WorksheetsCL ATA 51-57
Total questions: 111
Worksheet time: 56mins
Composite materials are used for (level 1)
Secondary structure.
Primary structure.
Primary and secondary structure.
The fuselage is divided into: (level 1)
the forward fuselage, the center fuselage and the rear fuselage.
the nose forward fuselage, the forward fuselage, the center fuselage, the rear fuselage, the rear/cone fuselage and the tail cone.
the nose forward fuselage, the forward fuselage, the center fuselage, the rear fuselage, and the cone/rear fuselage.
The function of the engine pylons installed under each wing is: (level 3)
support the engine, transmit the engine thrust to the aircraft and enable the routing and attachment of all the systems connected with the engine.
support the engine, transmit the engine thrust to the aircraft and supports the thrust reverser system.
give the engine an aerodynamic shape and supports the thrust reverser system and enable the routing and attachment of all the systems connected with the engine.
The primary structure of the horizontal stabilizer are: (level 1)
the attachment fittings.
the spar boxes (Center, Left Hand and Right Hand sides)
the leading edge and the trailing edge.
The cabin windows are: (level 1)
installed and removed from the inside and outside of the aircraft.
installed and removed from the outside of the aircraft.
installed and removed from the inside of the aircraft.
Each outer wing has: (level 1)
a main structure (outer wing box), a wing tip, a leading edge and leading edge devices, a trailing edge and trailing edge devices.
the wing spars (front and rear), the ribs (1-27), the top and bottom skin panels, the top and bottom stringers, the wing-root joint.
the front and the rear spars, top and bottom skin panels, the two main frames, internal spanwise lattice ribs, the left rib 1 and the right rib 1.
The structure repair manual is (level 1)
a non-customized document.
a non-approved document
a customized document.
An allowable damage (level 3)
has significant effect on the strength or fatigue life of the structure.
enables the damaged airplane may be returned into service without repair.
must require minimal rework such as cleanup or drilling of stop holes.
Corrosion is one typical defect of (level 1)
composite material
aluminum alloy
CFRP
Fuselage and wing are mainly made from (level 1)
aluminum alloy
steel
composite
Radome made from (level 1)
aluminum alloy
QFRP composite
CFRP composite
On typical fuselage structure of A320/321 airplane, the standard frames: (level 3)
have common Z-shaped section
are attached to the skin and stringers by sheet metal cleats.
all above
What is the first document to be used to assess the structure damage? (level 1)
IPC
AMM
SRM
The main load carrying member of a wing are: (level 2)
rear spar and front spar
Ribs
Both A and B
The fuselage stringer reinforce the skin panel in (level 1)
The circumferential direction
The longitudinal direction
Both A and B
Most of sheet metal used in the airplane structure is: (level 1)
Steel alloy
Aluminum alloy
Titanium alloy
What is the purpose of the damper nitrogen bottle and emergency operation cylinder? (level 3)
To damp the door opening and closing
To assist in opening and closing the door to do it
To damp the door opening/closing and to pressurize the cylinder in case of emergency opening
A wing give airfoil section by the: (level 1)
Spars
Ribs
Stringers
Aircraft structure is made of : (level 1)
Metallic materials only.
Composite materials only.
Both metallic and composite materials.
Composite material CFRP means: (level 1)
Carbon Fiber Reinforced Plastic.
Composite Fiber Reinforced Plastic.
Carbon Fiber Reinforced Product.
The Radom of A320 is made of: (level 3)
CFRP
AFRP
QFRP
Choose the correct statement: (level 3)
The A321 A/C has 8 type C passenger doors
The A321 A/C has 4 type C passenger doors and 4 type III emergency exit doors.
The A321 A/C has 4 type C passenger doors and 4 type C emergency exit doors.
For A320/A321 A/C: (level 3)
Bulk cargo door is located between fr10 and fr12.
Bulk cargo door is located between fr30 and fr32.
Bulk cargo door is located between fr60 and fr62.
Fuselage of A320 A/C is divided into? (level 3)
Three main parts: forward, center and rear fuselage.
Four main parts: nose, forward, center and rear fuselage.
Five main parts: nose forward, forward, center, rear and rear/cone fuselage.
Pylon box of A320 A/C is made of: (level 3)
Steel and Aluminum alloys.
Steel and Titanium alloys.
Aluminum and Titanium alloys.
A320 A/C THS Tip is made of: (level 3)
Aluminum alloy.
Titanium alloy.
Steel alloy.
On A320 A/C, Wing spar is made of: (level 3)
Titanium alloy.
Steel alloy.
Aluminum alloy.
Delamination in composite material means: (level 3)
Separation between skin plies.
Separation between skin and core.
Separation between cores.
In each SRM chapter, allowable damage page block is: (level 3)
Page 000-099.
Page 100-199.
Page 200-999.
When structure damage of A320 A/C is not mention in SRM, repaired solution must be approved from: (level 3)
Airbus.
Vietnam Airlines.
VAECO.
The forward fuselage extends from: (level 2)
FR1 to FR24
FR24 to FR35.8
FR35.8 to FR47
The pressurized zone of the A/C are: (level 3)
The radome, wing center box, nose and main gear bays, belly fairing and cone/rear fuselage
The cockpit, cabin, avionics compartment and the FWD and AFT cargo compartments.
The cockpit, cabin, avionics compartment, wing center box, nose and cone/rear fuselage.
The Structural Repair Manual describes two types of repair which are designed for the repair of structural damage. They are defined as follows: (level 3)
Major repairs, minor repair
Permanent Repairs, Temporary Repairs.
None of above
Allowable damage is: (level 3)
which have effected on the structural strength or on other aspects of airworthiness (e.g.: fire resistance, electrical conductivity, system, aerodynamics, aircraft performance, etc.).
which does not have effect on the structural strength or on other aspects of airworthiness (e.g.: fire resistance, electrical conductivity, system, aerodynamics, aircraft performance, etc.).
Which have no repair instruction given in SRM.
Permanent Repairs are: (level 2)
Major repairs or major structural replacements requiring special repair drawings and information from the aircraft manufacturers.
Repairs are designed for quick fabrication/installation, and restore ultimate strength. Good appearance, aerodynamic smoothness and maximum fatigue resistance are not required.
Repairs fully restore the structural integrity of the aircraft.
The dents in metallic parts on external aerodynamic surfaces can cause: (level 2)
A reduction in flight performance; a good effect on flight characteristics, a bad effect on stall speed; Buffeting.
A reduction in flight performance; a bad effect on flight characteristics, a bad effect on stall speed; Buffeting.
None above.
Primary structure is: (level 2)
Structure parts significantly transmit ground, flight and pressure load.
Structure parts that do not significantly transmit ground, flight and pressure load.
An element that contributes significantly to the carrying of flight, ground or pressure load, and whose integrity is essential in maintaining the overall structural integrity of the airplane
A method of nondestructive inspection used to check a piece of composite for crack damage is: (level 2)
Ultrasonic inspection
Eddy-current inspection
Tap test.
The fuselage stringers reinforce the skin panels in (level 3)
The circumferential direction
The longitudinal direction.
Both a and b.
Fuselage frames are numbered to: (level 3)
Give an easy reference for location of component etc.
Ensure that frames are manufactured to the correct specification.
Aid the manufacturer on assembly in the jig.
The chord of a wing is measured from (level 2)
Wingtip to wingtip
Wing root to the wingtip.
Leading edge to trailing edge.
A wing is given airfoil section by the: (level 2)
Spars
Ribs.
Stringers
Passenger windows in aircraft have: (level 3)
Two pane
One pane
Three pane.
The airplane is divided into (level 3)
9 major zones
7 major zones
8 major zones.
What is a Category A repair? (level 3)
A permanent repair and no other actions are necessary.
A permanent repair for which supplemental inspections are necessary at the specified threshold and repeat intervals.
A time-limited repair which must be replaced or reworked within a specified time limit.
What is a Category B repair? (level 3)
A permanent repair and no other actions are necessary.
A permanent repair for which supplemental inspections are necessary at the specified threshold and repeat intervals.
A time-limited repair which must be replaced or reworked within a specified time limit.
What is a Category C repair? (level 3)
A permanent repair and no other actions are necessary.
A permanent repair for which supplemental inspections are necessary at the specified threshold and repeat intervals.
A time-limited repair which must be replaced or reworked within a specified time limit.
Where you can get the WEIGHT VARIANT information (level 3)
“Weight Variant Information” in the INTRODUCTION of the SRM.
“Weight Variant Information” in the chapter of the SRM.
“Weight Variant Information” in the table content of related chapter
A wing give aerofoil section by the: (level 3)
Spars
Ribs
Stringers
What indicates the green light in the cargo door access? (level 3)
The cargo door is closed and locked
The cargo door is not closed
The cargo door is open and locked
What happen when the passenger door is opened from the outside and the slide system is armed? (level 3)
The locking mechanism is blocked
The escape slide will deploy
The slide system is disarmed
What happens when the arming lever of the PAX door is set to the ARMED position? (level 3)
The girt bar stay attached to the cabin floor.
The girt bar slide towards the telescopic fork.
The telescopic fork slide towards the girt bar fitting
Door seal features: (level 2)
One piece
Pressurized by cabin air
All above
What is made of the main pylon structure? (level 2)
The stainless steel and the titanium alloy
The aluminium alloy and the titanium alloy
The aluminium alloy and Aramid Fiber Reinforced Composite
Airplane structure is from (level 1)
Metal material
Composite material
Metal and composite material
Stabilizer made mainly from (level 2)
Aluminum alloy
Steel
CFRP composite
Which force do spigot / spigot bearing transmit from pylon to wing structure (level 2)
Engine thrust
Engine weight
Lateral force
Deboning and delamination is defect of (level 2)
Composite material
Steel
Titanium
On A320/321 aircraft, Composite materials represent (level 2)
About 15% of the A/C structural weight
About 30% of the A/C structural weight
About 50% of the A/C structural weight
A321 Vertical stabilizer leading edge protected by: (level 1)
Stainless steel
Titanium
Glass Fiber Reinforced Plastic (GFRP)
Elevator structure is mainly from (level 3)
Aluminum/CFRP
Composite CFRP
Composite GFRP/ CFRP
Which statement below is correct? (level 3)
Most of the frames of the belly fairing become extension to the fuselage frames and are made of the aluminum alloy
Most of the belly fairing’s panels are made of the aluminum alloy
Most of the frames of the belly fairing are made of the steel alloy.
A dent or paint damage found on radome, inspection c/out and it can be repaired temporarily by (level 3)
Specific tape
Hi-speed tape
Any tape
The A/C weight variant (WV): (level 2)
Is always the same as it is the 1st time delivered.
May change with times depending on the modifications /SBs… application
Depends on the MSN only.
Which ATA is to be taken into account to assess the damage found on the pylon? (level 1)
ATA 52
ATA 53
ATA 54
The allowable limits can be found in SRM at: (level 1)
Page block 101 of ATA 51
Page block 101 of the relevant ATA where the damage located
Page block 201 of ATA 51
Necessary information to carry out permissible repairs can be found in SRM at: (level 2)
Page block 101.
Page block 201 of the relevant ATA where the damage located
Page block 201 of ATA 51
What is not true about SRM (level 1)
SRM is updated
SRM is customized
SRM is approved by DGAC
Cockpit window visibility is determined IAW (level 2)
AMM
SRM
MEL
Inspection of a structure damage of SDR must give information (level 2)
Type of damage
Dimension and location of damage
Type of damage, dimension and location of damage
How many jacking points in A320F aircraft: (level 2)
2
3
4
The fuselage stringer reinforces the skin panel in (level 2)
The circumferential direction
The longitudinal direction
Both A and B
The door seal around the door is inflated through holes when (level 2)
Aircraft in flight only
The cabin is depressurized
The cabin pressure is available.
A321 Aircraft Fuel tank can arrange at: (level 1)
Wings
Horizontal stabilizers to control CG on some A/C
A and B
The main load carrying member of a wing are: (level 2)
rear spar and front spar
Ribs
Both A and B
Most of sheet metal used in the structure of a airplane is: (level 1)
Steel alloy
Aluminum alloy
Titanium alloy
Moisture drain valve in pressurized fuselage (level 2)
Open when the cabin is pressurized
Open when the cabin is de-pressurized
A or B
The reference (station 0) for all structural measurements in the X axis is located (level 2)
At the rib 1 of the aircraft.
100 in (254cm) forward of aircraft nose.
251.2 in. (638.2 cm) forward of the aircraft nose.
ALLOWABLE DAMAGE CAN BE FOUND AT (level 2)
PAGE BLOCK (PB 101)
PAGE BLOCK (PB 201)
A or B
How many cockpit windows are found on A321? (level 2)
02
04
06
The chord of a wing is measure from (level 2)
Wingtip to wingroot
Wingroot to wingtip
Leading edge to trailing edge.
A wing spar is subject mainly to: (level 2)
Bending load
Tension load
Shear load
SRI (STRUCTURAL REPAIR INSPECTIONS) TASK APPLY FOR: (level 2)
ALLOWABLE DAMAGE.
REPAIRABLE DAMAGE.
A OR B
WEIGHT VARIANT INFORMATION CAN FOUND AT: (level 2)
ATA 51
PB. 101 OF EACH CHAPTER
SRM INTRODUCTION PART
Composite materials are used for primary structure are: (level 2)
Carbon Fiber Reinforced Plastic (CFRP).
Aramid Fiber Reinforced Plastic (AFRP)
Fiber Reinforced Plastic (GFRP)
The opened frames are arranged at: (level 2)
Openings for windshield and side windows.
At the all PAX window area.
Both A & B.
Fr 35 to Fr 35.8 belong to: (level 2)
The A321 section 14A
The A320 section 14A
The A321 section 16A
The CLEAT is install at: (level 1)
Fuselage structure
Wing structure
Tail structure
The tail cone unit (that is located aft of Fr 77 and houses the APU) is connected to section 19 by: (level 2)
Four lugs and one spigot
Fastener as all structure sections
None of the above
The primary structure of pylon: (level 1)
The AFT fairing
The Lower fairing
None of the above
On A321 AC, which slat have de-ice function? (level 2)
Slats 3 to 5
Slats 2 to 5
All slats
The interconnecting strut is used on: (level 2)
Slat system
Flap system
Both Slat & Flap system.
Flap tab on A321 is installed on: (level 2)
Inboard Flap
Outboard Flap
Both inboard & outboard Flap
Aircraft structure is made of:
Metallic materials only.
Composite materials only.
Both metallic and composite materials.
The forward upper structure of Nose forward fuselage has: (level 1)
Titanium skins.
Aluminum Alloy skins.
Composite skins.
Leading edge of vertical stabilizer on A320 A/C is made of: (level 1)
CFRP.
AFRP.
GFRP.
The fixed side windows on A320 A/C have: (level 1)
1 layer.
2 layers.
3 layers.
The cabin windows of A320 A/C: (level 1)
Can remove/install from outside A/C.
Can remove/install from inside A/C.
Can remove/install from either inside or outside A/C.
In each SRM chapter, repair page block is: (level 1)
Page 000-099.
Page 100-199.
Page 200-999.
Where can you find the corrective action for each type of cabin window defect: (level 1)
In SRM.
In AMM.
Both of the above.
Vertical Stabilizer Tip is made of: (level 1)
GFRP.
Titanium alloy.
Aluminum alloy.
For 21 access panels in the bottom skin panel of the outer wing box, what is correct? (level 1)
They are non load-carrying panels
There are 7 non load-carrying clamped panels between rib 1 and rib 13, 14 load-carrying bolted panels between rib 14 and rib 27
There are 7 load-carrying bolted panels between rib 1 and rib 13, 14 non load-carrying clamped panels between rib 14 and rib 27
The crack of structure component causes by: (level 3)
Mechanical action or Inherent metallurgical characteristics.
Mechanical action or Thermal action or cycling.
Mechanical action or Inherent metallurgical characteristics or Thermal action or cycling.
The disbond of stucture component causes by: (level 3)
Mechanical action or Inherent metallurgical characteristics or Thermal action or cycling.
Chemical or electrochemical reaction or Inherent metallurgical characteristics or Thermal action or cycling.
Mechanical action or Chemical or electrochemical reaction or Thermal action or cycling.
Fixed door attached to Nose landing gear leg is made from: (level 3)
Aluminum alloy.
Titanium alloy.
CFRP (Carbon Fiber Reinforced Plastic).
Hinged fairing door of main landing gear (a small door hinged to the wing structure in the neighborhood of the upper end of the main leg) is made from: (level 3)
Aluminum alloy.
Titanium alloy.
CFRP (Carbon Fiber Reinforced Plastic).
The Forward Fuselage part of A320: (level 3)
Includes section 13/14/14A. Between frame 24 and frame 35.8.
Includes section 13/14. Between frame 24 and frame 35.
Includes section 13/14. Between frame 24 and frame 35.8.
Includes section 13/14/14A. Between frame 24 and frame 35.
Stabilizer of A320 composed of: (level 3)
Trimmable Horizontal Stabilizer (THS), the vertical stabilizer.
Trimmable Horizontal Stabilizer (THS), the vertical stabilizer, elevators.
Trimmable Horizontal Stabilizer (THS), the vertical stabilizer, elevators, rudder.
Fill form – corrosion is: (level 3)
Depth of corrosion is smaller than 5% thickness of sheet.
The corrosion occur in CLADING only.
Depth of corrosion is smaller than 10% thicknees of sheet.
Standard practices, general procedures, typical repairs and rework procedures within allowable damage applicable to more than one chapter are included in: (level 3)
From chapter 52-57
Related chapter.
Chapter 51.
Where can you find the instruction to get information about Modification/Service Bulletin List. (level 3)
In Identification Scheme (Page Block 1 to 99)
Allowable Damage (Page Block 101)
Repairs (Page Block 201 to 999)
