d:PROGRAM NAME: WTBAL3TCn:WEIGHT AND BALANCE CALCULATION FOR AIRCRAFT: LEAR 25 #53TCx:WRITTEN BY WALT BRUBAKER :LAST UPDATE: 04/13/88B P(),W(),F(),T(),S$(),D(),I(),M()L :POUNDS, WING MOMENT, FUSE MOMENT, TIP MOMENT 2426,-1,-1,937110 2412,-1,-1,930110 2325,895820,-1,-1 2278,877260,-1,877210 2144,825230,-1,825320, 2010,772040,-1,77290086 1876,719260,-1,720610T@ 1742,666660,-1,668240pJ 1608,614100,-1,616010T 1474,561590,-1,563900^ 1340,509740,-1,511940h 1307,-1,574430,-1r 1340,509740,-1,511940| 1206,458040,530040,460220 1072,406400,471140,408620; 938,354750,412250,357030Z 804,303110,294060,305650y 670,251920,294470,254250 536,201050,235570,202960 268,99790,117790,100710 134,49690,58890,50000:STATION NAME, DEFAULT WT., INCHES "A/C EMPTY ",8557,382.078 "CREW ", 350,217U "BAGGAGE ", 0,402r "PROVISIONS ", 5,228& "FWD PASS. ", 0,2460 "LOUNGE FWD ", 0,270: "LOUNGE MID ", 0,291D "LOUNGE REAR", 0,312N "REAR PAX #1", 0,360 X "REAR PAX #2", 0,360=b "AFT SWIVEL ", 0,327Zl "FWD SWIVEL ", 0,294uv "L TIP FUEL ",1235,0 "L WING FUEL",1162.5,0 "FUSEL FUEL ",1307,0 "R WING FUEL",1162.5,0 "R TIP FUEL ",1195,0 "N53TC: NEW, OLD, CALC? ";L "",K$% K$"n" 8 K$"o" Kx K$"c" pUl x:RESET VARIABLES TO DEFAULTS~4 X   P(X),W(X),F(X),T(X)` X X  ( S$(X),D(X),I(X) X:ASK USER FOR INPUT VALUES X  )h "####: ";D(X);6r S$(X);? K$Q K$"" 0d K$"N" w K$"O"  K$"C" pD(X)(K$)& D(X) D(X)0 Xp:COMPUTE THE MOMENTS AND REPORT:CLEAN UP ANY VALUES OVER LIMITS% D( )  D( ) I D() P D() Pi D()  D()  D() P D() P D()  D() d:FIGURE OUT FUEL ARMS BASED ON WEIGHTS IN SLIDING SCALEx X  ) D( )D() P(X) T(X)  1 XGI( ) T(X)P(X)YI() I( )j X   D()D() P(X) W(X)   XI() W(X)P(X)I() I() X   D() P(X) W(X)   XI() F(X)P(X)U:CALC INDIVIDUAL MOMENTS, SUM MOMENTS AND WEIGHTS_O i"G z, X  6M(X) D(X) I(X)@OOM(X)JGGD(X)T X^COGhA(C4)^KXm:TEST VALUES FOR EXCEEDING LIMITSo:TEST FOR PAST REAR C.G.,r A N| "%MAC= ##.# MAX=30.0";A;Z "",K$d :TEST FOR UNDER FORWARD C.G. G'  A  "%MAC=##.# MIN=8.0%";A; "",K$ :TEST FOR UNDER FORWARD C.G. & OVER 10,000 LBS.,X(G') > A X b "%MAC=##.# MIN=##.#%";A;X;n "",K$x :TEST FOR OVER GROSS WEIGHT G <   "GROSS WT=##,### MAX=15,500";G;  "",K$ :TEST FOR OVER MAX WING BENDING WEIGHT<&XG(D( )D()D()D())O0 X, Vy: "WING BEND=##,### MAX=11,400";X;N "",K$X V "GROSS WT=##,### ";G;` "",K$j "TOTAL MOMENT=##,###,##";O;t "",K$ ~ "C.G.=###.## %MAC=##.#";C;A;  "",K$.  K$"n" A  K$"o" T  K$"c" pe  X  r  S$(X);  " WT=#,### MOM=#,###,### ARM=###";D(X);M(X);I(X);  "",K$ ( K$"n"  2 K$"o"  < K$"c" p F X!P