DOT/FAA/AR-MMPDS-01 Office of Aviation Research Washington, D.C. 20591

Metallic Materials Properties Development and Standardization (MMPDS) January 2003 Scientific Report This document is available to the U.S. public through the National Technical Information Service, Springfield (NTIS), Virginia 22161.

U.S. Department of Transportation Federal Aviation Administration

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Table 3.2.8.0(a). Material Specificationsfor 2219 Aluminum Alloy

Specification Form

AMS 4031AMS-QQ-A-250/30AMS 4162AMS 4163AMS 4144

Sheet and plateSheet and plateExtrusionExtrusionHand forging

3.2.8 2219 ALLOY

3.2.8.0 Comments and Properties 2219 is an Al-Cu alloy available in a wide variety ofproduct forms. As shown in Table 3.1.2.3.1(a), 2219-T351X and -T37 rolled plate and extruded shapes havea D SCC rating. This is the lowest rating and means that SCC failures have occurred in service or wouldbe anticipated if there is any sustained stress. In-service failures are caused by stressed produced by anycombination of sources including solution heat treatment, straightening, forming, fit-up, clamping, sustainedservice loads or high service compression stresses that produce residual tensile stresses. These stresses maybe tension or compression as well as the stresses due to the Poisson effect, because the actual failures arecaused by the resulting sustained shear stresses. Pin-hole flaws in corrosion protection are sufficient for SCC.Refer to Section 3.1.2.3 for comments regarding the resistance of the alloy to stress-corrosion cracking, andto Section 3.1.3.4 for comments regarding the weldability of the alloy. It has been used in critical cryogenicapplications as well as those applications in which high strength and creep resistance at relatively hightemperatures (400 to 600EF) are required.

The properties of extrusions should be based upon the thickness at the time of quenching prior tomachining. Selection of the mechanical properties based upon its final machined thickness may beunconservative; therefore, the thickness at the time of quenching to achieve properties is an important factorin the selection of the proper thickness column. For extrusions having sections with various thicknesses,consideration should be given to the properties as a function of thickness.

Material specifications for 2219 are presented in Table 3.2.8.0(a). Room-temperature mechanicaland physical properties are shown in Tables 3.2.8.0(b1) through (d). The effect of temperature on the physicalproperties is shown in Figure 3.2.8.0.

The temper index for 2219 is as follows:

Section Temper3.2.8.1 T623.2.8.2 T81, T851, T8510, and T85113.2.8.3 T8523.2.8.4 T87

3.2.8.1 T62 Temper Elevated temperature data for this temper are presented in Figures3.2.8.1.1(a) and (b). Typical room-temperature tensile and compressive stress-strain, compressive tangent-modulus, and full-range tensile stress-strain curves for 2219 aluminum alloy sheet and plate for this temperare shown in Figures 3.2.8.1.6(a) and (b).

3.2.8.2 T81 and T851X Tempers Elevated temperature data for these tempers are presentedin Figures 3.2.8.2.1(a) and (b). Typical room-temperature tensile and compressive stress-strain, compressive

MMPDS-011 February 2003

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tangent-modulus, and full-range tensile stress-strain curves for 2219 aluminum alloy for this condition areshown in Figures 3.2.8.2.6(a) and (b). Notched fatigue data for plate are presented in Figures 3.2.8.2.8(a)through (d).

3.2.8.3 T852 Temper Typical room-temperature tensile and compressive stress-strain, com-pressive tangent-modulus, and full-range tensile stress-strain curves for 2219 aluminum alloy for this temperare shown in Figures 3.2.8.3.6(a) through (e).

3.2.8.4 T87 Temper Elevated temperature data for this temper are presented in Figures3.2.8.4.1(a) and (b). Typical room-temperature tensile and compressive stress-strain, compressive tangent-modulus, and full-range tensile stress-strain curves for 2219 aluminum alloy sheet and plate for this temperare shown in Figures 3.2.8.4.6(a) through (e).

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Tab

le 3

.2.8

.0(b

1).

D

esi

gn

Mech

an

ica

l a

nd

Ph

ysic

al

Pro

pert

ies

of

2219 A

lum

inu

m A

lloy

Sheet

an

d P

late

Spec

ifica

tion

....

.A

MS

4031

&A

MS-

QQ

-A-

250/

30A

MS-

QQ

-A-2

50/3

0

Form

..

....

....

.Sh

eet a

nd p

late

Tem

per

....

....

.T6

2aT8

1T8

51

Thic

knes

s, in

. ..

..0.

020-

2.00

00.

020-

0.24

90.

250-

1.00

01.

001-

2.00

02.

001-

3.00

03.

001-

4.00

04.

001-

5.00

05.

001-

6.00

0

Bas

is

....

....

...

AB

AB

AB

AB

AB

AB

AB

AB

Mec

hani

cal P

rope

rties

:F t

u, ks

i:L

....

....

...

LT

....

....

..F t

y, ks

i:L

....

....

...

LT

....

....

..F c

y, ks

i:L

....

....

...

LT

....

....

..F s

u, ks

i ..

....

..F b

rub ,

ksi:

(e/D

= 1

.5)

....

(e/D

= 2

.0)

....

F bry

b , ks

i:(e

/D =

1.5

) ..

..(e

/D =

2.0

) ..

..e,

per

cent

(S-b

asis

):LT

..

....

....

54

54

36

36

37

37

31

84

107

62

79 c

55

55

37

37

39

38

32

85

109

64

81 ...

61

62

47

46

47

48

35

95

121

76

92 c

62

63

48

47

48

49

35

96

123

78

94 ...

61

62

47

46

47

48

36

95

121

76

94 8

62

63

48

47

48

49

36

96

123

78

94 ...

61

62

47

46

47

48

36

95

121

76

92 7

62

63

48

47

48

49

36

96

123

78

94 ...

... 62 ... 45 ... ... ... ... ... ... ... 6

... 63 ... 46 ... ... ... ... ... ... ... ...

... 60 ... 44 ... ... ... ... ... ... ... 5

... 61 ... 45 ... ... ... ... ... ... ... ...

... 59 ... 43 ... ... ... ... ... ... ... 5

... 60 ... 44 ... ... ... ... ... ... ... ...

... 57 ... 42 ... ... ... ... ... ... ... 4

... 58 ... 43 ... ... ... ... ... ... ... ...

E, 1

03 k

si

....

..E c

, 103

ksi

..

...

G, 1

03 k

si .

....

.

....

....

....

10.5

10

.8

4.0

0

.33

Phys

ical

Pro

perti

es:

, l

b/in

.3 ..

....

C, K

, and

....

0.10

3Se

e Fi

gure

3.2

.8.0

a D

esig

n al

low

able

s wer

e ba

sed

upon

dat

a ob

tain

ed fr

om te

stin

g sa

mpl

es o

f mat

eria

l, su

pplie

d in

O a

nd F

tem

per,

whi

ch w

ere

heat

trea

ted

to d

emon

stra

te re

spon

se to

hea

t tre

atm

ent

by su

pplie

rs.

Prop

ertie

s obt

aine

d by

use

r may

be

low

er th

an th

ose

liste

d if

the

mat

eria

l has

bee

n fo

rmed

or o

ther

wis

e co

ld o

r hot

wor

ked,

par

ticul

arly

in th

e an

neal

ed te

mpe

r, pr

ior t

o so

lutio

n he

at tr

eatm

ent.

b B

earin

g va

lues

are

dr

y pi

n v

alue

s per

Sec

tion

1.4.

7.1.

See

Tab

le 3

.1.2

.1.1

.c

T62

and

T81

: 0.

020-

0.03

9 in

., 6

perc

ent,

0.04

0-0.

249

in.,

7 pe

rcen

t; T6

2: 0

.250

-1.0

00 in

., 8

perc

ent,

1.00

1-2.

000

in.,

7 pe

rcen

t.

MMPDS-011 February 2003

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Specification . . . . . . . . . . AMS-QQ-A-250\30Form . . . . . . . . . . . . . . . . . SheetCondition . . . . . . . . . . . . . T87Thickness, in. . . . . . . . . . . 0.020-0.039 0.040-0.249Basis . . . . . . . . . . . . . . . . . A B A BMechanical Properties: Ftu, ksi: L . . . . . . . . . . . . . . . . . 63 64 63 64 LT . . . . . . . . . . . . . . . . 64 65 64 65 Fty, ksi: L . . . . . . . . . . . . . . . . . 51 52 51 52 LT . . . . . . . . . . . . . . . . 52 53 52 53 Fcy, ksi: L . . . . . . . . . . . . . . . . . 52 53 52 53 LT . . . . . . . . . . . . . . . . 55 56 55 56 Fsu, ksi . . . . . . . . . . . . . . 36 37 36 37 Fbrua, ksi: (e/D = 1.5) . . . . . . . . . . 99 100 99 100 (e/D = 2.0) . . . . . . . . . . 126 128 126 128 Fbrya, ksi: (e/D = 1.5) . . . . . . . . . . 83 85 83 85 (e/D = 2.0) . . . . . . . . . . 96 98 96 98 e, percent (S-basis): . . . . LT . . . . . . . . . . . . . . . . 5 ... 6 ... E, 103 ksi . . . . . . . . . . . . 10.5 Ec, 103 ksi . . . . . . . . . . . 10.8 G, 103 ksi . . . . . . . . . . . . 4.0 . . . . . . . . . . . . . . . . . . 0.33Physical Properties: , lb/in.3 . . . . . . . . . . . . 0.103 C, K, and . . . . . . . . . . See Figure 3.2.8.0

a See Table 3.1.2.1.1. Bearing values are dry pin values per Section 1.4.7.1.

Table 3.2.8.0(b2). Design Mechanical and Physical Properties of 2219 Aluminum AlloySheet Continued

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Specification . . . . . . . . . . . . . AMS-QQ-A-250\30Form . . . . . . . . . . . . . . . . . . . PlateCondition . . . . . . . . . . . . . . . T87

Thickness, in. . . . . . . . . . . . . 0.250- 1.0001.001-1.500

1.501-2.000

2.001-3.000

3.001-4.000

4.001-5.000

Basis . . . . . . . . . . . . . . . . . . . A B A B A B A B A B A BMechanical Properties: Ftu, ksi: L . . . . . . . . . . . . . . . . . . . 63 64 63 64 63 64 63 64 61 62 ... ... LT . . . . . . . . . . . . . . . . . . 64 65 64 65 64 65 64 65 62 63 61 62 ST . . . . . . . . . . . . . . . . . . ... ... ... ... 59 60 56 57 52 53 ... ...

Fty, ksi: L . . . . . . . . . . . . . . . . . . . 50 51 50 51 50 51 50 51 49 50 ... ... LT . . . . . . . . . . . . . . . . . . 51 52 51 52 51 52 51 52 51 51 49 50 ST . . . . . . . . . . . . . . . . . . ... ... ... ... 51 52 50 51 48 49 ... ...

Fcy, ksi: L . . . . . . . . . . . . . . . . . . . 51 52 51 52 51 52 ... ... ... ... ... ... LT . . . . . . . . . . . . . . . . . . 53 54 52 53 52 53 ... ... ... ... ... ... Fsu, ksi . . . . . . . . . . . . . . . . 37 38 37 38 37 38 ... ... ... ... ... ... Fbrua, ksi: (e/D = 1.5) . . . . . . . . . . . . 99 100 99 100 99 100 ... ... ... ... ... ... (e/D = 2.0) . . . . . . . . . . . . 126 128 126 128 126 128 ... ... ... ... ... ... Fbrya, ksi: (e/D = 1.5) . . . . . . . . . . . . 82 83 82 83 82 83 ... ... ... ... ... ... (e/D = 2.0) . . . . . . . . . . . . 94 96 94 96 94 96 ... ... ... ... ... ... e, percent (S-basis): . . . . . . LT . . . . . . . . . . . . . . . . . . 7 ... 6 ... 6 ... 6 ... 4 ... 3 ... E, 103 ksi . . . . . . . . . . . . . . 10.5 Ec, 103 ksi . . . . . . . . . . . . . 10.8 G, 103 ksi . . . . . . . . . . . . . . 4.0 . . . . . . . . . . . . . . . . . . . . 0.33Physical Properties: , lb/in.3 . . . . . . . . . . . . . . 0.103 C, K, and . . . . . . . . . . . . See Figure 3.2.8.0

a See Table 3.1.2.1.1. Bearing values are dry pin values per Section 1.4.7.1.

Table 3.2.8.0(b3). Design Mechanical and Physical Properties of 2219 Aluminum AlloyPlate Continued

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Table 3.2.8.0(c). Design Mechanical and Physical Properties of 2219 Aluminum Alloy HandForging

Specification ...............

Form ............................

Temper ........................

Thickness, in. ..............

Basis ............................

AMS 4144

Hand Forging

T852

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Table 3.2.8.0(d). Design Mechanical and Physical Properties of 2219 Aluminum AlloyExtruded ShapesSpecification . . . . . . . . . . . . . . . . AMS 4162 and AMS 4163a

Form . . . . . . . . . . . . . . . . . . . . . . Extruded shapesTemper . . . . . . . . . . . . . . . . . . . . T8511Cross-Sectional Area, in.2 . . . . . . #25Thickness or Diameter,b in. . . . . . #0.499 0.500-2.999Basis . . . . . . . . . . . . . . . . . . . . . . S SMechanical Properties:

Ftu, ksi:L . . . . . . . . . . . . . . . . . . . . . .LTc . . . . . . . . . . . . . . . . . . . . .

Fty, ksi:L . . . . . . . . . . . . . . . . . . . . . .LTc . . . . . . . . . . . . . . . . . . . . .

Fcy, ksi:L . . . . . . . . . . . . . . . . . . . . . .LT . . . . . . . . . . . . . . . . . . . . .

Fsu, ksi . . . . . . . . . . . . . . . . . . . .Fbrud, ksi:

(e/D = 1.5) . . . . . . . . . . . . . . .(e/D = 2.0) . . . . . . . . . . . . . . .

Fbryd, ksi:(e/D = 1.5) . . . . . . . . . . . . . . .(e/D = 2.0) . . . . . . . . . . . . . . .

e, percent:L . . . . . . . . . . . . . . . . . . . . . .LTc . . . . . . . . . . . . . . . . . . . . .

58 56

42 39

43 43 33

87113

69 84

6 4

58 56

42 39

42 41 33

81107

67 82

6 4

E, 103 ksi . . . . . . . . . . . . . . . . . .Ec, 103 ksi . . . . . . . . . . . . . . . . .G, 103 ksi . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

10.5 10.8 4.0 0.33

Physical Properties:, lb/in.3 . . . . . . . . . . . . . . . . . .C, K, and . . . . . . . . . . . . . . . .

0.103See Figure 3.2.8.0

a Design allowables for extrusions procured to AMS 4163 were based upon data obtained from testing samples of material, supplied in T3511 temper, which were precipitation heat treated by suppliers to demonstrate response to aging treatment.

b The mechanical properties are to be based upon the thickness at the time of quench.c Applicable providing LT dimension is $2.500 inches.d Bearing values are dry pin values per Section 1.4.7.1.

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-400 -200 0 200 400 600 800 1000

Temperature, F

K, Bt

u/[(h

r)(ft2

)(F)/ft

]

, 10

-6

in./in

./F

C, Bt

u/(lb

)(F)

0

20

40

60

80

100

0.00

0.05

0.10

0.15

0.20

0.25

0.30

8

9

10

11

12

13

14

15

- Between 70 F and indicated temperature

C - At indicated temperatureK - At indicated temperature

C

K (T8XX)

Figure 3.2.8.0. Effect of temperature on the physical properties of 2219 aluminum alloy.

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Temperature, F

-500 -400 -300 -200 -100 0 100 200 300 400 500 600 700 800

Perc

en

t Ftu

o

f Ro

om

Te

mpe

ratu

re

0

20

40

60

80

100

120

140

160

10,000 hr1000 hr

100 hr10 hr

1/2 hr

10,000 hr1000 hr

100 hr10 hr

1/2 hr

Strength at temperatureExposure up to 10,000 hr

Figure 3.2.8.1.1(a). Effect of temperature on the tensile ultimate strength (Ftu) of2219-T62 aluminum alloy sheet, 0.040-0.249, and plate, 0.250-1.000 in. thick.

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Temperature, F

-500 -400 -300 -200 -100 0 100 200 300 400 500 600 700 800

Perc

en

t Fty

o

f Ro

om

Te

mpe

ratu

re

0

20

40

60

80

100

120

140

160

hr10 hr

100 hr1000 hr

10,000 hr

hr10 hr

100 hr1000 hr

10,000 hr

Strength at temperatureExposure up to 10,000 hr

Figure 3.2.8.1.1(b). Effect of temperature on the tensile yield strength (Fty) of 2219-T62 aluminum alloy sheet, 0.040-0.249 and plate, 0.250-1.000 in. thick.

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0

10

20

30

40

50

0 2 4 6 8 10 12Strain, 0.001 in./in.

Compressive Tangent Modulus, 103 ksi

Stre

ss, k

si

Ramberg - Osgood n (L and LT - tension) = 13 n (L and LT - comp.) = 16

Thickness = 0.125 - 2.000 in.

L and LT CompressionL and LT Tension

TYPICAL

Figure 3.2.8.1.6(a). Typical tensile and compressive stress-strain and compressivetangent-modulus curves for 2219-T62 aluminum alloy sheet and plate at roomtemperature.

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Strain, in./in.0.00 0.02 0.04 0.06 0.08 0.10 0.12

Stre

ss, ks

i

0

10

20

30

40

50

60

70

80

X

Thickness: 0.125-2.00 in.

TYPICAL

Longitudinaland

Long transverse

Figure 3.2.8.1.6(b). Typical tensile stress-strain (full range) curve for 2219-T62aluminum alloy sheet and plate at room temperature.

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Temperature, F

-500 -400 -300 -200 -100 0 100 200 300 400 500 600 700 800

Perc

en

t Ftu

o

f Ro

om

Te

mpe

ratu

re

0

20

40

60

80

100

120

140

160

1/2 hr10 hr100 hr1000 hr10,000 hr

1/2 hr10 hr100 hr1000 hr10,000 hr

Strength at temperatureExposure up to 10,000 hr

Figure 3.2.8.2.1(a). Effect of temperature on the tensile ultimate strength (Ftu) of2219-T81 aluminum alloy sheet and 2219-T851 aluminum alloy plate.

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Temperature, F

-500 -400 -300 -200 -100 0 100 200 300 400 500 600 700 800

Perc

en

t Fty

o

f Ro

om

Te

mpe

ratu

re

0

20

40

60

80

100

120

140

160

1/2 hr10 hr

100 hr1000 hr

10,000 hr

1/2 hr10 hr

100 hr1000 hr

10,000 hr

Strength at temperatureExposure up to 10,000 hr

Figure 3.2.8.2.1(b). Effect of temperature on the tensile yield strength (Fty) of 2219-T81 aluminum alloy sheet and 2219-T851 aluminum alloy plate.

MMPDS-011 February 2003

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0

20

40

60

80

100

0 2 4 6 8 10 12Strain, 0.001 in./in.

Compressive Tangent Modulus, 103 ksi

Stre

ss, k

si

Ramberg - Osgoodn (L and LT - tension) = 20

n (L - comp.) = 19n (LT - comp.) = 21

Thickness = 0.040 - 2.500 in.

LT - compressionL - compression L and LT - tension

TYPICAL

Figure 3.2.8.2.6(a). Typical tensile and compressive stress-strain and compressivetangent-modulus curves for 2219-T81 aluminum alloy sheet and 2219-T851aluminum alloy plate at room temperature.

MMPDS-011 February 2003

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!

"#$%&

Figure 3.2.8.2.6(b). Typical tensile stress-strain curves (full range) for 2219-T81aluminum alloy sheet and 2219-T851 aluminum alloy plate at room temperature.

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Figure 3.2.8.2.8(a). Best-fit S/N curves for notched, Kt = 2.0, 2219-T851 aluminumalloy plate, longitudinal direction.

Correlative Information for Figure 3.2.8.2.8(a)

Product Form: Plate, 2.00 inch thick

Properties: TUS, ksi TYS, ksi Temp.,EF 68 52 RT

(unnotched) 94 RT

(notched)

Specimen Details: Notched, V-Groove, Kt = 2.00.195 inch gross diameter0.136 inch net diameter0.020 inch root radius, r60E flank angle,

Surface Condition: As machined

Reference: 3.2.8.2.8

Test Parameters:Loading - AxialFrequency - 7000 to 8000 cpmTemperature - RTEnvironment - Air

No. of Heats/Lots: 1

Equivalent Stress Equation:Log Nf = 7.92-2.69 log (Seq-16.0)Seq = Smax (1-R)0.64 ksiStd. Error of Estimate, Log (Life) = 0.313Standard Deviation, Log (Life) = 0.739R2 = 82%

Sample Size = 34

[Caution: The equivalent stress model may provide unrealistic life predictions for stress ratios beyond those represented above.]

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Figure 3.2.8.2.8(b). Best-fit S/N curves for notched, Kt = 3.2, 2219-T851 aluminumalloy plate, longitudinal direction.

Correlative Information for Figure 3.2.8.2.8(b)

Product Form: Plate, 2.00 inch thick

Properties: TUS, ksi TYS, ksi Temp.,EF 68 52 RT

(unnotched) 92 RT

(notched)

Specimen Details: Notched, V-Groove, Kt = 3.20.195 inch gross diameter0.136 inch net diameter0.006 inch root radius, r60E flank angle,

Surface Condition: As machined

Reference: 3.2.8.2.8

Test Parameters:Loading - AxialFrequency - 7000 to 8000 cpmTemperature - RTEnvironment - Air

No. of Heats/Lots: 1

Equivalent Stress Equation:Log Nf = 8.46-2.83 log (Seq-3.93)Seq = Smax (1-R)0.76Std. Error of Estimate, Log (Life) = 0.292Standard Deviation, Log (Life) = 0.64R2 = 79%

Sample Size = 39

[Caution: The equivalent stress model may provide unrealistic life predictions for stress ratios beyond those represented above.]

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Figure 3.2.8.2.8(c). Best-fit S/N curves for notched, Kt = 3.2, 2219-T851 aluminumalloy plate, long transverse direction.

Correlative Information for Figure 3.2.8.2.8(c)

Product Form: Plate, 2.00 inch thick

Properties: TUS, ksi TYS, ksi Temp.,EF 68 51 RT

(unnotched) 89 RT

(notched)

Specimen Details: Notched, V-Groove, Kt = 3.20.195 inch gross diameter0.136 inch net diameter0.006 inch root radius, r60E flank angle,

Surface Condition: As machined

Reference: 3.2.8.2.8

Test Parameters:Loading - AxialFrequency - 7000 to 8000 cpmTemperature - RTEnvironment - Air

No. of Heats/Lots: 1

Equivalent Stress Equation:Log Nf = 10.85-4.34 log (Seq)Seq = Smax (1-R)0.686 ksiStd. Error of Estimate, Log (Life) = 0.153Standard Deviation, Log (Life) = 0.610R2 = 94%

Sample Size = 25

[Caution: The equivalent stress model may provide unrealistic life predictions for stress ratios beyond those represented above.]

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Figure 3.2.8.2.8(d). Best-fit S/N curves for notched, Kt = 5.0, 2219-T851 aluminumalloy plate, longitudinal direction.

Correlative Information for Figure 3.2.8.2.8(d)

Product Form: Plate, 2.00 inch thick

Properties: TUS, ksi TYS, ksi Temp.,EF 68 (L) 52 (L) RT

(unnotched) 91 (L) RT

(notched)

Specimen Details: Notched, V-Groove, Kt = 5.00.300 inch gross diameter0.210 inch net diameter0.0035 inch root radius, r60E flank angle,

Surface Condition: As machined

Reference: 3.2.8.2.8

Test Parameters:Loading - AxialFrequency - 7000 to 8000 cpmTemperature - RTEnvironment - Air

No. of Heats/Lots: 1

Equivalent Stress Equation:Log Nf = 8.76-3.05 log (Seq)Seq = Smax (1-R)0.722 ksiStd. Error of Estimate, Log (Life) = 0.194Standard Deviation, Log (Life) = 0.660R2 = 91%

Sample Size = 38

[Caution: The equivalent stress model may provide unrealistic life predictions for stress ratios beyond those represented above.]

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0

20

40

60

80

100

0 2 4 6 8 10 12Strain, 0.001 in./in.

Stre

ss, k

si

Ramberg - Osgoodn (L) = 22

n (LT) = 17n(ST) = 14

Thickness = 4.001 - 6.000 in.

LT

TYPICAL

ST

L

Figure 3.2.8.3.6(a). Typical tensile stress-strain curves for 2219-T852 aluminumalloy hand forging at room temperature.

0

20

40

60

80

100

0 2 4 6 8 10 12Strain, 0.001 in./in.

Stre

ss, k

si

Ramberg - Osgoodn(L-tension) = 16

n(LT-tension) = 15n(ST-tension) = 15

Thickness = 6.001 - 8.000 in.

LT and ST

TYPICAL

L

Figure 3.2.8.3.6(b). Typical tensile stress-strain curves for 2219-T852 aluminumalloy hand forging at room temperature.

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0

20

40

60

80

100

0 2 4 6 8 10 12Strain, 0.001 in./in.

Comprsssive Tangent Modulus, 103 ksi

Stre

ss, k

si

Ramberg - Osgoodn (L) = 20

n (LT) = 19n(ST) = 17

Thickness = 4.001 - 6.000 in.

LT and ST

TYPICAL

L

L and LT

ST

Figure 3.2.8.3.6(c). Typical compressive stress-strain and compressive tangent-modulus curves for 2219-T852 aluminum alloy hand forging at room temperature.

0

20

40

60

80

100

0 2 4 6 8 10 12Strain, 0.001 in./in.

Compressive Tangent Modulus, 103 ksi

Stre

ss, k

si

Ramberg - Osgood n (L-comp.) = 12

n (LT-comp.) = 12n(ST-comp.) = 14

Thickness = 6.001 - 8.000 in.

LT and ST

TYPICAL

LTST

L

Figure 3.2.8.3.6(d). Typical compressive stress-strain and compressive tangent-modulus curves for 2219-T852 aluminum alloy hand forging at room temperature.

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Strain, in./in.0.00 0.02 0.04 0.06 0.08 0.10 0.12

Stre

ss, ks

i

0

10

20

30

40

50

60

70

80

X X X

Thickness: 6.001-8.000 in.

Longitudinal

Long transverse

Short transverse

TYPICAL

Figure 3.2.8.3.6(e). Typical tensile stress-strain curves (full range) for 2219-T852aluminum alloy hand forging at room temperature.

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Temperature, F

-500 -400 -300 -200 -100 0 100 200 300 400 500 600 700 800

Perc

en

t Ftu

o

f Ro

om

Te

mpe

ratu

re

0

20

40

60

80

100

120

140

160

1/2 hr10 hr

100 hr1000 hr

10,000 hr

1/2 hr10 hr

100 hr1000 hr

10,000 hr

Strength at temperatureExposure up to 10,000 hr

Figure 3.2.8.4.1(a). Effect of temperature on the tensile ultimate strength (Ftu) of2219-T87 aluminum alloy sheet and plate.

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Temperature, F

-500 -400 -300 -200 -100 0 100 200 300 400 500 600 700 800

Perc

en

t Fty

o

f Ro

om

Te

mpe

ratu

re

0

20

40

60

80

100

120

140

160

1/2 hr10 hr

100 hr1000 hr

10,000 hr

1/2 hr10 hr

100 hr1000 hr

10,000 hr

Strength at temperatureExposure up to 10,000 hr

Figure 3.2.8.4.1(b). Effect of temperature on the tensile yield strength (Fty) of 2219-T87 aluminum alloy sheet and plate.

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0

20

40

60

80

100

0 2 4 6 8 10 12Strain, 0.001 in./in.

Compressive Tangent Modulus, 103 ksi

Stre

ss, k

si

Ramberg - Osgoodn(L & LT-tension) = 14n (L & LT-comp.) = 14

Thickness = 0.125 - 1.000 in.

LT - compression L - compression

TYPICAL

L and LT - tension

Figure 3.2.8.4.6(a). Typical tensile and compressive stress-strain and compressivetangent-modulus curves for 2219-T87 aluminum alloy sheet and plate at roomtemperature.

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Strain, in./in.0.00 0.02 0.04 0.06 0.08 0.10 0.12

Stre

ss, ks

i

0

10

20

30

40

50

60

70

80

X

X

Thickness: 0.125-1.00 in.

Longitudinal

Long transverse

TYPICAL

Figure 3.2.8.4.6(b). Typical tensile stress-strain curves (full range) for 2219-T87aluminum alloy sheet and plate at room temperature.

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.

0 2 4 6 8 10 12

Stre

ss, k

si

0

10

20

30

40

50

60

Strain, 0.001 in./in.

n = 15.7

Short transverse

Ramberg-Osgood

TYPICAL

Thickness: 1.600 - 4.000 in.

Figure 3.2.8.4.6(d). Typical tensile stress-strain curve for 2219-T87 aluminum alloyplate at room temperature.

.

0 2 4 6 8 10 12

Stre

ss, k

si

0

10

20

30

40

50

60

Strain, 0.001 in./in.

n = 20.5

Ramberg-Osgood

TYPICAL

Long transverse

Thickness: 3.000 - 4.000 in.

Figure 3.2.8.4.6(c). Typical tensile stress-strain curve for 2219-T87 aluminum alloyplate at room temperature.

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Strain, in./in.0.00 0.02 0.04 0.06 0.08 0.10

Stre

ss, k

si

0

10

20

30

40

50

60

70

80

X

X

TYPICAL

Thickness: 1.600 - 4.000 in.

Short Transverse

Long Transverse

Figure 3.2.8.4.6(e). Typical tensile stress-strain curve (full range) for 2219-T87aluminum alloy plate at room temperature.

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Table 3.2.9.0(a). Material Specifications for2297-T87 Aluminum Alloy

Specification FormAMS 4330 Plate

3.2.9 2297 ALLOY

3.2.9.0 COMMENTS AND PROPERTIES 2297 is an Al-Cu-Li-Mn-Zr plate alloy withmoderately high strength and both high fatigue resistance and fracture toughness for durability anddamage tolerant applications. The alloy shows excellent short-transverse mechanical properties andstress-corrosion cracking resistance in plate thicknesses to 6-inches. Tensile properties show goodisotropy with only slightly lower strength in the in-plane 45 orientation, similar to the differences in in-plane properties usually found in Li-free high strength aluminum alloys.

The T87 condition is obtained after solution heat treating, quenching, stress-relief by stretching,and artificial aging to peak strength. Little, or no, reduction in fracture toughness is found after elevatedtemperature exposure.

This alloy is not designed to be welded. Use of mechanical fasteners only is recommended.

This alloy has shown a sensitivity to cold-hole expansion for improved fatigue resistance whenfastener holes, whose axes were perpendicular to the short transverse direction, were processed. Careshould be taken to ensure that all of the processing parameters have been evaluated prior to theapplication of cold expansion to prevent cracking in the material.

Material specifications for 2297 are shown in Table 3.2.9.0(a). Room temperature mechanicaland physical properties are shown in Table 3.2.9.0(b). Fracture toughness properties are shown in Table3.1.2.1.6. Cyclic stress-strain and strain-life curves are shown in Figure 3.2.9.0.6. Fatigue crackpropagation is shown in Figure 3.2.9.0.9.

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Table 3.2.9.0(b). Design Mechanical and Physical Properties of 2297-T87 Aluminum Alloy PlateSpecification . . . . . . . . . . . AMS 4330Form . . . . . . . . . . . . . . . . PlateTemper . . . . . . . . . . . . . . . T87Thickness, in. . . . . . . . . . . 3.001-4.000 4.001-5.000 5.001-6.000Basis . . . . . . . . . . . . . . . . S A B A BMechanical Properties:

Ftu, ksi:L . . . . . . . . . . . . . . . . . .LT . . . . . . . . . . . . . . . . .ST . . . . . . . . . . . . . . . . .45E . . . . . . . . . . . . . . . .

Fty, ksi:L . . . . . . . . . . . . . . . . . .LT . . . . . . . . . . . . . . . . .ST . . . . . . . . . . . . . . . . .45E . . . . . . . . . . . . . . . .

Fcy, ksi:L . . . . . . . . . . . . . . . . . .LT . . . . . . . . . . . . . . . . .ST . . . . . . . . . . . . . . . . .

Fsu, ksi S-L c . . . . . . . . . . . . . . .T-S c . . . . . . . . . . . . . . .

Fbrud, ksi:(e/D = 1.5) . . . . . . . . . .(e/D = 2.0) . . . . . . . . . .

Fbryd, ksi:(e/D = 1.5) . . . . . . . . . .(e/D = 2.0) . . . . . . . . . .

e, percent (S-basis):L . . . . . . . . . . . . . . . . . .LT . . . . . . . . . . . . . . . . .ST . . . . . . . . . . . . . . . . .

62625960

57575454

...

...

...

3038

98128

8599

54

1.5

6161b58b59

56b565254

...

...

...

3137

97126

8498

54

1.5

62646163

58575455

...

...

...

3339

102132

8599

...

...

...

60a60a57a59

55a55a5253

...

...

...

3236

95123

8296

54

1.5

62646163

58575456

...

...

...

3439

102132

8599

...

...

...E, 103 ksi . . . . . . . . . . . . .Ec, 103 ksi . . . . . . . . . . . .G, 103 ksi . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

11.3.........

Physical Properties:, lb/in.3 . . . . . . . . . . . . . .C, Btu/(lb)(EF) . . . . . . . .K, Btu/[(hr)(ft2)(EF)/ft] . ., 10-6 in./in./EF . . . . . . . .

0.096.........

a S-basis. The rounded T99 values are as follows; Ftu(L) = 61, Ftu(LT) = 62, Ftu(ST) = 59, Fty(L) = 57, Fty(LT) = 56.b S-basis. The rounded T99 values are as follows; Ftu(LT) = 62 ksi, Ftu(ST) = 59 ksi, Fty(L) = 57 ksi.c Standard letter designations for shear properties per ASTM B769: 1st letter refers to grain direction, 2nd letter refers to

loading direction.d Bearing values are dry pin values per Section 1.4.7.1.

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0

1 0

2 0

3 0

4 0

5 0

6 0

7 0

0 0 .0 0 2 0 .0 0 4 0 .0 0 6 0 .0 0 8 0 .0 1 0 .0 1 2 0 .0 1 4 0 .0 1 6

S tr a in , p e r c e n t

Stre

ss, k

si

S T D a t a

S T A ve ra g e

L D a t a

L A ve ra g e

Figure 3.2.9.0.6. Strain-life and cyclic stress-strain curves for 2297-T87,4 inch plate.

0.001

0.01

0.1

10 100 1,000 10,000 100,000 1,000,000 10,000,000

Fatigue Life, cycles

Stra

in R

ange

, %L Data

ST Data

L Average

ST Average

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Correlative Information for Figure 3.2.9.0.6

Product Form: Plate, 4.00 inch thick

Properties: TUS, ksi TYS, ksi Temp., EFST 63.5 56.0 RTL 64.6 59.8 RT

Specimen Details:Uniform gage test section0.250-inch diameter

Surface Condition: Machined and polished alongthe length of the specimen using acommercial metal polishing paste calledPOL Metal Polish. The specimens had amirror-like finish, estimated as an RMS of4.

Reference: 3.2.9.0

Test Parameters:Frequency - 0.5 - 5 Hz. (Higher frequencies

typically used for the longer tests at thelower strains.)

Temperature - RTEnvironment - Lab Air (approx. 50% relative

humidity)

No. of Heats/Lots: 1

Strain Ratio = -1

Stress-Strain Equations:ST Direction

()/2 = /E + p whereE = 11.3 x103 ksi (reported),p = 6.243 x 10-103.187 for < 50.86 ksi, and p = 1.606 x 10-34 17.598 for > 50.86 ksi.

L Direction()/2 = /E + p whereE = 11.3 x103 ksi (reported),p = 1.219 x 10-103.566 for < 50.03 ksi, and p = 1.074 x 10-37 19.478 for > 50.03 ksi.

Equivalent Strain Equations:ST Direction

Log Nf = -6.66-4.96 log (t - 0.001)Standard Error of Estimate = 0.249Standard Deviation in Life = 0.864R2 = 96 %Sample Size = 21

L DirectionLog Nf = -1.88-2.54 log (t - 0.0037)Standard Error of Estimate = 0.141Standard Deviation in Life = 0.722R2 = 98 %Sample Size = 21