Program Date 04/30/04

Rigid Pavement Design For AC Method

Airport Name: Any Airport Date: today's date
Associated City: Anywhere, USA
Design Firm: Engineer's Are Us Designer: Joe Engineer
AIP Number: 3-XX-XXX-XX
New Pavement Section Required Stabilized Subbase Is Required
15.3 PCC Thickness 700 psi New Concrete Flexural Strength
15.0 Stabilized Base
0.0 Subbase
0.0 Non-Frost Layer (free draining material)
Large Aircraft Parallel to Joints (standard design)
Overlay Sections
N/A Asphalt Overlay Thickness N/A Existing Slab Thickness
N/A Unbonded PCC without leveling course N/A PCC needed for existing section
N/A Unbonded PCC with leveling course N/A Existing Stabilized Subbase
N/A Bonded PCC N/A Existing Aggregate Subbase
N/A Existing Slab Flexural Strength
N/A F- Factor used in design
N/A Cr Factor
N/A Cb Factor

Frost Considerations (for new pavement section)

Dry Unit Weight of Soil (lb/cf ) 100
Degree Days ºF 250
Soil Frost Code Non-Frost Subgrade k-value was not modified for frost
Frost Depth Penetration (in) 22.53
k value on top of stabilized layer 366
k value on top of subbase layer 82
Original subgrade k value 82

Design Aircraft Information

DUAL WH-150 20 Design Life (years)
170000 lbs Gross Aircraft Weight
26,156 Equivalent Annual Departures

See Appendix 5 to AC 150/5320-6D for application of this software.

 FAA Rigid Pavement Design AC 150/5320-6D
Design Pavement Section
PCC Pavement
Stabilized Subbase Layer
Aggregate Subbase Layer
Subgrade
L
ayer

To assure correct answers - complete each step in

numerical order. If data is changed in any given step,
complete each step below that step.

This software may be used as noted in Appendix 5 of AC 150/5320-6D, Airport Pavement Design and Evaluation.
e each step in
in any given step,

uation.
Step 4 ENTER AIRCRAT DATA
(below)

Enter up to 21 aircraft (in any order) See right for Large Aircraft Optional design

e.g. Citation IV

weight MTOW

Each Individual
User's name for

Gear type AC

Default
150/5320-6D

Max Takeoff
grouping ----

Required for
Departures

Thickness
(optional)

.
Aircraft

Aircraft

Aircraft
Weight

Annual
.
B727-100 DUAL WH-150 3 170,000 26,156 15.35
None 2 0 0 0.00
None 0 0 0.00
None 2 0 0 0.00
None 0 0 0.00
None 2 0 0 0.00
None 0 0 0.00
None 0 0 0.00
None 0 0 0.00
None 0 0 0.00
None 0 0 0.00
None 2 0 0 0.00
None 0 0 0.00
None 0 0 0.00
None 0 0 0.00
None 0 0 0.00
None 0 0 0.00
None 0 0 0.00
None 0 0 0.00
None 0 0 0.00
None 0 0 0.00
Large Aircraft Design
Gear Parallel to Joints (standard)

Gear Skew to Joints (optional)

Recommended Critical Aircraft

 Required thickness for DUAL WH-150 at 170000 lbs k on top of all subbase = 366 psi PCC
Flexural Strength = 700

18
PCC THICKNESS (in)

17.5

17.08
17.04
16.99
16.94
16.89
16.83
17

16.77
16.71
16.64
16.57
16.5
16.41
16.32

16.5
16.22
16.11
15.99

16

15.5

15
1

10

11

12

13

14

15

16
ANNUAL DEPARTURES
i PCC
 From Aircraft Table
Aircraft Gross Load GL 170000 DUAL WH-150
9
Factor RGL 1 Initial thickness guess 12.470942
% load on gear WLP 0.475 Final thickness 15.347643
Coverage Factor RCA 3.48
Gear Type IGEAR 2 this variable used to determine load configuration (edge or center)
# wheels per gear ITW 2 1 find RC values
RC0 -1.7515 -1.75 -1.7515
RC1 0.611436 0.611 0.611436
RC2 0.07185 0.072 0.07185
RC0-2 0 0 Allowable Sig75 = 717.9487
RC1-2 0 0 B= 112.473214286
RC2-2 0 0
annual departures 26156 CONS = 931.7103
years design 20 CT4 = 1807085.2761
CT4 check 1807085.2761
DF 1.3 Radius of Relative thickness RR= 36.6644
Flex Strength 700 700 <-- New PCC Flex check RR 36.6644
Poisson Ratio 0.15
Concrete Modulus 4,000,000 Stress TH2 155.5375
check Th2 155.5375
Subgrade k value 366 TH2^0.5 12.47147
Difference 5.2590E-04

addition for traffic

total passes for 20 yrs 150321.84
Bb = 0.15603
RH = 1.23062046611

Total thickness = 15.34764335

15.34764 <--hidden value of thickness required for new design

Thick from new flex & exist section 15.3476433504

6 Existing slab thickness thick from existing Flex & section 16.1844312524
650 Existing Slab Strength
0.879548 F Factor 0.879547894
0.87 Cr Factor 2
0.96 Cb Factor 0

19.34747 thickness of AC overlay

12.69141 12.69141 thickness of unbonded PCC overlay without leveling course
14.29091 14.29091 Thickness of unbonded PCC overlay with leveling course
9.347643 9.347643 Bonded

SUBGRADE K value as improved by Aggregate layer

Original k input starting K value
starting subgrade K value 82 82 if check for zero
 if check for zero 82 Frost k Thickness of stabilized layer
Thickness of aggregate layer 0.0 0.00
type of aggregate material TRUE
K<50 K > 50 S=
Y= 1 166.3862 8.43862
X = 1.913813852
sk for <50 82 SK for >50 82

Final SK to use 500 or less 82

82
0.0
 departure thickness rounded x-grid xgrid
LOOKUP AIRCRAFT DATA 3000 3000 15.98508 15 15.99 3000 15
150000 3400 16.11017 16.11 3000 18
1 3800 16.22132 16.22 3400 18
0.475 4200 16.32134 16.32 3400 15
3.48 4600 16.41226 16.41 3800 15
2 5000 16.49559 16.5 3800 18
2 5400 16.5725 16.57 4200 18
-1.7515 5800 16.64391 16.64 4200 15
0.611436 6200 16.71056 16.71 4600 15
0.07185 6600 16.77304 16.77 4600 18
0 7000 16.83185 16.83 5000 18
0 7400 16.88738 16.89 5000 15
0 7800 16.93999 16.94 5400 15
8200 16.98997 16.99 5400 18
8600 17.03757 17.04 5800 18
9000 9000 17.083 18 17.08 5800 15
USED TO MAKE CHART 6200 15
Required thickness for DUAL WH-150 at 6200 18
6600 18
718.01 6600 15
7000 15
7000 18
7400 18
7400 15
7800 15
7800 18
8200 18
8200 15
8600 15
15.35000000 8600 18
9000 18
ess required for new design 9000 15

used for overlay design

used for light aircraft issues
<-- cell used for light aircraft minimum thickness notification

Stabilized subbase material

starting K value 82
if check for zero 82
ckness of stabilized layer 15.0

K<50 K > 50 S =
Y = 0.4073802778 166.39 10
X = 2.4729601297
sk for <50 297.1393231 SK for >50 366.3862

Final SK to use 500 or less 366.3862

366
15.0
xlabels PSI PSI thickness rounded x-grid xgrid xlabels
15 500 500 19.5507 14 19.55 500 14 14
15 520 19.04561 19.05 500 20 14
15 540 18.57072 18.57 520 20 14
15 560 18.12321 18.12 520 14 14
15 580 17.70061 17.7 540 14 14
15 600 17.30075 17.3 540 20 14
15 620 16.92171 16.92 560 20 14
15 640 16.56179 16.56 560 14 14
15 660 16.21947 16.22 580 14 14
15 680 15.89339 15.89 580 20 14
15 700 15.58234 15.58 600 20 14
15 720 15.28524 15.29 600 14 14
15 740 15.00109 15 620 14 14
15 760 14.729 14.73 620 20 14
15 780 14.46816 14.47 640 20 14
15 800 800 14.21784 20 14.22 640 14 14
USED TO MAKE CHART 660 14
Required thickness for DUAL WH-150 at660 20
680 20
680 14
700 14
700 20
720 20
720 14
740 14
740 20
760 20
760 14
780 14
780 20
800 20
800 14
 Required thickness for DUAL WH-150 at 170000 lbs k on top of all subbase = 366 psi 26156
departures -- subgrade k = 82
20
19.55
PCC THICKNESS (in)

19.05
19
18.57

18.12
18
17.7

17.3

16.92
17

16.56

16.22

15.89
16

15.58

15.29

15

14.73
15

14.47

14.22
14
1

10

11

12

13

14

15

16
PCC Flexural Strength
26156
Any Airport AIP Number AC Method
Anywhere, USA 3-XX-XXX-XX today's date
Engineer's Are Us Joe Engineer
INPUT VALUES

% load on main gear

Computed wheel
MTOW used by
weight MTOW

Load of aircraft
Gear type AC

design Aircraft
Equiv. annual
Departures of
150/5320-6D

Max Takeoff

departures of
grouping ----
Widebody?

Departures

Gear Type

equiv gear
Aircraft

Annual

design
(code)
Design Aircraft --- /---
Additional aircraft
B727-100 n DUAL WH-150 3 170,000 26,156 2 0.95 170,000 26,156 40,375 26,156
n None 2 0 0 0 0.00 0 0 0 0
n None 0 0 0 0.00 0 0 0 0
n None 2 0 0 0 0.00 0 0 0 0
n None 0 0 0 0.00 0 0 0 0
n None 2 0 0 0 0.00 0 0 0 0
n None 0 0 0 0.00 0 0 0 0
n None 0 0 0 0.00 0 0 0 0
n None 0 0 0 0.00 0 0 0 0
n None 0 0 0 0.00 0 0 0 0
n None 0 0 0 0.00 0 0 0 0
n None 2 0 0 0 0.00 0 0 0 0
n None 0 0 0 0.00 0 0 0 0
n None 0 0 0 0.00 0 0 0 0
n None 0 0 0 0.00 0 0 0 0
n None 0 0 0 0.00 0 0 0 0
n None 0 0 0 0.00 0 0 0 0
n None 0 0 0 0.00 0 0 0 0
n None 0 0 0 0.00 0 0 0 0
n None 0 0 0 0.00 0 0 0 0
n None 0 0 0 0.00 0 0 0 0
Equivalent Annual Departures of the DUAL WH-150 26,156