Commercial Aviation Safety_ 7th Edition Chapter 5 Questions (Answered)
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Commercial Aviation Safety: 7th Edition Chapter 5 Questions (Answered)
1.
What produces lift in an airfoil, airspeed, or groundspeed?
Lift is produced by the airspeed of the aircraft as the difference in pressure causes the air above
the wing to move faster than the air below the wing, producing lift and is not related to ground
speed. Ground speed is just the aircraft’s movement relative to the surface of the earth.
2.
List the key components of a turbofan engine
-
A powerful fan
-
A compressor
-
A combustor
-
Turbines
-
Exhaust ports
3.
What was the technical cause of the Comet Airplane Crashes
The main technical cause of these crashes were metal fatigue, primarily because of the design of
the aircraft’s distinct square shaped windows. The metal parts of the comet experienced a lot of
repeated cycles of stress and strain around the sharp corners of the square shaped windows, and
as they went through more pressurization and depressurization cycles, the metal developed
microscopic cracks. The cracks grew overtime with the aircraft’s repeated use, and this
ultimately led to catastrophic failure of the fuselage or an explosive decompression. After the
several crashes, the problem was identified and fixed to address these issues.
4.
Describe hindsight bias. How does it affect aviation safety
Hindsight bias is when people who were not involved in an incident think that they knew
something was going to happen despite there not being a way of knowing it in advance. In
Aviation this can tend to lead to a variety of problems. These problems include needless blaming
after accidents, thinking that whoever was involved should have seen it coming, learning less
from accidents because the person believes they are easy to predict, overconfidence, and near
misses may not get the attention they need because people may think that they are easy to avoid.
Hindsight bias should be limited as much as possible for continuously improving safety.
5.
List 3 changes that resulted from the Manchester Fire accident
The Manchester Fire in 1985 lead to multiple safety related changes, some of which included:
-
Improved fire safety at airports worldwide and the increased focus of fire prevention and
safety measures, which include better detection and response systems
-
Enhanced Aircraft design, which included the use of more fire resistant materials in cabin
interiors to make them less prone to catching fire
-
Cabin crew training was also enhanced to better handle most emergency situations, which
including dealing with fires on board mid flight
6.
What caused the two engines to run down in the incident to A340 G-VATL
The flight crew experienced fuel transfer problems due to a faulty fuel pump, which caused the
aircraft to become unstable with an excessive amount of fuel in the left wing tanks, which
eventually caused a loss of power on the right side engines as the left wing engines continued to
receive fuel while the right ones did not. The flight crew then performed the flameout restart
procedures to reignite the right wing engines, which they successfully did.
7.
What was the initiating event in the accident to the A380 operating flight QF32 and what
was the result?
The initiating event was a sudden, uncontained engine failure in the number 2 left engine. Which
disintegrated part of the engine and caused extensive damage. Fragments from the engine hit
various parts of the aircraft, which included the wing, fuel systems, and landing gear. The crew
declared an emergency, remained calm, planned their next moves carefully, and made a
successful return to Singapore. There were no fatalities.
8.
Describe 3 future technical challenges for the aviation industry.
Green Aviation: developing more sustainable and environmentally friendly technology to reduce
the impact of aviation on the atmosphere and the environment
Better autonomy: developing better systems to make piloting easier and safer and putting less
responsibility on humans where error can be more prone and slowly putting more responsibility
on systems and computers.
Better air traffic management: Finding ways to improve the air traffic system to minimize near
misses and incursions, while also boosting its efficiency
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Related Questions
Q1. During a test on a two stroke diesel engine on full load the following
observations were recorded:
Speed= 350 rpm
Net brake load= 590 N
Mean effective pressure= 2.8 bar
Fuel consumption=4.3 kg/h
Jacket cooling water= 500 kg/h
Temperature of jacket water at inlet and outlet= 25°C and 509C respectively
Air used per kg of fuel= 33kg
Temperature of air in test room= 25°C
Temperature of exhaust gases= 400°C
Cylinder diameter= 220 mm
Stroke length= 280 mm
Effective brake diameter= 1 m
Calorific value= 43900 KI/kg
Proportion of hydrogen in fuel= 15%
Mean specific heat of dry exhaust gases= 1.0 KI/kg K
Specific heat of steam= 2.09 KJ/kg K
Calculate: (1) indicated power (2) brake power (3) draw up heat balance sheet
on minute basis.
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Q1. During a test on a two stroke diesel engine on full load the following
observations were recorded:
Speed= 350 rpm
Net brake load= 590 N
Mean effective pressure= 2.8 bar
Fuel consumption=4.3 kg/h_
Jacket cooling water= 500 kg/h
Temperature of jacket water at inlet and outlet=25°C and Soyc respectively
Air used per kg of fuel= 33kg
Temperature of air in test room= 25°C
Temperature of exhaust gases= 400°c
Cylinder diameter= 220 mm
In solve to find mass of steam in exhaust gases m=(4.3/3600) *0.15 *9
Stroke length= 280 mm want clarification of the value 9 bleas
Effective brake diameter= 1 m
Calorific value= 43900 KJ/kg
Proportion of hydrogen in fuel= 15%
Mean specific heat of dry exhaust gases= 1.0 KI/kg K
Specific heat of steam= 2.09 KJ/kg K
Calculate: (1) indicated power (2) brake power (3) draw up heat balance sheel
on minute basis.
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Parameter
thrust
Thrust chamber pressure
Thrust chamber temperature
Working fluid
Universal gas constant
Ambient pressure:
At Sea level
value
5MN
7MPa
2800K
Air At Room Temperature (Ideal
Gas)
8.314 J. (Mol. K) -1
101325N/m²
At an altitude of 30km
1185.5 N/m²
MW= 29kg/Kw
The Following Performance and operation data was obtained from a
rocket with a a nozzle designed to produce maximum thrust at sea
level:
Determine;
A) Specific Impulse
B) Mass Flow Rate
C) Throat Diameter
D) Exit Diameter
E) Thrust Produced at An altitude of 30KM for the same fixed Nozzle
Geometry
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1 The following observations are recorded during a test on a
four-stroke petro engine, F.C = 25cc of fuel in 10 sec,
speed of the engine is 2600 rpm, B.P = 22 kW, Qair
0.00134 m, piston diameter
90 mm, density of the fuel = 0.85gm/cc , compression
ratio = 7.5, CV of fuel = 42000KJ/Kg, room temperature
= 24 °C
%3D
= 140mm, stroke length =
%3D
%3D
%3D
2 A six-cylinder 4-stroke cycle petrol engine is to be designed
to develop 250 kW of (b.p) at 2200 rpm the stroke / bore
ratio is to be 1.3:1. Assuming nm =80% and an indicated
mean effective pressure of 9.5 bar, determine the
required bore and stroke. If the compression ratio of the
engine is to be 7.5 to 1, determine consumption of petrol
in kg/h and in kg/bp.hr. Take the ratio of the indicated
thermal efficiency of the engine to that of the constant
volume air standard cycle as 0.65 and the calorific value
of the petrol as; 44770KJ/kg.
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4.
The efficiencies of aircraft can be very important indicators for meeting emission standards.
Often thermal efficiency needs to be estimated indirectly instead of conducting combustion
tests. A business jet is conducting testing at Mach 0.70 at sea level using the Jet A1 fuel
(LCV=43.15 MJ/kg) at a specific fuel consumption of 0.06 kg/(Nh). The propulsive jet velocity
is about 340 m/s. The local ambient air temperature is 288 K. Calculate the thermal efficiency
of the engine.
Hand written plzz
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Use Matlab
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3. At a load of 43,000 KW in a steam turbine generating set, 3600 RPM, the following data
appear in the log sheet.
Steam flow -190 Metric Tons/hour
Steam pressure - 8.93 MPaa
Steam temperature - 535C
Feed-water temperature - 230 C
Fuel Flow:
Bunker Oil -3.4 Metric Tons/hr
HHV=10,000 Kcal/hr
Local coal -18 Metric Tons/hr
HHV = 5350 Kcal/hr
Determine the overall boiler efficiency.
h at 8.93 MPa and 535°C -3475.7 KJ/kg
hf at 230°C-990.12 KJ/kg
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Please help me ?
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Question 3
(i)
What information is needed to make an accurate estimate of the annual
energy capture for a wind turbine? List at least two control mechanisms
available in modern wind turbines, which respond to variations of wind speed
and direction?
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true OR false
1. An inline 4 cylinder engine with a diameter of 4 in and stroke of 5 in has a piston displacement of 4 Liters.
2. A stream with depth of 6 ft and width of 2 m flowing at 8 ft/s will provide a mass flow rate of 96 slug per second.
3. A tractor pulling a disc plow with an average draft of 3480 lb and operating at a speed of 3.5 mph has a draft power of 32.48 horses.
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During testing of single cylinder two-stroke petrol engine following data were obtained. Brake torque = 640 Nm, cylinder diameter 21 cm, speed 350 rpm, stroke length = 28 cm, mean effective pressure = 5.6 bar, oil consumption = 8.16 kg/h, calorific value of the fuel = 42,705 kj/kg. Determine: Srake thermal efficiency
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Subject:SUBSONIC/APPLIED AERODYNAMICS
Question:Calculate the propeller power coefficient and static thrust of an engine-propeller combination at a standard altitude of 8km, with a shaft horsepower of 385 hp. The characteristics of the propeller are the following:
n = 45 rps
D = 1.9 m
CT/CP = 2.32
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1. What is the significance of subsonic low-speed wind tunnels?2. Distinguish between Calibrated and True Airspeed.
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Explain how the following jet engine works. Refer to each section of the engine andexplain the purpose of each section.
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9
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An airplane's turbojet engine produces 15,000 pounds of thrust at 150 knots, true airspeed. What
is the equivalent horsepower being produced?
O 5000 hp.
O 11,700 hp.
6923 hp.
No answer text provided.
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Q
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None
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Please use the following equations as appropriate.
L = ½ pv²SC₁ p = 21/v²SC, v²= 2L/PSC S=21/pv³C, Lift = Weight
Given the following:
Wingspan
Avg Chord
Altitude
Airspeed
40 ft.
5 % ft.
10,000 ft.
140 m/h
10°
a
Flaps
What is the weight of this aircraft in equilibrium flight?
Retracted
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!
Required information
Air, at po = 160 lbf/in2 and To = 300°F, flows isentropically through a
converging-diverging nozzle. At section 1, where A₁ = 288 in², the
velocity is V₁ = 1900 ft/s.
Determine the inlet pressure (p₁) and the mass flow rate (m.).
3945.6 lbf/ft2
25.970 slug/s.
The inlet pressure is
The mass flow rate is
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A four-stroke, four-cylinder diesel engine running at 2000 rpm develops 60 kW. Brake
thermal efficiency is 30% and calorific value of fuel (CV) is 42MJ / k_{g} . Engine has a bore of 120 mm and stroke of 100 mm. Take p_{a} = 1.15 kg / (m ^ 3) air-fuel ratio- 15:1 and eta_{m} = .8 Calculate (i) furl consumption kg/s) : (ii) air consumption (m^ 3/s );(ii) indicated thermal efficiency; (iv) volumetric efficiency: (v) brake mean effective pressure and (vi) mean piston speed.
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Please , solve all two questions completely by clear handwritten
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4.
The following data provide details for a piston-propeller engine combination for
a single-seater aircraft:
Table 4
Parameter
Value
Pistons
4
Bore
11.1 cm
Stroke
9.84 cm
Compression ratio
6.75
Mechanical efficiency
0.83
Propeller efficiency
0.85
Fuel-to-air ratio
0.08
Pintake
1 atm
Tintake
11.85°C
RPM
2800
Fuel properties:
Density
Energy released per kg
Oxidizer properties:
Y
R
Ср
0.51 kg/m³
46.1 MJ/kg
1.4
288 J/kg. K
1008 J/kg. K
(a). Graph the ideal and actual P-V diagram for the above engine.
Calculate:
(b). The power available.
(c). The mean effective pressure.
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- Q1. During a test on a two stroke diesel engine on full load the following observations were recorded: Speed= 350 rpm Net brake load= 590 N Mean effective pressure= 2.8 bar Fuel consumption=4.3 kg/h Jacket cooling water= 500 kg/h Temperature of jacket water at inlet and outlet= 25°C and 509C respectively Air used per kg of fuel= 33kg Temperature of air in test room= 25°C Temperature of exhaust gases= 400°C Cylinder diameter= 220 mm Stroke length= 280 mm Effective brake diameter= 1 m Calorific value= 43900 KI/kg Proportion of hydrogen in fuel= 15% Mean specific heat of dry exhaust gases= 1.0 KI/kg K Specific heat of steam= 2.09 KJ/kg K Calculate: (1) indicated power (2) brake power (3) draw up heat balance sheet on minute basis.arrow_forwardQ1. During a test on a two stroke diesel engine on full load the following observations were recorded: Speed= 350 rpm Net brake load= 590 N Mean effective pressure= 2.8 bar Fuel consumption=4.3 kg/h_ Jacket cooling water= 500 kg/h Temperature of jacket water at inlet and outlet=25°C and Soyc respectively Air used per kg of fuel= 33kg Temperature of air in test room= 25°C Temperature of exhaust gases= 400°c Cylinder diameter= 220 mm In solve to find mass of steam in exhaust gases m=(4.3/3600) *0.15 *9 Stroke length= 280 mm want clarification of the value 9 bleas Effective brake diameter= 1 m Calorific value= 43900 KJ/kg Proportion of hydrogen in fuel= 15% Mean specific heat of dry exhaust gases= 1.0 KI/kg K Specific heat of steam= 2.09 KJ/kg K Calculate: (1) indicated power (2) brake power (3) draw up heat balance sheel on minute basis.arrow_forwardParameter thrust Thrust chamber pressure Thrust chamber temperature Working fluid Universal gas constant Ambient pressure: At Sea level value 5MN 7MPa 2800K Air At Room Temperature (Ideal Gas) 8.314 J. (Mol. K) -1 101325N/m² At an altitude of 30km 1185.5 N/m² MW= 29kg/Kw The Following Performance and operation data was obtained from a rocket with a a nozzle designed to produce maximum thrust at sea level: Determine; A) Specific Impulse B) Mass Flow Rate C) Throat Diameter D) Exit Diameter E) Thrust Produced at An altitude of 30KM for the same fixed Nozzle Geometryarrow_forward
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