FAR 23 LOADS

3 REM----------- ------------------------------------------

4 REM         HEADING, COPYRIGHT, MENU

5 REM----------------------------------------------------------------

8 CLEAR:CLS

10 PRINT TAB(20)"SELECT I ON OF CRITICAL LOADS ----SELECT.BAS, VERSION 
1.3"

11 PRINT TAB(25)"(C) COPYRIGHT HAL C MCMASTER 1988,1993":PRINT:PRINT

18 REM    SAMPLE INPUT FILE IS BBSELECT

19 PRINT

20 PRINT "MENU"

30 PRINT "     1. INPUT VN FLTLOAD DATA FROM DISK FILE"

40 PRINT "     2. PRINT INPUT DATA ON PAPER"

50 PRINT "     3. SELECT CRITICAL WING LOADS"

60 PRINT "     4. SELECT CRITICAL HORIZONTAL TAIL LOADS"

70 PRINT "     5. SELECT CRITICAL FUSELAGE LOADS"

80 PRINT "     6. SELECT CRITICAL VERTICAL TAIL LOADS"

100 INPUT "ENTER ACTION ITEM NUMBER FROM MENU";Z$:Z=VAL(Z$)

102 IF Z=>2 THEN INPUT "IS PRINTER READY ";QP$:QP$=LEFT$(QP$,1)

105 IF QP$="Y" THEN LPRINT CHR$(27)CHR$(78)CHR$(6):LPRINT CHR$(27)"1"

CHR$(3):QP$="N":REM TO SKIP OVER PERFORATIONS AND SET LEFT MARGIN

110 ON Z GOSUB 1000,2000,3000,5000,4000,8000

120 GOTO 20

990 REM----------------------------------------------------------

991 REM          INPUT BALANCED FLTLOADS FROM DISK

992 REM-------------------------------------------- -----------

1000 PRINT "SUBROUTINE TO INPUT VN FLIGHT DATA FROM DISK FILE"

1010 INPUT "WHAT IS NAME OF DATA FILE YOU WANT TO INPUT" ; FLTDAT$

1011 REM   SAMPLE INPUT FILE IS SEL2ALT

1012 INPUT "WHAT DISK DRIVE IS IT IN (A: B: OR C:) ";DSK$

1014 FLTDAT$=DSK$+FLTDAT$

1020 OPEN "I",1,FLTDAT$

1030 INPUT ftl.DB,LEVEL,ICONFIG,MAC,XT,XW,ZW,S,NP

1035 DIM CND$(DB),V(DB),NZ(DB),PAL(DB),G(DB).CL(DB),LZW(DB),LT(DB),DX

(DB),KCNF$(DB),CG$(DB),ALT(DB),CASE(DB),W(DB),XXCG(DB)

1040 FOR 1=1 TO DB

1050 INPUTH,CND$(I),V(I),NZ(I),PAL(I),G(I),CL(I),LZW(I),LT(I),DX(I),

KCNF$(I),CG$(I),ALT(I),W(I),XXCG(I)

1060 CASE(I)=I

1070 NEXT

1080 CLOSE 1

1090 RETURN

1990 REM------------------------------------------------------

1991 REM         PRINT INPUT ON PAPER

1992 REM-- -------------------------------------------------------

2000 PRINT "SUBROUTINE TO PRINT INPUT DATA ON PAPER"

2005 HEAD$= "CASE CONDITION V KEAS     NZ ALPHAWL GCORR      CL LZ

WING LZTAIL     DX"

2007 P$="ftft# \       \ ft^.ftft +#.## +#ft.^ #.### +#.W +W#ft

+#W +####"

2010 LPRINT "CRUISE CONFIGURATION AT SEA LEVEL" 
2020 LPRINT "FOR CG1" 
2030 FOR 1=1 TO DB

2040 IF I>1 AND KCNF$(I)<>KCNF$(1-1) THEN LPRINT KCNF$(I);" AT ";ALT( 
I);" FEET"

196

 SELECTION OF CRITICAL LOADS

2050 IF I>1 AND CG$(I)<>CG$(I-1) THEN LPRINT "FOR ";CG$(I):LPRINT HEA

D$

2060 LPRINT USING P$ ; CASE( I ) , CND$ (I ) , V( I ) , NZ ( I )., PAL( I ) , G( I ) , CL( I ) , LZW

(I),LT(I),DX(I)

2070 NEXT

2090 RETURN

2990 REM-------------------------------------------------------------

2991 REM SEARCH FOR CRITICAL WING LOADS

2992 REM-------------------------------------------------------------

3000 PRINT "SUBROUTINE TO SEARCH FOR CRITICAL WING LOADS"

3005 REM

3006 REM

3010 PRINT "NOW SEARCHING ALL PHAA CONDITIONS FOR LARGEST RESULTANT A

IRLOAD ---IE SQR(LZW"2+DWX~2)"

3020 PHAA=0

3030 FOR 1=1 TO DB

3040 IF CND$(I )=" STALL +N" OR CND$(I)="MAN A" THEN R1PHAA=SQR(LZW(I)~

2+DX(I)~2)

3050 IF R1PHAA>PHAA THEN PHAA=R1PHAA:HCASE=I

3070 NEXT

3075 REM

3076 REM

3080 PRINT "NOW SEARCHING ALL PLAA CONDITIONS FOR LARGEST RESULTANT A

IRLOAD"

3090 PLAA=0

3100 FOR 1=1 TO DB

3110 IF CND$(I)="MAN D" OR CND$="GUST D" THEN R2PLAA=SQR( LZW( I) "2+DX (

I)"2)

3120 IF R2PLAA>PLAA THEN PLAA=R2PLAA:LCASE=I

3140 NEXT

3145 REM

3146 REM

3150 PRINT "NOW SEARCHING ALL PMAA CONDITIONS FOR LARGEST LOAD"

3160 PMAA=0

3170 FOR 1=1 TO DB

3180 IF CND$(I)="MAN C" OR CND$(I)="GUST +C" THEN R3PMAA=LZW(I)

3190 IF R3PMAA>PMAA THEN PMAA=R3PMAA:MCASE=I

3200 NEXT

3280 REM

3281 REM

3290 PRINT "NOW SEARCHING ALL ACCELERATED ROLL CONDITIONS FOR MAXIMUM

LZW"

3300 ACROLL=0

3310 FOR 1=1 TO DB

3320 IF CND$(I)="AC ROLL" OR CND$(I)="ACC ROLL" AND LZW( I) >ACROLL THE 
N ACROLL=LZW(I):XCASE=I

3340 NEXT

3345 REM

3346 REM

3350 PRINT "NOW SEARCHING ALL STEADY ROLL CONDITIONS FOR LARGEST WING 
TORSION"

3351 LPRINT TAB( 25 ) "CRITICAL LOAD SUMMARY" : LPRINT TAB( 25 )"------ --

3352 LPRINT "INPUT FOR WING":LPRINT "--- --- ---":LPRINT

197

FAR 23 LOADS

3355 INPUT "ENTER FULL DOWN AILERON DEFLECTION";DNAIL$:DN=VAL(DNAIL$)

3360 IF DN<0 OR DN>50 THEN 3355

3362 LPRINT "FULL DOWN AILERON DEFLECTION, DEG = ";DN

3365 INPUT "ENTER AIRFOIL SECTION MOMENT COEFFICIENT FOR NO AILERON D

EFLECTION";CM$:CM=VAL(CM$)

3370 IF CM<-1 OR CM>1 THEN 3365

3371 LPRINT "AIRFOIL PITCHING MOMENT COEFFICIENT WITH NO AILERON DEFL 
ECTION = ";CM

3372 NH=1:ALT(1)=0 
3374 FOR 1=2 TO DB

3376 IF ALT(I)OALT(I-1) THEN NH=NH+1:H(NH)=ALT(I) 
3378 NEXT I

3381 LPRINT "ALTITUDES ARE ";

3382 FOR L=1 TO LEVEL:LPRINT H(L);"  ";:NEXT L

3383 LPRINT

3384 FOR J=1 TO LEVEL

3385 FOR 1=1 TO DB

3390 IF CND$(I)0"ST ROL A" AND CND$ (I ) 0 "ST ROL C" AND CND$(I)0"ST

ROL D" THEN 3407

3395 IF CND$(I)="ST ROL A" AND ALT(I)=H(J) THEN VA(J)=V(I)

3400 IF CND$(I)="ST ROL C" AND ALT(I)=H(J) THEN VC(J)=V(I)

3405 IF CND$(I)="ST ROL D" AND ALT(I)=H(J) THEN VD(J)=V(I)

3407 NEXT I

3410 DA(J)=DN:DC(J)=VA(J)/VC(J)*DN:DD(J)=.5 *VA(J)/VD(J)*DN

3420 NEXT J

3425 TMIN=0

3430 FOR J=1 TO LEVEL

3435 FOR 1=1 TO DB

3440 IF CND$(I)0"ST ROL A" AND CND$(I)0"ST ROL C" AND CND$(I)0"ST

ROL D" THEN 3465

3445 IF CND$(I)="ST ROL A" AND ALT(I)=H(J) THEN  TA=(CM-.01*DA(J))*G(

I)*V(I)~2

3450 IF CND$(I)="ST ROL C" AND ALT(I)=H(J) THEN TA=(CM-.01*DC(J))*G(I

)*V(I)-2

3455 IF CND$(I)="ST ROL D" AND ALT(I)=H(J) THEN TA=(CM-.01*DD(J))*G(I

)*V(I)-2

3460 IF TA<TMIN THEN TMIN=TA:TCASE=I

3465 NEXT I,J

3490 REM

3491 REM

3500 PRINT "NOW PRINTING CRITICAL WING LOAD SUMMARY"

3510 LPRINT:LPRINT "CRITICAL WING LOADS":LPRINT --------- ---- ------

3511 LPRINT "   CASE ANGLE    CL    V KEAS  CONFIG     CG     ALT 
COND     FAR       "

3512 WING$="   #W  \  \  +#.M  ##ft.##  \     \  \   \  ##^#  \

\  \            \" 
3520 LPRINT USING WING$;HCASE;"PHAA";CL(HCASE);V(HCASE);KCNF$(HCASE) ;

CG$(HCASE);ALT(HCASE);CND$(HCASE);"23.333(b)"

3525 LPRINT USING WING$;LCASE;"PLAA";CL(LCASE);V(LCASE);KCNF$(LCASE);

CG$(LCASE);ALT(LCASE);CND$(LCASE);"23.333(b)"

3530 LPRINT USING WING$;MCASE;"PMAA";CL(MCASE);V(MCASE);KCNF$(MCASE);

CG$(MCASE);ALT(MCASE);CND$(MCASE);"23.333(c)OR(b)"

3540 LPRINT USING WING$;XCASE;"ACRL";CL(XCASE);V(XCASE);KCNF$(XCASE);

CG$(XCASE);ALT(XCASE);CND$(XCASE);"23.349(a)(2)"

198

 SELECTION OF CRITICAL LOADS

3550 LPRINT USING WING$;TCASE;"TORS";CL(TCASE);V(TCASE);KCNF$(TCASE};

CG$CTCASE);ALT(TCASE);CND$(TCASE);"23.349(b)"

3560 RETURN

3990 REM-------------------------------------------------------------

3991 REM          CRITICAL FUSELAGE LOADS

3992 REM--------------------------------------------------------------

4000 PRINT "SUBROUTINE TO SELECT CRITICAL FUSELAGE LOADS"

4010 PRINT "THIS SUBROUTINE MUST BE RUN AFTER MENU ITEM 4 HORIZONTAL

TAIL LOADS."

4011 INPUT "HAVE YOU RUN MENU ITEM 4 HORIZONTAL TAIL LOADS? ";HT$:HT$ 
=LEFT$(HT$,1)

4012 IF HT$0"Y" THEN 4990: REM   RETURN

4020 INPUT "IS ENGINE(S) MOUNTED ON NOSE OF FUSELAGE, WING OR AFT FUS

ELAGE (N W OR A)? ";EM$

4030 IF EM$0"N" AND EM$0"W" AND EM$0"A" THEN 4020

4040 PRINT: PRINT "NOW SEARCHING FOR THE LARGEST + & - VERTICAL FUSEL

AGE LOADS REACTED BY THE WING"

4050 PRINT "THESE COULD PRODUCE THE LARGEST VERTICAL SHEARS AFT OF TH

E MOST AFT WING ATTACH POINT OR FORWARD OF THE MOST FORWARD WING ATTA

CH POINT OR BOTH."

4060 VSMAX=-100000!:VSMIN=100000!

4070 INPUT "WHAT IS WING WEIGHT OR PRESS ENTER FOR DEFAULT OF .09 X G

ROSS WEIGHT ";WW$

4075 W^W(l)

4080 IF WW$="" THEN WW=9.000001E-02*W ELSE WW=VAL(WW$)

4090 FOR 1=1 TO DB

4100 VSHEAR=LZW(I)-NZ(I)*WW

4110 IF VSHEAR>VSMAX THEN VSMAX=VSHEAR:VSMAXCASE=I

4120 IF VSHEAR<VSMIN THEN VSMIN=VSHEAR:VSMINCASE^I

4130 NEXT I

4200 PRINT:PRINT "NOW SEARCHING FOR THE LARGEST PRODUCT OF BALANCING

TAIL LOAD AND VERTICAL FUSELAGE LOAD REACTED BY THE WING."

4210 PRINT "THESE COULD PRODUCE THE LARGEST BENDING MOMENTS ON THE AF

T FUSELAGE."

4215 PRINT "THEY COULD PRODUCE THE LARGEST BENDING MOMENTS ALSO IN TH

E FORWARD FUSELAGE SINCE THE FORWARD FUSELAGE BALANCES THE AFT FUSEL

AGE BENDING WITH SOME HELP FROM WING TORSION"

4220 BMMAX=-10000000ft:BMMIN=10000000ft

4230 FOR 1=1 TO DB

4240 PROD=-CLZW(I)-NZ(I)*WW)*LT(I)

4250 IF PROD>BMMAX AND SGN(NZ (I ) ) =+1 THEN BMMAX=PROD :BMMAXCASE=I

4260 IF PROD<BMMIN AND SGN(NZ(I))=-! THEN BMMIN=PROD:BMMINCASE=I

4270 NEXT I

4280 CLS:PRINT "NOW WORKING ON FUSELAGE LOADS DUE TO PITCHING CONDITI

ONS"

4300 PRINT: PRINT "THE AFT FUSELAGE MAY BE CRITICAL FOR DOWN BENDING

DUE TO UNCHECKED PULL-UP MANEUVER (DOWN TAIL LOAD) FOR AIRPLANES WITH

ENGINES MOUNTED ON THE NOSE OR WING. " 
4310 PRINT "THE DOWN LOAD ON THE HORIZONTAL TAIL MAY BE CARRIED FORWA 
RD TO THE WING ATTACH POINTS, ASSUMING THE FUSELAGE LOAD FACTOR TO BE

ZERO."

4315 PRINT "HOWEVER, THE LINEAR AND INERTIA FORCES MAY BE TAKEN INTO 
ACCOUNT IF DESIRED." 
4320 PRINT "THE MOMENT AT THE WING NEED NOT BE BALANCED WITH TORSION

199

FAR 23 LOADS

AT THE WING ATTACH POINTS. REF CAM 3.216-2 POLICY "

4325 PRINT "THE AFT FUSELAGE IS NOT CRITICAL FOR UNCHECKED PULL-UP MA

NEUVER FOR  AIRPLANES WITH ENGINES MOUNTED ON THE AFT FUSELAGE DUE TO

THE RELIEVING PITCHING INERTIA OF THE ENGINE." 
4330 PRINT: PRINT "THE UNCHECKED PUSH DOWN MANEUVER (UP TAIL LOAD) IS

CRITICAL FOR THE AFT FUSELAGE ONLY AT THE ATTACHMENT OF THE HORIZONT 
AL TAIL TO THE FUSELAGE AND THE LOCAL FUSELAGE MEMBERS. REF CAM 3.216 
-3 POLICY"

4340 PRINT:PRINT "THE CHECKED MANEUVERS ARE LIKELY TO BE CRITICAL ONL 
Y AT VP AND VD. THE CHECKED MANEUVER CONDITIONS AT VP ARE COVERED BY 
THE UNCHECKED MANEUVER CONDITIONS AND NEED NOT BE INVESTIGATED." 
4400 PRINT:PRINT "NOW SEARCHING FOR LARGEST VERTICAL LOAD INERTIA" 
4410 NZMAX=-10 
4420 FOR 1=1 TO DB

4430 IF NZ(I)>NZMAX THEN NZMAX=NZ(I):NZMAXCASE=I 
4440 NEXT I

4500 PRINT:PRINT "ROUTINE TO PRINT OUT CRITICAL FUSELAGE LOADS" 
4510 LPRINT CHR$(12)

4520 LPRINT "CRITICAL FUSELAGE LOADS" 
4530 LPRINT --------- -------- ------

4540 LPRINT:LPRINT "MAXIMUM TOTAL FUSELAGE LOAD ACTING DOWN ON WING F 
OR BALANCED AIRPLANE"

4550 LPRINT TAB(5)"TOTAL FUSELAGE DOWN LOAD ACTING ON WING = ";VSMAX

4551 LPRINT TAB(5)"NZ = ";NZ(VSMAXCASE)

4552 LPRINT TAB(5)"TAIL LOAD = ";LT(VSMAXCASE)

4553 LPRINT TAB(5)"CONDITION = ";CND$(VSMAXCASE)

4560 LPRINT TAB(5)"CASE NUMBER = ";VSMAXCASE

4570 LPRINT TAB(5)"THIS CONDITION MAY BE CRITICAL FOR DOWN SHEAR JUST

AFT OF THE REAR WING"

4580 LPRINT TAB(5)"ATTACHMENT OR JUST FORWARD OF THE FORWARD WING ATT 
ACHMENT OR BOTH"

4590 LPRINT TAB(5)"THIS IS PROBABLY THE MOST CRITICAL AFT FUSELAGE DO 
WN BENDING AND SHEAR"

4595 LPRINT TAB(5)"CONDITION FOR AFT MOUNTED ENGINE CONFIGURATION" 
4600 LPRINT:LPRINT "MAXIMUM AFT FUSELAGE DOWN BENDING FOR BALANCED CO 
NDITIONS"

4602 LPRINT TAB(5)"TOTAL FUSELAGE DOWN LOAD ACTING ON WING = ";LZW(BM 
MAXCASE)-NZ(BMMAXCASE)*WW

4604 LPRINT TAB(5)"CONDITION = ";CND$(BMMAXCASE) 
4606 LPRINT TAB(5)"CASE NUMBER = ";BMMAXCASE 
4610 LPRINT TAB(5)"TAIL LOAD = ";LT(BMMAXCASE) 
4620 LPRINT TAB(5)"NZ = ";NZ(BMMAXCASE) 
4630 LPRINT:LPRINT "MAXIMUM AFT FUSELAGE UP BENDING FOR BALANCED COND 
ITIONS"

4642 LPRINT TAB(5)"TOTAL FUSELAGE LOAD ACTING ON WING = ";LZW(BMMINCA 
SE)-NZ(BMMINCASE)*WW

4644 LPRINT TAB(5)"CONDITION = ";CND$(BMMINCASE) 
4646 LPRINT TAB(5)"CASE NUMBER = ";BMMINCASE 
4648 LPRINT TAB(5)"TAIL LOAD = ";LT(BMMINCASE) 
4650 LPRINT TAB(5)"NZ = ";NZ(BMMINCASE) 
4660 LPRINT:LPRINT "UNCHECKED PULL UP MANEUVER (DOWN TAIL LOAD)" 
4670 LPRINT TAB(5)"BALANCED DOWN TAIL LOAD = ";LT(H5CASE)

4672 LPRINT TAB(5)"UNBALANCED INCREMENT OF TAIL LOAD = ";UNBAL1

4673 LPRINT TAB(5)"TOTAL TAIL LOAD = ";U1CK

200

SELECTION OF CRITICAL LOADS

4674 LPRINT TAB(5)"XCG = ";XXCG(H5CASE)

4675 LPRINT TAB(5)"FS 20 PERCENT HORIZ TAIL = ";XT20

4676 LPRINT TAB(5)"UNBALANCED MOMENT ABOUT CG = ";UNBALMOMUNCK

4680 LPRINT TAB(5)"SEE HORIZONTAL TAIL LOADS FOR FURTHER DATA"

4681 LPRINT:LPRINT "CHECKED PULL UP MANEUVER (DOWN TAIL LOAD)"

4682 LPRINT TAB(5)"BALANCED DOWN TAIL LOAD = ";LT(H7CASE)

4683 LPRINT TAB(5)"UNBALANCED INCREMENT OF TAIL LOAD = ";I7CK

4684 LPRINT TAB(5)"TOTAL TAIL LOAD = ";L7MIN

4685 LPRINT TAB(5)"XCG = ";XCGDNCK

4686 LPRINT TAB(5)"FS 20 PERCENT HORIZ TAIL = ";XT20

4687 LPRINT TAB(5)"UNBALANCED MOMENT ABOUT CG = " ;UNBALMOMDNCK

4688 LPRINT TAB(5)"SEE HORIZONTAL TAIL LOADS FOR FURTHER DATA"

4700 LPRINT:LPRINT "LANDING CONDITIONS"

4710 LPRINT TAB(5)"FORWARD FUSELAGE IS CRITICAL FOR UP BENDING FOR 3 
WHEEL LEVEL LANDING"

4720 LPRINT TAB(5)"FORWARD FUSELAGE MAY BE CRITICAL FOR DOWN BENDING 
FOR 2 WHEEL LEVEL LANDING"

4800 LPRINT:LPRINT "GREATEST VERTICAL INERTIA FACTOR FOR CONCENTRATED

WEIGHT INSTALLATIONS"

4810 LPRINT TAB(5)"NZ = ";NZ(NZMAXCASE)

 LPRINT TAB(5)"CASE NUMBER = ";NZMAXCASE

 LPRINT TAB(5)"CONDITION = ";CND$(NZMAXCASE)

 LPRINT TAB(5)"BALANCING TAIL LOAD = ";LT(NZMAXCASE)

 COND$=LEFT$(CND$(NZMAXCASE),4)

 IF COND$="GUST" THEN LPRINT TAB(5)"PITCHING ACCELERATION WILL AD

 VERTICAL INERTIA FORWARD OF CG"

 RETURN

 REM--------------------------------------------------------------

 REM          SELECT CRITICAL HORIZONTAL TAIL LOADS

 REM------------- ------------------------------------------

PRINT "SUBROUTINE TO SELECT CRITICAL HORIZONTAL TAIL LOADS"

REM

REM

PRINT "NOW SEARCHING ALL CONDITIONS FOR LARGEST BALANCING TAIL L

4820 
4830 
4840 
4850 
4860 
D TO 
4900

4990

4991

4992 
5000

5005

5006 
5010 
OADS 
5020 
5030 
5032 
5034 
5040 
E=I 
5050 
E=I 
5060 
THEN 
5070 
THEN 
5080

5090

5091 
5100 
V=VA

5110

5111

LITMAX=-10000 :L2TMIN= 10000 :L3TFMAX=-10000 :L4TFMIN= 10000

FOR 1=1 TO DB

GG$=LEFT$(CND$,4)

IF GG$="GUST" THEN 5080

IF KCNF$(1)0"LANDING" AND LT(I)>L1TMAX THEN L1TMAX=LT(I):H1TCAS

IF KCNF$(!)<>"LANDING" AND LT(I)<L2TMIN THEN L2TMIN=LT(I):H2TCAS

IF KCNF$(I)="LANDING" AND CND$(I)0"LEV LAND" AND LT(I)>L3TFMAX

L3TFMAX= LT(I):H3TCASE=I

IF KCNF$(I)="LANDING" AND CND$(I)0"LEV LAND" AND LT(I)<L4TFMIN

L4TFMIN=LT(I):H4TCASE=I

NEXT

REM

REM

PRINT "NOW SEARCHING ALL FLAPS RETRACTED CONDITIONS AT NZ=1 AND

FOR LARGEST UNCHECKED MANEUVER TAIL LOADS"

U1CK=100000!:U2CK=-100000!:UNBAL1=100000!:UNBAL2=-100000!

LPRINT CHR$(12)

201

FAR 23 LOADS

5112 LPRINT "INPUT FOR HORIZONTAL TAIL":LPRINT "

5113 XT20=XT:LPRINT "FS 20 PERCENT MAC OF HORIZONTAL TAIL = ";XT20

5115 INPUT "ENTER HORIZONTAL TAIL AREA IN SQR FT";ST

5116 LPRINT "WING AREA, SQR FT = ";S

5117 LPRINT "HORIZONTAL TAIL AREA, SOR FT = ";ST

5120 INPUT "ENTER FULL ELEVATOR DEFLECTIONS FOR UP TRAILING EDGE AND 
DOWN TRAILING EDGE";EUP,EDN:EUP=ABS(EUP):EDN=ABS(EDN)

5121 LPRINT "FULL TRAILING EDGE UP ELEVATOR DEFLECTION = ";EUP

5123 LPRINT "FULL TRAILING EDGE DOWN ELEVATOR DEFLECTION, DEG = " ; EDN

5130 N=NP

5131 LPRINT "AIRPLANE MANEUVER LOAD FACTOR = ";N

5140 FOR 1=1 TO DB

5145 IF CND$(I)o"BAL A" THEN 5280

5150 IF CND$(I)="BAL A" THEN W=W(I)

5160 IF CND$(I)="BAL A" AND EUP=<10 THEN W1BAR=.55*N*W/S/1.5

5170 IF CND$(I)="BAL A" AND EUP=>30 THEN W1BAR=.8*N*W/S/1.5

5180 IF CND$(I)="BAL A" AND EUP>10 AND EUP<20 THEN W1BAR=(.55+(.7-.55

)*(EUP-10))*N*W/S/1.5

5190 IF CND$(I)="BAL A" AND EUP=>20 AND EUP<30 THEN W1BAR=(.7+(.8-.7)

*(EUP-20)/(30-20))*N*W/S/1.5

5200 LUPCK=-W1BAR*ST:UNBALUPTE=LUPCK-LT(I)

5210 IF LUPCK<U1CK THEN U1CK=LUPCK:H5CASE=I

5211 IF LUPCK=U1CK AND UNBALUPTE<UNBAL1 THEN U1CK=LUPCK:H5CASE=I:UNBA

L1=UNBALUPTE

5220 IF CND$(I)="BAL A" AND EDN=<10 THEN W2BAR=.55*N*W/S/1.5

5230 IF CND$(I)="BAL A" AND EDN=>30 THEN W2BAR=.8*N*W/S/1.5

5240 IF CND$(I)="BAL A" AND EDN>10 AND EDN<20 THEN W2BAR=(.55+(.7-.55

)*(EDN-10)/(20-10))*N*W/S/1.5

5250 IF CND$(I)="BAL A" AND EDN=>20 AND EDN<30 THEN W2BAR=(.7+(.8-.7)

*(EDN-20)/(30-20))*N*W/S/1.5

5260 LDNCK=+W2BAR*ST:UNBALDNTE=LDNCK-LT(I)

5270 IF LDNCK>U2CK THEN U2CK=LDNCK:H6CASE=I

5271 IF LDNCK=U2CK AND UNBALDNTE>UNBAL2 THEN U2CK=LDNCK:H6CASE=I:UNBA 
L2=UNBALDNTE 
5280 NEXT

5284 XARM5=XT20-XXCG(H5CASE)

5285 UNBALMOMUNCK=XARM5*UNBAL1

5290 REM

5291 REM

5300 PRINT "NOW SEARCHING ALL FLAPS RETRACTED CONDITIONS IN WHICH NZ= 
1 AND V=VC OR V=VD FOR LARGEST CHECKED MANEUVER DOWN TAIL LOAD" 
5305 L7MIN=100000!

5310 INPUT "ENTER LENGTH OF AIRPLANE IN FEET";LF$:LF=VAL(LF$):IF LF<0 
OR LF>100 THEN 5310

5314 FOR 1=1 TO DB

5315 IF CND$(I)0"BAL C" AND CND$( I ) <> "BAL D" THEN 5380

5325 IF CND$(I)="BAL C" OR CND$="BAL D" THEN W=W(I)

5330 IYY=W*LF~2/32.2/12:REM INERTIA ABOUT CG FOR LEVEL WEIGHT DISTRIB

UTION

5335 IYY=IYY*.44:REM INERTIA FOR TYPICAL WEIGHT DISTRIBUTION OF FAR 2

3 AIRPLANES

5340 THETADOT=39*N*(N-1.5)/V(I )

5350 L5T=IYY*THETADOT/((XT20-XXCG(I))/12)

202

SELECTION OF CRITICAL LOADS

5360 L6CK=LT(I)-L5T

5370 IF L6CK<L7MIN THEN L7MIN=L6CK:H7CASE=I:B7CK=LT(I):I7CK=-L5T:XCGD

NCK=XXCG(I)

5380 NEXT

5381 I=H7CASE

5383 XDNCKARM=XT20-XXCG(I)

5384 UNBALMOMDNCK=XDNCKARM*I7CK

5385 LPRINT "LENGTH OF AIRPLANE, FT = ";LF

5395 REM

5396 REM

5400 PRINT "NOW SEARCHING ALL FLAPS RETRACTED CONDITIONS IN WHICH NZ=

N AND V=VC OR V=VD FOR LARGEST CHECKED MANEUVER UP LOAD"

5410 L8MAX=-100000!

5412 FOR 1=1 TO DB

5414 IF CND$(I)0"MAN C" AND CND$ (I ) 0 "MAN D" THEN 5490

5440 IYY=W*LF-2/(32.2*12):REM INERTIA ABOUT CG FOR LEVEL WEIGHT DIST

RIBUTION

5445 IYY=IYY*.44:REM INERTIA FOR TYPICAL WEIGHT DISTRIBUTION OF FAR 2

3 AIRPLANES

5450 THETADOT=39*N*(N-1.5)/V(I)

5460 L9T=IYY*THETADOT/(XT20-XXCG(I))*12

5470 LOUNCK=LT(I)+L9T

5480 IF LOUNCK>L8MAX THEN L8MAX=LOUNCK:H8CASE=I:B8UNCK=LT(I):I8UNCK=L

9T:XCGUPUNCK=XXCG(I)

5490 NEXT

5495 REM

5496 REM

5500 PRINT "NOW SEARCHING FOR ALL GUST CONDITIONS WITH FLAPS RETRACTE 
D FOR LARGEST GUST TAIL LOADS"

5510 G1MAX=-100000!:G2MIN=100000!

5512 INPUT "ENTER SLOPE OF LIFT CURVE OF HORIZONTAL TAIL TAIL, CL/RAD 
";AT

5513 INPUT "ENTER SLOPE OF LIFT CURVE OF WING, CL/RAD";AW

5514 INPUT "ENTER ASPECT RATIO OF WING";ARW

5516 LPRINT "SLOPE OF LIFT CURVE OF HORIZONTAL TAIL, CL/RAD = ";AT

5517 LPRINT "SLOPE OF LIFT CURVE OF WING, CL/RAD = ";AW

5518 LPRINT "ASPECT RATIO OF WING = ";ARW

5519 LPRINT "MAC OF WING, FT = ";MAC/12

5520 FOR 1=1 TO DB

5530 IF CND$(I)="BAL C" OR CND$(I)="BAL D" THEN W=W(I) ELSE 5640

5540 IF CND$(I)="BAL C" THEN UDE= 50

5550 IF CND$(I)="BAL D" THEN UDE=25

5560 IF ALT>20000 THEN UDE=UDE*(1-.5*(ALT(I)-20000)/(50000!-20000))

5565 RHO=.002378*(1-ALT(I)/145800!)'4.265

5570 UG=2* (W/S) / (RHO*MAC/12*AW*32 . 2)

5580 KG=.88*UG/(5.3+UG)

5590 GINC=KG*UDE*V(I)*ST*AT*(1-36*(AW/57.3)/ARW)/498

5600 G3T=LT(I)+GINC

5610 IF G3T>G1MAX THEN G1MAX=G3T:HHCASE=I:B3UPGU=LT(I):IUPGUS=GINC

5620 G4T=LT(I)-GINC

5630 IF G4T<G2MIN THEN G2MIN=G4T:HJCASE=I:B4DNGU=LT(I):IDNGUS=-GINC

5640 NEXT

5690 REM

5691 REM

 203

FAR 23 LOADS

5700 PRINT "NOW SEARCHING ALL GUST CONDITIONS WITH FLAPS EXTENDED FOR

LARGEST GUST TAIL LOADS" 
5710 G5FMAX=-1000001:G6FMIN=100000! 
5720 FOR 1=1 TO DB

5730 IF CND$(I)=''BAL VF" THEN W=W(I) ELSE 5920 
5740 UDE=25

5750 UG=2*(W/S)/(.002378*MAC/12*AW*32.2) 
5760 KG=.88*UG/(5.3+UG)

5870 GINC=KG*UDE*V(I)*ST*AT*(1-36*AW/57.3/ARW)/498 
5880 G7T=LT(I)+GINC

5890 IF G7T>G5FMAX THEN G5FMAX=G7T:HKCASE=I:B5UPGU=LT(I):I5UPGU=GINC 
5900 G8T=LT(I)-GINC

5910 IF G8T<G6FMIN THEN G6FMIN=G8T:HLCASE=I:B6DNGU=LT(I):I6DNGU=-GINC 
5920 NEXT I

5990 REM

5991 REM

6000 PRINT "NOW CALCULATING UNSYMMETRICAL HORIZONTAL TAIL LOAD"

6010 PC=100-10*(N-1):HTMAX=0

6020 IF PC>80 THEN PC=80

6025 DIM L(12),HCASE(12)

6030 L(1)=L1TMAX:HCASE(1)=H1TCASE

6040 L(2)=L2TMIN:HCASE(2)=H2TCASE

6050 L(3)=L3TFMAX:HCASE(3)=H3TCASE

6060 L(4)=L4TFMIN:HCASE(4)=H4TCASE

6070 L(5)=U1CK:HCASE(5)=H5CASE

6080 L(6)=U2CK:HCASE(6)=H6CASE

6090 L(7)=L7MIN:HCASE(7)=H7CASE

6100 L(8)=L8MAX:HCASE(8)=H8CASE

6110 L(9)=G1MAX:HCASE(9)=HHCASE

6120 L(10)=G2MIN:HCASE(10)=HJCASE

6130 L(11)=G5MAX:HCASE(11)=HKCASE

6140 L(12)=G6MIN:HCASE(12)=HLCASE

6145 DIM LAB(12)

6150 FOR 1=1 TO 12

6160 LAB(I)=ABS(L(I))

6170 IF LAB(I)>HTMAX THEN HTMAX=LAB(I):HZCASE=HCASE(I)

6175 NEXT I

6180 RHSIDE=.5*HTMAX*SGN(LT(HZCASE))

6190 LHSIDE=(PC/100)*RHSIDE

6195 REM

6196 REM

7000 PRINT "NOW PRINTING OUT CRITICAL HORIZONTAL TAIL LOADS"

7010 LPRINT:LPRINT:LPRINT "CRITICAL HORIZONTAL TAIL LOADS":LPRINT "--

7020 LPRINT:LPRINT "UP BALANCING TAIL LOAD FLAPS RETRACTED, FAR 23.42 
1"

7021 LPRINT TAB(5)"REFERENCE CASE NUMBER";TAB(27)H1TCASE

7022 LPRINT TAB(5)"BALANCED CONDITION";TAB(28)CND$(HITCASE)

7023 LPRINT TAB(5)"BALANCED TAIL LOAD";TAB(27)L1TMAX

7026 LPRINT TAB(5)"V KEAS";TAB(27)V(H1TCASE)

7027 LPRINT TAB(5)"CG";TAB(28)CG$(H1TCASE)

7028 LPRINT TAB(5)"ALTITUDE";TAB(27)ALT(H1TCASE)

7029 LPRINT TAB(5)"DISTRIBUTION";TAB(28)"FIG B6 APPENDIX B"

7030 LPRINT:LPRINT "DOWN BALANCING TAIL LOAD FLAPS RETRACTED,FAR 23.4

204

FAR 23 LOADS

7084 LPRINT TAB(5)"INCREMENTAL TAIL LOAD";TAB(27)I7CK

7085 LPRINT TAB(5)"TOTAL TAIL LOAD";TAB(27)L7MIN

7086 LPRINT TAB(5)"V KEAS";TAB(27)V(H7CASE)

7087 LPRINT TAB(5)"CG";TAB(28)CG$(H7CASE)

7088 LPRINT TAB(5)"ALTITUDE";TAB(27)ALT(H7CASE)

7089 LPRINT TAB(5)"DISTRIBUTION";TAB(28)"FIG B7 APPENDIX B"

7090 LPRINT:LPRINT "UP LOAD CHECKED MANEUVER TAIL LOAD, FAR23.423 (B) "

7091 LPRINT TAB(5)"REFERENCE CASE NUMBER";TAB(27)H8CASE

7092 LPRINT TAB(5)"BALANCED CONDITION";TAB(28)CND$(H8CASE)

7093 LPRINT TAB(5)"BALANCED TAIL LOAD";TAB(27)B8UNCK

7094 LPRINT TAB(5)"INCREMENTAL TAIL LOAD";TAB(27)I8UNCK

7095 LPRINT TAB(5)"TOTAL TAIL LOAD";TAB(27)L8MAX

7096 LPRINT TAB(5)"V KEAS";TAB(27)V(H8CASE)

7097 LPRINT TAB(5)"CG";TAB(28)CG$(H8CASE)

7098 LPRINT TAB(5)"ALTITUDE";TAB(27)ALT(H8CASE)

7099 LPRINT TAB(5)"DISTRIBUTION";TAB(28)"FIG B8 APPENDIX B"

7100 LPRINT:LPRINT "UP GUST TAIL LOAD FLAPS RETRACTED, FAR 23.425(A)(

1)"

7101 LPRINT TAB(5)"REFERENCE CASE NUMBERS";TAB ( 27)HHCASE-5;" AND ";HHC

ASE

7102 LPRINT TAB(5)"FOR CONDITIONS";TAB(28)CND$(HHCASE-5);" AND ";CND$(H 
HCASE)

7103 LPRINT TAB(5)"BALANCED TAIL LOAD";TAB(27)B3UPGU

7104 LPRINT TAB(5)"INCREMENTAL TAIL LOAD";TAB(27)IUPGUS

7105 LPRINT TAB(5)"TOTAL TAIL LOAD";TAB(27)G1MAX

7106 LPRINT TAB(5)"V KEAS";TAB(27)V(HHCASE)

7107 LPRINT TAB(5)"CG";TAB(28)CG$(HHCASE)

7108 LPRINT TAB(5)"ALTITUDE";TAB(27)ALT(HHCASE)

7109 LPRINT TAB(5)"DISTRIBUTION";TAB(28)"FIG B8 APPENDIX B"

7110 LPRINT:LPRINT "DOWN GUST TAIL LOAD FLAPS RETRACTED, FAR 23.425(A

) (1 ) "

7111 LPRINT TAB(5)"REFERENCE CASE NUMBERS";TAB(27)HJCASE-2;" AND ";HJC 
ASE

7112 LPRINT TAB(5)"FOR CONDITIONS";TAB(28)CND$(HJCASE-2);" AND ";CND$(H 
JCASE)

7113 LPRINT TAB(5)"BALANCED TAIL LOAD";TAB(27)B4DNGU

7114 LPRINT TAB(5)"INCREMENTAL TAIL LOAD";TAB(27)IDNGUS

7115 LPRINT TAB(5)"TOTAL TAIL LOAD";TAB(27)G2MIN

7116 LPRINT TAB(5)"V KEAS";TAB(27)V(HJCASE)

7117 LPRINT TAB(5)"CG";TAB(28)CG$(HJCASE)

7118 LPRINT TAB(5)"ALTITUDE";TAB(27)ALT(HJCASE)

7119 LPRINT TAB(5)"DISTRIBUTION";TAB(28)"FIG B8 APPENDIX B"

7120 LPRINT:LPRINT "UP GUST TAIL LOAD FLAPS EXTENDED, FAR 23.425(A)(2 
)"

7121 LPRINT TAB(5)"REFERENCE CASE NUMBERS";TAB(27)HKCASE-2;" AND ";HKC 
ASE

7122 LPRINT TAB(5)"FOR CONDITIONS";TAB(28)CND$(HKCASE-2);" AND ";CND$( 
HKCASE)

7123 LPRINT TAB(5)"BALANCED TAIL LOAD";TAB(27)B5UPGU

7124 LPRINT TAB(5)"INCREMENTAL TAIL LOAD";TAB(27)I5UPGU

7125 LPRINT TAB(5)"TOTAL TAIL LOAD";TAB(27)G5FMAX

7126 LPRINT TAB(5)"V KEAS";TAB(27)V(HKCASE)

7127 LPRINT TAB(5)"CG";TAB(28)CG$(HKCASE)

7128 LPRINT TAB(5)"ALTITUDE";TAB(27)ALT(HKCASE)

206

SELECTION OF CRITICAL LOADS

7129 LPRINT TAB(5)"DISTRIBUTION";TAB(28)"FIG B8 APPENDIX B"

7130 LPRINT:LPRINT "DOWN GUST TAIL LOAD FLAPS EXTENDED, FAR 23.425(A) 
(2)"

7131 LPRINT TAB(5)"REFERENCE CASE NUMBERS";TAB(27)HLCASE-1;" AND ";HLC 
ASE

7132 LPRINT TAB(5)"FOR CONDITIONS";TAB(28)CND$(HLCASE-1);" AND ";CND$( 
HLCASE)

7133 LPRINT TAB(5)"BALANCED TAIL LOAD";TAB(27)B6DNGU

7134 LPRINT TAB(5)"INCREMENTAL TAIL LOAD";TAB(27)I6DNGU

7135 LPRINT TAB(5)"TOTAL TAIL LOAD";TAB(27)G6FMIN

7136 LPRINT TAB(5)"V KEAS" ;TAB(27)V(HLCASE)

7137 LPRINT TAB(5)"CG";TAB(28)CG$(HLCASE)

7138 LPRINT TAB( 5 ) "ALTITUDE" ;TAB( 27 )ALT(HLCASE)

7139 LPRINT TAB(5)"DISTRIBUTION";TAB(28)"FIG B8 APPENDIX B"

7140 LPRINT:LPRINT "UNSYMMETRICAL LOAD, FAR 23.427(a)"

7141 LPRINT TAB(5)"REFERENCE CASE NUMBER";TAB(27)HZCASE

7142 LPRINT TAB ( 5 )" BALANCED CONDITION" ; TAB( 28 )CND$ (HZCASE)

7143 LPRINT TAB(5)"BALANCED TAIL LOAD";TAB(27)LT(HZCASE)

7144 LPRINT TAB(5)"RH SIDE TAIL LOAD";TAB(27)RHSIDE

7145 LPRINT TAB(5)"LH SIDE TAIL LOAD";TAB(27)LHSIDE

7146 LPRINT TAB(5)"TOTAL TAIL LOAD";TAB(27)RHSIDE+LHSIDE

7147 LPRINT TAB(5)"V KEAS" ; TAB(27)V(HZCASE)

7148 LPRINT TAB( 5 ) "CG" ; TAB ( 27) CG$( HZCASE)

7149 LPRINT TAB( 5 ) "ALTITUDE" ;TAB( 27 )ALT(HZCASE)

7150 LPRINT TAB(5)"DISTRIBUTION";TAB(28)"SAME AS ";HZCASE;" CASE"

7151 RETURN

7990 REM--- -------- -------------------------------

7991 REM          SELECT CRITICAL VERTICAL TAIL LOADS

7992 REM--- -----------------------.--------- -----------

7995 LPRINT CHR$(12)

8000 PRINT "SUBROUTINE TO SELECT CRITICAL VERTICAL TAIL LOADS":LPRINT

:LPRINT

8010 LPRINT "INPUT FOR VERTICAL TAIL":LPRINT "---- --- ------- ----"

8020 INPUT "ENTER FULL DEFLECTION OF RUDDER";RD$ 
8030 RD=VAL(RD$):IF RD<0 OR RD>60 THEN 8020 
8035 LPRINT "FULL RUDDER DEFLECTION = " ; RD 
8040 GW=W(1)

8055 LPRINT "GROSS WEIGHT, LBS = ";GW 
8075 LPRINT "WING AREA, SOR FT = ";S 
8077 LPRINT "WING MAC = ";MAC/12;" FT"

8080 INPUT "ENTER VERTICAL TAIL TOTAL AREA";SV$:SV=VAL(SV$):IF SV<0 OR 
SV>S THEN 8080

8095 LPRINT "VERTICAL TAIL AREA, SQR FT = ";SV

8096 REM

8097 REM

8100 PRINT "NOW CALCULATING TOTAL VERTICAL TAIL MANEUVER ING LOAD FOR S

UDDEN FULL RUDDER DEFLECTION AT VA"

8110 IF RD=<10 THEN W1BAR=.55*N*GW/S/1.5

8120 IF RD=>30 THEN W1BAR=.8*N*GW/S/1.5

8130 IF RD>10 AND RD<20 THEN W1BAR=(.55+(.7-.55)*(RD-10))/(20-10)*N*GW

/S/1.5

8140 IF RD=>20 AND RD<30 THEN W1BAR=(.7+(.8-.7)*(RD-20)/(30-20))*N*GW/

S/1.5

8150 L1V=W1BAR*SV

207

FAR 23 LOADS

8190 REM

8191 REM

8200 PRINT "NOW CALCULATING TOTAL VERTICAL TAIL MANEUVERING LOAD FOR Y

AW TO A SIDESLIP OF 19.5 DEG WITH RUDDER MAINTAINED AT FULL DEFLECTION

11

8210 W2BAR=.55*N*GW/S/1.5 
8220 L2V=W2BAR*SV

8290 REM

8291 REM

8300 PRINT "NOW CALCULATING TOTAL VERTICAL TAIL MANEUVERING LOAD FOR A

YAW ANGLE OF 15 DEG WITH RUDDER .IN NEUTRAL POSITION" 
8310 W3BAR=.8*N*GW/S/1.5:L3V=W3BAR*SV

8390 REM

8391 REM

8400 PRINT "NOW CALCULATING TOTAL VERTICAL TAIL LOAD FOR GUST AT VC"

8430 INPUT "ENTER MAC OF VERTICAL TAIL IN FEET" ;VMAC$ :VMAC=VAL(VMAC$) :

IF VMAC<0 OR VMA03*MAC THEN 8430

8441 LPRINT "MAC OF VERTICAL TAIL, FT = ";VMAC

8443 INPUT "ENTER FS25% MAC OF VERTICAL TAIL";XV25$:XV25=VAL(XV25$):IF

XV25<0 OR XV25>1000 THEN 8443 
8447 LPRINT "FS 25 PERCENT VMAC = ";XV25 
8450 INPUT "ENTER SLOPE OF LIFT CURVE (PER RADIAN) OF VERTICAL TAIL";A 
VT$:AVT=VAL(AVT$):IF AVT<0 OR AVT>10 THEN 8450 
8465 LPRINT "SLOPE OF LIFT CURVE OF VERTICAL TAIL, CL/RAD = ";AVT 
8470 INPUT "ENTER LENGTH OF AIRPLANE IN FEET";LF$:LF=VAL(LF$):IF LF<0 
OR LF>100 THEN 8470

8485 LPRINT "LENGTH OF AIRPLANE, FT = ";LF 
8490 INPUT "ENTER WING SPAN IN FEET";B$:B=VAL(B$):IF B<0 OR B>200 THEN

8490

8505 LPRINT "WING SPAN, FT = ";B 
8525 LPRINT "WEIGHT OF WING, LBS = ";WW 
8527 LVT=0

8530 FOR 1=1 TO DB

8540 IF CND$(I)o"BAL C" THEN 8680 
8550 IF CND$(I)="BAL C" THEN W=W(I) 
8560 IK=(WW/32.2)*B~2/12+((W-WW)/32.2)*LF'2/12 
8570 K=SQR(IK/(W/32.2)) 
8580 SIG=(1-6.879E-06*ALT(I))"4.258 
8590 RHO=SIG*.002378 
8610 LXVT=(XV25-XCG)/12 
8620 IF ALT(I)<=20000 THEN UDE=50 
8630 IF ALT(I)>20000 THEN UDE=50-(25/30000)*(ALT(I)-20000) 
8640 UGT=2*W/(RHO*VMAC*32.2*AVT*SV*(K/LXVT)~2) 
8650 KGT=.88*UGT/(5.3+UGT) 
8660 VLT=KGT*UDE*V(I)*AVT*SV/498 
8670 IF VLT>LVT THEN LVT=VLT:VCASE=I 
8680 NEXT I

8990 REM

8991 REM

9000 PRINT "NOW PRINTING OUT CRITICAL VERTICAL TAIL LOADS"

9010 LPRINT:LPRINT:LPRINT "CRITICAL VERTICAL TAIL LOADS":LPRINT ------

9020 LPRINT:LPRINT "MANEUVER LOAD FOR SUDDEN FULL RUDDER DEFLECTION, F 
AR 23.441(a)(l)"

208

SELECTION OF CRITICAL LOADS

9021 LPRINT TAB(5)"TOTAL TAIL LOAD";TAB(27)INT(L1V)

9022 LPRINT TAB(5)"DISTRIBUTION";TAB(28)"FIG B7 APPENDIX B"

9030 LPRINT:LPRINT "MANEUVER LOAD FOR YAW TO SIDESLIP OF 19.5 DEG WITH 
RUDDER MAINTAINED AT FULL DEFLECTION, FAR 23.441(a)(2)"

9031 LPRINT TAB(5)"TOTAL TAIL LOAD";TAB(27)INT(L2V)

9032 LPRINT TAB(5)"DISTRIBUTION";TAB(28)"FIG B6 APPENDIX B"

9040 LPRINT:LPRINT "MANEUVER LOAD FOR A YAW OF 15 DEG WITH RUDDER IN N 
EUTRAL, FAR 23.441(A)(3)"

9041 LPRINT TAB(5)"TOTAL TAIL LOAD";TAB(27)INT(L3V)

9042 LPRINT TAB(5)"DISTRIBUTION";TAB(28)"FIG B8 APPENDIX B"

9050 LPRINT:LPRINT "SIDE GUST LOAD AT VC, FAR 23.443(b)"

9051 LPRINT TAB(5)"TOTAL TAIL LOAD";TAB(27)INT(LVT)

9052 LPRINT TAB(5)"DISTRIBUTION";TAB(28)"FIG B8 APPENDIX B"

9053 LPRINT TAB(5)"REFERENCE CASE NUMBER";TAB(27)VCASE 
9900 RETURN

209

