AF 1&2 Maybe Flashcards
Abnormal Flight Conditions?
Are in ATA chapter 5
The main dimensions for the A320 family are basically the same except for length?
A318 is 6.12 m (20 ft) shorter
A319 is 3.74 m (12ft 3in) shorter
A321 is 6.93 m (22ft 9in) longer
The A318 has a slightly different fin for stability?
Due to the fin tip extension, the A318 station numbers have changed. The new additional rib 12N is on the STA597.
What are the different ways to level the aircraft?
1, Alpha call ups on the MCDU (PITCH and ROLL) after aligning the Inertial Reference (IR).
2, Quick levelling with a spirit level in the fwd cargo compartment.
3, On older aircraft there was also the attitude monitor. The procedure consists in operating the jacks of the aircraft to move the bubble to the D4 position in the attitude monitor, which is located in the Refuel/Defuel control panel recess.
Before towing what safety precaution must be undertaken with the steering box?
On the nose wheel steering deactivation electrical-box, set the ground-towing control lever to the towing position and install the pin.
From outside the aircraft, how can you check if the parking brake is applied?
Check that the parking brake light is ON on the nose wheel steering deactivation electrical-box.
What is the max effective turn of a A321 with a steering angle of 75 degrees?
73 degrees
What are the maximum N/WS computed limits?
The BSCU transforms the N/WS angle and has limits.
1, Ruder pedals max 6 degrees
2, Hand wheels: max 74 degrees
What is the maximum towing angle?
The maximum towing angle is 95° on each side. Before towing, the
N/WS control lever has to be in the deactivation position with the
safety pin installed.
Parking and mooring procedures are in ATA chapter 10, what are the headlines?
1, Make sure that the landing gear ground is safetied?
2, Locking devices fitted
3, Wheel chocks are in position
4, Keep the access platform (GSE) at a sufficient distance from the aircraft (in wind, shock absorber rebound can cause movement of the aircraft).
5, If strong winds expected park into wind and consider filling aircraft with fuel.
What is the A320 family’s distance from dimension X?
254 cm or 100 in
Engine danger radius areas?
1, Idle 7.2ft to 19ft (2.2m to 5.79m)
2, Take off 19ft to 21.7ft (5.79m to 6.6m)
The placards and markings on the A/C give the data and instructions related to safety and maintenance. Some of these placards and markings are necessary to obey the regulation used for the Airbus aircraft type certification (JAR 25). Where can they be found for reference?
ATA chapter 11
The ground service connections layout is the same on the AIRBUS A318 and A319. The main difference between A320 and A321 servicing point is a second potable water draining panel. Where is this?
The second potable water draining panel is at the centre of the A/C on the A320.
The DFDR linear accelerometer is located where on the aircraft?
The linear accelerometer is near the A/C center of gravity.
How does the linear accelerometer communicate with the DFDR?
It sends the accelerations in the 3 axes (pitch, roll and yaw) to the DFDRS via the SDAC and FDIMU
Various reports can be printed, how would bleed status be indicated in regards to valve position?
Bleed status is indicated with discrete coded information and numerical values. In the discrete coded information, 0 indicates that the valve is closed and 1 indicates that the valve is open.
Can the Data Management Unit (DMU) be reprogrammed?
The Data Management Unit (DMU) is reprogrammable either with the assistance of the optional Ground Support Equipment (GSE) or partially (very limited) through the MCDU.
How do the MCDUs communicate with the FDIMU?
2 way communication using ARINC 429 DATABUS.
Under normal conditions which displays are driven from DMC 1?
Captains PFD, ND, EWD and SD screens.
How many different ECAM MODES are available?
The ECAM operates in four modes.
1, the normal mode according to the flight phase is automatically presented
2, the failure mode is automatically presented when warning/caution is triggered.
3, the advisory mode is automatically presented when a parameter is
drifting.
4, manual mode, through the ECP.
How many ECAM phases are there in normal mode?
In normal operation the ECAM system pages are displayed according to the current flight phase, this mode is called automatic mode. A flight is divided into 10 phases corresponding to an aircraft configuration change.
How are warnings and cautions displayed on the EWD?
The left memo area is dedicated to warnings and cautions (primary or independent failures) or memo information related to procedural pilot actions or memo information.
What causes a secondary failure and where is it displayed?
The right memo area of the EWD is dedicated to the system affected by a warning or a caution (secondary failure).
How many ECAM phases are there in normal mode?
In normal operation the ECAM system pages are displayed according to the current flight phase, this mode is called automatic mode. A flight is divided into 10 phases corresponding to an aircraft configuration change.
What LRU generates the flight phases?
These flight phases are generated by the FWC and used by the Display Units (DUs) to automatically call up the system pages.
What determines FWC flight phase 6?
Post lift off and RAD ALT above 1500FT (Cruise)
If the ECAM control panel fails how are the system pages entered?
In the event of an ECAM control panel failure, due to the built in redundancy, the system pages are still available through the ALL key.
What happens if the ALL key is pressed and held?
When the ALL key is pressed and held, all the system pages are displayed successively in one second intervals.
How many alerts levels are there and which is the highest priority?
The alerts are classified in three levels, level 3 being the highest.
What determines an independent failure?
An independent failure is a failure, which affects an isolated item of equipment or system without affecting another one. Example: Flight Warning Computer (FWC).
How is an independent failure displayed?
An independent failure is displayed with the title underlined.
What happens if a PFD fails?
In the case of PFD failure (detected) or if the PFD unit is switched off by means of its potentiometer, the PFD is automatically displayed on the ND unit.
What happens if the lower DU fails?
If the lower DU fails or if the lower display is turned to off, no automatic reconfiguration is possible, the ECAM works in single display mode. Each crew member also has the possibility to present the SD image on the ND side only, and never on the PFD side, by rotating the ECAM/ND transfer selector switch on the switching panel.
How are failures classified?
1, Class 1 failures are the most serious and require an immediate maintenance action subject to the Minimum Equipment List (MEL). 2, Class 2 failures may have consequences if a second failure occurs. A Class 2 failure must be repaired within 10 days.
3, Class 3 failures can be left uncorrected until the next scheduled maintenance check.
The symbol Advisory (ADV) located on the lower part of the EWD
is displayed pulsing, what could this be an indication of?
When there are several advisories on several SD pages. In this case,
the SD page which contains the first detected advisory is displayed.
However, ADV symbol will be pulsing in order to indicate to the crew
that there are one or several advisories.
What does a green colour arrow at the bottom of the EWD indicate?
The overflow arrow in green colour indicates that warning messages
exceed the capacity of the display on the left memo area.
When you press CLR a last time, the STATUS reminder STS on the
EWD indicates that the STATUS page is not empty and the CLR P/Bs go off.
On the status page, the cruise page (related to the present flight phase) comes back. The warning has been cleared. The ReCalL P/B lets the crew reactivate the Liquid Crystal Display (LCD) presentation of an alert inhibited either through the flight phase or by the CLR function.
How do the SDACs communicate with the DMCs?
Each DMC receives and processes the data from each of the two System Data Acquisition Concentrators (SDACs). The DMCs use SDAC 1 data providing it is valid. All data transfer is by ARINC 429. If the data is not valid or if SDAC 1 is not valid, the DMCs will use the data from SDAC 2.The switching is automatic.
With a clock failure or a loss of power supply, how is the time calculated?
With a clock failure or a loss of power supply, the digital displays are no longer available. With a loss of main electrical power supply, the time is still counted in memory through the A/C battery supply, except for the CHR and ET functions.
What power is supplied from the aircraft generators and the GPU?
115/200 volts, three phase,- 400 Hz,- 90 kV
What are the Emergency generator characteristics?
15/200 volts, three phase,- 400 Hz,- 5 kVA
What supplies power to the galleys?
The main and secondary electrical circuits of the galleys are supplied by AC BUS 1 and 2. The main electrical circuits are shed in single generator operation.
What supplies power to the galleys?
The main and secondary electrical circuits of the galleys are supplied by AC BUS 1 and 2. The main electrical circuits are shed in single generator operation.
At what temperature will the IDG Oil Temperature Monitoring system automatically disconnect the IDG?
If the oil outlet temperature is more than 200°C the IDG is automatically disconnected.
What condition must the engine be in for IDG disconnect?
Disconnection is only possible if the related engine is running above underspeed.
What maintenance activity must be performed after a thermal disconnection of the IDG?
After a thermal disconnection, the IDG must be replaced.
How is the frequency output of the APU controlled?
The APU generator is driven at a constant speed by the APU.
What condition would cause the primary galley power supply to be automatically shed?
In flight and with ONLY one AC generator online
What condition would cause the RAT to deploy automatically?
If AC BUS 1 and 2 are lost above a given airspeed (100 kts), the Ram Air Turbine (RAT) will extend automatically.
The CSM/G operation is monitored by a red FAULT light. The FAULT
light activation is controlled by either Battery Charge Limiter (BCL) 1or 2. What would cause this light to illuminate?
During transient configuration, or if the generator is faulty, there is no ESS Transformer Rectifier (TR) output, thus the FAULT light comes on.
In a normal configuration which wing fuel pumps are supplied by AC BUS 1.
In normal situations electrical supply of the wing fuel pumps is, Left pump 1 and right pump 1 are supplied by AC BUS 1.
If an avionics smoke warning occurs and smoke is confirmed what actions would be required by the crew and how would they know?
If an avionics smoke warning occurs and smoke is confirmed, GENerator 1 LINE SMOKE P/BSW light comes on amber on the EMERgency ELECtrical PoWeR panel.
In this case, several actions have to be taken by the cockpit crew concerning mainly the ventilation and communication systems. If the smoke warning remains 5 min after actions on the ventilation and communication systems, the avionics smoke procedure displayed on ECAM/EWD has to be applied.
What is the main function of the BCL?
The main function of the BCL is to control the battery contactor and BATtery FAULT warning. Also, BCL 1 and BCL 2 control the EMERgency GENerator FAULT warning.
The skin panels just above and below the windshield are made of what material and why?
The skin panels just above and below the windshield are made of titanium alloy for bird impact requirements.
The forward engine to pylon and the aft engine to pylon attach fitting are designed for what loads?
The forward engine to pylon fitting transmits the engine thrust, side loads and vertical loads. The aft engine to pylon fitting reacts to vertical loads, side loads and roll movement.
What type of flaps are fitted to the A321?
The A321 flaps are fowler flaps with a tab on the trailing edge.
The off wing escape slide release mechanism has three different parts:- the latch pin,- the manual release handles,- the release cable path. What must you do with the latch pin before undertaking maintenance tasks?
To disarm the latch pin you have to press it against the spring load and rotate the pin a quarter turn anti clock-wise. Make sure that the latch pin is fully retracted.
Where can you check the slide bottle pressure?
1, FAP
2, The gauge needle is in the green band on the door itself
What is the purpose of the cockpit ANN LT SW?
The cockpit ANN LT SW is mainly used to test all the ANN LTs in the cockpit or to dim the ANN LTs in night conditions. A switch with 3 positions (DIM, BRT, TEST) is located on the overhead control and indicating panel 25VU.
How are the emergency lights powered?
The 28V DC/6V DC converters of the EPSUs supply the emergency lights as long as the 28V DC ESS SHED BUS is available. If the 28V DC SHED ESS BUS voltage falls below 16V, the EPSUs internal batteries continue to supply the loads for at least 10 minutes.
What 2 signals determine the operation of the LOGO Lights?
If the main gear struts are compressed or the flaps are extended at least 15°. The logo lights are controlled together with the navigation lights by the NAV & LOGO SW.
The Landing lights are controlled by a 3 position switch ON/OFF/RETRACT. What happens if the Landing light is on and RETRACT is selected?
RETRACT, retracts the landing light and shuts it off.
What supplies the escape slide indication on the ECAM DOOR page.
The slide proximity switches give an escape slide indication on the ECAM DOOR page.
What supplies the escape slide indication on the DOOR indicator on the actual door?
A slide and locking shaft proximity sensors trigger a “SLIDE ARMED” indication on the door itself.
What hydraulic systems are connected via the PTU?
The green and yellow systems
Which hydraulic system is capable of powering the rudder?
All 3
When will the PTU automatically operate?
pressure difference of 500 psi between the green and yellow systems.
Where are the EDPs located on the engine?
The EDPs 1 and 2 are located on the accessory gearbox of engine 1 (EDP 1 green system) and engine 2 (EDP 2 yellow system).
The reservoir is normally pressurized with air to prevent cavitation of the pumps. How is this achieved?
The reservoir is pressurized to 50 psi (3.45 bar) and is sealed to hold the pressure when there is no air supply. The threshold of the LP switch is 22 psi (1.52 bar). The threshold of the pressure relief valve is 77 psi (5.3 bar).
If the reservoir needs to be depressurized for a long time during a
maintenance task, what must be used?
If the reservoir needs to be depressurized for a longer time during a maintenance task, a special tool needs to be installed. Unscrew the normal depressurizing valve and install the maintenance tool to prevent unwanted pressure build up.
Before undertaking a Hydraulic reservoir top up what must done first?
Make sure the hydraulic system will not be pressurized during this task. Open the access panel to the hydraulic ground service panel. The direct reading gauge on the reservoir will show the actual air pressure inside the reservoir.
