TL
761.1
.U6
1943
ENGINEERING
494258
(AMENDED TITLE PAGE)
ANC-5
Amendment-1*
ANC BULLETIN 22 Oct. 1943
STRENGTH OF AIRCRAFT ELEMENTS
WAR DEPARTMENT
ARMY AIR FORCES
NAVY DEPARTMENT
BUREAU OF AERONAUTICS
DEPARTMENT OF COMMERCE
JVIL AERONAUTICS ADMINISTRATION
Issued by the
ARMY-NAVY-CIVIL COMMITTEE
ON AIRCRAFT DESIGN CRITERIA
Under the Supervision of the
AERONAUTICAL BOARD
(Revised Edition - December 1942)
The contents of this Bulletin shall not be reproduced in whole or
in part without specific authority of the Aeronautical Board * See reverse side
U
11 eel', b46;
ANC-5, Amendment-1, as approved October 22, 1943, consists of changes in the texts which require reprinting of the following sheets:
1. Title Page
2. Pages 1-0 and 1-1
3. Pages 1-26 and 1-27
4. Pages 1-28 and 1-29
5. Pages 3-0 and 3-1
6. Page 3-2
7. Pages 4-2 and 4-3
8. Pages 4-4 and 4-5
9. Pages 4-6 and 4-7
10. Pages 4-12 and 4-13
11. Pages 4-14 and 4-15
12. Pages 5-0 and 5-1
13. Pages 5-2 and 5-3
14. Pages 5-4 and 5-5
15. Pages 5-6 and 5-7
16. Pages 5-8 and 5-9
17. Pages 5-10 and 5-11
18. Pages 5-12 and 5-13
19. Pages 5-14 and 5-15
20. Pages 5-16 and 5-17
21. Pages 5-18 and 5-18A
22. Pages 5-18B and 5-19
23. Pages 5-26 and 5-27
24, Pages 6-6 and 6-7
25. Pages 6-10 and 6-11
These sheets shall be inserted in lieu of the same pages of ANC-5, (Revised Edition - December 1942.)
4 4 58
CHAPTER
GENERAL
1-0
1.0 GENERAL ANC-5
1.00 INTRODUCTION PURPOSE AND USE OF HANDBOOK Amendment No. 1.
Oct. 22, 1943•
Since many aircraft manufacturers supply airplanes for both commercial and military use, standardization of the requirements of the various Governmental procuring or certificating agencies is of direct benefit to the manufacturer. Although the types and purposes of military airplanes often differ greatly from those of commercial airplanes, necessitating certain differences in the structural requirements, the requirements for strength of materials have for some time been near.Ly identical. This publication has therefore been prepared to eliminate the necessity for referring to different handbooks and bulletins in calculating the allowable stresses or minimum strength of typical structures. With a few exceptions (which are noted in the appropriate places) the material contained herein is acceptable to the Army Air Forces, Bureau of Aeronautics of the Navy, and the Civil Aeronautics Administration.
1.01 SCOPE OF HANDBOOK
Only the most commonly used materials are included in this publication. Until a structural material has been used for some time and in considerable quantities, the strength properties will probably vary considerably as manufacturing processes are improved and modified. In such cases special rulings should be obtained by the manufacturer from the procuring or certificating agency. These rulings will be based upon specimen tests and will eventually form a basis for standard accepted strength properties.
In addition to the strength of the materials themselves, there are contained herein the most commonly-used methods and formulas by which the strength of various structural components are calculated. In some cases the methods presented are empirical and subject to further refinement. Likewise, it is expected that additional material can be added from time to time as the methods of handling new problems become more uniform and reliable.
Engineers making use of the material contained herein are invited to submit comments and suggestions as to the expansion and improvement of the handbook. Such comments should be submitted directly to the committee in charge of this publication.
1.02 USE OF STRENGTH SPECIFICATIONS
i
As the materials commonly used in aircraft construction are more or less standardized as to composition and physical properties, it is customary to assign standard values to the strength properties for procurement specification purposes. The values so assigned represent the minimum values which will be accepted under a given specification. In general the allowable stress and strength values given herein are based on such minimum values. However, as a result of recent changes made by both the Army and Navy in regard to the
Amend-1 basis of selection for design allowables for certain materials, there are instances where these services are permitting higher design allowables than those corresponding to material possessing minimum guaranteed properties. The tables, section, etc., affected by such changes (as of the date of Amendment No. 1 to ANC-5) have been appropriately marked herein and, in such cases, they contain the separate columns of values acceptable respectively to the Army and Navy, and to the CAA. The allowable strength values acceptable for use in the design of civil aircraft are based upon minimum guaranteed properties. In connection with further changes which may be made from time to time by any of the Services, in regard to higher design allowables, this suggested that an appropriate notation be made herein covering reference to the source of such values. In this way, ANC-5 may be maintained as an up-to-date reference. Changes in procurement specification will, of course, require corresponding changes in allowable strength properties to be used for design purposes.
- 1
GENERAL ANC-5
Amendment No. 1.
Oct. 22, 1943
1.531 Crushing or Crippling Stress (Fc ). The upper limit of the allowable column stress for local failure is called the crusHing or crippling stress and is designated Fee. The crushing stresses of round tubes subject to plastic failure generally can be expressed by a modified form of the equation for the buckling of a thin-walled cylinder in compression (see Sec. 1.630) as given below:
F = KED 1:43) Dt
The effective modulus El can be determined from the basic column curve for primary failure by the method given in Sec. 1.512. As the value of the effective modulus corresponds to a given value of stress it usually is convenient to: (1) assume a value of Fcc; (2) compute the corresponding value of El; (3) substitute these values into Eq. 1:43 and solve for D/t. This latter value is the D/t at which crushing will occur at the assumed stress. Values of the constant K must be determined empirically. As noted above, Eq. 1:43 applies to plastic failure; i.e., for stresses above the proportional limit. In the case of thin-walled tubes which fail locally at stresses below the proportional limit, the initial eccentricities are likely to be larger relatively and the constant should be suitably reduced.
1.54 COLUMNS OF UNCONVENTIONAL CROSS SECTION
1.540 General. In the case of columns having unconventional cross sections which are particu-17aFfnubject to local instability, it is necessary to establish the curve of transition from local to primary failure. In determining the strength curves for such columns, sufficient tests should be made to cover the following points:
1.541 Nature of "Short Column" Curve. The test specimens should cover a range of LI/p which will extend to the Euler range, or at least well beyond the values to be used in construction. When columns are to be attached eccentrically in the structure, some tests should be made to determine the effects of eccentricity. This is important particularly in the case of'open sections, as the allowable loads may be affected considerably by the location of the point of application of the column load.
1.542 Local Failure. When local failure occurs, the crushing or crippling stress Fcc can be determined by extending the "short column" curve for the specific cross section under consideration to a point corresponding to zero LI/p. When a family of columns ofthe same general cross section is used, it is often possible to determine a relationship between F, and some factor depending on the wall thickness, width, diameter, or some combination of-these dimensions. Extrapolations of such data should be avoided by covering an adequate range in the tests.
1.543* Reduction of Test 'Results on Aluminum Alloys to Standard. Although there is no completely
rational method for correcting the results of compression tests to standard, the use of
the correction factors given in Fig. 1-4 is considered satisfactory and is acceptable to Olen' the Navy and the Civil.
*For current Army requirements relative to the procedures and methods of reducing test re-
sults, refer to Arm7 Air Force Specification C-1803A. For current Navy requirements refer to Bureau of Aeronautics Specification NAVAER SS-9.
1-26
•
■
•
■
IIIIIIMIMMINIIII 11111111111111111111111111
TIMM 111•••••••=111111•••••••••••••••••••••••••
•
• •
• ILIUMEMOILIZA11111•1011111111A MUM!' =La IIERrrlomriiimr-marliimmo
• rulommparlIMERILIAmona MEM NKR MUM MOM 11164111P411.•••
•
•
•
• ME • 11=11111••■ OM • MIMEO 11111111iMMIETO
111111111111I111111111111 1111111•111 • 111111111111111•1111•111E
• • •I1 IIIIRE.1111111111 MEW ME1111•1111 IIII
•
•
• I I
INI
•
•
•
•
•
111111111111 MIME= =EMI= MOM 1111111111111111111
Ci11•11111111•••••••• •11111111•11=1•11111111•111111111111
OIIIIIIMO =EMU= ME1111 EME111111/1=114•11111111111•1111•11111 1111111EM MBE MEI MU= WEI= 1111111•1111=1•111111111111 11111111111111•111111• E1111■ 111111111111•1 1•111111•21111111111111111
111••NM= •••• MBE
• ••••••••• 1111•1111111 1111111111•11•1111111•1•11111 EMIIIIIIMMEMEMEMIll EMMEN II= II= MEI= ••••••••
•111111=11111111111111 1111•11•1111 MN MIIIIIIEMEEMEMII
1111111/1111111111111•••••••=11•1111111==111111111111•••••= 111111111111111 MI= 111•111•11•111111111•1111111111•1111•11••=1.111111
1111111111•111111111111•11•1111=111=111111111111111111•1111111111111•11111
11111111110111111•11111=1111•111111=IIIM 1111•1•1111111111111111111•••
• 1111111111111111111.1111111111•11 =IL= IMIIMON1•••••••••••
• 111111•11•11••• MEM I= 111•11.•••1111, MUMMER=
IMMO= MR1111111111111111
11011111111MEMIIMEMEIM11MMO ENE •=111111•1111111111•111•111111111111 1•1111=11111111MMIIIIM IMMEMIEllt=
111111111=1111111•11=1111 1•111111111111111/1•••• 1111•1111111MOO
M1111111111111•111111111111=11111E11•11111111111111 IMAM MK= MIN ••111111•••11••• Mil =WWII • Min UM= IMOERITEM
■=MI 11•11111111111••••••11•111=111•1111111r=1/1•111111M 111111111•••••• 1111111111=11=1,1•1111•1101111111011111►/11111 MIR=
11=111111111•••••••• 1111=Elfi ■ I• 111=11/111/111•••••••• •
r
1111••••••••=1111•11111111•11111=111EIMUMMIMIE • MEE ••••=1111111111=1111111111•1111=1111 IM/11WIREEMMIMIIIIMO
I
z
x
0 a.
0
U) U)
U)
r•MIad-*-1IIWH-4WC
U)
(1)
cr
U)
0
1
-
c1; U)
O
03
4
0
4
I
• MEM 111111111111 11•=1111 111111=11 •1111 111111111111•111111
0
co.
27
N
0 tn
1-
-: z in
la Ed
M Z F
Eld
a. Z
O 0:
Id 0
0 in 1-- atr) —
di
..z.
ld 0 I- 1-
in W
IL Id a -
o F IL to
)IL I Z
tp 00 0W
r0 U v.
i--w
tn 2.
in it c;
re 0 iil
w F.
>0 IL. ii.
O oir) 0 w
w -1 0
15: u 0
O < —1
>
t., W 11. ...1
1*: W la
I 2d
< akJ
0 I
2 IL I-'s D
i-: E 0
I 0 W Z
3 k)
II it
t) 2-
IL1 0 D
0 U -I
<
I
17
, a
1/11 r
NEN muummismormusill
11111111/11•111=11••••••=1111
A A
Fr
11111%/
1111•1111111111111111111 =MEM= •••••••••• •••••••••••••=111=1=
11=111111•111•1111.11••••••1111 111111111111111•• 111111111•=11•••••111111111
0 0
04
NOLLV32:11I10, -,1
GENERAL ANC-5
Amendment No. 1.
Oct. 22, 1943.
Aeronautics Administration, for use in connection with tests on aluminum alloys. (Note that an alternative method, acceptable to the Civil Aeronautics Administration only, is given in paragraph 1.544). In using Fig. 1-4, the correction of the test result to standard is made by simply multiplying the stress developed in the test by the factor K. This factor may be considered applicable regardless of the type of failure involved (i.e., column, crushing, or twisting).
For obtaining compressive yield strengths for use in Fig. 1-4, the methods that should be used are;
a. Direct compressive stress-strain measurements of the specimen.
b. In case a compression member is formed from sheet material, and the use of method (a) is not feasible, direct tensile stress-strain measurements should be taken on the original sheet in a direction normal to the length of the compression member. The cross and with-grain yield ratios given in Table I-1 then should be used to compute the compressive yield along the length of the compression member. In case the compression member is manufactured indiscriminately with respect to material grain, the test specimen should be made with the grain parallel to its length.
c. In case neither methods (a) nor CO are feasible or applicable, it should be assumed that the compressive yield of the specimen is 15 percent greater than the minimum established yield for the material.
TABLE I-1
RELATIONSHIP BETWEEN WITH AND CROSS GRAIN PROPERTIES OF ALUMINUM ALLOY
SHEET*
Amend-1
Property For 24ST, and For 24SRT and
Alclad 245T Alclad 24SRT
Tensile strength (w) • = 1.02 Tensile Str. (x) = 1.14 Tensile yield(x) = 0.96 Tensile yield(x) = 1.06 Tensile yield(x)
Tensile yield (w) = 1.02 Tensile Str. (x)
Compressive yield(w) Compressive yield(x) = 1.17 Tensile yield (x) -= 0.96 Tensile yield (x) = 1.08 Tensile yield (x)
w = with grain, x = cross grain
*This applies only to material heat-treated and flattened by the mill and not reheat-treated.
- 28
G
For compression members stretched a controlled amount after heat treatment or made from sheet with the material grain normal to the direction of the expected load, it is reasonable to increase the value of the "minimum!' yield to be used as the basis for the correction of tests results. Such increases will depend upon rigid manufacturing control of the stretching or forming. For stretched material. the compressive yields for both the stretched and the =stretched conditions shculd be determined, and the ratio between the two used to multiply the "miniimun" established compressive yield for the "as received" material.. For compression nsmbers formed from sheet, cross-grain, the "minimum" canpressive yield may be taken as 1.08 times the specification tensile yield, if the material. is 17STs Alclad 17ST, 24STs or Alelad 24ST; and is 1.06 times the specification tensile yield, if the material. is 24SRT or Alelad 245R'T.
1.544 Reduction of Test Results to Standard—Civil Aeronautics Administration Method. The following method of correcting test results to standard is acceptable to the Civil Aeronautics Administration only. It is not restricted as to the type of material involved in the tests. Although the corz-ection of compression test results by means of a factor which • is a ilinction of thecompressive yield stresses involved is a more rational procedure, the following method gives reasonable; results and obviates the difficulties involved in determining the compressive yield stresses.
a. The correction parameter R is taken as the ratio of the specification (or guaranteed) ultimate tensile stress of the material to the actual ultimate tensile stress of a coupon cut from the test specimen.
b. The column intercept obtained from primary failure tests is corrected by multiplying by R.
c. Local or crushing failure test points are corrected by the folloming factor:
IC • R,
where II is the ratio of the actual local failure test stress, Fee, to the ultimate tensile stress of a coupon Gut from the test specimen (n • Fee/Ftu).
d. In cases where it is difficult to determine whether the failure of the specimen is primary or local, the test results are corrected by miltiplying by R.
e. Corrections for the variation of the modulus of elasticity from the specification value are" considered negligible and are therefore neglected.
- 29
CHAPTER 3 METALS-GENERAL
METALS - GENERAL ANC-5
Amendment No. 1. 'Oct. 22, 1943
3.0 EXPLANATION OF MECHANICAL PROPERTIES TABLES
3.00 The mechanical properties of various metals are given in the tables at the end of each
chapter. In all applications, the values specified are the maximum acceptable for Amend-1 strength calculations. The following notes apply to the various items; the numbers be-
low correspond to the numbers in the tables:
(1) Ftu - Ultimate tensile stress. (From tests of standard specimens).
(2) F, - Tensile stress at which the permanent strain equals 0.002.
Qr (From tests of standard specimens).
(3)- Tensile stress at which the permanent strain equals 0.0001.
'IP (From tests of standard specimens).
(4) E - Average ratio of stress to strain for stress below proportional limit.
(5) Elongation - This factor is a measure of the ductility of the material and is based on a tension test.
(6) Feu - Ultimate (block) compressive stress. (Obtained from flat end compression tests of specimens ha-Ang an L/P of approximately 12).
(7) F - Same as (2), but obtained from a compression test. cy
(8) F - Same as (3), but obtained from a compression test.
cp
(9) Fco
(10) Ec - Same as (4), but obtained from a compression test.
(11) F -Ultimate stress in pure shear. This value represents the average
su shearing stress over the cross section and applies to cases in which an actual shear failure takes place. (Such as the shear failure of rivets or bolts).
(12) Fst - Modulus of rupture in torsion. This value applies only to solid cylindrical specimens having a length to diameter ratio of approximately 15.
(13) F -Proportional limit in torsion. This represents the shearing stress at
sp which the permanent strain equals 0.0001, as obtained from torsion tests.
(110 G - Modulus of rigidity in shear. This corresponds to the value E for tensile stresses. It will apply in calculating the shear deflection of webs, provided that no wrinkling occurs.
3 - 1
- Column yield stress. Upper limit of the allowable column stress for primary failure. (See Sec. 1.513).
METALS - GENERAL ANC-5Amendment No. 1.
Oct. 22, 1943
(15) F - Ultimate bearing stress. This value may be used for the design of the connecting elements of rigid joints onlywhen there is no possibility of relative movements between the parts joined, without deformation of these parts.
(16) Rockwell Number - These values are useful as a means of checking the uniformity of a material and as an approximate means of determining the ultimate tensile stress of wrought materials.
(17) Brinell Number - These values serve the same purposes as item (16) above. (17a) Vickers Numbers - Similar to Brinell.
(18) F - Endurance limit in bending. This value is the maximum alternating bending stress which a polished solid round specimen can withstand in a rotating-beam test for the stated number of cycles of completely reversed stress. Since the rotating-beam test cannot be applied to sheet, an alternating flexure test is substituted using an unpolished sheet specimen. Surface roughness and corrosion conditions may decrease these values appreciably. (See Sec. 1.416).
Endurance limit in torsion. This value is the maximum alternating
(19) Fse - shear stress which a polished solid round specimen can withstand for the stated number of cycles of completely reversed stress.
(20) w - Specific weight. Values given are average values.
(21) The nominal chemical composition is given for reference purposes only. See the corresponding Army, Navy, Federal, or SAE specification for details as to chemical composition.
3.01 The methods of using the materials and their allowable strength properties will be speci-
fied by the procuring or certificating agency. That is, additional factors of safety or arbitrary reductions in allowable stresses may be considered necessary in particular cases. In general, the values listed represent "safe" values for materials conforming to the specifications given.
3.02 Deleted.
Amend-1
3 - 2
1%.0 , ....., 4...", i) 0 0
Q r-I 0 0 , ,...., ,...0 e
.d • 43 43
a • a$ 0 e
43 43 Z M
0 0 0
= Z Z
i. . Ct N N at N N
Long Calms(a) , ,--- ,—, .... ...... "*".... .., 1
"*.... ',... ''.... ...... %No ..
e. . . tO tO CO
....... ...... ...... 0 • ..40 2
tO CO CO 'W 'W
0 a po ca co co
°IL` E co
cg
a 0. :a0 CO 0 a)
„..4 -..., vs •. 14 •
..,4. ;:ii CO a •
0 cg 0) CO
ri CO
. Irt IP tt3 in ids IP V
a Otg ...I Cg CV CU CNI 01
A .. .. .. .. ..
r.1 ril r-1 r-1 I-1 H
1' La La 02 A
•-, 7, A A a ....
'g Q. , 0-, #..... Q. ie..,
0 N. „.., ...4":1,.. Q. "*"., .......
0 :4 14 0..1
.....,A .4 1, ....1 15 L,.. co ca-
cg .4, it; sf4
c. cr, a; r4 CZ
r4 • tt;'
• 0-1• S e CO
ril Lo r1 r-4
r4
sh w
CO 0
10 t3/4-•
El § §
la. (j): e 5 8 in in
.0 10 CO
rse. ri-1 H
art IN §
04 § § § Kr tr7
4)tO WNO 14 LI) 8 la tO
rab OD ri f-1 f-1
1 LO 2 53 nZi TS
• ..-1 4 _A VI Vr-1.
ti! t-1 1 CO CO w 4-)0
CO
I Itft 43 I{.0 4.3 010
4S O. 4t 0 1 0
s Q s 1 $
44 .0 0
I 0 03 0
vi f 4 1
B. it t.. $:: 7:11, 2
0 4-1 43 as
43 r4 I-4 rk. id
4-1=0 signs 0
t!0
.0 4
V : 1 48 i i 2 c 2
.qii 111141
r-1 9 .0 r4
1 0 ril 46 0
0 40 01.4 2 .40, 2
geri 44 t—I 0 43
6 9 +I e1 0 i
0 al 01
43
P. tiO 0 r=4 4,
- . 9. • l'' a r 1'4 t ES4 " '9 410
Z-1 tela$ Of,
420 ,ra _o_ o 0 c,
....... bo m o
d° 79 z I
A 4 fa g o rA 1
II 1400 4/) En
= .r1 0 01 ig
...b.;44111)141111
• • • 0 0 o •
4. 4..4.4.
a0.00 zzzz
ANC-5
Amendment No. 1.
Oct. 22, 1943.
4.21 Simple Beams. Beams of solid, tubular, or similar cross-sections can be assumed to fail through exceeding an allowable modulus of rupture in bending (F,). For solid sections, it usually can be assumed that Fb equals the ultimate tensile stress. This assumption is conservative and higher values may be used if substantiated by test data.
4.210 Round Tubes. For round tubes, the value of Fb will depend on the D/t ratio, as well as the ultimate tensile stress. Figure 4 -20.gives the bending modulus of rupture for chrome molybdenum steel tubing.
4.211 Thin-walled Cylinders. Information on the failure of thin-walled cylinders in bending is given in Secs. 1.631 and 1.641.
4.212 Unconventional Cross-sections. Sections other than solid or tubular should be tested to determine the allowable bending stress.
4.22 Built-up Beams. Built-up beams usually will fail due to local failures of the component parts. In welded steel tube beams, the allowable tensile stresses should be reduced properly for the effects of welding.
4.23 Thin-Web Beams. The allowable stresses for thin-web beams will depend on the nature of the failure and are determined from the allowable stresses of the web in tension and of the flanges and stiffeners in compression. See Ref. 15 for general stress analysis methods.
4.3 TORSION
•
4.30 General. The torsion failure of steel tubes may be due to plastic failure of the metal, elastic instability of the walls, or to an intermediate condition. Pure shear failure usually will not occur within the range of wall thicknesses commonly used for aircraft tubing.
4.31 Allowable Torsional Shear Stresses. In the range of low values of D/t, no theoretical formula is applicable directly. The results of tests have been used to determine the empirical curves of Figs. 4-21 and 4-22.
For high values of D/t, the equations given in Sec. 1.632 can be used, provided that the allowable stress so determined does not exceed the proportional limit in shear.
4.4 COMBINED LOADINGS
4.40 Amend-1 Round Tubes in Bending and Compression. The general theory of failure under combined loadings is given in Sec. 1.424. In the case of combined bending and compression it is necessary to consider the effects of secondary bending; that is, bending produced by the axial load acting in conjunction with the lateral deflection of the column. In general, Eq. 1:37 Sec. 1.424 can be used in the following form for safe values:
fb, fd.
Tr- = 1.0
Fb rcy
4 - 3
STEEL
(4:2)
STE T, ANC-5
Where fb = maximum bending including effects of secondary bending.
Amendment No. 1 Oct. 22, 19431,
Fb = bending modulus of rupture
fc = axial compressive stress
Fcy = compressive yield stress
In no case shall the axial compressive stress, fc, exceed the allowable stress, Fc, for
a simple column.
4.41 Tubes in Bending and Torsion. Equation 1:37, Sec. 1.424 can tie used in the following
forms for safe values:
(4:3)
(4:4)
Higher values can be used if substantiated by adequate test data.
4.42 Tubes in Bending, Compression and Torsion. The bending stresses should include the ef-
fects of secondary bending due to compression. The following empirical equation will
serve as a working basis, pending a more thorough investigation of the subject:
Amend-1
Round tubes: Streamline tubes:
Rb2 + Ra2 = 1.0
Rb + Rs = 1.0
Amend-1 fb f 2 = 1.0 (4:5)
C (y.
cy
In no case shall the axial compressive stress, fc, exceed the allowable stress, Fc, for a simple column.
4.5 JOINTS, FITTINGS AND PARTS
4.50 Bolted and Riveted Joints.
4.500 Allowable Shear Stresses. The allowable shear stress for rivets, bolts and pins is give in Table 4-13.
4.501 Allowable Bearing Stresses. The basic values of the allowable bearing stresses for various steels will be found in the tables at the end of this chapter. These stresses are applicable only when the D/t ratio (diameter of rivet over thickness of sheet) is less than 5.5. When this ratio is equal to or greater than 5.5, the allowable bearing strengths must be substantiated by tests covering both yield and ultimate of the joint. The allowable bearing strength of steel sheets on rivets, bolts, and pins is given in Table 4-14. These values are to be used only for the design of the connecting elements of rigid joints when there is no possibility of relative movement between the parts joined without deformation of these parts. For other types of joints, the allowable bearing stresses are to be reduced by dividing by the factors of safety specified in Table 4-2 (designated as "bearing factors" or are to be used in accordance with Table 4-3, whichever is applicable.
For antifriction bearings the critical limit load should not exceed the manufacturer's non-Brinell rating.
4 - 4
TABLE 4-2 (1)
BEARING FACTORS R)R PLAIN (2) BEARINGS (3) HAVING NO OR INFREQUENT (4) RELATIVE ROTATION UNDER DESIGN LOADS
( The requirements of this table are mandatory on Army and Navy airplanes and are recommended on civil airplanes. Note also the requirements in C.A.R. 04.271 to 04.277 inclusive which apply to civil airplanes. )
Infrequent Relative Rotation under Design Loads Shook(5) or Factor(7)
Vibration
NONE (6) NONE 1.0
YES NONE 2.0
NONE (5) YES 2.0
YES YES 2.5
t
NOTES:
(1) The factors given in this table are applicable to other materials as well as to steel.
(2) "Plain' bearings as against anti-friction bearings (ball bearings, etc.).
(3) Bearings are distinguished from fittings, in general, in that a bearing is a pin-jointed
fitting which permits relative movement between the parts joined other than that due
to deformation of the parts under load.
(4) For rotations in the order of 100 revolutions per hour, and up, see Table 4-3.
(5) No relative rotation under design loads; to illustrate, same landing gear joints have no relative rotation under landing loads, although they have relative rotation during retraction.
(6) Shook is considered to occur in such structures as landing gears, gun mounts, hoisting, towing and mooring connections.
(7) It should be noted that the fitting factors specified by the procuring or certificating agency also apply to the bearing surfaces. If the applicable fitting factor exceeds the bearing factor, the former shall be used in lieu of (not in addition to) the latter, and vice-versa.
Revised
Dec., 1942
TABLE 4-3
ULTIMATE BEARING STRESS FOR PLAIN LUBRICATED BEARINGS
HAVING FREQUENT RELATIVE MOTION
(The requirements of this table are mandatory on Army and Navy airplanes and are recommended on civil airplanes. Note also the requirements in C.A.R. 04.271 to 04.277 inclusive which apply to civil airplanes.)
TYPE OF BEARING SHOCK OR VIBRATION LUBRICATION lb./sq. in.
Free fits, frequent relative movement approximately 100 revolutions per hour (or equivalent) per flight. NONE • 15,000
GREASE
Free fits, subject to very frequent relative movement, with three or more bearings in, line, sealed or protected. NONE GREASE 12,000
Free fits, subject to very frequent relative movement, with three or more bearings in line, NONE LIGHT 8,000
unprotected from dirt. . GREASE
Free fits, subject to very frequent relative movement with three or more bearings in line, YES OIL 1,500
unprotected from dirt.
4-5
S'
4.502 Hollow-end Rivets. If hollow-end rivets with solid cross sections for a portion of the length (AN 450) are used, the strength of these rivets may be taken equal to the strength of solid rivets of the same material, provided that the bottom of the cavity is at least 25 percent of the rivet diameter from the plane of shear, as measured toward the hollow end, and further provided that they are used in locations where they will not be subjected to appreciable tensile stresses.
4.51 Welded Joints.
4.510 Effects of Welding on Base Metal. The allowable stresses in the base metal near the weld for steels that have been welded after heat-
Revised treatment are given in the tables at the end of this chapter. When Dec., 1942 heat-treated after welding, the allowable stresses should be reduced to 80 percent of the standard heat-treated values.
The 80 percent factor mentioned above does not apply in the case of small angle welds. The following tables give.(1) the tension allowables near any angle weld of chrome molybdenum tubes and (2) the bendin; modulus allomables near welds of such tubing (Ref. 18). The allowable column stress for melded alloy steel round tubing is given by Fig. 4-5.
TABLE 4 - 4
TENSION ALLOWABLES NEAR MELDS IN STEEL TUBING (x-4130)
Type of Weld Normalized Tube Welded Welded after HT or Norm.after Weld HT after Welding
* Tapered Welds of. 30° or Less. .947 Ftu 90,000 psi** .90 Ftu
All others. .841 Ftu . 80,000 psi .80 Ftu
*Note: Gussets or plate inserts considered 0° "taper" with it.
** For (X-4130) Special, comparable values to the Ftu, equal to 90,000 and 80,000, are stresses 94,500, and 84,100 psi, respectively.
TABLE 4 - 5
BENDING MODULUS ALLOWABLES NEAR 'WELDS IN TUBING (x-4130)
Type of Weld Normalized Tube Welded Welded after HT crNorm.after Weld HT after Welding
,
Tapered Welds of 30° or Less .947(Fb,Fig. 4-20) for Ftu = 95,000 Fb, Fig. 4-20 .90-(Fb,Fig.4-20)
All others. .841(Fb,Fig. 4-20) for Ftu = 95,000 for F = 900 000 tu .80 (Fb,Fig.4-20)
Fb, Fig. 4-20 for Ftu = 80,000
560217 0 - 43 - 2 .4- 6
ANC-5, Amendment No. 1. Oct. 22, 1943.
4.511 Allowable Loads for Welded Seams. The allowable load on the weld metal in welded seams can be computed from the following formulas:
(Low carbon steel) P = 32,000 Lt - (4:6)
Amend-1 (Chrome-molybdenum steel) P = .48 Lts. (4:7)*
where P = allowable load, lbs.
L = Length of welded seams, ins.
t = thickness of thinnest material joined by the weld in the case of lap welds between two steel plates or between plates and tubes, ins.
t = average thickness in inches of the weld metal in the case of tube assemblies. (Cannot be assumed greater than 1.25 times the thickness of the welded stock).
s = 90,000 psi for material not heat-treated after welding.
s = ultimate tensile stress of material heat-treated after welding, but not to exceed 150,000 psi.
*Applicable only where heat-treatable welding rod is used.
4.512 Welded Cluster. In welded structure where 7 or more members converge, the allowable stress shall be determined by dividing the normal allowable stress by a materials factor of 1.5, unless the joint is reinforced in a manner for which specific authority has been obtained from the licensing or procuring agency. A tube that is continuous through a joint should be assumed as 2 members.
4.52 Brazed Joints. The term "brazing" is defined as a method of joining steel parts by means of a copper-zinc mixture which is applied by melting with an air-gas flame or dipping into the molten mixture. The strength of brazed joints depends upon the area and the clearances between the parts to be joined. A brazing mixture may have a shearing strength as high as 40,000 pounds per square inch, but this strength is influenced by several factors, and, therefore, should not be used in design. In general a value of 10,000 pounds per square inch can be assumed as the allowable ultimate shear stress. Procedures and restrictions in the use of brazing will be found in the detailed requirements of the procuring or licensing agencies and should be observed carefully.
147 -
TABLE 4 - 8 ALLOY STEELS2
MECHANICAL PROPERTIES OF MATERIALS
CONDITION 0 (i) ® (2) (i),.%
, . NORMALIZED PLATE NORMALIZED PLATE NEAR WELDING WHEN WELDED AFTER HEAT TREATMENT (1-4130) SPECIAL NORMALIZED(2)
TUBE AND BAR TUBE AND BAR TUBES - .188n THICK AND UNDER
OVER .188" THICK .188" THICK AND (1-4130) SPECIAL
(%4130) UNDER (1,4130) .
SPECIFICATION ARMY
NAVY BAR 46823 RD TUBING 44T18
RD. TUBING 44T18 STR. TUBING 44T17
STR. TUBING 44T17
FEDERAL
SAE 14130 1-4130 A 1-4130 1-4130
. . ,
COMPRESS ION TENSION — Ultimate Stress, psi Ft u 95 000 84 000(4) 100 000
1 90 000
2 Fty Yield Stress, psi 70 000 75 000 85 000
3 Ftfl Proportional Limit, psi 50 000
'
4 . Modulus of Elasticity, psi r 29 000 000 29 000 000 29 000 000
E 29 000 000
5 Elongation in 2 in., % 12
-
' Feu Ultimate (block) Stress, psi 90 000 95 000 76 6002 100 000
6 , -
7 Foy Yield Stress, psi 70 000 75 000 85 000
8 F op Proportional Limit, psi 50 000
9 F„ Column Yield Stress, psi 74 100 79 500 90 100
10 Be Modulus of Elasticity, psi 29 000 000 29 000 000 29 000 000 29 000 000
,
11 F„ Ultimate Stress, psi N 55 000 52 500 58 000
65 000
12 Fst Torsional Modulus of 80 000 80 000 73 500 84 000
Rupture, psi
13 Fsp Proportional Limit 40 000 40 000
(torsion), psi
14 G Modulus of Rigidity 11 000 000 11 000 000 11 000 000 11 000 000
(torsion), psi /
- ,
1-r 15 Fbr M- 140 000 140 000 130 000 147 000
il Ultimate Stress, psi
go
-
16 Rockwell Number
,17 1 Brinell Number --
g 18 Fbe Bending Endurance Limit, psi 45 000 45 000
E. (300,000,000 cycles of completely reversed stress)
.4
19 Fee Torsional Endurance Limit, psi .
(20,000,000 cycles of completely reversed stress)
20 w Specific Weight, 0.2833 lb/cu in. 490 lb/cu ft.
, ..
r 2/ Nominal
Chemical Composition
.411=1 22 REMARKS line are for use properties received". it connection with stated are guaranteed If annealed and reheatWith reference intended for tubing 4 should also be normalized is not to civil aircraft only. Their use is permissable
1. See notes in Chapter 3. must be used. but is of the tubing. These properties
2. The properties in this provided that the tensile apply only to tubing "as and column 2 of this Table applicable to solid sections, near the weld. (See Sec. normalized, where, in 1.341) Column in column 4 of Table 4-'7
this instance, seven or More by a materials been obtained as two members. welds at angles or less are used, in column 3, this value is not
near welds to plastic instability of the wall
the steel is welded and then
by the manufacturer -treated, the properties to Feu .,- 76, 600 psi where failure is due used in cases where be interpreted as the allowable stress unless the joint or procuring agency.
or less to the center stress near the
welding are given
heat-treated. by dividing mallet for whioh
through
welds formed
to be
3. In welded structures where the normal allowable stress specific authority has a joint should be assumed members converge, factor of 1.5, from the licensing shall be determined is reenforoed in a
4. Where joints with tapered by outs of 60 degrees 94,500 psi. of 30 degrees the allowable tensile A tube that is continuous
5. Tension and bending allowables heat-treated after line, or fish mouth welding can be assumed
in Sec. 4.510.
4-12
ANC-5- Amendment No. 1. Oct.
TABLE 4 ... 9 (2)
MECHANICAL PROPERTIES OF MATERIALS ' ALLOY STEELS
CONDITION (i) (i) (i) (i)
HEAT TREATED TO HEAT TREATED TO HEAT TREATED TO HEAT TREATED TO
Fes .100 000 psi Ftee126 000 psi Ftes150 000 psi 1.1„.180 000 psi
SPECIFICATION ARMY
NAVY -
FEDERAL - -
SAE
1 Ftu Ultimate Stress, psi 100 000 125 000 150 000 180 000
;a 2 Fty Yield Stress, psi 80 000 100 000 , 135 000 165 000
o 3 Ftp Proportional Limit, psi 70 000 90 000 115 000 140 000
R
4 E Modulus of Elasticity, psi 29 000 000 29 000 000 29 000 000 29 000 000 ,
6 Elongation in 2 in., % , .
.
• Feu Ultimate (block) Stress, psi 100 000 125 000 150 000 180 000
COMPRESSION
1-4
0 co CO ...1 CD
F.7 Yield Stress, psi 100 000 135 000 165 000 ,
1
F op Proportional Limit, psi 70 000 90 000 115 000 ..,
140 000
Foo Column Yield Stress, psi 80 000 100 000 135 000 165 000
B0 Modulus of Elasticity, psi 29 000 000 29 000 000 29 000 000 29 000 000
- ,
11 Fs, Ultimate Stress, psi * 65 000 75 000 90 000 105 000
12 Fst Torsional Modulus of 90 000 110 000 125 000 . 145 000
Rupture, psi
13 Fep Proportional Limit 66 000 65 000 80 000 95 000
(torsion), psi
14 G Modulus of Rigidity 11 000 000 11 000 000 11 000 000 11 000 000
(torsion), psi
1 16 Fbr Ultimate Stress, psi 140 000 175 000 190 000 200 000
2
co
16 Rockwell Number
17 Brinell Number
El 18 Fbe ..-1 50 000 oompletely reversed stress) 78 000 85 000
V4 Bending Endurance Limit, psi 65 000
(300,000,A0 cycles of
19 Fs. Torsional Endurance Limit, psi _
(20,000,000 cycles of completely reversed stress)
20 a, Specific Weight, 0.2833 lb/6u in. 490 lbiou ft.
21 Nominal • Chemical Composition
22 REMARKS
(1) See notes in Chapter 3.
(2) Except as noted, the values given in this table apply to any of the structural alloy steels
containing less than 1/2 percent carbon. Any of these steels will display the properties
given in the column oorresponding to its ultimate tensile stress. These values apply to the materials in various forms, Isiah as bars, rods, tubes, sheet, castings, forging., etc. In the case of castings , the above values correspond to those obtained from test bars. Reference should be made to the specific requirements of the procuring or certificating agency in regard to the use of the above values in the design of castings.
•
4-13
ANC-5- Amendment No 1- Oot- 22. 19A
TABLE 4 ... 10 (2)
MECHANICAL PROPERTIES OF MATERIALS ALLOY STEELS
CONDITION HEAT TREATED (3)
TO F+ 200 000
psi
SPECIFICATION ARMY
NAVY
FEDERAL .
,
SAE1
O3 1 Ftu Ultimate Stress, psi 200 000 ..-
n . _
2 Ft, ' 165 000
Yield Stress, psi
o Ftp Proportional Limit, psi 150 000
' 4 E Modulus of Elasticity, psi 29 000 000
5 Elongation in 2 in., %
• Ultimate (block) Stress, psi • 200 000 -
COMPRESSION o co co -4 o
tiq .4 .4 .4 .4
0 0 0 NJ
Yield Stress, psi 165 000 .
Proportional Limit, psi 150 000
Column Yield Stress, psi 165 000
Modulus of Elasticity, psi
11 Fsu Ultimate Stress, psi 115 000
12 Fst Torsional Modulus of 155 000
Rupture, psi
13 Fsp Proportional Limit 105 000 _
(torsion), psi .
14 G Modulus of Rigidity 11 000 000 .
(torsion), psi
H 15 Fbr Ultimate Stress, psi
16 Rockwell Number
17 - . _Brinell Number
1 18 Fbe Bending Endurance Limit, psi 94 000
H (300,000,000 cycles of completely reversed stress)
!a-14 o.
19 Fs, Torsional Endurance Limit, psi .-
(20,000,000 cycles of .completely reversed stress) _
. 20 w Specific Weight, 0.2833 lb/cu in. 490 lb/cu ft.
.
_ 21 Nominal
. Chemical Composition .
4-.14
See notes in Chapter 3.
22
REMARKS
(1)
(2) Except as noted, the values given in this table apply to any of the structural alloy steels containing less than 0 percent carbon. Any of these steels will display the properties given in the column corresponding to its ultimate tensile stress. These values apply to the materials in various frame, such as bars, rods, tubes, sheet, castings, forgings, etc. In the case of castings the above values correspond to those obtained from test bars. Reference should be made to the specific requirements of the procuring or certificating agency in regard to the use of the above values in the design of castings.
( 3 ) The use Of higher heat-treatments than that corresponding to P. 180 000 psi shall be based on rulings of the procuring or licensing agenoies.
TABLE 4 - 11 Lt_1_,
MECHANICAL PROPERTIES OF MATERIALS CORROSION RESISTING (STAINLESS)
STEEL SHEET AND STR I P
CONDITION ANNEALED SHEET AND STRIP COLD ROLLED SHEET AND STRIP.
•
1/4 HARD 1/2 BARD 3/4 HARD HARD
SPECIFICATION AN -QQ-S -772, Class I and II
r
Compression [ Tension 1 Fiu Ultimate Stress, psi L2 T2 75 000 125 000 150 000 175 000 185 000
75 000 125 000 150 000 175 000 185 000
2 Fiy 3 L T 30 000 75 000 110 000 135 000 140 000
Yield Stress, psi 30 000 75 000 110 000 135 000 140 000
3 F Proportional Limit, psi 5 L T 14 000 35 000 35 000 45 000 55 000
, tp 16 009 45 000 55 000 55 000 55 000
,
A 11 . L T 29 000 000 27 000 000 26 000 000 26 000 000 26 000 000
' Initial Modulus 4 29 000 000 28 000 000 28 000 000 28 000 000 28 000 000
of Elasticity, psi ,
5 % Elongation in 2 Inches L T Class I7-8 12 7-8 3-7 3-4
40 12 3-7 3-4
40
Class II L T 40 25 15-18 10-12 8-9,
40 25 15-18 10-12 8-9
. .-
6 F Ultimate (block) Stress, psi L 50 000 110 000 130 000 155 000 170 000
Cu T 50 000 130 000 155 000 175 000 195 000
7 F Yield Stress, psi L T 35 000 65 000 85 000 95 000 105 000
cy 35 000 100 000 120 000 140 000 170 000
8 F cp12 L T 12 000 28 000 34 000 40 000 48 GOO
Proportional Limit, psi 000 55 000 66 000 70 000 80 000
9 ?co 5 L T 35 000 65 000 105 000 125 000 150 000
Column Yield Stress, P ei 35 000 110 000 135 000 165 000 190 000
10 E0 Initial Modulus 4 L 28 000 000 '26 000 000 26 000 000 26 000 000 26 000 000
of Elasticity, psi 7 28 000 000 27 000 000 27 000 000 27 000 000 27 000 000
'° 11 Fsu Ultimate Stress, psi 40 000 67 500 ,80 000 95 000 100 000
2
co
12 Fst Torsional Modulus 46 000 80 000 90 000 110 000 115 000
of Rupture, psi .
13 F sp Proportional Limit, , . -
(torsion)
psi
14 Gpsi Modulus of Rigidity, 12 500 000 12 000 000 11 500 000 11 000 000 11 000 000
(torsion)
co 15 Fbr Ultimate Stress, psi - 75 000 150 000 180 000 190 000 195 000
--.
,
0 co
16 w Rockwell Number B 80 - - ... ..
C - 25 32 37 41
17 Brinell Number 150 255 297 342 387
g 18PI,. Bending Endurance Limit psi (20 000 000 cycles) L T 33 000 62 000 72 000
-r4 33 000 62 000 72 000
,fs r'a` Ih.,
19 Fse Torsional Endurance Limit psi 30 000 50 000 54 000
(20 000 000 cycles)
6 - 20 W Specific Weight, lb/cu in. 0.286 -1
-
REMARKS notes in Chapter 3. •
Longitudinal direction to rolling.
Transverse direction to rolling.
0.2% offset yield stresses and the 0.01% offset proportional limit were
on the basis of the initial moduli of elasticity, as shown by
stress-strain data.
moduli should only be used up to the proportional limit. Beyond this
refer to the Tangent Moduli Curves, Figures 4-23 to 4-26
values of Fwece determined by extending the Tangent Moduli Curves to
moduli villas.
date are based on relatively few tests, and therefore are to be used
as a guide in design.
determined
1. See
2. L = T
' 3. The
toe
4. Initial value
5. The zero
6. These only
4-15
CHAPTER 5 ALUMINUM ALLOY
ALUMINUM ALLOYS ANC-5
Amendment No. 1.
Oct. 22, 1943.
5.0 GENERAL PROPERTIES
5.00 The allowable design properties of various aluminum alloys are listed insthe tables at
the end of this chapter. In general these design properties are based upon the minimum strength properties guaranteed by the material procurement specification. However, in the case of certain of these materials, the Army and Navy are currently permitting
Amend-1 the use of design properties in excess of those which are based upon minimum specification values. These higher design allowables have been determined from extensive statistical strength data obtained in the inspection testing of the particular materials, and the values which have been selected represent strength properties which will be equalled or exceeded by the properties possessed by approximately 90% of the material. In the case of a material for which the Army and Navy are permitting the use of these increased allowables two columns of values appear in the pertinent table. The column designated as applicable to the Army and Navy is based upon the above described probability criteria. The column designated as applicable to CAA is based upon the minimum specification values, In cases where only one column of allowables is included, this is based upon minimum specification values and is applicable to all agencies.
5.1 COLUMNS
5.10 Column Formulas
5.100 Primary Failure. The general formulas for primary instability are given in Sec. 1.27. For convenience, these formulas are repeated in Table 5-1 in simplified form applicable to round aluminum alloy tubes. These formulas can also be used for columns having cross sections other than those of round tubes when local instability is not critical.
5.101 Local Failure. Table 5-1 also contains notes and references concerning the local insta-
bility of round tubes. The local failure stresses for columns having cross sections
of other shapes are given in the allowable stress curves at the end of this chapter.
5.11 Column Stress Curves. Curves of the allowable column stresses for various cross sectional
shapes am given in Figs. 5-1 to 5-6. The allowable stress is plotted against the effective slenderness ratio which is defined by the formula:
L'/p = L /p 4 (5:1)
The geometrical properties of circular corrugations are given in Fig. 5-7 in order to facilitate their use in conjunction with Figs. 5-3 to 5-6.
5.2 BEAMS
5.20 General. See Sec. 1.21, Eq. 1:3, and Sec. 1.414 for general information on beams.
5.21 Simple Beams. Beams of solid, tubular, or similar cross sections can be assumed to fail
through exceeding an allowable modulus of rupture in bending (F,). For solid sections it can usually be safely assumed that Fb equals the ultimate teksile stress.
5.210 Round tubes. For round tubes the value of F will depend on the D/t ratio as well as the ultimate tensile stress. The bending modulus of rupture of 17ST round tubes is given in Fig. 5-8. It should be noted that these values apply only when the tubes are restrained against local buckling at the loading points. (These curves were obtained from National Bureau of Standards test data).
5.211 Thin-Walled Cylinders. Information on the failure of thin-walled cylinders in bending is given in Secs. 1.631 and 1.641.
5 - 1
_ AA • 1 • C1i T . Note (a). L 1/p L'/p shall not exceed 150 without specific authority from the procuring or certificating agency.
raI %I.° K 4 C4 A Note (b). Critical LYp is that above which the columns are "long" and below which they are llshortli. Note (c). Must be determined by test unless conservatively assumed.
1 6.0 al
K 4
..,
Fong Columns (a) CI par_ , a a 105.8x106/(Lo/p)*
r et „ft, --..
.......• ..... 0 .....,
0 8 2
g ri 14
• (X)
18 0 hc;
ri •-1
Critical L'/P(b) L0 g........ Pel N a °Catli, • CV C...
to • 8 g; i
i-1
e
7 tO r446. 2'693-000`L2 42,500-550.5 L' /p 50,000-421.0 L'/p "A0,000-700.0 L' /p
8 co ,
it N
, . ' rl
•
0
o P14 . 0 , § §
ft tin @ Si gil
44 ' , ' te) cg
+ 4. 40
e-L_ L. j
tb
ttr 8 0 4 3
c‘P to
.0
,....
ea Aluminum Alloy General 12 17ST &I M . rn Nt1 CU
il 4. (As received) V
as as Oi
4308 E
Alk 413
t.- al
r-4 0
XI
12
5 -- 2
ANC-5, Amendment No. 1, Oct. 22, 1943,
5.212 Unconventional Cross-Sections. Sections other than solid or tubular should be tested to determine the allowable bending stress.
5.22 Built-up Beams. Built-up beams will usually fail due to local failures of the component parts. In aluminum alloy construction the strength of fittings and joints is an important feature.
5:23 Thin-web beams. The allowable stresses for thin-web beams will depend on the nature of the failure and are determined from the allowable stresses of the web in tension and of the flanges or stiffeners in compression. See Ref. 15 for general stress analysis methods.
5.3 TORSION
5.30 General. The torsional failure of aluminum-alloy tubes may be due to plastic failure of the metal, elastic instability of the walls, or to an intermediate condition. Pure shear failure will not usually occur within the range of wall thicknesses commonly used for aircraft tubing.
Allowable Torsional Shear Stresses. In the range of low values of D/t no theoretical formula is directly applicable. The result of tests have been used to determine the empirical curves of Fig. 5-9.
For high values of D/t the equations given in Sec. 1.632 can be used provided that the allowable stress so determined does not exceed the proportional limit in shear.
5.4 COMBINED LOADINGS
5.40 Round Tubes in Bending and Compression. The general theory of failure under combined loadings is given in Sec. 1.424. In the case of combined bending and compression it is necessary to consider the effects of secondary bending, that is, bending produced by the
Amend-1 axial load acting in conjunction with the lateral deflection of the column. In general, Eq. 1:37, Sec. 1.424 can be used in the following forms for safe values:
fb c
Fb F 1.0
cy
where fbl = maximum bending stress including effects of secondary bending.
Fb = bending modulus of rupture.
fc = axial compressive stress.
Fcy = compressive yield stress.
In no case shall the axial compressive stress, fe, exceed the allowable stress, Fc, for a simple column.
5.41 Tubes in Bending and Torsion. Equations 1:37 Sec. 1.424 can be used in the following forms for safe values:
Round tubes:2 Streamline tubes: Rb
Higher values can be used if substantiated by adequate test data.
5.31
(5:2)
Rb+ RS2 = 1.0
+ Rs = 1.0
(5:3)
(5:4)
5 - 3
5.42 ANC-5, Amendment No. 1, Oct. 22, 1943.
Amend-1 Tubes in Bending, Compression and Torsion. The bending stresses should include the effects of secondary bending due to compression. The following empirical equation will serve as a working basis, pending a more thorough investigation of the subject:
fb fc f 2
b cy s
In no case shall the axial compressive stress, f c, exceed the allowable stress, Fc2 for a simple column.
5.5
5.50 Bolted and Riveted Joints.
5.500 Shear. The allowable shear stresses for protruding head rivets are given in table 5-14. It will be noted that the shear strength values for rivets may be based on the rivet area
Amend-1 deteraped from the nominal hole diameter provided that the nominal hole diameter is not larger than the value listed in Table 5-14. In cases where the nominal hole diameter is larger than the listed value, computations of rivet area should be based on the listed hole diameter and not on the actual value. It will be noted that values for the allowable bearing strength of rivets are also given in Table 5-14. These allowable bearing stresses are 3.33 times the allowable shear stress values.
5.501 Bearing. The basic values of allowable bearing stresses for aluminum alloys will be found in the tables at the end of this chapter. These values apply only when cylindri-
Amend-2 cal holes are involved (see Section 5.503 regarding Flush Rivets). The bearing yield stresses given in these tables are the stresses which will result in permanent set in the hole (in a single sheet) equal to 2% of the hole diameter. In the case of riveted joints using protruding head rivets it should be noted that these bearing values are applicable only when the DA ratio is less than 5.5, and that the allowable bearing stress for such joints should not exceed the allowable rivet bearing stress as given in Table 5-14. When the DA ratio is greater than 5.5, the allowable bearing strengths must be substantiated by test covering both yield and ultimate of the joint.
In computing the allowable bearing load, the bearing area may be based on the nominal hole diameter, with the restrictions outlined in Section 5.500.
The bearing stresses given in the Tables at the end of this chapter are to be used only for the design of the connecting elements of rigid joints when there is no possibility of relative movement between the parts joined without deformation of these parts. For other types of joints the allowable bearing stresses are to be reduced by dividing by the factors of safety (designated as "bearing factors") specified in Table 4-2.
5.502 Hollow-end rivets. If hollow-end rivets with solid cross-sections for a portion of the length (AN450) are used, the strength of these rivets may be taken equal to the strength of solid rivets of the same material, provided that the bottom of the cavity is at least 25 percent of the rivet diameter from the plane of shear, as measured toward the hollow end, and further provided that they are used in locations where they will not be subjected to appreciable tensile stresses.
5-4
JOINTS, FITTINGS AND PARTS
ANC-5, Amendment No. 1. Oct. 22, 1943
5.5o3 Flush Rivets. Tables 5-16, 5-17 and 5-18 contain allowable single-shear and bearing
strength data applicable to both machine countersunk and dimpled flush riveted joints
employing rivets with head angles of 78°, 100° and 115°, respectively. These strength Revised values are applicable when the edge distance is equal to or greater than two times the Dec., nominal rivet diameter. The allowable bearing loads have been established from test
1942 data using the lower of either of the following values:
(1) Value equal to ultimate test load times 1/1.15
1.5
(2) Value equal to yield test load times 1715 The yield load is taken
Amend-1 at a permanent set across the joint of 4% of the nominal rivet diameter.
5.51 Welded Joints. Since torch welding generally is not considered acceptable as a method of joining major structural parts wade of aluminum alloy, no values for allowable stresses for such joints will be given.
•
5.52 Tension Lugs. The strength of tension lugs can be computed by the fomulas given in Sec. 4.53.
5 - 5
ANC-5. Amendment No. 22
.• .
TABLE 5 - 2 (1)
ALLOWABLE DESIGN PROPERTIES .
(in 1000's of psi) • • ALUMINUM ALLOY 143
. ,
CONDITION 14ST EXTRU- DED SHAPES. 14ST EXTRU- DED SHAPES • THICKNESS 14ST EXTRU- DED SHAPES. THICKNESS (0.750" and 14ST EXTRUDED SHAPES (all thick-nesses af-ter heat-treatment) .
THICKNESS (0.50" to up)
(0.125" to 0.749")
0.499")
.
Specification Army AN-A-8 AN-A-8 AN-A-8 AN-A-8
_ Navy . , AN-A-8 AN-A-8 AN-A-8 AN-A-8
1. Ftus Tension Ultimate Stress 60 65 68 60
2. Fty, Tension Yield Stress 50 55 58 50
5. Elongation in 2 in., %
7. Far Compression, Yield Stress 50 55 58 50
11. Feu, Shear Ultimate Stress 36 36 ' 36 36
15. earing Uitirnte, , 90 90 90 90
Fbru,B (e/D=1.5)) . _
Stress'
Bearing Ultimate , 114 114 114 114
Fbru, Stress (e/D2c2.0)
F Bearing Yield . 70 .70 '70 70
bry, Stress ke/D=g1.5)
Fib Bearing Yield (e/b:=2.0) 80 80 80 80
17, Stress
4. E, Eco Modulus of Elasticity 10,500 10,500 10,500 10,500
&
10.
14. G, Modulus of Rigidity 3,900 3,900 3,900 3,900
20. w, Specific Weight 0.101 lbsiou. in. 174 lbs/cu. ft.
See Notes in Chapter 3 Remarks:
(1) For extrusions with outstanding legs, the load carrying ability of such legs
should be determined on the basis of the properties in the appropriate column
corresponding to the leg thickness. .
(2) D.:hole diameter; e.edge distance measured from the hole centerline in the
direction of stressing. Use value of e/D=.2.0 for all larger values of edge distance.
. •
5 - 6
TABLE 6 - 3 ALUMINUM ALLOY 17S
. ALLOWABLE DESIGN PROPERTIES ,
(in 1000's of psi)
CONDITION 17ST BAR 17ST BAR 3.0" thick) - ,
AND ROD AND ROD 17ST .
(up to .750" (.751" to EXTRUDED
thick) SHAPES
Specification Army QQ-A -351 QQ-A-351 QQ-A -351 - .
,
Navy QQ-A-351 QQrA-351 QQ-A-351
. .
1. Ftu, Tension Ultimate Stress 55 55 50
4
2. Fty, Tension Yield Stress 32 32 32
5. Elongation in 2 in., % 12
7. Foy, Compression Yield Stress 32 . 32 30
, .
11. F,u, Shear Ultimate Stress 34 34 31
15. Bearing Ultimate (1) 83 83 75
Stress (e/D,=1.5)
Ultimate,._ 105 105 95
fibru, Bearing e
Stress ( /D..2.0)
Fbr7i Beariimstres Yiesld (e/b .5) 45 45 45
Fbry, Bearing NrYeis:ld 51 . 51 51
(e/D:=2.0) ,
4. Es Bo; Modulus of Elasticity 10,500 10,500 10,500.
10. .
14. G, Modulus of Rigidity 3,900 3,900 3,900
20. w, Specific Weight 0.101 lb cu. in. 174 lb/ou. ft.
See Notes in Chapter 3 ---1..-- •
Remarks:
(1) D=hole diameter; eniedge distance measured from the hole centerline in the direction of stressing. Use value of e/b=m2.0 for all larger values of edge distanoe.
. s
5 -
, , , __ •
TABLE 5 - 4 ALUMINUM ALLOY 24ST (1) HEAT-TREATED BY USER
ALLOWABLE DESIGN PROPERTIES
(in 1000's of psi)
CONDITION 24ST SHEET AND PLATE ALCLAD 24ST ALCLAD 24ST SHEET AND .
SHEET. PLATE. THICKNESS
THICKNESS ..›..064"
.‹.064"
Specification fly AIT,A..12 AN...A..13 AN.A.AM .
_ _
Navy AN-A-12 AN-A-.13 AN-A-13
. .
1. Ftu, Tension Ultimate Stress 62 56 60
2. Fty, Tension Yield Stress 40 37 38
5. Elongation in 2%4
7. Foy, Compression Yield Stress 40 . 37 38
11. Fmi, Shear Ultimate Stress 37 34 36 .
,
15. Bearing Ultimate 93 84 90
Fbru' Stress (e/D=1.5)
Floru' Bearing Ultimate , 118 106 114
Stress (e/Dx-'2.0)
F Bearing Yield 56 52 ' 53
bry, Stress (e/D=1.5) _
Bearing Yield 64 59 61
Fbry' Stress (WD:=2.0) .
.
4. E, Ec;Modulus of Elasticity 10,500 Pri:10,500(3) Sec: 9,500 Pri:10,500 ),
& Seo:10,000•
10.
14. G' Modulus of Rigidity 3,900 _
20. w, Specific Weight 0.100 lb/cu.in 173 lb/cu.ft
See Notes Notes in Chapter 8 Remarks:
(1) This table applies to all material supplied in the "0" temper and heat-treated by the user, and to all material supplied in the "T" temper and subsequently reheat-treated by the user.
(2) D=hole diameter; e==edge distance measured from the hole centerline
in the direction of stressing. Use value of elb=.2.0 for all larger values of edge distance.
(3) Effective modulus for columns may be assumed to be 10.2x106 psi.
(4) Effective modulus for columns maybe assumed to be 10.3x106 psi
5 - 8
ANC-5. Amen•ment No. 1. Oct. 22, 1913
( )
ALUMINUM ALLOY 24S AS FURNISHED BY MILL
TABLE 5 - 5
ALLOWABLE DESIGN PROPERTIES (in 1000's of psi)
24ST SHEET. THICKNESS
.00.250"
24ST PLATE. 24ST PLATE.
THICKNESS THICINESS
(0.251" to (1.001" to
1.000") 2.000")
24ST ROD
AND BAR
4C:3.000"
Army
Navy
Specification
AN-A-12
AN-A-12
AN-A-12 AN-A-12
AN-A-12 AN-A-12 QQ-A.,354 QQ-A-354
Army Navy CAA Army Navy Army CAA Army Navy CAL
CAL Navy_ _
1.1 Fill, Tension Ultimate Stress 66 64 66 62 63 60 64 62
Bearing Yield /D2.0) 80 79 80 64 79 64 69 64
Fbry, Stress (e/
F Tension Yield Stress 43
Elongation in 2 in., %
42
43
40
42
40
43
40
40
42
39
43
40
40 42
38 38
Fes, Compression Yield Stress F,u, Shear Ultimate Stress
40
36
43
38
40
38
15.
Bearing Ultimate, (2)
'bru' Stress (e/D=1.5)
Bearing Ultimate
Pbrus Stress ke D=2.0)
99
98
99
93 94
90
96
93
125
123
125
118 120
114 122
118
F , Bearing Yield (ey_
D
bry Stress / 1.5)
70
69
70
56 69
56
60
56
4. 10. 14. 20.
K, Eo; Modulus of Elasticity
G, Modulus of Rigidity
w, Specific Weight 10,500 10,500 10,500
3,900
0.100 lb/cu. in. 173 lb/cu. ft.
10,500
3,900.
Remarks:
(1) This table applies only to material supplied by the mill in "T" temper, and so used without a reheat-treatment.
(2) D=hole diameter; ez.edge distance measured from the hole centerline in the direction of stressing. Use value of e/D=2.0 for all larger values of edge distance.
5 - 9
See Notes
N m
TABLE 5 - 6 . _
ALLOWABLE DESIGN PROPERTIES (1)
(in 1000's of psi) ALUMINUM ALLOY 248
0 AS FURNISHED BY MILL
CONDITION ' ALCLAD 24ST SHEET. THICKNESS ALCLAD 24ST ALCLAD 24ST ALCLAD 24ST
4.<0.064" SHEET AND STRIP STRIP
PLATE < 0.064" .11" 0.064"
(0.064" to
0.500")
Specification I know AN-A-13 AN-A-13 AN-A-13 AN-A-13
Navy AA-A-13 AN-A-13 AN-A-13 AE-A-13
Arm CAA Army CAA
Navy _ Navy
1. Ftu, Tension Ultimate Stress 61 59 64 62 56 60
2. Fty, Tension Yield Stress 41 39 42 40 37 38
5. Elongation in 2 in., %
7. Foy, Compression Yield Stress 41 39 42 40 37 38
11. Fsu, Shear Ultimate Stress 37 38 38 38 34 36
15. Fbru, BearigeUlsstimatt4A.1.5) (2) 91 90 96 95 84 90
Fbrus BearimMimate i 116 114 122 120 106 114
k V D 2.0)
Bearing Yield ( , ,‘ 67 65 69 66 52 53
FbrY' ' Stress ei'/D=1'..Q)
Fbry, Beag%sYield (e/D 2.0) 76 74 78 75 59 61
4. 11, NO Modulus of Elasticity PHI 10,5083) Pri: 10,500 Sec: 10,000 Pri: 10,5(C08) Pri: 10,W Sec: 10,000
& Sec: 9,500 Sec: 9,500
10,
14. G, Modulus of Rigidity
20. Ir, Specific Weight 0.100 ib u. in. 173 lb/eu. ft.
4 Remarks:
See Notes in Chapter 1. —I"— (1) This tablerapplies only to material supplied by the mill in the "T" temper, and so used -without a reheat-treatment.
(2) D..hole diameter; e..edge distance measured from the hole centerline
in the direction of stressing. Use value of q/D==2.0 for all larger values of edge distance.
(3) Effective Modulus for columns may be assumed to be 10.2 x 106 psi.
(4) Effective Modulus for columns may be assumed to be 10.3 x 106 psi.
•
5 - 10
588217 0 - 43 - 3
C-5. Amendment No. 1. Oct. 22
TABLE 5 - 7 ALUMINUM ALLOY 24S
ALLOWABLE DESIGN PROPERTIES •
(in 1000's of psi)
CONDITION 24SRT SHEET ALCLAD 24SRT ALCLAD 24SRT
AND PLATE. SHEET. SHEET AND
THICKNESS THICKNESS PLATE.
0400* 0.0.064" THICKNESS
, ;at0.064"
.
Specification Army AN-A-12 AN-A-13 AN-A13
,
Navy AN-A-12 AN-A-13 AN-A-13
. ,
Army Navy CAA Army Navy CAA Army Army CAL
1. Ft , Tension. Ultimate Stress 71 69 66 62 68 66
2. Fty, Tension Yield Stress 55 52 51 48 53 50 .
5. Elongation in 2 in., %
7. Foy' Compression Yield Stress 55 52 51 48 53 50
11. Feu, Shear Ultimate Stress 43 42 40 38 41 41
1" Beargfellitimate(eib.1.5)(1) Fbru, 106 105 99 95 102 100 •
Bearing Ultimat 135 133 125 120 129 127
p . e(e/D=2.0)
bru. Stress
FbrisBealue: fields (e/b.1.5) 88 83 81 77 84 80
.
F Bearing Yield 100 95 93 88 97 91
117' Stress (e/D=2.0) . .
4. E, Eo; Modulus of Elasticity 10,500 (2) Pri:10,500(3) Sect:10,000
& Pri:10,500
10. Sea; 9,500
14. G, Modulus of Rigidity 3,900
20. w, Specific Weight 0.100 lbiou. in 173 lb/cu. ft.
See Notes in Chapter 3 Remarks:
(1) D= hole diameter; e==edge distance measured from the hole centerline in the direction of stressing. Use value of e/D..2.0 for all larger values of edge distance.
(2) Effective Modulus for oolmmns may be assumed to be 10.2 x 106psi.
(3) Effeotive Modulus for columns may be assumed to be 10.3 x 106 psi.
5-11
nr.+ 1P)
• --______=__ M ___ _J. --.
TABLE 5 - 8 (1)
ALLCWABLE DESIGN PROPERTIES . (in 1000's of psi) ALUMINUM ALLOY 244 ARTIFICIALLY AGED
CONDITION (2) (2) ALCLAD (3) (3)
- ALCLAD 248-T80. THICKNESS 24S-780. THICKNESS ALCLAD 24S-T81. THICKNESS ALCLAD 24S-T81. THICKNESS IP .064"
< .064" , .064" 4 .064" .
.
Specification ArmY 11 354 11 354 11 354 11 354
Nav7(81 ,
(4) ..
1. Ftu,Tensian Ultimate Stress L 60 62 64 67
...
T 60 62 62 65
...
2. Ft,Tension Yield Stress L 47 49 56 59
T 47 49 54 56
5. Elongation in 2 in., % n L 8 8 5
5T
8 8 5 5
, .
7. Foy, Compression. Yield Stress L , 47. 49 55 57
...--
T 47 49 E5 57
11. Fsu•Shear Ultimate Stress 35 36 36 38
15. Bearing Ultimate (e/Dx,1.55) 90 93 9A 100
Fbru Stress
Bearing Ultimate (/_. 114 118 122 127
e
Fbru* /1) 2.0)
Stress
Fbry, Bearlueneld (e/D =1.5) 66 69 . 78 83
Fbry, Bearing Yield (e/D=2.0) 75 78 90 94
Stress
4. E E ; Modulus of Elasticity (6) (7) (6) (7)
& si, 0 Pri: 10,500 Pri: 10,500 Pri: 10,500 Pri: 10,500
10. Sec: 9,500 See: 10,000 Sec: 9,500 Sees 10,000
14. G, Modulus of Rigidity •
20. mr, Specific Weight 173 lb/cu. ft.
0.100 1b441.,. in./
1 . Remarks:
See Notes in Chapter 3 ---losi- (1) The values in this table are allowable design properties. However, the Army and Navy will permit higher allowable design properties, provided they are substantiated by adequate test data to the satisfaction of the procuring agency.
(2) This column applies to material for which "T" temper has been obtained by the aircraft manufacturer by heat-treating fram "0" temper, or by reheat-treating "T" temper material, followed by artificial aging.
(3) This column applies to "T" temper material mill-heat-treated and flattened, which has been artificially aged.
(4) Lam Longitudinal (with grain); 7= Transverse (across grain)
(5) Dm. hole diameter; e= edge distance measured fram the hole centerline
in the direction of stressing. Use value of e/D..2.0 for all larger values
of edge distance.
(6) Effective Modulus for columns may be assumed to be 10.2 x 106
(7) Effective Modulus far columns may be assumed to be 10.3 x 106
(8) Navy contractors shall obtain approval of their artificial aging processes (time and temperature control) prior to the use of artificially aged material in design.
5-12
ANC-5, Amendment 101.
. _
TABLE 5 9 (1)
ALLOWABLE DESIGN PROPERTIES ALUMINUM ALLOY 24$
(in 1000's of psi) ARTIFICIALLY AGED
_
CONDITION ALCLAD(2) 24S-T84. THICKNESS ALCLAD(2) 24S-T84, THICKNESS A-..064" ALCLAD (3) 24S-T86. THICKNESS 4C .064" ALCLAD (3) 24S-T86. THICKNESS
<.064" .064"
Specification Army 11 354 11 354 11 354 11 354
Navy 8)
(4)
1. Ftu, Tension Ultimate Stress L 67 70 68 71
.
T 66 69
2. Fty, Tension Yield Stress L 63 66 66 68
T _ 62 65
5. Elongation in 2 in., % L 5 5 4 4
T 3 3
7. Fey, Compression Yield Stress L 62 65 63 66
T 65 68
11. Fop Shear Ultimate Stress 38 40 38 40
15. Bearing Ultimate 100 105 102 106
Fu' Stress (e/b...1.5)0)
Bearing Ultimate , 127 .. 129 135
Fbrut Stress (e/Du.2.0) 133 .
,
Bearing Yield 88 92 91 95
Fbrys Stress (e/D .5)
Bearing Yield 101 106 104 109
Fbrys Stress (e/D 2.0)
4. E, E43; Modulus of Elasticity Pri:10,5(X)(6) Sec: 9,600 Pri:10,500(7) Sec:10,000 Pri:10,500(s) Sec: 9,500 Pri 310, 600(1 Sec:10,000
&
10.
14. G, Modulus of Rigidity .
,
20. w, Specific Weight • 0.100 lb/cu. in. 173 1.13/cu. ft.
See Notes in Chapter 3 —01— Remarks:
(1) The values in this table are allowable design properties. However, the ArMY and Navy will permit higher allowable design properties, provided they are substantiated by adequate test data to the satisfaction of the procuring agency.
(2) This column applies to "T" temper material which has been subjected to a stretching or rolling operation resulting in a permanent elongation or set between 3 0 and 4 percent, followed by artificial aging.
(3) This column applies to "RT" temper material which has been artificially aged.
(4) L ,.. Longitudinal (with grain); T.= Transverse (across grain)
(5) D==hole diameter; e==edge distance measured from the hole centerline in the
direction of stressing. Use value of e/Don2.0 for all larger values of edge distance.
(6) Effective Modulus for columns may be assumed to be 10.2 x 106 psi.
(7) Effective Modulus for columns may be assumed to be 10.3 x 106 psi.
(8) Navy contractors shall obtain approval of their artificial aging processes (time and temperature control) prior to the use of artificially aged material in design.
5 - 13
ANC-5. Amendment No. 1. Oct. 22. 19L1_
TABLE 5 - 10 c,
ALLOWABLE DESIGN PROPERTIES ALUMINUM ALLOY 248
. ..
(in 1000' s of psi)
CONDITION 24ST ROUND 24ST ROUND AND SQUARE 24ST
AND SQUARE TUBING (After re- heat Treat- STREAMLINE
TUBING ment) TUBING
(As Received)
S pecification Army 10 235 10 235 57 187-2
Navy MIT-T-785 MW-T-785 44-T-31
Army Navy CAA
1. Ftu, Tension Ultimate Stress 70 64 64 62
2. Fty, Tension Yield Stress 46 42 40 . 40
5. Elongation in 2 in., % .
7. Fey, Compression Yield Stress 46 - 40 40
42
11. Fsu, Shear Ultimate Stress 42 39 39 38 _
.
15. Bearing Ultimate (1) 105 96 96 93 -
Fbruo Stress (e/D = 1.5) _
Bearing Ultimate 133 Fbru° Stress (e/D = 2.0) 122 118
122
F Bearing Yield 64 59 56 56 ,
bry' Stress (e/D = 1.5)
Bearing Yield 74 67 64 64
Fbryt Stress (e/D = 2.0)
4. E, HO Modulus of Elasticity 10. 10,500 10,500
& • 10,500
14. G, Modulus of Rigidity 3,900 3,900 3,900
20. w, Specific Weight 0.100 lb/cu. in. 173 lb/cu. ft.
•
. , '
See Notes in Chapter 5 -oft- Remarks:
(1) D= hole diameter) e = edge distance measured from the hole centerline
in the direction of stressing. Use value of e/pms2.0 for all larger values of edge distanoe.
. .
5 - 14
ANC- •mdn
TABLE 6 - 11ALUMINUM ALLOY 24A1) EXTRUSIONS
ALLOWABLE DESIGN PROPERTIES
(in 1000's psi)
,
CONDITION 249T EXTRU- 24ST EXTRU- 24ST EXTRU- 24ST EXTRU- 124ST EXTRUSIONS (All thicknesses after heattreatrent)
• SIONS. SION. SIONS. SIONS.
THICKNESS THICKNESS THICKNESS THICKNESS
4(0.250" (0.250" to (0.750" to .2r.1.500"
0.749") 1.499")
Specification . Army QQ-A-354 QQ-A-354 QQ-A-354 QQ-A-354 QQ-A-354
,
Navy QQ-A-354 QQ-A-354 QQ-A-354 QQ-A-354 - QQ-A-354
Army Navy CAA ArmY Navy CAA Army Navy CAL Army Navy CAA
1. Ftu, Tension Ultimate Stress 61 57 63 60 65 65 70 70 57
2. F Tension Yield Stress 47 42 47 44 47 46 52 52 38
ty, , . .
5. Elongation in 2 in., %
7. F Compression Yield Stress Foy, 41 38 42 41 44 44 50 50 38
, .
11. F,u, Shear Ultimate Stress 37 35 37 36 37 37 38 38 35
. .
15.. Fbru,BearigglIimate001-1.5)(2) 91 85 91 85 91 85 91 85 85
FBearing Ultimate , 116 108 bru, Stress (e/D=2.0) 108 ' 116 108 116 108 108
116
.b s Bearing Yield 66 59 66 60 66 61 66 62 53
'ry Stress (e/D=1.5)
Fbry.Bearing Yield , / 75 67 75 ' 69 75 71 75 73 61
Stress ke/D=2.0)
4. E, leo Modulus of Elasticity 10. 10,500 10,500 10,500 10,500
& 10,500
14. G, Modulus of Rigidity 3,900 3,900 3,900 3,900 3,900
20. w, Specific Weight 0.100 lbAu. in. 173 lb/cu. ft.
See Notes in Chapter 3 -sr- Remarks:
(1) For extrusions with outstanding legs, the load carrying ability of suoh legs
• should be determined on the basis of the properties in the appropriate column corresponding to the leg thickness.
(2) . D.. hole diameter; emedge distance measured from the hole centerline in the
direction of stressing. Use value of e/D=.2.0 for all larger values of edge distance.
5-.15
ANC-5. Amendment No. 1. Oct. 22. 19L
TABLE 5 - 12 ALUMINUM ALLOY 52S
ALLOWABLE DESIGN PROPERTIES
(in 1000's of psi)
CONDITION. 52ST-1/4 H SHEET , 52ST-0 If SHEET 52ST-4/4 H 528T-H SHEET
SHEET
Specification Army . QS-A-318 QQ-A,318 QQ-A-318 QQ-A-318
Navy 47A11 47A11 47All 47A11
1. Ftu, Tension Ultimate Stress 31 34 ' 37 39
2. Fty' Tension Yield Stress , 21 24 29 33
5. Elongation in 2 in., % •
7. Fcy' Compression Yield Stress 21 24 29 33
11. Feu, Shear Ultimate Stress 18 20 22 23
15. Bearing Ultimate (1) 50 54 59 62
. Fbru, Stress (e/D = 1.5)
Fbru# Bearslgss timotet7D = 2.0) 65 71 78 82
Bearing Yield Fbry' Stress (e/D = 1.5) 34 41 46
29
,,,,, Bearing Yield 34 38 46 53
rbr ' Stress (e/D = 2.0)
4. H, Bo Modulus of Elasticity 10,000 10,000 10,000 10,000
&
10.
14. G, Modulus of Rigidity 3,800 3,800 3,800 3,800
20. w, Specific Weight 0.096 lb cu. in. 167 lb/cu. ft.
See Notes in Chapter 3 ---sui.- Remarks:
(1) D =hole diameter; e = edge distance measured from the hole centerline
in the direction of stressing. Use value of e/p.m2.0 for all larger values of edge distance.
5 - 18
ANC-5 Amendment No. . Oct. 22
TABLE 5 - 13 ALUMINUM ALLOY
ALLOWABLE DESIGN PROPERTIES 538
(in 1000's of psi) 618
CONDITION 53ST BAR. 61ST SHEET 61ST 61ST EXTRU-SIONS. ALL SIZES.
. HEAT TUBING .
TREATED AND
AGED.
Sp ecifications Army Q0 A-331 11 326 1W- T-789 ,
Navy QQ-A-331 QQ-A-327 7414,T=789
1. Ftu, Tension Ultimate Stress 32 42 42 38
2. F.,... Tension Yield Stress 25 35 35 . 35
,,,Y,
5. Elongation in 2 in., % 14 8 8 10
7. Fcy, Compression Yield Stress 25 35 35 35
11. Fsu, Shear Ultimate Stress 21 27 27 24
15* Bearing Ultimate (1) 51 67 67 61
vbru* Stress (e/D 1.1.5)
F Bearing Ultimate 67 88 88 80
bru, Stress . (e/D= 2.0) _
FBearing Yield (e/D:.1.5) 35 49 49 49
bry' Stress
Bearing Yield 4Q 56 56 56
Fbry' Stress (e/D=2.0)
4. & Es Ea; Modulus of Elasticity 10. 10,000 10,000 10,000
10,000
14. G, Modulus of Rigidity 3,800 3,800 3,800 3,800
20. 0.097 lb/cu. in. 0.098 lb in. 169 Ibicu. ft.
w, Specific Weight
w,
168 lbicu. ft.
See Notes in Chapter 3 ------auw— Remarks:
(1) D=hole diameter; e=edge distance measured from the hole centerline
in the direction of stressing. Use value of e/D=2.0 for all larger
values of edge distance.
5-17
ANC 5. Am endment No. 1. Oct. 22. 1943 •
Remarks:
(1) The driven head diameter shall be at least 1.3 times the nominal shank diameter of the rivet.
(2) The 5178T-A" designation refers to 17ST rivets aged at room temperature at least four days after quenching and before driving.
( 3 ) Shear and bearing strength values may be based on areas corresponding to the nominal hole diameter, provided that the nominal hole diameter is not larger than the value listed below. If the nominal hole diameter is larger than the listed value, the listed value shall be used.
STANDARD RIVET HOLE DRILL SIZES
AND NOMINAL HOLE DIAMETERS
Rivet Size 1/16 3/32 1/8 5/32 3/16 1/4 5/16 3/8
Drill No. 51 41 30 21 11 F P W
Nominal Hole .067 .096 .1285 ,159 .191 .257 .323 .386
Diameter
5 18
(1)
ALUMINUM ALLOY RIVETS PROTRUDING HEAD TYPE
TABLE 5 - 14
ALLOWABLE DESIGN PROPERTIES (in 1000's of psi)
CONDITION
568
24ST
A17ST
17ST
178T-A
( 2 )
AN-FF-a551 AN-FF-R551 AN-FF-R551 AN-FF-R551
CAA Army
Navy CAA
AN-FF-R551 AN-FF-R551
AN-FF-R551 AN-FF-R551
Army
Navy
Specification
Army Navy
AN-FF-R551 AN-FF-R551
ArmY Navy
CAA
Army
Navy
CAA
Feu, Shear Ultimate Stress (3) 30
Fbrm, Bearing Ultimate Stress (3) 100
28
34
33
38
35
43.
37
27
93
113
110
126
116
136
123
90
ANC-5, Amendment No. 1Oct. 22
TABLE 5 - 14A ,
ALLOWABLE DESIGN PROPERTIES (1)
(in 1000's of psi) ALUMINUM ALLOY
CASTINGS
CONDITION 195=14 195-T6 220-T4 CASTINGSMold B195-T6 (Permanent
SAND SAND SAND 356-T6 SAND CASTINGS Castings)
CASTINGS CASTINGS
Specification Army AN-W.1-390 AN-QQ-A-390 AN-WI-A-392 AN-QQ-A-394 AN-QQ-A-383
Navy AN-QQ-A-390 AN-QQ-A-390 AN-Qty-A-392 AN-QQ-A-394 AN-QQ-A-383
1. Ftu, Tension Ultimate Stress 29 32 42 30 35
2. Fty, Tension Yield Stress 13 20 22 20 22
- .
5. Elongation in 2 in., % 6 3 12 3 2
7. FAY' Compression Yield Stress 14 4 22 23 20
11. Fem, Shear Ultimate Stress 23 29 31 26
15. Fbru, Bearig.etjalstilnat:VD. 1.6)(2) _ _
Fbrus Bearing Ultimate 40 45 68
Stress (e/D..2.0)
F Bearing Yield f e/D - l .5 )
brys, Stress %
F Bearing Yield , . .
bry, Stress (e/D..2.0)
4. N, E0; Modulus of Elastioity 10,300 10,300 10,300 10,300
&
10.
14. G, Modulus of Rigidity 3,800 3,800 3,800 3,800
20. iv, Specific Weight Wm. in. 0.100 0.092 0.095
See Notes in Chapter 3 *r► Remarks:
(1) Reference should be made to the specific requirements of the procuring or certificating money in regard to the use of the above values id the design of oastings.
(2) D,= hole diameter; emedge distanoe measured from the hole centerline in the direction of stressing. Use value of e/D..2.0 for all larger values of edge distance.
5 - 18A
ANC--5. Amendmen
TABLE 5 - 14B NUM ALLOY FO ALUMRGINGS
ALLOWABLE DESIGN PROPERTIES
(in 1000's of psi)
(1)
CONDITION 14ST 17ST 26ST A.51ST 53ST
Army QQ-A-367 , QQ-A-367 0Q-4-367 QQ-A-367 QQ- -4Q7
Specification QQ-A-367 QQ-A-367 QQ-A-367 _ Q4-A-367 - -367
Navy
1. Ftu, Tension Ultimate Stress 65 55 55. 44 36
2. F+,_ Tension Yield Stress 50 30 30 34 30
"»
5. Elongation in 2 in., % 10 16 16 12 14
7. F05" Compression Yield Stress 50 30 30 34 30
11. Fsu, Shear Ultimate Stress 40 34 34 28 23
15.Fb Bearing Ultimate , (2) 98 83 83 70 58
ru. Stress (e/D=1.5)
F Bearing Ultimate, i 124 105 105 92 76
brus Stress (e/D=2.0)
.. Bearing Yield (e/11.1.5) 70 42 42 48 42
'brY4 Stress
... Bearing Yield 80 48 48 54 48
'Ion" Stress (e/D=2.0)
4. 10. 10,500 10,500 10,500 10,000 10,000
& B, Bo Modulus of Elasticity
14. G, Modulus of Rigidity 3,900 3,900 3,900 MOO 3,800
20. 'rip Speoifio Weight 0.101b u. in. 0.097 lbiou. in.
i Remarks:
See Notes in Chapter 3 ---00— (1) These properties may be used for Almninum Alloy Forgings up to 4 inches in
diameter or thickness. .
(2) D= hole diameter; e..edge distanoe measured from the hole centerline in the direotion of stressing. Use value of 0..2.0 for all larger values of edge distance.
5 - 18B
*I
NEMEMMOMOMOMMMEMMEMMOMUMMERMEMMEMMESMIEW7AMOMMEMMOOMOMMOMM11 OMMOSOMMMOMMOM moommommommunimanommommmommemomme.mmummumwmumpl=....ENFRs'Invm7momemmi
KMM111WMOMOROMMMEMIIMMOMMOMEMMEMMEMMEMMO,AMMUMOMMMOMMUMM,MAIREMEMMORMUMMEMOMMIMM mosmirommamismimmummanommummommmaidemminsimmummiggammomommismimmismi
j:
immommenrsbniummennumummommin me vmmommommumniwzmonsomma.qmommomm mmum NOMDOURIONSMWOMMEMMOMMEMMOOMMEMMEMIMMEMSEMBOMMINIMMMOMMEMEMEM:NOSMOMMOMMEM
■'5,LMOWX\nAMMIIMMOOMMOMEMMOMMEMINIAMMIIMMIMMOOMMEMEMMOSZNOMMSONIWZMEMEMMAMON SPfilk -mirmenommommummammimmommomplime BMSOMMIMMIIMMMOMMOOMMEMMOMMIIMME ■
uiiniir=fo h. A.d
MAMMESINUIM ,IIIIMMIONNINIMMOOMMEMOIMEMN ,mmuummossimmummom mom - ,mommimmiss
immommuomm _"47AniebnEnurzessummemnimissiir-aumnsosestmqwr,rcalrail34-iripraimmimumew sommoressomterombinamimanossmomm.immnaminaiazia4,-4.ilmia ii.aMMOREMMOMUMM MOMMUMMOMMMOMMONOSIKNEMWIMOOMMOREMMMMEZEMMEMEMEMUMMORMIIMMOM MMUMMEMMOIMMUMMEME ROMMOOMMEREMERMIIMMOOM.041=104MMEMMIHMIMM ',OMENS MMOMMUMEMEMM MMOMMIIMMEMEMSOMMOME
OMEMMIMMMOIMOSOOMMEMOMMO:M
• ".44
NEW11141111111111.1"AlinE104111111111M11111 . ;UN MEM= MO MINH EMU MI II Ma ENNIS!
1•111•11111Of - 41AuCi, 7,1,fflii31.E.2411.11111Mii......NIMIEM111111111.2.1%iiladisinromammemilMINIMIRMIIIIMIIIM Emeamosma
assms
minmemmommummumummemmEmmonsummiNzmg Z!mmummimumiLiammums.mmikammiwiamommsnm
MM
OMMOMOEMO RRIO
MMEMEMEMEMEMMAM MOUOMM OR IB
MMOOMMOM MU
MMO RMI MU
IMMOMMUMMUMM MEM
-
'me
ha....
MEMOMSM MEMOMEMONMEMM
50 40 30 20 10
Fc' ALLOWABLE COLUMN STRESS IN THOUSANDS OF PSI
50
40
30
20
10
0
0
II
OMMOOKIMMOMMOMMESUMMEMEMMEM IIMMUMMEM mmemmommesmosommommonsamplAiroIiiiiiuummaraim
MI111111111111111111111111111MMMENIMMMIIII UM MI 111111.011111W1,111111111MMINME
11211
4
20 40 60 80 100 120 140 160
(a) ROUND 17ST TUBING
IIIIMIHrlirrar1:11:1111111111:13:1111:111171111naall:M.111711:71:11111111110111.11ainnin
OMMEMMIRMOIRMSMOOMMEMMORMOMSUMEMWOMMEMEROMMMUMMOMMOMEMMOMMOMMOMMEMMINIMMOIMMEM IMMEMIIMOMOOMMOMMIIMMOMMOOMMUMMEMEMMEMEMONTOMMEMMEROMMEAMOMMOMMEMMEMOMMEMMOMMOOM MMOIMMOMMOMMINIMMUMOOMMOMMEMMUMMINIMMOMEMWTOMMEnOMMOOMIOMMEMMEMOMEMOMOMMOMMOMMONOMM OMMIIIMOOMMUMMUMMEMEMMOMMIMAMMOMOMMOMMOOMWAMISMIWOMEMMERMIMMOMMENUOMMIWOMMEMOMMEMEM MOMMMOMMOMMEMEMMEMEMMUMMUMMUMOMMOMMEMMIN.MMEMMOMMOSOMMEMOMFMMUMMMMIMMEMEMEMMIUM
:::::::!::::. imummlimmmummmmumaummauumm mommommummemmemommommummommill
embiAmmelesimsemmennus OMMEMMEMMO411.17EN. MMOOMMEROMMEMMOUMMEUMOMMOMMBOM esmacmmummommigligpmmummemil mumislsmathig.aidzmmacwommonsimmommompommomasm ommilwmummmmus•lornms 111.1111111111111 riMMEMMOMMUMMAWQMSMOMEMMEMOMMOMMEMEMOMMO 110111MMIMNIMOMMOMMOMME ROM. IIMMEMMEM 711MOMMIIREMMODOWPWALAIN:10AVLSCOMMOMMOM
iiNOMMIIMOhYMMOWAAM,7401-4. 01.66AbbildEMMEMOOM
1111111.0401111MW,PUISOMIlliambdulifillmiallIIIIIIMINREIM,E111111111111111111111111104MMIlkiq MOMMOMMEMMEMOMMME OPIPWMVOSIP nORMMUOMMOMMOOOMMEMEMMMEMMUSZEMSOMMEMMOMINAISOMMuiliNEMEMINIMUMSMMOMMEXIM aruumbilosa ,iitsimminsimosonsmassimissapommummensimKnommaaolunsimmomum mommxi-iihzt Timammommummaimmommommamormommuustall::1104:::::::::::::
maimm■mu .mum% fass:::::::CirainumalTillrimmolsostiormseia6ounsairmcmum mommummmmommumems,ga;d=i:ginimmommimosibzimmmlbzommmmumamm smmusw‘mignr,aile UNEMEMOMOOMMOMMOSEWS=WOMMEMMOMMEMEMMIOMMEMOMMaMMEMOMMEMINIMMO
MEMMIILVAMM OSCMSISSEMMOSUMMOMMILMEMMEMOMOMMEMEMMEMMOMMUMINZNOMmemMEMOMMO
MOMUMV4311SM giv,7mminommismemmommusmazommommommommummommismiumanimifimummommEm
immummoommum umbnammaimmmaimmommentommimmummom=.im7wsz7grvirrim&ammammumme SakiNUMW.MMIMMEMMEMMO,UMMINIMMEMMIWZia.iaddlOilia0W4AMMOMMOMMOMME .MPT4A10.1111:4MEMEMEMOMOAMMIIMEMEMMEMMEMMOMMOOMMEN.EMOMMEMEMMEMME
.-W&LignallikalligglUI:011171MORMIllrall0111111114:11111nnentrann:::1111 SIIIIINIMMIIIMISIMME1111111.11MMEsM11110.01.11MMIPLar;I:W.17111•••••■
momminimmommwmammimmsgmmummonicmmommuommawAimiummmumsgmnimmommommommommil MEMMEMMINIOOMMIMMOMMEMMIMMOMMMEM1041.NUMMEMMEMMAEMIWOMBOMMW,2111OMMEM,411111MEMMOMMIMEMM MMOOMMOMMEMMUMMEMOMMEMOMMEMMINIMMOliNCOMOMMOMOMMOMMIESOMMANOOMMOMMIMMEMEMEMEMEMME MUMMEMEMEMMEMSRMIIMMOSEMMOMMSOMMEMMEMIWN:NrOMMIMMEMEMUMIMMEMEMMOMMMMOMMIIMMO WOMMOMMUUMEMMIMMIMMEMMIMMIUMMERMSEMOMMO.," MMOMMOMMIMMERMEMEMMEMNRIBOOMMOOMEMOM ammemmummemommosommummmommmommummimmwmfti. UMMEMMESIMMMOOMMOSMAWAIMMIIMEMORUO IMUMEMEMUOMMEMOMMIMMOMMMOMMOOMSEMOMEMMMUSUI, MEMMIIMMIRMMOOMMOOMMORWAMIUMEEMOMMEMM mommulummmommummommemummmiummummsmommhnommemmismommummilmemmemmommommimm munimmummemmosmommommmossommisminnimminsmommommummmummammumummemmmmommume OMMEMMINUMMUMUMMIMMEMOMMIMMEMEMEMMUMMEMMEMMEMEMEMOAIMMINIMMMEMOMMERMOMMEMOMmommEMM MMEMMUMEMEMOMMOSIImmimmominommERMOOMSOMMEMMEnmiEUMMIZ!..MNIMMEMISMOMEMMEOMMOMMIMMEMEM OMEMMOMMEMMUMMEMSEMMEMMESSEMMOMMINOMMEMEMMOMMUMMOMMEMMI.ZIMIMMOMOMOOMUMMOMMEMEMINE immommummomommmommmommmiummommmummummummommommummaiz .umemmummommessimma masimasmilimimmommessassimmosmsmossomsamammasiz-filsousinnuomma MEMOMMOMMUMEMOMMEMOMMOOMMOOMMUMMOMMUMMEMEMIIMMOMEEMEMMEMMInmii-.2.M.MEMMORM MOMMOMMSOMMEMEMMOOMMOMMOMMMEMMEMEMMOOMMOMOMMEMSMEMMOMMUREMMEMMOMMOOMOwsOMMIMMO MEMOMMEMOMEMMEMEMOMMEMMEMMUSEMOMMEMOMMEMEMESOMUMMEMMEMEMMOMMINIMMKOMOMMROMMEMM
0 20 40- 60 80 100 120 140 160
./1
(b) STREAMLINE 17ST TUBING
FIG. 5-1 ALLOWABLE COLUMN AND CRUSHING STRESSES ALUMINUM ALLOY TUBING - I7ST
5-19
Revised
Deo., 1942
ANC-5
Amendment No. 1.
Oct. 22, 1943.
1
5-26
TABLE 5-16
ALLOWABLE STRENGTH OF FLUSH RIVETED JOINTS
78° HEAD ANGLE
I MACHINE COUNTERSUNK
ALLOWABLE BEARING STRENGTH
- LB. PER RIVET
Sheet Allof 17ST Alclad 17ST '-24ST 2 T
Alclad
Illa.orRIvet-W,2 118 5/32 3/16 2( 2 1 8 2 - / 1 8 2 1 ' 2 1 8 2 C
16
Thickness of t 92 104 120 130 139 151 166 197 215 237 241 113 347 409 446 525 573 627 687 756 922 105 119 138 149 160 173 190 225 241 241 241 129 151 181 200 217 239 266 325 360 400 429 429 294 307 324 344 365 416 448 481 520 563 666 397 468 510 601 655 717 787 865 966 122 138 160 173 185 201 220 241 241 241 241 150 175 210 231 251 277 308 376 417 429 429 429 340 356 375 398 423 482 518 557 602 652 670 460 542 590 695 758 830 910 966 966 131 149 172 186 199 217 237. 241 241 241 241 162 189 226 249 271 299 332 405 429 429 366 384 405 430 456 520 558 600 650 495 585 635 750 815 895 91
Thinnest Sheet .020 .025 .032 .036 .040 .045 .051 .064 .072 .081 .091 .102 .128 132 429 m 2g
158 257 429 7
174 269
189 283
209 300
232 319
284 364
315 391
350 421
389 455
429 492
582
II DIMPLED
ALLOWABLE SHEAR STRENGTH
- LB. PER RIVET
Rivet Dia. - 3132 1/8 5/32 3/16,
41t4A17ST 276 480 735 1020
17ST 300 530 810 1130
24ST 350 620 950 1325
ALLOWABLE BEARING STRENGTH
- LB. PER RIVET
gheet Allo 1 ST Alolad 1 ST 2 SL Alclad 2 ST -.
asory ve 3 3 = 32 32 2 1, 32 • 32 1 = 32 _ •A
. ,
Thickness of .020 170 204 194 233 225 270 243 291
Thinnest Sheet
.025 185 238 388 212 272 444 246 315 514 265 340 555
.032 208 287 427 521 230 328 488 596 276 380 565 690 276 410 610 745
.036 221 312 449 559 253 358 514 640 293 414 595 740 316 447 642 799
.040 234 340 471 597 268 389 539 683 310 450 624 790 334 486 673 853
.045 250 374 498 646 287 429 570 739 332 480 660 855 350 535 712 923
.051 270 415 532 706 310 475 609 808 350 550 705 935 350 594 761 1009
.064 314 503 604 831 350 576 692 951 350 620 735 1100 350 620 864 1188
.072 560 650 910 620 743 1042 620 860 1205 620 928 1301
.081 699 1000 800 1146 925 1325 950 1325
.091 1103 1262 1325 1325
.102 1210 1325 1325 1325
.128 -
Revised
Dec., 1942 5-27
ALLOWABLE SHEAR STRENGTH
- LB. PER RIVET
3[32 1/8 5/-32
186 331 518
206 368 574
241 429 670
',rivet Dia.
tvanT
17ST 24ST
)/16.
745
828
966
ANC-5, Amendment No. 1. Oct. 22, 1943.
TABLE 6 - 5 MAGNESIUM ALLOY I
MECHANICAL PROPERTIES OF JULTERTATA SAND CASTINGS.
•0 HEAT-TREATED 0 CD PL (i) 1.!
CONDITION HEAT TREATED HELT-TREATED HEAT TREATED AND AGED
AND AGED
SPECIFICATION ARMY AN-W-5-56 AN-QQ41-56 AN-QQ-M-56 ANQQ-M-56 Comp. C
---- Comp. A Comp. A Comp. C
NAVY AN-QQ-M-56 AN-QQ-M-56 AN-QQ-M-56 0..010p-M-56 Comp. C
r,mp. A Comp. A Comp. C
FEDERAL
SAE
1 Ftu Ultimate Stress, psi 32 000 34 000 32 000 34 000
2 F+,-.' Yield Stress, psi 10 000 16 000 10 000 18 000
o .
PI 3 Ftp Proportional Limit, psi
4 IC Modulus of Elasticity, psi 6 500 000 Li. 6 500 000 U!.. 6 600 000 6 500 000
5 Elongation in 2 in., % 7 3 6 1
z 6 Fou Ultimate (block) Stress, psi 41 000 Lt . _ 41 000 49 000
... _ , 45 000 12
U3
g9
Cil Foy Yield Stress, psi 11 000 LE_ 16 000 2L 13 000 18 000
7
8 F.p Proportional Limit, psi
F.0 Column Yield Stress, psi
10 E. Modulus of Elasticity, psi 6 500 000 1-1— 6 500 000 1-1--I 6 500 000 6 500 000
il 11 F„ Ultimate Stress, psi 16 000 18 000 18 000 20 000
12 Fat Torsional Modulus of
Rupture, ' psi
13 Fsp Proportional Limit
(torsion), psi
14 G Modulus of Rigidity 2 400 000 N 2 400 000 2 400 000
(torsion), psi 2 400 000
m 15' 15' , Fbr t 44 000 ,u
2 Ultimate Stress, psi , 47 000
16 Rockwell Number
17 Brinell Number3 ill: 51 69 • Ix 63 78
ti 18 Fba Bending Endurance Limit, psi al_ x 12 500 411 000
competey reversed stress) 0500,000,000 cycles of 9 Q00
l
9 000
19 B'(20,000,000 Fse Torsional Endurance Limit, psi i
cycles of
completely reversed stress)
20 w Specific Weight, .066 lb/cu in. lb/6u ft.
A 21 Nominal 6.5% Al, 3.0% Zn, 0.2% Bia 9.0% AI, 2.0% 2n, 0.2%- Mn.
Chemical Composition
22 REMARKS
_ 1. See notes in Chapter 3.
2. The above values are minis.", values obtained from cast test bare. Reference should
be made to the specific requirements of the procuring or certificating memo,
with regard to the use of the above values in the design of castings.
3. 500-Kg load on 10-mm ball, or load (in Kg) equal to five times the square of the diameter of the ball (imam).
k
6-6
ANC-5, Amendment No. 1. Oct. 22, 1943. .
TABLE 6 - 6 MAGNESIUM ALLOY L
MECHANICAL PROPERTIES OF MTERTALR SAND CASTINGS.
CONDITION (I) (i) (:) (:)
AS CAST
ARMY AN-Q0-M-56
Comp. B
NAVY AN -QQ-N-56
Comp. B
FEDERAL SPECIFICATION
SAE .--
izt 1 Ftu . 12 000 . .
0 Ultimate Stress, psi
.
co
2 F......1 Yield Stress, psi N
4 000
3 F..- Proportional Limit, psi
..F
4 N Modulus of Elasticity, psi 6 500 000 II, .
6 Elongation in 2 in., % 3 . -
COMPRESS ION Fcu Ultimate (block) Stress, psi 24 000 LE - 1
_
o CO CO -.1• 0) ,
F Fay Yield Stress, psi 4000
F Fop Proportional Limit, psi . ,
Foo Column Yield Stress, psi .
E, Modulus of Elasticity, psi 6 600 000
11 Pau Ultimate Stress, psi N
10 000
12 Fst Torsional Modulus of
Rupture, psi
13 FSp Proportional Limit
(torsion), psi
14 G Modulus of Rigidity (torsion), psi
2 400 000
J
tb 15 Fbr Ultimate Stress, psi •.
1-4
I=
16 Rockwell Number
17 Brinell Aumberj 33
d4 18 Fbe Bending Endurance Limit, psi
(600,000,000 cycles of completely reversed stress)
19 r"'(20,000,000 Fse Torsional Endurance Limit, psi
cycles of
completely reversed stress) .
20 , Specific Weight, .064 lb/6u in. lb/cu ft.
w
21 Nominal
Chemical Composition 1.5% Ma
. 22 REMARKS
1. See notes in Chapter 3. .
2. The above values are minimum values obtained from cast test bars. Reference should
be made to the specific requirements of the procuring or certificating agency
with regard to the use of the above values in the design of castings.
3. 500-Kg load on 10 -lin ball, or load (in Kg) equal to five times the square of the
diameter of the ball (in mm).
6-7
4 4 c8
ANC-5, Amendment No. 1. Oct. 22, 1943.
TABLE 6-9 CASTING ( MISCELLANEOUS
MECHANICAL PROPERTIES OF UMTATA ALLOYS a
---1
• MANGANESE BRONZE HYDRAULIC BRONZE PHOSPHOR BRONZE
CONDITION
ALUMINUM BRONZE
' ARMY
SPECIFICATION
NAVY QQ-B-671 QQ-B-726 AN-B-691 QQ-B-691 .
FEDERAL QQ-B-871 W-B-726 40S-691 (Composition 2) -5-69/
(Composition 6)
SAE , -
Pes 1 Ftu Ultimate Stress, psi 65 000 65 000 30 000 ._, 35 000
N ,
2 F Yield Stress, psi 28 000 25 000ML
3 Ftp Proportional Limit, psi • 12 000 12 000
4 N Modulus of Elasticity, psi 14 000 000 14 000 000
5 Elongation in 2 in., % 20 20 20 DE, 10 EL
COMPRESSION Fou Ultimate (block) Stress, psi 50 000 50 000
1-,
0 CO CO ...1 CD
A
Foy Yield Stress, psi
F cp Proportional Limit, psi
Poo Column Yield Stress, psi , .
E0 Modulus of Elasticity, psi a '
-
. I1 Fou Ultimate Stress, • psi 40 000 40 000 . -
12 Piot Torsional Modulus of 60 000 60 000
Rupture, psi
13 Fsp Proportional Limit (torsion), psi
14 0 Modulus of Rigidity 4 500 000 4 500 000
(torsion), psi
al 15 Fbr Ultimate Stress, psi 80 000 80 000
16 Rockwell Number
17 Brinell Number
H E. .4 F.4 18 Fbo Bending Endurance Limit, psi 14 000 14 000
t (500,000,000 cycles of ..._
completely reversed stress)
19 Foe Torsional Endurance Limit, psi
_ (20,000,000 cycles of completely reversed stress)
20 w Specific Weight, lb/cu in. lb/cu ft.
21 Nominal
Chemical Composition
22 REMARKS • •
1. See notes in Chapter 3.
2. The above values are minimum values obtained from cast test bars. Reference should be made to the specific requirements of the procuring or certificating agency with regard to the use of the above values in the design of castings.
560217 0 - 43 - 4 . 6-10
U)
a:
12.5
O
N
a
4 10 CO
3
• 0
7.5
co
W
5
2
0
2.5
CD
4
0 0
0
4
20 40 60 80 100 120 140 160
IIIIIIIII1111111111111f
A.A.F. Speo. 11 332
Navy Speo. 44T36, Alloy 8.—
'111114i
Notes Crushing stresses are:
not oritioal for D/t ratios less than 40.
Fty. 17 000
&ler Curve
N
FIG 6- I ALLOWABLE COLUMN STRESSES FOR MAGNESIUM ALLOY ROUND TUBING
5
f
20
15
10
5
El
0
0 5 10 . I5
20
FIG 6-2 TORSIONAL MODULUS OF RUPTURE FOR MAGNESIUM ALLOY ROUND TUBING -
36 000
25
A.A.F. Speo. 11 332
. Navy Speo. 44T35, Alloy
30
35
40
Revised
Doc., 1942 6 — I 1
U.S.GOVERNMENT PRINTING OFFICE 1943
Ill 1111111111111. F
I.'
3 9352 07939974 7
;,/