問題一覧
1
Excessive tension in aircraft fabric is
usually caused by excessive dope film on new covering.
2
Epoxy resins advantage that they
do not react with the solvents and dopes used for fabric coverings.
3
Fabric repair seams on a fabric covered aeroplane should be
covered with tape.
4
Cyanate esters
the material’s has dielectric properties for manufacturing high speed radomes.
5
Non-heat treatable aluminum alloys can be hardened by
strain hardening.
6
is the only inspection method for identifying excess tension in aircraft fabric covering .
Observation
7
The name given to the longitudinal direction of the fiber in woven fabric is
warp
8
Carbon fibre composites are known of these general characteristics :
High tensile strength and High compressive strength
9
a thermosetting resin
once cured , it cannot be become liquid again by heating .
10
A fibre made
of glass.
11
Curved wooden parts are made by
soaking or steaming wood strips then clamping in a jig to set the bend.
12
The usual method of repairing elongated bolts in a wooden structure is done by
fitting steel bushes.
13
is high resistance to corrosive materials. It is normally produced and used only as a surface matt to reduce cost
C’ Glass
14
Polyester fabric, used on a fabric covered airplane may be attached to the structure by
strings or by use of fabric adhesives.
15
Specific repair instruction and limitations of damage of composite are provided in
Structural Repair Manual.
16
In aircraft engineering terms, a composite usually consists of
a plastic resin matrix and reinforcing fibres of various materials.
17
Phenolics are fairly brittle system but they have a
good fire/smoke toxicity performance.
18
Strength
is the name of the ability to support load without breaking.
19
In (5052-H24) the letter H indicates
Strain hardening .
20
is a standard soda glass in common use for windows , etc.
‘A’ Glass
21
When selecting wood suitable for aircraft structural use, the growth
rate should be more than 6 rings per inch (25 mm).
22
Adhesive joints are liable to experience main types of stress:
●Tensile ●Shear ●Cleavage and ●Peel .
23
do not resist flame well and burn through more quickly than other fibres.
Aramid fibres
24
is an improved electrical grade of glass for modern radomes
D’ Glass
25
Common method of non-destructive of composite material are:
●Tap test ●Ultrasonic inspection ●Radiography/ X ray ●Vibration method and ●Thermal imaging
26
The composite part must be as strong and durable as
the original.
27
Stiffness
is the ability of a material to support a load without bending too much.
28
A disadvantages of Thermoplastic
lack rigidity not commonly used for aeronautical composite resins.
29
Iron oxide is sometimes added to aircraft dope to improve its
durability to adhesion
30
A visible wrinkle found across the face of piece of wood , in a wooden structural member , is most likely
a compression shake caused by compression load.
31
Most aircraft control system pulleys are made from
Tufnol
32
wood shrinkage occurs greatest in the
tangential direction to the growth ring.
33
The composite structural defect of separation of composite panel plies is called
delamination.
34
The best type of wood to be used in the construction of aircraft is
Sitka Spruce
35
a resin characteristics
Have ambient temperature storage
36
On a wooden aircraft structure if there is no evidence of fiber adhesion in the glue in a failed glued joint,
this may indicate glue deterioration .
37
are two or three-part systems have good environmental resistance and heat resistance up to150˚C.
Polyesters
38
Retarder is used to slow the drying time of dope finishes to prevent
blush
39
Impact resistance
is the ability of a material to withstand impact without shattering.
40
The name of time between heating and quenching
is cooling time (typically seven seconds)
41
Plastics are made from materials obtained from
animal or vegetable products and coal or petroleum by-products.
42
proposed repair scheme should meet all the original design requirements
for the structure.
43
Lap seam is the only seam type in a fabric covering requires that the selvedge be left on ,or the fabric edge cut with
pinking shears.
44
are made from pure carbon and are black in colour.
Carbon fibres
45
is a simple structure built-up from layers of cloth impregnated with resin.
A laminate
46
Ceramic fibres are used in heat resistant blankets and to weave fireproof cloth for engine and pylon protection.
high temperature application is required ,e.g. a firewall.
47
Epoxy resins
are the most widely used resin types for aerospace adhesive and composite applications.
48
the fibres in composite can be wound tightly to increase
strength
49
Ring shake defect of wood is indicated by a parting of the
annular rings.
50
Fish – eyes are small areas which have not dried uniformly due to
surface contamination with oil, wax or silicone products.
51
Lacing cord or stringing chord used on aircraft fabric covering must have a minimum breaking strength of
60 Ib
52
The standard wood type for aircraft wood structures is
Spruce