1.T.O.1F-16A-lFLIGHT MANUAL PUBNR USAF/EPAF SERIES AIRCRAFT036802F-16A/B BLOCKS 10 AND 15/J.q:'~:-,j "~.,,"(,._,., '.(/,.., .'., ,.~ ", ,.,f'" -.,r ..---" ~LOCKHEED MARTIN CORPORATION;14 "'..... ----..'--.....'),~"--. L ..... . F33657-75-C-0310 F42620-01-D-0058COMPL. TIM CHG:.'.. ,'"-,',"~.,i,-",._-. ",l.---------------------------------~IF-16A-l-0001XCommanders are responsible for bringing this publication to the attention of all Air Force personnel cleared for operation of subject aircraft.Published under authority of the Secretary of the Air Force.14 AUGUST 1995 CHANGE 1415 AUGUST 2003

2. 10. 1 F- 16A- 1DISTRIBUTION STATEMENTDistribution is authorized to Department of Defense (DOD) components only (Direct Military Support). Other requests for this document shall be referred to OO-ALCIYPVT, 6080 Gum Ln., Hill AFB, UT 84056-5825. EXPORT CONTROL NOTICE WARNING: This document contains technical data whose export is restricted by the Arms Export Control Act (Title 22, U.S.C. Sec. 2751 et seq) or the Export Administration Act of 1979 as amended (Title 50, U.S.C. app. 2401 et seq). Violations of these export laws are subject to severe criminal penalties. Disseminate in accordance with provisions of AFI 61-204. HANDLING AND DESTRUCTION NOTICEFor unclassified, limited documents, destroy by any method that will prevent disclosure of contents or reconstruction of the document. SUPPLEMENTAL NOTICEThis manual is incomplete without T.O. 1F-16A-1-1, T.O. 1F-16A-1-3 (Block 10), or T.O. 1F-16A-1-4 (Block 15 and l@]). For RNLAF, when operating with the Orpheus Reconnaissance System, this manual is incomplete without T.O. NE1F-16A-1.SUPERSEDURE NOTICESee Technical Order Index, T.O. 0-1-CD-1, CAT-1-4, for current status of Flight Manuals, Safety Supplements, Operational Supplements, and Flight Crew Checklists. This manual supersedes T.O. 1F-16A-1SS-421.T-2Change 14 3. T. O. 1F- 16A- 1 Reproduction for nonmilitary use of the information or illustrations contained in this publication is not permitted. The policy for military use reproduction is established for the Army in AR380-5, for the Navy and Marine Corps in OPNAVINST 5510.1B, and for the Air Force in Air Force Instruction 31-401.INSERT LATEST CHANGED PAGES. DESTROY SUPERSEDED PAGES.LIST OF EFFECTIVE PAGES NOTE:Changes to the current issue are indicated by a vertical line in the outer margins of the page.Dates of issue for original and changed pages are:Original .. Change ... Change ... Change ... Change ... o '" 14 Aug . 1 ... 25 Mar . 2 .... 10 Feb . 3 .... 15 Sep 4 .... 2 MarChange Change Change Change Change95 96 97 97 98... . ... . ... . ... . .. ,.Change Change Change Change Change5 , .... 4 Jan 99 6 '" 15 May 99 7 , .. 15 Mar 00 8 ' ... 15 Dec 00 9 ... Not Issued... 10 ... Not Issued .... 11 .... 15 Jul 02 .. , 12... 15 Nov 02 . .. 13 .... 15 Apr 03 ... 14... 15 Aug 03TOTAL NUMBER OF PAGES IN THIS PUBLICATION IS 584, CONSISTING OF THE FOLLOWING: Page No.* Change No.Title T-2 ............... ' A ............... .. B C .................... .D .................... . a .................... . b Blank .............. .i ..................... . ii ..... , ........ , ...... , III . . . . . , . . . . . . . . . . . . . . .iv ..... , .............. . vi ..... , ........ , ..... . vii .... , ........ , ..... . viii .... , .............. . ix ... ,., ........ , x ................... .. Xl . . . . . . . . . . . . . . , . . . . . ,.... , ........ , ..... .... , .............. ................... ................... ................... ...................o 13 13 13 12ov ............. ' "xii xiii xiv xv xvi 1-114 14 14 14 14 14 14. , . . , .1-2 ................... . 1-3 .. , ................ . 1-4 ................. , . 1-4.1 ................. . 1-4.2 Blank .......... , 1-5 .................. . 1-6 ..... " ......... " .' 1-6.1 ................ . 1-6.2 Blank ........... . 1-7 ................... , 1-8 ................... , 1-9 ..12 ]212 12 13 8 8 88* ChangePage No. 1-10 1-11 1-12 1-13 1-14 1-15 1-16 1-17 1-18 1-19 1-20 1-21No.o o o o o o o o1-22 .................. .11-23 1-24 1-25 1-26 1-27 1-28 1-29 1-30 1-311............... , .... . ........... 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DESTROY SUPERSEDED PAGES.LIST OF EFFECTIVE PAGES (Cont) Page No.*Change No.1-72 . . 0 1-73 . .. . . . . . .. . . . .. .. . . 0 1-74. . . . . . . . . . . . . . . . . . . 12 1-75................... 2 1-76. . . . . . . . . . . . . . . . . . . 0 1-77 .. .. . . . . . . . . . . . . . .. .. 12 1-78................... 13 12 1-78.1 ............. . . . . 1-78.2 Blank . . . . . . . . . . . 1 1-79 ................... , 11 1-80 ................... , 0 1-81 ................... , 0 1-82. . . . . . . . . . . . . . . . . . . 0 1-83 ....... , ........ , . . 3 0 1-84 ................ '" 1-85 ................ , .. ,. 13 1-86 ....... , ........ , . . 0 1-87 , ............... , . . 2 1-88 ................ , . . 2 1-89 , . . . . . . . . . . . . . . . . . . 2 1~90 . . . . . . . . . . . . 0 1-91 '" .......... ,. . ... 0 1-92 , .................. , 0 1-93,.... .... .......... 2 1-94 Blank ............ , 2 1-95 .................. , 3 1-96 .................. , 3 ] -97 ................... 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" 13 1-144 ........... , ...... , . 0 1-145 ........... , . . . . . . 0 1-146. . . . . . . . . . . . . . . . . . 0 1-147 .... , ............ . o 1-148 ............ , .... . o 12 1-149 ............ , .. , .. 1-150 .... , ............ . o 1-151 ............. , ... . 12Change 14*Change No.1-172... 1-173., ................. 1-174., ................. 1-175 ... , .. .. ........... 1-176 ............ , . . . . . . 1-177 ... , . . .. .. .. . .... .. 1-178 ............ , ..... 1-179.................. 1-180 ... , .............. 1-181 ............ , ....... 1-182. . . . . . . . . . . . . . . . . . 1-183 ................. , . 1-184 ................ '" 1-184.1 . . . . . . . . . . . . . . . . .. 1-184.2 ............ , . . . 1-185 ............. , 1-186 .............. , ... 1-187 .............. , ... 1-188 ..... , ............ , 1-189 .............. , ... '. 1-190 .................. ,. 1-191. . . . . . . . . . . . . . . . . . . . 1-192. . . . . . . . . . . . . . .. . . .. 1-193 ................ , . 1-194. . . . . . . . . . . . . . . . . . 1-195. . . . . . . . . . . . . . . . . . 1-196 ....... , . . . . . . . . . . 1-197 . . . . . . . . . . . . . . . . . . 1-198 ................. . 1-199 ................. . 1-200 ................. . 1-201, ........ , ... , ... . 1-202 ......... , ....... .0 0 0 0 2 0 0 0 12 0 12 12 012 12 12 0 0 0 0 12 0 13 12 13 12 12 13 4o o oo1-152 ...... , .......... .31-202.1 ....... , ....... .121-152.1 ........ , ...... . 1-152.2 Blank ......... . 1-153 ...... , .......... . 1-154 ...... , .......... , 1-155 ...... , . , ...... . 1-156 ...... , ........ , . 1-157 ................. , 1-158 ............... , . , 1-159 ................. . 1-160 ............... , .. 1-161 ................. . 1-162 ........ , ....... . 1-163 ........ . 1-164 ........ , ... , ... . 1-165 ................. , 1-166. , ............... , 1-167. , .............. . 1-168 .......... , ..... . 1-169 .......... , ..... . 1-170 ....... , .. , ...... , 1-171 ..13 21-202.2 ....... 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DESTROY SUPERSEDED PAGES.LIST OF EFFECTIVE PAGES (Cont) Page No.*Change No.2-1 . . 11 2-2 . . . . . . . . . . . . . . . . . . . . 11 2-2.1 . . . . . . . . . . . . . . . . . . 5 2-2.2 Blank ...... . . . . . . 5 2-3 . . . . . . . . . . . . . . . . . . . . 13 2-4 . . . . . . . . . . . . . . . . . . . . 12 2-5 . . . . . . . . . . . . . . . . . . . . 12 2-6 . . . . . . . . . . . . . . 12 2-7 .................... 11 2-8 . . . . . . . . . . . . . . . . . . . . 13 11 2-9 . . . . . . . . . . . . . . . . . . . . 2-10 . . . . . . . . . . . . . . . . . . . 14 14 2-11 . . . . . . . . . . . . . . . . . . . 0 2-12 . . . . . . . . . . . . . . . . . . . 2-13 .................. . 2-14 . . . . . . . . . . . . . . . . . . . 4 0 2-15 . . . . . . . . . . . . . . . . . . . 2-16 . . . . . . . . . . . . . . . . . . . 12 2-17 .................. . 2-18 . . . . . . . . . . . . . . . . . . . 12 8 2-18.1 ............. 2-18.2 Blank. . . . . . . . . . 8 2 2-19 . . . . . . . . . . . . . . . . . . . 2-20 . . . . . . . . . . . . . . . . . . . 5 11 2-20.1 .................. 2-20.2 Blank. . . . . . . . . . . 11 2-21 ................... 11 2-22 . . . . . . . . . . . . . . . . . . . 13 2-23 . . . . . . . . . . . . . . . . . . . 13 2-24.. ... .... .. .. ...... 2 2-25 . . . . . . . . . . . . . . . . . . . .. 12 2-26.. .. . .. .. .. .. 11 2-27 . . . . . . . . . . . . . . . . . . . 12 2-28 . . . . . . . . . . . . 13 2-28.1 ................ 13 2-28.2 Blank. . . . . . . . . . . 7 11 2-29 . . . . . . . . . . . . . . . . . . 2-30 ................. . 11 2-31 .................. . o 2-32 .................. . 2 o 2-33 .................. . 2-34 .................. . o 2-35 .............. 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" ...... . 3-45 ......... , ........ .3-46 ................. . 3-47 ................. . 3-48 .. .*Change No. 12 3 12o 2o o 12 3 3o 12 5 5o 23o 12 13o o 8o 12 14 13 8 6 7 7 5o 3 8 77 66 14 13 13 11 1 13 13 13 13 18o o 11 115Page No.*Change No.3-49 .. . 3-50 .................... , 3-50.1 ................. 3-50.2 Blank. . . . . . . . . . . 3-51 . . . . . . . . . . . . . . . . . . . 3-52 . . . . . . . . . . . . . . . . . . . . 3-53 ...... , . .... ....... 3-54.................... 3-55 . . . . . . . . . . . . . . . . . . . 3-56. . . . . . . . . . . . . . . . . . . 3-56.1 .,. . . . . . . . . . . . . . . 3-56.2 Blank . . . . . . . . . . . 3-57 . . . . . . . . . . . . . . . . . . . 3-58. . . . . . . . . . . . . . . . . . . 3-59. . . . . . . . . . . . . . . . . . . 3-60. . . . . . . . . . . . . . . . . . . 3-61 . . . . . . . . . . . . . . . . . 3-62. . . . . . . . . . . . . . . . . . . 3-63. . . . . . . . . . . . . . . 3-64 ...... 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' ...... . 3-96 .. 3-97 ..13 8 7 0 012 3 0 7 7 7 7 8 11 11 3 6 13 7 8 8 1 4 8 4 1 11 11 1 413 13 4o 8 2 11 12 14 13 14 14 14 7 88 5 4 8 4* Zero in this column indicates an original page.Change 14C 6. 10. 1F- 16A- 1 INSERT LATEST CHANGED PAGES. DESTROY SUPERSEDED PAGES.LIST OF EFFECTIVE PAGES (Cont) Page No. 3-98 .. 3-99 .............. , ... . 3-100 ................ . 3-101 ................. . 3-102 ................ . 3-]03 ................. . 3-104 ........... . 3-104.1 ......... . 3-104.2 Blank ... . 3-105 ........... . 3-106 ................. . :1-107 ............. . :3-108 ......... . 3-109 ........ . 3-110 ........... . 3-111 ............. . 3-112 ............. . 3-113 ... , ......... . 3-114 ........... . 3-115 ............. . 3 0 116 ........... . 3-117 .......... . 3-118 ........... . ~3-119 .......... . :3-120 ... , ............ . 3-121 ................. . 3-122 ................. . 3-123 ................. . 3-124 ................. . 3-125 ................. . 3-126 ............... . 3-127 ............ . 3-128 .. . :3-129 ... .3-130. 3-131 ... ;:3-132 ... . 3-132.1 ............ . 3-132.2 Blank ...... . 3-13:3.. . .......... . 3-134 .............. , 3-135 ................ . 3-136 ......... , . 3-137 ......... , ....... . 3-138 ................. . 3-139 ................ . 3-140 ......... , ...... . 3-140.1 ....... , ...... . 3-140.2 .............. . 3-141 .... . 3-142 ... . 3-143 .. . 3-144 .. . 3-145 .. . 3-146 .. .*Change No. 111 88 13 8 13o 5o o oo5 11 11:3 12 7Page No.4-1 4-2 Blank ............. . 5-1 ................... . 5-2 ................... . 5-3 . . . .......... . 5-4..... . ....... . 5-4.1 ................. . 5-4.2 Blank ........... . 5-5 ................... . 5-6 ................... . 5-7 ........... . 5-8 .................. . 5-9 ................... . 5-10 ................... . 5-11 .................. . 5-12 .......... , ...... . 5-12.1 ................ . 5-12.2 ........ , ....... . 5-13 ............... '" . 5-14 .................. . 6-1 ................... . 6-2 ., ................ .2 26-3 ., 6-4 .. 6-5 ., ................ .o6-6 .................. .26-7 ........... . 6-8 ... . 6-9 ... . 6-10 .. . 6-11 ........... . 6-12 ................. . 6-13 ................. . 6-]4 .. . 6-15 ................ . 6-16 Blank ......... . 7-1 ................. . 7-2 .. 7-3 .. 7-4 .' 7-5 ., ... 7-6 .. 7-7 ..1113 12o 11 11 11 11 11 4 4 4 43 4 7 88 11 1111 11 67 8*Change No.7-8 ................. .8-1 8-2 8-3 8-4 8-5 8-6.................. . .................. . .. .' .. . ............ . ............. .8-7 ............. . 8-8 .. .8-9 .. 8-10 .... 8-11 ..o o 3 8 1111 8 2o o 13 81o o 811 8 13 3 8o o o 3o 44 4 4 4 4 8 8 88 12 131o 8 8 813 13 13 1:3 1:3 13 13 13 13 1:3 13* Zero in this column indicates an original page.oChange 14Page No.*Change No.13 13 13 13 13 13 13 13 8-20.. . .... .. ....... .. . 13 8-21 . . . . . . . . . . . . . . . . . . . 13 8-22 ..................... 13 8-23.. . .... .. ....... . . . 13 8-24 . . . . . . . . . . . . . . . . . . . 13 8-25 ................. , . 13 8-26 . . . . . . . . . . . . . . . . . . . 13 8-27 . . . . . . . . . . . . . . . . . . . 13 8-28 ............ , . .... . 13 8-29 ...... , .. .... . .... . 13 8-30 ...... , .......... , . 13 8-31 . . . . . . . . . . . . . . . . . . . 13 13 8-32 ...... , ..... , .. . .... 8-33 .................. '" 13 8-34 ............ , ... .. . 13 8-35 ...... , .. " ., ..... . 13 8-36. . . . . . . . . . . . . . . . . . . 13 8-37 . . .. . . . . . . . . . . . . . . . 13 8-38 Blank. . . . . . . . . . . . . 13 Glossary_1 ............ 13 Glossary_2 ............ 13 Glossary_3 ........... 13 Glossary_4 ........... 13 Glossary_5 ............ 13 Glossary _6 Blank .. 08-12 8-13 8-14 8-15 8-16 8-17 8-18 8-19..... . ................... ....... .. ....... ... ................... ........... ..... .. .. ................... .. ....... .......... ................... 7. TO. 1F- 16A-l FLIGHT MANUAL, SAFETY SUPPLEMENT, AND OPERATIONAL SUPPLEMENT STATUSThis supplement status page is based on information available as of 15 August 2003. It is not an official status page. Flight ManualBasic DateChange No. and DateT.O. IF-16A-l14 Aug 199514Supplemental Flight ManualsBasic DateChange No. and DateT.O. IF-16A-l-128 Nov 19941015 Feb 2003T.O.IF-16A-I-315 Nov 1999615 Jun 2003T.O. IF-16A-I-415 Nov 1999615 Jun 2003Flight Crew ChecklistBasic DateChange No. and DateT.O.IF-16A-ICL-l7 Mar 19941415 Aug 200315 Aug 2003INCORPORATED SAFETY AND OPERATIONAL SUPPLEMENTST.O. NumberDateIF-16A-lSS-42103 Jul 03Flight Manual Sections AffectedShort Title Nozzle Failure LogicII, IIIOUTSTANDING SAFETY AND OPERATIONAL SUPPLEMENTST.O. NumberDateShort TitleFlight Manual Sections AffectedNoneuI.' .,/.:~Change 14a/(b blank) 8. T.O. 1F-16A- 1TABLE OF CONTENTS SECTION IDescription and Operation1-1SECTION IINormal Procedures2-1SECTION IIIEmergency Procedures3-1SECTION IVCrew Duties4-1SECTION VOperating Limitations5-1SECTION VOperating Limitations (Stores) - Block 10T.O. IF-16A-I-3Operating Limitations (Stores) - Block 15T.O. IF-16A-I-4SECTIONVand~SECTION VIFlight Characteristics6-1SECTION VIIAdverse Weather Operation7-1SECTION VIIIAir Refueling Procedures8-1GLOSSARYStandard and Nonstandard AbbreviationsAPPENDIX APerformance Data - FI00-PW-200T.O.IF-16A-l-lAPPENDIXB(Not Applicable)T.O. IF-16A-l-lAPPENDIXCPerformance Data - FI00-PW-220 or FI00-PW-220ET.O. IF-16A-l-lGlossary 1Change 13 9. T.O. 1F-16A-lBEFOREYOU TAKE OFF, READ THIS!1 F-16X-1--0002X@SCOPEThis manual contains the necessary information for safe and efficient operation of the aircraft. These instructions provide a general knowledge of the aircraft and its characteristics and specific normal and emergency operating procedures. Pilot experience is recognized; therefore, basic flight principles are avoided. Instructions in this manual are prepared to be understandable to the least experienced pilot who can be expected to operate the aircraft. This manual provides the best possible operating instructions under most conditions. Multiple emergencies, adverse weather, terrain, etc., may require modification of the procedures. This manual must be used with one or more of the following manuals to obtain information necessary for safe and efficient operation: T.O. IF-16A-l-lSupplemental Flight Manual, F-16AIB AircraftT.O. IF-16A-5-2 T.O. IF-16A-6CF-lT.O. IF-16A-25-1T.O. IF-16A-25-10T.O. IF-16A-34-1-1T.O.I-IM-44-1FDT.O. IF-16A-34-1-3T.O. IF-16A-1-3Supplemental Flight Manual, F-16AIB Aircraft (Block 10)T.O. IF-16A-34-1-4T.O. IF-16A-1-4Supplemental Flight Manual, F-16AIB Aircraft (Block 15 andT.O.IF-16A-39~) IIChange 13T.O. l-lC-lLoading Data Acceptance and FUllctional Check Flight Procedures Manual, F-16AIB Aircraft Nuclear Weapons Delivery Manual (SECRET) (Title Unclassified) Aircrew Practice Bomb Delivery Procedures Avionics and Nonnuclear Weapons Delivery Flight Manual Combat Weapons Delivery Software (CWDS) Avionics and Nonnuclear Weapons Delivery Flight Manual ~ Avionics and Nonnuclear Weapons Delivery Flight Manual M Aircraft Battle Damage Repair Basic Flight Crew Air Refueling ProceduresI 10. T. O. 1F- 16A- 1 PERMISSIBLE OPERATIONSThe flight manual takes a positive approach and normally states only what can be done. Unusual operations or configurations are prohibited unless specifically covered herein. Clearance must be obtained before any questionable operation which is not specifically permitted in this manual is attempted. HOW TO BE ASSURED OF HAVING LATEST DATAIRefer to T.O. 0-I-CD-l, CAT-I-4 for a listing of all current flight manuals, safety supplements, operational supplements, and checklists. Also, check the flight manual title page, the title block of each safety and operational supplement, and all status pages contained in the flight manual or attacood to formal safety and operational supplements. Clear all discrepancies before flight.instructions in the supplement. Vhen lengthy additions are required, the formal supplement provides one-sided insert page(s) to the flight manual and checklist. This supplement page(s) is attached to the original page(s). The original page(s) remains in the manual or checklist in case the supplement is rescinded and the page(s) is needed. Added page(s) (e.g., 3-48.1) are inserted in proper numerical sequence and may be printed on both sides. SAFETY SUPPLEMENTSInformation involving safety is promptly forwarded in a safety supplement. Urgent information is published in interim safety supplements and transmitted by electronic message. Formal supplements are mailed. The supplement title block and status page (published with formal supplements only) should be checked to determine the effect of this supplement on this manual and other outstanding supplements.ARRANGEMENTIOPERATIONAL SUPPLEMENTSThe manual is divided into eight sections and three supplemental appendices. ILLUSTRATIONSCockpit arrangement, cockpit console, and cockpit instrument panel illustrations display the delivered configuration plus the approved equipment modifications. For details of equipment modification, see the individual equipment illustration.Information involving changes to operating procedures is forwarded by operational supplements. The procedure for handling operational supplements is the same as for safety supplements. CHECKLISTThe checklist contains itemized procedures without all of the amplification. Primary line items in the flight manual and checklist are identical.SUPPLEMENT INFORMATION AND GUIDELINES HOW TO GET PERSONAL COPIESSupplements are safety or operational and are indicated -ISS or -IS, respectively. Supplements are issued as interim electronic messages or formal printed copies. All interim supplements are assigned odd numbers, such as -ISS-195. When an interim supplement is formalized, it will be assigned the next following even number, such as -ISS-196. Formal supplements not preceded by an interim supplement are also assigned even numbers. If an interim supplement is not to be formalized, a statement cancelling the next assigned even supplement number is included in the REMARKS section of the interim supplement. If a formal supplement is not preceded by an interim supplement, a statement cancelling the previous odd supplement number is included on the status page of the formal supplement. Occasionally, a supplement has dual references in the instructions; this is because the supplement applies to the present and subsequent manual. Minor text/illustration changes or deletions are given asEach pilot is entitled to a personal copy of the flight manual, safety supplements, operational supplements, and a checklist. The required quantities should be ordered before needed to assure their timely receipt. Check with the publication distribution officer whose job is to fulfill T.O. requests. Basically, the required quantities must be ordered from the appropriate T.O. Index. T.O. 00-5-1 and T.O. 00-5-2 give detailed information for properly ordering these publications. Insure a system is established at each base to deliver the publications to the pilots immediately upon receipt. FLIGHT MANUAL BINDERSLooseleaf binders and sectionalized tabs are available for use with the manual. They are obtained through local purchase procedures and are listed in the Federal Supply Schedule (FSC Group 75, OfficeChange 13iii 11. T.O. 1F-16A-1Supplies, Part n. Check with supply personnel for assistance in procuring these items. CHANGE SYMBOLIThe change symbol, as illustrated by the black line in the margin of this paragraph, indicates changes made to the current issue. WARNINGS, CAUTIONS, AND NOTESThe following definitions apply to Warnings, Cautions, and Notes found throughout the manual.I WARNING I Operating procedures, techniques, etc., which could result in personal injury or loss of life if not carefully followed.PILOT'S RESPONSIBILITY - TO LET US KNOWEvery effort is made to keep the flight manual current. Review conferences with operating personnel and a constant review of safety investigation and flight test reports assure inclusion of the latest data in the manual. Comments, corrections, and questions regarding this manual or any phase of the flight manual program are welcomed. These should be forwarded on AF Form 847 in accordance with AFI 11-215 through command headquarters to OO-ALCI YPVT, 6080 Gum Lane, Hill AFB, UT 84056-5825. PUBLICATION DATEThe date appearing on the title page represents the currency of material contained herein. AIRCRAFT AND COCKPIT DESIGNATION CODESSystem and/or component effectivity for a particular aircraft version/cockpit is denoted by a letter code enclosed in a box located in the text or on an illustration. The symbols and designations are as follows: No code - F-16A and F-16B aircraftOperating procedures, techniques, etc., which could result in damage to equipment ifnot carefully followed.~F -16A aircraft[IDF-16B aircraftNOTErnflF -16B aircraft, forward cockpit~F -16B aircraft, rear cockpit~Air Defense~BelgiumUSE OF WORDS SHALL, WILL, SHOULD, AND MAY~DenmarkThe word shall or will is used to indicate a mandatory requirement. The word should is used to indicate a nonmandatory desired or preferred method of accomplishment. The word may is used to indicate an acceptable or suggested means of accomplishment.~Netherlands~Norway[g]USAF~USAFIUSNAn operating procedure, technique, etc., which is considered essential to emphasize.USE OF WORDS AS DESIRED AND AS REQUIRED ENGINE DESIGNATION CODESAs desired allows pilot preference in switch/control positioning. As required indicates those actions which vary based on mission requirements. AIRSPEED REFERENCESAll references to airspeed quoted in knots refer to indicated airspeed. ivChange 12System and/or component effectivity for a particular engine version is denoted by an engine code enclosed in a box located in the text or on an illustration. The symbols and designations are as follows: No code - Any engineI PW200 IFIOO-PW-200I PW2201FIOO-PW-220 or F100-PW-220E 12. IO.lF-16A-l HAVE QUICK RADIO DESIGNATION CODESSystem and/or component effectivity for a particular HAVE QUICK radio version is denoted by a HAVE QUICK radio code enclosed in a box located in the text or on an illustration. The symbols and designations are as follows: No codeHAVE QUICK II or HAVE QUICK II PHASE III HQIIHAVE QUICK III HQ11.2ItHAVE QUICK II PHASE IIBLOCK DESIGNATION CODES/SERIAL NUMBER/ TAIL NUMBER CROSS-REFERENCEBecause of differences in configuration between aircraft and to avoid repetitious use of aircraft serial numbers, a block effectivity system is used. The block effectivities reflect the aircraft block, the aircraft serial number, and the tail number. Attrited aircraft are removed from the listing. This system is used throughout the manual, both in text and illustrations. 13. T. O. 1F- 16A- 1 AIRCRAFT MODIFICATION/RETROFIT INFORMATIONThis list includes the applicable T.O.IECP effectivities. It is not an official status page. Refer to T.O. 0-1-1-4 for the complete listing of TCTO's. Throughout this manual, black TV screen symbols containing white numerals (D) are used to distinguish information related to aircraft which are modified by TV CODE/ T.O.NO. 1F-16-1751SHORT TITLE Integration of Pressure Breathing for G (PBG) (ECP 1677)a specific T.O.IECP. Information pertaining to modified aircraft is identified by an appropriate effectivity symbol. Information which is not identified by an effectivity symbol is considered common to all aircraft. Information pertaining only to unmodified aircraft has the appropriate effectivity symbol preceded by LESS. For example, LESS 0 indicates that the information is only applicable to aircraft not modified by a specific T.O.IECP. EFFECTIVITY RETROFIT PRODUCTION ~ NA~ All~~ AllNA~ NArrrnNA INQ] NAISummary: Retrofit authorized Est start date - In work Installs a new oxygen system which provides pressure breathing for g (PBG).@)1F-16-1791RLG Capability (ECP 1707A)~ NA~ TBD ~ TBD INQ] All ~ All~All~ Complete~ NAINQ] NAI~All~ Complete MAll 1M AllSummary: Retrofit - As required Est start date - In work The INS gimbal INU is interchangeable with the ring laser gyro (RLG) INU. The only cockpit indications that a RLG INU is installed are the shorter alignment times, greater accuracy, and different memory addresses.VIChange 12 14. 10. 1 F- 16A-lTVCODEI T.O. NO. NAEFFECTIVITY PRODUCTION RETROFITSHORT TITLE Early Provisions for Improved Capability (ECP 0350)~F-16A 80-0541 and on; F-16B 80-635 and onNA~ F-16A 80-35471NAFA-56 and on; F-16B 80-35881 FB-13 and on ~F-16A 80-3596 and on; F-16B 80-3612 and onNA[N;J F-16A 78-0258 and on; F-16B 80-3649 and on M F-16A 78-0300 and on; F-16B 80-3689 and on I8Nl AllNA NAISummary: Retrofit NA Multinational Staged Improvement Plan (MSIP) installs improved avionics and provides for CARA, AMRAAM, and LANTIRN. BE1F-16-6007 NE1F-16-6001 N01F-16-6003Incorporate Increased Area Horizontal Tail (ECP 0425) (~mJ M ECP 4003)~ F-16A 80-0541NAand on; F-16B 80-635 and on ~F-16A 80-35471 FA-56 and on; F-16B 80-3588/ FB-13 and on[Q F-16A 80-3596 and on; F-16B 80-3612 and on I8Nl All~ F-16A 78-0116/FA-01thru 80-3546/FA-55; F-16B 78-0162/FB-01 thru 78-0173/FB-12 NAI~ CompleteMCompleteSummary: ~ mJ I!iQl Retrofit authorized Est start date - In work Increased horizontal tail area to reduce rotation speed, increase departure resistance, and make aircraft less susceptible to deep stall in the event of a departure.Change 12VII 15. T. O. 1F- 16A- 1TV CODE/ T.O.NO.1F-16-1977SHORT TITLE Improved Switch Guard for Fuel Master Switch (ECP 2120)EFFECTIVITY PRODUCTION RETROFIT AllNASummary: Retrofit authorized Est start date - In work Rescission date - TBD Modification replaces existing in-line switch guard with a side guard configuration.ff)1F-16-1958Z2 Software Provides F100-PW-220E Engine With PFL Capability (OCP 20007)~ NA~ All~ NA~IQ NAml All[N;] NA[N;] Allrrn[NQ] NACompleteCompleteSummary: Retrofit authorized Est start date - In work Modification adds Pilot Fault List reporting capability to aircraft equipped with F100-PW-220E engine.~[!J] F-16A 78-0001 thru 80-0540; F -16B All~NArn;J All [Q F-16A 78-0174 thru 78-0203; F-16B All[N;] NAModify WOW Switch for Interruption of ChafflFlare Dispense System (ECP 1212)~NAIQ NA1F-16-1404 BE1F-16-6004~ F-16A 78-0212 thru78-0257; F-16B All!NQ] NAI[fill CompleteSummary: ~ All Retrofit authorized Est start date - In Work Rescission date - Jul 01 ~ Rescission date - TBD Incorporate an NLG WOW safety mechanism to prevent inadvertent chaffi'flare dispensing on the ground.VIIIChange 12 16. T.O. 1F-16A- 1 TVCODEI T.O.NO.IF-16-1404EFFECTIVITY PRODUCTION RETROFITSHORT TITLE~NAModify WOW Switch for Interruption of ChaffIFlare Dispense System (ECP 1212)~ F-16A 80-0541 and on;F-16B NA ~NA~NA~NA[Qg] F-16A 80-3596 and on; F-16B NA~NA~ F -16A 78-0258 and on:~NAIrmF-16B NA CompleteISummary: ~ All Retrofit authorized Est start date - In Work Incorporate a right MLG WOW safety mechanism to prevent inadvertent chaff/flare dispensing on the ground. ~~Provide Cockpit Indication of Probe Heater Malfunction (ECP 1193)~1m~NAF-16A 87-0004 and on; F-16B 86-0197 and on AllF-16A 78-0001 thru 83-1117; F -16B 78-0077 thru 83-1173~IF-16-1365Complete~F-16A 78-0174 thru 80-3611; F -16B 78-0204 thru 80-3615 Complete Complete~ ~ISummary: Retrofit authorized Est start date - In Work Modification installs probe heat monitoring system and PROBE HEAT caution light to provide cockpit indication of possible probe heater failure or malfunction.00 2J-F100(l)-594 2J-F1 00(II)-649Redesigned 3rd Stage Fan and New 4th Stage Compressor BladesNAAll F100-PW-200 EnginesSummary: Retrofit - TBD Est start date - TBD Rescission date - TBD Modification reduces potential for 4th stage compressor blade failure. Completion of TCTO's removes the 600 KCAS limitation.Change 12ix 17. T.O. 1F-16A-l TVCODEI T.O.NO. (FI)2J-FIOO-930SHORT TITLE Incorporation of Arctic Trim to PW200 EnginesEFFECTIVITY PRODUCTION RETROFIT NAAll FIOO-PW-200 EnginesSummary: Retrofit authorized Start date - Jun 98 Modification retrims engines to reduce occurrences of AB initiation stalls during takeoff.00 IF-16-2170Modification of the Ejection Mode Selector Valve Console (ECP 2362)NAAll F-16BSummary: ~Retrofit authorized Start date - Feb 99 Modification enlarges the hole in the console to allow the EJECTION MODE SEL handle to seat properly in the NORM position.5El-2-15-510Incorporation of EDU 2.4.0. OFP to PW220 EnginesNAAll FIOO-PW-220 EnginesSummary: Retrofit authorized Start date - Feb 98 Modification installs EDU 2.4.0. OFP software for FIOO-PW-220 engines. Mter incorporation of EDU 2.4.0A OFP (TCTO 5El-2-15-5110), ~ actions are not required.00 IF-16-2077Installation of Improved Antiskid Braking SystemNA~ All ~All(OCP 5003B)Summary: ~Retrofit authorized Start date - Jan 99 Modification incorporates an improved Brake Control/Anti-skid Assembly to replace the current Brake Control and Antiskid Control Boxes.IF-16-2348Summary: xReplacement of Cabin Low Pressure SwitchNA~ ~NA All [g] All INEI All INOI AllRetrofit authorized Start date - Mar 02 Rescission date - TBD Modification replaces the cabin low pressure switch, lowering CABIN PRESS caution light illumination from 27,000 to 22,500 feet.Change 13 18. 10. 1F-16A-lBlock Designation Codes/Serio' Number/Tail Number Cross-Reference BLOCK 10 Serial and Tall Numbers Same for~[A] **78-0001## **78-0002## **78-0003# **78-0005 **78-0007# **78-0008 **78-0010# **78-0011# **78-0013## **78-0015 **78-0017# **78-0019# **78-0020# **78-0021## *78-0022# *78-0024# *78-0025## *78-0026 *78-0027## *78-0038# *78-0039## *78-0040## *78-0042## *78-0043## *78-0044 *78-0047# *78-0049# *78-0050## *78-0051# *78-0052## *78-0053## *78-0054# *78-0056 *78-0057## *78-0058# *78-0059## *78-0060# *78-0061 *78-0062 *78-0063# *78-0064# *78-0065##*78-0066## *78-0068# *78-0069 *78-0070# *78-0073# *78-0074## *78-0076# *79-0290## *79-0294# *79-0296 *79-0300# *79-0303 *79-0306# *79-0307 *79-0308# *79-0309## *79-0310# *79-0311# *79-0312# *79-0314# *79-0317# *79-0322# *79-0324 *79-0326 *79-0327 *79-0329# *79-0330 *79-0331# 79-0332 79-0334 79-0335## 79-0336# 79-0337## 79-0340## 79-0341# 79-0342# 79-0344 79-0345# 79-0346# 79-0348# 79-0349## 79-0351## 79-0352 79-0353# 79-0354# 79-0355# 79-0357 79-0359# 79-036079-0362 79-0363# 79-0364 79-0365# 79-0366## 79-0368 79-0370 79-0371 79-0373## 79-0375 79-0376# 79-0380## 79-0381# 79-0382## 79-0383# 79-0384# 79-0387## 79-0388## 79-0389 79-0393# 79-0394## 79-0395# 79-0396# 79-0399## 79-0401## 79-0402## 79-0403## 79-0404 79-0405# 79-0406## 79-0407## 79-0408 79-0409# 80-0474# 80-0475# 80-0476# 80-0479# 80-0480# 80-0481 80-0482# 80-0483# 80-0485# 80-0487# 80-0488## 80-0489# 80-0492 80-0493# 80-0494# 80-049580-0496# 80-0497# 80-0498# 80-0499 80-0500# 80-0504 80-0505 80-0506# 80-0507# 80-0508# 80-0509# 80-0510# 80-0511 80-0512# 80-0513# 80-0515# 80-0518# 80-0519# 80-0520# 80-0521# 80-0522 80-0523# 80-0524 80-0525# 80-0526 80-0527 80-0528# 80-0529# 80-0530# 80-0531# 80-0533# 80-0535## 80-0537# 80-0538# 80-0539# 80-0540#~OO **78-0077# **78-0079# **78-0080 **78-0081 **78-0082 **78-0083 **78-0084 **78-0085 **78-0087 **78-0088**RETROFITrED FROM BLOCK 1 *RETROFITrED FROM BLOCK 5 #STORAGE**78-0089 **78-0090## **78-0091 **78-0094 **78-0096 **78-0097## **78-0098 *78-0099# *78-0100 *78-0101 *78-0102 *78-0103# *78-0104# *78-0107# *79-0411 *79-0412 *79-0413## *79-0414 *79-0415# *79-0417 *79-0418# 79-0420 79-0421 79-0422 79-0426# 79-0427 79-0428 79-0429 79-0430 79-0431 79-0432 80-0623# 80-0625# 80-0628 80-0629# 80-0630 80-0631 80-0633 80-0634~[AJ Serial Number/ Tall Number**78-0 116/FA-O1# **78-0117/FA-02# **78-0118/FA-03### INACTIVE Change 8xi 19. T. o. 1F- 16A- 1Block Designation Codes/Serial Number/Tail Number Cross-Reference **78-0 119/FA-04# **78-0 120/FA-05# **78-0 124/FA-09# **78-0125/FA-10# **78-0131/FA-16# **78-0 132/FA-17# *78-0 133/FA-18# *78-0 134/FA-19# *78-0 135/FA-20# *78-0 136/FA-21# *78-0 137/FA-22# *78-0 138/FA-23 # *78-0 140IFA-25# 78-0 141/FA-26# 78-0 142/FA-27# 78-0 143IFA-28# 78-0 145/FA-30# 78-0 146IFA-31# 78-0 147/FA-32# 78-0 149/FA-34 78-0151/FA-36# 78-0 152/FA-37# 78-0 153/FA-38# 78-0 155/FA-40# 78-0 158/FA-43 # 78-0 159/FA-44# 78-0 160/FA-45 # 78-0 161/FA-46# 80-3538/FA-47 80-3539/FA-48 80-3540/FA-49# 80-3541/FA-50# 80-35421FA-51# 80-3544/FA-53 80-3546/FA-55~oo Serial Number/ Tall Number**78-0162IFB-01 **78-0 163/FB-02 **78-0 164IFB-03# **78-0 165/FB-04 **78-0166IFB-05 *78-0 168/FB-07 *78-0 169/FB-08 *78-017 01FB-09*78-0 171/FB-10 78-0173/FB-12~oo **78-0 1741E-174 **78-01761E-176 *78-01771E-177 *78-01781E-178 *78-0 1801E-180 *78-0181/E-181 *78-0 1821E-182 *78-0 1831E-183 *78-0 1841E-184 *78-0 1871E-187 *78-0 1881E-188 78-0 1891E-189 78-01901E-190 78-0191/E-191 78-01921E-192 78-0 1931E-193 78-0 1941E-194 78-0 1951E-195 78-0 1961E-196 78-0 1971E-197 78-01981E-198 78-01991E-199 78-02001E-200 78-0202lE-202 78-02031E-203~oo **78-0204IET-204 *78-0206IET-206 *78-0207IET-207 *78-0208IET-208 78-0210IET-210 80-0626IET-626~oo **78-0212/J-212 **78-0213/J-213 **78-0214/J-214 **78-0215/J-215 **78-0218/J-218 **78-0219/J-219 **78-0220/J-220**78-0221/J-221 **78-0222/J-222 **78-0223/J-223 *78-0226/J-226 *78-0228/J -228 *78-0229/J-229 *78-0230/J-230 *78-0231/J-231 *78-0232/J-232 *78-0234/J-234 *78-0235/J-235 *78-0236/J-236 78-0238/J-238 78-0239/J-239 78-0240/J-240 78-0241/J-241 78-0242/J-242 78-0243/J -243 78-0245/J-245 78-0246/J-246 78-0247/J-247 78-0248/J-248 78-0249/J-249 78-0250/J-250 78-0251/J-251 78-0253/J-253 78-0254/J -254 78-0255/J-255 78-0256/J-256 78-0257/J-257~oo **78-0259/J-259 **78-0260/J-260 **78-0261/J-261 **78-0262/J-262 **78-0263/J-263 **78-0264/J-264 *78-0265/J-265 *78-0266/J -266 78-0267/J-267 78-0268/J-268 78-0269/J-269 78-0270/J-270MOO **78-0272/272**78-0273/273 *78-0275/275 *78-02761276 *78-0277/277 *78-0279/279 *78-0281/281 *78-0282/282 *78-0284/284 78-0285/285 78-02861286 78-02881288 78-02891289 78-0291/291 78-0292/292 78-0293/293 78-0295/295 78-0297/297 78-0298/298 78-0299/299MOO ** 78-0302/302 *78-0304/304 78-0305/305 78-0306/306BLOCK 15 Serial and Tall Numbers Same for~OO ***80-0541# ***80-0542# ***80-0543# ***80-0545# ***80-0548# ***80-0549# ***80-0550 80-0551# ***80-0552# ***80-0553# ***80-0554 ***80-0556# 80-0557 ***80-0558 ***80-0559**RETROFITTED FROM BLOCK 1 *RETROFITrED FROM BLOCK 5 #STORAGE ***AIR DEFENSE FIGHTER xiiChange 8***80-0560# ***80-0561# ***80-0562# ***80-0563 ***80-0565 ***80-0567# ***80-0568# ***80-0569# ***80-0570# ***80-0571# ***80-0572# 80-0573## ***80-0575 ***80-0576# ***80-0577# ***80-0578 ***80-0579# ***80-0580# ***80-0581 ***80-0583# 80-0584 ***80-0587# ***80-0588# ***80-0589 ***80-0591# ***80-0593# ***80-0594 ***80-0596 ***80-0598# ***80-0601 ***80-0602 ***80-0603 ***80-0604 ***80-0605 ***80-0607# ***80-0608 80-0609 ***80-0611# ***80-0612 ***80-0613###INACTIVEf 20. T.O. 1F-16A-lBlock Designation Codes/Serial Number/Tail Number Cross-Reference ***80-0614# ***80-0615 ***80-0616 ***80-0619# ***80-0620# ***80-0621# ***80-0622 81-0663 ***81-0665 ***81-0666 81-0667 ***81-0668 ***81-0669# 81-0670 ***81-0673 ***81-0674 ***81-0675 81-0676 81-0677 81-0678 81-0679 ***81-0680 ***81-0681 ***81-0682# 81-0683 ***81-0685 ***81-0686# 81-0687 81-0688# ***81-0690# ***81-0691# ***81-0693 ***81-0694# ***81-0695 ***81-0696# ***81-0698# ***81-0699 ***81-0700# ***81-0701# ***81-0702# ***81-0703 ***81-0705# ***81-0707# ***81-0708# ***81-0709 ***81-0710# ***81-0711# ***81-0712 ***81-0713#***81-0715# ***81-0716# ***81-0718# ***81-0719# ***81-0720# ***81-0721## ***81-0722# ***81-0723 ***81-0725# ***81-0726# ***81-0727# ***81-0728# ***81-0729# ***81-0731 ***81-0732 ***81-0733# ***81-0734# ***81-0735# ***81-0736# ***81-0737# ***81-0738# ***81-0739# ***81-0740# ***81-0741# ***81-0742# ***81-0743# ***81-0744# ***81-0746# ***81-0748# ***81-0749# ***81-0751 ***81-0752# ***81-0753# ***81-0754# ***81-0755 ***81-0756# ***81-0757 ***81-0759 ***81-0760# ***81-0761 ***81-0762# ***81-0763 ***81-0764# ***81-0765# ***81-0767# ***81-0768# ***81-0769# ***81-0771# ***81-0772***81-0773 ***81-0774 ***81-0775 ***81-0776 ***81-0777 ***81-0778 ***81-0780# ***81-0781# ***81-0782 ***81-0783 ***81-0784# ***81-0785 ***81-0786 ***81-0787 81-0788 ***81-0789 81-0790 ***81-0791 81-0792# ***81-0793 81-0794# ***81-0795 81-0796 ***81-0797 ***81-0799 81-0800# ***81-0801 81-0802 ***81-0803 81-0804 ***81-0805 81-0806 ***81-0807 ***81-0809# 81-0810 ***81-0811# 82-0900 ***82-0901 82-0902 ***82-0903 82-0904 ***82-0905 82-0906 ***82-0907 82-0908 ***82-0910 82-0911 ***82-0913 82-0914*** AIR DEFENSE FIGHTER *RETROFITTED FROM BLOCK 5***82-0915# ***82-0916# ***82-0917# 82-0918# ***82-0919 ***82-0921 82-0922 ***82-0923# 82-0924 ***82-0926 82-0928 ***82-0929 ***82-0930 82-0931 ***82-0932 82-0933 ***82-0935 82-0936 82-0938 82-0941 ***82-0942# 82-0944# ***82-0945# 82-0946 ***82-0947# 82-0948# 82-0949 ***82-0950 ***82-0951 82-0952# ***82-0953 ***82-0955 ***82-0956 82-0957 ***82-0958# ***82-0960# ***82-0961 82-0962# ***82-0963# 82-0964 ***82-0966# ***82-0967 82-0968# ***82-0969# 82-0970 ***82-0972 ***82-0973# ***82-0974# 82-0975# #STORAGE82-0976 82-0977# ***82-0978# ***82-0979 82-0980 ***82-0981 82-0982# ***82-0983 ***82-0984 82-0986# ***82-0987 82-0988# ***82-0989 82-0991 ***82-0992 82-0993 ***82-0995 82-0996 ***82-0997 82-0999# ***82-1000 ***82-1001 82-1002# 82-1004# ***82-1005 ***82-1006 82-1007# ***82-1008 82-1009 ***82-1010# ***82-1012 82-1013 ***82-1014 ***82-1016# 82-1017# ***82-1019 82-1020 ***82-1021 82-1022# ***82-1023 82-1025 83-1066# 83-1068###INACTIVE Change 8xiii 21. T.O. 1 F-16A-lBlock Designation Codes/Serial Number/Tail Number Cross-Reference 83-1069# 83-1072# 83-1073# 83-1076# 83-1077# 83-1079 83-1080# 83-1081# 83-1083# 83-1084# 83-1085 83-1087 83-1088# 83-1090# 83-1091 83-1092# 83-1093 83-1094# 83-1095 83-1096# 83-1097 83-1098 83-1099 83-1100 83-1101# 83-1103 83-1104# 83-1105 83-1106 83-1108 83-1109 83-1110 83-1111 83-1112# 83-1113# 83-1114~[ID 80-0635 ***80-0636 ***80-0637 80-0638 ***81-0812 81-0813# 81-0815 81-0816 ***81-0817 ***81-0818***81-0819 ***81-0820 81-0821 81-0822# ***82-1026 ***82-1027 ***82-1031 ***82-1032# ***82-1033 ***82-1034 ***82-1035 ***82-1036 ***82-1039 ***82-1041 82-1043 ***82-1046 82-1047 ***82-1049 83-1166 83-1167# 83-1168# 83-1169 83-1170 83-1171# 83-1172~OOChange 887-0047IFA-10387-0048/FA-104 87-0050/FA-106 87 -005l1FA-107 87-0052/FA-108 87-0053IFA-109Serial Number/ Tall Number80-3547/FA-56 80-3548/FA-57 80-3549/FA-58 80-3551/FA-60 80-3552/FA-61 80-3556IFA-6580-3557/FA-66 80-3558/FA-67 80-3559/FA-68 80-3560IFA-6980-3561/FA-70 80-3562/FA-71 80-35631FA-7280-3564/FA-73 80-3565/FA-74 80-35661FA-7 5 80-3567IFA-76 80-3568IFA-77*** AIR DEFENSE FIGHTER xiv80-3569/FA-78 80-35721FA-81 80-3573/FA-82 80-3574/FA-83 80-3575/FA-84 80-3577/FA-86 80-3578/FA-87 80-3579/FA-88 80-3580/FA-89 80-3581/FA-90 80-35821FA-91 80-3583/FA-92 80-3584/FA-93 80-3585/FA-94 80-3586/FA-95 80-3587/FA-96 86-0073/FA-97 86-0074/FA-98 86-0075/FA-99 86-0076/FA-100 86-0077/FA-101 87-0046/FA-10287-0054/FA-110 87-0055IFA-111 87-0056IFA-11288-0039/FA-114 88-0040/FA-115 88-0041/FA-116 88-0042IFA-11788-0043/FA-118 88-0044/FA-119 88-0045/FA-120 88-0046/FA-121 88-004 71FA-122 89-000 1/FA-123 89-0002/FA-124 89-00031FA-125 89-00041FA-126 89-0005/FA-127 89-00061FA-128 89-00071FA-129 89-00081FA-130 89-00091FA-131 #STORAGE89-0010/FA-132 89-001l1FA-133 90-0025/FA-134 90-0026/FA-135 90-0027/FA-136~[ID 80-3589/FB-14 80-3590/FB-15 80-3592/FB-17 80-3593/FB-18 80-3594/FB-19 80-3595/FB-20 87 -000 lIFB-2188-00 171E-0 17 88-00 181E-0 18~[ID 80-3612IET-612 80-3613IET-613 80-3614IET-614 80-3615IET-615 86-0 1971ET-197 86-0 1981ET-198 86-0 1991ET-199 87 -0022IET-022[fOOOO88-0048IFB-2288-0049/FB-23 89-00 12/FB-24~OO 80-35961E-596 80-35971E-597 80-35981E-598 80-35991E-599 80-36001E-60080-360 lIE-60 1 80-36021E-602 80-36031E-603 80-36041E-604 80-36051E-60580-3606/E-606 80-3607/E-607 80-36081E-60880-3609/E-609 80-3610/E-610 80-361l1E-611 82-10 ll1E-O 11 82-1024/E-024 83-10701E-070 83-107 41E-07 4 83-10751E-075 83-11071E-107 87-00041E-00487 -OO05/E-005 87 -OO061E-006 87 -OO071E-007 87 -00081E-008 88-00 161E-0 1680-3616/J-616 80-3617/J-617 80-3619/J -619 80-3620/J -620 80-3622/J -622 80-3623/J-623 80-3624/J -624 80-3627/J-627 80-3628/J -628 80-3630/J-630 80-3631/J -631 80-3632/J -632 80-3633/J-633 80-3635/J-635 80-3636/J-63680-3637/J-637 80-3638/J -638 80-3640/J -640 80-3641/J-641 80-3642/J-642 80-3643/J -643 80-3644/J-644 80-3646/J -646 80-3647/J-647 80-3648/J -648 81-0864/J -864 81-08661J -866 22. T. O. 1F- 16A- 1Block Designation Codes/Serial Number/Tail Number Cross-Reference 81-0867/J-867 81-0868/J-868 81-0869/J-869 81-0870/J-870 81-08711J-871 81-0872/J-872 81-0873/J-873 81-087 4/J-87 4 81-0875/J-875 81-0876/J-876 81-0877/J-877 81-0878/J-878 81-0879/J-879 81-0881/J-881 83-1192/J-192 83-1193/J-193 83-1194/J-194 83-1196/J-196 83-1197/J-197 83-1198/J-198 83-1199/J -199 83-1201/J-201 83-1202/J-202 83-1203/J-203 83-1204/J-204 83-1205/J-205 83-1206/J-206 83-1207 /J-207 84-1360/J-360 84-1362/J-362 84-1363/J-363 84-1364/J-364 84-1365/J-365 84-1366/J-366 84-1367/J-367 85-0135/J-135 85-0 136/J-136 85-0137/J-137 85-0138/J-138 85-0139/J-139 85-0140/J-140 85-0141/J-141 85-0142/J-142 85-0143/J-143 85-0144/J-144 85-0145/J-145 85-0146/J-146 86-0055/J-055 86-0057/J-05786-0058/J-058 86-0060/J -060 86-0061/J-061 86-0062/J-062 86-0063/J -063 87-0508/J-508 87 -0509/J-509 87-0510/J-510 87-0511/J-511 87-0512/J-512 87-0513/J-513 87-0514/J-514 87-0515/J-515 87-0516/J-516 88-0001/J-001 88-0002/J -002 88-0003/J -003 88-0004/J-004 88-0005/J-005 88-0006/J -006 88-0008/J -008 88-0009/J -009 88-0010/J-010 88-0011/J-011 89-0013/J-013 89-00 14/J-014 89-0015/J-015 89-0016/J-016 89-0017/J-017 89-0018/J-018 89-0019/J-019 89-0020/J-020 89-00211J-021~[ID 80-3649/J -649 80-3650/J-650 80-3651/J-651 80-3652/J-652 80-3653/J-653 80-3654/J-654 80-3655/J-655 80-3656/J-656 80-3657/J-657 81-0882/J-882 81-0884/J-884 81-0885/J-885 83-1208/J-20883-1209/J-209 83-1210/J-210 83-1211/J-211 84-1368/J-368 84-1369/J-369 86-0064/J-064 86-0065/J -065 87 -0066/J -066 87-0067/J-067 87 -0068/J -068MOO 80-3658/658 80-3659/659 80-3660/660 80-36611661 80-3662/662 80-3663/663 80-3664/664 80-3665/665 80-3666/666 80-3667/667 80-3668/668 80-3669/669 80-3670/670 80-36711671 80-3672/672 80-3673/673 80-3674/674 80-3675/675 80-3677/677 80-3678/678 80-3680/680 80-36811681 80-3682/682 80-3683/683 80-3686/686 80-3687/687 80-3688/68887 -07121712~OO 90-0942/900942 90-0943/900943 90-0944/900944 90-0945/900945 90-0946/900946 90-0947/900947 92-0404/920404 92-0405/405 92-0406/406 92-0407/407 92-0408/920408 92-0409/920409 92-0410/920410~[ID 90-0948/948 90-0949/949 90-0950/950 90-0951/951 90-0952/952 92-0452/452 92-0453/453 92-0454/454 92-0455/455 92-0456/456 92-0457/457 92-0458/920458 92-0459/920459 92-0460/920460 92-04611920461MrnJ 80-3689/689 80-3690/690 80-3691/691 80-3692/692 80-3693/693 87-07111711Change 12xv 23. 10. 1 F- 16A- 1F-1 Ei Fighting Falcon AB1 F-16A-1-0003X @xvi 24. 10. 1F- 16A- 1SECTION I DESCRIPTION AND OPERATION TABLE OF CONTENTSPageThe Aircraft . . . . . . . . . . . . . . . . . . . . . Aircraft General Arrangement Aircraft General Data ........... Aircraft Gross Weight (NC GW) . Cockpit Arrangement. . Engine IPW200 I .. . . . . . . . . . . . . . . . . . . . . . Engine General Description IPW200 I Engine Fuel System I PW200 I .......... Unified Fuel Control (UFC) I PW200 I Electronic Engine Control (EEC)1-6 1-6 1-6 1-6 1-6.1 1-42 1-42 1-42 1-42I PW200 I . . . . . . . . . . . . . . . . . . . . . . . . .1-42Backup Fuel Control (BUC) System I PW200 I .. . . . . . . . . . . . . . . . . . . . . . .Main Fuel Pump IPW200 I ..... Afterburner (AB) Fuel PumpIPW200 I ........................ Compressor Inlet Variable Vanes (CIVV's) I PW200 I . . . . . . . . . . . . . . . Rear Compressor Variable Vanes (RCVV's) IPW200 I ............ Compressor Bleed Air I PW200 I .. Pressurization and Dump ValveIPW200 I .................... _ Exhaust Nozzle IPW200 I . . . . . . . . . . . . . . . . Convergent Exhaust Nozzle Control (CENC) I PW200 I ................ Engine Oil System IPW200 I . . . . . . Engine Anti-Ice System I PW200 I ..... Engine ANTI ICE Switch I PW200 I .... Engine and Accessory Drive GearboxesIPW200 I ........................... Engine Alternator I PW200 I ...... Engine Ignition System IPW200 I Jet Fuel Starter (JFS) I PW200 I . . ENG & JET START Control Panel I PW200 I ............ JFS Switch [8] mEl IPW200 I ..... JFS RUN Light [8] mEl IPW200 I JFS Operation I PW200 I ....... Engine Controls and IndicatorsIPW200 I ........................ EEC BUC Switch [8] mEl I PW200 I EEC Caution Light IPW200 I . . . . . BUC Caution Light IPW200 I . .STARTING FUEL Switch [8]mElI PW200 I ................... _MAX POWER Switch I PW200 I . . . RPM Indicator I PW200 I ............. NOZ POS Indicator I PW200 I . . . . . . . . . FTIT Indicator I PW200 I ............. FUEL FLOW Indicator I PW200 I OIL Pressure Indicator IPW200 I .. HYD/OIL PRESS Warning Light I PW200 I . . . . . . . . . . . . . . . . . . . . . . .ENGINE Warning Light I PW200 I . . REDUCED IDLE THRUST (RIT) Switch IPW200 I ................ Throttle I PW200 I ............... Engine Operating Characteristics1-44 1-44IPW200 I ....................... Ground Operation I PW200 I . . . .1-44AB Operation in Flight IPW200 I BUC Operation I PW200 I ............. Engine I PW2201 ... . . . . . . . . . . . . . . . . . . . . . . . Engine General Description I PW2201 .... Engine Fuel System I PW220 I .......... Engine Control System I PW220 I . . . . . . . . Main Fuel Control (MFC) I PW2201 ... Afterburner (AB) Fuel Control1-44 1-44 1-44 1-44 1-45 1-45 1-45 1-45 1-45 1-45 1-45 1-45 1-46 1-46 1-46 1-47 1-47 1-47 1-47 1-50 1-501-50 1-50 1-50 1-50 1-50 1-50 1-50 1-50 1-51 1-51 1-51 1-51 1-51Non-AB Operation in Flight I PW200 I . . . . . . . . . . . . . . . . . . .1-51 1-53 1-53 1-54 1-54 1-54 1-54 1-54PW2201 . . . . . . . . . . . . . . . . . . . . . . .1-54Digital Electronic Engine Control (DEEC) I PW2201 ............... Secondary Engine Control (SEC)1-56II PW2201 . . . . . . . . . . . . . . . . . . . . . . . . .Main Fuel Pump I PW2201 ........... Afterburner (AB) Fuel Pump IPW2201 . . . . . . . . . . . . . . . . . . . . . .Compressor Inlet Variable Vane (CIVV) Controll PW2201 ....... Rear Compressor Variable Vanes (RCVV's) I PW2201 ............. _ Compressor Bleed Air I PW2201 ... Pressurization and Dump Valve I PW2201 . . . . . . . . . . . . . . . . . . . . .Exhaust Nozzle I PW2201 . . . . . . . . . . . . . . . . Convergent Exhaust Nozzle Control (CENC) I PW2201 ................. Light-Off Detector (LO D) I PW220 I Engine Diagnostic Unit (EDU)I PW2201...................Engine Oil System I PW2201 . . Change 21-56 1-56 1-56 1-56 1-56 1-56 1-57 1-57 1-57 1-57 1-57 1-57 1-1 25. T.O. 1 F-16A-l EnbTine Anti-Ice System I PW220 I Engine ANTI ICE Switch I PW2201 .... Engine and Accessory Drive Gearboxes I PW2201 ......................... . Engine Alternator I PW2201 ..... . Engine Ignition System I PW220 I . Jet Fuel Starter (JFS) I PW2201 .. ENG & JET START Control Panel I PW2201 ........... . JFS Switch [8J mEl I PW2201 .... . JFS RUN Light [8J I PW2201 . JFS Operation I PW2201 ....... . Engine Controls and Indicators I PW2201 ................... . ENG CONT Switch I PW2201 ...... . AB RESET Switch [8J I PW220 I .... . ENGINE FAULT Caution Light~, rIDememI PW2201 .......................... .1-57 1-58 1-58 1-58 1-58 1-59 1-59 1-59 1-59 1-59 1-60 1-60 1-60 1-60ENGINE FAULT Caution Light LESS ~, LESS f1) I PW2201 ... .SEC Caution Light I PW2201 ......... . MAX POWER Switch[8J mEl I PW2201 .. RPM Indicator I PW2201 ............ . NOZ POS Indicator I PW2201 .. FTIT Indicator I PW2201 ........ . FUEL FLOW Indicator I PW220 I . OIL Pressure Indicator I PW2201 .. HYD/OIL PRESS Warning Light I PW2201 ....................... . ENGINE Warning Light I PW2201 .. REDUCED IDLE THRUST (RIT) Switch I PW2201 .............. . Throttle I PW220 I .............. . Engine Operating Characteristics I PW2201 ...................... . Ground Operations I PW2201 .. Non-AB Operation in Flight I PW2201 .................... .AB Operation in Flight I PW2201 . SEC Operation I PW2201 ........ . Fire and Overheat Detection System FIRE & OHEAT DETECT Test Button [A] mEl ............ . Fuel System ........ . Fuel Tank System ..... _ Fuel Transfer System ............. . Fuel Tank Vent and Pressurization System ....................... _ Engine Fuel Supply System ..... . Fuel Quantity Indicating System .... . Reservoir Fuel Level Sensing System . Fuel Low Caution Lights ...... . HUD FUEL Low/Bingo Indication ... . HUD TRAP FUEL Warning LESS ~1-2Change 121-60 1-60 1-60 1-60 1-60 1-60 1-63 1-63 1-63 1-63 1-63 1-63 1-63 1-63 1-63 1-65 1-65 1-67 1-67 1-67 1-67 1-67 1-69 1-69 1-69 1-78 1-78 1-78 1-78.1FUEL HOT Caution Light ...... . Fuel Tank Explosion Suppression System ..................... . Refueling System ... . Ground Refueling ......... . Air Refueling (AR) System .... . NVS AIR DISC MSL STEP Button ................ . Air Refueling (AR) Status Indicator ................. . Environmental Control System (ECS) Electrical Failures . Air-Conditioning .. _ Pressurization .............. . AIR SOURCE Knob [8J mEl " TEMP Knob [8J rntJ ...... . DEFOG Lever [8J mEl ....... . EQUIP HOT Caution Light ..... , . Cockpit Pressure Altimeter [8J mEl . CABIN PRESS Caution Light ... , , Anti-G System .. - - - ...... Electrical System .......... . Main AC Power System ......... . Overcurrent Protection Units Emergency AC Power System . DC Power System [BQ] ........ DC Power System LESS ~ . FLCS Power Supply ....... . External Power Provisions ..... . Electrical System Controls and Indicators ................ , . _ Electrical Power Distribution . Normal Operation .. Hydraulic System ..................... HYD PRESS Indicators and Warning Light ........................... . HYD PRESS Indicators ........... . HYD/OIL PRESS Warning Light ... . Emergency Power Unit (EPU) ....... . EPU Controls and Indicators . , ... . EPU Ground Safety Switch , ....... . EPU Switch .............. - - - - - - - - EPU Run Light .. . HYDRAZN Light . AIR Light ............ . EPU/GEN Test Switch ........ . EPU FUEL Quantity Indicator [8J mEl ................ . Hydrazine Leak Detector .. EPU Fired Indicator ... EPU Operation ........ . Landing Gear (LG) System ... . Main Landing Gear (MLG) .. Nose Landing Gear (NLG) .1-79 1-79 1-79 1-79 1-79 1-80 1-80 1-80 1-80 1-80 1-80 1-80 1-83 1-84 1-84 1-85 1-85 1-85 1-85 1-85 1-85 1-85 1-85 1-86 1-86 1-90 1-90 1-90 1-90 1-101 1-101 1-101 1-101 1-101 1-104 1-104 1-104 1-106 1-106 1-106 1-106 1-106 1-106 1-106 1-106 1-107 1-107 1-107 26. 10. 1 F- 16A- 1Landing Gear Controls and Indicators .. Landing Gear Handle ....... . Landing Gear Handle Down Permission Button ...... . DN LOCK REL Button . ALT GEAR Handle LG Warning Horn ........ _ HORN SILENCER Button .... . T.O.ILAND CONFIG Warning Light ..................... WHEELS Down Lights ..... Landing Gear Weight-on-Wheels (WOW) Switches ............ . Landing Gear Operation ........ . Nosewheel Steering (NWS) System .. NWS Controls and Indicators ........ . NWS NR DISC MSL STEP Button .. NWS Light .............. . NWS FAIL Caution Light ........ . Nosewheel Steering (NWS) System [ID . Wheel Brake System .. Toe Brake System .......... . Spin Down Braking System ... . Brakes Channel Switch lID rnfJ .. Parking Brake ~ ~ ........ . Antiskid System ........... . ANTI-SKID Switch lID mIl .. . ANTI SKID Caution Light .. Speedbrake System .......... . SPD BRK Switch ................ . SPEED BRAKE Position Indicator Drag Chute System m1 ~ ........ . DRAG CHUTE Switch m1 ~ .. Arrestment System. HOOK Switch ....... . HOOK Caution Light . Wing Flap System ................ _ Leading Edge Flaps (LEF's) .......... . LE FLAPS Switch ................ . LE FLAPS Caution Light .. Trailing Edge Flaps (TEF's) (Flaperons) ............ . ALT FLAPS Switch ..... . Flight Control System (FLCS) FLCS Limiters ....... . AOAlG Limiter ... . Roll Rate Limiter ........ . Rudder Authority Limiter Yaw Rate Limiter . FLCS Gains .... Cruise Gains . -//,tvII/I II'.'/../ 1/I11~,f'yw::JII-,"t1- V.../REGION 2 /I0 0 0/ /~I)~I"l"'-~40/,1' >'.'1-1,-~J~~ IA/III ,IVfI/1 /1/I'//L/,'."'"/.~I--1---Y/1.~~~//q..dv~v-+"S')'r-- -c- ~y~ ' ~V1/I'.~L~r--'r'T./~~yt-'.~rll'..!""'k-~"I-~ .~I I"'~~~::::N~ 'fj~/l~ / ;' ~ - -.......)~I?~~A- r--~~II II SL ~ I SL5"'"....... ~.......'"5 PSI DIFFERENTIAL PRESSURE....._10-:' ~.' .-'!"'~ .... ,:;. ~-~~ ~.'"" "" ... ::,: ... ..... :"": "=': .'. ~.'j:;a: ~-~""1" ...... ".- ...... ".". ", "" iOo'"~foI""t-~~-..-:,:;.~......'"'""1/....... ~'"1..'-) 1 c::r:;.J~~...................~....... ~.......'"......5 t-~...... ~u. 0 0 0.......~F"CONSTANT PRESSURE RANGE I II IIII I I I I10152025303540AIRCRAFT ALTITUDE - 1000 FEET455055601F-1eX-1-0001X@Figure 1-25.- DUMP - Cockpit pressure dump valve opens to atmospheric pressure. Cockpit pressure altitude increases if DUMP is selected above approximately 8000 feet MSL. Conditioned air ventilates cockpit and performs all other system functions.I-RAM - Engine bleed air valves close and the cockpit pressure dump valve opens to atmospheric pressure. Cockpit pressure altitude increases if RAM is selected above approximately 8000 feet MSL. All air-conditioning, cooling, and pressurizing functions shut off, including g-suit, m PBG, canopy seal, and fuel tank pressurization. The ram air valve opens to admit ram air to ventilate the cockpit and avionic equipment.TEMP Knob ~mElRefer to figure 1-26. The TEMP knob, located on the ECS panel, only controls cockpit temperature.Functions are: - AUTO - Cockpit temperature is automatically maintained (60-80F) relative to the setting of the knob. - MAN - The temperature control drives the air modulating valve to a set position. Cockpit temperature varies according to throttle setting, OAT, and cockpit heat load. If WARM is selected, the cockpit supply air temperature may exceed the maximum allowable limit of approximately 177F. This causes the warm air valve to cycle on and off. This is a normal occurrence and can be stopped by selecting a cooler setting. - TEMP OFF - Hot air mixing is shut off. Only air at approximately 35F is delivered to cockpit. Under extreme temperature conditions, system performance on the ground can be improved by advancing the throttle 1-3 percent above idle rpm. Ground operation with the radar in OFF improves cockpit cooling and ground operation with the radar in STBY improves cockpit heating.Change 31-83 121. T.O. 1 F-16A-lEnvironmental Control System Control Panel [8J IBF I (Typical)Defog Control Panel [A] IBF I (Typical) L1I 1. DEFOG Lever1. TEMP Knob 2. AIR SOURCE Knob ,'F-'6A-1~025A.Figure 1-26.DEFOG Lever ~ [lEIRefer to figure 1-27. The DEFOG lever, located on the far aft portion of the left console, mechanically controls a flapper valve in the cockpit air supply line. Functions are: MIN - Minimum airflow toward the canopy forward area and air vent in center pedestal; maximum airflow to outlets behind seat. MAX - Most of the cockpit air supply is diverted to the canopy forward area for defogging and to the air vent in the center pedestal. A partial opening of the cen ter pedestal air outlet allows a more balanced defogging of the right and left sides of the canopy. When placed in the full forward defog (MAX) position and with the TEMP knob in AUTO, the lever activates a switch which shifts the cockpit air supply control to full warm. The full warm air supply automatically terminates 3 minutes after activation. The lever may be cycled to restart the full warm, 3-minute period.1-84F-'6A-'~026A.Figure 1-27.Under extremely humid conditions or after initial engine start, fog may form at the cockpit air outlets as the cold air mixes with the moist cockpit atmosphere. This condition can be eliminated by selecting MAN and moving the TEMP knob toward WARM until the fog stops forming. In flight, while operating in AUTO, the most rapid method of eliminating air outlet fogging is by selecting the MAX position with the DEFOG lever. Fog may form on the interior surface of the canopy as a result of moisture in the cockpit air condensing on the cold surface. 1b warm the canopy surface above the dewpoint and permit the cockpit air to retain more moisture during cold weather operation, the DEFOG lever should be placed in a forward position and the TEMP knob positioned to MAN WARM. EQUIP HOT Caution LightThe EQUIP HOT caution light, located on the caution light panel, illuminates when the avionic equipment cooling air temperature/pressure is insufficient. 122. T.O. 1F- 16A-1Degraded equipment performance and/or damage can result from overheating. Therefore, when the EQUIP HOT caution light illuminates, the electronic equipment should be turned off unless it is essential for flight. Illumination of the EQUIP HOT caution light automatically interrupts electrical power to the radar. Turning the radar to OFF in flight does not close the radar cooling air shutoff valve. A short duration or intermittent EQUIP HOT caution light may occur when ground cooling air is disconnected. Cockpit Pressure Altimeter ~mElThe cockpit pressure altimeter, located on the right auxiliary console outboard of the stick, is labeled CABIN PRESS ALT. CABIN PRESS Caution LightIMAIN AC POWER SYSTEMAC power is normally supplied by a 40 kva main generator located on and driven by the ADG. The main generator supplies power to the overcurrent protection panels and LESS ~ ECM power panel and nonessential and essential ac buses. The main generator contains a permanent magnet generator (PMG) which provides one source of start power for the emergency power unit (EPU) if the main generator fails but is still rotating. Overcurrent Protection UnitsThe ~ eight, LESS ~ five overcurrent protection units, located on ~ overcurrent protection panels No.1 and No. 2, LESS~ overcurrent protection panel and ECM power panel, protect certain ac buses; stations 3, 5, and 7; ~ and inlet stations from overcurrent. The ELEC CAUTION RESET button on the ELEC control panel is used to reset a tripped overcurrent protection unit for the nonessential ac bus No. 1 ~ and the nacelle nonessential ac bus. The unit may not remain reset if the fault persists.The CABIN PRESS caution light, located on the caution light panel, illuminates when the cockpit pressure altitude is above W 22,500, LESS 00 27,000 feet.The items with nonresettable overcurrent protection units are the radar ac bus; stations 3, 5, and 7; and left and right inlet stations.ANTI-G SYSTEMEMERGENCY AC POWER SYSTEMThe anti-g system includes the ANTI-G panel/valve, the g-suit, m and PBG equipment. The g-suit connector and TEST button are located on the ANTI-G panel at the aft end of the left console. The ECS delivers cooled bleed air to the g-suit and to the oxygen regulator as a control pressure for PBG. Airflow is proportional to the positive g forces sensed. If an ECS shutdown occurs, g-suit m and PBG protection are not available.mIf the main generator fails, emergency ac power issupplied automatically by a 5 kva EPU generator driven by the EPU. The system supplies power to the essential ac buses. The overcurrent protection units are not functional if the EPU generator is supplying power. The EPU generator has a PMG which supplies de power through an ac to dc converter to the four FLCS branches. Refer to EMERGENCY POWER UNIT, this section, for further discussion of the EPU. DC POWER SYSTEM ~The system can be manually tested by depressing the anti-g TEST button to inflate the g-suit m and to check the PBG function. The system incorporates an automatic pressure relief valve.ELECTRICAL SYSTEM Refer to figure 1-28. The electrical system consists of a main ac power system, an emergency ac power system, a de power system, an FLCS power supply, and provisions for external ac power.DC power is supplied to the essential dc buses by ac to dc converters. With the main generator operating, one of these buses also powers the nonessential dc bus and nacelle dc bus. When the essential dc buses are powered, they power the battery buses; then the aircraft battery is disconnected and charged by a battery charger which receives power from essential dc bus No. 1. With the main generator failed and the EPU generator operating, only the essential de buses and battery buses are powered. If the main and EPU generators both fail, none of the dc buses is powered and the aircraft battery supplies power to the battery buses.Change 131-85 123. T.O. 1 F-16A-1DC POWER SYSTEM LESS [BQIDC power is supplied to the essential dc buses by ac to dc converters. With the main generator operating, one of these buses also powers the nonessential dc bus ~ and nacelle dc bus. When the essential dc buses are powered, they power the battery bus; then the aircraft battery is disconnected and charged by a battery charger which receives power from essential dc bus No. 1. With the main generator failed and the EPU generator operating, only the essential dc buses and battery buses are powered. If the main and EPU generators both fail, none of the dc buses is powered and the aircraft battery supplies power to the battery bus. FLCS POWER SUPPLYThe primary FLCS power supply includes a dedicated FLCS PMG, two dual-channel converter/regulators, and four inverters. Other FLCS power sources are the main generator, the EPU generator, the EPU PMG, the aircraft battery, and the FLCS batteries. The FLCS PMG is the primary power source for the FLCS during normal operations. The FLCS PMG is located on the ADG and shares the hydraulic system A pump shaft and generates power whenever the ADG is rotating. The PMG has four outputs, one for each branch of the FLCS, and generates sufficient power to operate the FLCS at 40 percent engine rpm or greater. ~ Two converter/regulators, having two channelseach, provide a separate channel for each inverter. Both converter/regulators receive power from the FLCS PMG and, if the EPU is running, the EPU PMG. The branch A and B converter/regulator also receives power from essential dc bus No. 1 and1-86battery bus No. 1 and the branch C and D converter/regulator also receives power from essential dc bus No. 1 and battery bus No.2. Each converter/regulator channel converts ac power from the FLCS PMG to dc, selects the power source with the highest voltage (within limits), and provides dc power to the respective inverter. Converter/regulator output voltages are regulated to prevent overvoltage to the FLCS inverters. LESS ~ Two converter/regulators, having two channels each, provide a separate channel for each inverter. The converter/regulators normally receive power from the FLCS PMG, dc essential bus No.1, and the battery bus. If the EPU is running, the EPU PMG also provides power to the converter/regulators. Each converter/regulator channel converts ac power from the FLCS PMG to dc, selects the power source with the highest voltage (within limits), and provides dc power to the respective inverter. Converter/regulator output voltages are regulated to prevent overvoltage to the FLCS inverters.Each inverter then changes dc to ac power for the FLCS. If the converter/regulator output voltage is less than the FLCS battery voltage, the FLCS battery powers the FLCS branch until balance is reached or the battery is depleted. The converter/regulators also provide fault indications for display on the ELEC control panel and provide test indications to the TEST switch panel. The primary function of the FLCS batteries is to provide temporary emergency power to the FLCS; the batteries are not intended to be a continuous emergency power source. The FLCS batteries are continually charged by power from the converter/regulators when the MAIN PWR switch is in BATT or MAIN PWR. When the MAIN PWR switch is OFF, a trickle charge circuit maintains the FLCS battery charge with power from the aircraft battery. 124. 10.lF-16A-lElectrical Power Distribution Diagram Blockto~MAIN PNR CONTACTORLEGEND: ELECTRICAL!I- - - - - MECHANICAL RESETTABLP 00MONITOR UNITIEXTERNAL PWA = CABLE RECEPTACLENONRESrnABLE~-c,n n n1ADGICen be powered by EPUPowered with EPU Running and Main Goo on Una- ~~ -IIIIIlIIIDCJuPROT!ANEL.~Powered thru NONESS AC BUI No. 20Powered thru Overcurrent Prot Panel~Powered thru ECM PowerPanelA F,I~-;ROVERCURRENT PROTECTION UNITT 0 CIRAOAR AC BUsl'PU ON~IDCBJ I:JW'm~I AC:BU; NO.1Le; f=': m c-.R I A G C HT S T R AI B~~;iJ ,P W R P NK LG'NI R P P B N A L;,A]~ -I BUSF~LI 1 0CBU~:VIII ~'~s~ BOX BUS IIY BRANCH'S{ B. C,FlCS PMG~ '--BAITERY CHARGER! CONTROL ASSEMBLV-- --IrHT S T R: ~BRANCH A TYPICALI CONY~.r.'" .TnoLB~S :] ,~L...... FLCS COMPUTERPt::'--+l 'PUr-P W RA N K LAND 0: BAITR I 0 G C1rlPMGI'PU '--+lAC TO DCFigure 128. (Sheet 1)Change 2187 125. T.O. 1F16AlElectrical Power Distribution Diagram Block 1.5Can be powered by EPU-Powered with EPU Running and Main Gen on Line Powered 1hru NONESS ACBUI No. 2 Powered ttlro Overcurrent Prot Penal No. 1 Powered lhru OvercurrentProt PeMI No. 2OVERCURRfNT PAOTECT10N UNIT FT 0 C, oP U W , R p P 0 N L111 1 DC?:-----10NONESS AC BUS NO. 1I~-I~ IiiEPU ONIt,JI DCESSENTIAL 1 r I BUS NO.~,,, ,0 P U N L P~ .c'~ t'BOX OUSCHARGER!ORANCH A {~r~~, , , , ,FlCS PMG:I~Oo':: ~~ 2 1-- - -,---i , , , , , , , Y-I C( NVTYPICALL- FlCS COMPUTER,I-,R0 G C H T P W S R T R P A N K L~us ' al ,1::-,PUf ...--lLO~T,r:ASSEMBLY'W11111:oc,.~t.~!J~io,A G c H T P W 5 R T R P A N K L-mI~t~ I AC-etrssi~RjIR71I'NlET II II, , , , , , , , , ,~ ,m~PRO~-"~N':-N(! , ,WTO.WfI, 6I~ [.cou ;NO ] Ii: II0 G H Y T A N C A / C 0 C L L P , W R, , , ,IADO, ,I:. ~ou~llllljyPWRL;.;; ,~c:::J.rJ 1m .f- - ELECTRiCAl ----- MECHANICAL RESETIABLP 0 NONReSETIABlE I2lIiITIliIllMAIN PWR CONTACTOR, UNI1LEGEND:PMG'PUIL,.fAC TO DC IFl'lA-l_108''''.FigUT'f!, -88Change 2128. (Sheet 2) 126. IO. l F16A-lElectrical Power Distribution Diagram Air Defense Fighter - - ELECTRICAl MECHANICALMONITOR UNITI-- --0 0MAIN PNR CONTACTORILEGEND:RESETTABLPt EXTERNAl f'INR .ECABLE RECEPTACLE-c::::::JCan be powered by EPU Powered with EPU Run nlng and Main Gan on Une Powered thru NONESS ACBus No.2 Powered thru Overcurr 001Prot Panel No. 1 Powered ttlru Overeurr onlProt Panel No. 2 OVERCURRENT PROTECTION U NITI~,~NU ~ JI~-W I" I~ L I L I 'C-BU , ."'o~, lAFrn I. ""pp N B A L Y;BU'~~~Aii.~~IESSENTIAl DC BUS NO. 11,1 I1 R I B G A H Y T A N C A / C a C,,a! , ,BRANCH B'W IACBu~SSIc,AND 0::t1PROT P~NE~ N ~ 1III",,6&71~->~BRANCH A TYPICALHTK~FlCS PMGLBAT' I~--I CONVIL - FLCSLR I a G C,:PW S R T R p A N'~ ,_OA~ '~~< ;~HT! ,1---,1---PW RT R p A N, KL" 'A~~'PUPMG11111oC~R I A G C;1B.I OVERCURRENTsBATTERY CONTROL~t ~, , , , ,PU N I L P1IH~Ai~P, W R' BOX BUS: , , , , , , , , , ,IADO- M~:TO a Ca p UW I RL L, , , , , , , , :INONESS AC BUS NO.1,M , ,I; I ~ 0 1~IJ;-------1NONRESETTABLE-IWZJ IIIIIIIIIlTI-M'PUI I~ACTQOCCOMPUTERlr15A-l-,oeu.. Figure 128. (Shftt 3)Change 21-89 127. T. O. 1F- 16A- 1 EXTERNAL POWER PROVISIONSThe external power provisions include a standard external power cable receptacle and a monitor unit which are part of the airframe. The monitor unit allows external power to be connected to the aircraft buses if the phasing, voltage, and frequency of the external power are correct. When connected, the external power provides the same power as the main generator. ELECTRICAL SYSTEM CONTROLS AND INDICATORSRefer to figure 1-29. ELECTRICAL POWER DISTRIBUTIONheld in TEST, the ACFT BATT TO FLCS and FLCS PMG lights go off. The FLCS BATT lights come on and the FLCS PWR lights remain on to indicate that the FLCS batteries are good. With the FLCS PWR TEST switch in NORM, when the MAIN PWR switch is moved to MAIN PWR for start on battery power, the lights do not change. If external power is used, the MAIN GEN, ACFT BATT TO FLCS, and the FLCS PWR lights go off when the MAIN PWR switch is moved to MAIN PWR. During engine start, the FLCS PMG light goes off before the engine reaches idle and the main generator comes on line at approximately 45 percent rpm. External power, if used, is disconnected from the aircraft buses when the main generator comes on line.Refer to figures 1-30 and 1-31. NORMAL OPERATIONPrior to engine start, the MAIN PWR switch is placed to BATT to permit a check of the aircraft and FLCS batteries. The ELEC SYS, FLCS PMG, and MAIN GEN lights come on. In addition, the ACFT BATT TO FLCS light comes on to indicate that the aircraft battery is powering the FLCS, and the FLCS PWR lights come on to indicate that the FLCS inverter outputs are good. With the FLCS PWR TEST switch1-90Anytime after selecting MAIN PWR, including in flight, the FLCS PWR TEST switch may be held momentarily in TEST to check inverter output. During the EPU test, the FLCS PWR lights come on to indicate that EPU PMG power is available to the FLCS. During engine shutdown, the ELEC SYS caution light and FLCS PMG and MAIN GEN lights come on as the engine spools down. The ACFT BATT TO FLCS light may also illuminate. 128. 10.lF-16A-lElectrical System Controls and Indicators ~ IBFI (Typical) 21. 2. 3. 4. 5. 6. 7. 8. 9. 10. 11. 12.3MAIN PWR Switch FLCS PMG Indicator Light MAIN GEN Indicator Light STBY GEN Indicator Light EPU GEN Indicator Light EPU PMG Indicator Light FLCS BAIT Indicator Lights ACFT BATT Indicator Lights ELEC SYS Caution Light ELEC CAUTION RESET Button FLCS PWR TEST Switch FLCS PWR Indicator Lights45 61211871F-16A-1-1067X@CONTROUINDICATOR 1.MAIN PWR SwitchPOSITIONIINDICATION MAINPWRConnects external power or the main generator to the electrical system and detennines function of FLCS PWR TEST switch. If ac power is not available, connects aircraft battery to the battery busBATTConnects aircraft battery to the battery bus, disconnects main generator or external power, determines function of FLCS PWR TEST switch, and is used to reset the main generatorOFFIn flight - inoperativeNOTE:During ground operation, if the MAIN PWR switch is moved from MAIN PWR to OFF without a delay of one second in BAIT, the EPU does not activate and electrical power for braking, NWS, hook, and radios is lost.FUNCTIONOn ground - disconnects all power from aircraft electrical system. Canopy operation and FLCS battery trickle charge are availableFigure 1-29. (Sheet 1)1-91 129. T. O. 1F- 16A- 1Electrical System Controls and Indicators [8] [1!E] (Typical) CONTROUINDICATOR 2.FLCS PMG Indicator LightI POSITIONIINDICATION FLCS PMG (amber)FUNCTION In flight- None of the FLCS branches are receiving power from the FLCS PMG On ground - FLCS PMG power is not available at one or more FLCS branches. Light is delayed 60 seconds after initial NLG WOW3.MAIN GEN Indicator LightMAIN GEN (amber)Indicates external power or main generator not connected to the electrical system4.STBY GEN Indicator LightSTBY GEN (amber)Not operational5.EPU GEN Indicator LightEPU GEN (amber)Indicates the EPU has been commanded on but the EPU generator is not providing power to both essential ac buses. The light does not function with the EPU switch in OFF (WOW) and the engine running6.EPU PMG Indicator LightEPU PMG (amber)Indicates the EPU has been commanded on but EPU PMG power is not available to all branches of the FLCS7.FLCS BATT Indicator LightsA, B, C, and D (amber)Indicates the respective FLCS battery discharging to the indicated FLCS branch8.ACFT BATT Indicator LightsTO FLCS (amber)In flight - indicates battery bus power is going to one or more FLCS branches and voltage is 25V or less On ground - indicates battery bus power is going to one or more FLCS branchesFAIL (amber)In flight - indicates aircraft battery failure (20V or less) On ground - indicates aircraft battery failure or cell voltage imbalance condition. Light is delayed 60 seconds after MLG WOW9.ELEC SYS Caution LightELEC SYS (amber)Figure 1-29. (Sheet 2)1-92Illuminates in conjunction with any of the above lights. Also illuminates if one or more FLCS batteries are not connected when the main generator is on line 130. T. O. 1F- 16A- 1Electrical System Controls and Indicators [8J [IE] (Typical) CONTROLIINDICATORPOSITIONIINDICATIONFUNCTION10.ELEC CAUTION RESET ButtonPushResets resettable overcurrent protection units and ELEC SYS caution light and clears MASTER CAUTION light for future indications11.FLCS PWR TEST SwitchTESTWhen MAIN PWR switch is in: MAINPWRBATTTests FLCS inverter Tests FLCS inverter output output on FLCB batteries on ground NORMMAINT 12.FLCS PWR Indicator LightsNonnal position. Tests EPU PMG power availability during EPU/GEN test on groundTests FLCS inverter output on aircraft batteryFor maintenance use on the ground. Inoperative in flightA, B, C, and D (green)Illuminate to indicate proper FLCB inverter output during FLCB power testsFigure 1-29. (Sheet 3)Change 21-93/{1-94 blank) 131. T.O.1F-16A-lAC Power Distribution Diagram Block 10 MAIN GENERATORQVERCURRENT PROT PANELFCC INS HeaterIFCRSUI 3, 5, 7 - ECM, EO &. Redar-Guided WeaponsInterference Blanker REO TT Probe HesterAircraft Banary HeatBr Flight loads RecorderHalon Haeter Seat AdjustFlood Console Ughts Flood Instrumant lighllStations 4 &. 6 - EO &.Formation Ughts Fuel Boost &. Transfer PumpsEPU GENERATORRadar-Guided Weapons Taxi Ught TlSLTWS'PU'PUON-wAir Dale Probe Heaters Inose &. fusel.ge l Altimeter (ELEen ADA Indicalor ADA Probe Heater.ADI AIM-9Anticolli.ion Strobe Light AR Ught (Flood) Data Transfer Unit DC ConverterCAOCINS LEF'. Nav/Fraq Display Primary Console Lights Primary Instrument UghtsDC Converter'CA FUEL FLOW Indicator HUD/eTVSEngine Ice Detector Fire/Overheat Detect & Test FUEL Quantity IndicatorG," HSI HYD PRESS IndicatorsIFF (mode 41 Inlet Strut Heater Lan~ Ught UQUID OXYGEN Quantity Indicator1AllfJLEGEND:otzIONELECTRICAL MECHANICAL RESETTABLE NONRESITTABLENOZ POS Indicator OIL Pressure Indicator Position Lights TACAN~ Can be powered by EPU _Powered thru NONESS AC Bus No.2c::::JPowered thru Overcurrent Prot Panel_Powered Ihru ECM Power Panel IFl&Al118 .......Figure 130. (Sheetl)Change 31-95 132. 10.lF-16A-lAC Power Distribution Diagram Block 15IADIMAIN GENERATORQVERCURAENT PROT PANEL NO. 1Oal8 ControlIOata Trenlifer Flight loads RecorderSia 3 , 5 , 7 - EeM, EO & Radar-Guided WeaponsNONESS ACausGPS INS Heater Interference BlankerFlood Console Lights Flood Instrument Lights Formation Lights Fuel Boost & Transfer Pumps Halon Heeler Inlet Strut HeaterNO. 1REOS t AdjustTT Probe HeaterStation 4 & 6 - EO &. Radar-Guided WeaponsEPU-ON-w -----------EPU GENERATORTaxi Light TISLTWS~ A1M-7/A1M-9/AIM- 1 20EPU ON-w Air Data Probe Heater.CADCInose & fuselage} Ahimetaf (ELECT)DC ConverterLEF'sEC' FCCNav/Freq Displav Primary Console Lights Primary Instrument LightsADA Indicator ADA Probe Healers"""""",.""""""FUEL FLOW Indicator HUO/CTVS .",1.."",..."""""""""""""""",,,,,,1'1111111111111: 1111:~. :I Anticollision Strobe Light AR Light !nood) DC Converter Engine Ice DetectorFUEL Quantity IndicatorLan~G,n "51[!]lIEJLight LIQUID OXYGEN Quantity IndicatorOIL Pressure Indicator Position Lights TACANHYD PRESS Indicators Can be powered by EPU Powered thru NONESS AC Bus No. 2 MECHANICAL RESEnABLE NONRESETTABLfPowered thru OverCUfrent Prot Panel No. , Powered thru Overcurrent Prot Panel No. 2 1f-1SA-1-1198A.Figure 130. (SMet 2)1-96Change 3 133. T.0.1F-16A-lAC Power Distribution Diagram LESS M Block 1.5MAIN GENERATOROVERCURRENT PROT PANEL NO. 1NONESS AC BUS NO. 2Aircraft Banery HeaterData Control Flight Loads Recorder Sla 3, 5, 7 - ECM, EO &: RadlH-Guided WeaponsFlood Console LightsFlood Instrument Lights Formation lights Fuel Boost &. Transfer Pumps Halon HeaterNONESS AC BUS NO. 1Inlet Strut Heater FCC INS Heater Interference BlankerREOnAIM-9/AIM-120Probe HeaterSeat Adjust Station 4 & 6 - EO &: Radar-Guided WeaponsTaxi light nSlEPU-TWSONEPU GENERATORAIM-9/AIM- 120EPU-w Air Data Probe Heaters Inose &: fuselagel Altimeter (ELEenINSCAOC DC Converter ECA FUEL FLOW Indicator HUD/ClVSADA Indicator ADA Probe HealersAnticollision Strobe Light AR Light [flood) Data Transfer Unit DC Converter-ONlEF's Nav!Freq Display Primary Console Lights Primary Instrument LightsEngine Ice Detector Fire/Overheat Detect &: Test FUEL Quantity Indicator Goo HSIHYD PRESS Indicators LESS ~ IFF (mode 4 ) Landing Light [!1[1f] LIQUID OXYGEN QuantilV IndicatorOIL Pressuro Indicator Position Lights TACANLEGEND:~ Can be powered by EPU- - - ELECTRICAL MECHANICALc:::::J CJo oRESETTABlE NQNRESETTABLE_Powered thru NONESS AC Bus No. 2 Powered Ihru Overcurrent Prot Panel No. 1 Powered thru Overcurrenl Prot Panel No. 2 IF- 16A-1 - 11988.Figure 130. (Sheet 3)Change 121-97 134. T.O.1F-16A-lDC Power Distribution Diagram Block 10IAl AlTAEl ButtonADA IndexerEnvironmental Control Test FCNPAR SystemFLCP 'aU Hghts, reset, arm,Autopilot Benary BUI Feeder CAOC Caution lightFlCS Power Source IFFeJUINSTR MODE Select'N'~;;:D~~H~~~~ .~~~~ VI~. 28 VOCI~BATTERY BUSNp~~ I~~~I~~I~ANTISKIO CAUTION LIGHT RELAV1 ;-LPARK VALlIEI'" t--_ lr, 8RAKE CONTROLI ANTI-SKID ASSVBUS NO. 1~CHANNEL SELECTORCHANNEL' OR CHANNEL 2 OUTPUT.w......., ~ "" , .-.umSllCe C~2 ., ~I-L-L -L ACI I~ ~olt-{FSHUTTlE VALVEPREBRAKE RESTRICTOR VAlVE-~FLCS INVERTERSB0~ ~~WHEEL LG UP PRESSURE SPEED SENSOR~-IfAQI L..., L,R'--'--TOE BRAKES,26 VAC 800 Ii, 4 INDEPENDENT EXCITATION POweR SOURCES FROM FLCS INVERTERSFigure 1-39. (Sheet 1)Change 6~BRAKE CHAN 2 ,.----"-----,BRAKE CHAN' ,.----"-----,~~1-116~CHANNEL 228 VDC 8ATTERVLESSl::::t!PM'~28 VDC 8ATTERV BUS NO. 2I~ 157. T.O.1F-16A-1HYO SYS B PRESSURE . . . .LEGEND: - - ELECTRICAL - - - - MECHANICAL _HYD POWER SUPPLYI ~ HYD RETURNcz:DBRAKE HYD CIRCUIT_PARKING BRAKE CIRCUIT[!]CHECK VALVELEFT METERINGVAlVEWHEEL SPeED SENSORLEFT BRAJ(1F-ll1A-1_2074-lJeFigure 139. (SMet 2)Change 61-116.1 158. T.O. 1F-16A-lI WheelBrake Schematic (Typical) LESS ifO..t:1 THROTILE POSITION SWITCH MLGNEAR IDLE28 VDC BAmRV BUSI~"'II/I". r I.. )..;~~~---,!},! ANTlSKIDCONTROL BOX. -N~~~I~r-~-h-fANTISKIOCAUTION'. ~I~r-o--wowLIGHT RELAY;::r:"::o--J2 8 VDC BATIERV BUS NO. 1BRAKE CONTROL ~ BOXI@lCHANNElL.... ;:;:.,;..,..,'.-,--m-./ I -., BATIERY BUSg~ANNEl 1 {~~t~ CHANNEL 2 OUTPUT~ 'i",~2B VDCF-o-]..0 4~ ~ 29" ~~ COMMAND -I II,~.-.JL _____I ,11-+-____...1 -.: LIMITISA-@;J ~RONNOTE:FLCS lains scheduled by air data inputs. -----,LEGEND ELECTRICAL - - - - MECHANICAL~AL;/SERVO AMPLIFIERISA--~ :SELECTOR~_________~29 ~I,...,!.. ....I I I I~ON'------'~AILERON.... SELECTOR A RUDDER INTERCONNECT'1LEFT HORtz TAILIAUTOPILOT ROLLtHI""""R-IG-HT-H-OR-IZ""" TAIL '-------'f--_I YAW RATE 1t---+-tI,TI--e-----.c YAW AXIS LATERAL I! l ~ ACCELERATION I I I~Ih/j-_.SELECTOR ~ -MECH LIMIT :1-++-+----....J-~A I..... SELECTOR.----+-_':.=====::~ r ,.,.....-____---, r - . . . .1 ,r-,--MANUAL PITCH ~ OVERRIDESTAB ILlTY/ COMMAND AUGMENTATIONIISELECTOR J~-I~_ _ _ _+--.-tNORMALhI , IPITCH INTEGRATOR_.....-------.1. -IISTICK LIMIT4I..JAUTOPILOT PITCH IMECH LIMIT "I HORIZ TAIL STICK FORCE IILLPITCH TRIMr:=l~I I~1F-1SX-1-0009xeFigure 1-42.1-124 167. T. O. 1F- 16A- 1FLCS Limiter Functions ROLL AXISYAW AXISMaximum AOA=25Maximum roll rate command decreases with:Maximum deflection (pedal command) reduced for:g command system until 15 AOA AOA above 15 AOA> 14 (zero roll rate) Airspeed less than 250 knots Roll rate>200/secPITCH AXISCAT Ig/AOA command system above 15 AOAMaximum AOA= 16-18 pending on GW)CAT III(de-g command system until 7 AOA at 100 knots to 15 AOA at 420 knots and above Horizontal tail deflection more than 5 trailing edge downMaximum roll rate command reduced by approximately 40 percent of CAT I authority. Additional decreases as function of AOA, airspeed, and horizontal tail positionNOTE: Zero rudder authority available at 26 AOA. Maximum deflection (pedal command) reduced for: AOA>3 (zero roll rate) Roll rate>200/secNOTE: Zero rudder authority available at 15 AOA.g/AOA command system above these valuesNOTES1. In takeoff/landing gains, the FLCS operates as a pitch rate command system until 10 AOA and a pitch rate/AOA command system above 10 AOA. 2. +9g available until 15 AOA. Maximum g decreases as a function of AOA and airspeed.1. In takeoff/landing gains, maximum roll rate is fixed at approximately one-half the maximum roll rate available in cruise gains, regardless of AOA, airspeed, or horizontal tail deflection. 2. Above 29 AOA, the yaw rate limiter cuts out stick roll commands and provides roll axis antispin control inputs.1. Above 29 AOA, the yaw rate limiter provides yaw axis antispin control inputs. 2. Above 29 AOA with MPO engaged, pedal-commanded rudder deflection is possible. 3. Maximum deflection (30) always available thru ARI and stability augmentation.Figure 1-43. Change 11-125II 168. T.O. 1F-16A-1AOAlG Limiter Function (Cruise Gains)10III9............. r .....CAr I SELECTED~..... 1-...8r- ..... I-r---tIIICJII 7a::0 ... CJ~II....IIftoI-6.... I'.;--r--1 II' ;---I(III,-I1CAT III SELECTED GW 25,000 POUNDS=I'I,I 'II1I' ~5.....,IIIQ-~O~ ON .".'0.0-I;~1>- FAST_.~ATTITUDEIa3sr~~~-Figu11! 1-51.1-138I 179. T.O.1F-16A-1AIR DATA SYSTEMStatic Pressure PortsRefer to figure 1-52. The air data system uses probes and sensors to obtain static and total air pressures, AOA, sideslip, and air temperature inputs. These air data parameters are processed and supplied to various systems.Two flush-mounted static pressure ports used for measuring sideslip are located on the fuselage left and right sides aft of the forward equipment bay doors. These two ports provide inputs to a differential pressure sensor for angle-of-sideslip measurement. The measurement is also used to compensate the third AOA source error. Probe Heat Monitor ~IProper AOA transmitter and fuselage air data probe operation is essential for safe flight operation. Interference from foreign objects (especially ice, internal or external) or improperly installed AOA transmit