|
|
NAVAIR 01−F14AAD−1
THE
1
AIRCRAFT
INDOCTRINATION
2
NORMAL
NATOPS FLIGHT MANUAL
3
PROCEDURES
NAVY MODEL
F−14D
FLIGHT
4
CHARACTERISTICS
AIRCRAFT
EMERGENCY
5
PROCEDURES
THIS PUBLICATION IS INCOMPLETE WITHOUT
NAVAIR 01−F14AAP−1.1 AND NAVAIR 01−F14AAD−1A
ALL−WEATHER
TACTICAL SOFTWARE EFFECTIVITY: OFP D04
6
OPERATIONS
COMM
7
PROCEDURES
WEAPON
8
SYSTEMS
FLIGHTCREW
9
COORDINATION
DISTRIBUTION STATEMENT C Ċ Distribution authorized to U.S. Govern-
ment Agencies and their contractors to protect publications required
for official use or for administrative or operational purposes only
(1 January 1991). Other requests for this document shall be referred to
NATOPS
Commanding Officer, Naval Air Technical Data and Engineering Service
10
EVALUATION
Command, Naval Aviation Depot North Island, Bldg. 90, Distribution, P.O.
Box 357031, San Diego, CA 92135−7031.
DESTRUCTION NOTICE Ċ For unclassified, limited documents, destroy
PERFORMANCE
11
by any method that will prevent disclosure of contents or reconstruction
DATA
of the document.
ISSUED BY AUTHORITY OF THE CHIEF OF NAVAL OPERATIONS
INDEX &
AND UNDER THE DIRECTION OF THE
FOLDOUTS
COMMANDER, NAVAL AIR SYSTEMS COMMAND
0801LP1032160
1 (Reverse Blank)
15 APRIL 2002
Change 2 — 15 JANUARY 2004
NATEC ELECTRONIC MANUAL
NOTICE
NOTICE
NAVAIR 01-F14AAD-1
16 JANUARY 2004
NAVAIR 01-F14AAD-1, Change 2, dated 15 January 2004, has a print error on page 65
(incorrect configuration). Remove and discard previously provided page 65/66 and
replace with attached pages.
Place this page behind title page after incorporation.
NOTICE
NOTICE
NAVAIR 01−F14AAD−1
INTERIM CHANGE SUMMARY
The following Interim Changes have been canceled or previously incorporated in this manual:
INTERIM
CHANGE
REMARKS/PURPOSE
NUMBER(S)
1 through 26
Previously incorporated
The following Interim Changes have been incorporated in this Change/Revision:
INTERIM
CHANGE
REMARKS/PURPOSE
NUMBER(S)
27
Modifies the L and/or R Fuel Press Light(s) and Warning Tone Emergency Procedure,
and Adds Fuel Imbalance / Fuel Quantity Balancing Emergency Procedure.
Interim Changes Outstanding Ċ To be maintained by the custodian of this manual:
INTERIM
ORIGINATOR/DATE
PAGES
CHANGE
REMARKS/PURPOSE
(OR DATE/TIME GROUP)
AFFECTED
NUMBER
5 (Reverse Blank)
CHANGE 2
PTTUZYUW RULSABU1234 2032006-UUUU--RHMCSUU.
ZNR UUUUU
P 212006Z JUL 04 ZYB
FM COMNAVAIRSYSCOM PATUXENT RIVER MD//4.0P//
TO ALL TOMCAT AIRCRAFT ACTIVITIES
AL ALL TOMCAT AIRCRAFT ACTIVITIES
INFO COMNAVAIRSYSCOM PATUXENT RIVER MD//5.0F/4.1//
COMNAVSAFECEN NORFOLK VA//11//
COMNAVAIRLANT NORFOLK VA//N421B//
COMNAVAIRPAC SAN DIEGO CA//N421B1//
COMFITWINGLANT OCEANA VA//N4//
NAVAIRDEPOT JACKSONVILLE FL//3.3.3//
NAVSURVTRAINST PENSACOLA FL//02/025//
BT
UNCLAS //N03711//
MSGID/GENADMIN/COMNAVAIRSYSCOM/4.0P//
SUBJ/F-14ABD AIRCRAFT NATOPS PUBLICATIONS INTERIM CHANGE -
/SAFETY OF FLIGHT//
REF/A/EML/COMNAVAIRFOR/20JUL2004//
REF/B/MSG/FITRON ON ZERO ONE/021438ZJUN2004//
REF/C/DOC/COMNAVAIRSYSCOM/15JAN2004//
REF/D/DOC/COMNAVAIRSYSCOM/15JAN2004//
REF/E/DOC/COMNAVAIRSYSCOM/15JAN2004//
REF/F/DOC/COMNAVAIRSYSCOM/15JAN2004//
REF/G/DOC/COMNAVAIRSYSCOM/15JAN2004//
REF/H/DOC/COMNAVAIRSYSCOM/15JAN2004//
NARR/REF A IS NATOPS REQUEST FOR RELEASE.
REF B IS NATOPS URGENT CHANGE RECOMMENDATION.
REF C IS F-14D POCKET CHECKLIST (PCL) 01-F14AAD-1B, DTD 15 APR 02
WITH CHANGE 2 DTD 15 JAN 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 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.
REF H IS F-14A FLIGHT MANUAL (NFM) 01-F14AAA-1, DTD 15 MAY 03 WITH
CHANGE 1 DTD 15 JAN 04.//
RMKS/1. IRT REFS A AND B, THIS MESSAGE ISSUES INTERIM CHANGE (IC)
NUMBER 18 TO REF C, INTERIM CHANGE (IC) NUMBER 29 TO REF D, INTERIM
CHANGE (IC) NUMBER 33 TO REF E, INTERIM CHANGE (IC) NUMBER 49 TO REF
F, INTERIM CHANGE (IC) NUMBER 107 TO REF G AND INTERIM CHANGE (IC)
NUMBER 151 TO REF H.
2. SUMMARY. THE FOLLOWING CHANGES MAKE MINOR CORRECTIONS TO REFS C
THROUGH H FOR THE L AND/OR R FUEL PRESS LIGHT(S) AND WARNING
TONE EMERGENCY PROCEDURE. THE CORRECTIONS FOLLOW A SIMPLE AND
LOGICAL PROGRESSION THROUGH EACH PCL AND NFM AS INDICATED.
3. CHANGE REF C (F-14D PCL) AS FOLLOWS:
A. PAGE 114, TITLE:
(1) DELETE: WARNING TONE.
(2) ADD: 10 SEC WARNING TONE.
NAVAIR 212005Z JUL04
Page 1 of 3
A1-F14AAA-1 IC 151
A1-F14AAA-1B IC 107
A1-F14AAP-1 IC 49
A1-F14AAP-1B IC 33
A1-F14AAD-1 IC 29
A1-F14AAD-1B IC 18
B. PAGE 114, LINE 3 (AFTER STEP 2):
(1) DELETE: AND WARNING TONE
(2) ADD: NA
C. PAGE 114, LINE 20 (AFTER WARNING PARAGRAPHS):
(1) DELETE: AND THE WARNING TONE
(2) ADD: NA
D. PAGE 114A, NOTE SECTION, SECOND NOTE PARAGRAPH, LINE 1:
(1) DELETE: AND
(2) ADD: AND/OR
4. CHANGE REF D (F-14D NFM) AS FOLLOWS:
A. CHAPTER 14, PAGE 14-18, PARAGRAPH 14.6.1.1, TITLE:
(1) DELETE: WARNING TONE
(2) ADD: 10 SEC WARNING TONE.
B. CHAPTER 14, PAGE 14-18, PARAGRAPH 14.6.1.1, LINE 3:
(1) DELETE: AND WARNING TONE
(2) ADD: NA
C. CHAPTER 14, PAGE 14-18, PARAGRAPH 14.6.1.1, SECOND COLUMN,
LINE 13:
(1) DELETE: AND THE WARNING TONE
(2) ADD: NA
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.
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. PAGE 124A, NOTE PARAGRAPH, LINE 1:
(1) DELETE: AND
(2) ADD: AND/OR
6. CHANGE REF F (F-14B NFM) AS FOLLOWS:
A. CHAPTER 14, PAGE 14-19, PARAGRAPH 14.6.1.1, TITLE:
(1) DELETE: WARNING TONE
(2) ADD: 10 SEC WARNING TONE.
B. CHAPTER 14, PAGE 14-19, PARAGRAPH 14.6.1.1, LINE 3:
(1) DELETE: AND WARNING TONE
(2) ADD: NA
C. CHAPTER 14, PAGE 14-19, PARAGRAPH 14.6.1.1, LINE 20:
(1) DELETE: AND THE WARNING TONE
(2) ADD: NA
D. CHAPTER 14, PAGE 14-19, PARAGRAPH 14.6.1.1, SECOND COLUMN,
SECOND NOTE PARAGRAPH, LINE 1:
(1) DELETE: AND
(2) ADD: AND/OR
7. CHANGE REF G (F-14A PCL) AS FOLLOWS:
A. PAGE 94, TITLE:
NAVAIR 212005Z JUL04
Page 2 of 3
A1-F14AAA-1 IC 151
A1-F14AAA-1B IC 107
A1-F14AAP-1 IC 49
A1-F14AAP-1B IC 33
A1-F14AAD-1 IC 29
A1-F14AAD-1B IC 18
(1) DELETE: WARNING TONE.
(2) ADD: 10 SEC WARNING TONE.
B. PAGE 94, LINE 3 (AFTER STEP 2):
(1) DELETE: AND WARNING TONE
(2) ADD: NA
C. PAGE 94, LINE 20 (AFTER WARNING PARAGRAPHS):
(1) DELETE: AND THE WARNING TONE
(2) ADD: NA
D. PAGE 94A, NOTE SECTION, SECOND NOTE PARAGRAPH, LINE 1:
(1) DELETE: AND
(2) ADD: AND/OR
8. CHANGE REF H (F-14A NFM) AS FOLLOWS:
A. CHAPTER 14, PAGE 14-15, PARAGRAPH 14.6.1.1, TITLE:
(1) DELETE: WARNING TONE
(2) ADD: 10 SEC WARNING TONE.
B. CHAPTER 14, PAGE 14-15, PARAGRAPH 14.6.1.1, LINE 3:
(1) DELETE: AND WARNING TONE
(2) ADD: NA
C. CHAPTER 14, PAGE 14-15, PARAGRAPH 14.6.1.1, SECOND COLUMN,
LINE 1:
(1) DELETE: AND THE WARNING TONE
(2) ADD: NA
D. CHAPTER 14, PAGE 14-15, PARAGRAPH 14.6.1.1, SECOND COLUMN,
SECOND NOTE PARAGRAPH, LINE 1:
(1) DELETE: AND
(2) ADD: AND/OR
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
3. KRISTIN SWIFT, 4.0P NATOPS CHIEF ENGINEER, TEL DSN 995-4193,
OR COMM (301)995-4193, EMAIL: KRISTIN.SWIFT(AT)NAVY.MIL
10. THIS MESSAGE WILL BE POSTED ON THE NATEC WEBSITE,
WWW.NATEC.NAVY.MIL WITHIN 15 DAYS OF RELEASE. NEW NATOPS IC MESSAGES
MAY BE FOUND IN TWO PLACES ON THIS WEBSITE:
(1) IN THE NATOPS IC DATABASE FOUND UNDER THE TMAPS OPTION, AND
(2) IN THE AFFECTED PUBLICATIONS(S) JUST AFTER THE IC SUMMARY PAGE
IF THE IC MESSAGE INCLUDES REPLACEMENT PAGES, THEY WILL BE
ADDITIONALLY PLACED WITHIN THE MANUAL AND REPLACED PAGES DELETED.
MESSAGES ARE NORMALLY POSTED IN THE DATABASE BEFORE APPEARING IN THE
PUBLICATION. THIS MESSAGE WILL ALSO BE POSTED ON THE NATOPS WEBSITE,
NATOPS.NAVAIR.NAVY.MIL. IF UNABLE TO VIEW THIS MESSAGE ON EITHER
THE NATEC OR NATOPS WEBSITES, INFORM THE NATOPS GLOBAL CUSTOMER
SUPPORT TEAM AT (301) 342-3276, DSN 342-3276, OR BY EMAIL AT
NATOPS(AT)NAVY.MIL.//
BT
#1234
NNNN
NAVAIR 212005Z JUL04
Page 3 of 3
A1-F14AAA-1 IC 151
A1-F14AAA-1B IC 107
A1-F14AAP-1 IC 49
A1-F14AAP-1B IC 33
A1-F14AAD-1 IC 29
A1-F14AAD-1B IC 18
PTTUZYUW RULSABU1234 2032005-UUUU--RHMCSUU.
ZNR UUUUU
P 212005Z JUL 04
FM COMNAVAIRSYSCOM PATUXENT RIVER MD//4.0P//
TO ALL TOMCAT AIRCRAFT ACTIVITIES
AL ALL TOMCAT AIRCRAFT ACTIVITIES
INFO COMNAVAIRSYSCOM PATUXENT RIVER MD//5.0F/4.1//
COMNAVSAFECEN NORFOLK VA//11//
COMNAVAIRPAC SAN DIEGO CA//N421B1//
COMNAVAIRLANT NORFOLK VA//N421B//
COMFITWINGLANT OCEANA VA//N4//
NAVAIRDEPOT JACKSONVILLE FL//3.3.3//
NAVSURVTRAINST PENSACOLA FL//02/025//
FITRON ONE ZERO ONE
BT
UNCLAS //N03711//
MSGID/GENADMIN/COMNAVAIRSYSCOM/4.0P//
SUBJ/F-14ABD AIRCRAFT NATOPS PUBLICATIONS INTERIM CHANGE -
/SAFETY OF FLIGHT//
REF/A/EML/COMNAVAIRFOR/20JUL2004//
REF/B/MSG/FITRON ONE ZERO ONE/011815ZJUL2004//
REF/C/DOC/COMNAVAIRSYSCOM/15JAN2004//
REF/D/DOC/COMNAVAIRSYSCOM/15JAN2004//
REF/E/DOC/COMNAVAIRSYSCOM/15JAN2004//
REF/F/DOC/COMNAVAIRSYSCOM/15JAN2004//
REF/G/DOC/COMNAVAIRSYSCOM/15JAN2004//
REF/H/DOC/COMNAVAIRSYSCOM/15JAN2004//
NARR/REF A IS NATOPS REQUEST FOR RELEASE.
REF B IS NATOPS URGENT CHANGE RECOMMENDATION.
REF C IS F-14D POCKET CHECKLIST (PCL) 01-F14AAD-1B, DTD 15 APR 02
WITH CHANGE 2 DTD 15 JAN 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 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.
REF H IS F-14A FLIGHT MANUAL (NFM) 01-F14AAA-1, DTD 15 MAY 03 WITH
CHANGE 1 DTD 15 JAN 04.//
RMKS/1. IRT REFS A AND B, THIS MESSAGE ISSUES INTERIM CHANGE (IC)
NUMBER 17 TO REF C, INTERIM CHANGE (IC) NUMBER 28 TO REF D, INTERIM
CHANGE (IC) NUMBER 32 TO REF E, INTERIM CHANGE (IC) NUMBER 48 TO REF
F, INTERIM CHANGE (IC) NUMBER 106 TO REF G AND INTERIM CHANGE (IC)
NUMBER 150 TO REF H.
2. SUMMARY. THE FOLLOWING CHANGES MAKE CORRECTIONS TO
REFS C THROUGH H FOR THE FUEL IMBALANCE/FUEL QUANTITY BALANCING
EMERGENCY PROCEDURE. THE CORRECTIONS FOLLOW A SIMPLE AND LOGICAL
PROGRESSION THROUGH EACH PCL AND NFM AS INDICATED. CHANGES MAY
REQUIRE THE INSERTION OF A NEW PAGE IN SOME PCLS. REPLACEMENT
PAGES CONTAINING THIS INTERIM CHANGE FOR DOWNLOADING AND
INSERTION INTO REFS C THRU H WILL BE ATTACHED TO THIS INTERIM
NAVAIR 212005Z JUL04
Page 1 of 11
A1-F14AAA-1 IC 150
A1-F14AAA-1B IC 106
A1-F14AAP-1 IC 48
A1-F14AAP-1B IC 32
A1-F14AAD-1 IC 28
A1-F14AAD-1B IC 17
CHANGE MSG WHEN IT IS POSTED ON THE NATEC AND NATOPS
WEBSITES (SEE LAST PARA BELOW)).
3. CHANGE REF C (F-14D PCL), FUEL CHAPTER, PAGE 118, 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) ADD (REPLACE WITH): "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 TO READ:
"FUEL QUANTITY BALANCING IS NOT REQUIRED PRIOR TO COMPLETION OF
WING/EXTERNAL TANK TRANSFER OR UNTIL ONE FUSELAGE TAPE DROPS BELOW
4,500 POUNDS."
C.
(1) DELETE: NA
(2) ADD: STATEMENT IN CAPITAL ITALICS, PRIOR TO STEP 1, TO
READ: "WITH A FUEL STATE BELOW 4500 POUNDS IN A SINGLE FEED GROUP
AND A FUEL SPLIT GREATER THAN 1500 POUNDS BETWEEN THE AFT/LEFT AND
FWD/RIGHT FEED GROUPS:"
D.
(1) DELETE: NA
(2) ADD (INSERT): NOTE PARAGRAPH IMMEDIATELY AFTER STEP 2
TO READ: "IF 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 PRECEDING (INSERTED)
NOTE PARAGRAPH, BUT PRIOR TO THE EXISTING 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 HAVE A SIGNIFICANT INFLUENCE..."
(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.
UPDATE THE NOTE PARAGRAPH TO READ: "WITH A HIGH QUANTITY IN THE
FWD/RT FUEL SYSTEM, THE GREATER STATIC HEAD PRESSURE, PARTICULARLY
IN NOSE-UP ATTITUDES CAN CAUSE OVERFILLING 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 OF 6,600 POUNDS OR
GREATER IN THE FWD/RT SYSTEM OR 6,200 POUNDS OF GREATER IN THE
AFT/LT SYSTEM."
H. (1) DELETE: STATEMENT IMMEDIATELY PRECEDING STEP 3 THAT
READS: "IF FUEL IMBALANCE INCREASES:"
(2) ADD (REPLACE WITH): "IF NO VENTING IS OBSERVED
AND/OR THE FUEL IMBALANCE IS CORRECTED WITH THE FUEL FEED
SWITCH:"
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
A1-F14AAP-1 IC 48
A1-F14AAP-1B IC 32
A1-F14AAD-1 IC 28
A1-F14AAD-1B IC 17
(2) ADD (INSERT): STATEMENT IMMEDIATELY PRIOR TO STEP 4 TO
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."
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 RESULT IN
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."
M. (1) DELETE (CHANGE): RENUMBER EXISTING STEP 4 TO NEW STEP 5
WITHOUT CHANGING VERBIAGE.
N. (1) DELETE: NA
(2) ADD (INSERT): STATEMENT AFTER NEW STEP 5 TO
READ: "IF INDICATIONS OF A FUEL LEAK EXIST:"
O. (1) DELETE: NA
(2) ADD (INSERT): NEW STEP 6 AFTER STATEMENT TO READ:
"6. REFER TO FUEL LEAK PROCEDURE (PAGE 116)."
4. CHANGE REF D (F-14D NFM), CHAPTER 14, PAGE 14-20, 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."
(2) ADD (REPLACE WITH): "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 TO READ:
"FUEL QUANTITY BALANCING IS NOT REQUIRED PRIOR TO COMPLETION OF
WING/EXTERNAL TANK TRANSFER OR UNTIL ONE FUSELAGE TAPE DROPS BELOW
4,500 POUNDS."
C.
(1) DELETE: NA
(2) ADD: STATEMENT IN CAPITAL ITALICS, PRIOR TO STEP 1, TO
READ: "WITH A FUEL STATE BELOW 4500 POUNDS IN A SINGLE FEED GROUP
AND A FUEL SPLIT GREATER THAN 1500 POUNDS BETWEEN THE AFT/LEFT AND
FWD/RIGHT FEED GROUPS:"
D.
(1) DELETE: NA
(2) ADD (INSERT): NOTE PARAGRAPH IMMEDIATELY AFTER STEP 2
TO READ: "IF 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 PARAGRAPH, BUT PRIOR TO THE EXISTING 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 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
A1-F14AAP-1 IC 48
A1-F14AAP-1B IC 32
A1-F14AAD-1 IC 28
A1-F14AAD-1B IC 17
(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.
UPDATE THE NOTE PARAGRAPH TO READ: "WITH A HIGH QUANTITY IN THE
FWD/RT FUEL SYSTEM, THE GREATER STATIC HEAD PRESSURE, PARTICULARLY
IN NOSE-UP ATTITUDES CAN CAUSE OVERFILLING 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 OF 6,600 POUNDS OR
GREATER IN THE FWD/RT SYSTEM OR 6,200 POUNDS OF GREATER IN THE
AFT/LT SYSTEM."
H. (1) DELETE: STATEMENT IMMEDIATELY PRECEDING STEP 3 THAT
READS: "IF FUEL IMBALANCE INCREASES:"
(2) ADD (REPLACE WITH): "IF NO VENTING IS OBSERVED
AND/OR THE FUEL IMBALANCE IS CORRECTED WITH THE FUEL FEED
SWITCH:"
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
(2) ADD (INSERT): STATEMENT IMMEDIATELY PRIOR TO STEP 4 TO
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."
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 RESULT IN
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."
M. (1) DELETE (CHANGE): RENUMBER EXISTING STEP 4 TO NEW STEP 5
WITHOUT CHANGING VERBIAGE.
N. (1) DELETE: NA
(2) ADD (INSERT): STATEMENT AFTER NEW STEP 5 TO
READ: "IF INDICATIONS OF A FUEL LEAK EXIST:"
O. (1) DELETE: NA
(2) ADD (INSERT): NEW STEP 6 AFTER STATEMENT TO READ:
"6. REFER TO FUEL LEAK PROCEDURE (PAGE 14-19)."
5. 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. FWD OR AFT COULD DEPLETE THE
SUMP TANKS."
(2) ADD (REPLACE WITH): "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 TO READ:
"FUEL QUANTITY BALANCING IS NOT REQUIRED PRIOR TO COMPLETION OF
WING/EXTERNAL TANK TRANSFER OR UNTIL ONE FUSELAGE TAPE DROPS BELOW
NAVAIR 212005Z JUL04
Page 4 of 11
A1-F14AAA-1 IC 150
A1-F14AAA-1B IC 106
A1-F14AAP-1 IC 48
A1-F14AAP-1B IC 32
A1-F14AAD-1 IC 28
A1-F14AAD-1B IC 17
4,500 POUNDS."
C.
(1) DELETE: NA
(2) ADD: STATEMENT IN CAPITAL ITALICS, PRIOR TO STEP 1, TO
READ: "WITH A FUEL STATE BELOW 4500 POUNDS IN A SINGLE FEED GROUP
AND A FUEL SPLIT GREATER THAN 1500 POUNDS BETWEEN THE AFT/LEFT AND
FWD/RIGHT FEED GROUPS:"
D.
(1) DELETE: NA
(2) ADD (INSERT): NOTE PARAGRAPH IMMEDIATELY AFTER STEP 2
TO READ: "IF 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 PARAGRAPH, BUT PRIOR TO THE EXISTING 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 HAVE A SIGNIFICANT INFLUENCE..."
(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.
UPDATE THE NOTE PARAGRAPH TO READ: "WITH A HIGH QUANTITY IN THE
FWD/RT FUEL SYSTEM, THE GREATER STATIC HEAD PRESSURE, PARTICULARLY
IN NOSE-UP ATTITUDES CAN CAUSE OVERFILLING 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 OF 6,600 POUNDS OR
GREATER IN THE FWD/RT SYSTEM OR 6,200 POUNDS OF GREATER IN THE
AFT/LT SYSTEM."
H. (1) DELETE: STATEMENT IMMEDIATELY PRECEDING STEP 3 THAT
READS: "IF FUEL IMBALANCE INCREASES:"
(2) ADD (REPLACE WITH): "IF NO VENTING IS OBSERVED
AND/OR THE FUEL IMBALANCE IS CORRECTED WITH THE FUEL FEED
SWITCH:"
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
(2) ADD (INSERT): STATEMENT IMMEDIATELY PRIOR TO STEP 4 TO
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."
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 RESULT IN
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
A1-F14AAA-1B IC 106
A1-F14AAP-1 IC 48
A1-F14AAP-1B IC 32
A1-F14AAD-1 IC 28
A1-F14AAD-1B IC 17
M. (1) DELETE (CHANGE): RENUMBER EXISTING STEP 4 TO NEW STEP 5
WITHOUT CHANGING VERBIAGE.
N. (1) DELETE: NA
(2) ADD (INSERT): STATEMENT AFTER NEW STEP 5 TO
READ: "IF INDICATIONS OF A FUEL LEAK EXIST:"
O. (1) DELETE: NA
(2) ADD (INSERT): NEW STEP 6 AFTER STATEMENT TO READ:
"6. REFER TO FUEL LEAK PROCEDURE (PAGE 126A)."
6. 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. FWD OR AFT COULD DEPLETE THE
SUMP TANKS."
(2) ADD (REPLACE WITH): "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 TO READ:
"FUEL QUANTITY BALANCING IS NOT REQUIRED PRIOR TO COMPLETION OF
WING/EXTERNAL TANK TRANSFER OR UNTIL ONE FUSELAGE TAPE DROPS BELOW
4,500 POUNDS."
C.
(1) DELETE: NA
(2) ADD: STATEMENT IN CAPITAL ITALICS, PRIOR TO STEP 1, TO
READ: "WITH A FUEL STATE BELOW 4500 POUNDS IN A SINGLE FEED GROUP
AND A FUEL SPLIT GREATER THAN 1500 POUNDS BETWEEN THE AFT/LEFT AND
FWD/RIGHT FEED GROUPS:"
D.
(1) DELETE: NA
(2) ADD (INSERT): NOTE PARAGRAPH IMMEDIATELY AFTER STEP 2
TO READ: "IF 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 PARAGRAPH, BUT PRIOR TO THE EXISTING 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 HAVE A SIGNIFICANT INFLUENCE..."
(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.
UPDATE THE NOTE PARAGRAPH TO READ: "WITH A HIGH QUANTITY IN THE
FWD/RT FUEL SYSTEM, THE GREATER STATIC HEAD PRESSURE, PARTICULARLY
IN NOSE-UP ATTITUDES CAN CAUSE OVERFILLING 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 OF 6,600 POUNDS OR
GREATER IN THE FWD/RT SYSTEM OR 6,200 POUNDS OF GREATER IN THE
AFT/LT SYSTEM."
H. (1) DELETE: STATEMENT IMMEDIATELY PRECEDING STEP 3 THAT
READS: "IF FUEL IMBALANCE INCREASES:"
NAVAIR 212005Z JUL04
Page 6 of 11
A1-F14AAA-1 IC 150
A1-F14AAA-1B IC 106
A1-F14AAP-1 IC 48
A1-F14AAP-1B IC 32
A1-F14AAD-1 IC 28
A1-F14AAD-1B IC 17
(2) ADD (REPLACE WITH): "IF NO VENTING IS OBSERVED
AND/OR THE FUEL IMBALANCE IS CORRECTED WITH THE FUEL FEED
SWITCH:"
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
(2) ADD (INSERT): STATEMENT IMMEDIATELY PRIOR TO STEP 4 TO
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."
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 RESULT IN
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."
M. (1) DELETE (CHANGE): RENUMBER EXISTING STEP 4 TO NEW STEP 5
WITHOUT CHANGING VERBIAGE.
N. (1) DELETE: NA
(2) ADD (INSERT): STATEMENT AFTER NEW STEP 5 TO
READ: "IF INDICATIONS OF A FUEL LEAK EXIST:"
O. (1) DELETE: NA
(2) ADD (INSERT): NEW STEP 6 AFTER STATEMENT TO READ:
"6. REFER TO FUEL LEAK PROCEDURE (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) ADD (REPLACE WITH): "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 TO READ:
"FUEL QUANTITY BALANCING IS NOT REQUIRED PRIOR TO COMPLETION OF
WING/EXTERNAL TANK TRANSFER OR UNTIL ONE FUSELAGE TAPE DROPS BELOW
4,500 POUNDS."
C.
(1) DELETE: NA
(2) ADD: STATEMENT IN CAPITAL ITALICS, PRIOR TO STEP 1, TO
READ: "WITH A FUEL STATE BELOW 4500 POUNDS IN A SINGLE FEED GROUP
AND A FUEL SPLIT GREATER THAN 1500 POUNDS BETWEEN THE AFT/LEFT AND
FWD/RIGHT FEED GROUPS:"
D.
(1) DELETE: NA
(2) ADD (INSERT): NOTE PARAGRAPH IMMEDIATELY AFTER STEP 2
TO READ: "IF 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 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
A1-F14AAP-1 IC 48
A1-F14AAP-1B IC 32
A1-F14AAD-1 IC 28
A1-F14AAD-1B IC 17
"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 HAVE A SIGNIFICANT INFLUENCE..."
(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.
UPDATE THE NOTE PARAGRAPH TO READ: "WITH A HIGH QUANTITY IN THE
FWD/RT FUEL SYSTEM, THE GREATER STATIC HEAD PRESSURE, PARTICULARLY
IN NOSE-UP ATTITUDES CAN CAUSE OVERFILLING 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 OF 6,600 POUNDS OR
GREATER IN THE FWD/RT SYSTEM OR 6,200 POUNDS OF GREATER IN THE
AFT/LT SYSTEM."
H. (1) DELETE: STATEMENT IMMEDIATELY PRECEDING STEP 3 THAT
READS: "IF FUEL IMBALANCE INCREASES:"
(2) ADD (REPLACE WITH): "IF NO VENTING IS OBSERVED
AND/OR THE FUEL IMBALANCE IS CORRECTED WITH THE FUEL FEED
SWITCH:"
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
(2) ADD (INSERT): STATEMENT IMMEDIATELY PRIOR TO STEP 4 TO
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."
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 RESULT IN
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."
M. (1) DELETE (CHANGE): RENUMBER EXISTING STEP 4 TO NEW STEP 5
WITHOUT CHANGING VERBIAGE.
N. (1) DELETE: NA
(2) ADD (INSERT): STATEMENT AFTER NEW STEP 5 TO
READ: "IF INDICATIONS OF A FUEL LEAK EXIST:"
O. (1) DELETE: NA
(2) ADD (INSERT): NEW STEP 6 AFTER STATEMENT TO READ:
"6. REFER TO FUEL LEAK PROCEDURE (PAGE 97)."
8. 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 IC 48
A1-F14AAP-1B IC 32
A1-F14AAD-1 IC 28
A1-F14AAD-1B IC 17
(2) ADD (REPLACE WITH): "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 TO READ:
"FUEL QUANTITY BALANCING IS NOT REQUIRED PRIOR TO COMPLETION OF
WING/EXTERNAL TANK TRANSFER OR UNTIL ONE FUSELAGE TAPE DROPS BELOW
4,500 POUNDS."
C.
(1) DELETE: NA
(2) ADD: STATEMENT IN CAPITAL ITALICS, PRIOR TO STEP 1, TO
READ: "WITH A FUEL STATE BELOW 4500 POUNDS IN A SINGLE FEED GROUP
AND A FUEL SPLIT GREATER THAN 1500 POUNDS BETWEEN THE AFT/LEFT AND
FWD/RIGHT FEED GROUPS:"
D.
(1) DELETE: NA
(2) ADD (INSERT): NOTE PARAGRAPH IMMEDIATELY AFTER STEP 2
TO READ: "IF 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 PARAGRAPH, BUT PRIOR TO THE EXISTING 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 HAVE A SIGNIFICANT INFLUENCE..."
(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.
UPDATE THE NOTE PARAGRAPH TO READ: "WITH A HIGH QUANTITY IN THE
FWD/RT FUEL SYSTEM, THE GREATER STATIC HEAD PRESSURE, PARTICULARLY
IN NOSE-UP ATTITUDES CAN CAUSE OVERFILLING 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 OF 6,600 POUNDS OR
GREATER IN THE FWD/RT SYSTEM OR 6,200 POUNDS OF GREATER IN THE
AFT/LT SYSTEM."
H. (1) DELETE: STATEMENT IMMEDIATELY PRECEDING STEP 3 THAT
READS: "IF FUEL IMBALANCE INCREASES:"
(2) ADD (REPLACE WITH): "IF NO VENTING IS OBSERVED
AND/OR THE FUEL IMBALANCE IS CORRECTED WITH THE FUEL FEED
SWITCH:"
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
(2) ADD (INSERT): STATEMENT IMMEDIATELY PRIOR TO STEP 4 TO
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
A1-F14AAP-1 IC 48
A1-F14AAP-1B IC 32
A1-F14AAD-1 IC 28
A1-F14AAD-1B IC 17
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 RESULT IN
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."
M. (1) DELETE (CHANGE): RENUMBER EXISTING STEP 4 TO NEW STEP 5
WITHOUT CHANGING VERBIAGE.
N. (1) DELETE: NA
(2) ADD (INSERT): STATEMENT AFTER NEW STEP 5 TO
READ: "IF INDICATIONS OF A FUEL LEAK EXIST:"
O. (1) DELETE: NA
(2) ADD (INSERT): NEW STEP 6 AFTER STATEMENT TO READ:
"6. REFER TO FUEL LEAK PROCEDURE (PAGE 14-16)."
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
3. KRISTIN SWIFT, 4.0P NATOPS CHIEF ENGINEER, TEL DSN 995-4193,
OR COMM (301)995-4193, EMAIL: KRISTIN.SWIFT(AT)NAVY.MIL
10. THIS MESSAGE WILL BE POSTED ON THE NATEC WEBSITE,
WWW.NATEC.NAVY.MIL WITHIN 15 DAYS OF RELEASE. NEW NATOPS IC MESSAGES
MAY BE FOUND IN TWO PLACES ON THIS WEBSITE:
(1) IN THE NATOPS IC DATABASE FOUND UNDER THE TMAPS OPTION, AND
(2) IN THE AFFECTED PUBLICATIONS(S) JUST AFTER THE IC SUMMARY PAGE.
IF THE IC MESSAGE INCLUDES REPLACEMENT PAGES, THEY WILL BE
ADDITIONALLY PLACED WITHIN THE MANUAL AND REPLACED PAGES DELETED.
MESSAGES ARE NORMALLY POSTED IN THE DATABASE BEFORE APPEARING IN THE
PUBLICATION. THIS MESSAGE WILL ALSO BE POSTED ON THE NATOPS WEBSITE,
NATOPS.NAVAIR.NAVY.MIL. IF UNABLE TO VIEW THIS MESSAGE ON EITHER
THE NATEC OR NATOPS WEBSITES, INFORM THE NATOPS GLOBAL CUSTOMER
SUPPORT TEAM AT (301) 342-3276, DSN 342-3276, OR BY EMAIL AT
NATOPS(AT)NAVY.MIL.//
BT
#1234
NNNN
NAVAIR 212005Z JUL04
Page 10 of 11
A1-F14AAA-1 IC 150
A1-F14AAA-1B IC 106
A1-F14AAP-1 IC 48
A1-F14AAP-1B IC 32
A1-F14AAD-1 IC 28
A1-F14AAD-1B IC 17
NAVAIR 01-F14AAD-1
F-14D AIRCRAFT
NATOPS FLIGHT MANUAL
INTERIM CHANGE 28 & 29
REPLACEMENT PAGES
---------------------------
1. Replacement pages for Interim Change Numbers 28 & 29 to the F-14D
NFM, NAVAIR 01-F14AAD-1 dated 15 Jan 2004, are attached as follows:
Page
Page Version Marking
------
----------------------
14-17
Change 2
14-18
Change 2 W/ IC 29
14-19
Change 2
14-20
Change 2 W/ IC 28
14-20a
Change 2 W/ IC 28
14-20b
Change 2 W/ IC 28
NAVAIR 212005Z JUL04
Page 11 of 11
A1-F14AAA-1 IC 150
A1-F14AAA-1B IC 106
A1-F14AAP-1 IC 48
A1-F14AAP-1B IC 32
A1-F14AAD-1 IC 28
A1-F14AAD-1B IC 17
NAVAIR 01−F14AAD−1
Note
14.5.13.1
OIL PRESS Light and/or
Abnormal Oil Pressure
Pulling the AICS cb while airborne may illumi-
nate the FCS CAUTION and ARI DGR lights.
1. Throttle (affected engine) Ċ IDLE.
Above about 600 knots, the PITCH SAS and
ROLL DGR lights will also be illuminated.
If oil pressure is below 15 psi, above 65 psi, or engine
These should clear with a MASTER RESET fol-
vibration:
lowing a programmer reset.
If shutdown is feasible:
8. Affected INLET RAMPS switch Ċ AUTO.
2. Throttle (affected engine) Ċ OFF.
9. Remain below 1.2 TMN.
3. Refer to Single Engine Cruise Operations, para-
graph 14.5.3.2.
When AICS programmer reset attempts are completed:
If shutdown is not feasible:
12. Wing sweep drive cb’s Ċ Reset (LD1 and LE1).
4. Rpm Ċ Set Minimum Rpm.
14.5.12
INLET ICE Light
5. Avoid high−g or large throttle movements.
1. ANTI−ICE switch Ċ ORIDE/ON.
6. Land as soon as practicable.
When clear of known icing conditions:
14.5.13.2
L or R OIL HOT Light
2. ANTI−ICE switch Ċ AUTO/OFF.
Illumination of an OIL HOT caution light may be
Ice may form on inlet and ramp surfaces without
an indication of above normal gearbox scavenge
any other visual indications, which may cause
oil temperature or high supply temperature. Con-
compressor stalls and/or FOD.
tinuous engine operation will result in reduced
gearbox life and lubrication degradation.
Note
On deck, OIL HOT light may be caused by
The formation of ice on pitot−static sensors may
underservicing or by excessive temperature on
result in DFCS detected failures that may not
deck. In the event of OIL HOT light on deck posi-
clear with a MASTER RESET.
tion throttles to OFF.
1. Oil pressure Ċ Check.
14.5.13
Oil System Malfunction
2. Throttle (affected engine) Ċ 85−Percent Rpm.
Malfunctions in the oil system are indicated by an L or
R OIL HOT light, OIL PRESS light, or by oil pressure below
If after 1 minute light is still illuminated:
or above normal.
3. Throttle (affected engine) Ċ OFF.
If oil pressure is over 65 psi, retard power until pressure
4. Refer to Single−Engine Cruise Operations, para-
is within the normal range. If pressure cannot be reduced, the
graph 14.5.3.2.
engine should be shut down to avoid rupturing oil lines. If oil
5. Relight engine for landing, if necessary.
pressure is less than 15 psi, bearing wear can be minimized
by maintaining a constant throttle setting and avoiding
6. Land as soon as possible.
unnecessary aircraft maneuvers. Bearing failure is normally
If light goes out, land as soon as practicable.
characterized by vibration, increasing in intensity with
bearing deterioration. When vibration becomes moderate to
14.5.14 RATS Operation In Flight
heavy, engine seizure is imminent if engine is not shut down.
Continued operation of an engine with oil pressure less than
1. Tailhook Ċ DOWN.
15 psi is likely to result in illumination of OIL HOT light or
If conditions permit:
an engine seizure. If conditions permit it is advisable to shut
down the engine to reduce damage and to save it for
2. ANTI ICE CONTR HOOK CONT/WSHLD/AIR
emergency use.
cb Ċ Pull (8C2).
14−17
CHANGE 2
NAVAIR 01−F14AAD−1
6. Land as soon as possible.
D Pulling the ANTI ICE CONTR HOOK
CONT/ WSHLD/AIR cb
(8C2) disables
D Illumination of both lights and the warning
RATS. Inform CV of increased wind−over−
tone may be indicative of a total motive−flow
deck requirements and gross weight settings
failure. Zero− or negative−g flight should be
for a non−RATS arrestment.
avoided.
D With the circuit breaker in and RATS operat-
D Complete loss of motive flow will result in the
ing, there is reduced thrust available for
sump tank interconnect and the engine feed
approach and use of afterburner may be
crossfeed valve remaining in the closed posi-
required to arrest sink rate.
tion, isolating the forward and aft systems. Con-
sequently, single−engine operation will cause
fuel on the opposite side to be unavailable.
If one light remains on:
3. No afterburner above 15,000 feet.
ANTI ICE CONTR HOOK CONT/WSHLD/
4. Fuel distribution Monitor (balance if required).
AIR circuit breaker (8C2) must be in prior to
5. Land as soon as practicable.
hook transition. Avoid icing conditions and rain
with circuit breaker pulled.
If migration occurs after balancing, as indicated by a
100 to 300 PPM increase on the inoperative side or a 100 to
Note
300 PPM decrease on the operative side above expected burn
D If RATS secures when the hook is raised with
rate according to indicated fuel flow:
no other weight−on−wheels indication, failure
is internal to the RATS circuitry.
6. FUEL PRESS ADVSY CB − PULL (8F1).
D With ANTI ICE CONTR HOOK CONT/
Note
WSHLD/AIR cb (8C2) pulled, approach
Pulling the FUEL PRESS ADVSY CB will cause
indexers will flash.
the engine crossfeed valve to close and the in-
operative side fuselage motive flow shutoff valve
14.6
FUEL SYSTEM MALFUNCTIONS
to open. This will reduce the amount of fuel
transfer from the operative side to the inoperative
14.6.1
Fuel Pressure Caution Lights/Low Fuel
side.
Pressure Warning Tone
Note
The L or R FUEL PRESS light and/or warning
Afterburner operations place an extreme demand on the
tone will extinguish when the FUEL PRESS
engine fuel feed system. Aircraft maneuvers in the zero to
ADVSY CB is pulled.
negative 0.5g flight regime aggravate the effect and may gen-
erate a situation where afterburner blowout and engine flame-
7. Maintain cruise power or less.
out occur. The first indication of this condition may be a fuel
8. Fuel distribution − monitor (balance if required).
pressure light or an aural tone (engine stall warning tone).
14.6.1.1
L and/or R FUEL PRESS Light(s) and
10 sec Warning Tone
1. Both throttles Ċ MIL Power or Less.
If the sump tank interconnect valve has failed,
selecting AFT or FWD on the FEED SWITCH
2. Restore aircraft to 1.0g flight.
could result in fuel migration to the inoperative
side. If fuel migration occurs after selecting AFT
If both lights remain on:
or FWD on the FEED SWITCH (as indicated by
3. Increase positive g’s to greater than 1.0g.
a 100 to 300 PPM increase on the inoperative
side), immediately return the feed switch to
4. Descend below 25,000 feet.
NORM.
5. Maintain cruise power settings or less.
9. Land as soon as possible.
CHANGE 2 w/ IC 29
14−18
NAVAIR 01−F14AAD−1
14.6.2
L or R FUEL LOW Light
1. DUMP switch OFF.
2. Fuel distribution Check (balance if required).
CV arrestment, CV touch and go, or normal field
If wing and/or external fuel remaining:
landings with full or partial fuel in the external
tanks is not authorized because of overload of the
3. WING/EXT TRANS switch ORIDE.
nacelle backup structure. Only minimum descent
rate landings are authorized.
4. Land as soon as practicable.
14.6.3.3
Wings Do Not Accept Fuel With Switch
14.6.3
Fuel Transfer Failures
in ALL EXTD Position
1. REFUEL PROBE switch FUS EXTD.
2. WING/EXT TRANS switch OFF.
14.6.3.4
Wings Accept Fuel With Switch in
Wing and external fuel will not transfer with
FUS EXTD Position
refuel probe switch in ALL EXTD. If probe exten-
1. WING/EXT TRANS switch ORIDE.
sion required, select FUS EXTD to enable transfer.
Note
Note
With AIR SOURCE OFF pushbutton selected,
external fuel tanks will not transfer.
Fuel management panel will be inoperative if
FUEL MGT PNL cb (RD1) is out.
14.6.4
Uncommanded Dump
1. Fuel Management Panel cbĊCheck in (RD1).
1. DUMP switch Check OFF.
2. FUEL FEED/DUMP cb Pull (RE1).
14.6.3.1
Wing Fuel Fails To Transfer
If wing fuel fails to transfer:
1. WING/EXT TRANS switch ORIDE.
Pulling the FUEL FEED/DUMP circuit breaker
One wing still does not transfer:
(RE1) isolates the right and left fuel systems. It
also deactivates the function of the feed switch,
2. FEED switch Select High Fuselage Tape Side.
the automatic balance functions, and the fuel
dump system. Should single engine operation
If wing fuel does not decrease after 2 minutes or wing
subsequently become necessary, useable fuel
fuel transfer complete:
will be limited to only what is available on the
3. FEED switch NORM.
operating side.
14.6.5
Fuel Leak
14.6.3.2
External Tanks Fail To Transfer or
Transfer Slowly
In the absence of actual visual detection, a fuel leak
Note
resulting from a malfunction or failure of a fuel system
component will usually result in a split in the fuel quantity
Descending below freezing level may thaw
possible frozen valves.
tapes or feeds. The flightcrew must determine from available
instruments (fuel flow and total fuel quantity) whether the
1. WING/EXT TRANS switch ORIDE.
aircraft is losing more fuel than the engines indicate they are
using. Corrective steps are based on confirmation of the leak.
If fuel continues to transfer improperly or does not
transfer:
Upon confirmation of abnormal decrease in fuel quantity:
1. Land as soon as possible.
2. REFUEL PROBE switch All Extend, Then
Retract.
3. Apply cyclic positive or negative g’s.
4. AIR SOURCE pushbutton OFF then RAM then
Use of afterburner with fuel leak should be lim-
ON (below 35,000 feet, less than 300 knots).
ited to emergency use only.
14−19
CHANGE 2
NAVAIR 01−F14AAD−1
2. WING/EXT TRANS switch OFF.
14.6.6 Fuel Imbalance/Fuel Quantity Balancing
If abnormal fuel quantity decrease ceases, fuel leak is
in wing/wing pivot or attachment points for auxiliary tanks:
Note
This cannot be determined until the fuel level has
AB operation is not recommended with a fuel
decreased to below the source of the leak. Do not
imbalance or with indications of venting fuel.
proceed until the wings are empty.
Note
If leak is not stopped, it is in engine/nacelle area, pro-
Fuel quantity balancing is not required prior to
ceed immediately with next step.
completion of wing/external tank transfer or until
3. FUEL FEED/DUMP cb Pull (RE1).
one fuselage tape drops below 4,500 pounds.
WITH A FUEL STATE BELOW 4500 POUNDS IN EITHER
THE AFT/LEFT OR FWD/RT FEED GROUPS AND A FUEL
SPLIT GREATER THAN 1500 POUNDS BETWEEN THE
Pulling the FUEL FEED/DUMP circuit breaker
AFT/LEFT AND FWD/RIGHT FEED GROUPS:
(RE1) isolates the right and left fuel systems. It
also deactivates the function of the feed switch,
1. Both throttles − MIL power or less.
the automatic balance functions, and the fuel
dump system. Should single engine operation
2. FEED SWITCH − select high fuselage tape side.
subsequently become necessary, useable fuel
Note
will be limited to only what is available on the
operating side.
D If practical, obtain a visual inspection for vent-
Note
ing fuel. Do not delay execution of emer-
gency procedures for visual inspection.
Enough time should be allowed for quantity
tapes/ feeds to develop split so that leak can be
D Indication of fuel balancing should appear
isolated to left or right feed group. Affected side
within 3 minutes of selecting the high fuselage
will be low side.
tape side.
4. Throttle (affected side) OFF.
D With a high quantity in the FWD/RT fuel sys-
5. Conditions permitting, allow rpm to decelerate to
tem, the greater static head pressure, particu-
windmill rpm.
larly in nose−up attitudes can cause overfilling
6. FUEL SHUT OFF handle (affected side) Pull.
of the AFT/LT fuel system and subsequent fuel
7. Refer to Single−Engine Cruise Operations, para-
venting. To prevent this, the feed switch should
graph 14.5.3.2.
be returned to NORM before the AFT/LT tape
reaches 6,200 pounds. Overfilling is indicated
Setting the WING/EXT TRANS switch to OFF stops
by a quantity of 6,600 pounds or greater in the
motive flow to the wings and inhibits external tank transfer
FWD/RT system or 6,200 pounds or greater in
and fuselage tank pressurization. Pulling the FUEL FEED/
the AFT/LT system.
DUMP circuit breaker (RE1) isolates the right and forward
system and the left and aft fuel system. This aids in determin-
If no venting is observed and/or the fuel imbalance is
ing the location of the leak and prevents loss of fuel from the
corrected with the fuel feed switch:
good side via the fuel system interconnects. The circuit
3. FUEL FEED SWITCH − As required and land as
breaker also deactivates the function of the FEED switch, the
soon as practicable.
automatic balance functions, and the fuel dump system.
Securing the engine and, if necessary, pulling the FUEL
SHUT OFF handle should stop most engine leaks.
If the sump tank interconnect valve has failed
closed, selecting AFT or FWD on the FUEL
FEED SWITCH could result in rapid increase of
the fuel imbalance. If this occurs (as indicated by
an imbalance increase of 100 to 300 PPM) imme-
diately return the FEED SWITCH to NORM.
CHANGE 2 w/ IC 28
14−20
NAVAIR 01−F14AAD−1
If fuel venting exists and/or fuel imbalance exceeds
14.7.1.1
L or R GEN Light
2,000 pounds:
1. Generator
(affected generator switch)
OFF/
4. FUEL FEED SWITCH − NORM.
RESET, Then NORM.
Note
If the generator fault is corrected, the generator will
Venting fuel in conjunction with an uncontrol-
be reconnected and the caution light will go off.
lable fuel split is indicative of a motive flow fail-
ure and can result in the high feed group having
If generator does not reset:
trapped/unusable fuel. If this occurs, aircrew
may have as little as 4,500 pounds of usable fuel
2. Generator (affected generator switch) TEST.
remaining and a new bingo profile may be
If the light goes off with the switch in TEST, the
required.
fault is in the respective electrical distribution sys-
5. Determine useable fuel and land as soon as possible.
tem. If light remains illuminated, the generator has
been disconnected automatically and the fault is in
If indications of a fuel leak exist:
IDG or generator control unit.
6. Refer to FUEL LEAK PROCEDURE (page 14−19).
14.7.1.2
L or R GEN and TRANS/RECT Lights
14.7
ELECTRICAL FAILURE
1. Generator
(affected generator switch)
OFF/
RESET, Then NORM.
14.7.1
Generator Failure
2. If L GEN and TRANS/RECT lights remain illumi-
A mechanical generator failure or an overheating
nated, select EMERG GEN on MASTER TEST panel.
automatically causes the CSD unit of the generator transmis-
sion to decouple from the engine. Once disengaged, the CSD
Note
cannot be reconnected in flight.
With R GEN and TRANS/RECT lights illumi-
Either generator by itself is capable of supplying the
nated, ac essential power is supplied by the L
electrical requirements of the aircraft. Even double generator
GEN. Selecting EMER GEN on the MASTER
failure will not cause total loss of electrical power; the 5−kVA
TEST panel (with R GEN and TRANS/RECT
emergency generator will automatically pick up the load for
lights) will not provide any additional power but
the essential ac and dc buses No. 1 and No. 2, and the DFCS
may cause an interrupt as the supply is trans-
bus.
ferred from the L GEN to the EMER GEN.
If the bidirectional pump is operating and pressure
3. Land as soon as practicable.
drops to between 2,000 and 1,100 psi (dependent upon the
load placed on the generator), the emergency generator will
14.7.2
Double Generator Failure
automatically shift to the 1−kVA mode and power only the
essential ac and dc No. 1 buses. If combined system hydraulic
1. Both generator switches Cycle.
pressure subsequently recovers, the emergency generator
switch must be cycled through OFF/RESET to NORM to
If operating on emergency generator, the following
regain the essential No. 2 ac and dc buses. Figure 14−5 lists
important systems are inoperative:
the equipment available with only the emergency generator
operating.
1. Emergency flight hydraulics.
With both engines inoperative, windmilling engine(s)
2. Outboard spoiler module and emergency flap
provide(s) hydraulic pressure for both the flight controls and
activation.
the emergency generator. However, the flight controls have
first priority and may cause the emergency generator to loiter
3. OBOGS concentrator heater (OBOGS may still
when low airspeeds reduce engine windmilling rpm. Approx-
function at a reduced but adequate level).
imately 450 knots must be maintained to ensure adequate
engine windmilling rpm for hydraulic pressure.
14−20a
CHANGE 2 w/ IC 28
NAVAIR 01−F14AAD−1
If temporary loss of combined system pressure causes
MASTER RESET will be required to regain
emergency generator to shift to 1 kVA mode (to drop No. 2
SAS, spoiler, authority stop, and ARI functions.
essential bus):
Note
2. EMERG generator switch Cycle.
DFCS synchronization can take up to 2 seconds
following a power interrupt. If the MASTER
RESET pushbutton is depressed during the syn-
chronization time, an additional depression of
the MASTER RESET pushbutton will be
required to restore spoiler functionality.
A shift to 1 kVA mode will cause loss of all DFCS
functions and spoilers without illumination of
4. Land as soon as practicable.
caution lights. If the 5 kVA mode is regained, a
CHANGE 2 w/ IC 28
14−20b
NAVAIR 01−F14AAD−1
SUMMARY OF APPLICABLE TECHNICAL DIRECTIVES
Information relating to the following recent technical directives has been incorporated in this manual.
CHANGE
DATE INC.
VISUAL
DESCRIPTION
NUMBER
IN MANUAL
IDENTIFICATION
AFC 793
Standard Central Air Data Computer
30 Sep 94
None
AFC 795
Radar Warning Receiver Modification
30 Sep 94
None
Panel size increased on
AFC 832
Incorporation of Unmodified OBOGS Monitor
15 May 95
pilot’s right console
5A BOL PWR circuit
AFC 843
BOL Chaff Incorporation
1 Feb 97
breakers at 2I9, 2I10
AFC 850
F−14D GPS Aircraft Mod
15 April 2002
None
AFC 874
Modification of Color Cockpit Television
15 April 2002
Effectivity: All F−14D and
System (CCTVS) Wiring (LECP 1291N5−001)
F−14D(R)s
AFC 880
AN/AVX−3 Tactical Imaging Set
15 April 2002
None
AVC 4412
Incorporation of Low Fuel Pressure Aural
15 April 2002
None
Tone Alarm (ECP 222)
AFC 919
NGS SAHRS
15 May 2003
None
Information relating to the following applicable technical directives will be incorporated in a future change.
CHANGE
VISUAL
DESCRIPTION
NUMBER
IDENTIFICATION
7 (Reverse Blank)
CHANGE 1
NAVAIR 01−F14AAD−1
F−14D NATOPS FLIGHT MANUAL
CONTENTS
Page
No.Ă
PART I THE AIRCRAFT
CHAPTER 1 AIRCRAFT AND ENGINE
1.1
AIRCRAFT
1−1
1.1.1
Aircraft Weight
1−1
1.1.2
Cockpit
1−1
1.1.3
Electronic Nomenclature
1−2
1.1.4
Technical Directives
1−2
1.1.5
Block Numbers
1−2
CHAPTER 2 SYSTEMS
2.1
AIR INLET CONTROL SYSTEM (AICS)
2−1
2.1.1
Normal AICS Operations
2−1
2.1.2
AICS Test
2−1
2.1.3
AICS Failure Modes of Operation
2−4
2.1.4
AICS Anti−Ice
2−9
2.2
ENGINE
2−9
2.2.1
Engine Control
2−11
2.2.2
Variable Exhaust Nozzle
2−16
2.3
FATIGUE ENGINE MONITORING SYSTEM
2−18
2.3.1
FEMS Functional Description
2−18
2.3.2
FEMS Operation
2−21
2.3.3
FEMS and OBC
2−21
2.4
ENGINE FUEL SYSTEM
2−21
2.4.1
Motive Flow Fuel Pump
2−21
2.4.2
Engine Fuel Boost Pump
2−21
2.4.3
Main Fuel Pump
2−21
2.4.4
Main Engine Control
2−21
2.4.5
Afterburner Fuel Pump
2−23
2.4.6
Afterburner Fuel Control
2−23
2.5
THROTTLES
2−23
2.5.1
Throttle Control Modes
2−23
2.6
ENGINE BLEED AIR
2−27
2.6.1
Engine Anti−Ice
2−27
2.6.2
Environmental Control System Leak Detection
2−29
2.7
ENGINE COMPARTMENT VENTILATION
2−30
2.7.1
Engine In−Flight Ventilation
2−30
2.7.2
Engine Ground Ventilation
2−30
11
ORIGINAL
NAVAIR 01−F14AAD−1
Page
No.Ă
2.8
ENGINE IGNITION SYSTEM
2−30
2.8.1
Main High−Energy Ignition
2−30
2.8.2
Afterburner Ignition
2−32
2.8.3
Backup Ignition
2−32
2.9
ENGINE STARTING SYSTEM
2−32
2.9.1
External Airstart
2−32
2.9.2
Engine Crank
2−32
2.9.3
Crossbleed Start
2−34
2.9.4
Airstarts
2−34
2.10
ENGINE OIL SYSTEM
2−34
2.10.1
Oil Cooling
2−35
2.10.2
Oil Pressure Indicators
2−35
2.10.3
OIL HOT Caution Lights
2−35
2.11
ENGINE INSTRUMENTS
2−35
2.11.1
Engine RPM Indicator
2−35
2.11.2
Exhaust Gas Temperature Indicator
2−35
2.11.3
Fuel Flow Indicator
2−37
2.11.4
Engine Instrument Group BIT
2−37
2.11.5
Engine Instrument Group Self−Test
2−37
2.11.6
Engine Oil Pressure Indicator
2−37
2.11.7
Exhaust Nozzle Position Indicator
2−37
2.11.8
Engine Monitor Display Format
2−37
2.11.9
MFD Engine Caution Legends
2−38
2.11.10
Engine Stall/Overtemperature Warning
2−38
2.12
FIRE DETECTION SYSTEM
2−39
2.12.1
Fire Detection Test
2−40
2.13
FIRE EXTINGUISHING SYSTEM
2−40
2.13.1
Fire Extinguisher Pushbuttons
2−40
2.13.2
Fire Extinguisher Advisory Lights
2−40
2.13.3
Fire Extinguisher Test
2−40
2.14
AIRCRAFT FUEL SYSTEM
2−40
2.14.1
Fuel Tankage
2−42
2.14.2
Fuel Quantity System
2−42
2.14.3
Engine Feed
2−43
2.14.4
Fuel Transfer
2−50
2.14.5
Fuel Quantity Balancing
2−54
2.14.6
Fuel Transfer/Feed During Single−Engine Operation
2−54
2.14.7
Fuel Dump
2−55
2.14.8
Internal Tank Pressurization and Vent
2−56
2.14.9
Fueling and Defueling
2−56
2.14.10
In−Flight Refueling
2−57
2.14.11
Hot Refueling
2−58
2.14.12
Automatic Fuel Electrical Controls
2−59
2.15
ELECTRICAL POWER SUPPLY SYSTEM
2−59
2.15.1
Normal Electrical Operation
2−59
ORIGINAL
12
NAVAIR 01−F14AAD−1
Page
No.Ă
2.15.2
Electrical Power Distribution
2−61
2.15.3
Degraded Electrical Operation
2−62
2.16
HYDRAULIC POWER SUPPLY SYSTEMS
2−69
2.16.1
Flight and Combined Systems
2−69
2.16.2
Hydraulic Power Distribution
2−72
2.16.3
Outboard Spoiler System
2−73
2.16.4
Backup Flight Control System
2−73
2.17
PNEUMATIC POWER SUPPLY SYSTEMS
2−77
2.17.1
Normal Canopy Control
2−77
2.17.2
Auxiliary Canopy Open Control
2−77
2.17.3
Emergency Gear Extension
2−77
2.18
MISSION COMPUTER SYSTEM
2−77
2.18.1
Aircrew Interface
2−77
2.18.2
Operational States
2−79
2.18.3
Aircraft Master Modes
2−79
2.19
STANDARD CENTRAL AIR DATA COMPUTER
2−79
2.19.1
Standard Central Air Data Computer Tests
2−79
2.20
WING−SWEEP SYSTEM
2−82
2.20.1
Wing−Sweep Performance
2−82
2.20.2
Wing−Sweep Modes
2−83
2.20.3
Wing−Sweep Interlocks
2−87
2.20.4
Wing−Sweep System Test
2−87
2.21
FLAPS AND SLATS
2−89
2.21.1
Flap and Slat Controls
2−89
2.21.2
Flap and Slat Operation
2−93
2.22
SPEEDBRAKES
2−95
2.22.1
Speedbrake Operation
2−95
2.23
FLIGHT CONTROL SYSTEMS
2−97
2.23.1
Longitudinal Control
2−97
2.23.2
Integrated Trim System
2−97
2.23.3
Lateral Control
2−102
2.23.4
Spoiler Control
2−105
2.23.5
Yaw Control
2−107
2.23.6
Direct Lift Control
2−109
2.24
DIGITAL FLIGHT CONTROL SYSTEM
2−109
2.24.1
Stability Augmentation System
2−110
2.24.2
Voltage Monitoring
2−125
2.24.3
Autopilot
2−125
2.24.4
Pilot Relief and Guidance Modes
2−126
2.24.5
DFCS Test
2−129
2.24.6
DFCS Control Panel Fault Reporting
2−131
2.25
LANDING GEAR SYSTEMS
2−132
2.25.1
Landing Gear Handle
2−132
2.25.2
Main Landing Gear
2−133
13
ORIGINAL
NAVAIR 01−F14AAD−1
Page
No.Ă
2.25.3
Nose Landing Gear
2−133
2.25.4
Landing Gear Normal Operation
2−135
2.25.5
Emergency Gear Extension
2−136
2.26
WHEELBRAKE SYSTEM
2−136
2.26.1
Brake Characteristics
2−138
2.26.2
Normal Braking
2−138
2.26.3
Antiskid
2−138
2.26.4
Auxiliary Brake
2−140
2.26.5
BRAKES Warning Light
2−140
2.26.6
Parking Brake
2−140
2.26.7
Wheel Antirotation
2−141
2.27
NOSEWHEEL STEERING SYSTEM
2−141
2.27.1
Nosewheel Steering Control
2−141
2.27.2
Nosewheel Centering
2−143
2.27.3
Shimmy Damping
2−143
2.28
NOSEGEAR CATAPULT SYSTEM
2−143
2.28.1
Nose Strut Kneel
2−143
2.28.2
Launch Bar
2−145
2.28.3
Holdback Fitting
2−145
2.29
ARRESTING HOOK SYSTEM
2−145
2.29.1
Arresting Hook Operation
2−145
2.30
ENVIRONMENTAL CONTROL SYSTEM
2−148
2.30.1
ECS Air Sources
2−148
2.30.2
Cockpit Air−Conditioning
2−151
2.30.3
Electronic Equipment Cooling
2−152
2.30.4
Pressurization
2−152
2.30.5
Windshield Air and Anti−Ice
2−154
2.30.6
Gun−Gas Purging
2−154
2.30.7
Degraded ECS Operation
2−154
2.31
OXYGEN SYSTEM
2−157
2.31.1
On−Board Oxygen Generating System (OBOGS)
2−157
2.31.2
Backup Oxygen System (BOS)
2−159
2.31.3
BOS Pressure Indicator
2−160
2.31.4
Emergency Oxygen Supply
2−160
2.32
PITOT−STATIC SYSTEM
2−160
2.32.1
Pitot−Static Heat
2−160
2.33
CONTROL AND DISPLAY SYSTEM
2−161
2.33.1
Display Types
2−161
2.33.2
Display Processors
2−169
2.33.3
System Operation
2−169
2.33.4
Heads−Up Display (HUD)
2−169
2.33.5
Multistatus Indicator (MSI)
2−170
2.33.6
Multifunction Displays (MFD)
2−174
2.33.7
Cursor Controls
2−174
2.33.8
Displays, Formats, and Symbology
2−176
2.33.9
MFD Formats
2−197
ORIGINAL
14
NAVAIR 01-F14AAD-1
Page
No.
2.34
DATA ENTRY UNIT
2-242
2.34.1
Data Entry Unit Operating Modes
2-242
2.34.2
DEU Menu Pages
2-248
2.35
FLIGHT INSTRUMENTS
2-248
2.35.1
Standby Attitude Indicator
2-248
2.35.2
Standby Airspeed Indicator
2-250
2.35.3
Standby Altimeter
2-250
2.35.4
AN/APN-194(V) Radar Altimeter System
2-250
2.35.5
Vertical Velocity Indicator
2-251
2.35.6
Standby Compass
2-251
2.35.7
Clock
2-251
2.36
ANGLE-OF-ATTACK SYSTEM
2-251
2.36.1
AOA Test
2-251
2.36.2
AOA Indicator
2-251
2.36.3
AOA Indexer
2-251
2.36.4
Approach Lights
2-251
2.37
CANOPY SYSTEM
2-254
2.37.1
Canopy Operation
2-255
2.38
EJECTION SYSTEM
2-256a
2.38.1
Ejection Seat
2-258
2.38.2
Command Ejection Lever
2-263
2.38.3
Ejection Initiation
2-263
2.38.4
Seat Operation After Ejection
2-265
2.39
LIGHTING SYSTEM
2-265
2.39.1
Exterior Lights
2-265
2.39.2
Interior Lights
2-268
2.39.3
Warning and Indicator Lights
2-269
2.40
STORES MANAGEMENT SYSTEM/JETTISON
2-278
2.40.1
SMS Weapons Replaceable Assemblies
2-278
2.40.2
Multistatus Indicator (MSI)
2-279
2.40.3
Stores Jettison Modes
2-279
2.41
MISCELLANEOUS EQUIPMENT
2-283
2.41.1
Boarding Ladder
2-283
2.41.2
Nose Radome
2-283
2.41.3
Systems Test and System Power Ground Panel
2-283
2.41.4
External Baggage Container (CNU-188/A)
2-284
CHAPTER
3 — SERVICING AND HANDLING
3.1
SERVICING DATA
3-1
3.1.1
Ground Refueling
3-1
3.1.2
Engine Oil
3-4
3.1.3
Integrated Drive Generator Oil
3-4
3.1.4
Hydraulic Systems
3-4
3.1.5
Pneumatic Systems
3-8
3.1.6
Backup Oxygen Supply
3-8
15
CHANGE 1
NAVAIR 01−F14AAD−1
Page
No.Ă
3.2
GROUND HANDLING
3−8
3.2.1
Danger Areas
3−8
3.2.2
Radar Radiation Areas
3−8
3.2.3
Towing Turn Radii and Ground Clearances
3−15
3.2.4
Tiedown Points
3−15
CHAPTER 4 OPERATING LIMITATIONS
4.1
LIMITATIONS
4−1
4.1.1
Engine Limits
4−1
4.1.2
Starter Limits
4−1
4.1.3
Airstart Envelope
4−1
4.1.4
Crosswind Limits
4−1
4.1.5
Ground Operations Limits
4−1
4.1.6
Ejection Seat Operation Limits
4−1
4.1.7
Autopilot Limits
4−1
4.2
AIRSPEED LIMITATIONS
4−1
4.2.1
Maximum Airspeeds
4−5
4.3
ACCELERATION LIMITS
4−5
4.3.1
Cruise Configuration
4−5
4.3.2
Approach Configuration
4−5
4.4
ANGLE−OF−ATTACK LIMITS
4−5
4.4.1
Cruise Configuration
4−5
4.4.2
Approach Configuration
4−10
4.5
MANEUVERING LIMITS
4−10
4.5.1
Approach Configuration
4−10
4.5.2
Cruise Configuration
4−10
4.5.3
Rolling Limits
4−10
4.5.4
Sideslip Limits
4−10
4.5.5
Prohibited Maneuvers
4−10
4.6
SAS LIMITS
4−13
4.7
TAKEOFF AND LANDING FLAP AND SLAT AND TRANSITION LIMITS
4−13
4.7.1
Clean and Symmetric Stores Loading
4−13
4.7.2
External Stores Loading With Up to 66,000 Inch−Pounds (5,500 Foot−Pounds) Asymmetry
(AIM−7 on Stations 1B or 8B equals 63,000 inch−pounds)
4−18
4.7.3
External Stores Loading With Greater Than 66,000 Inch−Pounds (5,500 Foot−Pounds) Asymmetry
4−18
4.8
GROSS WEIGHT LIMITS Ċ TAKEOFF, LAUNCH, AND LANDING
4−18
4.9
BARRICADE ENGAGEMENT LIMITS
4−18
4.10
CENTER OF GRAVITY POSITION LIMITS
4−18
ORIGINAL
16
NAVAIR 01−F14AAD−1
Page
No.Ă
4.11
EXTERNAL STORES AND GUN LIMITS
4−19
4.11.1
280−Gallon External Fuel Tank Limits
4−19
4.11.2
External Baggage Container (CNU−188/A)
4−19
4.11.3
Gun Burst Limits
4−19
4.11.4
Launch Limits
4−19
4.11.5
Jettison Limits
4−20
4.12
BANNER TOWING RESTRICTIONS
4−20
4.13
TACTICAL AIR RECONNAISSANCE POD SYSTEM LIMITATIONS
4−21
4.13.1
Authorized Stores Loading
4−21
4.13.2
Interim AIM−7 as Ballast
4−21
PART II INDOCTRINATION
CHAPTER 5 INDOCTRINATION
5.1
GROUND TRAINING SYLLABUS
5−1
5.1.1
Minimum Ground Training Syllabus
5−1
5.1.2
Waiving of Minimum Ground Training Requirements
5−1
5.2
FLIGHT TRAINING SYLLABUS
5−2
5.2.1
Flightcrew Flight Training Syllabus
5−2
5.2.2
Flightcrew Flight Training Phases
5−2
5.3
OPERATING CRITERIA
5−2
5.3.1
Ceiling/Visibility Requirements
5−2
5.3.2
NATOPS Qualification and Currency Requirements
5−3
5.3.3
Requirements for Various Flight Phases
5−4
5.3.4
Mission Commander
5−4
5.3.5
Minimum Flightcrew Requirements
5−5
5.4
FLIGHT CREWMEMBER FLIGHT EQUIPMENT REQUIREMENTS
5−5
PART III NORMAL PROCEDURES
CHAPTER 6 FLIGHT PREPARATION
6.1
PREFLIGHT BRIEFING
6−1
6.1.1
Administration
6−1
6.1.2
Missions
6−1
CHAPTER 7 SHORE−BASED PROCEDURES
7.1
CHECKLISTS
7−1
7.1.1
Tactical Air Reconnaissance Pod System
7−1
7.2
EXTERIOR INSPECTION
7−1
7.2.1
Area Around Aircraft
7−1
7.2.2
Foreign Object Damage and Leak Inspection
7−1
7.2.3
Ground Safety Devices and Covers
7−1
7.2.4
Surface Condition
7−2
17
ORIGINAL
NAVAIR 01−F14AAD−1
Page
No.Ă
7.2.5
Security of Panels
7−2
7.2.6
Leaks
7−2
7.2.7
Movable Surfaces
7−2
7.2.8
Inspection Areas
7−2
7.3
EJECTION SEAT INSPECTION
7−6
7.4
PILOT PROCEDURES
7−8
7.4.1
Interior Inspection Ċ Pilot
7−8
7.4.2
Prestart Ċ Pilot
7−10
7.4.3
Engine Start Ċ Pilot
7−11
7.4.4
Poststart Ċ Pilot
7−13
7.4.5
Taxiing
7−18
7.4.6
Taxi Ċ Pilot
7−20
7.4.7
Takeoff
7−20
7.4.8
Flaps−Up Takeoff
7−21
7.4.9
Formation Takeoff
7−22
7.4.10
Takeoff Aborted
7−22
7.4.11
Takeoff Checklist
7−22
7.4.12
Ascent Checklist
7−23
7.4.13
In−Flight BIT
7−23
7.4.14
Preland and Descent
7−23
7.4.15
Pattern Entry
7−24
7.4.16
Landing
7−24
7.4.17
Landing Checklist
7−26
7.4.18
Postlanding Ċ Pilot
7−27
7.5
RIO PROCEDURES
7−28
7.5.1
Interior Inspection Ċ RIO
7−28
7.5.2
Prestart Ċ RIO
7−29
7.5.3
Engine Start Ċ RIO
7−30
7.5.4
Poststart Ċ RIO
7−30
7.5.5
Taxi Ċ RIO
7−32
7.5.6
In−Flight Reconnaissance System Check Ċ RIO
7−32
7.5.7
TARPS Degraded Mode Procedures
7−33
7.5.8
Postlanding Ċ RIO
7−34
7.6
HOT REFUELING PROCEDURES
7−34
7.7
DECK−LAUNCHED INTERCEPT PROCEDURES
7−35
7.7.1
Pilot Procedures
7−35
7.7.2
RIO Procedures
7−35
7.8
HOT SWITCH PROCEDURES
7−36
7.8.1
On−Deck, Maintenance Troubleshooting
7−36
7.8.2
Hot Switch Procedures
7−36
7.9
FIELD CARRIER LANDING PRACTICE
7−36
7.9.1
Preflight Inspection
7−36
7.9.2
Takeoff
7−37
7.9.3
Radio Procedures and Pattern Entry
7−37
7.9.4
Pattern
7−37
7.9.5
Night FCLP
7−37
ORIGINAL
18
NAVAIR 01−F14AAD−1
Page
No.Ă
CHAPTER 8 CARRIER−BASED PROCEDURES
8.1
CARRIER PREFLIGHT
8−1
8.1.1
Launch
8−1
8.1.2
Briefing
8−1
8.1.3
Preflight
8−1
8.2
START AND POSTSTART
8−1
8.2.1
Carrier Alignment
8−1
8.2.2
SAHRS Standalone Carrier Alignment
8−3
8.2.3
GPS On−Deck IFA Alignment
8−3
8.3
TAXIING
8−4
8.3.1
Nosewheel Steering
8−4
8.3.2
Taxi Speed
8−4
8.3.3
Final Checker Aboard CV
8−4
8.4
CATAPULT HOOKUP (DAY)
8−4
8.4.1
Catapult Trim Requirements
8−5
8.4.2
Catapult Launch
8−5
8.4.3
Catapult Abort Procedures (Day)
8−6
8.5
LANDING
8−7
8.5.1
Carrier Landing Pattern (VFR)
8−7
8.5.2
Manual Approach Technique
8−7
8.5.3
Approach Power Compensator Technique
8−9
8.5.4
Waveoff Technique
8−9
8.5.5
Bolter Technique
8−9
8.5.6
Bingo Fuel
8−9
8.5.7
Arrested Landing and Exit From the Landing Area
8−10
8.5.8
Carrier−Controlled Approaches
8−10
8.5.9
Hold Phase
8−10
8.5.10
Platform
8−10
8.5.11
Ten−Mile DME Fix
8−10
8.5.12
Six−Mile DME Fix
8−10
8.5.13
Meatball Contact
8−12
8.6
WAVEOFF AND BOLTER
8−12
8.7
NIGHT FLYING
8−12
8.7.1
Briefing
8−12
8.7.2
Preflight
8−12
8.7.3
Poststart
8−12
8.7.4
Taxi
8−12
8.7.5
Catapult Hookup (Night)
8−12
8.7.6
Catapult Launch
8−12
8.7.7
Catapult Abort Procedures (Night)
8−13
8.7.8
Arrested Landing and Exit From Landing Area (Night)
8−13
CHAPTER 9 SPECIAL PROCEDURES
9.1
IN−FLIGHT REFUELING PROCEDURES
9−1
9.1.1
In−Flight Refueling Controls
9−1
9.1.2
In−Flight Refueling Checklist
9−1
9.1.3
In−Flight Refueling Techniques
9−1
19
ORIGINAL
NAVAIR 01−F14AAD−1
Page
No.Ă
9.2
FORMATION FLIGHT
9−2
9.2.1
Parade Formation
9−2
9.2.2
Break Formation
9−3
9.2.3
Diamond Four−Plane Formation
9−3
9.2.4
Cruise Formation
9−3
9.2.5
Aircraft Lighting During Night Formation Flight
9−4
9.3
BANNER TOWING
9−4
9.3.1
Ground Procedures
9−4
9.3.2
Shipboard Procedures
9−4
9.3.3
Flight Procedures
9−4
9.4
FUEL MANAGEMENT SYSTEM OPERATIONAL CHECK
9−7
CHAPTER 10 FUNCTIONAL CHECKFLIGHT PROCEDURES
10.1
FUNCTIONAL CHECKFLIGHTS
10−1
10.2
CHECKFLIGHT PROCEDURES
10−1
10.2.1
General Conduct
10−1
10.3
FUNCTIONAL CHECKFLIGHT PROCEDURES (PILOT)
10−2
10.3.1
Prestart
10−2
10.3.2
Start
10−2
10.3.3
Poststart
10−6
10.3.4
Taxi
10−13
10.3.5
Engine Runup
10−13
10.3.6
Takeoff and Climb
10−14
10.3.7
Ten Thousand Foot Checks
10−15
10.3.8
Fifteen Thousand Foot Checks
10−16
10.3.9
Ten Thousand Foot Checks
10−19
10.3.10
Airstarts (Twenty Thousand Feet)
10−20
10.3.11
Climb to Thirty−Five Thousand Feet
10−20
10.3.12
High−Speed Dash (Thirty−Five Thousand Feet)
10−21
10.3.13
Zoom Climb (Forty Thousand Feet)
10−22
10.3.14
Twenty Thousand Foot Checks
10−22
10.3.15
Fifteen Thousand Foot Checks
10−24
10.3.16
Approach and Landing
10−27
10.4
FUNCTIONAL CHECKFLIGHT PROCEDURES (RIO)
10−27
10.4.1
Prestart
10−27
10.4.2
Poststart
10−27
10.4.3
Taxi
10−28
10.4.4
Takeoff and Climb
10−28
10.4.5
Ten Thousand Foot Checks
10−28
10.4.6
Fifteen Thousand Foot Checks
10−28
10.4.7
Twenty−Five Thousand Foot Checks
10−29
10.4.8
Climb to Thirty−Five Thousand Feet
10−29
10.4.9
High−Speed Dash (Thirty−Five Thousand Feet)
10−29
10.4.10
Descent/Twenty Thousand Foot Checks
10−29
10.4.11
Approach
10−31
10.4.12
Landing
10−32
10.4.13
In Chocks
10−32
10.4.14
Postflight
10−32
ORIGINAL
20
NAVAIR 01−F14AAD−1
Page
No.Ă
PART IV FLIGHT CHARACTERISTICS
CHAPTER 11 FLIGHT CHARACTERISTICS
11.1
PRIMARY FLIGHT CONTROLS
11−1
11.1.1
Pitch Control
11−1
11.1.2
Roll Control
11−1
11.1.3
Directional (Yaw) Control
11−1
11.1.4
Stability Augmentation System
11−1
11.2
SECONDARY FLIGHT CONTROLS
11−2
11.2.1
Maneuver Flaps and Slats
11−2
11.2.2
Landing Flaps, Slats, and DLC
11−2
11.2.3
Speedbrakes
11−2
11.3
GENERAL FLIGHT CHARACTERISTICS
11−2
11.3.1
Static Longitudinal Stability
11−2
11.3.2
Dynamic Longitudinal Response Characteristics
11−2
11.3.3
Maneuvering Stick Force
11−2
11.3.4
Roll Performance
11−3
11.3.5
Roll Response
11−3
11.3.6
Dutch Roll
11−3
11.3.7
Trim Characteristics
11−4
11.4
ASYMMETRIC THRUST FLIGHT CHARACTERISTICS IN COMBAT
AND CRUISE CONFIGURATION
11−4
11.4.1
General
11−4
11.5
ENGINE STALLS AND FLAMEOUT
11−5
11.5.1
Medium and High−Subsonic Airspeed
11−5
11.5.2
Low Subsonic Airspeed
11−6
11.6
HIGH ANGLE OF ATTACK FLIGHT CHARACTERISTICS
11−6
11.6.1
Directional Stability
11−6
11.6.2
Dihedral Effect
11−6
11.6.3
External Stores
11−6
11.6.4
DFCS Stability Augmentation System
11−6
11.6.5
Maneuvering Flaps and Slats
11−7
11.6.6
Lateral Control Reversal
11−7
11.6.7
Miscellaneous
11−9
11.6.8
Stall Characteristics
11−9
11.6.9
Vertical Stalls
11−9
11.6.10
DFCS Degraded Control Modes
11−9
11.7
DEPARTURE FROM CONTROLLED FLIGHT
11−10
11.7.1
General
11−10
11.7.2
Lateral Stick−Induced Departures
11−13
11.7.3
Rudder−Induced Departures
11−13
11.7.4
Multi−Axis Control−Induced Departures
11−13
11.7.5
Asymmetric−Thrust−Induced Departures
11−14
11.7.6
Accelerated Departures
11−14
11.7.7
Inertia Coupling
11−14
11.7.8
Departure Recovery
11−15
11.7.9
Upright Departure Recovery
11−15
21
ORIGINAL
NAVAIR 01−F14AAD−1
Page
No.Ă
11.7.10
Flat Spin
11−20
11.7.11
Negative AOA Departures
11−20
11.7.12
Inverted Stall/Departure
11−20
11.7.13
Inverted Spin
11−21
11.8
TAKEOFF AND LANDING CONFIGURATION FLIGHT CHARACTERISTICS
11−21
11.8.1
Baseline Flight Characteristics
11−21
11.8.2
Crosswind Landings
11−22
11.8.3
Normal Stalls
11−22
11.8.4
Stall Recovery
11−22
11.8.5
Asymmetric Thrust Flight Characteristics
11−22
11.8.6
Degraded Approach Configuration
11−27
11.8.7
Outboard Spoiler Module Failure
11−27
11.8.8
SAS Off
11−27
11.8.9
Aft Wing−Sweep Landings
11−27
11.8.10
DFCS Degraded Control Modes
11−30
11.9
ASYMMETRIC WING SWEEP
11−31
11.9.1
Wing−Sweep Design Limitations
11−31
11.9.2
Asymmetric Wing−Sweep Flight Characteristics
11−32
11.10
DUAL HYDRAULIC FAILURES BACKUP FLIGHT CONTROL MODULE
FLIGHT CHARACTERISTICS
11−33
11.10.1
General
11−33
11.10.2
Low Mode Cruise and Formation
11−36
11.10.3
High Mode Cruise and Formation
11−36
11.10.4
In−Flight Refueling
11−36
11.10.5
Landing
11−37
11.10.6
BFCM Thermal Durability
11−37
11.11
FLIGHT CHARACTERISTICS WITH AFT CG LOCATIONS
11−38
11.11.1
Store Effects on Cg Location
11−38
11.11.2
Wing−Sweep Effects on Stability
11−38
11.11.3
Cruise and Combat Flight Characteristics With Aft Cg
11−38
11.11.4
Takeoff and Landing Configuration Flight Characteristics with Aft Cg
11−38
PART V EMERGENCY PROCEDURES
CHAPTER 12 GROUND EMERGENCIES
12.1
ON−DECK EMERGENCIES
12−1
12.1.1
Engine Fire on the Deck
12−1
12.1.2
Abnormal Start
12−1
12.1.3
START VALVE Light After Engine Start
12−1
12.1.4
Uncommanded Engine Acceleration on Deck
12−1
12.1.5
Ground Egress Without Parachute and Survival Kit
12−2
12.1.6
Emergency Entrance
12−2
12.1.7
Weight On−Off Wheels Switch Malfunction
12−2
12.1.8
Binding/Jammed Flight Controls On Deck
12−4
12.1.9
Brake Failure at Taxi Speed
12−4
ORIGINAL
22
NAVAIR 01−F14AAD−1
Page
No.
CHAPTER 13 Ċ TAKEOFF EMERGENCIES
13.1
ABORTED TAKEOFF
13−1
13.1.1
Aborted Takeoff Checklist
13−1
13.2
SINGLE−ENGINE FAILURE FIELD/CATAPULT LAUNCH/WAVEOFF
13−2
13.2.1
Angle−of−Attack/Endspeed Consideration
13−2
13.2.2
Rate of Climb Consideration
13−2
13.2.3
Stores Jettison Considerations
13−2
13.2.4
Aircrew Coordination
13−2
13.2.5
Single−Engine Failure Field/Catapult Launch/Waveoff
13−3
13.3
BLOWN TIRE DURING TAKEOFF
13−3
13.3.1
Blown Tire During Takeoff; Takeoff Aborted or After Landing Touchdown
13−3
13.3.2
Blown Tire During Takeoff; Takeoff Continued or After Landing Go−Around
13−3
CHAPTER 14 Ċ IN−FLIGHT EMERGENCIES
14.1
COMMUNICATIONS FAILURE
14−1
14.1.1
Flightcrew Attention Signals
14−1
14.1.2
COMM−NAV Emergency Procedures
14−1
14.2
PITOT−STATIC SYSTEM FAILURES
14−1
14.3
EMERGENCY JETTISON
14−2
14.4
FIRE LIGHT AND/OR FIRE IN FLIGHT
14−4
14.5
ENGINE EMERGENCIES
14−5
14.5.1
Compressor Stall
14−5
14.5.2
Airstarts
14−7
14.5.3
Single−Engine Flight Characteristics
14−11
14.5.4
Engine Overspeed (N1 or N2 OSP Legend)
14−12
14.5.5
Engine START VALVE Light
14−12
14.5.6
Engine Transfer to SEC Mode
14−12
14.5.7
Uncommanded SEC Mode Rpm Decay
14−13
14.5.8
Uncommanded Engine Acceleration Airborne (No Throttle Movement)
14−15
14.5.9
Exhaust Nozzle Failed (No Nozzle Response to Throttle Movement)
14−15
14.5.10
Stuck/Jammed Throttle(s)
14−15
14.5.11
AICS Malfunctions
14−16
14.5.12
INLET ICE Light
14−17
14.5.13
Oil System Malfunction
14−17
14.5.14
RATS Operation In Flight
14−17
14.6
FUEL SYSTEM MALFUNCTIONS
14−18
14.6.1
Fuel Pressure Caution Lights/Low Fuel Pressure Warning Tone
14−18
14.6.2
L or R FUEL LOW Light
14−19
14.6.3
Fuel Transfer Failures
14−19
14.6.4
Uncommanded Dump
14−19
14.6.5
Fuel Leak
14−19
14.6.6
Fuel Imbalance/Fuel Quantity Balancing
14−20
14.7
ELECTRICAL FAILURE
14−20
14.7.1
Generator Failure
14−20
14.7.2
Double Generator Failure
14−20a
23
CHANGE 2
NAVAIR 01−F14AAD−1
Page
No.Ă
14.7.3
Double Transformer−Rectifier Failure
14−22
14.7.4
TRANS/RECT Light
14−22
14.7.5
Electrical Fire
14−22
14.7.6
Total Electrical Failure
14−24
14.8
ECS MALFUNCTIONS/FAILURES
14−25
14.8.1
ECS Leak/Elimination of Smoke and Fumes
14−25
14.8.2
COOLING AIR Light
14−27
14.8.3
TARPS ECS Lights Illuminate
14−27
14.8.4
SENSOR COND Light Illuminated and/or PUMP Phase Circuit Breakers Popped
or APG−71 PM Acronym
14−28
14.8.5
Cockpit Temperature Control Malfunction
14−28
14.8.6
Cockpit Overpressurization on Deck
14−28
14.8.7
CABIN PRESS Light
14−28
14.8.8
WSHLD HOT Light
14−28
14.9
OXYGEN SYSTEM FAILURE
14−29
14.9.1
OBOGS Light
14−29
14.9.2
B/U OXY LOW Light (Both Cockpits)
14−29
14.9.3
B/U OXY LOW Light (Pilot Only)
14−30
14.9.4
B/U OXY LOW Light (RIO Only)
14−30
14.10
LAD/CANOPY LIGHT AND/OR LOSS OF CANOPY
14−30
14.10.1
LAD/CANOPY Light With RIO CANOPY Light/Canopy Loss
14−30
14.10.2
LAD/CANOPY Light Without RIO CANOPY Light
14−31
14.11
HYDRAULIC SYSTEM MALFUNCTIONS
14−31
14.11.1
Combined Pressure Approximately 2,400 to 2,600 Psi
14−31
14.11.2
Flight Pressure Approximately 2,400 to 2,600 Psi
14−31
14.11.3
Combined Pressure Zero
14−32
14.11.4
Flight Pressure Zero
14−33
14.11.5
Both Combined and Flight Pressure Zero
14−33
14.11.6
Backup Flight Module Malfunction
14−35
14.11.7
Low Brake Accumulator Pressure
14−35
14.12
FLIGHT CONTROL FAILURES OR MALFUNCTIONS
14−35
14.12.1
Controllability Check
14−35
14.12.2
Uncommanded Roll and/or Yaw
14−37
14.12.3
DFCS Flight Control Failures or Malfunctions
14−38
14.12.4
Rudder Authority Failure
14−40
14.12.5
Horizontal Tail Authority Failure
14−42
14.12.6
Spoiler Malfunction
14−42
14.12.7
FLAP Light
14−45
14.12.8
Flap and Slat Asymmetry
14−46
14.12.9
WING SWEEP Lights
14−47
14.12.10
Unscheduled Wing Sweep
14−47
14.12.11
CADC Light
14−47
14.12.12
AUTOPILOT Light
14−48
14.12.13
Weight On−Off Wheels Switch Malfunction
14−48
14.13
DEPARTURE/SPIN
14−49
14.13.1
Vertical Recovery
14−49
14.13.2
Upright Departure/Flat Spin
14−49
14.13.3
Inverted Departure/Spin
14−50
ORIGINAL
24
NAVAIR 01−F14AAD−1
Page
No.Ă
CHAPTER 15 LANDING EMERGENCIES
15.1
DUAL−ENGINE LANDING, ONE OR BOTH ENGINES IN SECONDARY MODE
15−1
15.2
SINGLE−ENGINE LANDING PRIMARY MODE
15−1
15.3
SINGLE−ENGINE LANDING SECONDARY MODE
15−3
15.3.1
Single−Engine Landing Ċ SEC Mode
15−4
15.4
LANDING GEAR EMERGENCIES
15−6
15.4.1
Landing Gear Emergency Lowering
15−6
15.4.2
Landing Gear Malfunctions
15−8
15.4.3
LAUNCH BAR Light
15−9
15.5
BLOWN−TIRE LANDING
15−10
15.6
FLAP AND SLAT LANDING EMERGENCIES
15−10
15.6.1
No−Flaps and No−Slats Landing
15−10
15.6.2
Auxiliary Flap Failure
15−10
15.7
WING−SWEEP EMERGENCIES
15−11
15.7.1
Aft Wing−Sweep Landings
15−11
15.7.2
Asymmetric Wing Sweep
15−11
15.8
AFT HUNG ORDNANCE LANDINGS
15−16
15.8.1
Landing with Aft Hung Ordnance
15−17
15.9
FIELD ARRESTMENTS
15−17
15.9.1
Field Arresting Gear
15−17
15.9.2
Short−Field Arrestment
15−18
15.9.3
Long−Field Arrestment
15−18
15.9.4
Engaging Speeds
15−18
15.10
BARRICADE ARRESTMENT
15−18
15.11
ARRESTING HOOK EMERGENCY DOWN
15−21
15.12
FORCED LANDING
15−21
15.13
GROUND ROLL BRAKING FAILURES
15−21
CHAPTER 16 EJECTION
16.1
EJECTION
16−1
16.1.1
Ejection Envelope
16−1
16.1.2
Ejection Preparation
16−5
16.1.3
Ejection Initiation
16−6
16.2
MANUAL BAILOUT
16−6
16.3
SURVIVAL/POSTEJECTION PROCEDURES
16−6
16.3.1
Manual Man/Seat Separation
16−7
16.3.2
Survival Kit Deployment
16−7
16.3.3
Parachute Steering
16−9
16.3.4
Parachute Landing Preparation
16−9
16.3.5
Raft Boarding
16−9
25
ORIGINAL
NAVAIR 01−F14AAD−1
Page
No.Ă
PART VI ALL−WEATHER OPERATIONS
CHAPTER 17 INSTRUMENT PROCEDURES
17.1
AUTOMATIC CARRIER LANDING SYSTEM
17−1
17.1.1
Mode I
17−1
17.1.2
Mode II
17−1
17.1.3
Mode III
17−1
17.1.4
Flight Director
17−1
17.2
AIRCRAFT SUBSYSTEMS
17−2
17.2.1
Data Link
17−2
17.2.2
Digital Flight Control System
17−2
17.2.3
Radar Beacon (AN/APN−154)
17−2
17.2.4
ACLS Beacon Augmentor (R−1623)
17−2
17.2.5
Approach Power Compensator Performance
17−3
17.2.6
ACLS/ILS Displays (MFD and HUD)
17−3
17.2.7
Instrument Landing System (AN/ARA−63)
17−5
17.3
SURFACE SUBSYSTEMS
17−8
17.3.1
Automatic Landing System (AN/SPN−42)
17−8
17.3.2
Instrument Landing System (AN/SPN−41)
17−8
17.4
ACLS PROCEDURES
17−10
17.4.1
Preflight
17−10
17.4.2
Poststart Checks
17−10
17.4.3
Approach Phase
17−10
17.4.4
Landing Phase
17−12
CHAPTER 18 EXTREME WEATHER OPERATIONS
18.1
ICE AND RAIN
18−1
18.1.1
Icing
18−1
18.1.2
Rain
18−1
18.2
HYDROPLANING
18−2
18.2.1
Dynamic Hydroplaning
18−2
18.2.2
Viscous Hydroplaning
18−3
18.2.3
Combined Dynamic andViscous Hydroplaning
18−3
18.2.4
Reverted Rubber Skids
18−3
18.2.5
Landing On Wet Runway
18−4
18.3
TURBULENCE AND THUNDERSTORMS
18−4
18.3.1
In the Storm
18−4
18.4
COLD−WEATHER OPERATIONS
18−4
18.4.1
Preflight
18−5
18.4.2
Engine Start
18−5
18.4.3
Taxiing
18−5
18.4.4
Takeoff
18−5
18.4.5
Landing
18−6
18.4.6
After Landing
18−6
18.4.7
Before Leaving Aircraft
18−6
ORIGINAL
26
NAVAIR 01−F14AAD−1
Page
No.Ă
18.5
HOT−WEATHER AND DESERT OPERATIONS
18−6
18.5.1
Taxiing
18−6
18.5.2
Takeoff
18−6
18.5.3
Landing
18−6
PART VII COMMUNICATIONS−NAVIGATION EQUIPMENT AND PROCEDURES
CHAPTER 19 COMMUNICATIONS
19.1
COMMUNICATIONS AND ASSOCIATED EQUIPMENT
19−1
19.1.1
Communications Antennas
19−1
19.1.2
Communications Antenna Selection
19−1
19.1.3
Mutual Interference
19−1
19.2
INTERCOMMUNICATIONS
19−1
19.2.1
Audio Warning Signals
19−5
19.2.2
Pilot Tone Volume/TACAN Command Panel
19−7
19.3
V/UHF RADIO (AN/ARC−182)
19−7
19.3.1
Preset Channel(s) Load
19−7
19.3.2
Built−In Test (BIT)
19−7
19.3.3
Have Quick (Antijam) Mode
19−7
19.3.4
Have Quick Load Instructions
19−12
19.3.5
Radio Frequency Control/Indicators (RFCI)
19−18
19.4
V/UHF AUTOMATIC DIRECTION FINDER (OA−8697)
19−18
19.5
UHF VOICE SECURITY EQUIPMENT (TSEC/KY−58)
19−19
19.5.1
KY−58 Operation
19−19
19.5.2
Prelaunch
19−19
19.5.3
Postlaunch
19−19
19.5.4
After Landing
19−19
19.6
JOINT TACTICAL INFORMATION DISTRIBUTION SYSTEM
19−19
19.6.1
JTIDS Terminal
19−21
19.6.2
JTIDS Controls
19−23
19.6.3
Mission Data Loader (MDL)
19−23
19.6.4
JTIDS System Operation
19−23
19.7
IN−FLIGHT VISUAL COMMUNICATIONS
19−27
19.8
GROUND HANDLING SIGNALS
19−27
CHAPTER 20 Ċ NAVIGATION SYSTEM
20.1
NAVIGATION SYSTEM
20−1
20.1.1
AN/ASN−139 Inertial Navigation Set
20−1
20.1.2
Miniature Airborne GPS Receiver (MAGR)
20−3
20.1.3
AN/USN−2(V) Standard Attitude Heading Reference System (SAHRS)
20−5
20.1.4
Mission Computer System (MCS)
20−5
20.1.5
Navigation Data Initialization
20−6
20.1.6
Displays Subsystem
20−6
20.1.7
Programmable Tactical Information Display (PTID)
20−6
27
ORIGINAL
NAVAIR 01-F14AAD-1
Page
No.
20.1.8
Converter Interface Unit (CIU)
20-6
20.1.9
Standard Central Air Data Computer (SCADC)
20-6
20.1.10
AN/ARN-118 Tactical Air Navigation (TACAN) System or
AN/URC-107 Joint Tactical Information Distribution System (JTIDS)
20-8
20.1.11
AN/ASW-27C Data Link (D/L)
20-11
20.1.12
UHF Automatic Direction Finder (ADF)
20-11
20.1.13
Bearing Distance Heading Indicator (BDHI)
20-11
20.1.14
AN/URC-107 Joint Tactical Information Distribution System (JTIDS)
20-12
20.2
NAVIGATION SYSTEM DATA DISTRIBUTION
20-12
20.2.1
Navigation Data Display
20-12
20.3
NAVIGATION SYSTEM OPERATION
20-20
20.3.1
GPS Operation
20-20
20.3.2
Navigation Modes
20-27
20.3.3
MAGR Initialization
20-37
20.3.4
INS and SAHRS Concurrent Alignment
20-38
20.3.5
Concurrent Carrier Alignment
20-45
20.3.6
Initially Entered Navigation Parameters
20-52
20.3.7
Navigation Database
20-55
20.3.8
Flight Plan Management
20-59
20.3.9
Tactical Navigation
20-72
CHAPTER
21 — IDENTIFICATION
21.1
IDENTIFICATION TRANSPONDER (AN/APX-100)
21-1
21.1.1
IFF Transponder
21-1
21.1.2
Altitude Computations
21-6
21.2
IFF INTERROGATOR (AN/APX-76)
21-6
21.2.1
IFF Self-Test
21-7
PART VIII — WEAPON SYSTEMS
CHAPTER 22 — TARPS SUBSYSTEM
22.1
RECONNAISSANCE SYSTEM
22-1
22.1.1
TARPS Pod
22-2
22.1.2
Serial Frame Camera
22-2
22.1.3
Panoramic Camera
22-2
22.1.4
Data Display System
22-2
22.1.5
TARPS Environmental Control System
22-2
22.1.6
Controller Processor Signal Unit
22-2
22.2
DISPLAY SYSTEM
22-2
22.3
TARPS EQUIPMENT CIRCUIT BREAKERS
22-2
CHANGE 1
28
NAVAIR 01-F14AAD-1
Page
No.
22.4
RECONNAISSANCE DISPLAYS AND FORMATS
22-9
22.4.1
MFD RECON DATA Status Format
22-9
22.4.2
Reconnaissance Fault/Problem Reporting
22-9
22.4.3
Reconnaissance Steering Selection
22-11
22.4.4
HUD/VDI Symbology
22-13
22.5
RECONNAISSANCE SYSTEM OPERATION
22-13
22.5.1
Reconnaissance Parameter Entry
22-13
22.5.2
In-Flight Entry of Reconnaissance Waypoint Parameters
22-21
22.5.3
One-Fix Update
22-21
22.5.4
Plotting Command Course/Map Target Leg
22-21
22.5.5
Cycling Sensors
22-21
22.6
PILOT RECONNAISSANCE OPERATION
22-21
22.6.1
Navigation Visual Surface Waypoint Update
22-21
22.6.2
Pilot TARPS Steering
22-21
22.6.3
Identification of Targets Using Television Camera Set
22-22
22.6.4
Altitude (AGL) Mechanization
22-22
22.7
SENSOR CAPABILITIES AND LIMITATIONS
22-22
22.7.1
Lineal Coverage
22-22
22.7.2
Serial Frame Camera
22-22
22.7.3
Panoramic Camera
22-23
22.7.4
Long-Range Oblique Photography Camera (KS-153A With 610-mm Lens)
22-24
22.7.5
Photographic Film
22-26
22.7.6
Digital Data System
22-26
CHAPTER
23 — NAVIGATION COMMAND AND CONTROL GRID
23.1
NAVIGATION COMMAND AND CONTROL GRID
23-1
23.1.1
NAV GRID Data Entry
23-1
23.1.2
NAV GRID Displays
23-3
CHAPTERS 24 TO 36 — (REFER TO NAVAIR 01-F14AAD-1A)
PART IX — FLIGHTCREW COORDINATION
CHAPTER 37 — FLIGHTCREW COORDINATION
37.1
INTRODUCTION
37-1
37.2
PILOT AND RIO RESPONSIBILITIES
37-1
37.2.1
Aircrew Coordination
37-1
37.2.2
Pilot Responsibilities
37-1
37.2.3
Radar Intercept Officer Responsibilities
37-1
37.2.4
Mission Commander
37-1
37.2.5
Specific Responsibilities
37-1
29
CHANGE 1
NAVAIR 01−F14AAD−1
Page
No.Ă
37.3
SPECIAL CONSIDERATIONS
37−4
37.3.1
Functional Checkflights
37−4
37.3.2
Formation Flights
37−4
37.3.3
Training
37−4
37.3.4
SAR
37−4
37.4
PROCEDURES, TECHNIQUES, AND CHECKLISTS
37−4
37.4.1
General
37−4
37.4.2
Pilot
37−5
37.4.3
RIO
37−5
CHAPTER 38 AIRCRAFT SELF−TEST
38.1
AIRCRAFT SELF−TEST OVERVIEW
38−1
38.2
MASTER TEST PANEL CHECKS
38−1
38.2.1
MASTER TEST Switch Operation
38−3
38.3
ON−BOARD CHECKOUT
38−3
38.3.1
Built−in−Test Description
38−7
38.3.2
Test Prerequisites/Restrictions
38−9
38.3.3
Avionic BIT Operation
38−10
38.3.4
Joint Tactical Information Distribution System On−Board Check
38−36
38.4
COOPERATIVE SUPPORT SOFTWARE
38−40
38.4.1
CSS Operation
38−40
38.5
RADAR SYSTEM BUILT−IN TEST
38−47
38.5.1
BIT Modes
38−48
38.5.2
Radar BIT Operation
38−51
38.5.3
Flycatcher
38−70
PART X NATOPS EVALUATION
CHAPTER 39 NATOPS EVALUATION AND QUESTION BANK
39.1
NATOPS EVALUATION PROGRAM
39−1
39.1.1
Concept
39−1
39.1.2
Implementation
39−1
39.1.3
Definitions
39−1
39.2
GROUND EVALUATION
39−2
39.2.1
Open−Book Examination
39−2
39.2.2
Closed−Book Examination
39−2
39.2.3
Oral Examination
39−2
39.2.4
Emergency
39−2
39.2.5
Malfunction
39−2
39.2.6
MFT and WST Procedures Evaluation
39−2
39.2.7
Grading Instructions
39−2
39.3
FLIGHT EVALUATION
39−2
39.3.1
Instrument Flight Evaluation
39−2
ORIGINAL
30
NAVAIR 01-F14AAD-1
Page
No.
39.4
OPERATIONAL DEPLOYABLE SQUADRONS
39-3
39.5
TRAINING AND EVALUATION SQUADRONS
39-3
39.6
FLIGHT EVALUATIONS
39-3
39.6.1
Mission Planning and Briefing
39-3
39.6.2
Preflight and Line Operations
39-3
39.6.3
Taxi and Runup
39-3
39.6.4
(*) Takeoff and Transition
39-3
39.6.5
Climb and Cruise
39-3
39.6.6
(*) Approach and Landing
39-3
39.6.7
Communications
39-3
39.6.8
(*) Emergency and Malfunction Procedures
39-3
39.6.9
Postflight Procedures
39-3
39.6.10
Mission Evaluation
39-3
39.7
RECORD AND REPORTS
39-3
39.7.1
Critique
39-4
39.8
FLIGHT EVALUATION GRADING CRITERIA
39-4
39.8.1
Flight Evaluation Grade Determination
39-4
39.8.2
Final Grade Determination
39-4
39.9
APPLICABLE PUBLICATIONS
39-4
39.10
NATOPS EVALUATION QUESTION BANK
39-4
PART XI — PERFORMANCE DATA (REFER TO NAVAIR 01-F14AAP-1.1)
CHAPTER 40 — TACTICAL IMAGING SET
40.1
AN/AVX-3 TACTICAL IMAGING SET
40-1
40.1.1
Remote Control Unit (RCU)
40-1
40.1.2
Image Transceiver
40-1
40.1.3
Video Tape Recorder (VTR)
40-1
40.1.4
Interface Box
40-3
40.2
OPERATING INSTRUCTIONS
40-3
40.2.1
Powerup Sequence
40-3
40.3
RESETTING RCU AND IMAGE TRANSCEIVER
40-4
40.4
SETTINGS MENUS
40-5
40.4.1
Settings Menus’ Format
40-5
40.4.2
Send-to-Call-Sign-Menu
40-6
40.4.3
Modify Call Sign Menu
40-6
40.4.4
Edit Call Sign Menu
40-6
40.4.5
Send/Delete Function Menu
40-6
40.4.6
Capture Rate Menu
40-6
40.4.7
Capture Time Menu
40-7
40.4.8
Max Key Time
40-7
40.4.9
Automatic Transmit Menu
40-7
40.4.10
Compression Method Menu
40-7
40.4.11
Compression Ratio Menu
40-8
31
CHANGE 1
NAVAIR 01−F14AAD−1
Page
No.
40.4.12
PTAC Quick Start Menu
40−8
40.4.13
Local Call Sign Menu
40−8
40.4.14
Display Brightness Menu
40−9
40.4.15
Image Dimension menu
40−9
40.4.16
View Communications Cable Identification Menu
40−9
40.4.17
EIS Configuration Menu
40−9
40.4.18
Date and Time Menus
40−10
40.4.19
Format SRAM Card Menu
40−10
40.4.20
Waveburst Version Menu
40−10
40.5
POWER DOWN SEQUENCE
40−10
40.6
CAPTURING/COMPRESSING/SAVING/TRANSMITTING/RECEIVING IMAGES
40−10
40.6.1
Voice and Data Modes
40−10
40.6.2
Capturing Images
40−11
40.6.3
Compressing/Saving Images
40−12
40.6.4
Transmitting Images
40−13
40.6.5
Receiving Images
40−13
40.7
VIEWING IMAGES
40−14
40.8
CONTROLLING VTR FUNCTIONS
40−17
40.8.1
Function Operations
40−18
40.9
ERROR MESSAGES
40−19
40.9.1
DEW
40−19
40.9.2
COMMS ERROR
40−19
40.9.3
INTERNAL ERROR
40−19
40.9.4
COMMAND ERROR
40−19
CHANGE 1
32
NAVAIR 01−F14AAD−1
LIST OF ILLUSTRATIONS
Page
No.Ă
CHAPTER 1 Ċ AIRCRAFT AND ENGINE
Figure 1Ć1.
Aircraft Dimensions
1−2
Figure 1Ć2.
Characteristics and Limitations (Sheet 1 of 2)
1−3
Figure 1Ć3.
Electronic Nomenclature
1−5
CHAPTER 2 SYSTEMS
Figure
2Ć1.
Air Inlet Control System
2−2
Figure
2Ć2.
AICS Control and Indicators (Sheet 1 of 2)
2−3
Figure
2Ć3.
Variable−Geometry Inlet Configuration
2−5
Figure
2Ć4.
AICS Normal Operating Mode
2−6
Figure
2Ć5.
Fail−Operational Mode Ċ No INLET Light
2−6
Figure
2Ć6.
Fail−Safe Mode Ċ INLET Light Illuminated
2−7
Figure
2Ć7.
Ramp Monitor Logic
2−8
Figure
2Ć8.
AICS Anti−Ice System
2−10
Figure
2Ć9.
F110−GE−400 Engine
2−10
Figure
2Ć10.
ENG MODE SELECT Panel and ENG SEC Lights
2−12
Figure
2Ć11.
AFTC Functional Relationships
2−13
Figure
2Ć12.
Rich Stability Cutback Ċ F110−GE−400 Engine
2−15
Figure
2Ć13.
Variable Area Exhaust Nozzle
2−17
Figure
2Ć14.
FEMS Multifunction Display Configuration
2−18
Figure
2Ć15.
Fatigue Engine Monitoring System Diagram
2−19
Figure
2Ć16.
Flight Maintenance Indicator
2−20
Figure
2Ć17.
Engine Fuel System
2−22
Figure
2Ć18.
Afterburner Fuel Sequencing
2−24
Figure
2Ć19.
Throttle Interlocks
2−25
Figure
2Ć20.
Throttle Control
2−26
Figure
2Ć21.
Autothrottle Controls and Indicators (Sheet 1 of 2)
2−28
Figure
2Ć22.
Engine Bleed Air/Compartment Ventilation
2−30
Figure
2Ć23.
Anti−Ice Control
2−31
Figure
2Ć24.
Engine Start System
2−33
Figure
2Ć25.
Engine Instruments (F110−GE−400)
2−36
Figure
2Ć26.
MFD Engine Monitor Display
2−38
Figure
2Ć27.
Fire Detection System
2−39
Figure
2Ć28.
Fire Extinguishing Switches and Advisory Lights
2−41
Figure
2Ć29.
Fuel Tanks
2−41
Figure
2Ć30.
Fuel Controls and Indicators (Sheet 1 of 3)
2−44
Figure
2Ć31.
Engine Fuel Feed
2−47
Figure
2Ć32.
Aft Fuselage Fuel Transfer
2−49
Figure
2Ć33.
Forward Fuselage Fuel Transfer
2−50
Figure
2Ć34.
Wing and External Tank Fuel Transfer
2−52
Figure
2Ć35.
Fuel Vent and Dump
2−56
Figure
2Ć36.
Refueling System
2−57
Figure
2Ć37.
Generator Panel
2−60
Figure
2Ć38.
Circuit Breaker Alphanumeric Index (Sheet 1 of 5)
2−64
Figure
2Ć39.
Hydraulic System Controls and Indicators (Sheet 1 of
2)
2−70
Figure
2Ć40.
Outboard Spoiler System
2−74
Figure
2Ć41.
Backup Flight Control System
2−75
33
ORIGINAL
NAVAIR 01−F14AAD−1
Page
No.Ă
Figure
2Ć42.
Mission Computer System Architecture
2−78
Figure
2Ć43.
CADC Functional Relationships
2−80
Figure
2Ć44.
CADC Processor
2−80
Figure
2Ć45.
CADC Processor Indicators
2−81
Figure
2Ć46.
Wing−Sweep Controls and Indicators (Sheet 1 of 2)
2−84
Figure
2Ć47.
Wing−Sweep Modes
2−86
Figure
2Ć48.
Wing−Sweep Interlocks
2−88
Figure
2Ć49.
Flap and Slat Controls and Indicators (Sheet 1 of 2)
2−90
Figure
2Ć50.
Wing Control Surfaces
2−92
Figure
2Ć51.
Maneuver Flap Envelope
2−94
Figure
2Ć52.
Maneuver Slat/Flap Automatic Schedule for CADC
2−94
Figure
2Ć53.
Speedbrakes
2−95
Figure
2Ć54.
Speedbrake Control and Indicator
2−96
Figure
2Ć55.
Control Surface Indicators (Sheet 1 of 2)
2−98
Figure
2Ć56.
Longitudinal Control System
2−100
Figure
2Ć57.
Longitudinal System Authority
2−100
Figure
2Ć58.
Control Stick and Trim (Sheet 1 of 2)
2−101
Figure
2Ć59.
Integrated Trim Schedules
2−103
Figure
2Ć60.
Lateral Control System
2−103
Figure
2Ć61.
Lateral System Authority
2−104
Figure
2Ć62.
Spoiler Control System
2−105
Figure
2Ć63.
Spoiler Gearing Schedule
2−106
Figure
2Ć64.
Yaw Control System
2−108
Figure
2Ć65.
Yaw System Authority
2−108
Figure
2Ć66.
DFCS Rates and Authorities
2−110
Figure
2Ć67.
DFCS Controls and Indicators (Sheet 1 of 3)
2−111
Figure
2Ć68.
DFCS Up and Away ARI Functions
2−114
Figure
2Ć69.
DFCS Pitch Interfaces and Control Functions (Sheet 1 of
3)
2−117
Figure
2Ć70.
DFCS Failure Modes and Indications (Sheet 1 of 4)
2−121
Figure
2Ć71.
DFCS DCP System Display Codes
2−131
Figure
2Ć72.
Landing Gear Controls and Indicators (Sheet 1 of 2)
2−134
Figure
2Ć73.
Wheelbrake Controls and Indicators
2−137
Figure
2Ć74.
Antiskid BIT Box
2−139
Figure
2Ć75.
Nosewheel Steering Controls
2−142
Figure
2Ć76.
Launch Bar Controls
2−144
Figure
2Ć77.
Nosewheel Strut and Launch Bar Positions
2−146
Figure
2Ć78.
Arresting Hook Controls
2−147
Figure
2Ć79.
Air−Conditioning and Pressurization Controls and Indicators (Sheet
1 of
2)
2−149
Figure
2Ć80.
Avionic Equipment Liquid Cooling Controls and Lights (Sheet 1 of 2)
2−153
Figure
2Ć81.
Cabin Pressure Schedule
2−155
Figure
2Ć82.
Canopy Defog Controls and Windshield Air
2−156
Figure
2Ć83.
Oxygen System Controls and Indicators (Sheet 1 of 2)
2−158
Figure 2Ć84 .
Backup Oxygen Duration Chart
2−161
Figure
2Ć85.
Airstream Sensors
2−162
Figure
2Ć86.
Display Systems Controls and Indicators (Sheet 1 of 4)
2−163
Figure
2Ć87.
Display Format Groups (Sheet 1 of 2)
2−167
Figure
2Ć88.
Heads−Up Display
2−170
Figure
2Ć89.
Pilot Displays Control Panel (Sheet 1 of 3)
2−171
Figure
2Ć90.
Multistatus Indicator Symbols/Meanings
2−174
Figure
2Ć91.
Multifunction Display (Sheet 1 of 2)
2−175
Figure
2Ć92.
Cursor Controls
2−177
Figure
2Ć93.
Warning, Caution, Advisory Functions (Sheet 1 of 3)
2−179
Figure
2Ć94.
Test Patterns
2−182
ORIGINAL
34
NAVAIR 01-F14AAD-1
Page
No.
Figure
2-95.
HUD TLN Basic Format (Sheet 1 of 4)
2-183
Figure
2-96.
HUD Declutter Levels
2-187
Figure
2-97.
HUD Added Symbology (Sheet 1 of 2)
2-189
Figure
2-98.
HUD Symbology Available on TLN Formats (Sheet 1 of 2)
2-191
Figure
2-99.
HUD A/A Search Formats (Sheet 1 of 2)
2-193
Figure
2-100.
HUD Symbology Available on A/A Formats (Sheet 1 of 2)
2-195
Figure
2-101.
HUD A/G Basic Format
2-198
Figure
2-102.
HUD Symbology Available on A/G Formats (Sheet 1 of 2)
2-199
Figure
2-103.
HUD Overlay Formats
2-201
Figure
2-104.
HUD Manual Reticle Format
2-202
Figure
2-105.
Slaved DEU Page Control
2-203
Figure
2-106.
MFD MENU Displays
2-204
Figure
2-107.
MFD Spin Indicator Display
2-206
Figure
2-108.
MFD Warning/Caution/Advisory and Message Overlays (Sheet 1 of 2)
2-207
Figure
2-109.
Computer and OBC Messages (Sheet 1 of 4)
2-209
Figure
2-110.
Typical MFD Alphanumeric Format
2-213
Figure
2-111.
MFD VDI Formats — Takeoff, Landing, Navigation (Sheet 1 of 9)
2-215
Figure
2-112.
MFD VDI Symbology Available on TLN Formats (Sheet 1 of 2)
2-224
Figure
2-113.
MFD VDI Air-to-Air and Air-to-Ground Formats (Sheet 1 of 6)
2-226
Figure
2-114.
MFD VDI Symbology Available on Air-to-Air and Air-to-Ground Formats (Sheet 1 of 2)
2-231
Figure
2-115.
MFD VDI Air-to-Ground (A/G) Format
2-233
Figure
2-116.
MFD VDI Recon Overlay Format
2-234
Figure
2-117.
MFD VDI Radar and IRSTS Overlay Formats (Sheet 1 of 2)
2-235
Figure
2-118.
MFD HSD Format (Sheet 1 of 4)
2-237
Figure
2-119.
Plot Line and Course Line Displays (Sheet 1 of 2)
2-241
Figure
2-120.
MFD SMS Format—CAP/Attack, Fighter Wingforms (Sheet 1 of 2)
2-243
Figure
2-121.
MFD Engine Monitor Format (Sheet 1 of 2)
2-245
Figure
2-122.
Data Entry Unit/Main Menu Page
2-247
Figure
2-123.
Data Entry Parameters
2-249
Figure
2-124.
Angle-of-Attack Conversion (Sheet 1 of 2)
2-252
Figure
2-125.
Angle-of-Attack Displays
2-254
Figure
2-125A. Auxiliary Pneumatic Selector Valve Reset
2-256
Figure
2-126.
Cockpit Canopy Control Handle and Indicator Lights
2-257
Figure
2-127.
Ejection Seat (Sheet 1 of 2)
2-259
Figure
2-128.
Survival Kit
2-262
Figure
2-129.
Command Ejection Lever
2-264
Figure
2-130.
Cockpit Light Controls (Sheet 1 of 3)
2-266
Figure
2-131.
Pilot Indicator Lights (Sheet 1 of 5)
2-270
Figure
2-132.
RIO Indicator Lights (Sheet 1 of 3)
2-275
Figure
2-133.
Multistatus Indicator
2-279
Figure
2-134.
Jettison Controls
2-281
Figure
2-135.
ACM Jettison Selection and Display
2-282
Figure
2-136.
Systems Test and System Power Ground Panel
2-283
Figure
2-137.
CNU-188/A External Baggage Container
2-284
CHAPTER 3
SERVICING AND HANDLING
Figure 3-1.
Aircraft Servicing Locations
3-1
Figure 3-2.
Aircraft Servicing Data (Sheet 1 of 2)
3-2
Figure 3-3.
Aircraft Servicing (Sheet 1 of 3)
3-5
Figure 3-4.
Runup Danger Areas — Exhaust Jet Wake Velocity and Temperature
3-9
Figure 3-5.
Radar Radiation Hazard Areas (Sheet 1 of 4)
3-10
Figure 3-6.
Noise Danger Areas
3-14
35
CHANGE 1
NAVAIR 01−F14AAD−1
Page
No.Ă
Figure 3Ć7.
Towing Turn Radii
3−16
Figure 3Ć8.
Towing
3−17
Figure 3Ć9.
Tiedown Arrangement (Sheet 1 of 2)
3−18
CHAPTER 4 OPERATING LIMITATIONS
Figure 4Ć1.
Store Station Configuration
4−2
Figure 4Ć2.
Instrument Markings
4−3
Figure 4Ć3.
Engine Operating Limits
4−4
Figure 4Ć4.
Maximum Allowable Airspeeds (Sheet 1 of 3)
4−6
Figure 4Ć5.
Variation of Maximum Allowable Normal Load Factor With Gross Weight
4−9
Figure 4Ć6.
Maximum Allowable Angle of Attack Rudder Deflections
4−11
Figure 4Ć7.
Angle−of−Attack Limits
4−12
Figure 4Ć8.
Maneuvering Limits Ċ Cruise Configuration (Roll SAS Off or Degraded DFCS)
4−13
Figure 4Ć9.
Maneuvering Limits Ċ Rolling (Sheet 1 of 3)
4−14
Figure 4Ć10.
Flap Limitations
4−17
CHAPTER 7 SHORE−BASED PROCEDURES
Figure 7−1. Exterior Inspection
7−2
Figure 7−2. Ejection Seat Safe−and−Arm Module
7−7
Figure 7−3. Taxi Turn Radii (Maximum Nosewheel Steering 70_)
7−19
Figure 7−4. Field Carrier Landing Practice
7−38
CHAPTER 8 CARRIER−BASED PROCEDURES
Figure 8−1. Catapult Launch Trim Requirements
8−5
Figure 8Ć2.
Center−of−Gravity Variation With Fuel Loading
8−6
Figure 8−3.
Carrier Landing Pattern
8−8
Figure 8Ć4.
Carrier−Controlled Approach (Typical)
8−11
CHAPTER 10 FUNCTIONAL CHECKFLIGHT PROCEDURES
Figure 10−1. Flight Profile
10−1
CHAPTER 11 FLIGHT CHARACTERISTICS
Figure 11−1. Lateral−Control−Induced Departure Areas
11−8
Figure 11Ć2. Cross−Control−Induced Departure Areas
11−12
Figure 11−3. F−14 Departure Recovery Diagram
11−16
Figure 11−4. Spin Arrow Displays
11−18
Figure 11−5. MFD−1/PTID Right Spin Display (INS and SAHRS Failed)
11−19
Figure 11−6. Stall Speeds for Wing Rock at 25 Units AOA
11−23
Figure 11−7. Minimum Control Speed, Ground (VMCG)
11−24
Figure 11−8. Rudder Effectiveness
11−25
Figure 11−9. Landing Approach Airspeed (15 Units AOA)
11−28
Figure 11−10. Asymmetric Wing−Sweep Landing Approach
11−34
CHAPTER 12 GROUND EMERGENCIES
Figure 12Ć1. Emergency Entrance
12−3
ORIGINAL
36
NAVAIR 01−F14AAD−1
Page
No.Ă
CHAPTER 14 IN−FLIGHT EMERGENCIES
Figure 14−1. Airspeed Indicator Failure
14−2
Figure 14−2. External Stores Jettison
14−3
Figure 14−3. Airstart Envelope
14−9
Figure 14Ć4. Secondary Mode Thrust Levels
14−14
Figure 14−5. Emergency Generator Distribution (Sheet 1 of 2)
14−21
Figure 14Ć6. Failure of Both Transformer−Rectifiers Equipment Inoperative List
14−23
CHAPTER 15 LANDING EMERGENCIES
Figure 15−1. Landing Gear Malfunction Emergency Landing Guide
15−7
Figure 15−2. Asymmetric Wing−Sweep Landing Approach Airspeed
15−12
Figure 15−3. Emergency Field Arrestment Guide (Sheet 1 of 2)
15−19
CHAPTER 16 EJECTION
Figure 16−1. Minimum Ejection Altitude (Sheet 1 of 3)
16−2
Figure 16−2. Proper Ejection Position
16−6
Figure 16−3. Ejection Initiation
16−7
Figure 16−4. Life Preserver Assembly Inflation
16−8
CHAPTER 17 INSTRUMENT PROCEDURES
Figure 17−1. Radar Beacon Panel (Sheet 1 of 2)
17−4
Figure 17−2. ACLS/ILS Steering (Sheet 1 of 3)
17−6
Figure 17−3. AN/ARA−63 Decoder Panel
17−9
Figure 17−4. ACLS Mode I and II Approaches
17−11
Figure 17−5. SPN−41 ILS Approach
17−14
CHAPTER 18 EXTREME WEATHER OPERATIONS
Figure 18−1. Icing Danger Zone
18−2
Figure 18−2. Combined Viscous and Dynamic Tire Hydroplaning
18−3
CHAPTER 19 COMMUNICATIONS
Figure 19Ć1. Communications and Associated Equipment
19−2
Figure 19−2. Antenna Select Panel
19−3
Figure 19−3. Intercommunication Controls (Sheet 1 of 2)
19−4
Figure 19−4. Glossary of Tones
19−6
Figure 19−5. Pilot TONE VOLUME/TACAN CMD Panel
19−8
Figure 19−6. AN/ARC−182 V/UHF Control Panel (Sheet 1 of 2)
19−9
Figure 19−7. Radio Frequency/Channel Indicator (Sheet 1 of 2)
19−11
Figure 19−8. Pilot VOLUME Control Panel
19−13
Figure 19Ć9. Common BIT Indications
19−14
Figure 19−10. Example of an ARC−182 Have Quick II MWOD Fill
19−14
Figure 19−11. Have Quick II Error Codes
19−18
Figure 19−12. KY−58 Controls (Sheet 1 of 2)
19−20
Figure 19−13. JTIDS Control Panels (Sheet 1 of 3)
19−24
Figure 19−14. In−Flight Communications (Sheet 1 of 4)
19−27
Figure 19−15. Deck/Ground Handling Signals
19−31
37
ORIGINAL
NAVAIR 01−F14AAD−1
Page
No.Ă
CHAPTER 20 NAVIGATION SYSTEM
Figure 20−1.
Navigation System
20−2
Figure 20−2.
NAV MODE Select/Computer Reset Panel
20−4
Figure 20−3.
DEU Navigation Formats
20−7
Figure 20−4.
TACAN Controls and Indicators (Sheet 1 of 3)
20−9
Figure 20−5.
Navigation System Data Distribution
20−13
Figure 20−6.
HUD Navigation Outputs (TLN Basic)
20−14
Figure 20−7.
MFD VDI (TLN Basic) Navigation Outputs
20−16
Figure
20Ć8.
Own−Aircraft Basic Data Format
20−17
Figure 20−9.
MFD HSD Format Ċ Navigation Outputs
20−18
Figure 20−10.
Navigation Data Display Summary (Sheet 1 of 2)
20−21
Figure
20Ć11.
GPS Status Format (Sheet 1 of 3)
20−24
Figure 20−12.
Crypto Loading Panel Location
20−27
Figure 20−13.
Navigation Modes and Navigation Sensor Data
20−28
Figure
20Ć14.
NAV System Aid Format
20−28
Figure
20Ć15.
INS In−Flight Align Formats
20−32
Figure
20Ć16.
Secondary Navigation Mode Manually Selected
20−33
Figure
20Ć17.
IMU Backup Navigation Mode Selection
20−34
Figure 20−18.
SAHRS Backup SLV and DG Modes (Sheet 1 of 2)
20−36
Figure 20−19.
MFD MENU1 and MENU2 Displays
20−39
Figure 20−20.
DEU Own−Aircraft Data Entry (Typical)
20−40
Figure 20−21.
DD/PTID Own−Aircraft Data Entry
20−41
Figure
20Ć22.
MFD Ground Alignment Formats
20−42
Figure
20Ć23.
GPS On−Deck IFA Alignment
20−44
Figure
20Ć24.
CV Alignment Formats Ċ SINS
20−46
Figure
20Ć25.
CV Alignment Formats Ċ Manual (Sheet 1 of 2)
20−47
Figure 20−26.
DD Align Data Entry
20−50
Figure 20−27.
SAHRS Standalone Align MFD Format
20−50
Figure 20−28.
Data Entry Unit Waypoint Pages (Typical)
20−53
Figure
20Ć29.
MFD Waypoint Data Format
20−54
Figure 20−30.
DD Waypoint Data Entry
20−54
Figure
20Ć31.
Magnetic Variation Source Selection and DD Entry
20−56
Figure 20−32.
Waypoint Numbering Scheme
20−58
Figure 20−33.
DEU Waypoint Type Format
20−58
Figure 20−34.
Waypoint Types and Associated Symbols
20−59
Figure 20−35.
MFD Flight Plan Format
20−60
Figure 20−36.
MDL Reversionary Waypoint Format
20−61
Figure
20Ć37.
Flight Plan Data Format
20−62
Figure 20−38.
Flight Plan Format ć Waypoint Add Page (Sheet 1 of
2)
20−64
Figure
20Ć39.
Flight Plan Format ć Waypoint Replacement Page (Sheet
1 of
2)
20−67
Figure 20−40.
Flight Plan Format ć Waypoint Transfer Page (Sheet 1 of 2)
20−69
Figure 20−41.
MDL Reversionary Waypoint Format ć MDL Waypoint Transfer
20−71
Figure 20−42.
Flight Plan Format ć Waypoint Delete Page (Sheet 1 of 2)
20−73
Figure 20−43.
Steering Mode Summary
20−76
Figure 20−44.
Destination Steering Displays (Sheet 1 of 2)
20−78
Figure 20−45.
TACAN Steering Mode Formats (Sheet 1 of 2)
20−80
Figure 20−46.
Typical GPS Steering Formats (Sheet 1 of 2)
20−82
Figure 20−47.
Auto Waypoint Steering Displays (Sheet 1 of 2)
20−84
Figure 20−48.
Commanded Ground Speed Indication
20−86
Figure 20−49.
Manual Steering Mode Formats (Sheet 1 of 2)
20−87
Figure 20−50.
Data−Link Steering Mode Formats (Sheet 1 of 2)
20−89
Figure 20−51.
INS UPDATE MFD Formats (Sheet 1 of 4)
20−92
ORIGINAL
38
NAVAIR 01−F14AAD−1
Page
No.Ă
Figure 20−52. DD Control Panel With GND MAP Selected
20−96
Figure 20−53. MFD TSD Format
20−97
Figure 20−54. HUD/Designate Position Update
20−98
Figure 20−55. Navigation System Continuous Update MFD Format
20−100
FigureĂ20−56. Surface Waypoint Position MFD Formats (Sheet 1 of 2)
20−101
Figure 20−57. Cursor Controls
20−104
CHAPTER 21 IDENTIFICATION
Figure 21−1. IFF Control Panels (Sheet 1 of 3)
21−2
Figure 21−2. Mode 4 Caution and Reply Light Logic
21−5
Figure 21−3. IFF Display Formats
21−8
CHAPTER 22 TARPS SUBSYSTEM
Figure 22−1. Tactical Air Reconnaissance Pod System
22−1
Figure 22−2. TARPS Component Locations
22−3
FigureĂ22−3. Controller Processor Signal Unit (Sheet 1 of 5)
22−4
Figure 22−4. MFD MENU2 Format
22−9
Figure 22−5. MFD RECON DATA Status Format
22−10
Figure 22−6. TARPS Advisories
22−10
Figure 22−7. MFD OBC/Maintenance Failure Formats
22−12
Figure 22−8. HUD/VDI Reconnaissance Symbology (Sheet 1 of 2)
22−14
Figure 22−9. HUD Reconnaissance Display (Command Course Steering) (Sheet 1 of 2)
22−16
Figure 22−10. Dynamic Steering Point Display
22−18
Figure 22−11. MFD RECON WPT DATA 1 Format
22−19
Figure 22−12. MFD RECON WPT DATA 2 Format
22−19
Figure 22−13. DEU Reconnaissance Selection
22−20
Figure 22−14. KS−87D Serial Frame Camera Characteristics
22−23
Figure 22−15. KA−99A Panoramic Camera Characteristics
22−24
Figure 22−16. KS−153A Still Picture Camera Characteristics (610−Mm Standoff Configuration)
22−25
CHAPTER 23 NAVIGATION COMMAND AND CONTROL GRID
Figure 23Ć1. DEU NAV GRID Data Entry Ċ Typical
23−2
FigureĂ23−2. DD NAV GRID Data Entry
23−3
Figure 23−3. PTID NAV GRID Displays
23−4
Figure 23−4. TSD NAV GRID Display
23−5
CHAPTER 38 AIRCRAFT SELF TEST
Figure 38−1. On−Board Checkout
38−2
Figure 38−2. Test Types
38−3
Figure 38−3. Master Test Panel (Sheet 1 of 2)
38−4
Figure 38−4. Subsystem BIT Mode Test Times (Sheet 1 of 2)
38−6
Figure 38−5. Definition of BIT Status Types
38−8
Figure 38−6. Equipment Subsystem BIT Status Types
38−9
Figure 38−7. BIT Interlocks Test Restrictions (Sheet 1 of 2)
38−11
Figure 38−8. OBC Display Format Types
38−13
Figure 38−9. OBC Failure Acronyms (Sheet 1 of 11)
38−14
Figure 38−10. DFCS Caution Lights and Acronyms (Sheet 1 of 2)
38−25
Figure 38Ć11. DFCS Fault Codes (Sheet 1 of 6)
38−27
Figure 38−12. OBC Basic Format
38−33
39
ORIGINAL
NAVAIR 01−F14AAD−1
Page
No.Ă
Figure 38−13.
Format Examples
38−34
Figure 38−14.
OBC Computer Messages
38−37
Figure 38−15.
OBC/CSS Messages
38−38
Figure 38−16.
OBC−Related Warning/Caution/Advisory Messages
38−39
Figure 38−17.
DEU CSS Page
38−41
Figure 38−18.
DEU Pages for Operator Code and Data Type
38−41
Figure 38−19.
DEU Flycatcher Pages
38−42
Figure 38−20.
MD CSS Display Format
38−43
Figure 38−21.
Flycatcher Error Messages
38−44
Figure 38−22.
DEU Block Address Pages
38−45
Figure 38−23.
DEU Trap Pages
38−46
Figure 38−24.
Block Address/Trap Error Messages
38−47
Figure 38−25.
DD Radar Warning Maltese Cross
38−48
Figure 38Ć26.
MFD/PTID ORT Abort Displays
38−50
Figure 38−27.
Test−in−Progress Display
38−52
Figure 38−28.
WRA Common Names and Designators
38−53
Figure 38Ć29.
BIT Menu Display Format
38−54
Figure 38−30.
Degraded Mode Assessment Format
38−54
Figure 38−31.
Maintenance Display Format (Test Complete)
38−55
Figure 38−32.
Maintenance Display (Test Complete)
38−55
Figure 38−33.
Test Target Menu
38−56
Figure 38Ć34.
Continuous Monitor Display
38−57
Figure 38−35.
Radar Continuous Monitor Acronyms
38−58
FigureĂ38−36.
OBC Continuous Monitor Acronyms
38−59
Figure 38−37.
PTID Menu for TCS IBIT, In Progress
38−61
Figure 38−38.
TCS BIT Prompts and RIO Responses
38−61
Figure 38−39.
Initial C/D TEST Display
38−62
Figure 38−40.
C/D TEST 1 Display (After Aging Is Completed)
38−62
Figure 38−41.
C/D TEST 2 Display
38−63
Figure 38−42.
C/D TEST 3 Display
38−63
Figure 38−43.
DD Responses for SCU/SSP/DD Select Tests
38−64
Figure 38−44.
DD Responses for SHC Select Tests
38−64
Figure 38−45.
DD Responses for PTID Select Tests
38−64
Figure 38−46.
BIT Static DD Display (ATTK Selected)
38−65
Figure 38−47.
BIT Static PTID Display (ATTK Selected)
38−66
Figure 38−48.
BIT Static DD Display (GND STAB or TV Selected)(Sheet
1 of 2)
38−67
Figure 38−49.
BIT Static PTID Display (Non−ATTK Selection)
38−69
Figure 38−50.
BIT DD Dynamic Display
38−70
Figure 38Ć51.
BIT Dynamic PTID Display (ATTK Selected)
38−71
Figure 38−52.
Special Test 80−Instrumentation Test
38−71
CHAPTER 40 Ċ TACTICAL IMAGING SET
Figure 40−1. Tactical Imaging Set Controls and Indicators (Sheet 1 of 2)
40−2
Figure 40−2. Settings Menus Sequence
40−5
ORIGINAL
40
NAVAIR 01−F14AAD−1
LIST OF ABBREVIATIONS AND ACRONYMS
A
AGR Air−to−ground ranging.
AIC Air inlet control; air intercept control.
A/A Air−to−air.
AICS Air inlet control system.
AAA Anti−aircraft artillery.
A/J Antijam.
AAC Aviation armament change.
AM Amplitude modulation.
AAI Air−to−air interrogator.
A/N Alphanumeric.
AAW Anti−air warfare.
AOA Angle of attack.
AB Afterburner.
AOB Angle of bank.
ac Alternating current.
AON Angle−off−the−nose.
ACC Aircrew system change.
APC Approach power compensator.
ACL Automatic carrier landing.
APCS Approach power compensator system.
ACLS Automatic carrier landing system.
ARDP Advance radar data processor.
ACM Air combat maneuver.
ARI Automatic rudder interconnect.
ACQ Acquisition (TCS).
ARSP Advance radar signal processor.
ACS Automatic channel select.
ASC Advanced signal converter.
A/D Analog−to−digital.
ASE Allowable steering error.
ADAC Airborne data acquisition computer.
ASH Automatic stored heading.
ADF Automatic direction finder.
ASPJ Airborne self−protection jammer.
ADI Altitude director indicator.
ASR Air surveillance radar.
ADL Armament datum line.
ATDC Airborne tactical data control.
ADRL Automatic distribution requirements list.
ATDS Airborne tactical data system.
AEC Automatic exposure control.
ATLS Asymmetric thrust limiting system.
AFB Airframe bulletin.
AVB Avionic bulletin.
AFC Airframe change.
AVC Avionic change.
AFTC Augmenter fan temperature control.
AVIA TID AOA, VV, ILS, and ACLS.
A/G Air−to−ground.
AWCS Airborne weapons control system.
AGI Armament gas ingestion.
AWL All−weather landing.
AGL Above ground level.
AYC Accessories change.
41
ORIGINAL
NAVAIR 01−F14AAD−1
B
CAT Catapult.
CATM Captive air training missile.
BARO Barometric.
CATCC Carrier air traffic control center.
BATR Bullet at target range.
CAW Caution, advisory, warning.
BCD Binary code decimal.
cb Circuit breaker.
BDA Bomb damage assessment.
CC Cubic centimeter.
BDHI Bearing distance heading indicator.
CCA Carrier controlled approach.
BER BIT evaluation report.
CCIP Continuously computed impact point.
BFCM Backup flight control module.
CCRS Command course.
BIDI Bidirectional hydraulic pump.
CCTVS Color cockpit television sensor.
Bingo Return fuel state.
CDI Course deviation indicator.
BIST Built−in self test.
CDIR Camouflage detection infrared.
BIT Built−in test.
cg Center of gravity.
BLD Basic landing display.
CGTL Command ground track line.
BMT BIT moving target.
Charlie time Expected time over ramp.
BOL BOFORS launcher.
CIC Combat information center.
Bolter Hook down, unintentional touch and go.
CICU Computer integrated converter unit.
BOS Backup oxygen system.
CIPDU Control indicator power distribution unit.
BPS Beam power supply.
CIU Converter interface unit.
BRU Bomb rack unit.
CM Continuous monitor.
BSF Band suppression filter.
CMB Code matrix box.
BTOF Bullet time of flight.
CMM Continuous monitor mode.
CMPTR Computer.
C
CNI Communication−navigation−identification.
CA Cartridge actuated device.
CNO Chief of Naval Operations.
CADC Central air data computer.
COT Crew operation trainer.
CAINS Carrier aircraft inertial navigation system.
CP Central processor.
CAP Combat air patrol; computer address panel.
CPS Controller processor signal unit; cycles per second.
CARQUAL Carrier qualifications.
CRT Cathode ray tube.
CAS Calibrated airspeed.
CSD Constant speed drive.
ORIGINAL
42
NAVAIR 01-F14AAD-1
CSS Control stick steering.
DRO Destructive readout.
CV Aircraft carrier.
DROT Degraded range on target.
CVA Aircraft carrier approach.
DSPT Dynamic steering point.
CVIC Aircraft carrier intelligence center.
DSS Data storage set.
CVS Course vectoring symbols.
DSU Data storage unit.
CWI Continuous-wave illuminator.
DTM Data transfer module.
D
E
D/A Digital-to-analog.
EAC Expected approach clearance time.
dB Decibel.
EAS Equivalent airspeed.
dc Direct current.
ECA Expanded chaff adapter.
DD Digital display.
ECCM Electronic counter-countermeasures.
DDP Digital data processor.
ECM Electronic countermeasures.
DDPG Digital data processor group.
ECS Environmental control system.
DDS Data display system; digital data system.
ECU Electronic control unit.
DECM Defensive electronic countermeasures.
EED Electroexplosive devices.
DEST Destination.
EGT Exhaust gas temperature.
DEU Data entry unit.
EIF Exposure interval factor.
DF Direction finder.
EIG Engine instrument group.
DFCS Digital flight control system.
EMCON Electronic radiation control.
DFM Dogfight mode.
EMSP Engine monitoring system processor.
DG Directional gyro.
ETA Estimated time of arrival.
D/L Data link.
DLC Direct lift control.
F
DLS Data-link system.
FAM Familiarization.
DMA Degraded mode assessment.
FCF Functional checkflight.
DME Distance measuring equipment.
FCLP Field carrier landing practice.
DP Decision point.
FD Fault direction.
DPG Data processor group.
FEMS Fatigue engine monitoring system.
DPGS Data processing ground station.
FF Fuel flow.
DR Dead reckoning.
43
CHANGE 1
NAVAIR 01-F14AAD-1
F/F Fighter to fighter.
H
FF/DL Fighter-to-fighter data link.
HDG Heading.
FHF Failure history file.
HEFOE Hydraulic electric fuel oil engine.
FI Fault isolation.
HERO Hazards of electromagnetic radiation to ordnance.
FL Flight level.
hot start A start that exceeds normal starting
temperatures.
FLOLS Fresnel lens optical landing system.
HPRF High pulse repetition frequency.
FLRP Fighter link reference point.
HSD Horizontal situation display.
FMC Fighter mode command; forward motion compensa-
tion; forward motion correction.
HSI Horizontal situation indicator.
FMI Flight maintenance indicator.
HUD Heads-up display.
FMLP Field mirror landing practice.
hung start A start that results in a stagnated rpm and
temperature.
FOD Foreign object damage.
FOV Field of view.
I
fpm feet per minute.
IAS Indicated airspeed.
FRL Fuselage reference line.
IBIT Initiated BIT.
FRS Fleet replacement squadron.
ICAO International Civil Aviation Organization.
FTCM Flight test continuous monitoring.
ICS Intercommunications systems.
FTJU Fuel tank jettison unit.
IDG Integrated-drive generator.
FWD Forward.
IF Intermediate frequency.
IFB Interference blanker.
G
IFF Identification, friend or foe.
G Guard channel.
IFOV Instantaneous field of view.
g Gravity.
IFR Instrument flight rules.
G/A Ground to air.
IFT In-flight training.
GACH Gimble angle crosshair.
IFX IFF transponder.
GCA Ground-controlled approach
IGV Inlet guide vane.
GCI Ground-controlled intercept.
ILCOS Instantaneous lead computed optical sight.
GCU Generator control unit; gun control unit.
ILS Instrument landing system.
GPS Global positioning system.
IMC Instrument meteorological conditions.
GSS Gun scoring system.
GT Ground track.
CHANGE 1
44
NAVAIR 01−F14AAD−1
IMN Indicated Mach number.
L
IMU Inertial measurement unit.
LAOT Low−PRF antenna on target.
InHg Inch of Mercury.
LAR Launch acceptability region.
INS Inertial navigation system.
LARI Lateral automatic rudder interconnect.
IP Initial point.
LBA Limits of basic aircraft.
IPF Interference protection feature.
LCD Liquid crystal display.
IR Infrared.
LCOS Lead computing optical sight.
IRCM Infrared countermeasures.
LCU Load control unit.
IRLS Infrared line scanner.
LE Leading edge.
IRNR Infrared not ready.
LOROP Long−range oblique photography.
IRRS Infrared reconnaissance set.
LOS Line of sight.
IRST Infrared search and track.
LOX Liquid oxygen.
IRT Infrared test.
LPA Life preserver assembly.
IRW Infrared wide.
LPRF Low pulse repetition frequency.
ITER Improved triple ejector track.
LS Line scanner.
ITS Integrated trim system.
LSO Landing signal officer (Paddles).
IU Interface unit.
LTE Launch to eject.
J
M
JAT Jam angle track.
M Mach.
JTIDS Joint tactical information distribution system.
MAC Mean aerodynamic chord.
K
MAD Magnetic azimuth detector.
KCAS Knots calibrated airspeed.
MAG VAR Magnetic variation.
KCP Keyer control panel.
MAN Manual.
KEAS Knots equivalent airspeed.
MAS Missile auxiliary subsystem.
kHz Kilohertz.
MATS Missile auxiliary test set.
KIAS Knots indicated airspeed.
MAX Maximum.
KTS Knots.
MCF Motion compensation factor.
45
ORIGINAL
NAVAIR 01-F14AAD-1
MCM Monitor control message.
N
MCS Mission computer system.
NACES Navy aircrew common ejection seat.
MCT Memory confidence test.
NAG Air-to-ground mode.
MDL Mission data loader.
NATOPS Naval Air Training and Operating Procedures
Standardization.
meatball Glideslope image of mirror landing system.
NATSF Naval Air Technical Services Facility.
MEC Main engine control.
NAV GRID Navigation command and control grid.
MER Multiple ejector rack.
NAVRIT Naval airborne video recorder and image
MFD Multifunction display.
transceiver.
MFT Mission flight trainer.
NDRO Nondestructive readout.
MHz Megahertz.
NECT Net entry control terminal.
MIL Military.
NFL Notch filter let.
MITS Missile interface test set.
NFO Naval flight officer.
MLC Mainlobe clutter.
NFOV Narrow field of view.
MLG Main landing gear.
NFR Notch filter right.
MMGS Multiple mode gunsight.
nm Nautical miles.
MOAT Missile on aircraft test.
NOTAM Notice to airmen.
MPRU Missile power relay unit.
NOZ Nozzle.
MPS Missile power supply.
NPG Network participant group.
MR Maintenance readout.
NPS Navigation power supply.
MRL Manual rapid lock-on.
NR Number.
MRT Military rated thrust.
NRNG No range.
MSEC Message security.
NSV Navigation state vector.
MSI Multistatus indicator.
NTDS Naval tactical data system.
MSL Mean sea level.
NTR Network time reference.
MSS Mission support system.
NVIS Night vision imaging system.
MTDS Marine tactical data system.
NWP Naval warfare publication.
MTM Magnetic tape memory.
NWPM Non-write-protected memory.
MTP Master test panel.
NWS Nosewheel steering.
MVR Mission video recorder.
N1 Low-pressure compressor rotor speed.
MWOD Multiple word of day.
N2 High-pressure compressor rotor speed.
CHANGE 1
46
NAVAIR 01-F14AAD-1
O
PPC Powerplant change.
OAT Outside air temperature.
pph Pounds per hour.
OBC On-board check.
PPI Plan position indicator.
OBCCM On-board check continuous monitor.
PPLI Precise participant location and identification.
OBOGS On-board oxygen generating system.
PRI Primary.
OFT Operational flight trainer.
PS Pulse search.
OFP Operational flight plan.
Ps Static pressure.
ORT Operational readiness test.
psi Pounds per square inch.
OSP Overspeed.
PSTT Pulse single-target track.
OWF Overwing fairing.
PSU Power switching unit.
PT Engine power trim.
P
Pt Total pressure.
Paddles Landing signal officer.
PTID Programmable tactical information display.
PA Power approach.
PTO Pilot takeover.
PAL Pilot automatic lock-on.
PTP Point to point.
PAN Panoramic.
PT7 Turbine exhaust pressure.
PAP Precision approach point.
PAR Precision approach radar.
Q
PC Pulse compression.
Q Dynamic pressure.
PCD Precision course direction.
R
PD Pulse Doppler.
RACH Radar angle crosshair.
PDCP Pilot display control panel.
RARI Rudder automatic rudder interconnect.
PDS Pulse Doppler search.
RATS Reduced arrestment thrust system.
PDSTT Pulse Doppler single-target track.
RDO Recovery duty officer.
PFPM Potential flightpath marker.
RDP Radar data processor.
PGU Improved round for the M-61 gun (new bullet).
RDR Radar.
PH Phoenix missile.
RDSCU Radar sensor control unit.
PID Positive identification.
RECON Reconnaissance.
PIO Pilot-induced oscillation.
RF Radio frequency.
PLM Pilot lock-on mode.
RFCI Radio frequency/control indicators.
POL Petroleum, oil, lubricants.
RGSTT Range-gated single target track.
PP Peak power.
47
CHANGE 1
NAVAIR 01−F14AAD−1
RHA Recording head assembly.
SEC Secondary.
RIO Radar intercept officer.
SHC Sensor hand control.
RNAV Area navigation.
SHDG Stored heading ground align.
ROE Rules of engagement.
SIF Selective identification feature.
ROM Read−only memory.
SINS Ship’s inertial navigation system.
ROT Range on target.
SMAL Single−mode alignment.
rpm High−pressure compressor rotor speed (N2).
SMDC Shielded mild detonator cord.
RRC Rounds remaining counter.
SMP Store management processor.
R/T Receiver−transmitter.
SMS Stores management system.
RTF Return to force.
SOP Standard operating procedures.
RTGS Real time gunsight.
SP Sparrow missile.
RTT−I Round trip timing interrogation.
SPAM Special aid to maintenance.
RWR Radar warning receiver.
SPS Solenoid power supply.
RWS Range while search.
SRA Shop replaceable assembly.
STAB AUG Stability augmentation.
S
STBY Standby.
SA Semiautomatic acquisition mode.
STN Source track number.
SAHRS Standard attitude heading reference system.
STT Single−target track.
SAM Surface−to−air missile.
SSI Standard serial interface.
SAR Search and rescue.
SW Sidewinder missile.
SAS Stability augmentation system.
SAT Simultaneous alignment and test.
T
SC Sensor control.
TACAN Tactical air navigation.
SCADC Standard central air data computer.
TAC DRO Tactical destructive readout.
SCP Sensor control panel.
TADIL Tactical digital information link.
SDIS Sensor display indicator set.
TAMPS Tactical aviation mission planning system.
SEAD Suppression of enemy air defense.
TARPS Tactical air reconnaissance pod system.
SEAM Sidewinder expanded acquisition mode.
TAS True airspeed.
SEAWARS Seawater−activated release system.
TBT Turbine blade temperature.
ORIGINAL
48
NAVAIR 01−F14AAD−1
TCA Turbine compressor assembly.
TVT Television track.
TCR Time code readout.
TWS Track while scan.
TCS Television camera set.
U
TDC Throttle designator controller.
UHF Ultra high frequency.
TDRS Tactical data recording system.
UHT Unit horizontal tail.
TDMA Time−division multiple access.
UTM Universal test message.
TDS Tactical data system.
TED Trailing edge down.
V
TER Triple ejector rack.
Vc Closing velocity rate.
TEU Trailing edge up.
vC Computed MAG VAR.
TID Tactical information display.
VDI Vertical display indicator.
TIMS Terminal input messages.
VDIG Vertical display indicator group.
TIS Tactical imaging set.
VEC Vector.
TIT Turbine inlet temperature.
VERT Vertical.
TLN Takeoff, landing, navigation.
VFR Visual flight rules.
TMA Target under missile attack.
Vg/H Velocity/height.
TMN True Mach number.
V/H Velocity altitude factor (Vg/H).
TOD Time of day.
VHF Very high frequency.
TOF Time of fall.
VID Visual identification.
TOMS Terminal output messages.
VLA Vertical lever arm.
TOT Time on target.
vM Manual MAG VAR.
T/R Transformer−rectifier.
Vmcg Minimum control groundspeed.
TS Static temperature.
VMCU Voltage monitor control unit.
TSD Tactical situation display.
VR Rotation speed.
TSEC Transmission security.
VSL Vertical scan lock−on.
TT2 Compressor inlet temperature.
VSV Variable stator vane.
TT4 Compressor discharge temperature.
VSWR Voltage standing wave ratio.
TTG Time to go.
VTR Videotape recorder.
TV Television.
VV Vertical velocity.
TVS Television search.
V1 Critical engine failure speed.
49
ORIGINAL
NAVAIR 01−F14AAD−1
W
WSPD Windspeed.
WCS Weapon control system.
WST Weapons system trainer.
WDIR Wind direction.
Y
WFOV Wide field of view.
YY Geographic reference point for NAV GRID.
WOD Wind over the deck; word of the day.
WOW Weight on wheels or weight off wheels.
Z
WPM Weapons program memory.
ZTOD Zulu time of day.
WRA Weapons replaceable assembly.
ZTOT Zulu time on target.
ORIGINAL
50
NAVAIR 01−F14AAD−1
PREFACE
SCOPE
tribution Requirements List (ADRL) maintained by Naval
Air Technical Data and Engineering Service Command, in
This NATOPS flight manual is issued by the authority
San Diego, CA. If there is a continuing need for this publicaĆ
of the Chief of Naval Operations and under the direction of
tion, each activity’s Central Technical Publication Librarian
Commander, Naval Air Systems Command in conjunction
must send a revised ADRL report on floppy disk to Naval Air
with the naval air training and operating procedures standardĆ
Technical Data and Engineering Service Command. If an
ization (NATOPS) program. This manual, together with the
activity does not have a library, then send a letter to the
supplemental manuals listed below, contains information on
Commanding Officer, Naval Air Technical Data and EngiĆ
all aircraft systems, performance data, and operating proceĆ
neering Service Command, Naval Air Depot North Island,
dures required for safe and effective operations. However, it
Bldg. 90, Code 3.3A, P.O. Box 357031, San Diego, CA
is not a substitute for sound judgment. Compound emergenĆ
92135−7031, requesting assignment of a distribution account
cies, available facilities, adverse weather or terrain, or conĆ
number (if necessary) and automatic mailing of future issues
siderations affecting the lives and property of others may
of the publications needed.
require modification of the procedures contained herein.
Read this manual from cover to cover. It is your responsibility
Note
to have a complete knowledge of its contents.
The ADRL floppy disk can be used only to place
APPLICABLE PUBLICATIONS
an activity on the mailing list for automatic disĆ
tribution of future issues of the publications. It
The following applicable publications complement
cannot be used to make one−time orders of publiĆ
this manual:
cations from current stock. To get publications
from stock, see One−Time Orders above.
NAVAIR 01−F14AAP−1.1 (Performance Charts)
Once established on automatic distribution for this or
NAVAIR 01−F14AAD−1A (Supplemental)
any other NAVAIR technical publication, an activity must
submit an ADRL report on floppy disk at least once every
NAVAIR 01−F14AAD−1B (Pocket Checklist)
12ămonths to update or confirm their automatic distribution
NAVAIR 01−F14AAD−1F (Functional Checkflight
requirement.
Checklist)
Note
HOW TO GET COPIES
Activities not submitting an ADRL report on
floppy disk for more than 12 months may be
One−Time Orders
dropped from distribution of all NAVAIR techniĆ
cal publications.
If this publication is needed on a one−time basis (withĆ
out future updates), it can be ordered IAW NAVSUPP 409
UPDATING THE MANUAL
(MILSTRIP/MILSTRAP) from NAVICP Philadelphia via
DAAS through the local supply system or the requisition may
To ensure that the manual contains the latest proceĆ
be submitted to Naval Supply System Command, Naval LoĆ
dures and information, NATOPS review conferences are held
gistics Library
(NLL) web site www.nll.navsup.navy.mil.
in accordance with the current OPNAVINST 3710.7 series.
This publication is also available to view or download from
the NATEC website www.natec.navy.mil
CHANGE RECOMMENDATIONS
Automatic Distribution (With Updates)
Recommended changes to this manual or other
NATOPS publications may be submitted by anyone in accorĆ
This publication and changes to it are automatically
dance with the current OPNAVINST 3710.7 series.
sent to activities that are established on the Automatic DisĆ
51
ORIGINAL
NAVAIR 01−F14AAD−1
Routine change recommendations are submitted
WARNINGS, CAUTIONS, AND NOTES
directly to the model manager on OPNAV 3710/6 shown on
the next page. The address of the model manager of this
The following definitions apply to WARNINGs,"
aircraft is:
CAUTIONs," and Notes" found throughout this manual.
Commanding Officer
Fighter Squadron 101
NAS Oceana
Virginia Beach, VA 23460−5220
An operating procedure, practice, or condition,
Attn: F−14D Model Manager
etc., that may result in injury or death if not careĆ
fully observed or followed.
Change recommendations of an URGENT nature
(safety of flight, etc.,) should be submitted directly to the
NATOPS advisory group member in the chain of command
by priority message.
YOUR RESPONSIBILITY
An operating procedure, practice, or condition,
NATOPS flight manuals are kept current through an
etc., that may result in damage to equipment if
not carefully observed or followed.
active manual change program. Any corrections, additions,
or constructive suggestions for improvement of its content
should be submitted by routine or urgent change recommenĆ
Note
dation, as appropriate.
An operating procedure, practice, or condition,
etc., that is essential to emphasize.
NATOPS FLIGHT MANUAL INTERIM CHANGES
WORDING
Flight manual interim changes are changes or correcĆ
tions to the NATOPS flight manuals. They are issued by CNO
The concept of word usage and intended meaning that
or NAVAIRSYSCOM either as printed pages or as a naval
has been adhered to in preparing this manual is as follows:
message. The Interim Change Summary page is provided as
a record of all interim changes. Each manual custodian
Shall" has been used only when application of a proĆ
should check the Interim Change Summary page to see that
cedure is mandatory.
all interim changes have been incorporated.
Should" has been used only when application of a
CHANGE SYMBOLS
procedure is recommended.
Revised material is indicated by a black vertical line in
May" and need not" have been used only when
either margin of the page like the one printed next to this
application of a procedure is optional.
paragraph. The change symbol shows where there has been
a change. The change might be material added or information
Will" has been used only to indicate futurity, never to
restated. A change symbol in the margin by the chapter numĆ
indicate any degree of requirement for application of
ber and title indicates a new or completely revised chapter.
a procedure.
ORIGINAL
52
NAVAIR 01−F14AAD−1
NATOPS/TACTICAL CHANGE RECOMMENDATION
OPNAV 3710/6 (4−90) S/N 0107−LF−009−7900
DATE
TO BE FILLED IN BY ORIGINATOR AND FORWARDED TO MODEL MANAGER
FROM (originator)
Unit
TO (Model Manager)
Unit
Complete Name of Manual/Checklist
Revision Date
Change Date
Section/Chapter
Page
Paragraph
Recommendation (be specific)
j CHECK IF CONTINUED ON BACK
Justification
Signature
Rank
Title
Address of Unit or Command
TO BE FILLED IN BY MODEL MANAGER (Return to Originator)
FROM
DATE
TO
REFERENCE
(a) Your Change Recommendation Dated
j Your change recommendation dated
is acknowledged. It will be held for action of
the review conference planned for
to be held at
j Your change recommendation is reclassified URGENT and forwarded for approval to
by my DTG
/S/
MODEL MANAGER
AIRCRAFT
53
ORIGINAL
NAVAIR 01−F14AAD−1
ORIGINAL
54
NAVAIR 01−F14AAD−1
PART I
The Aircraft
Chapter 1 Ċ Aircraft and Engine
Chapter 2 Ċ Systems
Chapter 3 Ċ Servicing and Handling
Chapter 4 Ċ Operating Limitations
55 (Reverse Blank)
ORIGINAL
////////////////////////// |
||
|
|
|