51 52 53

the Structure Repair Manual is a customized document exclusive to specific airlines. true. False.

The introduction chapter of the SRM provides airplane information such as Weight Variant and Airplane Allocation List. True. false.

The weight variant given in the Airplane allocation list always represents the current status of the aircraft. true. False.

for permanent repairs with inspection program, inspections are not quoted along with the repair. true. False.

each subject within the SRM uses a four-element numbering system. true. False.

what is the first document to use to assess damage on the aircraft structure?. aircraft Operation Manual. pilot's Handbook. Structure Repair Manual. maintenance Manual.

Where is general information or information applicable to more than one chapter included in the SRM?. chapter 50. Chapter 51. chapter 52. chapter 53.

In the "MOD/Definition Comparison" service, what does the "Aircraft status" criterion allow you to filter by?. the family of the aircraft. the type of aircraft. The status of the aircraft (e.g. delivered or to be delivered). the owner ICAO code of the aircraft.

What is the primary purpose of the Structure Repair Manual (SRM)?. to provide a list of all Airbus aircraft models. To provide guidelines on how to repair aircraft. to provide a history of Airbus. to provide a list of all aircraft manufacturers.

How is the SRM organized?. by aircraft model. by type of damage. By ATA specification. by date of publication.

What is the significance of 'Allowable Damage'?. it indicates damage that requires immediate repair. it indicates damage that can be ignored. It indicates damage that can be temporarily tolerated without immediate repair. it indicates damage that has been repaired previously.

What does a 'gouge' refer to?. a line of damage. A damage area resulting in a cross-sectional change. a mark caused by a sharp object. a series of scratches.

What causes 'corrosion'?. physical impact. Chemical or electro-chemical effect. exposure to high temperatures. regular wear and tear.

Which factors determine the type of surface protection for components?. material and Function. Material, Function, and Location. function and Location. only Material.

which of the following is NOT an exception to external areas having surface protection?. leading edges of slats. apu exhaust. Wing flaps. cabin Pressurization Control System Outflow Valve.

What is the definition of corrosion?. enhancement of metals. Destruction of metals by chemical effects. strengthening of metals. natural wear and tear of metals.

which of the following is NOT a step necessary for satisfactory control of corrosion?. regular maintenance. Applying heat. initial identification of corrosion. complete removal of corrosion when it occurs.

Which of the following is NOT a corrosive agent?. acids. alkalies. Pure water. salts.

Which atmosphere can cause special problems due to the presence of oxidized sulphur and nitrogen compounds?. marine Atmosphere. Industrial Atmosphere. tropical Atmosphere. desert Atmosphere.

How many main zones are the internal areas of an aircraft divided into, in terms of surface protection?. two. Three. four. five.

Which of the following is NOT a group of protective treatment mentioned?. pretreatment. paint coatings. special coatings. Heat treatments.

What is the primary purpose of pretreatment of materials?. to add color to the materials. to increase weight. To increase corrosion resistant properties and provide a good surface for paint adhesion. to make the material shiny.

What is the primary cause of corrosion in the general atmosphere?. lack of oxygen. excess of nitrogen. Moisture and oxygen. carbon dioxide.

Which of the following is NOT a step necessary for satisfactory control of corrosion?. regular maintenance. Applying heat. initial identification of corrosion. complete removal of corrosion when it occurs.

The fastener contact area of the tool must be rough and textured. true. False.

A clear indication of a loose fastener is when the head of a fastener is rolled upwards at its periphery. True. false.

If a fastener is suspected to be loose, it should be ignored until the next maintenance cycle. true. False.

The use of a washer under a nut/collar is only permitted when used in the original construction. True. false.

It's always recommended to use two washers instead of one under the nut/collar. true. False.

The hand hammering method is the most recommended method for installing rivets in the aircraft structure. True. False.

What is the primary concern when drilling titanium due to its nature?. its flexibility. Its hardness. its lightness. its transparency.

What should be checked regarding the drilling equipment?. the color of the drill. the weight of the drill. Wear of bearings and spindle concentricity. the brand of the drill.

Which of the following is NOT an indication of drilling problems?. different amounts of swarf emerging from flutes. drill turning blue. outer corners of drill breaking off. Drill making a humming sound.

Which of the following is NOT a method used for the installation of rivets?. continuous squeeze riveting process. pneumatic hammering. Electric drilling. hand hammering.

What is the recommended hole pitch value for a nonpressure tight joint in aluminum alloy assemblies?. 2 to 3D. 3 to 4D. 4 to 6D. 5 to 7D.

For aluminum rivets installed in aluminum alloy assemblies with a thickness of 1.2 mm or thicker, what is the recommended edge distance value in terms of 'D'?. minimum 1.5 x 'D'. Minimum 2.0 x 'D'. minimum 2.5 x 'D'. minimum 3.0 x 'D'.

What is the primary benefit of the cold expansion process?. it increases the weight of metal structures. It increases the fatigue life of metal structures. it increases the temperature resistance of metal structures. it increases the elasticity of metal structures.

By how much does the hole diameter increase as a result of the expansion process?. one to two percent. two to four percent. Three to five percent. five to seven percent.

Which of the following is NOT a step in the cold expansion of holes in aluminum alloy structure?. drilling a start hole. Painting the cold expanded hole. reaming the start hole. cold expanding the start hole.

If the maximum oversize of a hole following cold expansion is exceeded, what should be done?. ignore the discrepancy. fill the hole with a sealant. Contact AIRBUS. re-drill the hole.

Why is it recommended to use a lubricant when drilling aluminum alloys?. to make the drill shiny. To help remove swarf and reduce heat build-up. to make the hole bigger. to color the aluminum.

After rivets are installed, why is inspection necessary?. To ensure the joint is tight and rivets are correctly formed. to check the color of the rivets. to ensure the rivets are shiny. to measure the length of the rivets.

Which of the following can indicate a loose fastener?. a shiny spot around the fastener. a red mark on the fastener. A black or dark grey stain adjacent to the fastener head. the fastener making a sound.

What is the primary purpose of using a countersunk fastener?. to provide a decorative finish. To give a smooth surface. to strengthen the materia. to increase the weight of the material.

Which of the following is NOT a type of tool used to produce the countersunk recess?. a countersink bit with an integral pilot pin. a countersink bit with a replaceable pilot pin. A countersink tool with a builtin hammer. An adjustable countersink tool with a replaceable pilot pin.

What should be observed before countersinking?. the color of the material. The minimum part thickness. the brand of the tool. the temperature of the material.

What type of doors are the forward and aft passenger doors of the Airbus A320 Family?. swing-type doors. sliding doors. Plug-type doors that open upward, outward, and forward. hydraulic doors that open automatically.

How do the passenger doors of the Airbus A320 Family open?. open inward and upward. swing outward and downward. Open upward, outward, and forward parallel to fuselage. automatically open and close hydraulically.

What is the purpose of the slide ARMING/DISARMING lever on the passenger doors?. control cabin temperature. activate emergency lighting. disarm the escape slide. Connect the slide to the floor for automatic deployment.

How does the escape slide on the passenger doors deploy in an emergency?. automatically inflates when the door is opened from the outside. manually inflated by passengers. Automatically inflates when the slide-arming lever is disarmed. equires activation by cabin crew.

How many overwing emergency exits are typically found on the Airbus A321?. two exits. Four exits. six exits. none of the above.

How can the overwing emergency exits on the A318, A319, and A320 be opened for evacuation?. only from inside. only from outside. Both from inside or outside. they cannot be opened for evacuation.

How are the cargo compartment doors of the Airbus A320 Family operated?. electrically using the yellow system. Manually with a locking handle. hydraulically using the blue system. automatically via the cockpit controls.

What is the function of the bulk cargo door on the A320 and A321 aircraft?. provides access to the avionics compartment. Gives access to the bulk cargo compartment. opens into the passenger cabin. acts as an emergency exit.

How are the avionics compartment access doors on the lower fuselage operated?. Manually. electrically. automatically. using a hand pump.

What is the purpose of the Cockpit Door Locking System (CDLS) in the Airbus A320 Family?. control cabin temperature. Prevent unauthorized cockpit access. manage the escape slide. activate the emergency lighting.

How is the cockpit door typically locked when the aircraft is powered?. manually with a key. Automatically by CDLS. electronically with a keypad. physically by flight crew.

What does the cockpit door escape hatch feature, and how is it kept in position?. contains emergency supplies. has a locking handle. includes a keypad for access authorization. Secured with two pip-pins.

What components are part of the Cockpit Door Locking System (CDLS) in the Airbus A320 Family?. Cockpit door panel on the pedestal with a toggle switch. control cabin temperature. overhead control unit in cockpit with integrated maintenance annunciators. electrical release strikes.

What is the purpose of the buzzer located on the cockpit overhead panel?. control cabin temperature. prevent unauthorized cockpit access. Activate the emergency lighting. provide maintenance alerts.

How does the avionics compartment door locking mechanism operate on the Airbus A320 Family aircraft?. electrically. Manually. automatically. using a hand pump.

The escape slide inflates automatically when the slide-arming lever is in the _________ position and the door is opened from the inside. Armed. disarmed. closed. locked.

The A321 is equipped with four emergency exit doors located forward and aft of the _________. cockpit. avionics compartment. Wing. cargo compartment.

To activate the evacuation system through the overwing emergency exits on the A318, A319, and A320, authorized personnel must _________ the exits from the inside. Disarm. lock. open. activate.

The cargo compartment doors on the Airbus A320 Family give access to the forward and aft _________ compartments. Cargo. cockpit. avionics compartment. passenger.

In case of electrical failure, the cargo compartment door can be opened manually using a _________. be opened manually using a _________. hydraulic system electric pump. Hand pump. slide ARMING/DISARMING lever. keypad.

There are _________ avionics compartment access doors on the lower fuselage around the nose landing gear bay. two. three. Four. five.

The locking mechanism for the avionics compartment access doors is _________ on each door. different. Identical. electronic. manual.

The cockpit door on the Airbus A320 Family is designed to prevent _________. cabin temperature. Hijacking attempts. unauthorized access. mechanical failures.

The cockpit door escape hatch is secured with two _________ to keep it in position. toggle switches. Pip-pins. escape slides. keycards.

The A318 and A319 are equipped with two overwing emergency exits, and the A319 can optionally have _________ additional exits. one. Two. three. four.

The avionics compartment access doors on the lower fuselage open _________. Inward. outward. upward. downward.

To perform normal door opening from the outside, one must check that the arming lever is in the _________ position and that the cabin pressure indicator is not flashing. Disarmed. armed. locked. opened.

In case of emergency opening, the arming lever should be in the _________ position, and after pulling the door control handle rapidly fully up and releasing it, the door opens and locks automatically. Armed. locked. disarmed. opened.

How many main parts is the fuselage divided into?. three. four. Five. six.

What are the names of the main parts that make up the fuselage?. forward, center, rear, cone. nose, forward, center, rear, cone. upper, lower, middle, aft, tip. front, back, middle, aft, end.

How does the length of the A321 forward fuselage compare to the A320, and which frames does the additional section (14A) extend between?. It's eight frame bays longer, extending between Fr 35 and Fr 35.8. it's five frame bays longer, extending between Fr 47 and Fr 47.5. it's three frame bays shorter. it's four frame bays shorter.

The fuselage of the Airbus A320 is divided into five main parts. (True/False). True. false.

The forward fuselage of the A321 is longer by eight frame bays compared to the A320, and it includes an additional section between frames (Fr) 35 and 35.8. (True/False). True. false.

The A319 forward fuselage is four frame bays shorter than the A320. (True/False). True. false.

An additional emergency exit is installed on both sides of the A319 in section 15 to accommodate a cabin capacity of at least 160 passengers. (True/False). True. false.

The nose forward fuselage contains the nose landing gear bay and access and service door cutouts. (True/False). True. false.

The nose landing gear bay is shaped by three machined panels reinforced by horizontal and vertical extruded sections attached to the corresponding frames. (True/False). True. False.

The central panel of the lower fuselage in the nose forward fuselage contains an opening for access between Fr 3 and 5 and the opening for the nose landing gear bay between Fr 9 and 20. (True/False). True. false.

What is the extent of the cone/rear fuselage section, measured in frame numbers?. fr 65 to Fr 90. Fr 70 to Fr 87. fr 60 to Fr 80. fr 50 to Fr 75.

What does the rear pressure bulkhead separate within the fuselage? (Choose all that apply). pressurized rear fuselage. cargo compartment. Pressurized rear fuselage, Un-pressurized cone/rear fuselage. landing gear bay.

How is the tail cone unit connected to section 19?. By four lugs and one spigot. welded joints. glue and rivets. bolted connections.

What is the primary function of the engine pylons installed under each wing?. To support the engine. to house electrical wiring. to support the nacelle. to store fuel.

Which part of the pylon primarily houses most of the systems connected with the engine?. Secondary structure. primary structure. fairings. fan cowl doors.

How many points attach the pylon box to the wing?. Three. four. two. five.

What components make up the stabilizers?. Trimmable Horizontal Stabilizer (THS), elevators, vertical stabilizer, and rudde. wings, ailerons, flaps, and slats. engines, pylons, and nacelles. landing gear and doors.

What is the main structure of the Trimmable Horizontal Stabilizer (THS)?. Spar boxes. elevators. leading edge. trailing edge.

What are the primary functions of the engine pylons installed under each wing of the aircraft?. To support the engine, to transmit the engine thrust, to enable the routing and attachment of all the systems connected with the engine. To provide additional lift to the aircraft, to house the landing gear, to store fuel. To provide structural support to the wing, to house the pilot, to store luggage. To house the aircraft's avionics, to support the hydraulic system, to provide additional fuel storage.

Where can detailed information about the structure of the nacelle be found? (Choose all that apply). In the aircraft's maintenance manual, In the nacelle manufacturer documentation. in the pylon manufacturer documentation. in the nacelle manufacturer documentation. in the aircraft's flight operations manual.

How many points support the engine on the pylon box?. Two points. one point. three points. four points.

The hinge fittings of thrust reverser doors are installed on the forward fairing (secondary structure) of the pylon. True. false.

The pylon box is attached to the wing at two points. true. False.

The aft engine to pylon attach fitting is located at Rib 4 for the CFM 56-5 engine configuration. True. false.

Stabilizers include wings, flaps, slats, and ailerons. true. False.

The adjustment of the angle of incidence of the THS is achieved by a hydraulic actuator. True. false.

There are two spar boxes in the Trimmable Horizontal Stabilizer (THS). True. false.

The center joint in the spar box assembly is made from aluminum. true. False.

The leading edge of the Trimmable Horizontal Stabilizer (THS) includes avionics and hydraulics. true. False.