曝光臺(tái) 注意防騙 網(wǎng)曝天貓店富美金盛家居專(zhuān)營(yíng)店坑蒙拐騙欺詐消費(fèi)者

1,2-dichloroethane
Hexachloroethane
Methyl ethyl ketone
Tetrachloroethylene
Trichlorethylene
Trichlorethylene
Vinyl chloride
An undamaged or physically damaged composite is not
expected to contain any residual solvents that were introduced
during the production of the raw material or in
the manufacturing process of the composite part. Benzene
is the most likely compound from the list to be detected
in a fire-damaged sample. Benzene is an expected
combustion product of the fuel and resin. The char and
soot may contain traces of benzene.
Semi-volatile organics:
o,m,or p-Cresol(s)
1,4-dichlorobenzene
2,4-dinitrotoluene
Hexachlorobenzen
Hexachlorobutadiene
Nitrobenzene
Pentachlorophenol
Pyridine
2,4,5-trichlorethylene
2,4,6-trichlorethylene
Chemical knowledge of a specific resin system is needed
to determine if any semi-volatiles are a possibility. If a
compound is found to be part of the resin formulation it is
not expected to be detected once the composite has been
shaped to its final form. An undamaged or physically damaged
mishap-composite is not expected to contain any
detectable amounts of resin. Detection is highly unlikely
when using the TCLP preparation method for organic constituents
in a fire or physically damaged composite.
Pesticide and Herbicides:
Not applicable to mishap-composites.
(b) Contaminated Media. Contamination can be
caused by many sources within the mishap environment.
Blood-borne pathogen exposure will make the composite
debris a medical waste. Radiation exposure will cause
the debris to become a radioactive waste. Exposure to
hazardous liquids will cause the composite debris to become
hazardous waste. Fire suppressant soaked composites
may be a disposal issue. Information must be
gathered at and about the mishap needed to determine
if site contamination is a potential disposal problem for
the mishap-composite.
(5) Landfill. Landfills do not operate under the same
permit. One permit may require the D-listed compounds
and another may require the F and D-listed compounds.
One may require only a TCLP sample preparation while
the other may require a total preparation method.
TO 00-105E-9
Recommended Analysis Sample Type Possible
Contamination Levels
Comments
TPH Composite debrisppb or ppm VOA and semi-volatile molecular
weight range.
PAH Composite debrisppb or ppt Soxhlet extraction more efficient
than sonication preparation.
Semi-volatile organics Composite debrisppb or ppt Soxhlet extraction more efficient
than sonication preparation.
Volatile organics Composite debrisppb or ppt Headspace or heated purge isa
efficient preparation method.
Metals Composite debrisppb, ppm
TCLP metals Leachate ppm
Expected contamination° of a fire damaged composite: PNA, hydrocarbons, resin monomers, oxidized resin and
fiber compounds, petroleum fuel, aviation gas, jet propulsion fuel, halogenated products from the fire suppressant.
° Recommendation doesn’t consider cross-contamination possibilities.
• WHAT ARE THE COMPOSITE MATERIAL LAYERS?
• HAS IT BEEN CONTAMINATED AT THE MISHAP SITE?
• WHAT STATE?
• WHAT LANDFILL WILL BE USED?
• ARE ANY OF THE LISTED CONSTITUENTS WITHIN THE MATERIAL LAYERS.
• IS IT A SOLID WASTE OR A HAZARDOUS WASTE??
Table 3.5-1 Recommended Analysis for Possible Major Contaminants of a Fire-Damaged Composite.
3-30
TO 00-105E-9
d. PHOTO GALERY OF COMPOSITES. The following
photos are examples of composite materials in normal,
unburnt, burnt and damaged configurations.
Photo 1. Micrscopic View - Fiber/Matrix
Photo 2. Unidirectional prepreg.
Photo 3. Plain Weave Fabric
Photo 4. Twill Weave Fabric
3-31
TO 00-105E-9
Photo 5. Assorted Fabric Types
Photo 6. Carbon Fiber “prepreg” Tape
Photo 7. Glass Fiber “prepreg” Tape
Photo 8. Roving carbon fiber “prepreg”
3-32
TO 00-105E-9
Photo 9. Preparing to build the part by stacking
layers.Carbon fiber “uni” tape cut from a spool.
Photo 10. Stacking of Layers
Photo 11. Flat Carbon Fiber Laminate
Photo 12. Slightly Curved Carbon Fiber Laminate
3-33
TO 00-105E-9
Photo 13. Honeycomb Layer
Photo 14. Sandwich Laminate Layer Sequence
Photo 15. Cured Sandwich Laminate
Photo 16. Filament Winding Process
CELL SIZE
CELL PITCH
NODE
W
L
3-34
TO 00-105E-9
Photo 17. Hybrid Composite Parts
Photo 18. Fragment
Photo 19. Fragment
　
中國(guó)航空網(wǎng) m.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：航空資料37(104)