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MATERIAL CODE AND
METALLURGICAL
CONDITION BASIC TREATMENT * T.S. MPa *Y.S.
MPa *El
%
Min Max
5086 H.111 Annealed 240 290 100 18
5086 H.22 Quarter hard 280 330 190
2017 T.4 Quenched, rolled, aged 390 250 14
2024 T.4 Quenched, rolled, aged 430 270 14
2024 T.3 Quenched,
work-hardened, aged 440 290 14
* T.S. MPa : Tensile strength in megapascal
* Y.S. MPa : Yield strength in megapascal
* El % : Elongation
NOTE : Material code correspondences - see Paragraph 3.
3. MATERIAL CROSS-REFERENCE TABLES
A. Steels
FRANCE GERMANY
DIN USA
SAE-AISI
ASTM U.K.
B.S SPAIN
UNE
A - 50 St.50 A 306 4360 A 490
XC18S / 1017 En.2 D/3 F 1511
15CDV6 1.7734 / / FE.PL.525
Werkstoff AECMA
18M5
(TU52b) St 52.4 API.5A / /
25CD4S 25CrMo4 4125 En.20 A F 222
3ONCD16 30NiCrMo16 / En.30 B F 1260
35NC6f 36NiCr6 3135 En.110 /
B. Aluminum alloys
FRANCE GERMANY
DIN USA
SAE-AISI
ASTM U.K.
B.S SPAIN
UNE
AG4MC / 5086 1470 / NS8 /
AG5 3.3555 5056 N6 L.3320
AU4G 3.1325 2017 L 102 L.3120
AU4G1 3.1354 2024 3L 65 L.3140
ABAA
Validity : S / N 1 - 9999 51 30-01Page 205
(CA) SEP 04
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ABM
Validity : S / N 1 - 9999 51-30 01Page 206
(CA) SEP 04
COMPOSITE MATERIALS
MAINTENANCE PRACTICES
1. GENERAL
This chapter regroups the different defects which can be found on composite material parts when used. It defines a principle of repair for each of these defects.
2. LOCATION OF COMPOSITE AREAS - see Figure 201
Item DESCRIPTION AIRCRAFT TYPE VALIDITY
S / N MATERIALS
TB9
TB10 TB200 TB20 TB21
1 WING TIP X X 1 - 822 ABS HEAT FORMED PLASTIC
X X X 823 IMPAX 7000
ALLAX SC
X 1 - 947 EPDXY + HONEYCOMB
LAMINATE
X X 948 IMPAX 7000
ALLAX SC
2 UPPER DUCT SIDE PART X X X X 1 LAMINATE POLYESTER
3 EMPENNAGE TIP X X 1 LAMINATE POLYESTER
4 TAIL CONE X 1 - 274 ABS HEAT FORMED PLASTIC
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本文链接地址：TB20 MAINTENANCE MANUAL 51 标准施工/结构 TB20飞机维护手册(4)
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