haf f16 supplement

T.O. GR1F16CJ11

9 JUNE 1997CHANGE 815 JUNE 2003

Supplemental

FLIGHT MANUALHAF SERIES AIRCRAFT

F16C/DBLOCKS 50 AND 52 +

LOCKHEED MARTIN CORPORATION

F3365790C2002

F3365799C0059

Commanders are responsible for bringing this publication to the attention of all Air Force personnel cleared foroperation of subject aircraft.

GR1F-16C-1-0001X

T.O. GR1F16CJ11

T2Change 2

DISCLOSURE STATEMENT

This information is furnished on the conditions that it will not be released to another nation without thespecific authorization of the Department of the Air Force of the United States; it will be used for militarypurposes only; the recipient will report promptly to the United States any known or suspected compromise;and the information will be provided substantially the same degree of security afforded it by the Departmentof Defense of the United States. Also, regardless of any other markings on the document, it will not bedowngraded or declassified without the written approval of the originating US agency. Any request for thisdocument should be referred to OOALC/YPXG, 6089 Wardleigh Road, Hill AFB, UT 840565838.

SUPPLEMENTAL NOTICE

This manual is incomplete without T.O. GR1F16CJ1.

SUPERSEDURE NOTICE

See Technical Order Index, T.O. GR0171, for current status of Flight Manuals, Safety Supplements, Operational Supplements, and Flight Crew Checklists.

LIST OF EFFECTIVE PAGES

NOTE:Changes to the current issue are indicated by a vertical line in the outer margins of the page.

T.O. GR1F16CJ11

INSERT LATEST CHANGED PAGES. DESTROY SUPERSEDED PAGES.

Change 8A

HAFA8

Dates of issue for original and changed pages are:

Original 0 9 Jun 97. . . . . . . . Change 1 6 Apr 98. . . . . . . . . Change 2 15 Mar 99. . . . . . .

Change 3 15 Nov 99. . . . . . . Change 4 15 Jun 00. . . . . . . . Change 5 15 Mar 01. . . . . . .

Change 6 15 Apr 02. . . . . . . . Change 7 15 Nov 02. . . . . . . Change 8 15 Jun 03. . . . . . . .

TOTAL NUMBER OF PAGES IN THIS PUBLICATION IS 736, CONSISTING OF THE FOLLOWING:

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Title 8. . . . . . . . . . . . . . . . . . . .

T2 2. . . . . . . . . . . . . . . . . . . . . .

A 8. . . . . . . . . . . . . . . . . . . . . . .

B 8. . . . . . . . . . . . . . . . . . . . . . .

C 8. . . . . . . . . . . . . . . . . . . . . . .

D 8. . . . . . . . . . . . . . . . . . . . . . .

E 8. . . . . . . . . . . . . . . . . . . . . . .

F Blank 8. . . . . . . . . . . . . . . . .

i 7. . . . . . . . . . . . . . . . . . . . . . . .

ii 2. . . . . . . . . . . . . . . . . . . . . . .

A11 7. . . . . . . . . . . . . . . . . . . .

A12 8. . . . . . . . . . . . . . . . . . . .

A13 7. . . . . . . . . . . . . . . . . . . .

A14 7. . . . . . . . . . . . . . . . . . . .

A15 7. . . . . . . . . . . . . . . . . . . .

A16 7. . . . . . . . . . . . . . . . . . . .

A17 7. . . . . . . . . . . . . . . . . . . .

A18 7. . . . . . . . . . . . . . . . . . . .

A19 7. . . . . . . . . . . . . . . . . . . .

A110 7. . . . . . . . . . . . . . . . . . .

A111 7. . . . . . . . . . . . . . . . . . .

A112 7. . . . . . . . . . . . . . . . . . .

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A116 7. . . . . . . . . . . . . . . . . . .

A117 7. . . . . . . . . . . . . . . . . . .

A118 7. . . . . . . . . . . . . . . . . . .

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A120 7. . . . . . . . . . . . . . . . . . .

A121 7. . . . . . . . . . . . . . . . . . .

A122 7. . . . . . . . . . . . . . . . . . .

A123 7. . . . . . . . . . . . . . . . . . .

A124 7. . . . . . . . . . . . . . . . . . .

A21 7. . . . . . . . . . . . . . . . . . . .

A22 7. . . . . . . . . . . . . . . . . . . .

A23 7. . . . . . . . . . . . . . . . . . . .

A24 7. . . . . . . . . . . . . . . . . . . .

A25 7. . . . . . . . . . . . . . . . . . . .

A26 7. . . . . . . . . . . . . . . . . . . .

A27 7. . . . . . . . . . . . . . . . . . . .

A28 7. . . . . . . . . . . . . . . . . . . .

A29 7. . . . . . . . . . . . . . . . . . . .

A210 7. . . . . . . . . . . . . . . . . . .

A211 7. . . . . . . . . . . . . . . . . . .

A212 7. . . . . . . . . . . . . . . . . . .

A213 7. . . . . . . . . . . . . . . . . . .

A214 7. . . . . . . . . . . . . . . . . . .

A215 7. . . . . . . . . . . . . . . . . . .

A216 7. . . . . . . . . . . . . . . . . . .

A217 7. . . . . . . . . . . . . . . . . . .

A218 7. . . . . . . . . . . . . . . . . . .

A219 7. . . . . . . . . . . . . . . . . . .

A220 7. . . . . . . . . . . . . . . . . . .

A221 7. . . . . . . . . . . . . . . . . . .

A222 7. . . . . . . . . . . . . . . . . . .

A223 7. . . . . . . . . . . . . . . . . . .

A224 7. . . . . . . . . . . . . . . . . . .

A225 7. . . . . . . . . . . . . . . . . . .

A226 7. . . . . . . . . . . . . . . . . . .

A227 7. . . . . . . . . . . . . . . . . . .

A228 8. . . . . . . . . . . . . . . . . . .

A229 8. . . . . . . . . . . . . . . . . . .

A230 7. . . . . . . . . . . . . . . . . . .

A231 7. . . . . . . . . . . . . . . . . . .

A232 Blank 7. . . . . . . . . . . . .

A31 7. . . . . . . . . . . . . . . . . . . .

A32 7. . . . . . . . . . . . . . . . . . . .

A33 7. . . . . . . . . . . . . . . . . . . .

A34 7. . . . . . . . . . . . . . . . . . . .

A35 7. . . . . . . . . . . . . . . . . . . .

A36 7. . . . . . . . . . . . . . . . . . . .

A37 7. . . . . . . . . . . . . . . . . . . .

A38 7. . . . . . . . . . . . . . . . . . . .

A39 7. . . . . . . . . . . . . . . . . . . .

A310 7. . . . . . . . . . . . . . . . . . .

A41 7. . . . . . . . . . . . . . . . . . . .

A42 7. . . . . . . . . . . . . . . . . . . .

A43 7. . . . . . . . . . . . . . . . . . . .

A44 7. . . . . . . . . . . . . . . . . . . .

A45 7. . . . . . . . . . . . . . . . . . . .

A46 7. . . . . . . . . . . . . . . . . . . .

A47 7. . . . . . . . . . . . . . . . . . . .

A48 7. . . . . . . . . . . . . . . . . . . .

A49 7. . . . . . . . . . . . . . . . . . . .

A410 7. . . . . . . . . . . . . . . . . . .

A411 7. . . . . . . . . . . . . . . . . . .

A412 7. . . . . . . . . . . . . . . . . . .

A413 7. . . . . . . . . . . . . . . . . . .

A414 7. . . . . . . . . . . . . . . . . . .

A415 7. . . . . . . . . . . . . . . . . . .

A416 7. . . . . . . . . . . . . . . . . . .

A417 7. . . . . . . . . . . . . . . . . . .

A418 7. . . . . . . . . . . . . . . . . . .

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A420 7. . . . . . . . . . . . . . . . . . .

A421 7. . . . . . . . . . . . . . . . . . .

A422 7. . . . . . . . . . . . . . . . . . .

A423 7. . . . . . . . . . . . . . . . . . .

A424 7. . . . . . . . . . . . . . . . . . .

A425 7. . . . . . . . . . . . . . . . . . .

A426 7. . . . . . . . . . . . . . . . . . .

A427 7. . . . . . . . . . . . . . . . . . .

A428 7. . . . . . . . . . . . . . . . . . .

A429 7. . . . . . . . . . . . . . . . . . .

A430 7. . . . . . . . . . . . . . . . . . .

A431 7. . . . . . . . . . . . . . . . . . .

A432 7. . . . . . . . . . . . . . . . . . .

A433 7. . . . . . . . . . . . . . . . . . .

A434 7. . . . . . . . . . . . . . . . . . .

A435 7. . . . . . . . . . . . . . . . . . .

A436 7. . . . . . . . . . . . . . . . . . .

A437 7. . . . . . . . . . . . . . . . . . .

A438 7. . . . . . . . . . . . . . . . . . .

A439 7. . . . . . . . . . . . . . . . . . .

A440 7. . . . . . . . . . . . . . . . . . .

A441 7. . . . . . . . . . . . . . . . . . .

A442 7. . . . . . . . . . . . . . . . . . .

A443 7. . . . . . . . . . . . . . . . . . .

A444 7. . . . . . . . . . . . . . . . . . .

A445 7. . . . . . . . . . . . . . . . . . .

A446 7. . . . . . . . . . . . . . . . . . .

A447 7. . . . . . . . . . . . . . . . . . .

* Zero in this column indicates an original page.

LIST OF EFFECTIVE PAGES (Cont)

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BChange 8

A448 7. . . . . . . . . . . . . . . . . . .

A449 7. . . . . . . . . . . . . . . . . . .

A450 7. . . . . . . . . . . . . . . . . . .

A451 7. . . . . . . . . . . . . . . . . . .

A452 7. . . . . . . . . . . . . . . . . . .

A453 7. . . . . . . . . . . . . . . . . . .

A454 7. . . . . . . . . . . . . . . . . . .

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A456 7. . . . . . . . . . . . . . . . . . .

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A458 7. . . . . . . . . . . . . . . . . . .

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A460 7. . . . . . . . . . . . . . . . . . .

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A462 7. . . . . . . . . . . . . . . . . . .

A463 7. . . . . . . . . . . . . . . . . . .

A464 Blank 7. . . . . . . . . . . . .

A51/A61 7. . . . . . . . . . . . . . .

A62 7. . . . . . . . . . . . . . . . . . . .

A63 7. . . . . . . . . . . . . . . . . . . .

A64 7. . . . . . . . . . . . . . . . . . . .

A65 7. . . . . . . . . . . . . . . . . . . .

A66 7. . . . . . . . . . . . . . . . . . . .

A71 7. . . . . . . . . . . . . . . . . . . .

A72 7. . . . . . . . . . . . . . . . . . . .

A73 7. . . . . . . . . . . . . . . . . . . .

A74 7. . . . . . . . . . . . . . . . . . . .

A75 7. . . . . . . . . . . . . . . . . . . .

A76 8. . . . . . . . . . . . . . . . . . . .

A77 7. . . . . . . . . . . . . . . . . . . .

A78 7. . . . . . . . . . . . . . . . . . . .

A79 7. . . . . . . . . . . . . . . . . . . .

A710 Blank 7. . . . . . . . . . . . .

A81 7. . . . . . . . . . . . . . . . . . . .

A82 7. . . . . . . . . . . . . . . . . . . .

A83 7. . . . . . . . . . . . . . . . . . . .

A84 7. . . . . . . . . . . . . . . . . . . .

A85 7. . . . . . . . . . . . . . . . . . . .

A86 7. . . . . . . . . . . . . . . . . . . .

A87 7. . . . . . . . . . . . . . . . . . . .

A88 7. . . . . . . . . . . . . . . . . . . .

A89 7. . . . . . . . . . . . . . . . . . . .

A810 7. . . . . . . . . . . . . . . . . . .

A811 7. . . . . . . . . . . . . . . . . . .

A812 7. . . . . . . . . . . . . . . . . . .

A813 7. . . . . . . . . . . . . . . . . . .

A814 7. . . . . . . . . . . . . . . . . . .

A815 7. . . . . . . . . . . . . . . . . . .

A816 7. . . . . . . . . . . . . . . . . . .

A817 7. . . . . . . . . . . . . . . . . . .

A818 7. . . . . . . . . . . . . . . . . . .

A819 7. . . . . . . . . . . . . . . . . . .

A820 7. . . . . . . . . . . . . . . . . . .

A821 7. . . . . . . . . . . . . . . . . . .

A822 7. . . . . . . . . . . . . . . . . . .

A823 7. . . . . . . . . . . . . . . . . . .

A824 7. . . . . . . . . . . . . . . . . . .

A825 7. . . . . . . . . . . . . . . . . . .

A826 7. . . . . . . . . . . . . . . . . . .

A827 7. . . . . . . . . . . . . . . . . . .

A828 7. . . . . . . . . . . . . . . . . . .

A829 7. . . . . . . . . . . . . . . . . . .

A830 7. . . . . . . . . . . . . . . . . . .

A831 7. . . . . . . . . . . . . . . . . . .

A832 7. . . . . . . . . . . . . . . . . . .

A833 7. . . . . . . . . . . . . . . . . . .

A834 7. . . . . . . . . . . . . . . . . . .

A835 7. . . . . . . . . . . . . . . . . . .

A836 7. . . . . . . . . . . . . . . . . . .

A837 7. . . . . . . . . . . . . . . . . . .

A838 7. . . . . . . . . . . . . . . . . . .

A839 7. . . . . . . . . . . . . . . . . . .

A840 7. . . . . . . . . . . . . . . . . . .

A841 7. . . . . . . . . . . . . . . . . . .

A842 7. . . . . . . . . . . . . . . . . . .

A843 7. . . . . . . . . . . . . . . . . . .

A844 7. . . . . . . . . . . . . . . . . . .

A845 7. . . . . . . . . . . . . . . . . . .

A846 7. . . . . . . . . . . . . . . . . . .

A847 7. . . . . . . . . . . . . . . . . . .

A848 7. . . . . . . . . . . . . . . . . . .

A849 7. . . . . . . . . . . . . . . . . . .

A850 7. . . . . . . . . . . . . . . . . . .

A851 7. . . . . . . . . . . . . . . . . . .

A852 7. . . . . . . . . . . . . . . . . . .

A853 7. . . . . . . . . . . . . . . . . . .

A854 7. . . . . . . . . . . . . . . . . . .

A855 7. . . . . . . . . . . . . . . . . . .

A856 7. . . . . . . . . . . . . . . . . . .

A857 7. . . . . . . . . . . . . . . . . . .

A858 7. . . . . . . . . . . . . . . . . . .

A859 7. . . . . . . . . . . . . . . . . . .

A860 7. . . . . . . . . . . . . . . . . . .

A861 7. . . . . . . . . . . . . . . . . . .

A862 7. . . . . . . . . . . . . . . . . . .

A863 7. . . . . . . . . . . . . . . . . . .

A864 7. . . . . . . . . . . . . . . . . . .

A865 7. . . . . . . . . . . . . . . . . . .

A866 7. . . . . . . . . . . . . . . . . . .

A867 7. . . . . . . . . . . . . . . . . . .

A868 7. . . . . . . . . . . . . . . . . . .

A869 7. . . . . . . . . . . . . . . . . . .

A870 7. . . . . . . . . . . . . . . . . . .

A871 7. . . . . . . . . . . . . . . . . . .

A872 7. . . . . . . . . . . . . . . . . . .

A873 7. . . . . . . . . . . . . . . . . . .

A874 7. . . . . . . . . . . . . . . . . . .

A875 7. . . . . . . . . . . . . . . . . . .

A876 7. . . . . . . . . . . . . . . . . . .

A877 7. . . . . . . . . . . . . . . . . . .

A878 7. . . . . . . . . . . . . . . . . . .

A879 7. . . . . . . . . . . . . . . . . . .

A880 7. . . . . . . . . . . . . . . . . . .

A881 7. . . . . . . . . . . . . . . . . . .

A882 7. . . . . . . . . . . . . . . . . . .

A883 7. . . . . . . . . . . . . . . . . . .

A884 7. . . . . . . . . . . . . . . . . . .

A91 7. . . . . . . . . . . . . . . . . . . .

A92 7. . . . . . . . . . . . . . . . . . . .

A93 7. . . . . . . . . . . . . . . . . . . .

A94 7. . . . . . . . . . . . . . . . . . . .

A95 7. . . . . . . . . . . . . . . . . . . .

A96 7. . . . . . . . . . . . . . . . . . . .

A97 7. . . . . . . . . . . . . . . . . . . .

A98 7. . . . . . . . . . . . . . . . . . . .

A99 7. . . . . . . . . . . . . . . . . . . .

A910 7. . . . . . . . . . . . . . . . . . .

A911 8. . . . . . . . . . . . . . . . . . .

A912 8. . . . . . . . . . . . . . . . . . .

A913 7. . . . . . . . . . . . . . . . . . .

A914 7. . . . . . . . . . . . . . . . . . .

A915 7. . . . . . . . . . . . . . . . . . .

A916 7. . . . . . . . . . . . . . . . . . .

A917 7. . . . . . . . . . . . . . . . . . .

A918 Blank 7. . . . . . . . . . . . .

B11 3. . . . . . . . . . . . . . . . . . . .

B12 8. . . . . . . . . . . . . . . . . . . .

B13 8. . . . . . . . . . . . . . . . . . . .

B14 3. . . . . . . . . . . . . . . . . . . .

B15 3. . . . . . . . . . . . . . . . . . . .

B16 5. . . . . . . . . . . . . . . . . . . .

B17 4. . . . . . . . . . . . . . . . . . . .

B18 3. . . . . . . . . . . . . . . . . . . .

B19 1. . . . . . . . . . . . . . . . . . . .

B110 3. . . . . . . . . . . . . . . . . . .

B111 5. . . . . . . . . . . . . . . . . . .

B112 5. . . . . . . . . . . . . . . . . . .

B113 0. . . . . . . . . . . . . . . . . . .

B114 0. . . . . . . . . . . . . . . . . . .

B115 0. . . . . . . . . . . . . . . . . . .

B116 0. . . . . . . . . . . . . . . . . . .

B117 0. . . . . . . . . . . . . . . . . . .

B118 0. . . . . . . . . . . . . . . . . . .

B119 0. . . . . . . . . . . . . . . . . . .

B120 0. . . . . . . . . . . . . . . . . . .

B121 3. . . . . . . . . . . . . . . . . . .

B122 3. . . . . . . . . . . . . . . . . . .

B123 0. . . . . . . . . . . . . . . . . . .

B124 0. . . . . . . . . . . . . . . . . . .

B21 8. . . . . . . . . . . . . . . . . . . .

B22 3. . . . . . . . . . . . . . . . . . . .

B23 3. . . . . . . . . . . . . . . . . . . .

B24 8. . . . . . . . . . . . . . . . . . . .

B25 3. . . . . . . . . . . . . . . . . . . .

B26 0. . . . . . . . . . . . . . . . . . . .


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Change 8C

B27 3. . . . . . . . . . . . . . . . . . . .

B28 0. . . . . . . . . . . . . . . . . . . .

B29 3. . . . . . . . . . . . . . . . . . . .

B210 3. . . . . . . . . . . . . . . . . . .

B211 3. . . . . . . . . . . . . . . . . . .

B212 3. . . . . . . . . . . . . . . . . . .

B213 8. . . . . . . . . . . . . . . . . . .

B214 3. . . . . . . . . . . . . . . . . . .

B215 3. . . . . . . . . . . . . . . . . . .

B216 3. . . . . . . . . . . . . . . . . . .

B217 3. . . . . . . . . . . . . . . . . . .

B218 3. . . . . . . . . . . . . . . . . . .

B219 3. . . . . . . . . . . . . . . . . . .

B220 3. . . . . . . . . . . . . . . . . . .

B221 3. . . . . . . . . . . . . . . . . . .

B222 3. . . . . . . . . . . . . . . . . . .

B223 3. . . . . . . . . . . . . . . . . . .

B224 3. . . . . . . . . . . . . . . . . . .

B225 3. . . . . . . . . . . . . . . . . . .

B226 0. . . . . . . . . . . . . . . . . . .

B227 0. . . . . . . . . . . . . . . . . . .

B228 8. . . . . . . . . . . . . . . . . . .

B229 8. . . . . . . . . . . . . . . . . . .

B230 0. . . . . . . . . . . . . . . . . . .

B231 0. . . . . . . . . . . . . . . . . . .

B232 Blank 0. . . . . . . . . . . . .

B31 3. . . . . . . . . . . . . . . . . . . .

B32 3. . . . . . . . . . . . . . . . . . . .

B33 3. . . . . . . . . . . . . . . . . . . .

B34 3. . . . . . . . . . . . . . . . . . . .

B35 3. . . . . . . . . . . . . . . . . . . .

B36 3. . . . . . . . . . . . . . . . . . . .

B37 3. . . . . . . . . . . . . . . . . . . .

B38 3. . . . . . . . . . . . . . . . . . . .

B39 3. . . . . . . . . . . . . . . . . . . .

B310 3. . . . . . . . . . . . . . . . . . .

B41 3. . . . . . . . . . . . . . . . . . . .

B42 3. . . . . . . . . . . . . . . . . . . .

B43 3. . . . . . . . . . . . . . . . . . . .

B44 3. . . . . . . . . . . . . . . . . . . .

B45 3. . . . . . . . . . . . . . . . . . . .

B46 3. . . . . . . . . . . . . . . . . . . .

B47 0. . . . . . . . . . . . . . . . . . . .

B48 3. . . . . . . . . . . . . . . . . . . .

B49 3. . . . . . . . . . . . . . . . . . . .

B410 3. . . . . . . . . . . . . . . . . . .

B411 3. . . . . . . . . . . . . . . . . . .

B412 3. . . . . . . . . . . . . . . . . . .

B413 3. . . . . . . . . . . . . . . . . . .

B414 3. . . . . . . . . . . . . . . . . . .

B415 3. . . . . . . . . . . . . . . . . . .

B416 3. . . . . . . . . . . . . . . . . . .

B417 3. . . . . . . . . . . . . . . . . . .

B418 3. . . . . . . . . . . . . . . . . . .

B419 3. . . . . . . . . . . . . . . . . . .

B420 3. . . . . . . . . . . . . . . . . . .

B421 3. . . . . . . . . . . . . . . . . . .

B422 3. . . . . . . . . . . . . . . . . . .

B423 3. . . . . . . . . . . . . . . . . . .

B424 3. . . . . . . . . . . . . . . . . . .

B425 3. . . . . . . . . . . . . . . . . . .

B426 3. . . . . . . . . . . . . . . . . . .

B427 3. . . . . . . . . . . . . . . . . . .

B428 3. . . . . . . . . . . . . . . . . . .

B429 3. . . . . . . . . . . . . . . . . . .

B430 3. . . . . . . . . . . . . . . . . . .

B431 3. . . . . . . . . . . . . . . . . . .

B432 3. . . . . . . . . . . . . . . . . . .

B433 3. . . . . . . . . . . . . . . . . . .

B434 3. . . . . . . . . . . . . . . . . . .

B435 3. . . . . . . . . . . . . . . . . . .

B436 3. . . . . . . . . . . . . . . . . . .

B437 3. . . . . . . . . . . . . . . . . . .

B438 3. . . . . . . . . . . . . . . . . . .

B439 3. . . . . . . . . . . . . . . . . . .

B440 3. . . . . . . . . . . . . . . . . . .

B441 3. . . . . . . . . . . . . . . . . . .

B442 3. . . . . . . . . . . . . . . . . . .

B443 3. . . . . . . . . . . . . . . . . . .

B444 3. . . . . . . . . . . . . . . . . . .

B445 3. . . . . . . . . . . . . . . . . . .

B446 3. . . . . . . . . . . . . . . . . . .

B447 3. . . . . . . . . . . . . . . . . . .

B448 3. . . . . . . . . . . . . . . . . . .

B449 3. . . . . . . . . . . . . . . . . . .

B450 3. . . . . . . . . . . . . . . . . . .

B451 3. . . . . . . . . . . . . . . . . . .

B452 3. . . . . . . . . . . . . . . . . . .

B453 3. . . . . . . . . . . . . . . . . . .

B454 3. . . . . . . . . . . . . . . . . . .

B455 3. . . . . . . . . . . . . . . . . . .

B456 3. . . . . . . . . . . . . . . . . . .

B457 3. . . . . . . . . . . . . . . . . . .

B458 3. . . . . . . . . . . . . . . . . . .

B459 3. . . . . . . . . . . . . . . . . . .

B460 3. . . . . . . . . . . . . . . . . . .

B461 3. . . . . . . . . . . . . . . . . . .

B462 3. . . . . . . . . . . . . . . . . . .

B463 3. . . . . . . . . . . . . . . . . . .

B464 Blank 3. . . . . . . . . . . . .

B51/B61 3. . . . . . . . . . . . . . .

B62 3. . . . . . . . . . . . . . . . . . . .

B63 3. . . . . . . . . . . . . . . . . . . .

B64 3. . . . . . . . . . . . . . . . . . . .

B65 3. . . . . . . . . . . . . . . . . . . .

B66 3. . . . . . . . . . . . . . . . . . . .

B71 6. . . . . . . . . . . . . . . . . . . .

B72 3. . . . . . . . . . . . . . . . . . . .

B73 0. . . . . . . . . . . . . . . . . . . .

B74 3. . . . . . . . . . . . . . . . . . . .

B75 3. . . . . . . . . . . . . . . . . . . .

B76 3. . . . . . . . . . . . . . . . . . . .

B77 3. . . . . . . . . . . . . . . . . . . .

B78 3. . . . . . . . . . . . . . . . . . . .

B79 3. . . . . . . . . . . . . . . . . . . .

B710 Blank 0. . . . . . . . . . . . .

B81 3. . . . . . . . . . . . . . . . . . . .

B82 3. . . . . . . . . . . . . . . . . . . .

B83 8. . . . . . . . . . . . . . . . . . . .

B84 3. . . . . . . . . . . . . . . . . . . .

B85 3. . . . . . . . . . . . . . . . . . . .

B86 3. . . . . . . . . . . . . . . . . . . .

B87 3. . . . . . . . . . . . . . . . . . . .

B88 3. . . . . . . . . . . . . . . . . . . .

B89 3. . . . . . . . . . . . . . . . . . . .

B810 3. . . . . . . . . . . . . . . . . . .

B811 3. . . . . . . . . . . . . . . . . . .

B812 8. . . . . . . . . . . . . . . . . . .

B813 3. . . . . . . . . . . . . . . . . . .

B814 3. . . . . . . . . . . . . . . . . . .

B815 3. . . . . . . . . . . . . . . . . . .

B816 3. . . . . . . . . . . . . . . . . . .

B817 3. . . . . . . . . . . . . . . . . . .

B818 3. . . . . . . . . . . . . . . . . . .

B819 3. . . . . . . . . . . . . . . . . . .

B820 3. . . . . . . . . . . . . . . . . . .

B821 3. . . . . . . . . . . . . . . . . . .

B822 3. . . . . . . . . . . . . . . . . . .

B823 3. . . . . . . . . . . . . . . . . . .

B824 3. . . . . . . . . . . . . . . . . . .

B825 3. . . . . . . . . . . . . . . . . . .

B826 3. . . . . . . . . . . . . . . . . . .

B827 3. . . . . . . . . . . . . . . . . . .

B828 3. . . . . . . . . . . . . . . . . . .

B829 3. . . . . . . . . . . . . . . . . . .

B830 3. . . . . . . . . . . . . . . . . . .

B831 3. . . . . . . . . . . . . . . . . . .

B832 3. . . . . . . . . . . . . . . . . . .

B833 3. . . . . . . . . . . . . . . . . . .

B834 3. . . . . . . . . . . . . . . . . . .

B835 3. . . . . . . . . . . . . . . . . . .

B836 3. . . . . . . . . . . . . . . . . . .

B837 3. . . . . . . . . . . . . . . . . . .

B838 3. . . . . . . . . . . . . . . . . . .

B839 3. . . . . . . . . . . . . . . . . . .

B840 3. . . . . . . . . . . . . . . . . . .

B841 3. . . . . . . . . . . . . . . . . . .

B842 3. . . . . . . . . . . . . . . . . . .

B843 3. . . . . . . . . . . . . . . . . . .

B844 3. . . . . . . . . . . . . . . . . . .

B845 3. . . . . . . . . . . . . . . . . . .

B846 3. . . . . . . . . . . . . . . . . . .

B847 3. . . . . . . . . . . . . . . . . . .

B848 3. . . . . . . . . . . . . . . . . . .

B849 3. . . . . . . . . . . . . . . . . . .


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B850 3. . . . . . . . . . . . . . . . . . .

B851 3. . . . . . . . . . . . . . . . . . .

B852 3. . . . . . . . . . . . . . . . . . .

B853 3. . . . . . . . . . . . . . . . . . .

B854 3. . . . . . . . . . . . . . . . . . .

B855 3. . . . . . . . . . . . . . . . . . .

B856 3. . . . . . . . . . . . . . . . . . .

B857 3. . . . . . . . . . . . . . . . . . .

B858 3. . . . . . . . . . . . . . . . . . .

B859 3. . . . . . . . . . . . . . . . . . .

B860 3. . . . . . . . . . . . . . . . . . .

B861 3. . . . . . . . . . . . . . . . . . .

B862 3. . . . . . . . . . . . . . . . . . .

B863 3. . . . . . . . . . . . . . . . . . .

B864 3. . . . . . . . . . . . . . . . . . .

B865 3. . . . . . . . . . . . . . . . . . .

B866 3. . . . . . . . . . . . . . . . . . .

B867 3. . . . . . . . . . . . . . . . . . .

B868 3. . . . . . . . . . . . . . . . . . .

B869 3. . . . . . . . . . . . . . . . . . .

B870 3. . . . . . . . . . . . . . . . . . .

B871 3. . . . . . . . . . . . . . . . . . .

B872 3. . . . . . . . . . . . . . . . . . .

B873 3. . . . . . . . . . . . . . . . . . .

B874 3. . . . . . . . . . . . . . . . . . .

B875 3. . . . . . . . . . . . . . . . . . .

B876 3. . . . . . . . . . . . . . . . . . .

B877 3. . . . . . . . . . . . . . . . . . .

B878 3. . . . . . . . . . . . . . . . . . .

B879 3. . . . . . . . . . . . . . . . . . .

B880 3. . . . . . . . . . . . . . . . . . .

B881 3. . . . . . . . . . . . . . . . . . .

B882 3. . . . . . . . . . . . . . . . . . .

B883 3. . . . . . . . . . . . . . . . . . .

B884 3. . . . . . . . . . . . . . . . . . .

B91 7. . . . . . . . . . . . . . . . . . . .

B92 Blank 7. . . . . . . . . . . . . .

B93 Deleted 7. . . . . . . . . . . . .

B94 Deleted 7. . . . . . . . . . . . .

B95 Deleted 7. . . . . . . . . . . . .

B96 Deleted 7. . . . . . . . . . . . .

B97 Deleted 7. . . . . . . . . . . . .

B98 Deleted 7. . . . . . . . . . . . .

B99 Deleted 7. . . . . . . . . . . . .

B910 Deleted 7. . . . . . . . . . . .

B911 Deleted 7. . . . . . . . . . . .

B912 Deleted 7. . . . . . . . . . . .

B913 Deleted 7. . . . . . . . . . . .

B914 Deleted 7. . . . . . . . . . . .

B915 Deleted 7. . . . . . . . . . . .

B916 Deleted 7. . . . . . . . . . . .

B917 Deleted 7. . . . . . . . . . . .

B918 Deleted 7. . . . . . . . . . . .

C11 7. . . . . . . . . . . . . . . . . . . .

C12 8. . . . . . . . . . . . . . . . . . . .

C13 7. . . . . . . . . . . . . . . . . . . .

C14 7. . . . . . . . . . . . . . . . . . . .

C15 7. . . . . . . . . . . . . . . . . . . .

C16 7. . . . . . . . . . . . . . . . . . . .

C17 7. . . . . . . . . . . . . . . . . . . .

C18 7. . . . . . . . . . . . . . . . . . . .

C19 7. . . . . . . . . . . . . . . . . . . .

C110 7. . . . . . . . . . . . . . . . . . .

C111 7. . . . . . . . . . . . . . . . . . .

C112 7. . . . . . . . . . . . . . . . . . .

C113 7. . . . . . . . . . . . . . . . . . .

C114 7. . . . . . . . . . . . . . . . . . .

C115 7. . . . . . . . . . . . . . . . . . .

C116 7. . . . . . . . . . . . . . . . . . .

C117 7. . . . . . . . . . . . . . . . . . .

C118 7. . . . . . . . . . . . . . . . . . .

C119 7. . . . . . . . . . . . . . . . . . .

C120 7. . . . . . . . . . . . . . . . . . .

C121 7. . . . . . . . . . . . . . . . . . .

C122 7. . . . . . . . . . . . . . . . . . .

C123 7. . . . . . . . . . . . . . . . . . .

C124 7. . . . . . . . . . . . . . . . . . .

C21 7. . . . . . . . . . . . . . . . . . . .

C22 7. . . . . . . . . . . . . . . . . . . .

C23 7. . . . . . . . . . . . . . . . . . . .

C24 7. . . . . . . . . . . . . . . . . . . .

C25 8. . . . . . . . . . . . . . . . . . . .

C26 8. . . . . . . . . . . . . . . . . . . .

C27 7. . . . . . . . . . . . . . . . . . . .

C28 7. . . . . . . . . . . . . . . . . . . .

C29 7. . . . . . . . . . . . . . . . . . . .

C210 7. . . . . . . . . . . . . . . . . . .

C211 7. . . . . . . . . . . . . . . . . . .

C212 7. . . . . . . . . . . . . . . . . . .

C213 7. . . . . . . . . . . . . . . . . . .

C214 7. . . . . . . . . . . . . . . . . . .

C215 7. . . . . . . . . . . . . . . . . . .

C216 7. . . . . . . . . . . . . . . . . . .

C217 7. . . . . . . . . . . . . . . . . . .

C218 7. . . . . . . . . . . . . . . . . . .

C219 7. . . . . . . . . . . . . . . . . . .

C220 7. . . . . . . . . . . . . . . . . . .

C221 7. . . . . . . . . . . . . . . . . . .

C222 7. . . . . . . . . . . . . . . . . . .

C223 7. . . . . . . . . . . . . . . . . . .

C224 7. . . . . . . . . . . . . . . . . . .

C225 7. . . . . . . . . . . . . . . . . . .

C226 7. . . . . . . . . . . . . . . . . . .

C227 7. . . . . . . . . . . . . . . . . . .

C228 8. . . . . . . . . . . . . . . . . . .

C229 8. . . . . . . . . . . . . . . . . . .

C230 7. . . . . . . . . . . . . . . . . . .

C231 7. . . . . . . . . . . . . . . . . . .

C232 Blank 7. . . . . . . . . . . . .

C31 7. . . . . . . . . . . . . . . . . . . .

C32 7. . . . . . . . . . . . . . . . . . . .

C33 7. . . . . . . . . . . . . . . . . . . .

C34 7. . . . . . . . . . . . . . . . . . . .

C35 7. . . . . . . . . . . . . . . . . . . .

C36 7. . . . . . . . . . . . . . . . . . . .

C37 7. . . . . . . . . . . . . . . . . . . .

C38 7. . . . . . . . . . . . . . . . . . . .

C39 7. . . . . . . . . . . . . . . . . . . .

C310 7. . . . . . . . . . . . . . . . . . .

C41 7. . . . . . . . . . . . . . . . . . . .

C42 7. . . . . . . . . . . . . . . . . . . .

C43 7. . . . . . . . . . . . . . . . . . . .

C44 7. . . . . . . . . . . . . . . . . . . .

C45 7. . . . . . . . . . . . . . . . . . . .

C46 7. . . . . . . . . . . . . . . . . . . .

C47 7. . . . . . . . . . . . . . . . . . . .

C48 7. . . . . . . . . . . . . . . . . . . .

C49 7. . . . . . . . . . . . . . . . . . . .

C410 7. . . . . . . . . . . . . . . . . . .

C411 7. . . . . . . . . . . . . . . . . . .

C412 7. . . . . . . . . . . . . . . . . . .

C413 7. . . . . . . . . . . . . . . . . . .

C414 7. . . . . . . . . . . . . . . . . . .

C415 7. . . . . . . . . . . . . . . . . . .

C416 7. . . . . . . . . . . . . . . . . . .

C417 7. . . . . . . . . . . . . . . . . . .

C418 7. . . . . . . . . . . . . . . . . . .

C419 7. . . . . . . . . . . . . . . . . . .

C420 7. . . . . . . . . . . . . . . . . . .

C421 7. . . . . . . . . . . . . . . . . . .

C422 7. . . . . . . . . . . . . . . . . . .

C423 7. . . . . . . . . . . . . . . . . . .

C424 7. . . . . . . . . . . . . . . . . . .

C425 7. . . . . . . . . . . . . . . . . . .

C426 7. . . . . . . . . . . . . . . . . . .

C427 7. . . . . . . . . . . . . . . . . . .

C428 7. . . . . . . . . . . . . . . . . . .

C429 7. . . . . . . . . . . . . . . . . . .

C430 7. . . . . . . . . . . . . . . . . . .

C431 7. . . . . . . . . . . . . . . . . . .

C432 7. . . . . . . . . . . . . . . . . . .

C433 7. . . . . . . . . . . . . . . . . . .

C434 7. . . . . . . . . . . . . . . . . . .

C435 7. . . . . . . . . . . . . . . . . . .

C436 7. . . . . . . . . . . . . . . . . . .

C437 7. . . . . . . . . . . . . . . . . . .

C438 7. . . . . . . . . . . . . . . . . . .

C439 7. . . . . . . . . . . . . . . . . . .

C440 7. . . . . . . . . . . . . . . . . . .

C441 7. . . . . . . . . . . . . . . . . . .

C442 7. . . . . . . . . . . . . . . . . . .

C443 7. . . . . . . . . . . . . . . . . . .

C444 7. . . . . . . . . . . . . . . . . . .

C445 7. . . . . . . . . . . . . . . . . . .

C446 7. . . . . . . . . . . . . . . . . . .


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Change 8E/(F blank)

C447 7. . . . . . . . . . . . . . . . . . .

C448 7. . . . . . . . . . . . . . . . . . .

C449 7. . . . . . . . . . . . . . . . . . .

C450 7. . . . . . . . . . . . . . . . . . .

C451 7. . . . . . . . . . . . . . . . . . .

C452 7. . . . . . . . . . . . . . . . . . .

C453 7. . . . . . . . . . . . . . . . . . .

C454 7. . . . . . . . . . . . . . . . . . .

C455 7. . . . . . . . . . . . . . . . . . .

C456 7. . . . . . . . . . . . . . . . . . .

C457 7. . . . . . . . . . . . . . . . . . .

C458 7. . . . . . . . . . . . . . . . . . .

C459 7. . . . . . . . . . . . . . . . . . .

C460 7. . . . . . . . . . . . . . . . . . .

C461 7. . . . . . . . . . . . . . . . . . .

C462 7. . . . . . . . . . . . . . . . . . .

C463 7. . . . . . . . . . . . . . . . . . .

C464 7. . . . . . . . . . . . . . . . . . .

C51/C61 7. . . . . . . . . . . . . . .

C62 7. . . . . . . . . . . . . . . . . . . .

C63 7. . . . . . . . . . . . . . . . . . . .

C64 7. . . . . . . . . . . . . . . . . . . .

C65 7. . . . . . . . . . . . . . . . . . . .

C66 7. . . . . . . . . . . . . . . . . . . .

C71 7. . . . . . . . . . . . . . . . . . . .

C72 7. . . . . . . . . . . . . . . . . . . .

C73 7. . . . . . . . . . . . . . . . . . . .

C74 7. . . . . . . . . . . . . . . . . . . .

C75 7. . . . . . . . . . . . . . . . . . . .

C76 7. . . . . . . . . . . . . . . . . . . .

C77 7. . . . . . . . . . . . . . . . . . . .

C78 7. . . . . . . . . . . . . . . . . . . .

C79 7. . . . . . . . . . . . . . . . . . . .

C710 Blank 7. . . . . . . . . . . . .

C81 7. . . . . . . . . . . . . . . . . . . .

C82 7. . . . . . . . . . . . . . . . . . . .

C83 7. . . . . . . . . . . . . . . . . . . .

C84 7. . . . . . . . . . . . . . . . . . . .

C85 8. . . . . . . . . . . . . . . . . . . .

C86 7. . . . . . . . . . . . . . . . . . . .

C87 7. . . . . . . . . . . . . . . . . . . .

C88 7. . . . . . . . . . . . . . . . . . . .

C89 7. . . . . . . . . . . . . . . . . . . .

C810 7. . . . . . . . . . . . . . . . . . .

C811 7. . . . . . . . . . . . . . . . . . .

C812 7. . . . . . . . . . . . . . . . . . .

C813 7. . . . . . . . . . . . . . . . . . .

C814 8. . . . . . . . . . . . . . . . . . .

C815 8. . . . . . . . . . . . . . . . . . .

C816 7. . . . . . . . . . . . . . . . . . .

C817 7. . . . . . . . . . . . . . . . . . .

C818 7. . . . . . . . . . . . . . . . . . .

C819 7. . . . . . . . . . . . . . . . . . .

C820 7. . . . . . . . . . . . . . . . . . .

C821 7. . . . . . . . . . . . . . . . . . .

C822 7. . . . . . . . . . . . . . . . . . .

C823 7. . . . . . . . . . . . . . . . . . .

C824 7. . . . . . . . . . . . . . . . . . .

C825 7. . . . . . . . . . . . . . . . . . .

C826 7. . . . . . . . . . . . . . . . . . .

C827 7. . . . . . . . . . . . . . . . . . .

C828 7. . . . . . . . . . . . . . . . . . .

C829 7. . . . . . . . . . . . . . . . . . .

C830 7. . . . . . . . . . . . . . . . . . .

C831 7. . . . . . . . . . . . . . . . . . .

C832 7. . . . . . . . . . . . . . . . . . .

C833 7. . . . . . . . . . . . . . . . . . .

C834 7. . . . . . . . . . . . . . . . . . .

C835 7. . . . . . . . . . . . . . . . . . .

C836 7. . . . . . . . . . . . . . . . . . .

C837 7. . . . . . . . . . . . . . . . . . .

C838 7. . . . . . . . . . . . . . . . . . .

C839 7. . . . . . . . . . . . . . . . . . .

C840 7. . . . . . . . . . . . . . . . . . .

C841 8. . . . . . . . . . . . . . . . . . .

C842 7. . . . . . . . . . . . . . . . . . .

C843 7. . . . . . . . . . . . . . . . . . .

C844 7. . . . . . . . . . . . . . . . . . .

C845 7. . . . . . . . . . . . . . . . . . .

C846 7. . . . . . . . . . . . . . . . . . .

C847 7. . . . . . . . . . . . . . . . . . .

C848 7. . . . . . . . . . . . . . . . . . .

C849 7. . . . . . . . . . . . . . . . . . .

C850 7. . . . . . . . . . . . . . . . . . .

C851 7. . . . . . . . . . . . . . . . . . .

C852 7. . . . . . . . . . . . . . . . . . .

C853 7. . . . . . . . . . . . . . . . . . .

C854 7. . . . . . . . . . . . . . . . . . .

C855 7. . . . . . . . . . . . . . . . . . .

C856 7. . . . . . . . . . . . . . . . . . .

C857 7. . . . . . . . . . . . . . . . . . .

C858 7. . . . . . . . . . . . . . . . . . .

C859 7. . . . . . . . . . . . . . . . . . .

C860 7. . . . . . . . . . . . . . . . . . .

C861 7. . . . . . . . . . . . . . . . . . .

C862 7. . . . . . . . . . . . . . . . . . .

C863 7. . . . . . . . . . . . . . . . . . .

C864 7. . . . . . . . . . . . . . . . . . .

C865 7. . . . . . . . . . . . . . . . . . .

C866 7. . . . . . . . . . . . . . . . . . .

C867 7. . . . . . . . . . . . . . . . . . .

C868 7. . . . . . . . . . . . . . . . . . .

C869 7. . . . . . . . . . . . . . . . . . .

C870 7. . . . . . . . . . . . . . . . . . .

C871 7. . . . . . . . . . . . . . . . . . .

C872 7. . . . . . . . . . . . . . . . . . .

C873 7. . . . . . . . . . . . . . . . . . .

C874 7. . . . . . . . . . . . . . . . . . .

C875 7. . . . . . . . . . . . . . . . . . .

C876 7. . . . . . . . . . . . . . . . . . .

C877 7. . . . . . . . . . . . . . . . . . .

C878 7. . . . . . . . . . . . . . . . . . .

C879 7. . . . . . . . . . . . . . . . . . .

C880 7. . . . . . . . . . . . . . . . . . .

C881 7. . . . . . . . . . . . . . . . . . .

C882 7. . . . . . . . . . . . . . . . . . .

C883 7. . . . . . . . . . . . . . . . . . .

C884 7. . . . . . . . . . . . . . . . . . .

C885 7. . . . . . . . . . . . . . . . . . .

C886 7. . . . . . . . . . . . . . . . . . .

C887 7. . . . . . . . . . . . . . . . . . .

C888 7. . . . . . . . . . . . . . . . . . .

C889 7. . . . . . . . . . . . . . . . . . .

C890 7. . . . . . . . . . . . . . . . . . .

C891 7. . . . . . . . . . . . . . . . . . .

C892 7. . . . . . . . . . . . . . . . . . .

C893 7. . . . . . . . . . . . . . . . . . .

C894 7. . . . . . . . . . . . . . . . . . .

C895 7. . . . . . . . . . . . . . . . . . .

C896 7. . . . . . . . . . . . . . . . . . .

C897 7. . . . . . . . . . . . . . . . . . .

C898 Blank 7. . . . . . . . . . . . .

C91 7. . . . . . . . . . . . . . . . . . . .

C92 Blank 7. . . . . . . . . . . . . .

T.O. GR1F16CJ11

Change 7i

TABLE OF CONTENTS

SECTION I Description and Operation T.O. GR1F16CJ1

SECTION II Normal Procedures T.O. GR1F16CJ1

SECTION III Emergency Procedures T.O. GR1F16CJ1

SECTION IV Crew Duties T.O. GR1F16CJ1

SECTION V Operating Limitations T.O. GR1F16CJ1

SECTION V Operating Limitations (Stores) T.O. GR1F16CJ12

SECTION VI Flight Characteristics T.O. GR1F16CJ1

SECTION VII Adverse Weather Operation T.O. GR1F16CJ1

GLOSSARY Standard and Nonstandard Abbreviations T.O. GR1F16CJ1

APPENDIX A Performance Data-F100PW229 A11

APPENDIX B Performance Data-F110GE129 B11

APPENDIX C Performance Data-F100PW229/CFT C11

T.O. GR1F16CJ11

iiChange 2

AIRCRAFT AND COCKPIT DESIGNATION CODES

System and/or component effectivity for a particularaircraft version/cockpit is denoted by a letter codeenclosed in a box located in the text or on an illustration. The symbols and designations are as follows:

No code-F16C and F16D aircraft

C F16C aircraft

D F16D aircraft

DF F16D aircraft, forward cockpit

DR F16D aircraft, rear cockpit

BLOCK DESIGNATION CODES/SERIALNUMBER/TAIL NUMBER CROSSREFERENCE

Refer to T.O. GR1F16CJ1 for a complete block designation codes/serial number/tail number crossreference listing.

PILOT'S RESPONSIBILITY - TO LET USKNOW

Every effort is made to keep the flight manual current. Review conferences with operating personneland a constant review of safety investigation andflight test reports assure inclusion of the latest datain the manual. Comments, corrections, and questionsregarding this manual or any phase of the flightmanual program are welcomed. These should beforwarded on AF Form 847 in accordance with AFI11215 through command headquarters to OOALC/YPVT, 6080 Gum Lane, Hill AFB, UT 840565825.

PUBLICATION DATE

The date appearing on the title page represents thecurrency of material contained herein.

AIRCRAFT MODIFICATION/RETROFITINFORMATION

Refer to T.O. GR1F16CJ1 for a complete T.O./ECPlisting.

GLOSSARY

Refer to T.O. GR1F16CJ1 for standard and nonstandard abbreviations, terms, and symbols.

T.O. GR1F16CJ11

Change 7A11

APPENDIX A

F100PW229

PERFORMANCE DATA

Part 1-Introduction A11. . . . . . . . . . . . . . . . . . . . . . . Part 2-Takeoff A21. . . . . . . . . . . . . . . . . . . . . . . . . . . . Part 3-Climb A31. . . . . . . . . . . . . . . . . . . . . . . . . . . . . Part 4-Cruise A41. . . . . . . . . . . . . . . . . . . . . . . . . . . . Part 5-Endurance A51. . . . . . . . . . . . . . . . . . . . . . . . Part 6-Descent A61. . . . . . . . . . . . . . . . . . . . . . . . . . . Part 7-Landing A71. . . . . . . . . . . . . . . . . . . . . . . . . . . Part 8-Combat A81. . . . . . . . . . . . . . . . . . . . . . . . . . . Part 9-Mission Planning A91. . . . . . . . . . . . . . . . . .

PART 1-INTRODUCTION

TABLE OF CONTENTS Page

Introduction A11. . . . . . . . . . . . . . . . . . . . . . . . . . . . . Drag Index and Configuration

Weight A12. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Position Error Correction A13. . . . . . . . . . . . . . . . . . Airspeed Conversion A14. . . . . . . . . . . . . . . . . . . . . . Compressibility Correction to

Airspeed A14. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Miscellaneous Charts A14. . . . . . . . . . . . . . . . . . . . . Angle of Attack (AOA) A14. . . . . . . . . . . . . . . . . . . . Available Load Factor A15. . . . . . . . . . . . . . . . . . . . . Turn Conversion A15. . . . . . . . . . . . . . . . . . . . . . . . . Ground Vehicle Friction

ReadingToRCR Conversion A15. . . . . . . . . . . .

LIST OF CHARTS Figure Page

Drag Indexes and Weights-Basic Aircraft A11 A16. . . . . . . . . . . . . . .

Drag Indexes and WeightsSuspension Equipment A11 A17. . . . . . .

Drag Indexes and Weights-Individual Stores A11 A18. . . . . . . . . . . .

Position Error Correction-Airspeed and Altitude A12 A113. . . . . . .

Position Error Correction-Mach Number A12 A114. . . . . . . . . . . . . .

Airspeed Conversion A13 A115. . . . . . . . . . . Compressibility Correction

to Airspeed A14 A117. . . . . . . . . . . . . . . . .

Figure Page

Standard Atmosphere A15 A118. . . . . . . . . . Temperature Correction

for Compressibility A16 A120. . . . . . . . . . Angle of Attack A17 A121. . . . . . . . . . . . . . . . Available Load Factor A18 A122. . . . . . . . . . Turn Conversion A19 A123. . . . . . . . . . . . . . Ground Vehicle Friction

ReadingToRCRConversion A110 A124. . . . . . . . . . . . . . . . .

INTRODUCTION

The data presented in the charts is applicable to aircraft equipped with an F100PW229 engine. All performance data is based on use of all approved fuels.The data covers a flight spectrum ranging from sealevel to approximately 60,000 feet and 02.0 mach.No conservative factors are used in any of the fuelconsumption data presented herein. The appendix isdivided into nine parts with performance data presented in an appropriate order for flight planning.The usage of the material requires that (except Part9) all the text be presented first followed by all thecharts. Because of the large number of stores andstores loading combinations the aircraft is capable ofcarrying, most charts are presented in a drag indexformat. All charts are based on F16 test data, exceptthe Refusal Speed charts in Part 2 and all charts inPart 7. These exceptions are based on predictedbrake performance.

T.O. GR1F16CJ11

A12Change 8

NOTE

Limiting conditions relative to altitude,airspeed, stores, gross weight, etc., arepresented in Section V and should bechecked prior to selecting missionconditions. Some charts may presentdata for more than permissible maximun weight per Section V. Such weightpresentation does not have precedenceover the limits of Section V. All data isbased on the (1962) U.S. standardatmosphere and the (1966) U.S. standard atmosphere supplements. Pressurealtitude and true mach are used for alldata unless specified otherwise.

DRAG INDEX AND CONFIGURATIONWEIGHT

Drag index is a numerical factor which provides ameans for quantifying the effects on aircraft performance of adding stores to the basic aircraft. The dragindex system provides accurate corrections for storeeffects at all subsonic speeds (less than 1.0 mach). Atsupersonic speeds (greater than 1.0 mach), the sizeand shape of the store(s) affect drag to a significantdegree, and a single value of drag index can no longerexactly represent all stores and combinations at thesespeeds. Therefore, it should be noted that actualsupersonic performance may vary from that predicted by the performance charts.

Configuration weight is intended to facilitate missionplanning by precomputing the weight of a configuration which is to be added to the aircraft operatingweight to obtain aircraft start engine weight. Configuration weight is the weight of the complete configuration which is uploaded to the basic aircraft. Theconfiguration weight includes the weight of all thestores (missiles, bombs, pods, etc.), suspension equipment, full external fuel tanks (if used), and ECM pod(if used).

The drag index and configuration weight of authorized takeoff store loadings are presented in T.O.GR1F16CJ12, STORES LIMITATIONS.

The drag indexes and weights of specific stores andsuspension equipment items are given in figure A11.If the drag index and configuration weight for a specific loading are not presented in T.O.GR1F16CJ12, STORES LIMITATIONS (i.e., normal downloads), figure A11 may be used to determine drag index and configuration weight.

NOTE

The drag index for a specific loadingaccounts for the combined effects of thestores on drag and therefore may varyslightly from the drag index computedusing figure A11.

Configuration weight for a specificloading may vary slightly from theweight computed using figure A11due to rounding.

Aircraft start engine weight is determined by addingaircraft operating weight, internal usable fuel, and, ifinstalled, ammunition, chaff/flares, and configurationweight. All these weights are given in figure A11.

The aircraft operating weight given is an approximate value and includes pilot (D 2 ), oil, oxygen,unusable fuel, and tip missile launchers. For weightand balance information, refer to the individual aircraft Form F (DD Form 3654) and the Weight andBalance Handbook. An example of the determinationof the drag index, configuration weight, and aircraftstart engine weight is provided in the sample problemwhich follows.

REFER TO FIGURE A11.

Assume a loading of four AIM9L missiles onLAU129/A launchers, two MK 84 bombs, and two370gallon fuel tanks. The drag index and configuration weight for this loading from T.O. GR1F16CJ12,STORES LIMITATIONS, are 152 and 11,777 pounds,respectively.

For this example, drag index and configurationweight are computed as follows:

STA 1 and 9 (2 AIM9L missiles on LAU129/Alaunchers)

The basic aircraft drag index includes tip missileson 16S210 missile launchers. The drag index is 1for a tip missile on a LAU129/A missile launcherand the weight of an AIM9L is 195 pounds.

For two AIM9L's on LAU129/A launchers:

Drag index = 2 1 = 2 Weight= 2 195 = 390 pounds

T.O. GR1F16CJ11

Change 7A13

STA 2 and 8 (AIM9L missiles on LAU129/A launchers + adapters)

One AIM9L has a drag index of 5 and weighs 195pounds. The drag index of a LAU129/A launcherwith adapter is 6 and the weight is 113 pounds.Since AIM9L's are carried at stations 2 and 8,multiply each drag index and weight by 2 andsum the results.

For two AIM9L's and LAU129/A launchers withadapters:

Drag index = (25) + (26) = 22 Weight = (2195) + (2113) = 616

pounds

STA 3 and 7 (MK 84 on wing weapon pylon)

The drag index of one MK 84 bomb is 9 and thebomb weight is 1970 pounds. The drag index of apylon with MAU12C/A, D/A rack at station 3 or7 is 15 and the weight is 289 pounds. Since twoMK 84 bombs are to be carried on pylons, multiplyeach drag index and weight by 2 and sum theresults.

For two MK 84's on wing weapon pylons:

Drag index =(29) + (215) = 48 Weight =(21970) + (2281) = 4502

pounds

STA 4 and 6 (370gallon fuel tanks)

In a similar manner, find that the drag index ofone 370gallon fuel tank, mounted on station 4 or6 with single stores at 3 or 7, is 35 and its weightis 531 pounds (empty) or 3047 pounds (full). Notethat no rack is required to install the tank on thewing.

For two tanks:

Drag index = 235 = 70 Weight = 23047 = 6094

pounds(full)

The total store loading drag index and configurationweight can now be determined by summing the individual store station values.

Drag IndexConfiguration

Weight

STA 1 and 9 2 390

STA 2 and 8 22 616

STA 3 and 7 48 4,502

STA 4 and 6 70 6,094

Total 142 11,602pounds

Using these values plus the basic aircraft drag indexand weights, the drag index and start engine weightcan be determined:

Drag Index

Basic aircraft drag index = 7 C

Store loading drag index = 142

Drag index total = 149

Start Engine Weight

Aircraft operating weight = 20,168 C

Internal usable fuel (JP8) = 7,116 C

Ammunition (full drum) =287 Chaff/flares (not loaded) = 0 Configuration weight =11,602

Total start engine weight = 39,173pounds

NOTE

Assumed values for basic aircraftoperating weight and drag index areused in the sample problems throughout this appendix in order to eliminatereworking the problems whenever thebasic operating weight or drag indexchanges due to modifications. Thesample problems are aids in using theappendix and are not necessarilyapplicable to specific configurations.

POSITION ERROR CORRECTION

A single nosemounted pitotstatic probe suppliesstatic and total pressure information to the CADC,altimeter, and airspeed indicator. The CADC computes calibrated airspeed, true airspeed, true mach,and calibrated altitude and provides the requiredsignals to drive the airspeed and altitude indicationson the HUD.

T.O. GR1F16CJ11

A14Change 7

The CADC provides corrected (calibrated) altitudesignals to the altimeter when the altimeter is inELECT. When the altimeter is in PNEU, it displaysindicated (not corrected for position error) altitude.The airspeed indicator always displays indicated airspeed and mach number. Position error correctionsare shown in figure A12.


Enter Position Error Correction-Airspeed andAltitude chart with desired calibrated airspeed (A),proceed vertically to desired pressure altitude lines(B), then proceed horizontally to read altitudecorrection (C) and airspeed correction (D). Subtractthe corrections from the desired conditions to obtainindication reading. Mach position error correctionsmay be found in a similar manner.

SAMPLE PROBLEM.

A. KCAS = 380

B. Pressure altitude = 30,000 feet

C. Altitude correction = 175 feet

Altimeter reading = 30,000-175 =29,825 feet

D. Airspeed correction = 1.5 knots

Airspeed indicatorreading = 380-1.5 = 378.5

knots

AIRSPEED CONVERSION

Curves shown in figure A13 are presented as an aidfor conversion between calibrated airspeed, true airspeed, and mach number. Fahrenheit/Centigradetemperature conversion is also shown.


To obtain mach numbers, enter Airspeed Conversionchart with calibrated airspeed (A). Proceed verticallyto altitude (B) and horizontally left to read machnumber (C).

To obtain KTAS, enter Airspeed Conversion chartwith calibrated airspeed (A). Proceed vertically toaltitude (B), then horizontally left to temperature (D),and then vertically upward or downward, as applicable, to read KTAS (E).

SAMPLE PROBLEM.

A. KCAS = 225

B. Altitude = 40,000 feet

C. Mach number = 0.75

D. Temperature = -40C

E. KTAS = 446

COMPRESSIBILITY CORRECTIONTO AIRSPEED

Figure A14 is provided as an aid to converting calibrated airspeed into equivalent airspeed.


Enter Compressibility Correction to Airspeed chartwith calibrated airspeed (A), proceed vertically upward to altitude (B) and proceed horizontally left toread compressibility correction (C). Note that thechart can also be entered at (B) with mach and altitude. Subtract the compressibility correction fromcalibrated airspeed to obtain equivalent airspeed.

SAMPLE PROBLEM.

A. KCAS = 300


C. Compressibilitycorrection = 15 knots

KEAS = 300-15 = 285

MISCELLANEOUS CHARTS

STANDARD ATMOSPHERE, figure A15, and TEMPERATURE CORRECTION FOR COMPRESSIBILITY, figure A16, are included for information. Nosamples are provided for these charts since they areselfexplanatory.

ANGLE OF ATTACK (AOA)

AOA data is provided in figure A17 for information.AOA data for altitudes from sea level to 60,000 feetand from 0.31.2 mach is shown.


Enter AOA chart with GW (A), proceed horizontallyto altitude (B), vertically down to mach number (C),and horizontally left to read AOA (D).

SAMPLE PROBLEM.

A. GW = 33,000 pounds


C. Mach number = 0.80

D. AOA = 4.6 degrees

T.O. GR1F16CJ11

Change 7A15

AVAILABLE LOAD FACTOR

Load factors available with the LG handle in UP andthe STORES CONFIG switch in CAT I or CAT III arepresented in figure A18. The load factor data is presented as a function of altitude, mach, and GW and isvalid for all temperatures, throttle settings, and DI.The load factor value obtained from this chart isbased solely on the aerodynamic characteristics of theaircraft. Sustained load factor capabilities are presented in Part 8.


Determine either CAT I or CAT III loading. EnterAvailable Load Factor chart with mach (A). Proceedvertically to altitude (B) and then horizontally left tothe GW baseline and parallel guidelines to GW (C).Finally, proceed left to read available load factor (D).

SAMPLE PROBLEMS (CAT I).

A. Mach = 0.6


KCAS = 275

C. GW = 23,000 pounds

D. Available loadfactor = 4.7g

A. Mach = 1.4


KCAS = 794 (obtained fromfigure A13)



SAMPLE PROBLEMS (CAT III).

A. Mach = 1.6


KCAS = 584



A. Mach = 0.5


KCAS = 184



A. Mach = 0.8

B. Altitude = Sea level

KCAS = 529 (obtained fromfigure A13)



TURN CONVERSION

Figure A19 is provided as an aid for conversionbetween load factor, turn rate, turn radius, KTAS,and bank angle.

GROUND VEHICLE FRICTION READINGTORCR CONVERSION

Figure A110 is provided as an aid for conversionbetween ground vehicle friction reading and RCR/braking action level.

T.O. GR1F16CJ11

A16Change 7

Drag Indexes and Weights Basic Aircraft

DATA BASIS FLIGHT TEST

AIRCRAFT OPERATING WEIGHT LB* F16C** F16D**

BASIC AIRCRAFT 20,200 21,400

* INCLUDES PILOT ( D 2), OIL, UNUSABLE FUEL, AND TIP MISSILE LAUNCHERS.**ALL WEIGHTS ARE APPROXIMATE. REFER TO INDIVIDUAL AIRCRAFT WEIGHT AND BALANCE HANDBOOK FOR

ACTUAL AIRCRAFT WEIGHT.

DRAG INDEX (SUBSONIC/SUPERSONIC)* F16C F16D

BASIC AIRCRAFT 7/6 11/7

*AIM9L TIP MISSILES ON 16S210 LAUNCHERS INCLUDED.

EXPENDABLES WEIGHT LB F16C F16D

INTERNAL USABLE FUEL

EXTERNAL USABLE FUEL:

300GALLON TANK

370GALLON TANK

600GALLON TANK

CHAFF/FLARES

GUN AMMO:

FULL DRUM (511 ROUNDS)

FIRED OUT (RETAINED AMMO/CASINGS, 511 ROUNDS)

JP8

7116

2040

2516

3961

48*

287

130

5874

2040

2516

3961

96**

287

130

*CHAFF/FLARE WEIGHT BASED ON 2 FULLY LOADED CHAFF MAGAZINES AND 2 FULLY LOADED FLAREMAGAZINES

**CHAFF/FLARE WEIGHT BASED ON 4 FULLY LOADED CHAFF MAGAZINES AND 4 FULLY LOADED FLAREMAGAZINES

Figure A11.(Sheet 1)

T.O. GR1F16CJ11

Change 7A17

Drag Indexes and Weights Suspension Equipment


SUSPENSION EQUIPMENT STATION

JETTISON

WEIGHT

LB

TOTAL

WEIGHT

LB

DRAG

INDEX

ADAPTER (16S301)

AIM9 LAUNCHER (16S210)AIM9 LAUNCHER (16S210) +

ADAPTER (16S301)

CENTERLINE PYLON* (16S951)

NONJETTISON (NJETT) FUEL PYLON*

LANTIRN TARGETING PODPYLON (16S1150)

LAU88/A + WEAPON PYLON*LAU88 A/A + WEAPON PYLON*

LAU117/A, A(V)1/A, A(V)3/A +WEAPON PYLON*

LAU118(V)4/A + WEAPONPYLON*

LAU129/A LAUNCHERLAU129/A LAUNCHER +

ADAPTER (16S301)

TER (16S1750) + WEAPON PYLON*TER (66J45517) + WEAPON PYLON*

WEAPON PYLON* (16S1700)

2,3,7, OR 8

1 OR 9

2,3,7, OR 8

5

4 OR 6

5R

3 OR 73 OR 7

3 OR 7

3 OR 7

1 OR 9

2,3,7, OR 8

3,4,6, OR 73,4,6, OR 7

3,4,6, OR 7

0

0

0

0

0

0

468476

130

120

0

0

117 (123**)93 (99**)

0

26

72

98

177

304

42

749757

411

401

87

113

398 (404**)374 (380**)

281

2

0

6

7

8

3

2924

20

17

1

6

2424

15

* INCLUDES MAU12C/A, D/A.**WEIGHT IF BDU33 ADAPTERS ARE INSTALLED.


T.O. GR1F16CJ11

A18Change 7

Drag Indexes and Weights Individual Stores

DATA BASIS FLIGHT TEST NOTE: WEIGHT AND DRAG INDEXES DO NOT

INCLUDE SUSPENSION EQUIPMENT.

REFER TO SHEET 2.

STORE STATION RACK

WEIGHT

LB

(EACH STORE)

DRAG

INDEX

(EACH STORE)

A/A 37U36:

TARGET STOWED 3 OR 7 PYLON 903 39

TARGET DEPLOYED 3 OR 7 PYLON - 204

TOW REEL ONLY(TARGET/CABLE RELEASED) 3 OR 7 PYLON 495 29

AGM65A, B 3 OR 7 LAU88/A, A/A, 117/A,A(V)1/A, A(V)3/A 464 13/8

AGM65D 3 OR 7 LAU88/A, A/A, 117/A,A(V)1/A, A(V)3/A 493 13/8

AGM65G 3 OR 7 LAU117/A, A(V)1/A,A(V)3/A 672 8

AGM84D1 3 OR 7 PYLON WITH HIAK 1172 10

AGM88B 3 OR 7 LAU118(V)4/A 770 8

AIM9P, P1 1 OR 9 LAUNCHER 166 4*

AIM9P2, P3, P4, P5, N, N3 1 OR 9 LAUNCHER 178 4*

AIM9L, M, S 1 OR 9 LAUNCHER 195 4*

AIM9P, P1 2,3,7, OR 8 LAUNCHER + ADAPTER 166 5

AIM9P2, P3, P4, P5, N, N3 2,3,7, OR 8 LAUNCHER + ADAPTER 178 5

AIM9L, M, S 2,3,7, OR 8 LAUNCHER + ADAPTER 195 5

AIM120B 1 OR 9 LAUNCHER 341 0

AIM120B 2,3,7, OR 8 LAUNCHER + ADAPTER 341 4

AN/ASQ:

T17 (P4A) 1 OR 92,3,7, OR 8

LAUNCHERLAUNCHER + ADAPTER

122122

2**3

T20 (P4AX) 1 OR 92,3,7, OR 8


123123

2**3

T25 (P4AM) 1 OR 92,3,7, OR 8


125125

2**3

ATM84D1 3 OR 7 PYLON WITH HIAK 117 10

*USED FOR REMOVING WINGTIP AIM9 MISSILE SINCE BASIC AIRCRAFT CONFIGURATION INCLUDES AIM9'SAT STATIONS 1 AND 9. USING DRAG INDEX ZERO GIVES SLIGHTLY CONSERVATIVE RESULTS WITHOUT TIPMISSILES.

**USED FOR REPLACING WINGTIP AIM9 MISSILE. DRAG INDEX IS 2 LESS THAN AIM9 MISSILE AT STATION 1 OR 9.


T.O. GR1F16CJ11

Change 7A19




REFER TO SHEET 2.

STORE STATION RACK

WEIGHT

LB

(EACH STORE)

DRAG

INDEX

(EACH STORE)

BDU33B/B, D/B 3,4,6, OR 7 TER 24 1

BDU50/B, A/B 3,4,6, OR 7 PYLON/TER 510 5/9

BL755 MK 2 3,4,6, OR 7 PYLON/TER 610 19/23

BLU107/B 3,4,6, OR 7 PYLON/TER 482 5/8

BLU109/B 3 OR 7 PYLON 2020 12

CATM84D2 3 OR 7 PYLON WITH HIAK 1161 10

CATM88B (WITH WINGS AND

FINS) 3 OR 7 LAU118(V)4/A 795 8

CATM88B (WITHOUT WINGS

AND FINS) 3 OR 7 LAU118(V)4/A 733 8

CATM120A (107), B (106) 1 OR 9 LAUNCHER 345 0

CATM120A (107), B (106) 2,3,7, OR 8 LAUNCHER + ADAPTER 345 4

CBU52B/BCBU58/B, A/BCBU71/B

(SUU30 H/B)3,4,6, OR 73,4,6, OR 73,4,6, OR 7

PYLON/TER

PYLON/TERPYLON/TER

785800800

20/2420/2420/24

CBU87/B (SUU65/B) 3,4,6, OR 7 PYLON/TER 950 18/22

GBU10/B, A/B, C/B, D/B, E/B, F/B 3,4,6, OR 7 PYLON 2052 15

GBU10G/B, H/B, J/B 3,4,6, OR 7 PYLON 2135 17

GBU12/B, A/B, B/B, C/B, D/B, E/B 3,4,6, OR 7 PYLON 611 7

GBU12B/B, C/B, D/B, E/B 3 OR 7 TER 611 10

GBU24/B 3,4,6, OR 7 PYLON 2306 17

GBU24A/B 3,4,6, OR 7 PYLON 2354 20

ITM88B 3 OR 7 LAU118(V)4/A 770 8

IRIST 2,3,7, OR 8 LAUNCHER + ADAPTER 198 4

LANTIRN POD:NAVIGATIONTARGETING

5L5R

PYLONPYLON

429*553

32*19

*WITH PYLON.


T.O. GR1F16CJ11

A110Change 7




REFER TO SHEET 2.

STORE STATION RACK

WEIGHT

LB

(EACH STORE)

DRAG

INDEX

(EACH STORE)

LAU3/A, B/A, C/A, D/A ROCKETLAUNCHER WITH:

(19) M151 3,4,6, OR 7 PYLON/TER 496 14/20

(19) M156 3,4,6, OR 7 PYLON/TER 496 14/20

(19) MK 1 3,4,6, OR 7 PYLON/TER 418 14/20

(19) MK 5 3,4,6, OR 7 PYLON/TER 418 14/20

FIRED OUT (NO FWD FAIRING) 3,4,6, OR 7 PYLON/TER 76 26/39

EMPTY WITH FWD FAIRING 3,4,6, OR 7 PYLON/TER 78 14/20

LAU68A/A, B/A ROCKETLAUNCHER WITH:

(7) M151 3 OR 7 TER 215 9

(7) M156 3 OR 7 TER 215 9

(7) MK 1 3 OR 7 TER 194 9

(7) MK 5 3 OR 7 TER 194 9

FIRED OUT (NO FWD FAIRING) 3 OR 7 TER 67 17

EMPTY WITH FWD FAIRING 3 OR 7 TER 68 9

LAU131/A ROCKET LAUNCHERWITH:

(7) M151 3 OR 7 TER 223 9

(7) M156 3 OR 7 TER 223 9

(7) MK 1 3 OR 7 TER 195 9

(7) MK 5 3 OR 7 TER 195 9

FIRED OUT (NO FWD FAIRING) 3 OR 7 TER 68 18

EMPTY WITH FWD FAIRING 3 OR 7 TER 69 9

LAU5003/A ROCKET LAUNCHERWITH:

(19) CM151 (CRV7)(19) RA79 (CRV7)FIRED OUT (NO FWD FAIRING)EMPTY WITH FWD FAIRING

3 OR 73 OR 73 OR 73 OR 7

TERTERTERTER

5306587678

20203920


T.O. GR1F16CJ11

Change 7A111




REFER TO SHEET 2.

STORE STATION RACK

WEIGHT

LB

(EACH STORE)

DRAG

INDEX

(EACH STORE)

M129E2 3,4,6, OR 7 PYLON 229 16

MK 20 MOD 3,4 3,4,6, OR 7 PYLON/TER 490 11/14

MK 82 AIR 3,4,6, OR 7 PYLON/TER 540 7/11

MK 82 LDGP 3,4,6, OR 7 PYLON/TER 510 5/9

MK 82 (SNAKEYE) 3,4,6, OR 7 PYLON/TER 550 7/11

MK 84 AIR 3,4,6, OR 7 PYLON 2010 10

MK 84 LDGP 3,4,6, OR 7 PYLON 1970 9

MXU648A/A, C/A (TRAVEL POD)(MAX CARGO WT IS 300 LB)

3,4,5,6, OR 7 PYLON/TER 108(EMPTY)

10/10

SUU20A/A, B/A WITH: (A/A) (B/A)

(6) BDU33B/B, D/B 3,4,6, OR 7 PYLON 474420 14

(6) MK 106 3,4,6, OR 7 PYLON 360306 14

(4) M151 3,4,6, OR 7 PYLON 414360 14

(6) BDU33B/B, D/B+(4) M151 3,4,6, OR 7 PYLON 558504 14

(6) MK 106+(4) M151 3,4,6, OR 7 PYLON 444390 14

EMPTY 3,4,6, OR 7 PYLON 330276 12

SUU5003A/A, B/A WITH:(6) BDU33B/B, D/B(6) MK 106(4) CM151 (CRV7)(6) BDU33B/B, D/B+(4) CM151(6) MK 106+(4) CM151(4) RA79T (RA82) (CRV7)EMPTY

3,4,6, OR 73,4,6, OR 73,4,6, OR 73,4,6, OR 73,4,6, OR 73,4,6, OR 73,4,6, OR 7

PYLONPYLONPYLONPYLONPYLONPYLONPYLON

(A/A) (B/A)583546469432561524705668591554547510439402

14141414141412


T.O. GR1F16CJ11

A112Change 7




REFER TO SHEET 2.

STORE STATION RACK

WEIGHT

LB

(EACH STORE)

DRAG

INDEX

(EACH STORE)

TGM65A, B 3 OR 7 LAU88/A, A/A, 117/A,A(V)1A, A(V)3/A 447 13/8

TGM65D, G 3 OR 7 LAU88/A, A/A, 117/A,A(V)1A, A(V)3/A 474 13/8

300GALLON TANK (EMPTY/FULL):

NO STORES AT 4 OR 6 5 PYLON 392*/2432 15

STORES AT 4 AND 6 5 PYLON 392*/2432 18


NO STORES AT 3 OR 7 4 OR 6 NONE 531*/3047 27

AIM9'S AT 3 OR 7 4 OR 6 NONE 531*/3047 27

SINGLE RACKS OR STORES

AT 3 OR 7 4 OR 6 NONE 531*/3047 35

MULTIPLE STORES AT 3 OR 7 4 OR 6 NONE 531*/3047 39


NO STORES AT 3 OR 7 4 OR 6 PYLON (NJETT) 399*/4360 20

AIM9'S AT 3 OR 7 4 OR 6 PYLON (NJETT) 399*/4360 20

SINGLE RACKS OR STORES

AT 3 OR 7 4 OR 6 PYLON (NJETT) 399*/4360 30

MULTIPLE STORES AT 3 OR 7 4 OR 6 PYLON (NJETT) 399*/4360 32

300/370/600GALLON TANK WEIGHTS BASED ON JP8.*INCLUDES UNUSABLE FUEL.


T.O. GR1F16CJ11

Change 7A113

1F-16X-1-1-0002A


Position Error Correction Airspeed

and Altitude

800700600500400300200100

-1000

-500

0

500

1000

-10

-5

0

5

10

ALTIT

UDE CORRECTIO

N FEET

AIR

SPEED CORRECTIO

N KNOTS

CALIBRATED AIRSPEED KNOTS

PRESSURE ALTITUDE FEET

NOTE: USE ALTITUDE CORRECTION ONLY WHEN THE ALTIMETER MODE

SELECTOR IS IN THE PNEU (SECONDARY) OPERATIONS MODE.

PRESSURE ALTITUDE FEET

NOTE: SUBTRACT CORRECTION FROM DESIRED CONDITION TO OBTAIN INDICATOR READING.

D

B

BC

A


T.O. GR1F16CJ11

A114Change 7

1F-16X-1-1-0003X


Position Error Correction Mach Number

NOTE: SUBTRACT FROM THE TRUE MACH TO OBTAIN MACH INDICATOR READING.

-0.04

-0.03

-0.02

-0.01

0

0.01

0.02

0.03

0.04

0.4 0.6 0.8 1.0 1.2 1.4 1.6

TRUE MACH NUMBER

MACH CORRECTIO

N


T.O. G

R1F1

6C

J11

Change 7

A

11

5

Airspeed Conversion

1F-16X-1-1-0004X

STD TEMP

C

ALTITUDE

1000 FT

SL

5

10

15

20

25

30

35

40

45

50

55

60 -56

-56

-56

-56

-56

-54

-44

-35

-25

-15

-5

5

15

0.4

0.5

0.6

0.7

0.8

0.9

1.0

200 300 400 500 600 100 200 300 400 500 600

CALIBRATED AIRSPEED KNOTSTRUE AIRSPEED KNOTS

M

A

C

H

N

U

M

B

E

R

A

BD

C

E

-80 -70 -60 -50 -40 -30 -20 -10 0 10 20 30 40 50 60

140120100806040200-20-40-60-80-100FAHRENHEIT

CENTIGRADE

= ( )9/5 32+

-

F

FC

C

= ( )95/ 32


T.O. G

R1F1

6C

J11

A11

6

C

hange 7

Airspeed Conversion

1F-16X-1-1-0005X

1.0

1.2

1.4

1.6

1.8

2.0

600 700 800 900 1000 1100 1200

200 300 400 500 600 700 800

M

A

C

H

N

U

M

B

E

R

TRUE AIRSPEED KNOTS



T.O. GR1F16CJ11

Change 7A117

1F-16X-1-1-0006X

Compressibility Correction to Airspeed

NOTE: EQUIVALENT AIRSPEED = CALIBRATED AIRSPEED CORRECTION.

100 200 300 400 500 600 700 800

0

10

20

30

40

50

60

70

80

90

COM

PRESSIB

ILIT

Y CORRECTIO

N KNOTS


A

BC

Figure A14.

T.O. GR1F16CJ11

A118Change 7

Standard AtmosphereDATA BASIS US STANDARD ATMOSPHERE, 1966

STANDARD SEA LEVEL AIR:

T = 59F (15C)

P = 29.921 IN. OF HG

W = 0.076475 LB/CU FT

r = 0.0023769 SLUG/CU FT

1 IN. OF HG = 70.726 LB/SQ FT

1 IN. OF HG = 0.4912 LB/SQ IN.

a = 1116.4 FT/SEC

a = 661.48 KTS

ALTITUDEDENSITY

AIR TEMPERATURESPEED OF

PRESSURE

ALTITUDE

FEET

DENSITY

RATIO

r/r 1

DEG F DEG C

SPEED OF

SOUND

KNOTSIN. OF

HG

RATIO

P/P

-2000-1000

1.05981.0296

0.97140.9855

66.13262.566

18.96216.981

665.98663.73

32.1531.02

1.07451.0368

01000200030004000

1.00000.97110.94280.91510.8881

1.00001.01481.02991.04541.0611

59.00055.43451.86848.30244.735

15.00013.01911.038

9.0577.075

661.48659.23656.92654.60652.35

29.9228.8627.8226.8225.84

1.00000.96440.92980.89620.8637

50006000700080009000

0.86170.83590.81060.78600.7620

1.07731.09381.11071.12791.1456

41.16937.60334.03730.47126.905

5.0943.1131.132

-0.849-2.831

650.04647.72645.34643.02640.71

24.9023.9823.0922.2221.39

0.83200.80140.77160.74280.7148

10,00011,00012,00013,00014,000

0.73850.71560.69320.67130.6500

1.16371.18221.20111.22051.2403

23.33819.77216.20612.640

9.074

-4.812-6.793-8.774

-10.756-12.737

638.33635.95633.63631.25628.87

20.5819.7919.0318.2917.58

0.68770.66140.63600.61130.5875

15,00016,00017,00018,00019,000

0.62920.60900.58920.56990.5511

1.26061.28151.30281.32461.3470

5.5081.941

-1.625-5.191-8.757

-14.718-16.699-18.681-20.662-22.643

626.42624.04621.59619.21616.76

16.8916.2215.5714.9414.34

0.56430.54200.52030.49940.4791

20,00021,00022,00023,00024,000

0.53280.51500.49760.48070.4642

1.37001.39351.41761.44241.4678

-12.323-15.889-19.456-23.022-26.588

-24.624-26.605-28.587-30.568-32.549

614.32611.87609.42606.91604.46

13.7513.1812.6412.1111.60

0.45950.44060.42230.40460.3876

25,00026,00027,00028,00029,000

0.44810.43250.41730.40250.3881

1.49381.52061.54801.57621.6052

-30.154-33.720-37.286-40.852-44.419

-34.530-36.511-38.492-40.473-42.455

601.95599.43596.92594.41591.89

11.1010.6310.17

9.7259.297

0.37110.35520.33980.32500.3107


T.O. GR1F16CJ11

Change 7A119

Standard AtmosphereDATA BASIS US STANDARD ATMOSPHERE, 1966

STANDARD SEA LEVEL AIR:

T = 59F (15C)

P = 29.921 IN. OF HG

W = 0.076475 LB/CU FT

r = 0.0023769 SLUG/CU FT

1 IN. OF HG = 70.726 LB/SQ FT

1 IN. OF HG = 0.4912 LB/SQ IN.

a = 1116.4 FT/SEC

a 661.48 KTS

ALTITUDEDENSITY

AIR TEMPERATURESPEED OF

PRESSURE

ALTITUDE

FEET

DENSITY

RATIO

r/r 1

DEG F DEG C

SPEED OF

SOUND

KNOTSIN. OF

HG

RATIO

P/P

30,00031,00032,00033,00034,000

0.37410.36050.34730.33450.3220

1.63491.66541.69681.72911.7623

-47.985-51.551-55.117-58.683-62.249

-44.436-46.417-48.398-50.379-52.361

589.31586.80584.22581.64579.06

8.8858.4888.1067.7377.382

0.29700.28370.27090.25860.2467

35,00036,089*37,00038,00039,000

0.30990.29710.28440.27100.2583

1.79641.83471.87531.92091.9677

-65.816-69.700-69.700-69.700-69.700

-54.342-56.500-56.500-56.500-56.500

576.41573.57573.57573.57573.57

7.0416.6836.3976.0975.811

0.23530.22340.21380.20380.1942

40,00041,00042,00043,00044,000

0.24620.23460.22360.21310.2031

2.01552.06452.11482.16622.2189

-69.700-69.700-69.700-69.700-69.700

-56.500-56.500-56.500-56.500-56.500

573.57573.57573.57573.57573.57

5.5385.2785.0304.7944.569

0.18510.17640.16810.16020.1527

45,00046,00047,00048,00049,000

0.19360.18450.17580.16760.1597

2.27282.32812.38482.44282.5022

-69.700-69.700-69.700-69.700-69.700

-56.500-56.500-56.500-56.500-56.500

573.57573.57573.57573.57573.57

4.3554.1513.9563.7703.563

0.14550.13870.13220.12600.1201

50,00051,00052,00053,00054,000

0.15220.14510.13830.13180.1256

2.56302.62542.68922.75462.8216

-69.700-69.700-69.700-69.700-69.700

-56.500-56.500-56.500-56.500-56.500

573.57573.57573.57573.57573.57

3.4253.2643.1112.9652.826

0.11450.10910.10400.099090.09444

55,00056,00057,00058,00059,000

0.11970.11410.10870.10360.09877

2.89032.96063.03263.10633.1819

-69.700-69.700-69.700-69.700-69.700

-56.500-56.500-56.500-56.500-56.500

573.57573.57573.57573.57573.57

2.6932.5672.4462.3312.222

0.090010.085780.081760.077920.07426

60,00061,00062,00063,00064,00065,000

0.094140.089720.085510.081500.077670.07403

3.25933.33863.41983.50293.58813.6754

-69.700-69.700-69.700-69.700-69.700-69.700

-56.500-56.500-56.500-56.500-56.500-56.500

573.57573.57573.57573.57573.57573.57

2.1182.0181.9241.8331.7471.665

0.070780.067460.064290.061270.058400.05566

*Tropopause


T.O. GR1F16CJ11

A120Change 7

Temperature Correction for Compressibility

1F-16X-1-1-0007A

-80 -60 -40 -20 0 20 40 60

0.2

0.4

0.6

0.8

1.0

1.2

1.4

1.6

1.8

2.0

AMBIENT TEMPERATURE C

MACH NUM

BER

TOTAL TEMPERATURE C

TEMPERATURE RECOVERY

COEFFICIENT = 1.00

NOTE:

Figure A16.

T.O. GR1F16CJ11

Change 7A121

1F-16X-1-1-0008A

Angle of AttackDATA BASIS FLIGHT TEST

LG UP ALL DRAG INDEXES 1G LEVEL FLIGHT NO THRUST EFFECTS INCLUDED

CONFIGURATION: CONDITIONS:

0

4

8

12

16

20

24

2820

30

40

AOA DEGREES

GW

1000 POUNDS

48

AB

CD

Figure A17.

T.O. GR1F16CJ11

A122Change 7

1F-16CJ-1-1-1009A

9

8

7

6

5

4

3

2

1

18 28 38 0.4 0.8 1.2

AVAILABLE LOAD FACTOR G

GW 1000 LB

BASELINE

1.6 2.0

MACH NUMBER

9

8

7

6

5

4

3

2

1

18 28 38

AVAILABLE LOAD FACTOR G

GW 1000 LB

BASELINE

0.0 0.4 0.8 1.2 1.6 2.0

0.0

CAT III

CAT I

MACH NUMBER

48

48

Available Load FactorDATA BASIS FLIGHT TEST

ALL DRAG INDEXES

LG UP

ENGINE F100-PW-229

CONDITIONS:CONFIGURATION:

NOTES:

ALL TEMPERATURES

ALL THROTTLE SETTINGS

REFER TO SECTION V FOR G LIMITATIONS.

KCAS ON 9.0G LIMITER IS INACCURATE. (REFER TO FIGURE A1-3.)

2.4

2.4

Figure A18.

03040

50

55

60

65

7071

72

73

74

75

76

77

78

79

80

81

82

83

84

1

2

3

4

5

6

7

8

9

0 10 20 30 40

TURN RADIUS 1000 FEET

L

O

A

D

F

A

C

T

O

R

G

1F-16X-1-1-0009A

B

A

N

K

A

N

G

L

E

D

E

G

R

E

E

S

TURN RATE DEGREES/SECOND

Turn Conversion

T.O. G

R1F1

6C

J11

Change 7

A

12

3 Figure A19.

T.O. GR1F16CJ11

A124Change 7

1F-16X-1-1-0001X

26

24

22

20

18

16

14

12

10

8

6

4

2

0

0.80

0.70

0.60

0.50

0.40

0.30

0.20

0.10

0

MEDIUM

MEDIUM TO POOR

GROUND

VEHICLE

FRICTION

READING

RCR/

BRAKING

ACTION

LEVEL

Ground Vehicle Friction Reading-To-RCR

Conversion

NOTES:

IN MANY AREAS, GROUND VEHICLE FRICTION READING IS THE ONLY AVAILABLE MEASURE

FOR RUNWAY BRAKING ACTION.

NORMALLY THE GROUND VEHICLE FRICTION READING, ALSO REFERRED TO AS BRAKING

ACTION COEFFICIENT, IS GIVEN AS WHOLE NUMBERS, NOT AS DECIMALS (I.E., 40 INSTEAD

OF 0.40).

MEDIUM TO GOOD

POOR

GOOD

Figure A110.

T.O. GR1F16CJ11

Change 7A21

PART 2 - TAKEOFF

TABLE OF CONTENTS Page

Takeoff Data A21. . . . . . . . . . . . . . . . . . . . . . . . . . . . . Definitions of Terms A21. . . . . . . . . . . . . . . . . . . . . . Data Basis for Charts A22. . . . . . . . . . . . . . . . . . . . . Takeoff Planning A22. . . . . . . . . . . . . . . . . . . . . . . . . Takeoff Factor A22. . . . . . . . . . . . . . . . . . . . . . . . . . . . Takeoff Speed A23. . . . . . . . . . . . . . . . . . . . . . . . . . . . Takeoff Distance A23. . . . . . . . . . . . . . . . . . . . . . . . . Acceleration Check Speed A24. . . . . . . . . . . . . . . . . Refusal Speed A24. . . . . . . . . . . . . . . . . . . . . . . . . . . . Minimum AB Blowout Speed A24. . . . . . . . . . . . . . Takeoff Roll Trim With

Asymmetric Stores A25. . . . . . . . . . . . . . . . . . . . . Takeoff and Landing Crosswind

Limits A25. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Brake Energy Limits-Maximum

Effort Braking A25. . . . . . . . . . . . . . . . . . . . . . . . .

LIST OF CHARTS Figure Page

Takeoff Factor A21 A27. . . . . . . . . . . . . . . . . Takeoff Speed A22 A28. . . . . . . . . . . . . . . . . Takeoff Distance A23 A29. . . . . . . . . . . . . . Acceleration Check

Speed A24 A210. . . . . . . . . . . . . . . . . . . . . . Refusal Speed (NonAB) A25 A211. . . . . . . . Refusal Speed (AB) A26 A214. . . . . . . . . . . . Refusal Speed With DragChute (NonAB) A27 A217. . . . . . . . . . . . . . . Refusal Speed With DragChute (AB) A28 A221. . . . . . . . . . . . . . . . . . . . Minimum AB Blowout

Speed A29 A225. . . . . . . . . . . . . . . . . . . . . . Takeoff Roll Trim With

Asymmetric Stores A210 A226. . . . . . . . . . Takeoff and Landing Cross

wind Limits A211 A227. . . . . . . . . . . . . . . . Brake Energy Limits-Max

Effort Braking A212 A228. . . . . . . . . . . . . . Safe Tire Bead Temperature-

For Quick Turnaround A213 A231. . . . . . .

TAKEOFF DATA

All data needed for takeoff planning is presented inthis section. Takeoff data is presented for MIL andMAX AB throttle settings. For the purpose of Part 2,MIL thrust is called nonAB and MAX AB thrust is

called AB. All data is based on normal flap positions(LEF's are at - 2 degrees and TEF's are at 20 degreesdown while weight is on the MLG). Rotation speed,takeoff speed, ground run distance, accelerationcheck speed, maximum refusal speed, and crosswinddata may be determined from these charts. Effects ofwind, temperature, pressure altitude, runway slopeand length, drag index, and RCR are included onappropriate charts.

DEFINITIONS OF TERMS

Takeoff factor - A computed number which is a function of engine thrust, temperature, and altitude. It isused as a control parameter for most charts in thissection.

Rotation speed - Airspeed at which rotation to liftoffattitude should be started.

Takeoff speed - Airspeed at which the main tiresleave the ground.

Takeoff ground run distance (also takeoff distance) -Ground run in feet from brake release to takeoffspeed.

Refusal speed - Maximum airspeed that can beattained and still stop on remaining runway shouldtakeoff be aborted.

Minimum AB blowout speed - Minimum airspeed atwhich an AB blowout can occur and still reach takeoffspeed within the remaining runway length usingnonAB thrust.

Runway slope - Change in runway elevation dividedby runway length multiplied by 100 (expressed in percent uphill or downhill).

Aerodynamic braking (threepoint attitude) - Use offully opened speedbrakes and maximum horizontaltail deflection (without raising nose tire from runway)to increase deceleration. (Data base for aborted takeoff.)

Maximum effort braking - A single continuous wheelbrake application using maximum pedal pressureconsistent with maintaining directional control (antiskid on) in conjunction with aerodynamic brakingand drag chute.

T.O. GR1F16CJ11

A22Change 7

DATA BASIS FOR CHARTS

Estimated aerodynamic and propulsion data basedon wind tunnel and flight test results was used to generate the information presented in this section.Changes in LEF's positions and engine bleed requirements for weight on or off LG have been accounted for,as appropriate. Assumptions and approximationsmade during the construction of each chart are discussed along with the chart.

TAKEOFF PLANNING

Careful takeoff planning is essential from a standpoint of flight safety and mission success. Properplanning will permit maximum use of the capabilityof the aircraft to take off with heavy payloads whilemaintaining adequate safety margins. Takeoff planning comprises the following:

1. Determine aircraft configuration (total aircraft takeoff GW and drag index).

2. Obtain runway conditions for expected takeofftime (pressure altitude, temperature, windspeed,wind direction, length, slope, etc.).

3. Compute appropriate data.

This information will permit decisions to be maderegarding downloading or continuing or abortingtakeoff in the event of an emergency. Each chart isdiscussed in detail in the following paragraphs. Anexample takeoff planning problem is worked in conjunction with the discussion. The following typicalaircraft and field information is normally obtainedbefore using the charts:

Takeoff GW (aircraft operatingweight plus fuel,ammo, and stores)

= 33,000 pounds (Allow forground operation fuel consumption; refer to Part 3)(Normal taxi operationsrequire approximately 25pounds of fuel per minute)

Stores loading = Two AIM9L missiles atstations 1 and 9, two MK 84bombs at stations 3 and 7,two 370gallon fuel tanksat stations 4 and 6

Takeoff CG = Refer to Weight and Balance Form F (DD Form3654)

Drag index = Refer to T.O.GR1F16CJ12, STORESLIMITATIONS

Runway pressurealtitude = 2000 feet

Runwaytemperature = 42C

Runway length = 6000 feet (available length)

Runway conditions = Dry concrete (RCR = 23)

Runway slope = 1 percent (uphill)

Runway wind = 10 knots (headwind)

TAKEOFF FACTOR

The takeoff factor concept of presenting takeoff performance is used to simplify chart presentations. Thetakeoff factor is a computed number and is commonto all charts for a given thrust setting, pressure altitude, and temperature.


Enter the chart with runway temperature (A). Proceed horizontally to pressure altitude (B) and thenvertically down to read MIL takeoff factor (C) or MAXAB takeoff factor (D).

SAMPLE PROBLEM.

A. Runway temperature = 42C

B. Pressure altitude = 2000 feet

C. MIL takeoff factor = 2.54

D. MAX AB takeoff factor = 1.44

T.O. GR1F16CJ11

Change 7A23

TAKEOFF SPEED

Takeoff and rotation speeds are obtained from figureA22.


Enter chart with takeoff GW (A), proceed verticallyto takeoff speed line (B), and proceed horizontallyleft to takeoff speed (C) for 35 percent CG. Then compute takeoff and rotation speeds for the actual takeoff CG. Next, enter inset at ambient temperature (F),proceed vertically to altitude (G), and then proceedhorizontally left to maximum allowable takeoff GW(H).

SAMPLE PROBLEM.

A. GW = 33,000 pounds

B. CG = 37.0 percent

C. Takeoff speed at 35.0percent CG = 170 KIAS

D. Takeoff speed at 37.0percent CG:170 - (0.82.0) = 168 KIAS

E. Rotation speed:

NonAB = 158 KIAS

AB = 153 KIAS

Rotation to 8 degrees pitch angle for liftoff increasestakeoff speed 8 percent.

D. Takeoff speed at 37.0percent CG:1681.08 = 181 KIAS

E. Rotation speed:

NonAB = 171 KIAS

AB = 166 KIAS

F. Ambient temperature = 40 C

G. Altitude = 4000 feet

H. Maximum allowabletakeoff GW = 44,900 pounds

The takeoff GW is within the maximum allowabletakeoff GW limit.

For a takeoff GW of 47,000 pounds:

I. GW = 47,000 pounds

J. Takeoff speed = 206 KIAS

F. Ambient temperature = 40 C

G. Altitude = 4000 Feet

H. Maximum allowabletakeoff GW = 44,900 pounds

The takeoff GW is greater than the maximum allowable takeoff GW; therefore, the MLG tire li

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