F-14D. FLIGHT MANUAL (2004) - page 16
NAVAIR 01-F14AAP-1B
NATOPS POCKET CHECKLIST
F-14B
AIRCRAFT
DISTRIBUTION STATEMENT C — Distribution authorized to
U.S. Government agencies and their contractors to protect
publications required for official use or for administrative or
operational purposes only (1 June 1992). Other requests for
this document shall be referred to Commanding Officer,
Naval Air Technical Data and Engineering Command, Naval
Air Station North Island, Bldg. 90, Distribution, P. O. Box
357031, San Diego, CA 92135-7031.
DESTRUCTION NOTICE — For unclassified, limited docu-
ments, destroy by any method that will prevent disclosure
of contents or reconstruction of the document.
ISSUED BY AUTHORITY OF THE CHIEF OF NAVAL
OPERATIONS AND UNDER THE DIRECTION OF THE
COMMANDER, NAVAL AIR SYSTEMS COMMAND.
0801LP1030702
01 AUGUST 2001
Change 3 — 15 JANUARY 2004
NATEC ELECTRONIC MANUAL
NAVAIR 01-F14AAP-1B
Reproduction for nonmilitary use of the information or illustrations con-
tained in this publication is not permitted without specific approval of the
Commander, Naval Air Systems Command. The policy for use of classified
publications is established for the Navy and Marine Corps in OPNAVINST
5510-1 series.
LIST OF EFFECTIVE PAGES
NOTE: Text affected by current change indicated by vertical line in outer
margin.
DATES OF ISSUE FOR ORIGINAL AND CHANGED PAGES ARE:
Original
0
01 August 2001
Change 1
1
15 April 2002
Change 2
2
15 May 2003
Change 3
3
15 January 2004
TOTAL NUMBER OF PAGES IN THIS PUBLICATION IS
339 CONSISTING OF THE FOLLOWING:
Page No.
Issue
Page No.
Issue
77 thru 79
0
Front Cover
0
80
1
Inside Front Cover
3
81 thru 85
0
Title
3
86
2
A, B, C
3
87, 88
0
1, 2
3
89 thru 91
1
3 thru 7
0
92, 93
0
*8
3
94
1
9/(10 blank)
0
95
0
11
1
96
2
12 thru 18
0
97
0
19
3
98
1
23/(24 blank)
0
99, 100
2
25, 26
2
101 thru 103
0
27, 28
0
104
3
29/(30 blank)
0
105
2
31
0
106
3
106a/(106b blank)
2
32
1
107
3
33, 34
0
108
1
35, 36
2
109
2
37 thru 40
0
110
0
41
1
111
1
45/(46 blank)
3
112
0
47 thru 51
3
113
1
52
0
114
2
53, 54
3
115
0
55 thru 58
0
116, 117
1
59
1
118 thru 120
0
60 thru 65
0
121/(122 blank)
3
66
3
123, 124
3
67
0
124a, 124b
3
68
3
125
1
69/(70 blank)
0
126
0
71 thru 74
0
126a, 126b
3
75, 76
2
127, 128
3
A Change 3
NAVAIR 01-F14AAP-1B
LIST OF EFFECTIVE PAGES (continued)
Page No.
Issue
Page No.
Issue
209 thru 213
0
129/(130 blank)
1
214
2
131
1
215, 216
0
132
0
217
2
133 thru 136
1
218 thru 221
0
136a/(136b blank)
1
222 thru 224
1
137 thru 146
0
224a, 224b
1
147/(148 blank)
0
225
1
149
0
226
0
150
2
227
3
151 thru 153
0
228 thru 235
0
154
2
236
2
*155
3
237, 238
0
156, 157
1
239
2
158 thru 160
0
240
3
161, 162
2
241
0
162a/(162b blank)
2
242
2
163 thru 165
0
243 thru 260
0
166
2
261/(262 blank)
2
167 thru 170
0
263
3
171/(172 blank)
0
264
0
173
3
265
2
174
2
266 thru 269
0
175 thru 177
0
270
2
178
1
271, 272
3
179, 180
0
273, 274
0
181
3
275, 276
3
182 thru 184
0
277 thru 281
0
185/(186 blank)
0
282
2
187
2
283
0
188
0
284
2
189/(190 blank)
3
285 thru 289
0
190a, 190b
3
290
2
190c/(190d blank)
3
291
0
191 thru 194
0
292, 293
2
195 thru 198
2
294, 295
0
199
0
296
2
200
2
297, 298
0
201 thru 204
0
299/(300 blank)
0
204a, 204b
3
301 thru 312
2
205(206 blank)
3
313/(314 blank)
2
207/(208 blank)
0
Inside back cover
0
ADDITIONAL COPIES:
Additional copies of this manual and changes thereto may be procured
IAW NAVSUP P 409 from NAVICP, Philadelphia via DAAS or the requisi-
tion can be submitted to Naval Supply System Command, NLL, Web site
Change 3
B
NAVAIR 01-F14AAP-1B
INTERIM CHANGE SUMMARY
The following Interim Changes have been cancelled
or previously incorporated into this manual.
INTERIM
CHANGE
NUMBER(S)
REMARKS/PURPOSE
1 thru 30
Incorporated
The following Interim Changes have been incorporated into
this Change/Revision.
INTERIM
CHANGE
NUMBER(S)
REMARKS/PURPOSE
31
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 — To be maintained by the
custodian of this manual.
INTERIM
CHANGE
ORIGINATOR/DATE
PAGES
REMARKS/
NUMBER(S)
(or DATE/TIME GROUP)
AFFECTED
PURPOSE
C Change 3
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-F14AAP-1B
F-14B AIRCRAFT
PILOT'S POCKET CHECKLIST
INTERIM CHANGE 32 & 33
REPLACEMENT PAGES
---------------------------
1. Replacement pages for Interim Change Numbers 32 & 33 to the F-14B
PCL, NAVAIR 01-F14AAP-1B dated 15 Jan 2004, are attached as follows:
Page
Page Version Marking
------
----------------------
123
Change 3 W/ IC 33
124
Change 3 W/ IC 33
124a
Change 3 W/ IC 33
124b
Change 3
127
Change 3 W/ IC 32
128
Change 3 W/ IC 32
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-F14AAP-1B
CRITICAL PROCEDURE
Procedures marked with an asterisk are considered to be time
critical and are so identified to emphasize their importance.
Pilots should be able to accomplish these procedures without
reference to the checklist.
EMERGENCY PROCEDURES INDEX
ENGINE FLAMEOUT .
49
A
ENGINE OVERSPEED .
54
ABNORMAL START .
47
ENG TRANSFER TO SEC MODE .
55
ABORTED TAKEOFF .
187
AFT WING SWEEP LANDING .
163
F
AICS MALFUNCTION .
62
FCS CAUTION LT .
94
ARI/SAS OUT LT (WITH ROLL DGR,
FIELD ARRESTMENT GUIDE .
168
YAW DGR OR ARI DGR .
96
FIRE
71
ASYMMETRIC WING SWEEP .
108
AWG-9 ACRONYM, LIGHT,
FLAP AND SLAT ASYMMETRY .
90
COOLANT PUMP(S) .
17
FLAP LIGHT .
92
AUTOPILOT LIGHT .
99
FLAP/SLAT UP LANDING .
161
AUX FLAP FAILURE .
160
FLIGHT CONTROLS .
77
FUEL IMBALANCE/FUEL QUANTITY
B
BALANCING .
127
FUEL MALFUNCTIONS .
121
BACKUP FLIGHT MODULE FAILURE .
144
FUEL LEAK .
126a
BARRICADE ARRESTMENT .
157
BINDING/JAMMED FLIGHT
G
CONTROLS ON THE GROUND .
84
BLOWN TIRE — T/O, LDG .
160, 188
GENERATOR MALFUNCTIONS .
31
BRAKE FAILURE AT TAXI SPEED .
158
GROUND EGRESS .
27
BRAKE MALFUNCTIONS .
157
GROUND ROLL BRAKING FAILURE .
157
C
H
CABIN PRESS LT .
17
HOOK EMER DOWN .
156
CADC LIGHT .
119
HYDRAULIC MALFUNCTIONS .
129
CANOPY LIGHT OR CANOPY LOSS .
20
HZ TAIL AUTH LIGHT .
99
COCKPIT OVER PRESS ON DECK .
16
COCKPIT TEMP CONTROL
I
MALFUNCTION .
16
INLET LIGHT .
65
COMPRESSOR STALL .
48
INLET ICE LIGHT .
65
CONTROLLABILITY CHECK .
77
INVERTED DEPARTURE/SPIN .
106
COOLING AIR LIGHT .
14
CROSSBLEED AIRSTART .
53
L
D
LADDER LIGHT .
21
LANDING/LANDING GEAR .
147
DFCS POWER ON RESET (POR) .
80
WITH AFT HUNG ORDNANCE .
165
DOUBLE GENERATOR FAILURE .
31
LAUNCH BAR LIGHT .
155
LIGHTS — WARNING, CAUTION,
E
ADVISORY .
3
ECS MALFUNCTIONS .
9
LOW-BRAKE ACCUMULATOR .
144
ECS LEAK/ELIMINATION OF
SMOKE AND FUMES .
11
M
EJECT/EGRESS
25
MANUAL BAILOUT .
26
EJECTION
25
ELECTRICAL MALFUNCTIONS .
29
MSL COND LIGHT (AIM-54 ABOARD) .
18
ELECTRICAL FIRE .
73
ENGINE MALFUNCTIONS .
45
N
ENGINE FAILURE — T/O .
173
NO FLAPS/SLATS LANDING .
161
ENGINE FIRE ON THE GROUND .
72
NOZZLE FAILURE .
59
Change 3
1
NAVAIR 01-F14AAP-1B
CRITICAL PROCEDURE
Procedures marked with an asterisk are considered to be time
critical and are so identified to emphasize their importance.
Pilots should be able to accomplish these procedures without
reference to the checklist.
EMERGENCY PROCEDURES INDEX
SPOILER LIGHT/MALFUNCTIONS .
85
O
STAB AUG TRANSIENTS .
98
OIL MALFUNCTIONS .
45
START VALVE LIGHT .
48
OUTBD SPOILER MODULE MALF .
89
STUCK/JAMMED THROTTLES (A/B) .
61
OXYGEN SYSTEM FAILURE .
19
T
P
TAKEOFF .
185
PITCH SAS LIGHT .
95
TARPS ECS LIGHTS .
18
POWER ON RESET (POR) .
80
TEMP CONTROL MALFUNCTION .
16
TOTAL ELECTRICAL FAILURE .
37
R
TRIM — RUNAWAY STAB .
98
RAMPS LIGHT .
62
RATS OPERATION IN FLIGHT .
67
U
ROLL DGR LIGHT, YAW DGR LT
UNCOMMANDED FUEL DUMP .
126
AND/OR ARI DGR LIGHT .
96
UNCOMMANDED ENGINE ACCEL .
58
RUDDER AUTH LIGHT .
100
UNCOMMANDED ROLL AND/OR YAW .
83
RUDDER HARDOVER .
100
UNCOMMANDED SEC MODE
RUNAWAY STABILIZER TRIM .
98
RPM DECAY .
57
UNSCHEDULED WING SWEEP .
107
S
UPRIGHT DEPARTURE/FLAT SPIN .
104
SINGLE-ENGINE OPERATIONS .
171
SINGLE-ENGINE TAKEOFF .
173
W
SINGLE-ENGINE LDG — PRI MODE .
173
WEIGHT ON/OFF WHEELS .
39
SINGLE-ENGINE LDG — SEC MODE .
176
WINGS SWEEP LIGHTS .
106a
SMOKE AND FUMES .
11
WSHLD HOT LIGHT .
21
2
Change 3
NAVAIR 01-F14AAP-1B
ADVISORY
LIGHT
LIGHT
CAUSE
ACTION
ACLS or autopilot
Take control for manual land-
disengagement.
ing approach.
AHRS
Failure of AHRS or com-
Use INS-IMU; avoid IFR flight
pass controller.
if INS-IMU not available.
Selected A/P reference is
Depress autopilot reference
not engaged.
pushbutton to engage A/P
reference mode.
Indicates degraded ARI
1. MASTER RESET
performance
2. See page 96.
Loss of Roll or Yaw SAS
1. Ensure ROLL and YAW
and all ARI functions.
STAB AUG switches
ON.
2. MASTER RESET.
3. See page 96.
Autopilot or reference
1. MASTER RESET
failure.
AUX
Low-extinguisher agent
Report to maintenance.
FIRE EXT
pressure.
Auto throttle has been
1. Assume manual/boost
disengaged.
control.
2. Satisfy APC interlocks.
3. Reengage APC AUTO.
AWG-9
Overheat in AWG-9 cool-
1. AWG-9 LIQ COOLING
COND
ant loop.
switch OFF
2. AWG-9 OFF
3. See page 17.
Totalizer less than preset
Pilot option
value.
Bleed duct overheat con-
*1. AIR SOURCE pushbut-
dition or ECS regulating
ton OFF
failure.
2. See page 11.
WARNING/CAUTION/ADVISORY LIGHTS (SHEET 1 OF 6)
3
NAVAIR 01-F14AAP-1B
LIGHT
CAUSE
ACTION
Operating in Aux brake
1.
Turn antiskid off.
mode or antiskid failure
2.
Cautious brake
application
3.
Release emergency
brake
Cabin pressure failure.
1.
O2 mask on
2.
See page 17.
CADC failure.
1.
MASTER RESET.
2.
See page 119.
Canopy not locked.
*1.
Boost close
*2.
EJECT CMD lever —
PILOT
3.
See page 20.
Controls and displays
1.
Select cabin air.
hot.
2.
WCS switch OFF.
COOLING
Indication of possible
1.
AIR SOURCE OFF
AIR
bleed duct failure for-
2.
Assume ECS malfunc-
(IN FLIGHT)
ward of the pressure pri-
tion. See page 15.
mary heat exchanger
and 400_F modulating
valve.
COOLING
Inadequate cooling.
1.
See page 14.
AIR
(ON DECK)
EMERG STORES JETT
If not after emergency
pushbutton may be acti-
jettison:
vated. Normal after
On deck — Report to
emergency jettison.
maintenance.
In flight —
1. Do not press EMERG
STORES JETT
pushbutton.
2. Obtain visual check of
stores status.
3. Avoid populated areas.
4. Land as soon as
practicable.
WARNING/CAUTION/ADVISORY LIGHTS (SHEET 2)
4
NAVAIR 01-F14AAP-1B
LIGHT
CAUSE
ACTION
Engine mode control in
1. Throttle — LESS THAN
secondary
MIL
2. ENG MODE SELECT
switch — CYCLE
3. See page 55.
ENG
Low-extinguisher agent
Report to maintenance
FIRE EXT
pressure.
DFCS failure has
1. MASTER RESET.
occurred. With no other
2. See page 94.
lights, indicates loss of
redundancy only.
FILM LOW
Mission Recorder film
Change film magazine.
low.
Fire/overheat condition in
*1. Throttle IDLE
engine nacelle
*2. AIR SOURCE OFF.
3. See page 71.
Flap position disparity
1. Airspeed below 225
with commanded position
KIAS.
or asymmetric
2. See page 92.
procedures.
Usable fuel in L and AFT
1. DUMP switch OFF.
or R and FWD fuselage
2. See page 124.
tanks 1,000 pounds.
Sump tank boost pump
1. Both throttles — MIL
discharge less than 9 psi.
POWER OR LESS
2. Restore aircraft to 1.0g
flight.
3. See page 123.
AWW-4 electric fuse
Use manual fuse.
inoperative
Gen failure and/or dis-
1. Reset
connected from its ac
2. See page 31.
bus.
WARNING/CAUTION/ADVISORY LIGHTS (SHEET 3)
5
NAVAIR 01-F14AAP-1B
LIGHT
CAUSE
ACTION
Combined or flight pump
1. See page 133.
discharge pressure 2,100
psi or less.
CADC failure or failure of
1. MASTER RESET (10
actuators to follow
seconds)
schedule.
2. Above 400 KIAS, restrict
lateral control to 1/4
throw.
3. No oversweep on deck
4. See page 99.
IMU
Failure of IMU.
Switch to AHRS.
INTEG
Power loss or discrep-
1. MASTER RESET
trim
ancy between input sig-
2. Cycle INTEG TRIM cb’s
nal and position.
resetting DC (8F3), then
AC (1I2)
3. Pull cb’s and leave out if
light remains on.
Computer malfunction or
*1. Avoid abrupt throttle
ramp mispositioning.
movements.
*2. Decelerate below 1.2
IMN.
3. See page 62.
Icing condition exists
1. Select ORIDE/ON.
inlet or eng anti-ice is on.
2. When clear of icing con-
ditions select AUTO/
OFF.
3. See page 65.
LADDER
Ladder not stowed.
1. Airspeed minimum.
2. See page 21.
LAUNCH
Launch bar unlocked,
As appropriate.
BAR
engines < MIL thrust.
(Ground)
LAUNCH
Launch bar not locked in
1. Do not retract landing
BAR
up position or cocked
gear.
(Flight)
nose gear.
2. See page 155.
Actuated by any light on
Push to reset after discrete
caution panel.
MSG noted.
WARNING/CAUTION/ADVISORY LIGHTS (SHEET 4)
6
NAVAIR 01-F14AAP-1B
LIGHT
CAUSE
ACTION
ECS
MACH TRIM
Failure of mach trim
1. MASTER RESET
actuator to follow
2. Retrim manually.
program.
MSL COND
AIM-54 coolant hot or no
1. Check LIQ COOLING
flow.
switch.
2. LIQ COOLING switch to
AWG-9 if AWG-9/
AIM-54 selected.
3. See page 18.
NAV COMP
Navigation system advi-
Check Navigation System
sory.
status on CDNU.
Nosewheel steering is
Disengage before catapult
engaged.
or when runway heading
established.
Engine oil temp limits
1. On deck increase fuel
exceeded or high
flow.
scavenge-oil temp.
2. Airborne see page 66.
L or R oil press <11 psi.
1. Throttle IDLE.
2. See page 67.
Qty ≤ 2 liters.
1. Inform pilot.
2. See page 20.
Indicates inoperative
1. MASTER RESET.
pitch channel or pitch
2. If light remains, no
SAS failure.
limitations.
3. See page 95.
Computer/Mechanical
*1. Avoid abrupt throttle
malfunction or ramp mis-
movements.
positioning.
*2. Decelerate to below 1.2
IMN.
3. See page 62.
RATS
RATS operation enabled
As appropriate.
Radar operation on
WCS switch to STBY (as
ground is possible.
applicable).
Flaps fail down, airspeed
1. Reduce speed.
225 KIAS
2. Check FLAP handle.
Total temp 338_F, 2.4 M
3. MASTER RESET
WARNING/CAUTION/ADVISORY LIGHTS (SHEET 5)
7
NAVAIR 01-F14AAP-1B
LIGHT
CAUSE
ACTION
ECS
Indicates inoperative roll
1. MASTER RESET
channel and degraded
2. See page 96.
roll authority.
CADC failure or failure
1. MASTER RESET (10
of actuator to follow
seconds)
schedule.
2. See page 100.
Symmetric spoiler detec-
1. MASTER RESET.
tor has locked down
2. See page 85.
spoilers.
Starter solenoid air valve
1. Ensure ENG CRANK —
open after engine start.
OFF
2. AIR SOURCE pushbut-
ton OFF.
3. See page 48.
Engine stall and/or over-
See COMPRESSOR STALL
temp, or faulty monitor
and ENGINE FLAME-OUT
circuit.
procedures, page 48.
TARPS ECS
Overtemp in TARPS pod.
1. TARP sensors-OFF.
2. SYSTEM switch- OFF.
3. See page 18.
TRANS/
Lack of dc output from
Check bus tie:
RECT
either or both T/R.
Left T/R — Master Test.
Right T/R — OTBD spoilers
See page 31.
Landing gear not down
Lower gear.
with flaps down and
either throttles ≤ 85%.
Failure of both wing
1. Decelerate to below
sweep channels, or spi-
0.9 M.
der detent disengaged.
2. See page 106.
WING
Failure of one wing
1. MASTER RESET
SWEEP
sweep channel.
2. See page 106a.
WSHLD HOT
Center windshield temp
1. WSHLD AIR switch
300_F.
OFF.
2. See page 21.
Indicates inoperative yaw
1. MASTER RESET
channel and degraded
2. See page 96.
yaw authority.
WARNING/CAUTION/ADVISORY LIGHTS (SHEET 6)
8
Change 3
NAVAIR 01-F14AAP-1B
ECS
Index
AWG-9 COND LIGHT ILLUMINATED
AND/OR PUMP PHASE CIRCUIT
BREAKERS POPPED OR AWG-9 PM ACRONYM .
17
CABIN PRESS LIGHT .
17
CANOPY LIGHT OR CANOPY LOSS .
20
COCKPIT TEMPERATURE CONTROL
MALFUNCTION .
16
COOLING AIR LIGHT .
14
IN FLIGHT .
15
ON DECK .
14
COCKPIT OVER PRESSURIZATION ON DECK .
16
ECS LEAK/ELIMINATION OF SMOKE AND FUMES .
11
DIRECT INDICATIONS OF ECS MALFUNCTION .
11
INDIRECT INDICATIONS OF ECS MALFUNCTION .
11
LADDER LIGHT .
21
MSL COND LIGHT (AIM-54 ABOARD) .
18
OXYGEN SYSTEM FAILURE .
19
OXY LOW LIGHT (RIO ONLY) .
20
TARPS ECS LIGHTS .
18
WSHLD HOT LIGHT .
21
9/(10 blank)
NAVAIR 01-F14AAP-1B
ECS LEAK/
ELIMINATION OF
ECS
SMOKE AND FUMES
D Failure to immediately select AIR
SOURCE OFF upon indication of an
ECS leak may result in severe air-
craft damage.
D Selection of AIR SOURCE to RAM
allows bleed air to circulate through-
out the 400 °F manifold system.
DIRECT INDICATIONS OF ECS MALFUNCTION
a. BLEED DUCT caution light or FIRE warning
light
b. Smoke or fumes in cockpit
c. Heat emanating from behind aft right comer
of RIO cockpit
d. Complete loss of ECS airflow.
INDIRECT INDICATIONS OF ECS MALFUNCTION1
a. Audible pop or squeal from ECS
b. Rapid drop in cockpit airflow or reduced air-
flow
c. Electrical fire indications
d. Any ECS advisory light (AWG-9 COND, MSL
COND, or COOLING AIR).
CONTINUED
Change 1
11
NAVAIR 01-F14AAP-1B
The presence of any one direct indication or any two
indirect indications shall be treated as an ECS leak.
When an ECS leak occurs or smoke or fumes are present:
*1. AIR SOURCE .
OFF
*2. If smoke or fumes are present:
a. Altitude Below 35,000 Feet
b. Cabin PRESS switch DUMP
*3. RAM AIR INCR
Note
RAM air door may take up to 50 sec-
onds to fully open.
4. Airspeed Below .
300 KIAS/0.8 IMN
5. Nonessential electrical equipment .
Secure
6. CANOPY DEFOG-CABIN AIR
lever .
CANOPY DEFOG
7. Land as soon as possible.
If electrical fire:
8. Follow electrical fire procedures.
CAUTION
The emergency generator switch
should be left in NORM unless there are
overriding considerations that man-
date turning the emergency generator
off.
CONTINUED
12
NAVAIR 01-F14AAP-1B
Note
D
Securing all electrical power while
airborne closes cockpit dump valve
and cabin hot air valve, opens bleed
air shutoff valves and dual-pressure
regulator, and the ram air door re-
mains at its last commanded posi-
tion (ram air door takes up to 50
seconds to open). This results in full
cold air to the cockpit, uncontrolled
bleed air to circulate, and the loss of
normal cabin-dump capability. Mini-
mize low speed (less than 0.25 IMN)
and ground operations as the heat
exchanger cooling fan will be inop-
erative and ECS overheat condition
will result.
D
Selecting AIR SOURCE OFF elimi-
nates pressurization to the service
system (canopy, g-suit, external fuel
tanks, pressure/ ventilation suit, and
airbag seals). Rain removal, defog,
and heating systems are also elimi-
nated.
D
If ECS airflow continues, ensure AIR
SOURCE CONTROL (RC2) cb is in.
If cb RC2 has popped, ECS control is
lost.
CONTINUED
13
NAVAIR 01-F14AAP-1B
Note
Elimination of smoke or fumes without
electrical power may be accomplished
by ECS airflow. To obtain maximum
smoke/fume removal capability under
this condition, fly below 8,000 feet MSL
and set the throttle to maximum practi-
cal position. This will open the cabin
regulator valve for maximum ECS air-
flow. If smoke or fumes are not elimi-
nated, it is most probable that smoke/
fumes are being regenerated by an
ECS air leak. As a last resort, jettison
the canopy.
COOLING AIR LIGHT
ON DECK
1. AIR SOURCE .
Check L ENG, R ENG,
or BOTH ENG
2. Throttles . ..Advance Without Closing Nozzles
3. CANOPY DEFOG-CABIN
AIR lever .
CANOPY DEFOG
4. ECS .
MAN/FULL HOT
If light goes out:
5. Throttles .
IDLE
6. ECS .
As Desired
If light remains illuminated:1234
5. Secure systems.
CONTINUED
14
NAVAIR 01-F14AAP-1B
IN FLIGHT
1. AIR SOURCE .
OFF
Failure to immediately select AIR
SOURCE pushbutton OFF upon indica-
tion of an ECS leak (bleed air or hot air
leak indication) or upon hearing ECS
turbine whine may result in an uncon-
trollable electrical fire, catastrophic
ECS component failure, and/or loss of
flight controls.
If associated with any other direct or indirect indication of
ECS malfunction:
2. Perform ECS Leak/Elimination of Smoke and
Fumes procedure.
If not associated with any other direct or indirect indication
of ECS malfunction and operational requirements dictate
temporary reselection of RAM to regain lost service sys-
tems (external fuel transfer, cabin pressure, rain removal,
engine anti-ice, etc.):
3. AIR SOURCE .
RAM
4. RAM AIR switch .
FULL INCR
5. AIR SOURCE .
OFF (when service
system no longer required)
6. Land as soon as practicable.
15
NAVAIR 01-F14AAP-1B
COCKPIT TEMPERATURE CONTROL
MALFUNCTION
1. TEMP mode switch .
MAN
2. TEMP thumbwheel .
As Desired
If temperature control is not regained:
CAUTION
Reduce airspeed to 350 KIAS or 1.5 IMN,
whichever is lower, to prevent ram air at
temperature above 110 °F from entering air-
craft. After ram air flow is stabilized, air-
speed may be increased as required for
flightcrew comfort or to increase flow to
electronic equipment.
3. VENT AIRFLOW .
OFF
4. AIR SOURCE .
RAM (below 35,000 feet)
5. RAM AIR .
INCR (select amount of ram air
desired for flightcrew comfort)
COCKPIT OVER PRESSURIZATION ON DECK
1. AIR SOURCE pushbutton .
OFF
2. CABIN PRESS switch .
DUMP
3. Canopy .
OPEN when cockpit pressure
altimeter equals the field elevation
CONTINUED
16
NAVAIR 01-F14AAP-1B
The canopy may explosively leave the
aircraft upon unlocking of the canopy
sill locks if cockpit overpressure is not
reduced.
CABIN PRESS LIGHT
1. Oxygen masks .
ON
If below 15,000 feet:
2. CABIN PRESS switch .
Cycle
AWG-9 COND LIGHT ILLUMINATED AND/OR
PUMP PHASE CIRCUIT BREAKERS POPPED
OR AWG-9 PM ACRONYM
1. LIQ COOLING switch .
OFF
2. WCS switch .
OFF
3. ANT SVO HYD PH A, B, C
(IF2, IF4, IF6) cb’s .
Pull
4. AN/AWG-9 PUMP PH A, B, C
(2G3, 2G6, 2G7) cb’s .
Pull
If associated with any other direct or indirect indication of
ECS malfunction, perform ECS Leak/Elimination of
Smoke and Fumes procedure.
5. Land as soon as practicable.
17
NAVAIR 01-F14AAP-1B
TARPS ECS LIGHTS
1. TARPS sensors .
OFF
2. SYSTEM switch .
OFF
3. Pull TARPS cb’s:
a. RECON ECS CONT DC (8G7)
b. RECON ECS CONT AC (2E2)
c. RECON HTR PWR PH A (2B1)
d. RECON HTR PWR PH B (2D1)
e. RECON HTR PWR PH C (2F1)
f. RECON POD (1F4)
g. RECON POD CONTR (8F7)
h. RECON POD DC PWR NO 2 (8F1)
i. RECON POD DC PWR NO 1 (8F2)
4. Ask for visual check of pod by wingman.
5. Land as soon as practicable.
MSL COND LIGHT (AIM-54 ABOARD)
1. LIQ COOLING .
Check
If LIQ COOLING switch is in AWG-9/AIM-54:
2. LIQ COOLING .
AWG-9
3. STA 3/6 AIM-7/AIM-54 PUMP
PH A, B, C (1D1, 1D3, 1D7) cb’s .
Pull
4. MSL HTR PH A, B, C
(2G2, 2G5, 2G8) cb’s .
Pull
CONTINUED
18
NAVAIR 01-F14AAP-1B
If associated with any other direct or indirect indication of
ECS malfunction, perform ECS Leak/Elimination of
Smoke and Fumes procedure:
5. Land as soon as practicable.
OXYGEN SYSTEM FAILURE
1. Oxygen quantity .
Check
2. If possible, descend cabin altitude to less than
10,000 feet.
With mask removed, loss of cabin pres-
sure above 10,000 feet MSL can rapidly
cause hypoxia.
3. If not possible to descend, actuate emergency
oxygen.
Once emergency oxygen is actuated, the
oxygen flows until the emergency bottle
is depleted (approximately 10 minutes).
However, in worst case conditions,
depletion could occur in significantly
less than 10 minutes.
Change 3
19
NAVAIR 01-F14AAP-1B
OXY LOW LIGHT (RIO ONLY)
1. Notify pilot.
2. Oxygen quantity .
Less Than 2 Liters
3. Cabin altitude .
Less Than 10,000 Feet
4. Oxygen masks .
Release One
Side
With mask removed, loss of cabin pres-
sure above 10,000 feet MSL can rapidly
cause hypoxia.
5. OXYGEN switch .
OFF
Before landing:
6. OXYGEN switch and masks .
ON
CANOPY LIGHT OR CANOPY LOSS
*1. Canopy handle .
BOOST CLOSE
(canopy remaining)
*2. EJECT CMD lever .
Pilot
3. Airspeed and altitude .
Below 200 KIAS/
15,000 Feet
4. Seats and visors .
Down
5. If canopy has departed
aircraft .
Perform
Controllability Check
6. Land as soon as possible.
20
NAVAIR 01-F14AAP-1B
LADDER LIGHT
1. Airspeed .
Minimum Safe Operating
2. Obtain in-flight visual check if possible.
EJECT
EGRESS
3. Land as soon as practicable.
WSHLD HOT LIGHT
1. WSHLD AIR
OFF
If light remains illuminated:
2. Reduce airspeed to less than 300 KIAS or 0.8
IMN.
3. AIR SOURCE .
OFF (below 35,000 feet)
Note
If light remains illuminated after air
source is off, indication is faulty. Turn
ECS on and land as soon as practica-
ble.
4. RAM AIR
INCR
5. Land as soon as practicable.
21
NAVAIR 01-F14AAP-1B
EJECT
EGRESS
22
NAVAIR 01-F14AAP-1B
EJECT/EGRESS
Index
CONTROLLED EJECTION .
25
GROUND EGRESS WITHOUT
PARACHUTE AND SURVIVAL KIT .
27
MANUAL BAILOUT .
26
23/(24 blank)
NAVAIR 01-F14AAP-1B
CONTROLLED
EJECT/EGRESS
EJECTION
Do not secure engines. Unsuccessful
seat activation may require continued
flight to allow alternate egress method.
1. Place aircraft in safe envelope and attitude for
ejection.
2. Warn other crewmember.
3. EJECT CMD lever .
Select (RIO)
4. IFF/SIF .
EMERG/7700 (RIO)
5. Position report .
Transmit
6. Check altimeter.
7. Assume proper eject position:
a. Head pressed back against headrest.
b. Chin slightly elevated (10° up).
c. Back straight.
d. Hips against seat back.
e. Thighs flat on seat survival kit.
f. Elbows and arms pressed firmly against
body.
g. Feet on rudder pedals, heels on deck.
h. Visor down, oxygen mask tightened, helmet
secure.
CONTINUED
Change 2
25
NAVAIR 01-F14AAP-1B
D Positioning the legs aft prior to
ejection will cause the spine to flex
and will increase the possibility of
spinal injury and will also increase
likelihood of seat/thigh slap with
attendant leg injury.
D Proper body position is a critical
factor in preventing ejection
injuries.
D Minimum ejection altitudes are de-
pendent upon dive angle, airspeed,
and angle of bank.
MANUAL BAILOUT
Manual bailout below 2,000 feet AGL
(minimum sink rate): may not allow
sufficient altitude for parachute
deployment.
1. Warn RIO.
2. Place aircraft in safe envelope.
3. Ensure canopy is jettisoned.
4. Pitch trim .
Full Nose Down
CONTINUED
26
Change 2
NAVAIR 01-F14AAP-1B
5. Emergency restraint release .
Pull
6. Ensure seat pan and leg restraints are discon-
nected from ejection seat.
7. Release stick.
8. Roll forward and push free of aircraft.
ELECT
GROUND EGRESS WITHOUT PARACHUTE
AND SURVIVAL KIT
1. Kneel aircraft (if possible)
2. Canopy . .
Open or Jettison
3. Parking brake
Pull
4. Ejection seat
Safe
5. All fittings
Release
(restraint fittings and O2 hose)
27
NAVAIR 01-F14AAP-1B
ELECT
28
NAVAIR 01-F14AAP-1B
ELECTRICAL
Index
DOUBLE GENERATOR FAILURE .
31
ESSENTIAL BUSES NO. 1 (1 KVA MODE) .
33
ESSENTIAL BUSES NO. 2 .
34
FAILURE OF BOTH TRANSFORMER-RECTIFIERS
EQUIPMENT INOPERATIVE LIST .
36
L OR R GEN LIGHT .
31
L OR R GEN AND TRANS/RECT LIGHTS .
31
TOTAL ELECTRICAL FAILURE .
37
WEIGHT ON/OFF WHEELS SWITCH MALFUNCTION .
39
IN FLIGHT .
41
IN FLIGHT — PILOT .
42
IN FLIGHT — RIO .
42
ON DECK .
39
ON DECK — PILOT .
40
ON DECK — RIO .
40
29/(30 blank)
NAVAIR 01-F14AAP-1B
L OR R GEN LIGHT
ELECTRICAL
1. Generator (affected generator
switch .
OFF/RESET,
Then NORM
If generator does not reset:
2. Generator (affected generator
switch) .
TEST
a. GEN light off .
Distribution System
b. GEN light illuminated .
IDG or GCU
L OR R GEN AND TRANS/RECT LIGHTS
1. Generator (affected generator
switch) .
OFF/RESET, Then NORM
2. If L GEN and TRANS/RECT light remains
illuminated, select EMERG GEN on MASTER
TEST panel.
3. Land as soon as practicable.
DOUBLE GENERATOR FAILURE
1. Both generator switches .
Cycle
When operating on emergency generator, the following
important systems are inoperative:
a. Emergency flight hydraulics.
b. Outboard spoiler module and emergency flap
activation.
CONTINUED
31
NAVAIR 01-F14AAP-1B
If temporary loss of combined system pressure causes
emergency generator to shift to 1 kVA mode:
2. EMERG generator switch .
Cycle
CAUTION
A shift to 1-kVA mode will cause loss of
all DFCS functions and spoilers with-
out illumination of caution lights. If the
5 kVA mode is regained, a MASTER RE-
SET will be required to regain SAS,
spoiler, authority stop, and ARI
functions.
Note
DFCS synchronization can take up to
2 seconds following a power interrupt.
If the MASTER RESET pushbutton is
depressed during the synchronization
time, an additional depression of the
MASTER RESET pushbutton will be
required to restore spoiler functionality.
3. Land as soon as practicable.
CONTINUED
32 Change 1
NAVAIR 01-F14AAP-1B
ESSENTIAL BUSES NO. 1 (1 KVA MODE)
ACM Control
Fuel Quantity Indicator
AICS Ramp Stow
Hydraulic Pressure
Indication (Flight
Airspeed Indication
and Combined)
Altitude Low Warning
ICS
Approach Lights
IFF
Angle-of-Attack
Jettison (Emergency)
Indication
KY-28 or KY-58
AWG-15
Master Arm
Barometric Altimeter
Missile Release
ECM Destruct
Pilot Instrument Lights
Engine Backup
Radar Altimeter
Ignition
Standby Attitude
Engine Instrument
Indicator
Group
Turn-and-Slip
Engine Stall Tone
Indicator
Engine Stall Overtemp
VHF/UHF (Receiver-
Warning
Transmitter)
Antenna Selection
Fire Detection
Remote Indicator,
Fire Extinguishing
Cryptographics)
Flap/Slat Position Ind
Wing Position
Floodlights
Indications
CONTINUED
33
NAVAIR 01-F14AAP-1B
ESSENTIAL BUSES NO. 2
ACM Panel Lights
ECM (Navigational
Aids,
ADF
IFF Interrogator, and
Advisory Lights
Transmitter)
DFCS/SAS
Eject Command
Indicator
AHRS
Electronic Cooling
AICS
Emergency Generator
Air-Conditioning
Test
Air Source Control
Engine:
Antiskid Control
Anti-Ice
Arresting Hook Con-
Fan Speed Limiting
trol
Circuit of AFTC
Nozzle Reset
ARI AOA System
Oil Cooling (GRD
Auxiliary Flap Control
only)
BDHI
Oil Pressure
Beacon Augmenter
Indicators
Cabin Pressure Dump
Starting (Ground Use
or Crank)
CADC
Fuel Control
Caution Lights
Fuel Control Indicators
Cockpit Temperature
Flight Control Trim
Control
Fuel Feed/Dump/
Control Surface
Transfer
Position Indicator
Fuel Management Panel
(Tail, Rudder, and
Spoilers)
Ground-Roll Braking
CSDC
HUD
CONTINUED
34
NAVAIR 01-F14AAP-1B
ESSENTIAL BUSES NO. 2 (Cont.)
Hydraulic Valve
Radar Beacon
Control
Servo-pneumatic
Ice Detection
Altimeter
ILS
Speedbrakes
In-Flight Refueling
Spoiler Control
Probe/Light
Tacan
Launch Bar
Utility/Map Lights
PMDIG (Display Panel)
VDIG(R)
Nose Landing Gear
Warning Lights
Kneeling
Wheels and
Nosewheel Steering
Speedbrakes Position
Oxygen Quantity
Indicator
Indicators
Windshield Air
Probe Anti-Ice (AOA,
Windshield Anti-Ice
Total Temperature,
Pilot)
Wing Sweep
CONTINUED
Change 2
35
NAVAIR 01-F14AAP-1B
FAILURE OF BOTH TRANSFORMER-
RECTIFIERS EQUIPMENT INOPERATIVE
LIST
AIM-7 MOTOR FIRE
GUN CONTROL POWER
AIM-54 MISSILE
GYRO POWER
ALE-47 CHAFF/FLARE
IFF AIR TO AIR
DISPENSER
INTEGRATED TRIM
ALR-67 RECEIVER/
INTERRUPTION FREE
CONTROL
DC BUS FOR NO. 1
AMC BIT
AND 2
AMCS ENABLE
L AND R AIM-7
BATTERY ARM
ANTENNA LOCK
EXCITER
LIQUID COOLING
APX-72 TEST SET
CONTROL
AUTOTHROTTLE
MASTER TEST
CONTROL DISPLAY
MECHANICAL FUZING
STA 5 AND 6
SUBSYSTEMS
MECHANICAL FUZING
COOLING INTERLOCK
STA 3 AND 4
COUNTING
MECHANICAL FUZING
ACCELEROMETER
STA 1 AND 2
DATA LINK
MISSILE AUXILIARY
DDI/ANNUNCIATOR
SUBSYSTEMS
PANEL DIM CONTROL
MONITOR BUS
DEHYDRATOR UNIT
CONTROL
DIGITAL DATA INDICATOR
OUTBOARD SPOILER
EGI
MODULE
ELECTRONIC COOLING
RADAR SUBSYSTEMS
EMERG. GENERATOR
RIGHT DC TEST
CONTROL
STA 1A, 1B, 8A, 8B
FEMS
AIM-9 POWER
FUZE FUNCTION
STA 1, 8, 8B AIM-9
CONTROL
COOLING POWER
GROUND POWER
TARPS
GROUND TEST
TCS
GUN ARMED POWER
WINDSHIELD DEFOG
GUN CLEAR POWER
CONTROL
36
Change 2
NAVAIR 01-F14AAP-1B
TOTAL ELECTRICAL FAILURE
1. Descend or climb to known VFR conditions.
CAUTION
All DFCS functions and spoilers will be
lost. This will have an adverse effect on
flying qualities. Terminate aggressive
maneuvering immediately and remain
subsonic. Expect minimal damping of
oscillations in pitch and yaw and
severely degraded roll control with
flaps extended. Perform controllability
check.
Note
D The standby attitude gyro is capable
of providing reliable attitude infor-
mation (within 6º) for up to9 minutes
after a complete loss of power.
D Cabin pressure will be lost and ECS
will go full cold.
2. Attempt to contact radar facilities or other
aircraft by hand-held survival radio.
3. Make arrested landing as soon as possible.
The following systems are still available:
1. Airspeed indicator.
2. Altimeter (STBY mode).
CONTINUED
37
NAVAIR 01-F14AAP-1B
3. Cabin pressure altimeter.
4. Vertical velocity indicator.
5. Arresting hook (emergency extension only).
6. Standby attitude gyro (9 minutes).
7. Emergency wing sweep.
8. Landing gear.
9. Main flaps/slats.
10. Standby compass.
Ground engine operation without elec-
trical power supplied by either the gen-
erators or external power may cause
20-mm ammunition detonation be-
cause of excessive heat in the gun
ammunition drum.
CAUTION
Do not operate engines on the ground
without electrical power. Ground cool-
ing fans are shut off, causing hot bleed
air to cook off oil and hydrocarbons in
the ECS ducting, resulting in smoke in
the cockpit and possible damage to the
ECS turbine compressor.
CONTINUED
38
NAVAIR 01-F14AAP-1B
Note
D Total electrical failure will cause the
sump tank interconnect, engine
crossfeed, and motive flow isolation
valves to close, fully isolating both
tank systems. Wing and external
fuel will transfer into fuselage.
D If possible, section IFR descent
should be conducted to VFR condi-
tions for landing.
WEIGHT ON/OFF WHEELS SWITCH
MALFUNCTION
ON DECK
INDICATIONS:
1. WOW acronym is displayed.
2. Approach indexer is illuminated.
3. Nozzles may be partially closed at idle rpm.
4. Nosewheel steering is inoperative.
5. Launch bar light is illuminated
(if nosegear
turned > 10_).
6. Ground-roll braking is inoperative.
7. WG SWP MASTER TEST is disabled.
8. Oversweep is disabled.
9. Outboard spoiler module on with FLAP handle
UP (wings < 62_).
10. Aircraft will not kneel.
CONTINUED
39
NAVAIR 01-F14AAP-1B
If two or more of the preceding anomalies are detected,
the following action should be taken:
ON DECK — PILOT
1. Clear runway (if applicable).
2. Generators .
OFF
3. Throttles (after downlocks are in place) . . OFF
CAUTION
Failure of the left or right weight on/off
wheels switches to the in-flight mode
can cause loss of engine ejector air to
the engine oil, IDGs and hydraulic heat
exchangers, causing thermal discon-
nect and/or heat damage to the genera-
tors and aircraft hydraulic systems.
ON DECK — RIO
1. WCS .
OFF
With failure of the weight on/off wheels
switch to the in-flight mode, the follow-
ing functions are enabled.
a. AWG-9 can scan and radiate.
b. ALQ-126 can transmit.
c. Probe heaters will be on in AUTO.
CONTINUED
40
NAVAIR 01-F14AAP-1B
d. ALQ-167 can radiate (TARPS).
e. BOL chaff can dispense.
IN FLIGHT
For most systems, failure of both the left and right
weight-on-wheels switches is required to cause the
systems to revert to the on-deck mode. Should such
failures occur, the following anomalies can result:
INDICATIONS:1
a. Approach indexers are inoperative.
b. APC will not engage.
c. Outboard spoiler module inoperative (flaps
up).
d. Nozzles full open (gear down, throttles IDLE).
e. Ground-roll spoiler braking (throttles IDLE).
f. Radar will not scan.
g. Autopilot cannot be engaged.
h. BOL chaff will not dispense.
i. At high altitude, ground cooling fans may
overspeed and shut down, causing smoke in
cockpit.
j. RATS will be enabled airborne with the hook
handle down or the hook out of the stowed
position.
With RATS enabled airborne, military
power provides 20 to 25 percent less
thrust than normal, resulting in less
than optimum waveoff and bolter
performance.
CONTINUED
Change 1
41
NAVAIR 01-F14AAP-1B
If two or more of the above anomalies are detected, the
following action should be taken.
IN FLIGHT — PILOT
Do not move both throttles to IDLE un-
less ANTI SKID SPOILER BK switch is
set to OFF if weight on-off wheels
switch is suspected because of loss of
thrust and lift caused by nozzles open-
ing and spoilers deploying.
1. Throttles .
Any position except IDLE
2. ANTI SKID SPOILER BK switch .
OFF
3. Land as soon as practicable.
CAUTION
If weight on/off wheels switch failure is
suspected, cocked-up, high-sink rate
landing can result in damage to
afterburner.
IN FLIGHT — RIO
1. MLG SAFETY RLY NO. 1 and
MLG SAFETY RLY NO. 2 cb . ... Pull (6F5, 6F4)
CONTINUED
42
NAVAIR 01-F14AAP-1B
Note
D Circuit breakers can be reset after
touchdown to enable ground-roll
braking, antiskid, nozzles open at
idle, and nosewheel steering.
D Circuit breakers must be reset
simultaneously (within 0.1 sec) once
on deck or a secondary fault may be
declared which will inhibit ground
roll braking.
ENG
43
NAVAIR 01-F14AAP-1B
ENG
44
NAVAIR 01-F14AAP-1B
ENGINE
Index
ABNORMAL START .
47
AICS MALFUNCTION .
62
COMPRESSOR STALL .
48
CROSSBLEED AIRSTART .
53
ENGINE FLAMEOUT .
49
ENGINE OVERSPEED
(N2 107.7-PERCENT RPM) .
54
ENGINE START VALVE LIGHT .
48
ENGINE TRANSFER TO SEC MODE .
55
TRANSFER TO SECONDARY MODE RESULTS .
56
EXHAUST NOZZLE FAILED .
59
NO NOZZLE RESPONSE TO
THROTTLE MOVEMENT .
59
INLET ICE LIGHT .
65
L OR R OIL HOT LIGHT .
66
OIL PRESS LIGHT AND/OR
ABNORMAL OIL PRESSURE .
67
RATS OPERATION IN FLIGHT .
67
STUCK OR JAMMED THROTTLES
IN AFTERBURNER .
61
RAMPS LIGHT/INLET LIGHT .
62
UNCOMMANDED SEC MODE RPM DECAY .
57
UNCOMMANDED ENGINE ACCELERATION —
AIRBORNE (NO THROTTLE MOVEMENT) .
59
UNCOMMANDED ENGINE ACCELERATION —
ON DECK .
58
Change 3
45/(46 blank)
NAVAIR 01-F14AAP-1B
ABNORMAL START
ENGINE
1. Throttle (affected engine) .
OFF
2. BACKUP IGNITION switch .
Check OFF
CAUTION
A catastrophic Hot Start will occur if
the affected throttle is not immediately
secured following a loss of electrical
power during an engine start with the
RPM below forty percent. Air flow will
be cut off and fuel will continue to be
scheduled to the engine with the igni-
tors firing, causing a rapid and severe
rise in EGT that will not be observed on
the EIG due to power loss.
Note
D If hot start on deck, windmill engine
until EGT is below 250 _C before
attempting restart.
D If wet start, continue cranking until
tailpipe is clear of fuel.
Change 3
47
NAVAIR 01-F14AAP-1B
ENGINE START VALVE LIGHT
1. Ensure ENG CRANK .
OFF
2. AIR SOURCE .
OFF
Note
If operational necessity dictates, AIR
SOURCE L ENG or R ENG may be se-
lected provided the START VALVE light
remains out. Crossbleed airstarts may
not be available to the affected engine
after a START VALVE light illuminates
because of possible overspeed
damage.
If airborne:
3. ENG START (RE1) cb .
Pull
If on deck:12
3. Throttle (affected engine) .
OFF
COMPRESSOR STALL
*1. Unload aircraft (0.5 to 1.0g)
If greater than 1.1 IMN:
*2. Both throttles .
MIL
When 1.1 IMN or less:
*3. Both throttles .
Smoothly to IDLE
CONTINUED
48
Change 3
NAVAIR 01-F14AAP-1B
If EGT above 935_C and/or engine response abnormal:
*4. Throttle (affected engine) .
OFF
If EGT normal and/or airstart successful:
5. Perform engine operability check.
Note
After any stall, throttle movement should
be minimized until engine operability
checks are performed. Engines should
be exercised at 10,000 feet in cruise and
then at approach speeds, one at a time,
to ensure stall-free performance is avail-
able for landing. If engine performance is
abnormal, set power as necessary and
avoid further throttle movement. Land as
soon as practical.
ENGINE FLAMEOUT
*1. Throttle (affected engine) .
IDLE or Above
*2. BACKUP IGNITION switch .
ON
If hung start or no start:
*3. Throttle (affected engine) Cycle OFF, Then IDLE
If still hung or no start:
*4. ENG MODE SELECT switch .
SEC
CONTINUED
Change 3
49
NAVAIR 01-F14AAP-1B
If one engine is operable, perform a crossbleed airstart.
If both engines flamed out/inoperative or crossbleed not
possible:
D
A dual engine compressor stall may
result in a total electrical failure,
rendering the ICS, engine instru-
ments, spin direction indicators
(spin arrow and turn needle), and
displays inoperative.
D
If
sufficient hydraulic pressure
restores the
1-kVA mode of the
emergency generator, it may be nec-
essary to cycle the emergency gen-
erator
switch through OFF/
RESET to NORM to regain lost
engine instruments.
D
With existing ejection seat design
limitations, the decision to exceed
350 KIAS rests with the aircrew.
D
Sufficient hydraulic pressure for
smooth flight control inputs should
be available with one engine wind-
milling at
18 percent rpm or two
engines at 11 percent rpm.
D
Dive angles should not exceed 45_.
At 7,500 feet AGL minimum, com-
mence smooth 2g pullup to 20_ dive,
maximum. At 2,000 feet AGL mini-
mum, pull up to level flight. If airstart
is unsuccessful, convert airspeed to
altitude and eject at 350 KIAS or less
before controllability is lost.
CONTINUED
50
Change 3
NAVAIR 01-F14AAP-1B
*5. Airspeed .
450 KIAS (altitude permitting)
When start complete:
6. BACKUP IGNITION switch .
OFF
7. ENG MODE SELECT switch .
PRI
When PRI mode is restored:
8. Maintain constant subsonic airspeed in level
flight.
9. Affected L or R AICS (LF2 left,
LG2 right) cb .
Cycle
If WING SWEEP advisory light is illumi-
nated, cycling L AICS cb (LF2) may
cause unintentional wing sweep
unless WING SWEEP DRIVE NO. 1
(LE1) and WG SWP DR NO. 2/MANUV
FLAP (LE2) cb’s are pulled.
CONTINUED
Change 3
51
NAVAIR 01-F14AAP-1B
DATE: NOVEMBER 1988
F110-GE-400 ENGINE
DATA BASIS: FLIGHT TEST
NOTES
D WINDMILL RESTARTS SHOULD BE PERFORMED IN SEC-
ONDARY MODE. SECONDARY MODE PROVIDES HIGHER
WINDMILLING RPM AND FASTER ENGINE ACCELERATION.
D THE OPTIMUM RESTART RPM IS 15% OR GREATER.
RESTARTS FROM 10% RPM ARE SUCCESSFUL BUT AC-
CELERATE VERY SLOWLY AND ENGINE LIGHT OFF IS
HARDER TO DETECT.
D IF THE WINDMILL RESTART IS DELAYED MORE THAN 2
MINUTES FROM SHUTDOWN THE LEFT ENGINE WILL
REQUIRE UP TO 500 KIAS IN ORDER TO MAINTAIN A
MINIMUM 10% RPM. THE RIGHT ENGINE WILL MAINTAIN
15% RPM AT 450 KIAS.
AIRSTART ENVELOPE
52
NAVAIR 01-F14AAP-1B
CROSSBLEED AIRSTART
1. Throttle (bad engine) .
OFF
2. FUEL SHUT OFF handle .
Check In
3. Throttle (good engine) .
80-Percent
Rpm (minimum)
4. BACKUP IGNITION switch .
ON
5. ENG MODE SELECT .
PRI
6. ENG CRANK switch (bad engine) .
ON
7. Throttle (bad engine) .
IDLE Immediately
Note
The quickest light-offs are achieved
with throttle to IDLE at less than 10 per-
cent. Light-offs can take as long as 45
seconds.
If hung start:
8. Throttle (bad engine) .
OFF, Then IDLE
If still hung:
9. ENG MODE SELECT switch .
SEC
When start complete:
10. BACKUP IGNITION switch .
OFF
11. ENG MODE SELECT switch .
PRI
When PRI mode restored:
12. Maintain constant subsonic airspeed in level
flight.
CONTINUED
Change 3
53