WorksheetsM7A - Sub18,19,20
Total questions: 60
Worksheet time: 30mins
Torque loading is carried out to provide.
as tight a joint as possible.
sufficient clamping without over-stressing.
flexibility.
A Stiff nuts with fiber or nylon inserts
cannot be torque loaded.
cannot be used in areas in excess of 250ºC.
is pre lubricated and does not need lubricating.
Removal of corrosion from aluminium clad alloy is best done.
mechanically by buffing.
chemically by trichloroethylene.
chemically by sulphuric acid solution.
How is damage classified on an aircraft skin?
Negligible, repairable, replacement.
Negligible, allowable, replacement.
Negligible, allowable, repairable.
A jig is device that allows:
the manufacture, repair components to a high dimensional accuracy.
as a reference when checking the C of G position.
to support the structure during repairs.
The majority of nuts, bolts and set-screws, on an aircraft, are subject to a standard torque value. This depends on:
their material, finish, lubrication, thread type and size
their material, shape, lubrication
their material, shape, size
What is the initial step to be taken before starting an inspection on an aircraft?
Reviewing the aircraft logbooks
Cleaning the structure
Checking for oil or fluid leakage.
Which publication should be reviewed to provide background information and maintenance history of the aircraft?
Manufacturer's service bulletins
Aircraft logbooks
EASA regulations
The purpose of using a checklist during an inspection is:
To ensure no items are forgotten or overlooked
To record findings after the inspection
To provide a history of significant events
The function of the aircraft logbook is:
To provide instructions for the inspection
To record all data concerning the aircraft
To list all the tools required for inspection
What should be done after completing the inspections, regarding the aircraft logbook?
Close it and store it in a secure location
Review it for any missing information
Make appropriate entries certifying the aircraft's airworthiness
What should be ensured before starting aircraft inspection?
All systems are powered on
Fuselage and hull are checked for deterioration
All plates, access doors, fairings, and cowling are removed
What is the primary purpose of inspecting the engine and nacelle during an aircraft inspection?
To check for proper fuel level
To verify the condition of the exhaust stacks
To look for visual evidence of oil, fuel, or hydraulic leaks
What should be checked during the inspection of the landing gear?
Hydraulic lines for electrical issues
Brakes for proper adjustment
Communication and navigation equipment
What devices are recommended to aid in performing a visual inspection?
A checklist and magnifying glass
A flashlight and gauge
All of the above
Which external damage is commonly caused during ground servicing?
Corrosion
Dents or puncturing by ground equipment
Wear on landing gear tires
How are external leaks of oil and fuel systems typically rectified?
By adjusting the pressure levels
By replacing faulty components or seals
By performing additional tests on the system
The potential danger associated with a leak from an oxygen system is:
Risk of engine failure
Possibility of an explosion
Increased cabin pressure
How can proper landing gear strut servicing be visually inspected?
By measuring the linear amount of outer strut cylinder exposed
By observing the condition of the tires
By verifying the condition of the landing gear doors
What is the purpose of inspecting probes such as pitot tubes and angle of attack indicators?
To check for signs of overheating
To ensure proper alignment
To detect obstructions and condition
When inspecting an aircraft after a lightning strike, you should observe.
entry damage.
all signs of burning.
entry and exit damage.
To ensure protection against HIRF affecting audio and navigation aids.
ensure that all audio and navigation equipment is adequately screened.
inspect and check all bonding leads to ensure their serviceability and replace if defective.
ensure that the correct number of static wicks are fitted.
Which of the following is a preventive process against HIRF?
Monitoring HIRF on the communication system.
Visual inspections.
Periodically checking aircraft bonding.
Skin wrinkling on the lower surface of a wing is caused by.
hogging.
tension.
sagging.
The most easily detected sign of an excessive load having been imposed during a landing is:
Deformed gear
Wrinkled wing skin
Cracked frame
A lightning strike on an aircraft would show.
the entry and exit point.
the entry point only.
the exit point only.
Refer M 7.19.3. HIRF interference occurs when
in use on mid frequencies.
in use on low frequencies.
in use on all frequencies
Refer M 7.19.2. What is the primary purpose of bonding of metallic parts of an aircraft?
To provide a return path for electrical two-wire system.
To prevent high potential differences between metallic parts from building up.
To prevent lightening strikes.
Refer M 7.19.3. Which of the following could be a primary cause of HIRF protection failure?
Corrosion on bonding leads.
Broken or missing static wicks.
Unserviceable radio filters.
Refer M 7.19.2. What is the reason for a primary bonding connection’s large cross-sectional area?
To carry the static discharge current to the conducting nose wheel.
To carry lightening discharge current should the need arise.
To maintain the airframe at the same potential throughout.
Refer M 7.19.5. The primary concern during a special inspection after a flight through severe turbulence is
Inspecting the cabin interior
Checking for fuel leaks
Inspecting the upper and lower wing surfaces
Refer M 7.19.5. Which of the following is NOT a recommended area to inspect for structural damage after severe turbulence?
Fuselage skin
Nacelle skin
Tail skid
Refer M 7.19.5. What can flight data recorders provide regarding loads felt during turbulence?
Detailed analysis of structural damage
Information on the severity of gust conditions
Precise locations of stress points
Refer M 7.19.6. What should be done if an aircraft has been subjected to flood damage?
Replace all interior components
Clean, dry submerged parts thoroughly and treated with a corrosion inhibitor.
Ignore minor water damage
Refer M 7.19.6. How is potential structural damage assessed in aluminum structures that pass a visual inspection after fire exposure?
Through use of an eddy current conductivity tester
By visual examination of welds
Using a Rockwell C hardness tester
Refer M 7.19.6. Why do seaplanes require careful inspection for corrosion?
Due to exposure to saltwater
High altitude operation
Frequent landing gear usage
Refer M 7.19.6. What distinguishes the inspection requirements for aerial application aircraft?
Elevated risk of hail damage
Corrosive nature of chemicals used and flight profile
High-altitude operation
Refer M 7.19.6. How does the flight profile of aerial application aircraft affect inspection frequency?
It requires less frequent inspections
It necessitates more frequent inspections due to typical flight profile operation
It results in similar inspection intervals to other aircraft
Refer M 7.19.5. What is recommended for inspecting aircraft structures damaged by fire?
Replacement of visibly damaged components
Immediate return to service if no visible damage is present
Conducting a visual inspection only
Refer M 7.19.2. What is the primary purpose of special inspection procedures for abnormal events?
To expedite maintenance procedures
To determine the extent of damage to the aircraft structure
To identify routine maintenance tasks
Refer M 7.20.3. When storing parts you should use
monitor the temperature.
silica gel.
place in a sealed container.
Refer M 7.20.2. Maintenance Schedules are issued
in a folder with the operators name on the cover.
with an approval certificate by the CAA.
by the operator with CAA approval.
Refer M 7.20.4. After a mandatory inspection has been carried out by a Licensed Engineer, what is issued
a Certificate of Maintenance Review.
Certificate of Release to Service.
a Flight Release Certificate.
Refer M 7.20.4. A Certificate of Release to Service must be issued after
a repair has been carried out in accordance with an approved repair scheme.
a re-fuel has been done.
engine runs.
Refer M 7.20.4. The purpose of the CRS is
to ensure that the log book entry is complete.
to turn a log book or job card entry into a legal document and to ensure that the signatory takes full responsibility for the work done.
to comply with article 15 of the ANO which states that an aircraft must not fly unless it is properly equipped for the intended flight.
Refer M 7.20.4. What work has to be recorded and signed for?
Only work which entails a duplicate inspection.
Only work involving replacements.
All work carried out.
Refer M 7.20.3. Rubber components should be stored
in a cool dark area.
in warm and humid conditions.
in a well lit room.
Refer M 7.20.3. Storage of components to prevent corrosion is helped
by using silica gel.
by wrapping in grease proof paper.
by placing them in a plastic box.
Refer M 7.20.3. Dye penetrant kits should be stored
out of sunlight in a dry place.
in direct sunlight to keep it dry.
in a dark damp cupboard.
Refer M 7.20.5. What dictates the depth and frequency of maintenance work on an aircraft?
Manufacturer's warranty
Aircraft Maintenance Manual (AMM)
Pre-flight checklist
Refer M 7.20.5. What department ensures work is performed satisfactorily when maintenance is done at locations other than approved installations?
Quality Assurance
Maintenance Operations
Flight Operations
Refer M 7.20.5. What type of maintenance action is required for structural cracks and deformations out of tolerances in pressurized areas?
Scheduled maintenance
Deferred maintenance
Unscheduled maintenance
Refer M 7.20.6. What action must be taken when a life-limited item is removed from service to prevent its reinstallation?
It should be mixed with serviceable units.
Immediate removal/segregation from serviceable component storage areas.
It should be reinstalled after repair.
Refer M 7.20.6. What defines life limited parts or components?
They have the highest tolerance for damage.
Inspection can detect imminent failure.
Their fatigue life is often shorter than other parts on the aircraft.
Refer M 7.20.6. Where is the life-limits document typically found?
Aircraft Maintenance Manual (AMM)
Flight Operations Manual
Instructions for Continued Airworthiness
Refer M 7.20.6 What information should be recorded to trace the time in service of life-limited parts?
Manufacturer's warranty
Serial number, installation date, part number, part name, total time on item and aircraft
Maintenance crew's names
Refer M 7.20.3 What may be enacted to prevent rework on a life-limited item?
Immediate reinstallation
Disposal and quarantine action
Mixing with serviceable units
Refer M 7.20.5 What are typical examples of unscheduled maintenance items?
Painting the aircraft exterior
Installing new seats in the cabin
Corrosion treatment, adjustment or replacement of components not performing to standards, repair of structural cracks and deformations out of tolerances in pressurized areas
Refer M 7.20.5 What documentation is required for all maintenance work performed?
Manufacturer's warranty
Technical logbook entry and certificate of release to service
Pilot's flight log
Refer M 7.20.3 What is the purpose of the Minimum Equipment List (MEL)?
To list all equipment installed on the aircraft
To provide guidelines for maintenance procedures
To establish the minimum number of systems required for flight operation and procedures for handling equipment failures
