AUTMOTIVE TECH, TECH MANUAL & MIND TAP
6th Edition
ISBN: 9781305383180
Author: ERJAVEC
Publisher: CENGAGE L
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Textbook Question
Chapter 29, Problem 3RQ
Most fuel tank filler caps contain a pressure valve and a.
a. vapor separator
b. vacuum relief valve
c. one-way check valve
d. surge plate
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cutting
Instructions:
Do not copy the drawing.
Draw In third-angle orthographic projection, and to scale 1:1,
the following views of the hinge:
A sectional front view on A-A
A top view
⚫ A right view (Show all hidden detail)
Show the cutting plane in the top view
. Label the sectioned view
Note:
All views must comply with the SABS 0111 Code of Practice for
Engineering Drawing.
Galaxy A05s
Assessment criteria:
⚫ Sectional front view
026
12
042
66
[30]
11
10
1. Plot the moment (M), axial (N), and shear (S) diagrams as functions of z.
a)
b)
F₁ = 1250 N
F₁ = 600 N
M₁ = 350 000 N mm
F2 = 500 N
200 N
a = 600 mm
b=1000 mm
a=750 mm
b = 1000 mm
d)
M₁ = 350 000 N mm
F₁ = 600 N
F₂ =200 N
a = 600 mm
b = 1000 mm
M₁ 175 000 Nmm
F = 900 N
a-250 mm
b-1000 mm
-250 mm.
Figure 1: Schematics problem 1.
Given the following cross-sections (with units in mm):
b)
t=2
b=25
h=25
t = 1.5
b=20
b=25
t=2
I
t = 1.5
a=10
b=15
h-25
b=15
t=3
T
h=25
Figure 3: Cross-sections for problem 2.
1. For each of them, calculate the position of the centroid of area with respect to the given coordinate system
and report them in the table below.
2. For each of them, calculate the second moments of inertia I...
and I, around their respective centroid
of area and report them in the table below. Note: use the parallel axes theorem as much as possible to
minimize the need to solve integrals.
Centroid position
x
y
box
Moment of inertia
lyy
by
a)
b)
c)
d)
e)
Chapter 29 Solutions
AUTMOTIVE TECH, TECH MANUAL & MIND TAP
Ch. 29 - Fuel pump is a statement of the volume of the fuel...Ch. 29 - Explain the purpose of the relief valve and...Ch. 29 - Most fuel tank filler caps contain a pressure...Ch. 29 - What type of fire extinguisher should you have...Ch. 29 - What is the first thing that should be...Ch. 29 - Why is a plastic or metal restrictor placed in...Ch. 29 - Low fuel pump pressure causes a mixture and...Ch. 29 - True or False? Fuel pressure typically is at its...Ch. 29 - If fuel pump pressure or volume is less than...Ch. 29 - Which of the following statements about a fuel...
Ch. 29 - Low fuel pressure can be caused by all of the...Ch. 29 - If a fuel system loses pressure immediately after...Ch. 29 - List at least five safety precautions that should...Ch. 29 - Describe the operation of the evaporative system...Ch. 29 - True or False? On todays vehicles, an electric...Ch. 29 - Technician A says that excessively high pressure...Ch. 29 - Technician A replaces a damaged steel fuel line...Ch. 29 - While discussing electric fuel pumps: Technician A...Ch. 29 - To relieve fuel pressure on an EFI car: Technician...Ch. 29 - While discussing quick-disconnect fuel line...Ch. 29 - While discussing fuel filters: Technician A says...Ch. 29 - While discussing the various fuel filters used in...Ch. 29 - While discussing fuel tank filler pipes and caps:...Ch. 29 - While discussing electric fuel pumps: Technician A...Ch. 29 - While discussing electric fuel pumps: Technician A...
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- Problem 1: Analyze the canard-wing combination shown in Fig. 1. The canard and wing are made of the same airfoil section and have AR AR, S = 0.25, and = 0.45% 1. Develop an expression for the moment coefficient about the center of gravity in terms of the shown parameters (, and zg) and the three-dimensional aerodynamic characteristics of the used wing/canard (CL C and CM). 2. What is the range of the cg location for this configuration to be statically stable? You may simplify the problem by neglecting the upwash (downwash) effects between the lifting surfaces and the drag contribution to the moment. You may also assume small angle approximation. Figure 1: Canard-Wing Configuration.arrow_forwardProblem 2: Consider the Boeing 747 jet transport, whose layout is shown in Fig. 2 and has the following characteristics: xoa 0.25, 8 5500/2, b 195.68ft, 27.31ft, AR, 3.57, V = 0.887 Determine the wing and tail contributions to the CM-a curve. You may want to assume CM, reasonable assumptions (e.g., -0.09, 0, -4°. i=0.0°, and i = -2.0°. Make any other 0.9).arrow_forwardZ Fy = 100 N Fx = 100 N F₂ = 500 N a = 500 mm b = 1000 mm Figure 2: Schematics for problem 3. 1. Draw the moment (M), axial (N), and shear (S) diagrams. Please note that this is a 3D problem and you will have moment (M) and shear (S) along two different axes. That means that you will have a total of 5 diagrams.arrow_forward
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