A1-F14AAA-1B IC 106...
  • Page 13 SELECTING THE HIGH FUSELAGE TAPE SIDE." F. (1) DELETE: ENTIRE WARNING THAT BEGINS WITH "AIRCRAFT ATTITUDE WILL HAVE A SIGNIFICANT INFLUENCE..." (2) ADD: NA G. (1) DELETE: NA NAVAIR 212005Z JUL04 Page 3 of 11 A1-F14AAA-1 IC 150 A1-F14AAA-1B IC 106...
  • Page 14 (2) ADD (INSERT): NEW STEP 6 AFTER STATEMENT TO READ: "6. REFER TO FUEL LEAK PROCEDURE (PAGE 14-19)." CHANGE REF E (F-14B PCL), FUEL CHAPTER, PAGE 127 & 128 AS FOLLOWS: A. (1) DELETE: STATEMENTS UNDER FIRST WARNING: "DURING AB OPERATIONS, NORM SHALL BE SELECTED.
  • Page 15 THE HIGH FEED GROUP HAVING TRAPPED/UNUSABLE FUEL. IF THIS OCCURS, AIRCREW MAY HAVE AS LITTLE AS 4,500 POUNDS OF USABLE FUEL REMAINING AND A NEW BINGO PROFILE MAY BE REQUIRED." NAVAIR 212005Z JUL04 Page 5 of 11 A1-F14AAA-1 IC 150...
  • Page 16 (2) ADD (INSERT): NEW STEP 6 AFTER STATEMENT TO READ: "6. REFER TO FUEL LEAK PROCEDURE (PAGE 126A)." CHANGE REF F (F-14B NFM), CHAPTER 14, PAGE 14-20A, PARAGRAPH 14.6.6 AS FOLLOWS: A. (1) DELETE: STATEMENTS UNDER FIRST WARNING: "DURING AB OPERATIONS, NORM SHALL BE SELECTED.
  • Page 17 FUEL.DO NOT DELAY EXECUTION OF EMERGENCY PROCEDURES FOR VISUAL INSPECTION." (1) DELETE: NA (2) ADD (INSERT): NOTE PARAGRAPH AFTER PRECEEDING (INSERTED) NOTE PARAGRAPH, BUT PRIOR TO THE EXISTING WARNING PARAGRAPH TO READ: NAVAIR 212005Z JUL04 Page 7 of 11 A1-F14AAA-1 IC 150 A1-F14AAA-1B IC 106...
  • Page 18 CHANGE REF H (F-14A NFM), CHAPTER 14, PAGE 14-17, PARAGRAPH 14.6.6 AS FOLLOWS: A. (1) DELETE: STATEMENTS UNDER FIRST WARNING: "DURING AB OPERATIONS, NORM SHALL BE SELECTED. FWD OR AFT COULD DEPLETE THE SUMP TANKS." NAVAIR 212005Z JUL04 Page 8 of 11 A1-F14AAA-1 IC 150 A1-F14AAA-1B IC 106 A1-F14AAP-1...
  • Page 19 READ: "IF FUEL VENTING EXISTS AND/OR FUEL IMBALANCE EXCEEDS 2,000 POUNDS:" K. (1) DELETE: NA (2) ADD (INSERT): NEW STEP 4 TO READ: "FUEL FEED SWITCH - NORM." NAVAIR 212005Z JUL04 Page 9 of 11 A1-F14AAA-1 IC 150 A1-F14AAA-1B IC 106...
  • Page 20 9. POINTS OF CONTACT: A. F-14ABD NATOPS PROGRAM MANAGER, LT KYLE MILLER, TEL DSN 433-5147, OR COMM (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 OFFICER, TEL DSN 995-2052, OR COMM (301)995-2052, EMAIL: JAMES.NASH(AT)NAVY.MIL...
  • Page 21 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 attached as follows: Page Page Version Marking ------...
  • Page 23 NAVAIR 01-F14AAP-1B CRITICAL PROCEDURE Procedures marked with an asterisk are considered to be time critical and are so identified to emphasize their importance. Pilots should be able to accomplish these procedures without reference to the checklist. EMERGENCY PROCEDURES INDEX ENGINE FLAMEOUT .
  • Page 24 NAVAIR 01-F14AAP-1B CRITICAL PROCEDURE Procedures marked with an asterisk are considered to be time critical and are so identified to emphasize their importance. Pilots should be able to accomplish these procedures without reference to the checklist. EMERGENCY PROCEDURES INDEX SPOILER LIGHT/MALFUNCTIONS .
  • Page 25 NAVAIR 01-F14AAP-1B ADVISORY LIGHT LIGHT CAUSE ACTION ACLS or autopilot Take control for manual land- disengagement. ing approach. AHRS Failure of AHRS or com- Use INS-IMU; avoid IFR flight pass controller. if INS-IMU not available. Selected A/P reference is Depress autopilot reference not engaged.
  • Page 26 NAVAIR 01-F14AAP-1B LIGHT CAUSE ACTION Operating in Aux brake 1. Turn antiskid off. mode or antiskid failure 2. Cautious brake application 3. Release emergency brake Cabin pressure failure. 1. O mask on 2. See page 17. CADC failure. 1. MASTER RESET.
  • Page 27 NAVAIR 01-F14AAP-1B LIGHT CAUSE ACTION Engine mode control in 1. Throttle — LESS THAN secondary 2. ENG MODE SELECT switch — CYCLE 3. See page 55. Low-extinguisher agent Report to maintenance FIRE EXT pressure. DFCS failure has 1. MASTER RESET.
  • Page 28 NAVAIR 01-F14AAP-1B LIGHT CAUSE ACTION Combined or flight pump 1. See page 133. discharge pressure 2,100 psi or less. CADC failure or failure of 1. MASTER RESET (10 actuators to follow seconds) schedule. 2. Above 400 KIAS, restrict lateral control to 1/4 throw.
  • Page 29 NAVAIR 01-F14AAP-1B LIGHT CAUSE ACTION MACH TRIM Failure of mach trim 1. MASTER RESET actuator to follow 2. Retrim manually. program. MSL COND AIM-54 coolant hot or no 1. Check LIQ COOLING flow. switch. 2. LIQ COOLING switch to AWG-9 if AWG-9/ AIM-54 selected.
  • Page 30 NAVAIR 01-F14AAP-1B LIGHT CAUSE ACTION Indicates inoperative roll 1. MASTER RESET channel and degraded 2. See page 96. roll authority. CADC failure or failure 1. MASTER RESET (10 of actuator to follow seconds) schedule. 2. See page 100. Symmetric spoiler detec- 1.
  • Page 31 NAVAIR 01-F14AAP-1B Index AWG-9 COND LIGHT ILLUMINATED AND/OR PUMP PHASE CIRCUIT BREAKERS POPPED OR AWG-9 PM ACRONYM ..CABIN PRESS LIGHT .......
  • Page 32 NAVAIR 01-F14AAP-1B...
  • Page 33 NAVAIR 01-F14AAP-1B ECS LEAK/ ELIMINATION OF SMOKE AND FUMES D Failure to immediately select AIR SOURCE OFF upon indication of an ECS leak may result in severe air- craft damage. D Selection of AIR SOURCE to RAM allows bleed air to circulate through- out the 400 °F manifold system.
  • Page 34 NAVAIR 01-F14AAP-1B The presence of any one direct indication or any two indirect indications shall be treated as an ECS leak. When an ECS leak occurs or smoke or fumes are present: *1. AIR SOURCE ......
  • Page 35 NAVAIR 01-F14AAP-1B Note D Securing all electrical power while airborne closes cockpit dump valve and cabin hot air valve, opens bleed air shutoff valves and dual-pressure regulator, and the ram air door re- mains at its last commanded posi- tion (ram air door takes up to 50 seconds to open).
  • Page 36 NAVAIR 01-F14AAP-1B Note Elimination of smoke or fumes without electrical power may be accomplished by ECS airflow. To obtain maximum smoke/fume removal capability under this condition, fly below 8,000 feet MSL and set the throttle to maximum practi- cal position. This will open the cabin regulator valve for maximum ECS air- flow.
  • Page 37 NAVAIR 01-F14AAP-1B IN FLIGHT 1. AIR SOURCE ......Failure to immediately select AIR SOURCE pushbutton OFF upon indica-...
  • Page 38 NAVAIR 01-F14AAP-1B COCKPIT TEMPERATURE CONTROL MALFUNCTION 1. TEMP mode switch ....2. TEMP thumbwheel ....
  • Page 39 NAVAIR 01-F14AAP-1B The canopy may explosively leave the aircraft upon unlocking of the canopy sill locks if cockpit overpressure is not reduced. CABIN PRESS LIGHT 1. Oxygen masks ......
  • Page 40 NAVAIR 01-F14AAP-1B TARPS ECS LIGHTS 1. TARPS sensors ......2. SYSTEM switch ......
  • Page 41 NAVAIR 01-F14AAP-1B If associated with any other direct or indirect indication of ECS malfunction, perform ECS Leak/Elimination of Smoke and Fumes procedure: 5. Land as soon as practicable. OXYGEN SYSTEM FAILURE 1. Oxygen quantity .....
  • Page 42 NAVAIR 01-F14AAP-1B OXY LOW LIGHT (RIO ONLY) 1. Notify pilot. 2. Oxygen quantity ..Less Than 2 Liters 3. Cabin altitude ..Less Than 10,000 Feet 4.
  • Page 43 NAVAIR 01-F14AAP-1B LADDER LIGHT 1. Airspeed ..Minimum Safe Operating 2. Obtain in-flight visual check if possible. EJECT EGRESS 3. Land as soon as practicable. WSHLD HOT LIGHT 1. WSHLD AIR .
  • Page 44 NAVAIR 01-F14AAP-1B EJECT EGRESS...
  • Page 45 NAVAIR 01-F14AAP-1B EJECT/EGRESS Index CONTROLLED EJECTION ......GROUND EGRESS WITHOUT PARACHUTE AND SURVIVAL KIT .
  • Page 46 NAVAIR 01-F14AAP-1B...
  • Page 47 NAVAIR 01-F14AAP-1B CONTROLLED EJECT/EGRESS EJECTION Do not secure engines. Unsuccessful seat activation may require continued flight to allow alternate egress method. 1. Place aircraft in safe envelope and attitude for ejection. 2. Warn other crewmember. 3. EJECT CMD lever ....
  • Page 48 NAVAIR 01-F14AAP-1B D Positioning the legs aft prior to ejection will cause the spine to flex and will increase the possibility of spinal injury and will also increase likelihood of seat/thigh slap with attendant leg injury. D Proper body position is a critical...
  • Page 49 NAVAIR 01-F14AAP-1B 5. Emergency restraint release ... . . Pull 6. Ensure seat pan and leg restraints are discon- nected from ejection seat. 7. Release stick. 8. Roll forward and push free of aircraft.
  • Page 50 NAVAIR 01-F14AAP-1B ELECT...
  • Page 51 NAVAIR 01-F14AAP-1B ELECTRICAL Index DOUBLE GENERATOR FAILURE ..... ESSENTIAL BUSES NO. 1 (1 KVA MODE) ...
  • Page 52 NAVAIR 01-F14AAP-1B...
  • Page 53 NAVAIR 01-F14AAP-1B L OR R GEN LIGHT ELECTRICAL 1. Generator (affected generator switch ......OFF/RESET, Then NORM If generator does not reset: 2.
  • Page 54 NAVAIR 01-F14AAP-1B If temporary loss of combined system pressure causes emergency generator to shift to 1 kVA mode: 2. EMERG generator switch ....Cycle CAUTION A shift to 1-kVA mode will cause loss of all DFCS functions and spoilers with- out illumination of caution lights.
  • Page 55 NAVAIR 01-F14AAP-1B ESSENTIAL BUSES NO. 1 (1 KVA MODE) ACM Control Fuel Quantity Indicator Hydraulic Pressure AICS Ramp Stow Indication (Flight Airspeed Indication and Combined) Altitude Low Warning Approach Lights Angle-of-Attack Jettison (Emergency) Indication KY-28 or KY-58 AWG-15 Master Arm...
  • Page 56 NAVAIR 01-F14AAP-1B ESSENTIAL BUSES NO. 2 ACM Panel Lights ECM (Navigational Aids, IFF Interrogator, and Advisory Lights Transmitter) Eject Command DFCS/SAS Indicator AHRS Electronic Cooling AICS Emergency Generator Air-Conditioning Test Air Source Control Engine: Anti-Ice Antiskid Control Fan Speed Limiting...
  • Page 57 NAVAIR 01-F14AAP-1B ESSENTIAL BUSES NO. 2 (Cont.) Hydraulic Valve Radar Beacon Control Servo-pneumatic Ice Detection Altimeter Speedbrakes In-Flight Refueling Spoiler Control Probe/Light Tacan Launch Bar Utility/Map Lights PMDIG (Display Panel) VDIG(R) Nose Landing Gear Warning Lights Kneeling Wheels and Nosewheel Steering...
  • Page 58 NAVAIR 01-F14AAP-1B FAILURE OF BOTH TRANSFORMER- RECTIFIERS EQUIPMENT INOPERATIVE LIST AIM-7 MOTOR FIRE GUN CONTROL POWER AIM-54 MISSILE GYRO POWER ALE-47 CHAFF/FLARE IFF AIR TO AIR DISPENSER INTEGRATED TRIM INTERRUPTION FREE ALR-67 RECEIVER/ CONTROL DC BUS FOR NO. 1 AND 2...
  • Page 59 NAVAIR 01-F14AAP-1B TOTAL ELECTRICAL FAILURE 1. Descend or climb to known VFR conditions. CAUTION All DFCS functions and spoilers will be lost. This will have an adverse effect on flying qualities. Terminate aggressive maneuvering immediately and remain subsonic. Expect minimal damping of...
  • Page 60 NAVAIR 01-F14AAP-1B 3. Cabin pressure altimeter. 4. Vertical velocity indicator. 5. Arresting hook (emergency extension only). 6. Standby attitude gyro (9 minutes). 7. Emergency wing sweep. 8. Landing gear. 9. Main flaps/slats. 10. Standby compass. Ground engine operation without elec-...
  • Page 61 NAVAIR 01-F14AAP-1B Note D Total electrical failure will cause the sump tank interconnect, engine crossfeed, and motive flow isolation valves to close, fully isolating both tank systems. Wing and external fuel will transfer into fuselage. D If possible, section IFR descent should be conducted to VFR condi- tions for landing.
  • Page 62 NAVAIR 01-F14AAP-1B If two or more of the preceding anomalies are detected, the following action should be taken: ON DECK — PILOT 1. Clear runway (if applicable). 2. Generators ......
  • Page 63 NAVAIR 01-F14AAP-1B 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...
  • Page 64 NAVAIR 01-F14AAP-1B If two or more of the above anomalies are detected, the following action should be taken. IN FLIGHT — PILOT Do not move both throttles to IDLE un- less ANTI SKID SPOILER BK switch is set to OFF if weight on-off wheels...
  • Page 65 NAVAIR 01-F14AAP-1B Note D Circuit breakers can be reset 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 may be declared which will inhibit ground roll braking.
  • Page 66 NAVAIR 01-F14AAP-1B...
  • Page 67 NAVAIR 01-F14AAP-1B ENGINE Index ABNORMAL START ....... . . AICS MALFUNCTION .
  • Page 68 NAVAIR 01-F14AAP-1B...
  • Page 69 NAVAIR 01-F14AAP-1B ABNORMAL START ENGINE 1. Throttle (affected engine) ....2. BACKUP IGNITION switch ..Check OFF CAUTION...
  • Page 70 NAVAIR 01-F14AAP-1B ENGINE START VALVE LIGHT 1. Ensure ENG CRANK ....2. AIR SOURCE ......
  • Page 71 NAVAIR 01-F14AAP-1B If EGT above 935_C and/or engine response abnormal: *4. Throttle (affected engine) ....If EGT normal and/or airstart successful: 5. Perform engine operability check.
  • Page 72 NAVAIR 01-F14AAP-1B If one engine is operable, perform a crossbleed airstart. If both engines flamed out/inoperative or crossbleed not possible: D A dual engine compressor stall may result in a total electrical failure, rendering the ICS, engine instru- ments, spin direction indicators (spin arrow and turn needle), and displays inoperative.
  • Page 73 NAVAIR 01-F14AAP-1B *5. Airspeed ..450 KIAS (altitude permitting) When start complete: 6. BACKUP IGNITION switch ....7. ENG MODE SELECT switch .
  • Page 74 NAVAIR 01-F14AAP-1B F110-GE-400 ENGINE DATE: NOVEMBER 1988 DATA BASIS: FLIGHT TEST NOTES WINDMILL RESTARTS SHOULD BE PERFORMED IN SEC- ONDARY MODE. SECONDARY MODE PROVIDES HIGHER WINDMILLING RPM 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.
  • Page 75 NAVAIR 01-F14AAP-1B CROSSBLEED AIRSTART 1. Throttle (bad engine) ....2. FUEL SHUT OFF handle ... .
  • Page 76 NAVAIR 01-F14AAP-1B 13. Affected L or R AICS (LF2 left, LG2 right) cb ......Cycle If WING SWEEP advisory light is illumi-...
  • Page 77 NAVAIR 01-F14AAP-1B Note An overspeed condition in excess of 110 percent will result in momentary loss of rpm indication until N rpm falls below 110 ±.5 percent. EGT and FF indicators will continue to function normally. 4. Refer to Single-Engine Cruise Operations, page 181.
  • Page 78 NAVAIR 01-F14AAP-1B If WING SWEEP advisory light is illumi- nated, cycling L AICS cb (LF2) may cause unintentional wing sweep un- less WING SWEEP DRIVE NO. 1 (LE1) and WG SWP DR NO. 2/MANUV FLAP (LE2) cb’s are pulled. 4. Affected L or R AICS (LF2 left, LG2 right) cb .
  • Page 79 NAVAIR 01-F14AAP-1B 3. Stall warning is inoperative (engine overtemp warning still available) 4. No nozzle position indication. 5. No AB capability. 6. Decrease stall margin at low rpm. 7. 65- to 116-percent basic engine thrust available. 8. Main engine ignition continuously energized.
  • Page 80 NAVAIR 01-F14AAP-1B If WING SWEEP advisory light is illumi- nated, cycling L AICS (LF2) cb may cause unintentional wing sweep un- less WING SWEEP DRIVE NO. 1 (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 .
  • Page 81 NAVAIR 01-F14AAP-1B UNCOMMANDED ENGINE ACCELERATION — AIRBORNE (NO THROTTLE MOVEMENT) If the APC cutout switch is shorted, attempting to disengage auto throttles using a breakout force of greater than 11 pounds or via the APC cutout switch (CAGE/SEAM button) may not be effective.
  • Page 82 NAVAIR 01-F14AAP-1B Note D SEC mode transfer while in AB may result in pop stalls. Nonemergency manual selection of SEC mode air- borne should be performed in basic engine with the power set above 85 percent rpm. D If the fan speed limiter circuit has failed, engine rollback may occur with the selection of SEC mode.
  • Page 83 NAVAIR 01-F14AAP-1B STUCK OR JAMMED THROTTLES IN AFTERBURNER 1. L ENG or R ENG MODE ....2. Apply maximum inboard force on throttles and retard as required.
  • Page 84 NAVAIR 01-F14AAP-1B AICS MALFUNCTION RAMPS LIGHT/INLET LIGHT *1. Avoid abrupt throttle movements. *2. Decelerate to below 1.2 IMN. *3. Affected INLET RAMPS switch ..STOW Note A RAMPS light should always be ac- companied by an INLET light when the LDG GEAR handle is UP.
  • Page 85 NAVAIR 01-F14AAP-1B Note Pulling the AICS cb while airborne may 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.
  • Page 86 NAVAIR 01-F14AAP-1B Note Pulling the AICS cb while airborne may 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.
  • Page 87 NAVAIR 01-F14AAP-1B INLET ICE LIGHT 1. ENG/PROBE ANTI-ICE switch ..ORIDE/ON When clear of known icing conditions: 2. ENG/PROBE ANTI-ICE switch ..AUTO/OFF Ice may form on inlet and ramp sur-...
  • Page 88 NAVAIR 01-F14AAP-1B L OR R OIL HOT LIGHT CAUTION Illumination of an OIL HOT caution light may be an Indication of above- normal gearbox scavenge oil tempera- ture or high supply temperature. Continuous engine operation will result in reduced gearbox life and lubrication degradation.
  • Page 89 NAVAIR 01-F14AAP-1B OIL PRESS LIGHT AND/OR ABNORMAL OIL PRESSURE 1. Throttle (affected engine) ... . . IDLE If oil pressure is below 15 psi, above 65 psi, or engine vibration: If shutdown is feasible: 2.
  • Page 90 NAVAIR 01-F14AAP-1B With the cb in and RATS operating, there is reduced thrust available for approach and use of afterburner may be required to arrest sink rate. CAUTION Circuit breaker 7C2 must be in prior to hook transition. Avoid icing conditions and rain with 7C2 pulled.
  • Page 91 NAVAIR 01-F14AAP-1B FIRE Index ELECTRICAL FIRE ........
  • Page 92 NAVAIR 01-F14AAP-1B...
  • Page 93 NAVAIR 01-F14AAP-1B L OR R FIRE LIGHT FIRE AND/OR FIRE IN FLIGHT *1. Throttle (affected engine) ....IDLE *2. AIR SOURCE pushbutton ....
  • Page 94 NAVAIR 01-F14AAP-1B ENGINE FIRE ON THE GROUND PILOT *1. Both FUEL SHUT OFF handles ... Pull *2. Both throttles ......
  • Page 95 NAVAIR 01-F14AAP-1B ELECTRICAL FIRE *1. L and R generators ..... If uncommanded SAS or spoiler inputs are present: *2. PITCH, ROLL, and YAW STAB AUG switches .
  • Page 96 NAVAIR 01-F14AAP-1B 5. EMERG generator switch ... . . NORM 6. Land as soon as possible. CAUTION Do not operate engines on the ground without electrical power. Ground- cooling fans are shut off, causing hot...
  • Page 97 NAVAIR 01-F14AAP-1B FLIGHT CONTROLS Index ARI/SAS OUT LIGHT (WITH ROLL DGR, YAW DGR OR ARI DGR LIGHT ..... AUTOPILOT LIGHT .
  • Page 98 NAVAIR 01-F14AAP-1B Index (Cont.) RUDDER HARDOVER ......RUNAWAY STABILIZER TRIM ......
  • Page 99 NAVAIR 01-F14AAP-1B CONTROLLABILITY FLIGHT CONTROLS CHECK It is absolutely imperative that the aircrew thoroughly and safely evaluate the degraded handling character- istics of damaged or malfunctioning aircraft prior to continued flight and landing. This check does not take priority over existing emergency procedures.
  • Page 100 NAVAIR 01-F14AAP-1B emergency procedure(s) as necessary before beginning a controllability check. 1. Climb to 10,000 feet AGL minimum. 2. Obtain visual check if possible. 3. Decelerate gradually to 200 KIAS if feasible. 4. Dirty aircraft, one configuration change at a time, while flying straight and level.
  • Page 101 NAVAIR 01-F14AAP-1B 9. Fly simulated approach to evaluate lineup correc- tions, power changes, and waveoff/bolter perfor- mance, and flight characteristics. 10. For landing, use minimum safe control speed, but no slower than optimum AOA. 11. If performance and flight ... .
  • Page 102 NAVAIR 01-F14AAP-1B DFCS POWER ON RESET (POR) If controllability is unsuitable for landing approach due to complete loss of spoilers or other major flight control malfunction, consideration may be given to attempting a flight control computer reset in an at- tempt to regain adequate controllability for landing.
  • Page 103 NAVAIR 01-F14AAP-1B Observe PITCH SAS, ROLL DGR, YAW DGR, FCS CAUTION, ARI DGR, ARI/SAS OUT, SPOILERS, HZ TAIL AUTH, RUDDER AUTH, and AUTOPILOT caution lights illuminated. Note Attempt to reset cb’s 7B4, 7B5, and 7B6 simultaneously optimize DFCS power-up sequence.
  • Page 104 NAVAIR 01-F14AAP-1B Note D Minimize control stick inputs during or following MASTER RESET as this can result in the SPOILERS caution light with SPOILER CONTR cb’s pulled. D More than one MASTER RESET may be required to extinguish all caution lights.
  • Page 105 NAVAIR 01-F14AAP-1B UNCOMMANDED ROLL AND/OR YAW *1. If flap transition: FLAP handle ... . . Previous Position *2. Rudder and stick ..
  • Page 106 NAVAIR 01-F14AAP-1B Note SAS failure may cause uncommanded roll and/or yaw, even without illumina- tion of the associated lights. c. Spoiler malfunction d. Hardover rudder e. Structural damage. 10. Slow-fly aircraft to determine controllability at 10,000 feet AGL minimum. BINDING/JAMMED FLIGHT CONTROLS ON THE GROUND 1.
  • Page 107 NAVAIR 01-F14AAP-1B SPOILERS CAUTION LIGHT/SPOILER MALFUNCTION/SPOILER STUCK UP CAUTION If the current configuration is accept- able for landing, careful consideration should be given before depressing Master Reset when a spoiler actuator mechanical malfunction is suspected. A deployed spoiler that resulted from DFCS computers dropping off line is not considered a mechanical failure.
  • Page 108 NAVAIR 01-F14AAP-1B If failure remains/reoccurs: 2. Avoid abrupt lateral control movements and high roll rates. CAUTION With wings forward of 62_, excessive horizontal tail differential may cause severe structural damage. If spoiler(s) fail down: 3. Perform controllability check procedure, page...
  • Page 109 NAVAIR 01-F14AAP-1B 4. Perform controllability check procedure, page 77, using maneuvering flap/slat (preferred) or no-flap configuration only. Note If controllability is unsuitable for land- ing approach due to complete loss of spoilers, consideration may be given to attempting a power on reset in an at- tempt to regain at least one spoiler set.
  • Page 110 NAVAIR 01-F14AAP-1B Note If multiple failed-up spoiler panels re- sult in unsatisfactory handling quali- ties regardless of flap position, an at- tempt may be made to fail the panels down by removing power via the corre- sponding spoiler cb’s. This may take...
  • Page 111 NAVAIR 01-F14AAP-1B Note With cb’s 7G9 and 8C5 pulled, ground roll braking is not available. Reset on landing rollout if desired. OUTBOARD SPOILER MODULE MALFUNCTION An outboard spoiler module failure with flaps extended, below 180 KIAS, and with a combined hydraulic failure...
  • Page 112 NAVAIR 01-F14AAP-1B The following important equipment is inoperative: (1) Outboard spoilers (2) Flap and slat backup (3) ACL. 2. Evaluate flaps-down lateral control characteris- tics at safe altitude. If unacceptable: 3. Make flaps-up landing (No Flaps and No Slats Landing).
  • Page 113 NAVAIR 01-F14AAP-1B 5. Land as soon as practicable if aircraft is control- lable and minimum approach airspeed is within shipboard arresting gear limits. If asymmetry is so large as to make landing impossible or minimum safe approach speed is above shipboard ar- resting gear limits with no possible divert field available: 6.
  • Page 114 NAVAIR 01-F14AAP-1B Asymmetric slats may not be apparent until just before wing stall. Asymmetric slats can cause rapid rolloff above 15 units AOA. 12. If asymmetry has been corrected, land using 15 units AOA. 13. If asymmetry has not been corrected, flaps and...
  • Page 115 NAVAIR 01-F14AAP-1B AFTER LANDING/TAKEOFF FLAP TRANSITION REILLUMINATION AFTER ABOVE PROCEDURES 1. MASTER RESET ....Depress 2. If light is still illuminated, check FLAP handle and indicator position, then proceed with appropri- ate steps below.
  • Page 116 NAVAIR 01-F14AAP-1B Note If FLAP handle or flaps will not respond or FLAP light remains illuminated, refer Flap Slat Asymmetry procedures. FCS CAUTION LIGHT Note Verify maintenance file fault reporting acronyms (RIO) to troubleshoot sys- tem for maintenance debrief. 1. MASTER RESET pushbutton .
  • Page 117 NAVAIR 01-F14AAP-1B PITCH SAS LIGHT 1. MASTER RESET pushbutton ..Depress 2. If light remains illuminated ..No limitations CAUTION D The spoilers may be inoperative (ground roll braking) with a com- plete failure of the pitch computer.
  • Page 118 NAVAIR 01-F14AAP-1B ROLL DGR LIGHT, YAW DGR LIGHT AND/OR ARI DGR LIGHT 1. MASTER RESET pushbutton ..Depress 2. If light remains illuminated, aggressive maneu- vering should be terminated. 3. Remain below 0.93 IMN.
  • Page 119 NAVAIR 01-F14AAP-1B 4. Perform Controllability Check procedure. CAUTION D If spoilers are inoperative 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.
  • Page 120 NAVAIR 01-F14AAP-1B RUNAWAY STABILIZER TRIM 1. SPD BK/P-ROLL TRIM ENABLE (RA2) cb ..... . . Pull 2. Decelerate to below 300 KIAS.
  • Page 121 NAVAIR 01-F14AAP-1B AUTOPILOT LIGHT 1. MASTER RESET pushbutton ..Depress HZ TAIL AUTH LIGHT 1. MASTER RESET pushbutton ..Depress (10 seconds) If light remains illuminated above 400 KIAS/0.9 IMN: 2.
  • Page 122 NAVAIR 01-F14AAP-1B RUDDER AUTH LIGHT 1. MASTER RESET pushbutton ..Depress (10 seconds) 2. If light remains illuminated Above 250 KIAS, restrict rudder inputs to less than 10_ CAUTION D With rudder authority stops failed...
  • Page 123 NAVAIR 01-F14AAP-1B After completion of uncommanded roll/yaw procedures: 1. Confirm rudder hardover via cockpit indicator and/or RIO/wingman visual inspection. Note Restriction of authority, if any, of op- posing “good” rudder may be deter- mined by reference to the cockpit indicator.
  • Page 124 NAVAIR 01-F14AAP-1B If jettison is required, consideration should be given to keeping the wing stations symmetric and avoiding aft c.g. conditions. Note It is unknown what the fuel consump- tion will be in this configuration. There- fore, fuel quantity must be closely mo- nitored.
  • Page 125 NAVAIR 01-F14AAP-1B Prior to landing: Controllability of a rudder hardover air- borne is no indication of the ability to maintain directional control on deck. Upon touchdown, expect the aircraft to experience uncontrollable directional excursions potentially departing the landing area/runway. Note...
  • Page 126 NAVAIR 01-F14AAP-1B Asymmetric thrust limiter should only be disabled if required to assist/main- tain control. 9. Perform arrested landing. Use only opposing throttle for waveoff/ bolter. CAUTION If rudder pedal authority is restricted, nosewheel steering should not be en- gaged upon landing rollout.
  • Page 127 NAVAIR 01-F14AAP-1B If yaw rate is steady/increasing or spin arrow flashing or eyeball out g sensed: *5. Roll SAS — ON, Stick — Full into turn needle and aft. If recovery is indicated: *6. Controls ......
  • Page 128 NAVAIR 01-F14AAP-1B INVERTED DEPARTURE/SPIN *1. Stick ....Full Aft/Neutral Lateral Harness — LOCK *2. Throttles ......
  • Page 129 NAVAIR 01-F14AAP-1B WINGS SWEEP LIGHTS ADVISORY LIGHT ONLY No loss of normal control: 1. MASTER RESET ....Depress ADVISORY AND WARNING LIGHTS No auto or manual control: 1.
  • Page 130 NAVAIR 01-F14AAP-1B 106b...
  • Page 131 NAVAIR 01-F14AAP-1B UNSCHEDULED WING SWEEP 1. Emergency WING SWEEP handle ..... . Raise and Hold CAUTION Unscheduled wing sweep at superson- ic speed may cause structural damage.
  • Page 132 NAVAIR 01-F14AAP-1B ASYMMETRIC WING SWEEP With asymmetric wing-sweep emergency condition, divert field landing is preferable to CV landing at- tempt. See Asymmetric Wings Approach Airspeed chart for 14 or 15 units AOA with asymmetric wing configurations. CAUTION To preclude potential damage to air- craft, avoid all wing-sweep commands prior to performing steps 1 through 8.
  • Page 133 NAVAIR 01-F14AAP-1B 7. Confirm left and right wing position. Note Wing-sweep tape indicates actual right wing position. All other cockpit wing position indications may be unreliable, including wing-sweep handle position. Visually verify left wing position. If left wing is aft of 62_ spoiler cutout and right wing is at 20_, perform Asymmetric Wing Sweep Unac- ceptable for Landing procedure.
  • Page 134 NAVAIR 01-F14AAP-1B c. Landing gear ..... . Down d. Leave flaps as set until further determina- tions are completed. e. Slowly increase AOA to no more than 15 units (attempt to maintain 0°...
  • Page 135 NAVAIR 01-F14AAP-1B b. Flaps ....Lower incrementally to 20° to 25° CAUTION When flaps are set to greater than 25°, lateral pilot-induced oscillations are likely and may result in wingtip damage at touchdown and/or hard landings.
  • Page 136 NAVAIR 01-F14AAP-1B b. Approach airspeed ..14 Units AOA CAUTION Wing rock and wing stall may occur at 16 to 16-1/2 units AOA during flaps-up approaches. Rapid lateral stick inputs will result in pitch coupling. Excessive...
  • Page 137 NAVAIR 01-F14AAP-1B CAUTION Full spoiler authority will be required for landing with large wing-sweep asymmetry. Before attempting actual approach, trim away from forward wing (opposite stick forces) to ensure that maximum spoiler deflection is available. 7. Fly straight-in approach to arrested or normal landing.
  • Page 138 NAVAIR 01-F14AAP-1B Note D To reduce lateral stick force, the landing approach can be flown with rudder trim into the forward wing, allowing aircraft to yaw into the forward wing. Sideslip should be reduced with rudder just prior to touchdown.
  • Page 139 NAVAIR 01-F14AAP-1B Note Once spoiler operation is assessed, stick forces may be trimmed to reduce pilot workload during transit to field or CV. The use of lateral trim to reduce stick forces during actual approach and landing should be avoided as this reduces the spoiler deflection avail- able for roll control.
  • Page 140 NAVAIR 01-F14AAP-1B If spoilers are not operational: a. Emergency WING SWEEP handle ....Input a Small Aft Command 3. Note movement of left and right wings and attempt to regain wing-sweep asymmetry by using the following wing-sweep commands.
  • Page 141 NAVAIR 01-F14AAP-1B Note If right wing is jammed aft of spoiler cutout angle, matching left wing will re- sult in loss of spoiler control. If this re- duced lateral control is undesirable, left wing should be commanded just forward of spoiler cutout to regain spoiler control.
  • Page 142 NAVAIR 01-F14AAP-1B DATE: AUGUST 1986 DATA BASIS: FLIGHT TEST FLAPS UP APPROACH AIRSPEED (14 UNITS AOA) FLAPS/SLATS RETRACTED LANDING APPROACH AIRSPEEDS (15 UNITS AOA) MAIN FLAPS/SLATS EXTENDED: AUXILIARY FLAPS RETRACTED ASYMMETRIC WINGS APPROACH AIRSPEED...
  • Page 143 NAVAIR 01-F14AAP-1B CADC LIGHT 1. MASTER RESET ....Depress 2. CADC cb’s (LA2, LB2, LC2, LH2) ..
  • Page 144 NAVAIR 01-F14AAP-1B FUEL...
  • Page 145 NAVAIR 01-F14AAP-1B FUEL Index FUEL IMBALANCE/FUEL QUANTITY BALANCING ..FUEL LEAK ........
  • Page 146 NAVAIR 01-F14AAP-1B...
  • Page 147 NAVAIR 01-F14AAP-1B SEE IC # 32 L AND/OR R FUEL PRESS LIGHT(S) FUEL AND 10 SEC WARNING TONE 1. Both throttles ... . MIL Power or Less 2. Restore aircraft to 1.0g flight.
  • Page 148 NAVAIR 01-F14AAP-1B SEE IC # 32 If one light remains on:12 3. No afterburner above 15,000 feet. 4. Fuel distribution ....Monitor (balance if required) 5.
  • Page 149 NAVAIR 01-F14AAP-1B SEE IC # 32 Note The L or R FUEL PRESS light and/or warning tone will extinguish when the FUEL PRESS ADVSY CB is pulled. 7. Maintain cruise power or less. 8. Fuel distribution − monitor (balance if required).
  • Page 150 NAVAIR 01-F14AAP-1B SEE IC # 32 FUEL TRANSFER FAILURES CAUTION Wing and external fuel will not transfer with refuel probe switch in ALL EXTD. If probe extension required, select FUS EXTD to enable transfer. Note Fuel management panel will be inop- erative if FUEL MGT PLN cb (RC1) is out.
  • Page 151 NAVAIR 01-F14AAP-1B If external tanks fail to transfer or transfer slowly: Note Descending below freezing level may thaw possible frozen valves. 2. WING/EXT TRANS ....
  • Page 152 NAVAIR 01-F14AAP-1B CV arrestment, CV touch-and-go, or normal field landings with full or partial fuel in the external tanks are not autho- rized because of overload of the na- celle backup structure. Only minimum rate-of-descent landings (minimum sink rate) are authorized.
  • Page 153 NAVAIR 01-F14AAP-1B Pulling the fuel feed/dump circuit breaker (RD1) isolates the right and left fuel systems. It also deactivates the function of the feed switch, the auto- matic balance functions, and the fuel dump system. Should single engine operation subsequently be necessary, useable fuel will be limited to only what is available on the operating side.
  • Page 154 NAVAIR 01-F14AAP-1B Pulling the fuel feed/dump circuit breaker (RD1) isolates the right and left fuel systems. It also deactivates the function of the feed switch, the auto- matic balance functions, and the fuel dump system. Should single engine operation subsequently be necessary, useable fuel will be limited to only what is available on the operating side.
  • Page 155 NAVAIR 01-F14AAP-1B SEE IC # 32 FUEL IMBALANCE/FUEL QUANTITY BALANCING AB operation is not recommended with a fuel imbalance or with indications of venting fuel. Note Fuel quantity balancing is not required prior to completion of wing/external tank transfer or until one fuselage tape drops below 4,500 pounds.
  • Page 156 NAVAIR 01-F14AAP-1B SEE IC # 32 pounds. Overfilling is indicated by a quantity of 6,600 pounds or greater in the FWD/RT system or 6,200 pounds or greater in the AFT/LT system. If no venting is observed and/or the fuel imbalance is cor- rected with the fuel feed switch: 3.
  • Page 157 NAVAIR 01-F14AAP-1B HYDRAULIC Index BACKUP FLIGHT MODULE FAILURE ....BOTH COMBINED AND FLIGHT PRESSURE ZERO .......
  • Page 158 NAVAIR 01-F14AAP-1B...
  • Page 159 NAVAIR 01-F14AAP-1B COMBINED PRESSURE HYDRAULIC APPROXIMATELY 2,400 TO 2,600 PSI If hammering (cavitation) is experi- enced hydraulic system, component rupture is imminent, turn the hydraulic transfer pump switch (BIDI) — OFF. 1. HYD ISOL switch ..... . .
  • Page 160 NAVAIR 01-F14AAP-1B If WING SWEEP advisory light is illumi- nated, pulling L AICS (LF2) cb may cause unintentional wing sweep un- less WING SWEEP DRIVE NO. 1 (LE1) and WG SWP DR NO. 2/MANUV FLAP (LE2) cb’s are pulled. 5. L AICS cb .
  • Page 161 NAVAIR 01-F14AAP-1B COMBINED PRESSURE ZERO 1. HYD ISOL switch ..... . . 2. HYD TRANSFER PUMP switch ..
  • Page 162 NAVAIR 01-F14AAP-1B D An outboard spoiler module failure with flaps extended, below 180 KIAS, and with a combined failure rendering the inboard spoilers inop- erative, can result in asymmetric spoiler float such that the aircraft may not be flyable at normal ap- proach airspeeds.
  • Page 163 NAVAIR 01-F14AAP-1B CAUTION D Loss of combined pressure with landing flaps down may allow the auxiliary flaps to cycle causing mod- erate pitch oscillations. D Monitor remaining hydraulic system pressure since the MASTER CAU- TION and HYD PRESS lights will not illuminate if the remaining system fails.
  • Page 164 NAVAIR 01-F14AAP-1B h. Hook extend (emergency actuation available). i. Flaps slats (emergency actuation available). j. Landing gear (emergency actuation available). k. Wheelbrakes (emergency actuation available). l. Refuel probe (emergency actuation available if system fluid remains in return line). m. Auxiliary flaps.
  • Page 165 NAVAIR 01-F14AAP-1B After landing: 14. Do not taxi out of arresting gear. 15. Engines ....... .
  • Page 166 NAVAIR 01-F14AAP-1B 136b...
  • Page 167 NAVAIR 01-F14AAP-1B Note Pulling the AICS cb while airborne may 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.
  • Page 168 NAVAIR 01-F14AAP-1B FLIGHT PRESSURE ZERO 1. HYD TRANSFER PUMP switch ..SHUTOFF 2. Wing sweep ..... . .
  • Page 169 NAVAIR 01-F14AAP-1B The following important equipment is inoperative: a. One-half authority of SAS/ARI actuators in pitch, roll and yaw. b. ACLS. c. R AICS. d. Normal hook ....
  • Page 170 NAVAIR 01-F14AAP-1B D Do not attempt IMC or close night formation while in the LOW mode. D Operations of more than 8 minutes total in HIGH mode may fail the BFCM motor. The LOW mode should be selected as soon as practicable...
  • Page 171 NAVAIR 01-F14AAP-1B e. Hydraulic handpump. f. Landing gear (emergency actuation available). g. Hook extend (emergency actuation available). h. Refuel probe (emergency actuation available if system fluid remains in return line). i. Wheelbrakes (emergency actuation available). If in-flight refueling is required: 4.
  • Page 172 NAVAIR 01-F14AAP-1B Note Once engaged, the airspeed can safely be increased to 200 KIAS to improve the transfer rate. 8. EMERG FLT HYD switch ....
  • Page 173 NAVAIR 01-F14AAP-1B CAUTION D Waveoff performance from low pow- er settings is very poor. Carrying ex- tra speed during IMC approach will improve waveoff performance by permitting smooth rotation to 15 units AOA to break the rate of descent while the engines are accelerating.
  • Page 174 NAVAIR 01-F14AAP-1B After landing: 19. Do not taxi out of arresting gear. 20. Throttles .......
  • Page 175 NAVAIR 01-F14AAP-1B If accumulator cannot be recharged: 4. Make arrested landing as soon as practicable. 5. Parking brake ..Pull (to lock wheels). LAND/ LAND GEAR...
  • Page 176 NAVAIR 01-F14AAP-1B LAND/ LAND GEAR...
  • Page 177 NAVAIR 01-F14AAP-1B LANDING GEAR/LANDING Index AFT WING SWEEP LANDING ..... . . ARRESTING HOOK EMERGENCY DOWN ... .
  • Page 178 NAVAIR 01-F14AAP-1B...
  • Page 179 NAVAIR 01-F14AAP-1B LANDING GEAR LANDING GEAR/ MALFUNCTION LANDING 1. Remain below 280 KIAS. 2. Combined hydraulic pressure ..Check 3. If less than 3,000 psi, refer to combined hydrau- lic failure procedures.
  • Page 180 NAVAIR 01-F14AAP-1B A hyperextended main strut, whether caused by a broken piston or overex- tended piston barrel and/or main strut with a cocked wheel, will likely result in a combined hydraulic system failure while airborne, and a sheared strut upon touchdown.
  • Page 181 NAVAIR 01-F14AAP-1B LANDING GEAR INDICATES UNSAFE GEAR DOWN, TRANSITION LIGHT OUT 1. Transition light bulb ....Check (LTS TEST) CAUTION If associated with launch bar light, leave gear down and obtain visual check.
  • Page 182 NAVAIR 01-F14AAP-1B CAUTION During an airborne visual inspection of the main landing gear (even if the paint stripe across the drag brace knee pin appears to be straight), the possibility exists that the downlock actuator has failed and the gear may not be locked in the down position.
  • Page 183 NAVAIR 01-F14AAP-1B Failure to place the LDG GEAR handle to DN immediately after selecting UP may allow the main landing gear doors to receive the signal to close with the main gear struts extended, causing damage to the doors and inducing a possible combined hydraulic or brake system failure.
  • Page 184 NAVAIR 01-F14AAP-1B CAUTION D When landing with a nosegear un- safe down indication, anticipate possible nose landing gear col- lapse. This possibility shall be reduced by using the brake pedals to prevent rollback as the arresting gear reaches full extension and by setting the parking brake after the aircraft has stopped.
  • Page 185 NAVAIR 01-F14AAP-1B 3. Gear/sidebraces appear in place ..... Normal Landing If sidebraces are confirmed not in place: 4. Refer to Landing Gear Malfunction Emergency Landing Guide.
  • Page 186 NAVAIR 01-F14AAP-1B 3. Push LDG GEAR handle in hard, turn 90° clockwise, pull, and hold. 4. Gear position indication ....Check (12 seconds) 5. Make arrested landing if available.
  • Page 187 NAVAIR 01-F14AAP-1B If light is illuminated and hook is visually checked down:123 4. RAIN RPL/ANTI-ICE CONTR/ HK CONTR (7C2) cb .....
  • Page 188 NAVAIR 01-F14AAP-1B 5. Fly normal pattern and approach, on-speed, angle of attack, centerline, and meatball. Note Anticipate loss of meatball for a short period of time during the approach. Barricade stanchions may obscure the meatball. Upon engaging the barricade: 6. Throttles .
  • Page 189 NAVAIR 01-F14AAP-1B Complete loss of hydraulic fluid through the wheelbrake hydraulic lines will render the parking brake and nose- wheel steering ineffective. If brakes still inoperative: 4. HOOK ........
  • Page 190 NAVAIR 01-F14AAP-1B BLOWN TIRE LANDING CAUTION Do not allow aircraft to roll backward after the arrestment. The downlock ac- tuator may have been damaged by tire failure and rearward movement of the aircraft could cause the gear to collapse. 1. Obtain in-flight visual check if possible.
  • Page 191 NAVAIR 01-F14AAP-1B NO FLAPS AND NO SLATS LANDING 1. Gross weight. Reduce (weight consistent with existing runway length and conditions) 2. Flaps ........
  • Page 192 NAVAIR 01-F14AAP-1B CAUTION D Avoid slow approaches. Wing drop and increased sink rate may occur at 16.5 to 17.5 units AOA. D Aircrew should expect hot brakes following high-speed landings. Ap- plication of the parking brake could cause the brake assembly to fail and result in a brake failure.
  • Page 193 NAVAIR 01-F14AAP-1B 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) ALL DRAG INDEXES, 0_ FLAP, GEAR DOWN LANDING APPROACH AIRSPEED (15 UNITS) 162a Change 2 162a/(162b blank)
  • Page 194 NAVAIR 01-F14AAP-1B 162b...
  • Page 195 NAVAIR 01-F14AAP-1B AFT WING SWEEP LANDING Note CV arrestments are permitted with up to 40_ wing sweep; emergency barri- cade engagements are permitted with up to 35_ wing sweep. 1. Emergency WING SWEEP handle ....
  • Page 196 NAVAIR 01-F14AAP-1B If maneuvering flaps are used, ensure that maneuver flap thumbwheel is not actuated during the approach. 5. DLC and APC ....Do Not Engage 6.
  • Page 197 NAVAIR 01-F14AAP-1B Note Maximum airspeed for wheelbrake ap- plication is 165 KIAS at gross weight of 46,000 pounds and 145 KIAS at 51,000 pounds. LANDING WITH AFT HUNG ORDNANCE 1. Determine location of hung stores. Obtain visual check if possible.
  • Page 198 NAVAIR 01-F14AAP-1B Note Refer to Emergency Field Arrestment Guide maximum engagement speed (page 169). If arresting gear is not available: 10. If field arrestment is not available, spoiler brake ......
  • Page 199 NAVAIR 01-F14AAP-1B FIELD LANDING FINAL ARRESTING NO ARRESTING CONFIGURATION CONFIGURATION CARRIER LANDINGS GEAR AVAILABLE GEAR AVAILABLE NOTES NOTES NOTES COCKED NOSE LAND 1, 8, 11 ARRESTED 6, 8, 9, LAND 6, 9, 11, GEAR LANDING 11, 12, SIDE-BRACE NOT LAND...
  • Page 200 NAVAIR 01-F14AAP-1B MAXIMUM ENGAGING SPEED (KNOTS) (D) GROSS WEIGHT X 1,000 POUNDS LONG MAXIMUM FIELD OFF-CENTER TYPE OF LANDING ENGAGEMENT ARRESTING GEAR (FT) SHORT-FIELD LANDING (K) (L) ABORTED TAKEOFF (A) 51.8 69.8 E-28 E-28 (G) M-21 BAK-9 BAK-12 (H) DUAL...
  • Page 202 NAVAIR 01-F14AAP-1B...
  • Page 203 NAVAIR 01-F14AAP-1B SINGLE-ENGINE OPERATIONS Index SINGLE-ENGINE CRUISE OPERATIONS ... . . SINGLE-ENGINE FAILURE FIELD/CATAPULT LAUNCH/WAVEOFF ......
  • Page 204 NAVAIR 01-F14AAP-1B...
  • Page 205 NAVAIR 01-F14AAP-1B SINGLE-ENGINE SINGLE-ENGINE FAILURE FIELD/ OPERATIONS CATAPULT LAUNCH/ WAVEOFF *1. Set 10_ pitch attitude on the waterline (14 units AOA maximum). *2. Rudder ....
  • Page 206 NAVAIR 01-F14AAP-1B If after commencing final approach or in landing pattern:1 2. ATLS ......
  • Page 207 NAVAIR 01-F14AAP-1B 9. Check SAS ......10. If combined pressure zero ......
  • Page 208 NAVAIR 01-F14AAP-1B 15. Final approach airspeed: a. DLC engaged ....15 Units AOA b. DLC stowed ....
  • Page 209 NAVAIR 01-F14AAP-1B If divert not possible: Engine thrust and thrust response can be severely degraded such that level flight cannot be maintained in the full- flap landing configuration. DO NOT configure for landing until the perfor- mance test has been accomplished.
  • Page 210 NAVAIR 01-F14AAP-1B Note Climb performance will improve by 20 feet in 30-second climb for every 1,000-pound gross weight reduction. Minimum performance criteria is based on optimum conditions (day, VMC, steady deck, experienced aircrew, nor- mal wind over deck, etc.) and should be increased for degraded conditions based on judgment.
  • Page 211 NAVAIR 01-F14AAP-1B If hammering (cavitation) is experi- enced in the hydraulic system, compo- nent rupture is imminent. Turn the HYD TRANSFER PUMP switch (BIDI) OFF. 8. External stores ....
  • Page 212 NAVAIR 01-F14AAP-1B If combined pressure is zero, do not re- turn to auto (low) mode once module is selected on. If module is shut off after operation commences, it may not re- start. 18. For landing pattern, use 10 units AOA for pattern airspeed and do not attempt turns greater than 20°...
  • Page 213 NAVAIR 01-F14AAP-1B Note Bolters should be conducted by rotat- ing to 10_ pitch attitude not to exceed 14 units AOA. SINGLE-ENGINE CRUISE OPERATIONS 1. FUEL SHUT OFF handle (inoperative engine) ... . .
  • Page 214 NAVAIR 01-F14AAP-1B CAUTION An increase in fuel quantity on the in- operative engine side indicates 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...
  • Page 215 NAVAIR 01-F14AAP-1B...
  • Page 216 NAVAIR 01-F14AAP-1B...
  • Page 217 NAVAIR 01-F14AAP-1B TAKEOFF Index ABORTED TAKEOFF ....... BLOWN TIRE DURING TAKEOFF .
  • Page 218 NAVAIR 01-F14AAP-1B...
  • Page 219 NAVAIR 01-F14AAP-1B ABORTED TAKEOFF TAKEOFF *1. Throttles ......IDLE *2. Speedbrakes .
  • Page 220 NAVAIR 01-F14AAP-1B BLOWN TIRE DURING TAKEOFF TAKEOFF ABORTED OR AFTER LANDING TOUCHDOWN *1. Nosewheel steering ....Engaged *2. ANTI SKID SPOILER BK ..

  • Page 221: Table Of Contents

    NAVAIR 01-F14AAP-1B BINGO Note During descent with engines in PRI mode, advancing throttle(s) slightly to partially closed nozzle(s) will increase range. Drag Table ........
  • Page 222 NAVAIR 01-F14AAP-1B...
  • Page 223 NAVAIR 01-F14AAP-1B DRAG TABLE DRAG INDEX STORE STATION(S) (PER STATION) OPEN AIM−7 CAVITIES (CLEAN) 3, 4, 5, 6 5 (TOTAL) AIM−7 3, 6/5, 4 2, 2/2, 2 AIM−7 1B, 8B 6, 6 AIM−9 1, 8 8, 8 AIM−54 3, 4...
  • Page 224 NAVAIR 01-F14AAP-1B DRAG TABLE DRAG INDEX STORE STATIONS (PER STATION) MK 20/ROCKEYE/ 3, 6 OBU−99/100 4, 5 CBU−78 GATOR 3, 6 4, 5 CBU−59 APAM 3, 6 4, 5 TALD 3, 4, 5, 6 EXTERNAL FUEL TANK 2, 7 9, 9...
  • Page 225 NAVAIR 01-F14AAP-1B WEIGHT TABLE POUNDS STORE PER STORE 20 MM AMMUNITION LB/ROUND AIM−9 AIM−7 AIM−54 1,000 TARPS POD 1,750 AIM−54 RAIL/LAUNCHER AIM−54 RAIL FAIRINGS (COMBINED) MULTIPURPOSE PYLON (PAIR) AIM−54 ADAPTER/LAUNCHER AIM−7 ADAPTER/LAUNCHER AIM−9 ADAPTER/LAUNCHER AIM−9 LAUNCHER (1a, 8a) BRU−32/ADU−703A/A BRU−42 (ITER) MK 76 (3 BOMBS) MK 82/BSU−33 (NTP)
  • Page 226 NAVAIR 01-F14AAP-1B 190d...

  • Page 227: Gear Up/Flaps Up (48,000) - Two Engines

    NAVAIR 01-F14AAP-1B GEAR UP BINGO 48,000 lb FLAPS UP TWIN ENG DATE: SEPTEMBER 1987 DATA BASIS: ESTIMATED BASED ON FLIGHT TEST INITIAL ALTITUDE: SEA LEVEL CLIMB CRUISE DESCEND SEA LEVEL CRUISE FUEL REQ DIST (nmi) DIST (nmi) (lbs) INBD MACH...

  • Page 228: Gear Up/Flaps Down (48,000) - Two Engines

    NAVAIR 01-F14AAP-1B GEAR UP BINGO 48,000 lb FLAPS DOWN TWIN ENG DATE: SEPTEMBER 1987 DATA BASIS: ESTIMATED BASED ON FLIGHT TEST INITIAL ALTITUDE: SEA LEVEL CLIMB CRUISE DESCEND SEA LEVEL CRUISE FUEL REQ DIST (nmi) DIST (nmi) (lbs) INBD MACH...

  • Page 229: Gear Down/Flaps Up (48,000) - Two Engines

    NAVAIR 01-F14AAP-1B GEAR DOWN BINGO 48,000 lb FLAPS UP TWIN ENG DATE: SEPTEMBER 1987 DATA BASIS: ESTIMATED BASED ON FLIGHT TEST INITIAL ALTITUDE: SEA LEVEL CLIMB CRUISE DESCEND SEA LEVEL CRUISE FUEL REQ DIST (nmi) DIST (nmi) (lbs) INBD MACH...

  • Page 230: Gear Down/Flaps Down (48,000) - Two Engines

    NAVAIR 01-F14AAP-1B GEAR DOWN BINGO 48,000 lb FLAPS DOWN TWIN ENG DATE: SEPTEMBER 1987 DATA BASIS: ESTIMATED BASED ON FLIGHT TEST INITIAL ALTITUDE: SEA LEVEL CLIMB CRUISE DESCEND SEA LEVEL CRUISE FUEL REQ DIST (nmi) DIST (nmi) (lbs) INBD MACH...

  • Page 231: Gear Up/Flaps Up (48,000) - Single Engine

    NAVAIR 01–F14AAP–1B NAVAIR 01-F14AAP-1B GEAR UP 48,000 lb BINGO FLAPS UP SINGLE ENG DATE: SEPTEMBER 1987 N1 = WINDMILLING DATA BASIS: ESTIMATED N2 = 0 RPM BASED ON FLIGHT TEST INITIAL ALTITUDE: SEA LEVEL CLIMB CRUISE DESCEND SEA LEVEL CRUISE...

  • Page 232: Gear Up/Flaps Down (48,000) - Single Engine

    NAVAIR 01-F14AAP-1B NAVAIR 01–F14AAP–1B GEAR UP 48,000 lb BINGO FLAPS DOWN SINGLE ENG DATE: SEPTEMBER 1987 N1 = WINDMILLING DATA BASIS: ESTIMATED N2 = 0 RPM BASED ON FLIGHT TEST INITIAL ALTITUDE: SEA LEVEL MACH MACH FUEL REQ MACH INBD...

  • Page 233: Gear Down/Flaps Up (48,000) - Single Engine

    NAVAIR 01–F14AAP–1B NAVAIR 01-F14AAP-1B GEAR DOWN 48,000 lb BINGO FLAPS UP SINGLE ENG DATE: SEPTEMBER 1987 N1 = WINDMILLING DATA BASIS: ESTIMATED N2 = 0 RPM BASED ON FLIGHT TEST INITIAL ALTITUDE: SEA LEVEL CLIMB CRUISE DESCEND SEA LEVEL CRUISE...

  • Page 234: Gear Down/Flaps Down (48,000) - Single Engine

    NAVAIR 01-F14AAP-1B NAVAIR 01–F14AAP–1B GEAR DOWN 48,000 lb BINGO FLAPS DOWN SINGLE ENG DATE: SEPTEMBER 1987 N1 = WINDMILLING DATA BASIS: ESTIMATED N2 = 0 RPM BASED ON FLIGHT TEST INITIAL ALTITUDE: SEA LEVEL CLIMB CRUISE DESCEND SEA LEVEL CRUISE...

  • Page 235: Gear Up/Flaps Up - Wings 68_ (48,000) - Two Engines

    NAVAIR 01-F14AAP-1B GEAR UP BINGO 48,000 lb FLAPS UP TWIN ENG WINGS = 68_ DATE: SEPTEMBER 1987 DATA BASIS: ESTIMATED BASED ON FLIGHT TEST INITIAL ALTITUDE: SEA LEVEL SEA LEVEL CLIMB CRUISE DESCEND CRUISE INBOUND MACH MACH MACH DIST DIST...

  • Page 236: Gear Up/Flaps Up - Wings 68_ (48,000) - Single Engine

    NAVAIR 01-F14AAP-1B NAVAIR 01–F14AAP–1B GEAR UP 48,000 lb BINGO FLAPS UP SINGLE ENG WINGS = 68_ DATE: SEPTEMBER 1987 N1 = WINDMILLING DATA BASIS: ESTIMATED N2 = 0 RPM BASED ON FLIGHT TEST INITIAL ALTITUDE: SEA LEVEL SEA LEVEL CLIMB...

  • Page 237: Gear Up/Flaps Up (53,000) - Two Engines

    NAVAIR 01-F14AAP-1B GEAR UP BINGO 53,000 lb FLAPS UP TWIN ENG DATE: SEPTEMBER 1987 DATA BASIS: ESTIMATED BASED ON FLIGHT TEST INITIAL ALTITUDE: SEA LEVEL CLIMB CRUISE DESCEND SEA LEVEL CRUISE FUEL REQ DIST (nmi) DIST (nmi) (lbs) INBD MACH...

  • Page 238: Gear Up/Flaps Down (53,000) - Two Engines

    NAVAIR 01-F14AAP-1B GEAR UP BINGO 53,000 lb FLAPS DOWN TWIN ENG DATE: SEPTEMBER 1987 DATA BASIS: ESTIMATED BASED ON FLIGHT TEST INITIAL ALTITUDE: SEA LEVEL CLIMB CRUISE DESCEND SEA LEVEL CRUISE FUEL REQ DIST (nmi) DIST (nmi) (lbs) INBD MACH...

  • Page 239: Gear Down/Flaps Up (53,000) - Two Engines

    NAVAIR 01-F14AAP-1B GEAR DOWN BINGO 53,000 lb FLAPS UP TWIN ENG DATE: SEPTEMBER 1987 DATA BASIS: ESTIMATED BASED ON FLIGHT TEST INITIAL ALTITUDE: SEA LEVEL CLIMB CRUISE DESCEND SEA LEVEL CRUISE FUEL REQ DIST (nmi) DIST (nmi) (lbs) INBD MACH...

  • Page 240: Gear Down/Flaps Down (53,000) - Two Engines

    NAVAIR 01-F14AAP-1B GEAR DOWN BINGO 53,000 lb FLAPS DOWN TWIN ENG DATE: SEPTEMBER 1987 DATA BASIS: ESTIMATED BASED ON FLIGHT TEST INITIAL ALTITUDE: SEA LEVEL CLIMB CRUISE DESCEND SEA LEVEL CRUISE FUEL REQ DIST (nmi) DIST (nmi) (lbs) INBD MACH...

  • Page 241: Gear Up/Flaps Up - Wings 68

    NAVAIR 01-F14AAP-1B BINGO GEAR UP 53,000 lb FLAPS UP TWIN ENG WINGS = 68_ DATE: SEPTEMBER 1987 DATA BASIS: ESTIMATED BASED ON FLIGHT TEST INITIAL ALTITUDE: SEA LEVEL SEA LEVEL CLIMB CRUISE DESCEND CRUISE INBOUND MACH MACH MACH DIST DIST...
  • Page 242 NAVAIR 01-F14AAP-1B EXTENDED GEAR UP 48,000 lb RANGE BINGO FLAPS UP TWIN ENG DESCEND FUEL REQ (lb) FUEL REQ (lb) DISTANCE (nmi) INBD 100KT 100KT 100KT DIST DIST CLIMB CLIMB HEAD HEAD WIND HEAD KCAS (nmi) MACH WIND WIND 0.745...
  • Page 243 NAVAIR 01-F14AAP-1B GEAR UP BINGO 53,000 lb FLAPS UP TWIN ENG WINGS = 68_ DATE: SEPTEMBER 1987 DATA BASIS: ESTIMATED BASED ON FLIGHT TEST INITIAL ALTITUDE: SEA LEVEL SEA LEVEL CLIMB CRUISE DESCEND CRUISE INBOUND MACH MACH MACH DIST DIST...
  • Page 244 NAVAIR 01-F14AAP-1B...
  • Page 245 NAVAIR 01-F14AAP-1B REFERENCE DATA Administrative Brief ....... . . Airspeed Indicator Failure .
  • Page 246 NAVAIR 01-F14AAP-1B...

  • Page 247: Administrative Brief

    NAVAIR 01-F14AAP-1B Note A bracketed T [T] in a procedural step identi- fies items pertaining only to TARPS aircraft. ADMINISTRATIVE BRIEF The following items should be covered for each flight regard- less of the mission. 1. Event number 2. Launch/recovery times/recovery order 3.
  • Page 248 NAVAIR 01-F14AAP-1B EJECTION SEAT INSPECTION 1. Face curtain locking tab ....Up (locked) 2. Lower ejection handle ...
  • Page 249 NAVAIR 01-F14AAP-1B 17. Drogue slug shear pin ... . . Head Impressed 18. Top latch mechanism ..... .
  • Page 250 NAVAIR 01-F14AAP-1B 34. Raft release handles ....Note Type 35. Lapbelt restraint ..... . .

  • Page 251: Cockpit Procedures

    NAVAIR 01-F14AAP-1B COCKPIT PROCEDURES INTERIOR INSPECTION — PILOT NATOPS prohibits the attaching or storing of unauthorized equipment on or above the can- opy rails during CV launch or arrestment due to potential for missile hazard. 1. Harnessing ......
  • Page 252 NAVAIR 01-F14AAP-1B 20. THROTTLE MODE switch ....BOOST 21. L and R INLET RAMPS switches ..AUTO 22. ANTI SKID SPOILER BK switch .
  • Page 253 NAVAIR 01-F14AAP-1B 42. DISPLAYS panel ......43. ELEV LEAD knob ......
  • Page 254 NAVAIR 01-F14AAP-1B 56. CANOPY AIR DIFFUSER lever ..CABIN AIR 57. VIDEO CONTROL switch ....58. Storage case .
  • Page 255 NAVAIR 01-F14AAP-1B 24. DECM selector knob ..... . . 25. AN/ALE–47 DCDU, MODE/PWR switch ..
  • Page 256 NAVAIR 01-F14AAP-1B Note If wings are in OV SW, do not extend handle. 3. ICS ........
  • Page 257 NAVAIR 01-F14AAP-1B Failure of the EMERG STORES JETT push- button to illuminate during LTS check could indicate that the pushbutton light is burned out or that the test circuit is defective. If the switch is actuated, stores will jettison when weight is off wheels.
  • Page 258 NAVAIR 01-F14AAP-1B Flightcrews shall ensure that hands and for- eign objects are clear of front cockpit hand- holds and top of ejection seats and canopy sills to prevent personal injury and/or structural damage during canopy opening or closing sequence. Only minimum clearance is afforded when canopy is transitioning fore and aft.

  • Page 259: Engine Start - Pilot

    NAVAIR 01-F14AAP-1B PRESTART — RIO 1. Seat, ICS, and U/VHF foot switches ..Adjust 2. External power and air ..... .
  • Page 260 NAVAIR 01-F14AAP-1B CAUTION D If engine chugs and/or rpm hangup is encountered with one engine turning dur- ing normal ground start, monitor EGT for possible hot start. AIR SOURCE pushbut- ton should be set for the operating engine until rpm stabilizes at idle, then set to BOTH ENG.
  • Page 261 NAVAIR 01-F14AAP-1B Note Ensure combined and flight hydraulic pres- sures are zero prior to testing emergency flight hydraulic system to allow proper check of 300 psi priority valve. 6. ENG CRANK switch ... . .
  • Page 262 NAVAIR 01-F14AAP-1B Note During cold starts, oil pressure may exceed 65 psi. This pressure limit should not be exceeded for more than 1 minute. 7. Right throttle ... . .
  • Page 263 NAVAIR 01-F14AAP-1B Note D Loss of electrical power may result in smoke entering the cockpit via the ECS. 8. R GEN light .......
  • Page 264 NAVAIR 01-F14AAP-1B CAUTION If the transfer pump does not pressurize the combined system within 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.
  • Page 265 NAVAIR 01-F14AAP-1B POSTSTART — PILOT 1. STAB AUG switches ....All ON 2. MASTER TEST switch ... . .
  • Page 266 NAVAIR 01-F14AAP-1B d. R ENG MODE SELECT switch ... R ENG SEC light illuminates, RPM drop, right NOZ indicator pointer below zero. e. Advance R throttle to ensure engine response.
  • Page 267 NAVAIR 01-F14AAP-1B CAUTION If wings are not in oversweep, move the wings to 68° using wing sweep emergency handle in raised position. Then raise handle to full exten- sion and hold until HZ TAIL AUTH caution light goes out and OVER flag appears on wing sweep indicator.
  • Page 268 NAVAIR 01-F14AAP-1B Note An FCS CAUTION at this point probably indicates a PQVM fault due to a lack of pitch and roll attitude inputs from the IMU (DCP FAIL group will indicate IMU). This fault will not affect DFCS IBIT results and can be extin- guished with a MASTER RESET before or after, but not during OBC.
  • Page 269 NAVAIR 01-F14AAP-1B Increased suction around intakes during inlet ramp programming and the automatic move- ment of the horizontal stabilizers presents a FOD hazard and a potential for injury to ground personnel not clear of these areas. 21. Speedbrake switch ....
  • Page 270 NAVAIR 01-F14AAP-1B During night operations, aircraft with inoper- able tail and aft anticollision lights will not be visible from the rear quadrant even under opti- mum meteorological conditions, thus increas- ing midair potential. 30. Flaps and slats ......
  • Page 271 NAVAIR 01-F14AAP-1B Aircraft shall be considered down with PFCC, RFCC, or YFCC codes in the DCP FAIL group or with an inoperative DCP display. Initiation of OBC/IBIT with this condition will result in invalid IBIT indications. 37. MASTER TEST switch .
  • Page 272 NAVAIR 01-F14AAP-1B 50. MASTER RESET pushbutton ... . . Depress Note CV checklist resumes. 51. ANTI SKID SPOILER BK switch ..
  • Page 273 NAVAIR 01-F14AAP-1B 6. PTID power switch ......7. LIQ COOLING switch . . . AWG-9 or AWG-9/AIM-54...
  • Page 274 NAVAIR 01-F14AAP-1B c. Observe test completed on PTID. d. Altimeter ......Reset 19. CDNU .
  • Page 275 NAVAIR 01-F14AAP-1B c. PAN switch ....LEFT or RIGHT Observe exposure interval of 2.0 seconds, PAN go light illuminated, and frame counter for proper operation.
  • Page 276 NAVAIR 01-F14AAP-1B 31. Hand control panel ......32. AN/ALE-47 DCDU, MODE/PWR SWITCH STBY 33. CANOPY DEFOG-CABIN AIR lever .

  • Page 277: Final Checker (Aboard Cv)

    NAVAIR 01-F14AAP-1B FINAL CHECKER (ABOARD CV) 1. Hook ....DN on Director’s Signal Check RATS Advisory Light On, Then Up CAUTION Carrier operations with an inoperative RATS will increase wind-over-deck requirements.
  • Page 278 NAVAIR 01-F14AAP-1B TAXI — PILOT CAUTION Taxiing with the left engine secured is not authorized. Normal braking and nosewheel steering control will be lost if the hydraulic transfer pump (BIDI) fails while taxiing with the left engine secured. 1. Parking brake .
  • Page 279 NAVAIR 01-F14AAP-1B TAKEOFF CHECKLIST RIO CHALLENGE PILOT REPLY 1. “BRAKES” CHECK OK, ACCUMU- LATOR PRESSURE UP” 2. “FUEL TOTAL “NORMAL FEED, AUTO- TRANSFER DUMP OFF, lb” TRANSFER CHECKED, TOTAL WINGS/EXT AFT AND LEFT FORWARD AND RIGHT FEED TANKS FULL BINGO SET.
  • Page 280 NAVAIR 01-F14AAP-1B RIO CHALLENGE PILOT REPLY 10. “COMPASS, STANDBY “COMPASS SYNCHRO- NIZED, STANDBY GYRO GYRO, TURN ERECT, GOOD TURN NEEDLE, AND NEEDLE, ALTIMETER SET ALTIMETER” (LOCAL SETTING) ” CV — Approaching CAT on Director’s Signal 11. “WINGS” (visually “20°, AUTO, BOTH LIGHTS OUT”...
  • Page 281 NAVAIR 01-F14AAP-1B ASCENT CHECKLIST At level-off or 15,000 feet (whichever occurs first): 1. Cabin pressurization ..... . Check 2. Fuel transfer .
  • Page 282 NAVAIR 01-F14AAP-1B 14. DECM switch ......STBY 15. AN/ALE–47 DCDU, MODE/PWR SWITCH . . .

  • Page 283: Landing Checklist

    NAVAIR 01-F14AAP-1B Note Before reconnaissance system shutdown, run film leader to protect target imagery from inadvertent exposure during film download. 20. [T] FRAME switch ......

  • Page 284: Postlanding - Pilot

    NAVAIR 01-F14AAP-1B POSTLANDING — PILOT 1. Speedbrake switch ......2. ANTISKID SPOILER BK switch ... . .

  • Page 285: Postlanding - Rio

    NAVAIR 01-F14AAP-1B 16. EMERG generator switch ....17. Standby attitude gyro ..... .

  • Page 286: Hot Refueling Procedures

    NAVAIR 01-F14AAP-1B 18. Report ..... Ready for Shutdown After shutdown of both engines: 19. CANOPY handle ......

  • Page 287: Hot Switch Procedures

    NAVAIR 01-F14AAP-1B ON-DECK, MAINTENANCE TROUBLESHOOTING CAUTION To ensure a safe in-cockpit maintenance trou- bleshooting evolution, the following proce- dures should be used. 1. Parking brake ......

  • Page 288: In-Flight Refueling Checklist

    NAVAIR 01-F14AAP-1B 18. Ejection seats ......Armed 19. CANOPY handle ......

  • Page 289: Takeoff Speed And Ground Roll Distance, Flaps Up

    NAVAIR 01-F14AAP-1B WING = 20_ MILITARY POWER AIRCRAFT CONFIGURATION: ENGINES (2) F110-GE-400 ALL DRAG INDEXES HARD DRY RUNWAY 0_ FLAPS DATE: JANUARY 1990 GEAR DOWN DATA BASIS: ESTIMATED BASED ON FLIGHT TEST DISTANCE IN FEET PRESSURE ALTITUDE (FEET) HEAD- HEAD-...
  • Page 290 NAVAIR 01-F14AAP-1B WING SWEEP = 20_ MILITARY POWER CG = 6% AIRCRAFT CONFIGURATION: ENGINES (2) F110-GE-400 ALL DRAG INDEXES HARD DRY RUNWAY 35_ FLAPS DATE: JANUARY 1990 GEAR DOWN DATA BASIS: ESTIMATED BASED ON FLIGHT TEST DISTANCE IN FEET PRESSURE ALTITUDE...
  • Page 291 NAVAIR 01-F14AAP-1B WING SWEEP = 20_ MILITARY POWER CG = 16.2% AIRCRAFT CONFIGURATION: ENGINES (2) F110-GE-400 ALL DRAG INDEXES HARD DRY RUNWAY 35_ FLAPS DATE: JANUARY 1990 GEAR DOWN DATA BASIS: ESTIMATED BASED ON FLIGHT TEST DISTANCE IN FEET PRESSURE ALTITUDE...
  • Page 292 NAVAIR 01-F14AAP-1B ANGLE-OF-ATT FLIGHT CONDITION ACK UNITS CATAPULT (15 KNOTS EXCESS) 14.0 TRANSITION FROM CATAPULT 13.0 MILITARY POWER CLIMB ALL DRAG INDEXES SEA LEVEL COMBAT CEILING MAXIMUM POWER CLIMB ALL DRAG INDEXES SEA LEVEL COMBAT CEILING CRUISE AT ALTITUDES BELOW 20,000 FEET...

  • Page 293: Two-Engine Maximum Endurance On Station

    NAVAIR 01-F14AAP-1B FUEL REMAINING — POUNDS LANDING 4000 8000 12,000 16,000 20,000 WEIGHT ALT/SPEED ALT/SPEED ALT/SPEED ALT/SPEED ALT/SPEED TIME (MIN) TIME (MIN) TIME (MIN) TIME (MIN) TIME (MIN) 15,000/200 34,000/205 32,000/210 31,000/220 31,000/220 46,000 13,000/205 32,000/215 30,000/220 29,000/225 29,000/230 51,000...
  • Page 294 NAVAIR 01-F14AAP-1B FUEL REMAINING — POUNDS LANDING 4000 8000 12,000 16,000 20,000 WEIGHT ALT/SPEED ALT/SPEED ALT/SPEED ALT/SPEED ALT/SPEED TIME (MIN) TIME (MIN) TIME (MIN) TIME (MIN) TIME (MIN) 500/195 8,000/200 13,000/205 12,000/210 12,000/215 46,000 500/210 6,000/210 11,000/215 10,000/220 10,000/225 51,000...
  • Page 295 NAVAIR 01-F14AAP-1B DATE: SEPTEMBER 1987 FUEL GRADE: JP-5 DATA BASIS: FLIGHT TEST FUEL DENSITY: 6.8 lb/gal. ALL DRAG INDEXES, 35_ FLAP, GEAR DOWN EMERGENCY OPERATION (WING SWEEP LESS THAN OR EQUAL TO 50_) AIRSPEED CORRECTION TO BE ADDED TO DLC STOWED APPROACH SPEED...
  • Page 296 NAVAIR 01-F14AAP-1B EMERGENCY OPERATION (WING SPEED GREATER THAN 50_) AIRSPEED CORRECTION TO BE ADDED TO DCL STOWED APPROACH SPEED 15 UNITS 17 UNITS WING SWEEP (_) AOA (KIAS) AOA (KIAS) LANDING APPROACH AIRSPEED (15 UNITS AOA) (SHEET 2)
  • Page 297 NAVAIR 01-F14AAP-1B MAXIMUM BRAKING — HARD DRY RUNWAY WING = 20_ AIRCRAFT CONFIGURATION: ENGINES (2) F110-GE-400 ALL DRAG INDEXES IDLE POWER ALL DECELERATION DEVICES DATE: JANUARY 1990 FULL ANTISKID BRAKING DATA BASIS: ESTIMATED BASED 35_ FLAPS, GEAR DOWN ON FLIGHT TEST...
  • Page 298 NAVAIR 01-F14AAP-1B MAXIMUM BRAKING — HARD DRY RUNWAY WING = 20_ AIRCRAFT CONFIGURATION: ENGINES (2) F110-GE-400 ALL DRAG INDEXES IDLE POWER ALL DECELERATION DEVICES DATE: JANUARY 1990 FULL ANTISKID BRAKING DATA BASIS: ESTIMATED BASED 35_ FLAPS, GEAR DOWN ON FLIGHT TEST...
  • Page 299 NAVAIR 01-F14AAP-1B MAXIMUM BRAKING — HARD DRY RUNWAY WING = 20_ AIRCRAFT CONFIGURATION: ENGINES (2) F110-GE-400 ALL DRAG INDEXES IDLE POWER INBD SPOILERS SPEED BRAKES DATE: JANUARY 1990 FULL ANTISKID BRAKING DATA BASIS: ESTIMATED BASED 0_ FLAPS, GEAR DOWN ON FLIGHT TEST...
  • Page 300 NAVAIR 01-F14AAP-1B MAXIMUM BRAKING — HARD DRY RUNWAY WING = 20_ AIRCRAFT CONFIGURATION: ENGINES (2) F110-GE-400 ALL DRAG INDEXES IDLE POWER INBD SPOILERS, SPEED BRAKES DATE: JANUARY 1990 FULL ANTISKID BRAKING DATA BASIS: ESTIMATED BASED 35_ FLAPS, GEAR DOWN ON FLIGHT TEST...
  • Page 301 NAVAIR 01-F14AAP-1B CIRCUIT BREAKERS AND SERVICING DATA Index Ac Essential No. 1 Circuit Breaker Panel (Right Side) (Panel No. 5) ......
  • Page 302 NAVAIR 01-F14AAP-1B...
  • Page 303 NAVAIR 01-F14AAP-1B CIRCUIT BREAKERS ALPHANUMERIC INDEX AC ESS BUS NO. 2 FDR PH A AC ESS BUS NO. 2 FDR PH B AC ESS BUS NO. 2 FDR PH C ACM LT/SEAT ADJ/STEADY POS LT ACM PNL LT/INS SYNC ACM PNL PWR...
  • Page 304 NAVAIR 01-F14AAP-1B CIRCUIT BREAKERS ALPHANUMERIC INDEX AMC BIT/R DC TEST AMCS ENABLE AN/ALR-67 CONT AN/ARA-50 AN/ARA-50 AN/AWG-9 CMPTR PH A AN/AWG-9 CMPTR PH B AN/AWG-9 CMPTR PH C AN/AWG-9 PUMP PH A AN/AWG-9 PUMP PH B AN/AWG-9 PUMP PH C...
  • Page 305 NAVAIR 01-F14AAP-1B CIRCUIT BREAKERS ALPHANUMERIC INDEX ARA-63 ILS PH A ARA-63 ILS PH B ARA-63 ILS PH C ARC-159 NO. 1 ARC-159 NO. 2 ARMT GAS INGEST PWR AS/ARA–48 ANT ASW-27 (AC) ASW-27 (DC)/DDI AUTO PITCH DRIVE TRIM AUTO THROT AC...
  • Page 306 NAVAIR 01-F14AAP-1B CIRCUIT BREAKERS ALPHANUMERIC INDEX CHAN 1 CADC PH C CHAN 2 CADC COMB HYD PRESS IND CONTR/DISPL SUBSYS CONTR/DISPLAY PH A CONTR/DISPLAY PH B CONTR/DISPLAY PH C COUNTING ACCEL/TARPS/FEMS CSDC CSDC PH A CSDC PH B CSDC PH C DC ESS NO.
  • Page 307 NAVAIR 01-F14AAP-1B CIRCUIT BREAKERS ALPHANUMERIC INDEX EMERG GEN CONTR ENG AFT FAULT ENG ANTI-ICE/VALVES ENG L OIL PRESS ENG OIL COOL ENG/PROBE/ANTI-ICE ENG R OIL PRESS 7F10 ENG STALL TONE ENG STALL WARN LT ENG START EXHAUST NOZZLE/R ENG AFT CONT...
  • Page 308 NAVAIR 01-F14AAP-1B CIRCUIT BREAKERS ALPHANUMERIC INDEX FUEL TRANS ORIDE FUEL VENT VALVE GEN L CAUTION GEN R CAUTION GND PWR/COOLING INTERLK GND ROLL BRAKING/SPOILER POS IND GND TEST GUN ARMED POWER GUN CLR/GUN CONTR PWR DC GUN CONTR PWR AC...
  • Page 309 NAVAIR 01-F14AAP-1B CIRCUIT BREAKERS ALPHANUMERIC INDEX IFF A/A DC ILS ARA-63 DC ILS ARA-63 PH A ILS ARA-63 PH B ILS ARA-63 PH C INBD SPOILER CONTR INS SYNC/ACM PNL LT INST BUS FDR INST LT INTEG TRIM AC INTEG TRIM DC INTRF BLANKER INTRPT FREE DC BUS FDR NO.
  • Page 310 NAVAIR 01-F14AAP-1B CIRCUIT BREAKERS ALPHANUMERIC INDEX L PH C TEST/P. ROLL TRIM L PITOT STATIC HTR L TIT IND LCH BAR NLG STRUT ADVSY 2H10 LIQUID COOLING CONTR AC LIQUID COOLING CONTR DC MACH TRIM AC MACH TRIM DC MANUV FLAP/WG SWP DRIVE NO. 2...
  • Page 311 NAVAIR 01-F14AAP-1B CIRCUIT BREAKERS ALPHANUMERIC INDEX NOSE WHEEL STEER/AFCS NVG FLOOD LT OIL L HOT/BLEED AIR OIL R HOT OUTBD SPOILER CONTR OUTBD SPOILER PUMP OXY/BINGO CAUTION OXY QTY IND PEDAL SHAKER/ALPHA COMP P. ROLL TRIM/L PH A TEST P. ROLL TRIM/L PH B TEST P.
  • Page 312 NAVAIR 01-F14AAP-1B CIRCUIT BREAKERS ALPHANUMERIC INDEX R AICS LKUP PWR/ANTI-SKID R AICS RAMP STOW R AIM-7 BATT ARM R DC TEST/AMC BIT RAIN REPL/ANTI-ICE CONTR/HKCONTR RECON ECS CONT DC RECON ECS CONT AC RECON HTR PWR PH A RECON HTR PWR PH B...
  • Page 313 NAVAIR 01-F14AAP-1B CIRCUIT BREAKERS ALPHANUMERIC INDEX ROLL B DC RUDDER/TAIL/FLAP IND RUDDER TRIM/L DC TEST RUDDER TRIM PH A RUDDER TRIM PH B RUDDER TRIM PH C SEAT ADJ/ACM LT/STEADY POS LT SEMI REG PWR SUP PH A SEMI REG PWR SUP PH B...
  • Page 314 NAVAIR 01-F14AAP-1B CIRCUIT BREAKERS ALPHANUMERIC INDEX STA 3/6 AIM-7/AIM-54 PUMP PH B 1 D7 STA 3/6 AIM-7/AIM-54 PUMP PH C STA 4/5 AIM-7 PH A STA 4/5 AIM-7 PH B STA 4/5 AIM-7 PH C STA 5, 6, & 7 REL PWR A STA 5, 6, &...
  • Page 315 NAVAIR 01-F14AAP-1B CIRCUIT BREAKERS ALPHANUMERIC INDEX UTILITY LT VDI PH A VDI PH B VDI PH C WG SWP DR NO. 2/MANUV FLAP WHEELS POS IND WHITE FLOOD LT WING POS IND AC WING POS IND DC WING SWEEP DRIVE NO. 1...
  • Page 316 NAVAIR 01-F14AAP-1B Change 3...
  • Page 317 NAVAIR 01-F14AAP-1B AC LEFT MAIN CIRCUIT BREAKER PANEL (LEFT AFT) (PANEL NO. 1 — UPPER SEGMENT)
  • Page 318 NAVAIR 01-F14AAP-1B AC LEFT MAIN CIRCUIT BREAKER PANEL (LEFT AFT) (PANEL NO. 1 — LOWER SEGMENT)
  • Page 319 NAVAIR 01-F14AAP-1B AC RIGHT MAIN CIRCUIT BREAKER PANEL (LEFT AFT) (PANEL NO. 2)
  • Page 320 NAVAIR 01-F14AAP-1B AC ESSENTIAL NO. 2 PHASE A CIRCUIT BREAKER PANEL (LEFT) (PANEL NO. 3)
  • Page 321 NAVAIR 01-F14AAP-1B AC ESSENTIAL NO. 2 PHASE B AND C CIRCUIT BREAKER PANEL (LEFT) (PANEL NO. 4)
  • Page 322 NAVAIR 01-F14AAP-1B AC ESSENTIAL NO. 1 CIRCUIT BREAKER PANEL (RIGHT SIDE) (PANEL NO. 5) Change 2...
  • Page 323 NAVAIR 01-F14AAP-1B DC ESSENTIAL NO. 1 CIRCUIT BREAKER PANEL (RIGHT SIDE) (PANEL NO. 6)
  • Page 324 NAVAIR 01-F14AAP-1B DC ESSENTIAL NO. 2 CIRCUIT BREAKER PANEL (RIGHT AFT) (PANEL NO. 7 — UPPER SEGMENT) Change 2...
  • Page 325 NAVAIR 01-F14AAP-1B DC ESSENTIAL NO. 2 CIRCUIT BREAKER PANEL (RIGHT AFT) (PANEL NO. 7 — LOWER SEGMENT)
  • Page 326 NAVAIR 01-F14AAP-1B DC MAIN CIRCUIT BREAKER PANEL (RIGHT AFT) (PANEL NO. 8 — UPPER SEGMENT)
  • Page 327 NAVAIR 01-F14AAP-1B DC MAIN CIRCUIT BREAKER PANEL (RIGHT AFT) (PANEL NO. 8 — LOWER SEGMENT)
  • Page 328 NAVAIR 01-F14AAP-1B SERVICING DATA GROUND REFUELING Single-point refueling is through a standard pressure refueling receptacle on the forward right fuselage. Refueling is con- trolled by two selector valves and the vent pressure gauge adja- cent to the refueling receptacle. When aircraft fuel tanks are full, fueling stops automatically.
  • Page 329 NAVAIR 01-F14AAP-1B Note D If the aircraft is serviced with JP-4 fuel, the main fuel-control fuel-grade (specific gravity adjustment) selector on each engine should be reset to the JP-4 position. If the aircraft is being regularly serviced with JP-8 or JP-5...
  • Page 330 NAVAIR 01-F14AAP-1B Do not overservice oil storage tank. Overserv- icing can cause scavenge pump failure and subsequent engine failure. Note Engine oil quantity must be checked within 30 minutes after engine shutdown, otherwise, run engine at 80 percent rpm or greater for 10 min- utes to ensure proper servicing.
  • Page 332 NAVAIR 01-F14AAP-1B DOD IFR DESIGNATION NATO COMMERCIAL SUPPLEMENT SPECIFICATION CODE EQUIVALENT ITEM REMARKS CODE FUEL MIL-T-5624 (JP-5) F-44 NONE JP-5 SELECTOR ON MAIN ENG. CONT. SHALL BE SET TO JP5, JP4, OR MIL-T-5624 (JP-4) F-40 JET B JP-4 DENSITY OF OTHER...
  • Page 333 NAVAIR 01-F14AAP-1B PNEUMATIC PRESSURE SYSTEM PRESSURE EMERGENCY LANDING GEAR 3000 PSI AT 70_ F COMBINED HYDRAULIC 1800 PSI AT 70_ F FLIGHT HYDRAULIC 1800 PSI AT 70_ F CANOPY NORMAL (1200 PSI MINIMUM) 3000 PSI AT 70_ F CANOPY AUXILIARY (800 PSI MINIMUM)
  • Page 334 NAVAIR 01-F14AAP-1B AIRCRAFT SERVICING DATA (SHEET 3)
  • Page 335 NAVAIR 01-F14AAP-1B AIRCRAFT SERVICING DATA (SHEET 4)
  • Page 336 NAVAIR 01-F14AAP-1B AIRCRAFT SERVICING DATA (SHEET 5) Change 2...
  • Page 337 NAVAIR 01-F14AAP-1B AIRCRAFT SERVICING DATA (SHEET 6)
  • Page 338 NAVAIR 01-F14AAP-1B AIRCRAFT SERVICING DATA (SHEET 7)
  • Page 339 NAVAIR 01-F14AAP-1B AIRCRAFT SERVICING DATA (SHEET 8) 299/(300 blank)
  • Page 340 NAVAIR 01-F14AAP-1B...
  • Page 341 CARD 1 of 10 DFCS IN FLIGHT FAULT MATRIX CARDS OFP 4.4 How to use the DFCS IN FLIGHT FAULT MATRIX: These cards are organized according to the relative level of severity" of the six individual DFCS caution lights six pack". When a DFCS related failure is detected in flight, the aircrew can resolve the cause of that failure by identifying the caution/advisory lights illuminated and the AFC acronyms Ç...
  • Page 342 CARD 2 of 10 DFCS IN FLIGHT FAULT MATRIX CARDS OFP 4.4 The DFCS IN FLIGHT FAULT MATRIX cards are organized as follows: How to use the DFCS IN FLIGHT FAULT MATRIX (CARD 1/2 of 10) DFCS IN FLIGHT FAULT MATRIX ARI/SAS OUT (CARD 3/4 of 10) DFCS IN FLIGHT FAULT MATRIX ARI DGR (CARD 5/6 of 10)
  • Page 343 CARD 3 of 10 DFCS IN FLIGHT FAULT MATRIX CARDS OFP 4.4 ARI SAS/OUT LIGHT(S) ACRO(S) CONFIG FAILURE CAUSE(S) FUNCTIONALITY DEGRADE DCP FLT CODE(S) ARI/SAS OUT PC, RC, PA or UA 1. Internal DFCC test failure. 1. Total DFCS failure. Pitch, 1.
  • Page 344 CARD 4 of 10 DFCS IN FLIGHT FAULT MATRIX CARDS OFP 4.4 ARI SAS/OUT LIGHT(S) ACRO(S) CONFIG FAILURE CAUSE(S) FUNCTIONALITY DEGRADE DCP FLT CODE(S) ARI/SAS OUT 1. Mach 2F. 1. Pitch SAS inop. 1. AD01, 03, 04, ARI DGR Roll SAS/ARI inop. 05 &...
  • Page 345 CARD 5 of 10 DFCS IN FLIGHT FAULT MATRIX CARDS OFP 4.4 ARI DGR LIGHT(S) ACRO(S) CONFIG FAILURE CAUSE(S) FUNCTIONALITY DEGRADED DCP FLT CODE(S) ARI DGR PS, YA, PA or UA 1. YAW A computer fault. 1. Yaw SAS, ARI, SR half auth. 1.
  • Page 346 CARD 6 of 10 DFCS IN FLIGHT FAULT MATRIX CARDS OFP 4.4 ARI DGR LIGHT(S) ACRO(S) CONFIG FAILURE CAUSE(S) FUNCTIONALITY DEGRADED DCP FLT CODE(S) ARI DGR PA, PC, PA or UA 1. PITCH B computer fault. Pitch SAS half auth. PC##.
  • Page 347 CARD 7 of 10 DFCS IN FLIGHT FAULT MATRIX CARDS OFP 4.4 ROLL DGR LIGHT(S) ACRO(S) CONFIG FAILURE CAUSE(S) FUNCTIONALITY DEGRADED DCP FLT CODE(S) ROLL DGR 1. AICS cross check (> 600 kts or 1−2. Pitch SAS inop. 1−2. AICX. invalid Qbar).
  • Page 348 CARD 8 of 10 DFCS IN FLIGHT FAULT MATRIX CARDS OFP 4.4 FCS CAUTION LIGHT(S) ACRO(S) CONFIG FAILURE CAUSE(S) FUNCTIONALITY DEGRADE DCP FLT CODE(S) FCS CAUTION PS, RS PA or UA 1. IMU related fault. 1. No effect, pitch and roll axes 1.
  • Page 349 CARD 9 of 10 DFCS IN FLIGHT FAULT MATRIX CARDS OFP 4.4 LIGHT(S) ACRO(S) CONFIG FAILURE CAUSE(S) FUNCTIONALITY DEGRADED DCP FLT CODE(S) SPOILERS PA or UA 1. Outboard spoiler(s) fault. Affected L/R spoiler(s) inop. 1. SP3L, SP3R, SP4L, &/or SP4R PA or UA 1.
  • Page 350 CARD 10 of 10 DFCS IN FLIGHT FAULT MATRIX CARDS OFP 4.4 LIGHT(S) ACRO(S) CONFIG FAILURE CAUSE(S) FUNCTIONALITY DEGRADED DCP FLT CODE(S) – PS, RS, PA or UA 1. Weight−on−wheels 2F. Autopilot inop. Ground roll 1. DCP inop braking inop. DCP display (WOW# codes blank on deck.
  • Page 351 NAVAIR 01−F14AAP−1B F−14 DFCS UP/DOWN STATUS CARDS FLEET OFP 4.4 Card 1 of 2 F−14 DFCS SELF−TEST AND FAULT REPORTING DFCS self−tests include: a power−up BIT (PBIT), automatic−BIT (ABIT), and initiated−BIT (IBIT) modes. DFCS self−tests PBIT and ABIT are together referred to as the operational flight program (OFP) self−test mode.
  • Page 352 NAVAIR 01−F14AAP−1B F−14 DFCS UP/DOWNSTATUS CARDS FLEET OFP 4.4 Card 2 of 2 FAULT CODES DFCS UP/DOWN STATUS TABLE IBIT FAILURE INDICATION FUNCTIONS LOST 115V Aircraft 115 VAC power supply fault. Computer problems 28DC Aircraft 28 VDC power supply fault.
  • Page 353 NAVAIR 01−F14AAP−1B SAR ON SCENE COMMANDER CHECKLIST 1. Maintain sight Do not fly through any cloud layers. Parachute fall rate is about 1000 ft/min. 2. Squak 7700 3. Switch guard (243.0) for initial call Mayday, Mayday, Mayday." This is _____ on guard."...
  • Page 354 NAVAIR 01−F14AAP−1B Change 2...
  • Page 355 TO USE, DETERMINE WIND ANGLE RELATIVE TO RUN- WAY HEADING. ENTER CHART FROM LOWER LEFT ALONG WIND ANGLE LINE TO REPORTED 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.

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