LANDING LOADS

The program LANDLOAD.BAS calculates the loads for a tricycle 
landing gear with spring or oleo struts. The main and nose need 
not be the same type. The inputs needed for this program are the 
landing weight, the landing gear load factor, the assumed lift 
factor during landing, the station and waterline of the axles for 
the static position and the 25 percent compressed position if 
oleo or 100 percent compressed if spring strut, the rolling 
radius of the tires, the distance between the main wheels, the 
tail down bump angle and the weight and cg for the structural 
1imits.

The landing weight may be less than the maximum take-off 
weight under the conditions specified by FAR 23.473(b) and (c). A 
common practice is to use 95 percent of the maximum take off 
weight. This requires that the fuel tank capacity is at least 
fuel enough for one-half hour of operation at maximum continuous 
power plus the capacity equal to the weight difference between 
the maximum take off weight and the design landing weight.

An example using the Beach Banana 36 might make this 
clear. The max take off weight is 3400 pounds. The landing weight 
is .95 x 3400 = 3230 pounds. The max continuous power is 265 HP. 
You can assume the fuel rate for a reciprocating engine is .5 
pounds of fuel per hour for each horsepower.

The fuel for one-half hour is .5 x 265 HP x 1/2 HR = 66.25 
pounds or 11.04 gallons. The fuel equal to the max weight less 
the landing weight is 3400-3230 = 170 pounds or 28.33 gallons. 
Then the required fuel capacity must be 11.04 + 28.33 = 39.37 
gallons. You would use at least a 40 gallon fuel tank capacity.

The reduced landing weight may be used for level landing 
conditions, tail down landing conditions and one wheel landing 
conditions. The side load conditions, braked roll conditions and 
supplementary nose wheel conditions should be calculated for 
maximum take-off weight.

The dimensions and formulas of FAR 23 Appendix C and FAR 
23.471, 23.479, 23.473, 23.477, 23.479, 23.481, 23.483, 23.485, 
23.493, and 23.487 are the basis for these calculations.

Program LGFACTOR.BAS is provided to estimate the landing 
load factor that you need, since test data is usually not 
available in the design stage. The load factor should be revised 
if necessary before certification so as to be not be less than 
that determined by tests. The load factor calculations are. based 
on FAR 23.473(d), (e), (f) and (g).

263

FAR 23 LOADS

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

5 REM          HEADING AND COPYRIGHT

7 REM--------------------------------------------------------------

10 PRINT "PROGRAM TO CALCULATE LANDING LOADS --- LANDLOAD.BAS, VERSION

1.2" 
12 PRINT "(C) COPYRIGHT HAL C MCMASTER 1988,1989"

15 LPRINT CHR$(27)"N"CHR$(6):REM   TO SKIP OVER PERFORATIONS

16 LPRINT CHR$(27)"1"CHR$(4):REM   TO SET LH MARGIN

17 ANG$="\                                                \+tf.#f#" 
20 DIM VMP(33),DMP(33),SMP(33),RMP(33),VNP(33),DNP(33),SNP(33), 
RESULT(3 3) 
30 DIM NVP(33),NDP(33),NS(33),WL(33),PITCHP(33),ROLLP(33),YAWP(33)

32 DIM PHIN(33),PHIM(33),VN(33),DN(33)/SN(33),VM(33),DM(33),SM(33)

33 DIM NR(33),NV(33),ND(33),NNS(33),GA(24),ROLL(24),YAW(24)

34 DIM DE$(33),CG(33),POL$(33),FAA$(33),EQN$(33),EQM$(33),EQLFP$(33) , 
EQNGD$(33),EQMGD$(33) ,EQMOMP$(24),EQMOM$(24)

35 REM-------------------------------------------------------------

36 REM   INPUT AND ECHO PRINT + CALCULATE DRAG FACTOR AND LG GEOMETRY

37 REM------------------------------ --------------------- --------

38 LPRINT "CALCULATION OF LANDING GEAR GEOMETRY":LPRINT

39 LPRINT "INPUT":LPRINT

40 INPUT "ENTER MAX LANDING WEIGHT ";W:LPRINT "MAX LANDING WEIGHT = ";

TAB(32)W

45 INPUT "ENTER DESIGN MAXIMUM WEIGHT (GROSS WEIGHT) ";GW:LPRINT "

GROSS WEIGHT = ";TAB(32)GW

47 WR=GW/W

50 IF W=<3000 THEN K=.25

60 IF W=>6000 THEN K=.33

70 IF W>3000 AND W<6000 THEN K=.25+(W-3000)/(6000-3000)*(.33-.25)

80 INPUT "ENTER GEAR LOAD FACTOR";NLG:LPRINT "GEAR LOAD FACTOR = ";

TAB(32)NLG 
90 INPUT "ENTER WING LIFT FACTOR, L=<.667 ";LF:LPRINT "WING LIFT

FACTOR = ";TAB(3 2)LF 
100 NAP=NLG+LF 
110 K=NAP/NLG*K 
120 GAMMA=ATN(K)*57.3 
150 INPUT "IS MAIN GEAR AN OLEO STRUT OR SPRING STRUT, 0 OR S ";

MSTRUT$ 
160 IF MSTRUT$="0" THEN INPUT "ENTER COORDINATES X, Z OF MAIN GEAR

AXLES FOR 25 PERCENT DEFLECTION ";XMG(1),ZMG(1):LPRINT "XMG 25 % DEF

= ";TAB(32)XMG(1);TAB(41)"ZMG 25 % DEF = ";ZMG(1) 
170 IF MSTRUT$="S" THEN INPUT "ENTER COORDINATES X, Z OF MAIN GEAR

AXLES FOR 100 PERCENT DEFLECTION ";XMG(1),ZMG(1):LPRINT "XMG 100 %

DEF = ";TAB(32)XMG(1);TAB(41)"ZMG 100 % DEF = ";ZMG(1) 
180 IF MSTRUT$<>"0" AND MSTRUT$0"S" GOTO 150 
190 INPUT "IS NOSE GEAR AN OLEO STRUT OR SPRING STRUT, 0 OR S ";

NSTRUT$ 
200 IF NSTRUT$="0" THEN INPUT "ENTER COORDINATES X, Z OF NOSE GEAR

AXLE FOR 25 PERCENT DEFLECTION ";XNG(1),ZNG(1):LPRINT "XNG 25 % DEF =

";TAB(32)XNG(1);TAB(41)"ZNG 25 % DEF = ";ZNG(1) 
210 IF NSTRUT$="S" THEN INPUT "ENTER COORDINATES X,Z OF NOSE GEAR

AXLES FOR 100 PERCENT DEFLECTION ";XNG(1),ZNG(1):LPRINT "XNG 100 %

DEF = ";TAB(32)XNG(1);TAB(41)"ZNG 100 % DEF = "ZNG(l) 
220 IF NSTRUT$ <>"0" AND NSTRUT$ <>"S" GOTO 190

264

 LANDING LOADS

230 INPUT "ENTER COORDINATES X,Z OF MAIN GEAR FOR STATIC DEFLECTION ";

XMG(2),ZMG(2):LPRINT "XMG STATIC DEF = ";TAB(32)XMG(2);TAB(41)"ZMG

STATIC DEF = ";ZMG(2)

240 INPUT "ENTER COORDINATES X,Z OF NOSE GEAR FOR STATIC DEFLECTION ";

XNG(2),ZNG(2):LPRINT "XNG STATIC DEF = ";TAB(32)XNG(2);TAB(41)"ZNG

STATIC DEF = ";ZNG(2)

245 INPUT "ENTER COORDINATES X,Z OF NOSE GEAR FOR FULLY EXTENDED

DEFLECTION ";XNG(3),ZNG(3):LPRINT "XNG FULLY EXTENDED DEF = ";

TAB(32)XNG(3);TAB(41)"ZNG FULLY EXTENDED DEF = ";ZNG(3);" REF" 
247 INPUT "ENTER COORDINATES X,Z OF MAIN GEAR FOR FULLY EXTENDED

DEFLECTION ";XMG(3),ZMG(3):LPRINT "XMG FULLY EXTENDED DEF = ";

TAB(32)XMG(3);TAB(41)"ZMG FULLY EXTENDED DEF = ";ZMG(3);" REF" 
250 INPUT "ENTER ROLLING RADIUS MAIN GEAR ";RM:LPRINT "ROLLING RADIUS

MAIN GEAR = ";TAB(32)RM 
260 INPUT "ENTER ROLLING RADIUS NOSE GEAR ";RN:LPRINT "ROLLING RADIUS

NOSE GEAR = ";TAB(32)RN 
265 INPUT "ENTER TREAD (DISTANCE BETWEEN MAIN WHEELS)";TREAD:LPRINT

"TREAD BETWEEN MAIN WHEELS = ";TAB(32)TREAD 
270 REM   J=1 FOR 3 POINT AND 2 POINT LEVEL LANDING ATTITUDE,  J=2 FOR

GROUND ROLL AND J=3 FOR TAIL DOWN ATTITUDE 
280 FOR J=1 TO 2

290 GRA(J)=-ATN((ZMG(J)-ZNG(J))/(XMG(J)-XNG(J)))+ATN((RM-RN)/((XMG(J)-
XNG(J))-2+(ZMG(J)-ZNG(J))-2)-.5):GRA(J)=GRA(J)*57.3 
300 NEXT J

310 BETA(1)=GAMMA+GRA(1) 
320 BETA(2)=GRA(2) 
330 INPUT "ENTER GROUND ANGLE FOR TAIL DOWN ATTITUDE MEASURED FROM

GROUND LINE TO A WATERLINE ";GRA(3):BETA(3)=GRA(3) 
335 LPRINT "TAIL DOWN ANGLE GROUND TO WL = ";TAB(32)GRA(3) 
425 LPRINT:LPRINT "WEIGHT/CG DATA:":LPRINT 
430 LPRINT "CG NO","WCG","XCG","ZCG" 
440 FOR 1=1 TO 3

450 IF 1=1 THEN PRINT "FOR AFT MAX LANDING WEIGHT ENTER CG#,WCG,XCG, 
ZCG"

460 IF 1=2 THEN PRINT "FOR FWD MAX LANDING WEIGHT ENTER CG#,WCG,XCG, 
ZCG"

470 IF 1=3 THEN PRINT "FOR FWD LIGHT LANDING WEIGHT ENTER CGft,WCG,XCG, 
ZCG"

480 INPUT CG(I),WCG(I),XCG(I),ZCG(I):LPRINT CG(I),WCG(I),XCG(I),ZCG(I)

481 NEXT I

482 LPRINT:LPRINT:LPRINT "CALCULATED LANDING GEAR GEOMETRY":LPRINT,:

LPRINT USING ANG$;"DRAG LOAD FACTOR, K = ";K:LPRINT USING ANG$;"GAMMA 
= ARCTAN(K) = ";GAMMA

483 LPRINT USING ANG$;"GROUND ANGLE FOR 3 WHEEL LEVEL LANDING = ";

GRA(l)

484 LPRINT USING ANG$;"GROUND ANGLE FOR LEVEL LANDING NOSE WHEEL CLEAR 
= ";GRA(1)

485 LPRINT USING ANG$;"GROUND ANGLE FOR GROUND ROLL = ";GRA(2)

486 LPRINT USING ANG$;"GROUND ANGLE FOR TAIL DOWN ATTITUDE = ";GRA(3)

487 LPRINT "BETA = GAMMA - GROUND ANGLE = ANGLE BETWEEN RESULTANT LOAD 
AND FUS STA"

488 LPRINT USING ANG$ "BETA FOR 3 WHEEL LEV LAND = ";BETA(1)

489 LPRINT USING ANG$ "BETA FOR LEV LAND NOSE WHEEL CLEAR = ";BETA(1)

490 LPRINT USING ANG$ "BETA FOR GROUND ROLL = ";BETA(2)

265

FAR 23 LOADS

491 LPRINT USING ANG$;"BETA FOR TAIL DOWN ATTITUDE = ";BETA(3) 
500 DEF FNBP(XMG,XCG,BETA,ZCG,ZMG)=(XMG-XCG)/COS(BETA/57.3)+((ZCG-ZMG)

*(XMG-XCG)*TAN(BETA/57.3))*SIN(BETA/57.3)

510 DEF FNAP(XCG,XNG,BETA,ZCG,ZNG)=(XCG-XNG)*COS(BETA/57.3)-(ZCG-ZNG)

*SIN(BETA/57.3)

520 DEF FNDP(XMG,XNG,BETA,ZMG,ZNG)=(XMG-XNG)*COS(BETA/57.3)-(ZMG-ZNG)

*SIN(BETA/57.3)

530 LPRINT:LPRINT TAB(38)"AP";TAB(48)"BP";TAB(58)"DP";TAB(68)"CP"

540 REM   FOR 3 PT & 2 PT LEV LAND

550 FOR 1=1 TO 3

560 J=1

570 AP(J,I)=FNAP(XCG(I),XNG(J),BETA(J),ZCG(I),ZNG(J))

580 BP(J,I)=FNBP(XMG(J),XCG(I),BETA(J),ZCG(I),ZMG(J))

590 DP(J,I)=FNDP(XMG(J),XNG(J),BETA(J),ZMG(J),ZNG(J))

600 NEXT I

610 XMG(3)=XMG(1):ZMG(3)=ZMG(1)

620 FOR 1=1 TO 3

630 J=3

640 BP(J,I)=(XMG(J)-XCG(I))*COS(GRA(J)/57.3)-(ZCG(I)-ZMG(J))*

SIN(GRA(J)/57.3)

650 NEXT I

660 FOR 1=1 TO 3

670 J=2

680 AP(J,I)=FNAP(XCG(I),XNG(J),GRA(J),ZCG(I),ZNG(J))

690 BP(J,I)=FNBP(XMG(J),XCG(I),BETA(J),ZCG(I),ZMG(J))

700 DP(J,I)=FNDP(XMG(J),XNG(J),BETA(J),ZMG(J),ZNG(J))

702 ZT=ZNG(J)-RN*COS(GRA(J)/57.3)

704 XT=XNG(J)+RN*SIN(GRA(J)/57.3)

706 ZL=ZMG(J)-RM*COS(GRA(J)/57.3)

708 XL=XMG(J)+RM*SIN(GRA(J)/57.3)

710 ZS=ZT+(XCG(I)-XT)*(ZL-ZT)/(XL-XT)

712 CP(J,I)=(ZCG(I)-ZS)*COS(GRA(J)/57.3)

720 NEXT I

730 FOR J=1 TO 3

740 FOR 1=1 TO 3

750 IF J=1 THEN LPRINT "3 PT AND 2 PT LEV LAND FOR CG NO ";CG(I);

760 IF J=2 THEN LPRINT "GROUND ROLL FOR CG NO ";CG(I);

770 IF J=3 THEN LPRINT "TAIL DOWN ATTITUDE FOR CG NO ";CG(I);

780 IF J=1 OR J=3 THEN LPRINT TAB(37)INT(AP(J,I)*1000)/1000;TAB(47) 
INT(BP(J,I)*1000)/1000;TAB(57)INT(DP(J,I)*1000)/1000

790 IF J=2 THEN LPRINT TAB(37)INT(AP(J,I)*1000)/1000;TAB(47) 
INT(BP(J,I)*1000)/1000;TAB(57)INT(DP(J.I)*1000)/1000;TAB(67) 
INT(CP(J,I)*1000)/1000

791 REM---------------------------------------------------------------

792 REM       CALCULATE WHEEL LOADS RELATIVE TO GROUND

793 REM---------------------------------------------------------------

800 NEXT I

810 NEXT J

820 WL(1)=WCG(1):WL(2)=WCG(2):WL(3)=WCG(3)

830 WL(4)=WCG(1):WL(5)=WCG(2):WL(6)=WCG(3)

840 WL(7)=WCG(1):WL(8)=WCG(2):WL(9)=WCG(3)

850 WL(10)=WCG(1):WL(11)=WCG(2):WL(12)=WCG(3)

860 WL(13)=WCG(1)*WR:WL(14)=WCG(2)*WR:WL(15)=WCG(3)

870 WL(16)=WCG(1)*WR:WL(17)=WCG(2)*WR:WL(18)=WCG(3)

266

LANDING LOADS

880 WL(19)=WCG(1)*WR:WL(20)=WCG(1)*WR

890 WL(21)=WCG(2)*WR:WL(22)=WCG(2)*WR

900 WL(23)=WCG(3):WL(24)=WCG(3)

910 FOR M=1 TO 24:VMP(M)=0:NEXT M

920 VMP(1)=.5*NLG*WL(1)*AP(1,1)/DP(1,1)

930 VMP(2)=.5*NLG*WL(2)*AP(1,2)/DP(1,2)

940 VMP(3)=.5*NLG*WL(3)*AP(1,3)/DP(1,3)

950 VMP(4)=.5*NLG*WL(4)

960 VMP(5)=.5*NLG*WL(5)

970 VMP(6)=.5*NLG*WL(6)

980 VMP(7)=.5*NLG*WL(7)

990 VMP(8)=.5*NLG*WL(8)

1000 VMP(9)=.5*NLG*WL(9)

1010 VMP(10)=.5*NLG*WL(10)

1020 VMP(11)=.5*NLG*WL(11)

1030 VMP(12)=.5*NLG*WL(12)

1040 VMP(13)=.5*1.33*WL(13)*AP(2,!)/(.8*CP(2,1)+DP(2,1))

1050 VMP(14)=.5*1.33*WL(14)*AP(2,2)/(.8*CP(2,2)+DP(2,2))

1060 VMP(15)=.5*1.33*WL(15)*AP(2,3)/(.8*CP(2,3)+DP(2,3))

1070 VMP(16)=.5*1.33*WL(16)

1080 VMP(17)=.5*1.33*WL(17)

1090 VMP(18)=.5*1.33*WL(18)

1100 VMP(19)=.5*1.33*WL(19)

1110 VMP(20)=.5*1.33*WL(20)

1120 VMP(21)=.5*1.33*WL(21)

1130 VMP(22)=.5*1.33*WL(22)

1140 VMP(23)=.5*1.33*WL(23)

1150 VMP(24)=.5*1.33*WL(24)

1160 FOR L=1 TO 24:DMP(L)=0:NEXT L

1170 DMP(1)=K*VMP(1)

1180 DMP(2)=K*VMP(2)

1190 DMP(3)=K*VMP(3)

1200 DMP(4)=K*VMP(4)

1210 DMP(5)=K*VMP(5)

1220 DMP(6)=K*VMP(6)

1230 DMP(10)=K*VMP(10)

1240 DMP(11)=K*VMP(11)

1250 DMP(12)=K*VMP(12)

1260 DMP(13)=.8*VMP(13)

1270 DMP(14)=.8*VMP(14)

1280 DMP(15)=.8*VMP(15)

1290 DMP(16)=.8*VMP(16)

1300 DMP(17)=.8*VMP(17)

1310 DMP(18)=.8*VMP(18)

1320 FOR L=1 TO 24:SMP(L)=0:NEXT L

1330 SMP(19)=-.5*WL(19)

1340 SMP(20)=.33*WL(20)

1350 SMP(21)=-.5*WL(21)

1360 SMP(22)=.33*WL(22)

1370 SMP(23)=-.5*WL(23)

1380 SMP(24)=.33*WL(24)

1390 FOR L=1 TO 24

1400 RMP(L)=(VMP(L)~2+DMP(L)-2)~.5

1410 NEXT L

267

FAR 23 LOADS

1650 FOR L=1 TO 33

1660 VNP(L)=0

1670 NEXT L

1680 VNP(1)=NLG*WL(1)*BP(1,1)/DP(1,1)

1690 VNP(2)=NLG*WL(2)*BP(1,2)/DP(1,2)

1700 VNP(3)=NLG*WL(3)*BP(1,3)/DP(1,3)

1710 VNP(13)=1.33*WL(13)-2*VMP(13)

1720 VNP(14)=1.33*WL(14)-2*VMP(14)

1730 VNP(15)=1.33*WL(15)-2*VMP(15)

1740 VNP(25)=2.25*WCG(1)*WR*BP(2,1)/DP(2,1):VNP(26)=VNP(25):VNP(27):

VNP(25) 
1750 VNP(28)=2.25*WCG(2)*WR*BP(2,2)/DP(2,2):VNP(29)=VNP(28):VNP(30)^

VNP(28) 
1760 VNP(31)=2.25*WCG(3)*BP(2,3)/DP(2,3):VNP(32)=VNP(31):VNP(33)=

VNP(31)

1770 FOR L=1 TO 33:DNP(L)=0:NEXT L

1780 DNP(1)=K*VNP(1)

1790 DNP(2)=K*VNP(2)

1800 DNP(3)=K*VNP(3)

1810 DNP(25)=.8*VNP(25)

1820 DNP(26)=-.4*VNP(26)

1830 DNP(28)=.8*VNP(28)

1840 DNP(29)=-.4*VNP(29)

1850 DNP(31)=.8*VNP(31)

1860 DNP(32)=-.4*VNP(32)

1870 FOR L=1 TO 33:SNP(L)=0:NEXT L

1880 SNP(27)=.7*VNP(27)

1890 SNP(30)=.7*VNP(30)

1900 SNP(33)=.7*VNP(33)

1910 FOR L=1 TO 33

1920 RESULT(L)=(VNP(L)~2+DNP(L)~2)~.5

1930 NEXT L

1940 PRINT "L","VNP","DNP","SNP","RESULT"

1950 FOR L=1 TO 33:PRINT L,INT(VNP(L)),INT(DNP(L)),INT(SNP(L)),

INT(RESULT(L)):NEXT L

2420 FOR L=1 TO 9:NVP(L)=(2*VMP(L)+VNP(L)+LF*WL(L))/WL(L):NEXT L

2430 FOR L=10 TO 12:NVP(L)=(VMP(L)+LF*WL(L))/WL(L):NEXT L

2440 FOR L=13 TO 24

2450 NVP(L)=(2*VMP(L)+VNP(L))/WL(L)

2460 NEXT L

2470 FOR L=1 TO 9

2480 NDP(L)=(2*DMP(L)+DNP(L))/WL(L)

2490 NEXT L

2500 FOR L=1 TO 24:NS(L)=0:NEXT L

2510 NS(19)=(SMP(19)-SMP(20))/WL(19)

2520 NS(20)=(SMP(20)-SMP(19))/WL(20)

2530 NS(21)=(SMP(21)-SMP(22))/WL(21)

2540 NS(22)=(SMP(22)-SMP(21))/WL(22)

2550 NS(23)=(SMP(23)-SMP(24))/WL(23)

2560 NS(24)=(SMP(24)-SMP(23))/WL(24)

2570 FOR L=10 TO 12

2580 NDPfL)=(DMP(L)+DNP(L))/WL(L)

2590 NEXT L

2600 FOR L=13 TO 24

268

LANDING LOADS

2610 NDP(L)=(2*DMP(L)+DNP(L))/WL(L)

2620 NEXT L

2630 PRINT "L";TAB(10)"VMP";TAB(20)"DMP";TAB(30)"SMP";TAB(40)"RMP" ;

TAB(50)"NVP",-TAB(60)"NDP";TAB(70)"NS"

2640 FOR L=1 TO 24:PRINT L;TAB(10)INT(VMP(L));TAB(20)INT(DMP(L));

TAB(30)INT(SMP(L));TAB(40)INT(RMP(L));TAB(50)INT(NVP(L)*1000)/1000;

TAB(60)INT(NDP(L)*1000)/1000;TAB(70)INT(NS(L)*1000)/1000:NEXT L

2700 FOR L=1 TO 24:PITCHP(L)=0:ROLLP(L)=0:YAWP(L)=0:NEXT L

2710 PITCHP(4)=-2*RMP(4)*BP(1,1)

2720 PITCHP(5)=-2*RMP(5)*BP(1,2)

2730 PITCHP(6)=-2*RMP(6)*BP(1,3)

2740 PITCHP(7)=-2*RMP(7)*BP(3,1)

2750 PITCHP(8)=-2*RMP(8)*BP(3,2)

2760 PITCHP(9)=-2*RMP(9)*BP(3,3)

2770 PITCHP(10)=-RMP(10)*BP(1,1)

2780 PITCHP(11)=-RMP(11)*BP(1,2)

2790 PITCHP(12)=-RMP(12)*BP(1,3)

2800 PITCHP(16)=-2*(VMP(16)*BP(2,1)+DMP(16)*CP(2,1))

2810 PITCHP(17)=-2*(VMP(17)*BP(2,2)+DMP(17)*CP(2,2))

2820 PITCHP(18)=-2*(VMP(18)*BP(2,3)+DMP(18)*CP(2,3))

2830 PITCHP(19)=-2*VMP(19)*BP(2,1)

2840 PITCHP(20)=-2*VMP(20)*BP(2,1)

2850 PITCHP(21)=-2*VMP(21)*BP(2,2)

2860 PITCHP(22)=-2*VMP(22)*BP(2,2)

2870 PITCHP(23)=-2*VMP(23)*BP(2,3)

2880 PITCHP(24)=-2*VMP(24)*BP(2,3)

3000 FOR L=10 TO 12:ROLLP(L)=VMP(L)*TREAD/2:NEXT L

3010 ROLLP(19)=-.83*WL(19)*CP(2,1)

3020 ROLLP(20)=.83*WL(20)*CP(2,1)

3030 ROLLP(21)=-.83*WL(21)*CP(2,2)

3040 ROLLP(22)=.83*WL(22)*CP(2,2)

3050 ROLLP(23)=-.83*WL(23)*CP(2,3)

3060 ROLLP(24)=.83*WL(24)*CP(2,3)

3100 FOR L=10 TO 12:YAWP(L)=-DMP(L)*TREAD/2:NEXT L

3110 YAWP(19)=-.83*WL(19)*BP(2,1)

3120 YAWP(20)=.83*WL(20)*BP(2,1)

3130 YAWP(21)=-.83*WL(21)*BP(2,2)

3140 YAWP(22)=.83*WL(22)*BP(2,2)

3150 YAWP(23)=-.83*WL(23)*BP(2,3)

3160 YAWP(24)=.83*WL(24)*BP(2,3)

3170 PRINT "L","PITCHP","ROLLP","YAWP"

3180 FOR L=1 TO 24:PRINT L,INT(PITCHP(L)),INT(ROLLP(L)), INT (YAWP( L ))

NEXT L

3990 REM------------- --------------------------------------.

3991 REM     CALCULATE LOADS RELATIVE TO AIRPLANE DATUM

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

4000 FOR L=1 TO 6:PHIM(L)=BETA(1):NEXT L 
4010 FOR L=7 TO 9:PHIM(L)=-BETA(3):NEXT L 
4015 FOR L=i0 TO 12:PHIM(L)=BETA( 1):NEXT L

4020 FOR L=13 TO 18:PHIM(L)=ATN(.8)*57.3+BETA(2):NEXT L

4021 FOR L=19 TO 24:PHIM(L)=BETA( 2):NEXT L

4022 FOR L=1 TO 3:PHIN(L)=BETA(1):NEXT L

4023 FOR L=4 TO 12:PHIN(L)=0:NEXT L

4024 FOR L=13 TO 15:PHIN(L)=BETA(2):NEXT L

269

4025 FOR L=16 TO 24:PHIN(L)=0:NEXT L

4030 FOR L=25 TO 31 STEP 3 PHIN(L )=ATN( . 8 )*57 . 3+BETA(2 ) :NEXT L

4040 FOR L=26 TO 32 STEP 3 PHIN(L)=ATN(-. 4 ) *57 . 3+BETA(2 ) :NEXT L

4050 FOR L=27 TO 33 STEP 3 PHIN(L)=BETA(2):NEXT L 
4060 PRINT "L","PHIN","PHIM"

4070 FOR L=1 TO 33:PRINT L,PHIN(L),PHIM(L):NEXT L

4071 FOR L=1 TO 33:VN(L)=RESULT(L)*COS(PHIN(L)/57.3):DN(L)=RESULT(L)* 
SIN(PHIN(L)/57.3):NEXT L

4072 FOR L=1 TO 33:VM(L)=RMP(L)*COS(PHIM(L)/57.3):DM(L)=RMP(L)* 
SIN ( PHIM(L)/57.3):NV(L)=0:ND(L)=0:NEXT L

4073 FOR L=1 TO 6:NV(L)=LF*COS(GRA(1)/57.3)+(VN(L)+2*VM(L))/WL(L):NEXT 
L

4074 FOR L=7 TO 9 :NV( L ) =LF*COS(GRA( 3 )/57 . 3 )+(VN(L )+2*VM( L ) )/WL( L ) : NEXT 
L

4075 FOR L=10 TO 12:NV(L)=LF*COS(GRA(1)/57.3)+VM(L)/WL(L):NEXT L

4076 FOR L=13 TO 18:NV(L)=(VN(L)+2*VM(L))/WL(L):NEXT L

4077 FOR L=1 TO 6:ND(L)=LF*SIN(GRA(1)/57.3)+(DN(L)+2*DM(L))/WL(L):NEXT 
L

4078 FOR L=1 TO 33:NNS(L)=0:NEXT L

4079 FOR L=19 TO 23 STEP 2:NNS(L)=(SMP(L)-SMP(L+1))/WL(L) :NEXT L

4080 FOR L=20 TO 24 STEP 2:NNS(L)=-((SMP(L-1)-SMP(L)))/WL(L):NEXT L

4081 FOR L=7 TO 9:ND(L)=-LF*SIN(GRA(3)/57.3)+2*DM(L)/WL(L):NEXT L

4082 FOR L=10 TO 12:ND(L)=LF*SIN(GRA(1)/57.3)+DM(L)/WL(L):NEXT L

4083 FOR L=13 TO 15:ND(L)=(DN(L)+2*DM(L))/WL(L):NEXT L

4084 FOR L=16 TO 24:ND(L)=2*DM(L)/WL(L):NEXT L

4086 FOR L=19 TO 24:NV(L)=2*VM(L)/WL(L):NEXT L

5000 PRINT:PRINT "L";TAB(10)"VN";TAB(20)"DN";TAB(30)"VM";TAB(40)"DM";

TAB(50)"NV";TAB(60)"ND";TAB(70)"NNS"

5010 FOR L=1 TO 33

5020 PRINT L;TAB(10)INT(VN(L));TAB(20)INT(DN(L));TAB(30) INT(VM(L));

TAB(40)INT(DM(L));TAB(50)INT(NV(L)*1000)/1000;TAB(60)INT(ND(L)*1000)/ 
1000;TAB(70)INT(NNS(L)*1000)/1000:NEXT L

5101 REM-------------------------------------------------------------

5102 REM     PRINT OUT HEADINGS FOR LOADS RELATIVE TO GROUND

5103 REM--------------------------------------------------------------

5105 WIDTH LPRINT 160

5110 LPRINT CHR$(12)

5115 LPRINT CHR$(27)"!"CHR$(5):REM   TO SELECT COMPRESSED ELITE

5117 LPRINT CHR$(27)"1"CHR$(3):REM   SET LH MARGIN

5120 LPRINT "LIMIT GROUND REACTIONS AND LOAD FACTORS";TAB(82)"CG ";

CG(3);TAB(88)WCG(3);" LBS  XCG=";XCG(3);TAB(114)"ZCG=";ZCG(3) 
5130 LPRINT STRING$(39,"-");TAB(82)"CG ";CG(2 ) ;TAB(88)WCG(2);" LBS

XCG=";XCG(2);TAB(114)"ZCG=";ZCG(2)

5140 LPRINT "VALUES ARE WITH RESPECT TO GROUND LINE -- DENOTED BY P 
(PRIME)";TAB(82)"CG ";CG(1);TAB(88)WCG(1);" LBS  XCG=";XCG(1) ;

TABfll4)"ZCG=";ZCG(l)

5150 LPRINT STRING$(157,"-")

5160 LPRINT "CASE CONDITION";TAB(24)"CG";TAB(27)"POINT"; TAB(36)

"FUSELAGE" ;TAB( 45) "<- ------- NOSE GEAR ----- >";TAB(84)"

<-------__ LEFT MAIN GEAR ----------><-- AIRPLANE

- - >" 
5170 LPRINT "    ------------------;TAB(27)"OF";TAB(36)"AXIS";TAB(45)

M _"__."________         _ _ _         _ _

---*--------.-------.--------------_-.--      - - >

270

LANDING LOADS

5180 LPRINT " NO  DESCRIPTION";TAB(24)"NO";TAB(27)"LOAD";TAB(36)" 
ANGLE";TAB(45)"EQUATIONS";TAB(62)"VNP";TAB(68)"DNP";TAB(75)"SN" ;

TAB(78)"RESULT";TAB(84)" EQUATIONS";TAB(102)"VMP";TAB(109)"DMP" ;

TAB(115)"SM";TAB(121)"RESM";TAB(126)"EQUATIONS";

5181 LPRINT TAB(143)"NVP";TAB(149)"NDP";TAB(156)"NS" 
5190 LPRINT STRING$(157,"-")

5195 REM--------------------------------------------------------------

5196 REM    SET UP ARRAYS FOR LOADS RELATIVE TO GROUND

5197 REM--------------------------------------------------------------

5200 DE$(1)="THREE WHEEL LEVEL" 
5210 DE$(2)="     LANDINS" 
5220 DE$(3)="INCLINED REACTIONS" 
5230 DE$(4)="TWO WHEEL LEVEL" 
5240 DE$(5)="     LANDING" 
5250 DE$(6)="INCLINED REACTIONS" 
5260 DE$(7)="TAIL DOWN LANDING" 
5270 DE$(8)="     VERTICAL" 
5280 DE$(9)="    REACTIONS" 
5290 DE$(10)="ONE WHEEL LEVEL" 
5300 DE$(11)="     LANDING" 
5310 DE$(12)="INCLINED REACTIONS" 
5320 DE$(13)="          NOSE" 
5330 DE$(14)="GROUND    GEAR" 
5340 DE$(15)="ROLL-     DOWN" 
5350 DE$(16)="WHEELS    NOSE" 
5360 DE$(17)="BRAKED    GEAR" 
5370 DE$(18)="          CLEAR" 
5380 DE$(19)="          LT DRIFT" 
5390 DE$(20)="GROUND    RT DRIFT" 
5400 DE$(2i)="SIDE LOAD LT DRIFT" 
5410 DE$(22)="LEFT      RT DRIFT" 
5420 DE$(23)="VALUES    LT DRIFT" 
5430 DE$(24)="          RT DRIFT" 
5440 DE$(25)="          AFT" 
5450 DE$(26)="          FWD" 
5460 DE$(27)="SUPPLE-   SIDE" 
5470 DE$(28)="          AFT" 
5480 DE$(29)="          FWD" 
5490 DE$(30)="NOSE      SIDE" 
5500 DE$(31)="CONDITION AFT" 
5510 DE$(32)="          FWD" 
5520 DE$(33)="          SIDE" 
5530 POL$(1)=" " 
5540 POL$(2)=" " 
5550 POL$(3)=" " 
5560 POL$(4)="CENTER" 
5570 POL$(5)=" " 
5580 POL$(6)="  OF" 
5590 POL$(7)=" EACH" 
5600 POL$(8)=" " 
5610 POL$(9)="WHEEL" 
5620 POL$(10)=" " 
5630 POL$(11)=" " 
5640 POL$(12)=" "

271

FAR 23 LOADS

5650 POL$(13)=" " 
5660 POL$(14)=" " 
5670 POL$(15)=" " 
5680 POL$(16)="GROUND" 
5690 POL$(17)=" " 
5700 POL$(18)="CONTACT" 
5710 POL$(19)="POINT" 
5720 POL$(20)=" " 
5730 POL$(21)=" " 
5740 POL$(22)=" " 
5750 POL$(23)=" " 
5760 POL$(24)=" " 
5770 POL$(25)="CL AXLE" 
5780 POL$(26)="CL AXLE" 
5790 POL$(27)="GROUND" 
5800 POL$(28)="CL AXLE" 
5810 POL$(29)="CL AXLE" 
5820 POL$(30)="GROUND" 
5830 POL$(31)="CL AXLE" 
5840 POL$(32)="CL AXLE" 
5850 POL$(33)="GROUND" 
5900 FAA$(1)=STR$(GRA(1)) 
5910 FAA$(2)=" " 
5920 FAA$(3)=" DEG WITH" 
5930 FAA$(4)=" GROUND" 
5940 FAA$(5)=" " 
5950 FAA$(6)=" LINE" 
5960 FAA$(7)=STR$(GRA(3)) 
5970 FAA$(8)=" DEG WITH" 
5980 FAA$(9)=" GROUND" 
5990 FAA$(10)=STR$(GRA(1)) 
6000 FAA$(11)=" DEG WITH" 
6010 FAA$(12)=" GROUND" 
6020 FAA$(13)=" " 
6030 FAA$(14)=" " 
6040 FAA$(15)=" " 
6050 FAA$(16)=" " 
6060 FAA$(17)=STR$(GRA(2)) 
6070 FAA$(18)=" " 
6080 FAA$(19)=" " 
6090 FAA$(20)=" WITH" 
6700 FAA$(21)=" GROUND" 
6710 FAA$(22)=" " 
6720 FAA$(23)=" " 
6730 FAA$(24)=" " 
6740 FAA$(25)=" " 
6750 FAA$(26)=" " 
6760 FAA$(27)=" " 
6770 FAA$(28)=" " 
6780 FAA$(29)=" " 
6790 FAA$(30)=" " 
6800 FAA$(31)=" " 
6810 FAA$(32)=" " 
6820 FAA$(33)=" "

LANDING LOADS

6890 VPN$=STR$(NLG):VPN$=LEFT$(VPN$,5)

6900 EON$(1)="VP="+VPN$+"WBP/DP"

6905 K$=STR$(K):K$=MID$(K$,2,5)

6910 EQN$(2)="DNP="+K$+"VPN"

6920 EQN$(3)="S=0"

6930 EQN$(4)="  NOSE"

6940 EQN$(5)="  WHEEL"

6950 EON$(6)="  CLEAR"

6960 EQN$(7)="  NOSE"

6970 EON$(8)="  WHEEL"

6980 EQN$(9)="  CLEAR"

6990 EQN$(10)="  NOSE"

7000 EQN$(11)="  WHEEL"

7010 EQN$(12)="  CLEAR"

7020 EQN$(13)="VNP=1.33-2VMP"

7030 EQN$(14)="DNP=0"

7040 EQN$(15)="S=0"

7050 EQN$(16)="  NOSE"

7060 EQN$(17)="  WHEEL"

7070 EQN$(18)="  CLEAR"

7080 EQN$(19)="  NOSE WHEEL"

7090 EQN$(20)="  CLEAR"

7100 EON$(21)="  NOSE WHEEL"

7110 EQN$(22)="  CLEAR"

7120 EQN$(23)="  NOSE WHEEL"

7130 EQN$(24)="  CLEAR"

7140 EQN$(25)=" "

7150 EQN$(26)=" "

7160 EQN$(27)=" "

7170 EQN$(28)="DNP=.8VNP  S=0"

7180 EQN$(29)="DNP=-.4VNP S=0"

7190 EQN$(30)="DNP=0 S=+.7VNP"

7200 EQN$(31)=" "

7210 EQN$(32)=" "

7220 EQN$(33)=" "

7230 VMP$=STR$(NLG/2):VMP$=LEFT$(VMP$,5)

7240 EOM$(1)="VMP="+VMP$+"WAP/DP"

7245 K$=STR$(K):K$=LEFT$(K$,5)

7250 EQM$(2)="DMP="+K$+"VMP"

7260 EQM$(3)="S=0"

7265 K2$=STR$(NLG/2):K2$=LEFT$(K2$,5)

7270 EQM$(4)="VMP="+K2$+"W"

7280 EOM$(5)="DMP="+K$+"VMP"

7290 EQM$(6)="S=0"

7300 EQM$(7)="VMP="+K2$+"W"

7310 EQM$(8)="DMP=0"

7320 EQM$(9)="S=0"

7330 EQM$(10)="VMP="+K2$+"W"

7340 EQM$(11)="DMP="+K$+"VMP"

7350 EQM$(12)="S=0"

7360 EQM$(13)="VMP=.665WAP/"

7370 EQM$(14)="    (.8CP+DP)"

7380 EQM$(15)="DMP=.8VMP  S=0"

7390 EQM$(16)="VMP=.665W"

273

FAR 23 LOADS

7400 EQM$(17)="DMP=.8VMP"

7410 EQM$(18)="S=0"

7420 EQM$(19)=" "

7430 EQM$(20)=" "

7440 EQM$(21)="S(LD)=-.5W INBD"

7450 EQM$(22)="S(RD)=.33W OUTB"

7460 EQM$(24)=" "

7470 EQM$(25)=" "

7480 EQM$(26)=" "

7490 EQM$(27)=" "

7500 EQM$(28)=" "

7510 EQM$C29)=" "

7520 EQM$(30)=" "

7530 EQM$(31)=" "

7540 EQM$(32)=" "

7550 EQM$(33)=" "

7600 EQLFP$(1)="NVP=SUM(VP)"

7605 LF$=STR$(LF):LF$=LEFT$(LF$,5)

7610 EQLFP$(2)="    /W+"+LF$

7620 EQLFP$(3)=" "

7630 EQLFP$f4)=" "

7640 EQLFP$(5)="NS=SUM(S)/W"

7650 EQLFP$(6)=" "

7660 EQLFP$(7)=" "

7670 EQLFP$(8)=" "

7680 EQLFP$(9)=" "

7690 EQLFP$(10)=" "

7700 EQLFP$(11)=" "

7710 EQLFP$(12)=" "

7720 EQLFP$(13)="NVP=SUM(VP)/W"

7730 EQLFP$(14)=" "

7740 EQLFP$(15)=" "

7750 EQLFP$(16)=" "

7760 EQLFP$(17)="NS=SUM(S)/W"

7770 EQLFP$(18)=" "

7780 EQLFP$(19)=" "

7790 EQLFP$(20)=" "

7800 EQLFP$(21)=" "

7810 EQLFP$(22)=" "

7820 EQLFP$(23)=" "

7830 EQLFP$(24)=" "

7840 EQLFP$(25)=" "

7850 EQLFP$(26)=" "

7860 EOLFP$(27)=" "

7870 EQLFP$C28)=" "

7880 EQLFP$C29)=" "

7890 EQLFP$(30)=" "

7900 EQLFP$(31)=" "

7910 EQLFP$(32)=" "

7920 EQLFP$(33)=" "

7930 CG(4)=CG(1)

7931 CG(5)=CG(2)

7932 CG(6)=CG(3)

7933 CG(7)=CG(1)

274

LANDING LOADS

7934 CG(8)=CG(2)

7935 CG(9)=CG(3)

7936 CG(10)=CG(1)

7937 CG(11)=CG(2)

7938 CG(12)=CG(3)

7939 CG(13)=CG(1)

7940 CG(14)=CG(2)

7941 CG(15)=CG(3)

7942 CG(16)=CG(1)

7943 CG(17)=CG(2)

7944 CG(18)=CG(3)

7945 CG(19)=CG(1)

7946 CG(20)=CG(1)

7947 CG(21)=CG(2)

7948 CG(22)=CG(2)

7949 CG(23)=CG(3)

7950 CG(24)=CG(3)

7951 CG(25)=CG(1)

7952 CG(26)=CG(1)

7953 CG(27)=CG(1)

7954 CG(28)=CG(2)

7955 CG(29)=CG(2)

7956 CG(30)=CG(2)

7957 CG(31)=CG(3)

7958 CG(32)=CG(3)

7959 CG(33)=CG(3) 
8000 FRM$="#ft  \               \ ft# \     \ \       \ \            \

mm m>> m## w#t \            \mm m^ mm mm \

8004 REM--------------------------------------------------------------

8004 REM-

8005 REM  ROUTINE TO PRINT LOADS WITH RESPECT TO GROUND

8006 REM----------- -----------------------------------------------

8010 FOR 1=1 TO 24 :LPRINT USING FRM$;I;DE$(I);CG(I);POL$(I);FAA$(I);

EQN$(I);VNP(I);DNP(I);SNP(I);RESULT(I);EQM$(I);VMP(I);DMP(I);SMP(I);

RMP(I);EQLFP$(I);NVP(I);NDP(I);NS(I)

8011 IF 1=12 THEN LPRINT TAB(6)"LEFT WHEEL LOADED";TAB(36)"LINE"

8012 IF 1=12 THEN LPRINT STRING$(157,"-")

8014 IF 1=3 THEN LPRINT STRING$(26,"-");TAB(45)STRING$(79,"-");

TAB(126)"NDP=SUM(DP)/W";TAB(140)STRING$(18,"-")

8016 IF 1=6 THEN LPRINT STRING$(26,"-");TAB(35)STRING$(90,"-");

TAB(140)STRING$(18,"-")

8017 IF 1=9 THEN LPRINT TAB(36)"LINE"

8018 IF 1=9 THEN LPRINT STRING$(26,"-");TAB(35)STRING$(90,"-");

TAB(140)STRING$(18,"-")

8020 IF 1=15 THEN LPRINT "--  MAIN ";STRING$(17,"-");TAB(45)STRING$

(80,"-");TAB(126)"NDP=SUM(DP)/W";TAB(140)STRINGS(18,"-")

8022 IF 1=18 THEN LPRINT STRING$(26,"-");TAB(36)"DEG";TAB(45)STRING$

(80,"-");TAB(140)STRING$(18,"-")

8024 IF 1=20 THEN LPRINT "-  ROLL ";STRING$(17,"-");TAB(45)STRING$

(39,"-");TAB(84)"VMP=.665W";TAB(100)STRING$(23,"-");TAB(140)STRING$

(18,"-")

8026 IF 1=22 THEN LPRINT "--  GEAR ";STRING$(17,"-");TAB(36)"LINE";

TAB(45)STRING$(38,"-");TAB(100)STRING$(25,"-");TAB(140)STRINGS(18,"-") 
8028 IF 1=24 THEN LPRINT STRING$(33,"-");TAB(45)STRING$(113,"-") 
8030 NEXT I

275

FAR 23 LOADS

8040 FRM$="ftft \                \ f# \     \ \       \ \            \

###### ^#^# ####f #####"

8042 FOR 1=25 TO 33 :LPRINT USING FRM$;I;DE$(I);CG(I);POL$(I);FAA$(I) ;

EQN$ (I ) ;VNP(I);DNP(I);SNP (I ) ;RESULT(I)

8050 IF 1=27 THEN LPRINT "-- MENTARY ";STRINGS (20,"-");TAB(60)STRING$

(24,"-")

8052 IF 1=30 THEN LPRINT "-- WHEEL "; STRING$(23,"-");TAB(60)STRING$

(24,"-")

8054 IF 1=33 THEN LPRINT STRING$(157,"-" )

8060 NEXT I

8095 REM--------------------------------------------------------------

8096 REM    PRINT OUT HEADINGS FOR LOADS RELATIVE TO AIRPLANE DATUM

8097 REM-------------------------------------------------------------

9000 LPRINT CHR$(12) 
9010 LPRINT "LIMIT GROUND REACTIONS AND LOAD FACTORS";TAB(82)"CG ";

CG(3);TAB(88)WCG(3);" LBS XCG=";XCG(3);TAB(114)"ZCG=";ZCG(3) 
9020 LPRINT STRING$(39,"-");TAB(82)"CG ";CG(2);TAB(88)WCG(2);" LBS

XCG=";XCG(2);TAB(114)"ZCG=";ZCG(2) 
9030 LPRINT "VALUES ARE WITH RESPECT TO AIRPLANE DATUM";TAB(82)"CG ";

CG(1);TAB(88)WCG(1);" LBS XCG=";XCG(1);TAB( 114 ) "ZCG=";ZCG(1)

9040 LPRINT STRINGS(154,"-")

9050 LPRINT "CASE CONDITION" ; TAB( 25 ) "CG POINT" ; TAB( 35 )"<- ------

NOSE GEAR -------- - > " ; TAB C 81 ) " <- ------ MAIN GEAR - - - -

9060 LPRINT STRINGS(23,"-");TAB(29)"OF";TAB(35)STRING$(119,"-") 
9070 LPRINT " NO";TAB(6)"DESCRIPTION";TAB(25)"NO LOAD";TAB(37)"PHIN" ;

TAB(43)"RESULT";TAB(50)"EQUATIONS";TAB(64)"VN" ;TAB(71)"DN";TAB(76)"SN" 
;TAB(81)"PHIM";TAB(89)"RESM";TAB(94)"EQUATIONS";TAB(111)"VM";TAB(117) 
"DM";TAB(123)"SM";

9080 LPRINT TAB(130)"NR"; TAB(137)"NV";TAB(145)"ND";TAB(153)"NS"

9085 REM-------------------------------------------------------------

9086 REM   SET UP ARRAYS FOR LOADS RELATIVE TO AIRPLANE DATUM

9087 REM-------------------------------------------------------------

9090 LPRINT STRINGS(153,"-") 
9100 EQNGD$(1)="VN=RCOS(PHIN)" 
9110 EQNGD$(13)="VN=RCOS(PHIN)" 
9115 EQNGD$(28)="VN=RCOS(PHIN)" 
9120 EQNGD$(2)="DN=RSIN(PHIN)" 
9130 EQNGD$(14)="DN=RSIN(PHIN)" 
9140 EQNGD$(29)="DN=RSIN(PHIN)" 
9150 EQNGD$(3)="SN=SNP" 
9160 EQNGD$(15)="SN=SNP" 
9170 EQNGD$(30)="SN=SNP" 
9180 EQNGD$(4)="NOSE" 
9190 EQNGD$(7)="NOSE" 
9200 EQNGD$(10)="NOSE" 
9210 EQNGD$(16)="NOSE" 
9220 EQNGD$(5)="WHEEL" 
9230 EQNGD$(8)="WHEEL" 
9240 EQNGD$(11)="WHEEL" 
9250 EQNGD$(17)="WHEEL" 
9260 EQNGD$(19)="NOSE WHEEL" 
9270 EQNGD$(21)="NOSE WHEEL" 
9280 EQNGD$(23)="NOSE WHEEL" 
9290 EQNGD$(6)="CLEAR"

276

LANDING LOADS

9300 EONGD$(9)="CLEAR"

9305 EONGD$(12)="CLEAR"

9310 EONGD$(18)="CLEAR"

9320 EQNGD$(20)="CLEAR"

9330 EONGD$(22)="CLEAR"

9340 EQNGD$(24)="CLEAR"

9350 EQNGD$(25)=" "

9360 EQNGD$(26)=" "

9370 EQNGD$(27)=" "

9380 EQNGD$(31)=" "

9390 EQNGD$(32)=" "

9400 EQNGD$(33)=" "

9410 EQMGD$(1)=" "

9420 EOMGD$(2)=" "

9430 EQMGD$(3)=" "

9440 EQMGD$(4)=" "

9450 EQMGD$(5)="VM=RCOS(PHIM)"

9460 EQMGD$(6)=" "

9470 EQMGD$(7)="DM=RSIN(PHIM)"

9480 EQMGD$(8)=" "

9490 EQMGD$(9)="SM=SMP"

9500 FOR 1=10 TO 33:EQMGD$(I)=" ":NEXT

9600 FOR 1=1 TO 24

9610 NR(I)=(NV(I)"2+ND(I)"2)~.5

9620 NEXT I

9979 REM---------------- ------------

9980 REM    PRINT LOADS WITH RESPECT TO AIRPLANE DATUM

9981 REM- --------------------------------------------------------

9990 FRM2$="^ \                \ ## \     \W.### #### \

\#W #W# >m M.##> #ft### \          \ ##### Wftft

###^# #.### >.>>> ##.M >#.^#" 
9995 REM ROUTINE TO PRINT LOADS WITH RESPECT TO AIRPLANE REFERENCE

AXES

10000 FOR 1=1 TO 24 
10010 LPRINT USING FRM2$;I;DE$(I);CG(I);POL$(I);PHIN(I);RESULT(I);

EONGD$(I);VN(I);DN(I);SN(I);PHIM(I);RMP(I);EQMGD$(I);VM(I);DM(I);

SMP(I);NR(I);NV(I);ND(I);NS(I)

10020 IF 1=3 THEN LPRINT STRING$(25,"-");TAB(35)STRING$(59,"-");

TAB(110)STRING$(45,"-")

10021 IF 1=6 THEN LPRINT STRING$(25,"-");TAB(35)STRING$(59,"-") ;

TAB(110)STRING$(45,"-")

10022 IF 1=9 THEN LPRINT " "

10023 IF 1=9 THEN LPRINT STRING$(25,"-");TAB(35)STRING$(59,"-");

TAB(110)STRING$(45,"-")

10024 IF 1=12 THEN LPRINT TAB(5)"LEFT WHEEL LOADED"

10025 IF 1=12 THEN LPRINT STRING$(25,"-");TAB(35)STRING$(59,"-") ;

TAB(110)STRING$(45,"-")

10026 IF 1=15 THEN LPRINT"- MAIN";TAB(15)STRING$(79,"-");TAB(110) 
STRING$(45,"-")

10027 IF 1=18 THEN LPRINT STRING$(25,"-");TAB(35)STRING$(59,"-") ;

TAB(110)STRING$(45,"-")

10028 IF 1=20 THEN LPRINT STRING$(25,"-");TAB(35)STRING$(59,"-");

TAB(110)STRING$(45,"-")

10029 IF 1=22 THEN LPRINT STRING$(25,"-");TAB(35)STRING$(59,"-");

277

FAR 23 LOADS

TAB(110)STRING$(45,"-")

10030 IF 1=24 THEN LPRINT STRING$(154,"-" )

10031 NEXT I

10039 FRM3$="## \                \ ^ \     Vftft^.W #^# \ 
\W# ##tt# ^t#r'

10040 FOR 1=25 TO 33

10050 LPRINT USING FRM3$;I;DE$(I);CG(I);POL$(I);PHIN(I);RESULT(I);

EQNGD$(I);VN(I);DN(I);SNP(I)

10060 IF 1=27 THEN LPRINT "-- MENTARY";TAB(15)STRING$(32,"-");

TABf62)STRING$(17,"-")

10070 IF 1=30 THEN LPRINT "--";TAB(15)STRING$(32,"-");TAB(62)STRING$

(17,"-")

10080 IF 1=33 THEN LPRINT STRING$(78,"-")

10090 NEXT I

10891 REM-------------------------------------------------------------

10892 REM    CALCULATE UNBALANCED ROL, PITCH AND YAW MOMENTS

10893 REM---------------------------------------------------------------

10900 FOR 1=1 TO 6:GA(I)=GRA(1):NEXT I

10910 FOR 1=7 TO 9 :GA( I )=GRA( 3 ) .-NEXT I

10920 FOR 1=10 TO 12:GA(I)=GRAf1):NEXT I

10930 FOR 1=13 TO 24:GAfI)=GRA(2):NEXT I

11000 FOR 1=1 TO 24

11010 ROLL(I)=ROLLP(I)*COS(GA(I)/57.3)+YAWP(I)*SIN(GA(I)/57.3)

11020 YAW(I)=YAWP(I)*COS(GA(I)/57.3)-ROLLP(I)*SIN(GA(I)/57.3)

11030 NEXT I

11035 PRINT "I","ROLL(I)","YAW(I)"

11040 FOR 1=1 TO 24:PRINT I,ROLL(I),YAW(I):NEXT I

12000 LPRINT CHR$fl2)

12005 REM------------------------------------------------------------

12006 REM    PRINT HEADINGS FOR UNBALANCED MOMENTS

12007 REM-------------------------------------------------------------

12010 LPRINT "LIMIT UNBALANCED MOMENTS";TAB(88)"CG ";CG(3);TAB(94) 
WCG(3);" LBS XCG=";XCG(3);TAB(120)"ZCG=";ZCG(3) 
12020 LPRINT STRINGS(24,"-");TAB(88)"CG ";CG(2);TAB(94)WCG(2);" LBS

XCG=";XCG(2);TAB(120)"ZCG=";ZCG(2) 
12030 LPRINT "VALUES ARE WITH RESPECT TO GROUND LINE - DENOTED BY

P(PRIME) AND TO AIRPLANE DATUM";TAB(88)"CG ";CG(1);TAB(94)WCG(1);"

LBS XCG=";XCG(1);TAB(120)"ZCG=";ZCG(1) 
12035 LPRINT STRINGS(129,"-") 
12040 LPRINT "CASE CONDITION";TAB(25)"CG POINT";TAB(36)"<- - - -

RELATIVE TO GROUND LINE ------><----- RELATIVE TO AIRPLANE

DATUM ---->"

12050 LPRINT STRING$(23,"-");TAB(29)"OF";TAB(35)STRING$(95,"-") 
12060 LPRINT " NO DESCRIPTION";TAB(25)"NO LOAD";TAB(36)"EQUATIONS";

TAB(54)"PITCHING";TAB(64)"ROLLING";TAB(75)"YAWING";TAB(83)"EQUATIONS" ;

TAB(100)"PITCHING";TAB(111)"ROLLING";TAB(122)"YAWING" 
12070 LPRINT STRING$(129,"-")

12080 FRM6$="## \                \ #^ \     \ \                \ 
ftttft###f ####### ####### \                \ #^##^ ####^#

#######"

12095 REM-------------------------------------------------------------

12096 REM     SET UP ARRAYS FOR UNBALANCED MOMENTS

12097 REM------------------------------------------------------------

12100 FOR 1=1 TO 24:EQMOMP$(I)=" ":NEXT I

278

LANDING LOADS

12110 EQMOMP$(4)="PMOMP=-2RM*BP"

12130 EQMOMP$(10)="PMOMP=-RM*BP"

12140 EQMOMP$(11)="RMOMP=VMP*TREAD/2"

12150 EQMOMP$(12)="YMOMP=DMP*TREAD/2"

12170 EOMOMP$(16)="PMOMP=-2(VMP*BP+"

12180 EQMOMP$(17)="        DMP*CP)"

12190 EQMOMP$(19)="PMOMP=-2VMP*BP"

12200 EQMOMP$(20)="RMOMP=-.83W*CP"

12300 FOR 1=1 TO 24 : EQMOM$ ( I )=" "-.NEXT I

12310 EOMOM$(10)="PMOM=PMOMP"

12320 EQMOM$<12)="RMOM=RMOMP*COS(GA)"

12330 EQMOM$(13)="YMOM=YMOMP*COS9GA)"

12340 EQMOM$(14)="    -RMOMP*SIN(GA) "

12395 REM--------------------------------------------------------------

12396 REM     PRINT OUT UNBALANCED MOMENTS

12397 REM-------- -.-----------------------.---.-----------------.--

12400 FOR 1=1 TO 24

12410 LPRINT USING FRM6$;I;DE$(I);CG(I);POL$(I);EQMOMP$(I);PITCHP(I);

ROLLP(I);YAWP(I);EQMOM$(I);PITCHP(I);ROLL(I);YAW(I)

12420 IF 1=3 THEN LPRINT STRING$(26,"-");TAB(35)STRING$(47,"-") ;

TAB(102)STRINGS(28,"-")

12430 IF 1=6 THEN LPRINT STRING$(26,"-");TAB(53)STRING$(29,"-");

TAB(102)STRINGS(28,"-")

12435 IF 1=9 THEN LPRINT " "

124,40 IF 1=9 THEN LPRINT STRING$(26, "-" ) ;TAB( 35 )STRJ.NG$( 47 , "-");

TAB (102)STRINGS(28,"-")

12450 IF 1=12 THEN LPRINT TAB(5)"LEFT WHEEL LOADED";TAB(87)"+YMOMP*

SIN(GA)"

12460 IF 1=12 THEN LPRINT STRINGS(26,"-");TAB(35)STRING$(47,"-");

TAB(102)STRING$(28,"-")

12470 IF 1=15 THEN LPRINT "-- MAIN";TAB(14)STRING$(68,"-");TAB(102 )

STRING$(28,"-")

12480 IF 1=18 THEN LPRINT STRING$(26,"-");TAB(35)STRING$(47,"-");

TAB(102)STRING$(28,"-")

12490 IF 1=20 THEN LPRINT ST1RING$( 26 ,"-") ;TAB(53 )STRING$(29 ,"-");

TAB(102)STRING$(28,"-")

12500 IF 1=22 THEN LPRINT STRING$(26,"-" h'TAB(53)STRING$(29,"-");

TAB(102)STRING$(28,"-")

12510 IF 1=24 THEN LPRINT STRING$(129,"-")

12520 NEXT I

279

FAR 23 LOADS

Example input and output  for Landing Gear Geometry:

CALCULATION OF LANDING GEAR GEOMETRY 
INPUT

MAX LANDING WEIGHT = 3230

GROSS WEIGHT = 3400

GEAR LOAD FACTOR = 2.5

WING LIFT FACTOR = .667

XMG 25 % DEF = 96.3 ZHG 25 % DEF = 55.9

XNG 25 % DEF = 1.9 ZNG 25 9. DEF = 46.9

XMG STATIC DEF = 96.7 ZMG STATIC DEF =  59.6

XNG STATIC DEF = 2.4 ZNG STATIC DEF =  49.5

XNG FULLY EXTENDED DEF = 1.6     ZNG FULLY EXTENDED DEF :=  45.1  REF

XHG FULLY EXTENDED DEF = 96.2    ZMG FULLY EXTENDED DEF =  54.2  REF

ROLLING RADIUS MAIN GEAR = 8

ROLLING RADIUS NOSE GEAR = 5.7

TREAD BETWEEN MAIN WHEELS = 114.5

TAIL DOWN ANGLE GROUND TO WL = 15

WEIGHT/CG DATA:

CG NO         WCG XCG ZCG

5             3230 85.1          93

6             3230 76.12         93

7             2800 72.64         92

CALCULATED LANDING GEAR GEOMETRY

DRAG LOAD FACTOR, K =                              +0.324 
GAMMA = ARCTAN(K) =                               +17.978 
GROUND ANGLE FOR 3 WHEEL LEVEL LANDING =           -4.057 
GROUND ANGLE FOR LEVEL LANDING NOSE WHEEL CLEAR =  -4.057 
GROUND ANGLE FOR GROUND ROLL =                     -4.724 
GROUND ANGLE FOR TAIL DOWN ATTITUDE =             +15.000 
BETA = GAMMA - GROUND ANGLE = ANGLE BETWEEN RESULTANT LOAD AND FUS STA 
BETA FOR 3 WHEEL LEV LAND =                       +13,921 
BETA FOR LEV LAND NOSE WHEEL CLEAR =              +13.921 
BETA FOR GROUND ROLL =                             -4.724 
BETA FOR TAIL DOWN ATTITUDE =                     +15.000

AP        BP        DP       CP 
3 PT AND 2 PT LEV LAND FOR CG NO  5  69.666    19.796    89.462 
3 PT AND 2 PT LEV LAND FOR CG NO  6  60.95     28.512    89.462 
3 PT AND 2 PT LEV LAND FOR CG NO  7  57.812    31.649    89.462 
GROUND ROLL FOR CG NO  5             86.001    8.809     94.011    42.136 
GROUND ROLL FOR CG NO  6             77.052    17.759    94.811    42.879 
GROUND ROLL FOR CG NO  7             73.501    21.309    94.811    42.17 
TAIL DOWN ATTITUDE FOR CG NO  5      0         1.216     0 
TAIL DOWN ATTITUDE FOR CG NO  6      0         9.890001  0 
TAIL DOWN ATTITUDE FOR CG NO  7      0         13.511    0