pavimento rígido.xls

7/30/2019 Pavimento Rgido.xls

1/13

Program Date 02/10/03

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 Not Required0.0 PCC Thickness 650 psi New Concrete Flexural Strength

6.0 Stabilized Base

4.0 Subbase

0.0 Non-Frost Layer (free draining material)

Large Aircraft Parallel to Joints (standard design)

Overlay SectionsN/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 FactorN/A Cb Factor

Frost Considerations (for new pavement section)

Dry Unit Weight of Soil (lb/cf ) 100

Degree Days F 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 253

k value on top of subbase layer 130

Original subgrade k value 100

Design Aircraft Information


2/13

Design Pavement Section

FAA Rigid Airport Pavement Design

PCC Pavement

Stabilized Subbase

Aggregate Subbase

Subgrade

To assure correct answers - complete ea

numerical order. If data is changed in a

complete each step below that step.

This software is currently under development and is not officially adopted as a FAA standard. Designs developed

should be checked against AC 150/5320-6D to insure accuracy and conformance to existing standards


3/13

ayer

Layer

h step in

y given step,

using this program


4/13

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

User'snamefor

Aircraft

(optional)

e.g.CitationIV

Aircraftgrouping

----Geartype

AC150/5320-6D

. . DefaultWeight

MaxTakeoff

weightMTOW

Annual

Departures

Thickness

Requiredfor

EachIndividual

Aircraft

3 0 0 0.00

2 0 0 0.00

0 0 0.00

2 0 0 0.00

0 0 0.00

2 0 0 0.00

0 0 0.00

0 0 0.000 0 0.00

0 0 0.00

0 0 0.00

2 0 0 0.00

0 0 0.00

0 0 0.00

0 0 0.00

0 0 0.00

0 0 0.00

0 0 0.00

0 0 0.00

0 0 0.00

Step 4 ENTER AIRCRAT DATA

(below)


5/13

Recommended Critical Aircraft







Recommended Critical AircraftRecommended Critical Aircraft












Gear Parallel to Joints (standard)

Gear Skew to Joints (optional)

arge rcra esgn


6/13

15.99 1

6.11 1

6.22 1

6.32

16.41

16.5 16.

57

1

6.64

16.71

16.77

16.83

16.89

16.94

16.99

17.04

17.08

3000

3400

3800

4200

4600

5000

5400

5800

6200

6600

7000

7400

7800

8200

8600

9000

15

15.5

16

16.5

17

17.5

18

PCCTHICKNESS

(in)

ANNUAL DEPARTURES

Required thickness for None at 0 lbs k on top of all subbase = 253 psi PCC Flexural

Strength = 650


7/13

From Aircraft Table

Aircraft Gross Load GL 0 1Factor RGL 0 Initial thickness guess 10.000000

% load on gear WLP 0 Final thickness 0.000000

Coverage Factor RCA 0

Gear Type IGEAR 0 this variable used to determine load configuration (edge or center)

# wheels per gear ITW 0 1 find RC values

RC0 0 0 0

RC1 0 0 0

RC2 0 0 0

RC0-2 0 0 Allowable Sig75 = 666.6667

RC1-2 0 0 B= #DIV/0!

RC2-2 0 0

annual departures 0 CONS = 1347.8497

years design 20 CT4 = 1347849.6743

CT4 check 1347849.6743

DF 1.3 Radius of Relative thickness RR= 34.0730

Flex Strength 650 650


8/13

if check for zero 100 Frost k Thickness of stab

Thickness of aggregate layer 4.0 0.00

type of aggregate material FALSEK 50 S =

Y = 0.873695301 175 7.5

X = 2.088283195

sk for 50 130

Final SK to use 500 or less 130

130

4.0


9/13

departure thickness rounded x-grid xgrid

LOOKUP AIRCRAFT DATA 3000 3000 15.98508 15 15.99 3000 15

0 3400 16.11017 16.11 3000 180 3800 16.22132 16.22 3400 18

0 4200 16.32134 16.32 3400 15

0 4600 16.41226 16.41 3800 15

0 5000 16.49559 16.5 3800 18

0 5400 16.5725 16.57 4200 18

0 5800 16.64391 16.64 4200 15

0 6200 16.71056 16.71 4600 15

0 6600 16.77304 16.77 4600 18

0 7000 16.83185 16.83 5000 180 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 None at 0 lbs k o 6200 18

6600 180.00 6600 15

7000 15

7000 18

7400 18

7400 15

7800 15

7800 18

8200 18

8200 15

8600 15

0.00000000 8600 18

9000 18

new design 9000 15


10/13

ilized layer 6.0

K 50 S =Y = 0.698232404 232.83 10

X = 2.338273354

sk for 50 252.8292

Final SK to use 500 or less 252.8292

253

6.0


11/13

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 1415 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 None at 0 lbs k 660 20

680 20680 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


12/13

19.55

1

9.05

18.57

18.12

17.7

17.3

16.9

2

16.56

16.22

15.89

15.58

15.29

15

14.73

14.47

14.22

500

520

540

560

580

600

620

640

660

680

700

720

740

760

780

800

14

15

16

17

18

19

20

PCCTHICKNESS(in)

PCC Flexural Strength

Required thickness for None at 0 lbs k on top of all subbase = 253 psi 0 departures --

subgrade k = 100


13/13

Any Airport AIP Number AC Method

Anywhere, USA 3-XX-XXX-XX today's date

Engineer's Are Us Joe Engineer

INPUT VALUES

Design Aircraft --- /---

Additional aircraft Widebody?

Aircraftgrou

ping

----Geartype

AC150/5320

-6D

MaxTakeoff

weightMTO

W

Annual

Departures

GearType

(code)

%loadonmaing

MTOWused

by

design

Departuresof

equivgear

Computedwheel

Loadofaircr

aft

Equiv.annua

l

departuresof

designAircraft

n 3 0 0 0 0.00 0 0 0 0

n 2 0 0 0 0.00 0 0 0 0

n 0 0 0 0.00 0 0 0 0

n 2 0 0 0 0.00 0 0 0 0

n 0 0 0 0.00 0 0 0 0

n 2 0 0 0 0.00 0 0 0 0n 0 0 0 0.00 0 0 0 0

n 0 0 0 0.00 0 0 0 0

n 0 0 0 0.00 0 0 0 0

n 0 0 0 0.00 0 0 0 0

n 0 0 0 0.00 0 0 0 0

n 2 0 0 0 0.00 0 0 0 0

n 0 0 0 0.00 0 0 0 0

n 0 0 0 0.00 0 0 0 0

n 0 0 0 0.00 0 0 0 0n 0 0 0 0.00 0 0 0 0

n 0 0 0 0.00 0 0 0 0

n 0 0 0 0.00 0 0 0 0

n 0 0 0 0.00 0 0 0 0

n 0 0 0 0.00 0 0 0 0

n 0 0 0 0.00 0 0 0 0

Equivalent Annual Departures of the None 0

pavimento rígido.xls

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