aircraft genekal - egyptair.com

Airbus Service Company, Inc., / Training Center (Miami, Florida)

AIRCRAFT GENEKAL

1. List all emergency exits available on the A300: A. Six Type "A" plug type doors, two sliding windows and forward cargo door B. Six Type "A" plug type doors, two windows, two 1 one exits and avionics door C. Six plug type doors, two type 1 exits and aft cargo door D. Four plug type doors, two type 1 exits and sliding windows

2. Cargo compartment doors are operated by the A. BLUE Hydraulic system B. GREEN Hydraulic system C.- YELLOW Hydraulic system D. BLUE Hydraulic system

3. All MAIN CABIN DOORS and EMERGENCY EXITS are equipped with a pneumatic opening system: A. True B. False

4. Which cabin sign or signs come on automatically with a loss of cabin pressure? A. NO SMOKING B. FASTEN SEAT BELTS C. RETURN TO SEAT D. All of the above

5 . With the batteries only supplying the AIC Electric power, only the following lights would be Illuminated: A. Glareshield lighting B. MAP light C. CM3 Dome light D. Stormlights

6. In the AUTO position, the NO SMOKING sign comes on automatically if: A. The gear is down and locked B. Flaps are extended greater than FL8 (7. Cabin pressure drops with automatic P/A announcement D. Both A and C

Revised: 1111 7/92


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7. A "T" in the lower left corner of some indicator lights means: A. The lights are dimmable B. They should be out with no system failures C. - They may be pressed to test system integrity D. They constantly receive a trickle charge

8. Electrical upidown and backward motion of the pilots' seats is inhibited when the seatback is reclined more than: A. 5" B. 8" C. 10" D. 13"

9. Which of the following statements is true describing MAGNETIC ANNUNCIATORS (MA s) : A. BLACK means monitored circuit or equipment is satisfactory B. WHITE means circuit or equipment is faulty

(- ---

C. MAS stay white after a fault disappears D.v All of the above

Revised: 11117192


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AIR CONDITIONHVG AND PRESSURPZATION

1. CABIN PRESSURIZATION is controlled automatically by: A. Increasing engines to fight idle B. Calling for cooler air in the cabin and cockpit C, Adjusting the pressure'regulating valves D. Increasing the speed of the airconditioning packs

2. In addition to a refrigeration unit, the packs also have: A. A FLOW CONTROL valve B. A WATER SEPARATOR C. A TURBINE by-pass valve D_ All of the above

3. Unheated air from the cold air manifold is distributed to the cabin by: A. Ceiling level diffuser B.: Outlets above the overhead stowage compartments C. Through gaspers in passenger service units D. All of the above

4. Both A/C pressurization systems operate at the same time in order to more quickly regulate changes in the A/C pressure: A. True B. False

5 . Discharge valves or pressure regulating valves also function as NEGATIVE RELIEF and SAFETY RELIEF valves: A. True B. False

6. Three extractor fans operate in the ventilation systems of the: A. APU B. Batteries C. Instrument Panels D. Both 13 and C

[REF: TP-0389.2171

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C o ~ I ~ O ~ G AN]D BRESSURI[ZAmON - Cont'd

7. Temperature may be automatically or manually controlled by: A. Varying the pack inlet temperature

I B. Adding the trim air C. Closing the pressure regulating valves D. Turning on the LAV and GALLEY BLOWER FANS

8. Ground AUX VALVE closes when the: A. Gear is retracted B. Cabin is fully pressurized C Throttles are set to T. 0 D. Landing gear is compressed

9. The ground AUX VALVE will remain closed if the cabin pressure is greater than: A. .5 psi B. 1.0 psi C. 2.0 psi D. 3.0 psi

10. Closing the FWD and AFT PRESSURE REGULATING VALVE switches also closes the: A. RAM AIR INLET valves B. TURBINE INLET valves C. PACK valves D. Both A and C

11. On the CABIN PRESSURE PANEL, the RATE KNOB will adjust the cabin rate between: A. 100and500FPM B. 200 and 1,000 FPM C. 200and2,OOOFPM D. 300and3,000FPM

Revised: 11/17/92

I Airbus Service Company, Inc., / Training Center (Miami, Florida) I ~

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Am C O ~ I ~ ~ G PRESSmZAnON - Cont7d

12. EXCESS ALT light illuminates red with CABIN PRESS LT on MWP when cabin ALT exceeds: A. 8,600 ft k300ft B. 9,200 ft +500ft t

C. 12,500 ft D. 14,000 ft

13. PRESSURE KI light illuminates red with CABIN PRESS LT on MU?) when cabin pressure exceeds: A. 8.85psi B. 6.65psi C. 9.25 psi D. 9.75 psi

14. EXCESS ALT light is depressed and turns green to indicate that cabin pressure controller, pressure regulating valves and valve position indicators are serviceable: A. True B. False

15. In the event of a complete electrical failure, the A/C can be depressurized by use of the MANUAL AUX valve: A. True B. False

16. The cabin temperature is automatically controlled in AUTO CONTROL between: A. 55°F and 90°F B. 66OFand85"F C. 65°F and 85°F D. 7U°Fand80"F

17. TRIM AIR will not shut completely off if an overheat is detected in the duct and must be closed manually: A. True 3. False

Revised: 11/17/92 [REF. TP-0389.2171


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COmITI[ONI[NG P ~ S S ~ Z A T I O N - Cont'd

18. The TRIM AIR VALVE will close if an overpressure is detected in the hot manifold and the TRIM AIR PRESS HI LT comes on: A. True -- A -

*- a .c . * g 5 &A,, - 4, - .

B=_ False

19. Moving the CARGO (FWD) ISOL VALVES to CLOSE, will close how many valves: A. One (1) B. Two(2) C Three (3) D. Four (4)

20. VENTILATION EXTRACTION FANS with switch in AUTO will run continuously when: A. The gear is down B. Gear struts are depressed C: Cabin pressure differential is below 1 psi D. Engines are running at idle or above

2 1. Oxygen masks wdl automatically deploy when the cabin reaches: A. 8,600ft B. 10,600 ft C. 12,500-12,900 ft D. 13,500-14,000 ft


AUTOMATIC FLIGHT SYSTEMS

1. The A300 is equipped with the following sub-systems in the AUTO-FLIGHT SYSTEM: A. 1 Yaw Damper, 2 Pitch Trims, 2 Autothrottles, 2 Autopilots B. 2 Yaw Dampers, 1 Pitch Trim, 1 Autothrottle, 2 Autopilots C. 2 Yaw Dampers, 2 Pitch Trims, 1 Autothrottle, 2 Autopilots D. 2 Yaw Dampers, 2 Pitch Trims, 2 Autothrottles, 2 Autopilots

2. FAIL PASSIVE means that all AUTO FLIGHT SUB SYSTEMS may lose one of their components and still have continued operation with the same performance after the fxst failure: k True B~S- L False

3. Which function below is NOT accomplished by the YAW DAMPER? A. Turn Coordination B. Auto-rudder deflection after engine failure C: . Trimming the elevator D. Damping lateral oscillations

8 *% +" * - & e ? a - - - - +----- - P *

4. Normdly, both YAW DAMPERS are engaged with system #2 automatically and system #1 being driven and in stand-by: A. True B. False

5. Loss of blue hydraulic pressure wdl cause the #1 Yaw Damper to disengage: A. True B. False

6. The main purpose of the PITCH TRTM is to: A. Automatically hold positive pitch with engine failure B. Cancel loads generated by artificial fuel C. Eliminate overcontrol during alpha-floor D. Move the three hydraulic motors to position the elevator

7. The PITCH TRnil system automatically maintains the elevator and the THS in the same plane by moving the THS: A. -

l rue B. False

Airbus Service Company, Inc., / Training Center (Miami, Ron&)

L>- ,"'

1 AUTOMATIC FLIGHT SYSTEMS - Cont'd

I 8. The pitch can be trimmed manually by mechanically using the pitch trim control wheel and electrically using the rocking levers on the control column: A.-. True B. False -

9. The control wheel rocking levers are stiU usable and engaged with the AP engaged: A?@' True R ' T

Bp: False r-

10. Attempting to protect the AIC in clean configuration against high angle of attack, high mach number and high altitude is called: A. Mach Trim ..*. 5 -

, -$ f*. ,? a-.--"<*--=-&l", - Alpha Trim *, - C. Manual Trim D. Turb Trim

I I. Manual, Electrical and Auto Trim may be overridde ilot but - it - is not possible for him to override Mach Trim and Alpha Trim: Ybw-$--= : x . +

A . True B1.' False 2 ,-

* 67 ?<*y"g;/ 12. ALPHA TRLM function: *- * - -

A. Gives a nose up signal when ax speed is approachng MMOIVMO B. Gives a nose down signal to the THS with high angle of attack C. Trims the elevators down as airspeed increases D. Gives a nose up signal to the THS

- - -- 13. There are &Q ANGLE-OF-ATTACK sensors located on each side of the cockpit area:

rue B. False-:

14. Both Pitch Trim Control Levers will disengage if the electrical trim is overridden by manually tnmrning or holding the pitch trim control wheel:

,-

A. True ! B. False k

Airbus Service Company, Inc., / Training Cenfer (Miami, Florida)

AUTOMATPC FLIGHT SYSTEMS - Conrt'd

15. The second Pitch Trim System must be selected following a single channel disengagement since it does not automatically take over: A. True B.f False 1

16. The Auto Throttle System will NOT perform which of the following: A. Capture and hold a selected speed B. Capture and hold N1 C Protect the A/C against high "G" forces D. Protect the A/C against high angle of attack

17. Placing the ATS arming lever in position, ARMS the autothrottle but there is no mechanical connection to the throttle: A%-" True -

B. False

18. In speed mode, the ATS controls the throttles to capture and hold: A. 250 knots below 10,000 feet Bk2 Speed selected on control panel C. MAX speed limited by N l computer D. 78 Mach above 28,000 feet in cruise

19. In normal operation, with autothrottles operating: A. N2 is limited to compute max engine speed B. N1 and speed modes may be engaged simultaneously C . Speed mode is normally use for T I 0 D,= N1 Limit Computer limits N1 speed to MAX value computed

30. ALPHA FLOOR will cancel SPEED MODE automatically and make engagement impossible with AIC at a high angle of attack: A . True B. Fdse

Revised: 1 i l l7192

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Airbus Service Comparqv, Inc., / Training Center (Miami, Florida) . -

AUTOMATIC FLIGHT SYSTEMS - Cont'd

21. In LAND mode, the ATS moves the throttles to the 5" Electrical stop at: A. 100 feet B. 50 feet C* 20 feet

/

D. 15 feet

22. Autothrottles are not required when making a Category IT1 or Land 111 Approach and Landing: A. True B:+ False

23. The N1 mode is normally engaged and used in: A%"+ -> Takeoff

B. Level Flight C. Descent /

i D . Approaches --

24. SPEED MODE is normally m u s e d when A/C is: A. In Level Flight B. Climbing C. Taking off D . Descending

25. The N1 mode may be cancelled by the crew by: A. Disconnecting instinctive pushbutton B. Pressing N1 pushbutton again C. Pressing SPEED pushbutton D. All of the above

26. ed in order to engage FLEX or T . 0 on the N1 computer:

B. False

Revised: 11/17/92 [REF: TP-0389 -2171

I Airbus Service Company, Inc., / Training Center (Idiami, Florida)

AUTOhaAnC FLIGHT SYSTEMS - Cont'd

27. How many modes may be selected using the ATS? - A s TWO (2) &$$ ,? :s&2%-&+m

. k ; !FA:&-& B. Three (3)

28. Moving the ATS ARMING LEVER to the raised position activates the ATS: A. True Be4 False

29. Can the SPEED MODE be used on the ground for takeoff: A. Yes B..' No

30. Normally, N1 mode is activated for T . 0 or G.A by: A. Moving ATS arming lever to raised position B. Selecting FLEX or T .0 on the NS computer

C"'V - p-e- ' Raising one of the GO-LEVERS ; P- - .;.- -+ --, D. Manually pushing the throttles fokard

3 1. If the angle of attack becomes too high for the configuration, the: A. ATS switches over to SPEED MODE BI ATS switches over to N1 MODE C. ATS calls for MAX ENG POWER regardless of N1 LIMITER position D. ATS causes the AP to increase the PITCH ATTITUDE

32. ALPHA FLOOR is inhibited below: A. Traffic pattern altitude B. 700 feet above the ground C: 100 feet above the ground D. 10,000 . . . . on pressure altimeter

33. If the NS LA4IT COMPUTER is inoperative, will the ATS operate in the SPEED SELECT MODE? A. " r es B. No

Revised: 11/17/92

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Airbus Service Cornparry, Inc., / Training Center (Miami, Horida)

AUTONhATIC FLIGHT SYSTEMS - Cont'd

34. In the LAND MODE FLARE-OUT, SPEED SELECT MODE is disengaged automatically at: A. 20 feet B .---. Touchdown C. 70 knots D. Engine shutdown

35. Autothrottles may be used for single-engine landings: A. True B3-" False

36. If GA MODE is engaged on the ATS, pressing the GA PUSHBUTTON again disengages the ATS and THR OFF flashes on the FPI. A. True B: False T'--

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37. Two APs may be selected ON simultaneously in: A. Approach B. - Landing C. Cruise D. Go-Around

38. CWS is available normally when: A. AP is in LAND MODE B. AP is in MAN MODE C. AP is in COMMAND MODE D. AP is in NAV MODE

39. The Pilot is unable to manually move the controls when the AP is in command: A. True B: False

Revised: 11117192 [REF: TP-0389.2171

Airbus Service Company, Znc., / Training Center (Miami, Florida)

c i


40. If both APs are engaged in LAND MODE, when do they both operate: A. When 2nd AP is engaged B. Below 1,500 feet AGL C+-' Below 700 feet D. GA if selected below 700 feet E. Both C and D

41. AUTOTHROTTLES DE-CLUTCH in T . 0 or FLEX when the selected thrust setting is stabilized: A;T True B. False

42. It is necessary to always arm the ATS in order to ARM the ALPHA FLOOR system: A.%- True B. False

43. Engaging either AP in command automatically engages the associated FID: Aft" True B. False

44. Selecting an UPPER MODE is necessary in order to use the FD roll bar: A, True B. False

45. Which action below does not occur if FD FAILS? A. FD light goes off B. Lights on FPI relating to FD go off CY * FD BARS remain in their position D. FD FLAG comes into view on corresponding AD1

46. When AP is engaged in CMD, associated FD is automatically engaged. When AP is disengaged, associated FD also disengages in normal modes: A. True B: - False

Revised: 11117192 14 of 73 [REF: TP-0389.2171


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a. a "

*- -.. == c-- ,> 2h'+-e :.*- -

* %* & --" 47. ALT ACQ AMBER may be selected using the ALT PUSHBUTTON on the ALT

CONTROL PANEL: i - +

,,y++*~e& A. True ":- .. - *: 5; AM>~rja; + .~ B.9 -' False

48. The FD UPPER MODE which is not a l~g i tud ina l (pitch) mode is: A. IAS - B. ALT- C. ALTACQ- DY-* VIL

49. The FD UPPER MODE which is not a LATEWL - _ MODE is: A. BIB- B':"' U S

C. HDGSEL-

50. One mode of the FD common to both LATERAL and LONGITUDINAL MODES is: A. ALT B. VL C. BIB D.' APPR

5 1. The Captain or First Officer Pushbutton above the ALT selects the BAR0 reference for ALT ACQ and ALT Alert System: A . True B. False

52. ALT ACQ AMBER may be selected using the ALT ACQ PUSHBUTTON on the ALT CONTROL PANEL: A - True B. False

Rcviscd: 11/17/92 [REF: TP-0389.2171

Airbus Service Company, Inc., / Training Center (Miami, Florida) a I-


53. On an ILS APPROACH, the: A. VIL changes from AMBER to GREEN B. G/S changes from AMBER to GREEN C. FD BARS COMMAND or HOLD ILS FLIGHT PATH D S All of the above

54. Second FD should be engaged after: A. 1,500 feet above ground= B. LOC Captured" C. G/S Captured- D. A/C Stabilized on Descent, E;>=a B, C and D above

55. In order to display INS information on the FDs, the following must be accomplished: A. FD BAR SW.OFF B. VLIINS S W. in NAV C . NAV PUSHBUTTON UPPER MODE selected D . B and C above

56. The SRS.is a FLIGHT DIRECTOR SUB-MODE which will not: A. Provide guidance during takeoff B. Provide guidance during manual GA CI- Provide guidance during High--Mt$limb D. Initiate protection with high angle of attack

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57. Which condition is not necessary to engage the SRS for takeoff: A. AIC on ground Brg' Lateral mode engaged C. No FD engaged in pitch upper mode D. Action on the Go-lever

58. During TAKFOFF, the FD PITCH BAR directed by SRS commands: A. V, + 10 knots on 2 Engines -:. B. V, with engine fadure

i' C. VR + 10 knots kz- - D. A and B above

Airbus Service Company, Inc., / Trainirig Center (Miami, Florida)

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59. Angle of attack of 9.5", with slats extended, always engages the A FLOOR PROTECTION: A:$ True B False a ,

8 - . * - n z , . 6 " - -- 2,. -- hi 6 r - 60. ALPHA FLOOR activation does not cause any lights on FPI to come on:

A. True B.,. False

61. Which of the following is not true about the AP ENGAGEMENT? * - - .=+

A. Hold existing HDG if roil-is less than 5" B. Hold existing Roll Att between 5" and 30" C. Decreases and holds 30" if engaged between 30" and 45 " D. - Decreases and holds 45" if engaged between 45" and 60"

62. When the AP is engaged in CMD POSITION, the following is nottrue: -- A. Associated FD is automatically engaged B: FD BARS appear on ADIs C. CWS is available in pitch D. CWS is available in roll

63. BEAM DEVIATION LIGHT comes on when intercepting the LOC on a CAT 11 or CAT IV approach: A:-- True B. False

64. In an AUTOLAND APPROACH, GA and FLARE circuits should complete their testing by: A. Outer marker B. 1,000 feet AGL C: 700 feet AGL D. 50 feet-AGL

Revised 11/17/92 170f 73 W F . TP-0389.2171 -

Airbus Service Company, Inc., / Training Center (Miami, Florida) 9

THC FLIGHT SYSmMS - Csnt'd

65. FLARE lights come on at approximately: A. 100feet B. 200 feet C ; 50 feet D. 20 feet

66. Above 700 feet, the engagement of the GA mode will disconnect the last AP engaged during the approach: Ad.: True B. False

67. FLAPS must be at least 8" or greater in order to engage go-around on the AP: A .;. True B. False

i -< 68. On an AUTOLAND APPROACH, you hear "click, click, click". What does this

indicate? A. LAND 1 changed to LAND 2 B. LAND 2 changed to LAND 3 C - LAND 3 changed back to LAND 2 D. All of the above

69. AUTOLAND RED LIGHT will not come on if: A. BEAM DEVIATION LIGHT comes on B. AP OFF LIGHT comes on C. Long FLARE D, All of the above

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Revised 11/17/92 18 of 73 [REF: TP-0389.2171

Airbus Service Company, k c . , / Training Center (Miami, Ron'&)

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1. The APU is an independent source of: A. Pneumatic pressure for engine starting B. Electrical power C. Pneumatic pressure for airconditioning D? All of the above

2. It is recommended to leave the APU running for takeoff: A. True B:, False

3. In flight, the APU provides emergency power for airconditioning below: A. MAX CRUISE B. 30,000 ft C? 15,000 ft D. 10,000 ft

4. The APU can be started up to: A. 30,000 ft B.r 25,000 ft C. 15,000 ft D. 10,000 ft

5 . The APU GAS TURBINE is powered by a triple spool design, using a low press spool, a high pressure spool and a turbine spool: A. True B."."? False

6. With the Control Sys selected to STBY, the APU can be operated: A. Only in flight B. On the ground and in flight CF' Only on the ground D. Only in an emergency

Revised: 1 1/17/92

Airbus Service Company, Inc., / Training Center (filiami, Florida)

7. If the APU is automatically shutdown by a malfunction, indications are: A. The FAULT light on the APU panel illuminates B. APU light on M W P illuminates C. The SSG sounds D.' All of the above

8. What are the MAX N1 and N2 RPM limits: A. 98% B. 100% C." 110% D. 120%

9. What are the MAX EGT limit? A. 550°C in flight

- X~,

B. 565°C on the ground CT'" 585°C - D. 6OO0C

10. The FLAP WARNING light on the APU panel illuminates when the air intake flap: A. is in transit B disagrees with the landing gear position C. is open on the ground D. BothAandB.

11. If the air intake flap remains open in flight, maximum speed for starting the APU is: A27 .55m

12. The APU is normally supplied with fuel from the right wing tanks: A. True B; False

Airbas Service Company, Inc., / Training Center (iWiLPmi, FT58ida)

1

13. At what RPM does the starter cut out and start light extinguish? A. 45% N1 B. 50% N1 C.: 5 0 % N 2 D. 95% N2

14. When using pneumatic air, the APU shut down is delayed for: A. 30 sec B. 60 sec C. 75 Sec D:. 90sec

15. The APU can be shutdown: A. Only at the M U panel B. Only at the APU panel or the ground interphone panel C; On the APU, ground interphone , or refuel panels D. Only manually

16. Oil quantity, before starting the APU, should be: A. 4 quarts B: 6 quarts C. 8 quarts D. 4 gallons

17. The starter motor is limited to: A. 2 motor duty cycles of 1 rnin, 3 rnin cooling between cycles, 30 rnin cooling after

2 cycles B.; 4 cycles, 5 rnin cooldown, 60 rnin cooling C. 6 cycles, 2 min cooldown, 30 rnin cooling D. 5 cycles, 4 min cooldown, 60 min cooling

18. If the APU is operated in wing anti-icing on the ground, its use after T.O. is limited to: A. 5,000 ft 5: 10,000ft C. 20,oooft D. 30,000 ft

Revised: 1 1/17/92 [REF: TP-0389.2171

Airbus Service Company, Inc., / Trcining Center (ivia~ni, Flonkh)

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810 CATIONS

Which is not a RADIO MASTER SUPPLY position? A. SYS 1 3. SYS 2 C 3 STAND-BY D. ESS SYS

r - The AUDIO SELECTOR panel has - reception PB and transmission keys: A. 5 - 7 B. 4 - 10 C. 10 - 6 D 1 3 - 7

A green Light comes on to indicate the selected side and FREQ on the VHF transceiver: A2 True B. False

VHFS is electrically supplied by : (RADIO MASTER in ESS SYS position): A. TheACBUS#S B. AC BUS #2 CW DC ESS BUS D. DC normal BUS

After selecting a transmission key, which switch must be used to permit transmission? A. The marker switch 3. The NAV switch CY The INTIRADIO switch D. The voice only key

The TFR switch should not be used unless a VHF transmitter fails: A. True B y False

I Revised: 11/17/92

[REF: TP-0389.2171

Airbus Sewice Company, k c . , / Training Center (Miami, Florida) f I

CO CATIONS - Csnt'd

7. The HF radio systems require how many minutes for warm up? A. 1 minute 3. 2 minutes C. 3 minutes D. 5 minutes

! 8. When the Radio Master Supply SW. is in the SYS 1 position, the HF 1 Radio is powered I by: A. AC BUS 1 and AC ESS BUS B: AC BUS 1 and DC Normal BUS

I C . AC BUS 2 and DC Normal BUS D. ACESSBUS

i 9. The CABIN INTPH SW. on the pilot's overhead panel connects the:

A. Flight interphone system and maintenance jack boxes B.s-- Flight and cabin interphone systems C. Cabin service interphone system and maintenance jack boxes

1 D. All of the above

10. ATC Transponder No. l is normally supplied by: A. ACESSBUS B. AC EMERG BUS C. Hot BATT BUS D. DC ESS BUS

11 . With ATC MODE SELECTOR in the STBY position, both transponders are elecolcally supplied: A.: True B. False

12. Pressing and ATTENDANT CALL PB on the CALLS panel will: A. Call all flight attendants 3. Call appropriate flight attendant(s) c . :- Call appropriate flight attendant(~) and energize hi tone on speakers

. D. Turn on all NO SMOKING/SEAT BELT lights for landing .

13. Reset PB must be pressed after using calls system: A: True B. False

Revised: 11/17/92 23 of 73

Airbus Service Company, Inc., / Training Center (Miami, Flu&)

1. The AC Electrical SYS can be supplied by: A. Three engine driven generators B. Two engine driven generators in parallel C. Two engine driven generators, one APU generator, or external power unit D. The APU and one engine generator in parallel

2. The technical electrical system can be powered by: A. Any one generator B. Any two generators C. Two generators, one engine plus RAT D. One generator plus the RAT

3. How many AC Buses are powered by 115V, 400 HZ? A. Two (2) B. Three (3) C Four(4) D. Five (5)

4. How many TRs supply power to DC Normal and Essential Buses? A. Two (2) _B, Three (3) C. Four (4) D. Five (5)

5. How many batteries supply power to the DC BUS? _A. Three (3) B. Four (4) C. Five (5) D. Six(6)

6. The AC Emergency BUS and DC essential buses power the: A. Capan ' s FLT INST and First Officer's #2 NAV and COM Radios B. F.O's Primary and Flight Instruments C . No. 1 and No.2' NAV Instruments D> - - Captain's FLT INST, #1 NAV and COM Radios

Revised: 11/17/92 24 of 73


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7. In reference to the QM, if AC Essential Bus fails, batteries will power AC Emerg and DC ESS for approximately: A. 30 minutes B. 60 minutes C1 52 minutes D. 45 minutes

8. With both APU generator and external power available, the one engaged first has priority: A? +" True B. -* False

9. CSDs may be disconnected by holding the SW.no longer than: A. 2 seconds B. 3 seconds C. 3 seconds D. 1 minute

10. The AC ESSENTIAL BUS is normally powered by: A. AC BUS 1 * B. AC BUS 2 C. ACBUS3 D. AC EMERG. BUS

11, The AC EMERG BUS is normally powered by: A. AC BUS 1 B. AC BUS 2 C. The emergency inverter D. The AC ESS BUS

12. During NORMAL operations, batteries are controlled by CLUs: A. True B. False

Revised: 11/17/92 [REF: TP-0389.2171

Airbus Service Company, Inc., / Training Gnter (~Viarni, Florida)

I a

ELECTRICAL - Cont'd

13. If a GEN LOAD HI light illuminates, GALLEY SW. will trip to SHED: a. True B. False - -

14. When illuminated, the EXT PWR AVAIL light indicates: A. APU is powering the electrical system B. External power is connected

. External power is connected and parameters normal D. None of the above

15. Normally loss of generator power must be manually transferred: A. True B. False

- , 1 16. If a GEN OFF light is illuminated, it indicates:

A. Related generator is set to OFF RESET B. GEN SW. is ON and FAILURE has been detected C. GEN SW. is ON and line contactor has failed D. All of the above .*

17. The AC ESS BUS selector is normally set to which position? 4. G E N 1 _r

B. GEN2 c. NORM D. APU GEN

18. GEN HI Light indicates: A. Generator has failed B Excessive load on respective generator P.>.

C. CSD oil is overheating D. Generator output more than 400 HZ and 115 volts.

Rzvised: 11117192

Airbus Service Company, Inc., / Training Center (lWiami, .Floniik)

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CABIN SERVICE LOAD SHED SW. cuts _ L I power to these units except: A. =Passenger reading/sidewall lights . Passenger PA System C. - Logo lights D. -Passenger service units

In flight, the GEN LOAD MI Light will automatically trip the GALLEY SW. to the SHED position: A. True B. False - What is the minimum battery voltage with the emergency inverter operating? A. 17 V B. 2 0 V C. 2 3 V D. 30 V

What is the maximum continuous amps on a TR? A. 125AMPS EL 150 AMPS C. 225 AMPS D. 250 AMPS

An AC generator can be operated with a load of 1.5 (150 %) for: A. 2 minutes maximum B. 3 minutes maximum Ct i4 5 minutes maximum D. Unlimited

Electrical loads may be shed by moving SMOKE SWITCHES. Which switch or CB removes all equip? A. FLT DECK SMOKE B. MAIN BAY SMOKE C. BAIT SMOKE

MIN EQUIP CB's on Overhead Panel

External power must be constantly checked to prevent overiunder voltage and overlunder frequency: A. True B. False

-x -

Revised: 11/17/92 [REF: TP-0389.2171

Airbus Service Company, Inc., / Training Center (Miami, Florida) f

EMERGENCY EQUIIBrnNT

1. Each pilot and the CM3 are provided with a portable oxygen bottle and full face mask: A. True B .r , False

*>.

2. The cabin will be equipped with 5 megaphones and 2 first aid kits: A. I - - 1 B.--* 2 -- 2 C. 3 - - 4 D. 6 - - 2

3. Emergency lighting receives its electrical power from: A 28VDCESSBUS B. H5V AC ESS BUS C. A C B U S 1 D. DC NORMAL BUS

4. EXIT LIGHTS must be taken from the aircraft in order to illuminate the slides: A. True 13.:" False

5 . The evacuation command system provides crew and passengers a visuallaudio warning when evacuation is imminent: A:- True B. False

6. The flight crew is provided with a chemical generated oxygen system for emergency oxygen: A. True B: False

7. Oxygen for the crew should normally be in the N/100% for emergency use: e

6 " - A. Tiue L- B.- False

Revised. 11/17/92 _____ 28 of 73

- - - -- -- - -

[REF. TP-0389.2171

Airbus Service Company, Inc., / Training Center (Miami, Norida) e G

8. Passenger masks automatically drop if cabin altitude exceeds: A. 8,600 ft B. 10,500 ft +300 C. 12,500 ft f 500 D. 14,00 ft -500 +O

9. PASSENGER OXY SYS can be actuated manually by: A. CM1 on overhead panel B. CM2 on overhead panel C;.- CM3 on engineer's panel D. Flight Attendant at FWD Exit Door

10. TIMER NOT RESET light: A. Shows passengers are using oxygen 23. Indicates mask did not drop C: Indicates mask doors are open D. Indicates cabin is above 14,000 ft

11. EMRG EXIT LT in ARM POSITION, lights in cabin come on if: A , 28 V DC Power is lost B. AC ESS is lost C. Batteries are charging D. No. 1 AC BUS is lost

12. EVAC SW. in ARM position allows: A. The CM1 to initiate evacuation B. CM3 to initiate evacuation C.' CM1 or Cabin Attendant to initiate evacuation D. CM3 or Cabin Attendant to initiate evacuation

13. There are how many escape slides on the AIC? A. 4 at main doors B. 6 at main doors C. 6 dual lane main doors and one single lane at each emergency exit D. 6 at main doors and 4 gailey exit slides

Revised: 11/17/92 29 of 73

Airbus Service Company, Inc., / Training Center (Miami, Roridn) a t

14. The flight compartment door can be forced open toward the cabin: A: True B. False

15. CO, Pressure used to inflate the slides is normally: A. 2,500 psi I 3 3,OOOpsi C. 3,500 psi D. 3,750 psi

16. The two emergency exit doors do not have a pneumatic opening to help open d u f i g emergencies: A? True B. False

17. The CEILING LIGHTS and EMERG. EXIT signs may be turned on by: A. M I N C A B L T - O N B. EMERG.EXITLT-ON C. EMERG. SW.on PURSER'S Panel D,- Any of the above 3 j x

18. If 28V DC power is lost, batteries will power the 6V lights for: A. 10 minutes B., 13 minutes C. 20 minutes D. 60 minutes

19. The EhfERG EXIT LT ON annunciator on the SIGNS panel will illuminate AMBER when: A. EMERG switch on PURSER'S panel is pressed B. EMERG EXIT LT selector is in ON position C . EMERG EXIT LT is in ARM and TEST RESET is pressed D: Any of the above .-

Revised: 11/17/92 [REF: TP-0389.2171

20. Passenger oxygen generator provides oxygen for approximately: A. 5 minutes B. 10 minutes C- 15 minutes D. 30 minutes

i - 1

I I 21. The HORN SHUT OFF switch on the EVAC SIGNAL PANEL will: i i

A. Extmguish the EVAC LIGHT B. Disarm the evacuation warning system C. Cancel the audible warning and extinguish the EVAC LIGHT

i D . Cancel the audible warning

1 I 22. Crew oxygen system has a dual distribution circuit supplied by:

A.: Two (2) oxygen cylinders B. Three (3) cylinders C. Two (2) Oxygen generating units D. Two (2) Cylinders and two (2) generating units

23. Crew oxygen cylinders are normally charged to about: A. 1,500 psi B. 1,600psi C:- 1,800 psi D. 2,000 psi

24. Crew oxygen regulator is N (normal) position provides 100% 4 above: A. 20,000 ft

25. Passenger oxygen is activated by generating units: A. When the related door is open B. By the cockpit crew C. If the cabin exceeds 10,000 ft D3' When the mask is pulled down

Revised: 11117192 31 of 73 [REF: TP-0389.2171

Airbus Service Company, Inc., / Training Center (&&mi, Florida)

> >

26. On CREW OXY panel, with crossfeed at NORM, the AFT OXY CYL1NL)ER supplies:

A, " First Officer and Flight Engineer B. First Officer and Captain C. Captain and Flight Engineer DI * Captain and observers

Revised: 11/17/92

Airbus Service Company, Inc., / Training Cenier (A.fkrni, Florida) d I

1. The fire detection system and extinguishing system is provided for the following systems except : A. No. 1 Engine B. No. 2 Engine C. Aft Cargo Compartment D. APU

2. A smoke detection system is provided for the: A. Flight Compartment B. Weather radar and batteries C. Main and min. equipment bays D. - All of the above

3. A smoke detection and extinguishing system is provlded for the cargo compartments: A.-," True B. Z -^False c

4. Two loops in parallel detect fire and overheat in the engine compartments: A. True B. False

--*

5 . Each engine fire system has one freon bottle in the engine pylon: A. True B.*. False

6. The APU has one bottle and is discharged: A. Automatically in flight B, Automatically on the ground C. Manually by turning the fire handle D. B or C above

7. If fire detected on both loops or one loop when selected, indications are: A. Fire Bell sounds B. FIRE LT on MWP and FIRE HANDLE illuminates C. Engine fuel lever and loop lights illuminate D.L All of the above .

Revised: 11/17/92 33 of 73

Airbus Service Company, Znc., / Training Center (Miami, Florida) 8 1

FIRE PROTECTION - Cont'd

8. In addition to the above warnings, the APU on the ground adds: A. A RED LIGHT on the FUELIDEFUEL PANEL B. A RED LIGHT on the NOSE GEAR C. A BELL in the NOSE GEAR WHEELWELL D. None of the above

9. With FIRE DETECT LOOPS set at both, a fxe detected by one loop will: A. Sound fire warning B. Light both loops C. Indicate a faulty system D: Light one loop light, SSG sounds alongwith LOOPS LT on the MWP

10. A fire bell may be cancelled: A. Press FIRE BELL CANCEL or AUDIO CANCEL SWITCH

i B. Pull related FIRE HANDLE i C. Automatically when fire goes out

D. Any of the above

11. How many bottles are provided for the FWD and MID Cargo area? A. One bottle in each compartment B. Two bottles in each compartment C. Two bottles to use in either compartment D. None - Oxygen is starved by sealmg compartment

12. The AFT CARGO compartment has one bottle: A. True B? False

13. With an engine fire, the second bottle is discharged after: A. 10seconds B. 20 seconds C. 30 seconds D, 60 seconds

Revised: 11/17/92 [REF: TP-0389.2171

Airbus Service Company, Znc., / Training Center (Miami, Florida) t 1

FIRE PROTECTION - Cont'd

14. With a cargo fire, the second bottle is discharged after: A. 30 minutes B.- 60 minutes C. 90 minutes D. 120 minutes

15. Smoke detected in AFT CARGO COMPARTMENTS will automatically close the isolation and Temp. Control valves: A: True B. False

I

16. The SNIFFER FAN draws air from: ~ A. Battery Box , B. Main Avionics Compartment I

C. Radar Box D. Min. Equip. Bay

17. FLT DECK SMOKE LT detects smoke from: A. Main Avionics Bay B. Weather Radar C. Battery Box D,. .b Any of the above

18. If in flight with one loop selected, a light on the loop must be treated as an actual fire: A? True B. False

Revised: 11/17/92

Airbus Service Company, Inc., / Training Center (naiarni, Florida)

1. Which of the following is not a primary flight control? A. Rudder B. Roll S . -. .

C; Flaps D. Ailerons E. Elevator

2 Secondary flight controls consist of slats, flaps and ground spoilers: A. True B. False

3. All primary flight controls are powered by how many hydraulic systems? A. One (1) B. Two(2) c, Three (3) D. Four (4)

4. If the SERVO CONTROLS lever is set to OFF: A. Hydraulic supply to the system is cut off B. JAM and SERVO warning are de-activated C. Controls are frozen D.? Both A and B above

5. Which does not control roll of the AIC? A. All speed aileron B. Low speed aileron C i - All spoilers D. Three (3) roll spoilers

6. Roll inputs are not received from: A. Artificial feel B. Rudder C. All speed aderon droop

I D Trim - /

Revised: 11/17/92

Airbus Service Company, Inc., / Training Center (hIiarni, Ronda)

*- i

I

7. The control wheel will raise the spoilers above: A. 5" 43. 10" C . , ' 15" D. 25"

8. A signal from the flaps drops the ASA a maximum of: A, 5" 3. 10" C. 12" D. 15"

9. If one elevator cable jams, the other will operate the elevator: A. Below 185 knots B. Below 195 knots C. Above 195 knots D. Over 200 knots

10. The pitch trim system can be actuated electrically and also provides: A. Mach Trim B. Angle of Attack Trim C . Rudder Trim ' D . BothAandBabove

11. Pitch trim has: A System 1 active, System 2 standby B. Both systems active C. System 2 active, System 1 standby D. Both systems active with manual backup

12. Auto disengagement of pitch trim will:

4% Trip Pitch Trim lever off B. Illuminate Pitch Trim Light on MWP C. SSG will sound D?2 All of the above ' 9 --

As* "*# &%a p " --La -=. - --. *- - * 2" *--*,-

Revised: 11/17/92 37 of 73

Airbus Service Company, d m . , / Training Center (itfiarni, Florida)

ii I

FLIGHT CONmOLS - Cont'd

13. A jammed THS servo valve will initiate warnings and disconnect the system: A. True B.: - False

14. Rudders may be moved with the pedals from: A. 20" at low speed, 10" at high speed B. 25" at low speed, 15" at high speed C, 30" at low speed, 5" at high speed D. 30" at low speed, 10" at high speed

15. Roll spoilers and LSA are hydraulically linked to the ASA: A. True B.? False

. 16. A Detent bell crank will release if a jam is detected in the: A. Ailerons B. . Elevators C. THS D. Rudder

17. The THS is controlled. by how many hydraulic motors? A. One (1) B. Two(2) Cr- Three (3) D. Four (4)

18. Yaw control is operated by moving the rudder with how many servo controls? A. Four (4) B - Three (3) C. Two (2) D. One (1)

19. If reverse thrust is selected, speed brake armed, ground spoilers will automatically extend:

I

. _, A , - True B. False

38 of 73 [REF: TP-(3389.2171

Airhus Service Company, Pnc., / Training Center (~VJiizrni, No&) 3

20. SLATS and FLAPS are both protected by Pressure-Off Brakes to stop movement in case of asymmetrical conditions: A. True B. False

2 1. Deflection of the ground spoilers is: A. Inner SB 35" - outer SB 35" - roll spoilers 50" B. Inner SB 50" - outer SB 35" - roll spoilers 50" C. Inner SB 25" - outer SB 50" - roll spoilers 50" D. Inner SB 50" - outer SB 10" - roll spoilers 25"

22. In the air, how many SBs are used? A. One (1) each wing B. Two(2)eachwing C. Three (3) each wing D, Four (4) each wing

23. How many SBs are used as ground spoilers? A. Five (5) each wing B :: Four (4) each wing C. Three (3) each wing D. Two (2) each wing

24. The FLAP CONTROL lever has: A. Four (4) positions, two (2) gates B:- Five (5 ) positions, two (2) gates C. Six (6) positions, one (1) gate D. Seven (7) positions

25. When T . 0 CONFIG TEST is pressed, warnings indicate: A. SB extended, parking brakes are set B '+- . SB extended, trim not set for T.O., slats not set for T.O. C . SB lever is not armed D. Cargo door not locked

Revised: 11/17/92


26. A blue light (LS) illuminated on the FCPI indicates: A. LSA is jammed B. HSAarejammed C. LSA position is displayed on aileron scale D. Takeoff is prohibited

27. If pitch feel is operating in high speed configuration, PITCH DISAGREE and PITCH FEEL lights on MWP with SSG when: A. Flaps are extended 8" or more B. Flaps are extended 15" or more C. Flaps are extended 16" or more D. Flaps are extended 25" or more

28. The speed brake lever cannot be moved in flight if the ground spoilers are armed: A. True B. False

29. The blue KRUG light on the slatslflaps position indicator is illuminated: A. When the KRUG flaps are retracted B. Steady during KRUGER flap transit C. When KRUGER flaps are extended D. Only on the ground

30. The PITCH FEEL LT ON indicates that one pitch feel system has faded and the other is operating: A. True B. False

3 1. The PITCH DISAGREE ON LT comes on if the pitch feel is operating in the high speed configuration: A. True B. False

Revised: 11/17/92

Airbus Service Company, dnc., / Training Center (&mi, Florida)

32. Stabilizer trim may be set mechanically or manually: A. - 5" nose down to +30° nose up B. - 10" nose down to -25" nose up C., - 3" nose down to + 12" nose up D. - l o nose down to + lo0 nose up

33. RUDD DISAGREE LT comes on when rudder travel is in the high speed configuration and flaps are 8" or more: A. True B. False

34. RUDDER TRAVEL LT comes on when there is a failure in one rudder travel system: A. True B. False

35. RUDDER TRIM will trim the rudder about: A 5" to either side B. 12" to either side C 21" to either side D. 30" to either side

36. Moving the FLAP lever to its first position will extend the flap to 8": A. True B.- False

37. Flaps use which hydraulic system for power? A. Blue and yellow B. Green and yellow C. Green and blue D. None of the above

38. Slats use which hydraulic system for power? A. Blue and yellow B. Blue and green C. Green and yellow D. Any of the above

Revised: 11/17/92


39. The main landing gear wheel speed must be above - for the ground spoilers to extend: A.- 50 knots B. 100 knots C. 150 knots D. 200 knots

40. STAB TRIM must be set for T.O. between: A. 5"upand1 .5"down B . 3 .5"upand1.5"down C. 1.5" up and 3.5" down D. 7" up and 5" down

41. The CONFIG LT will come on if: A:: All of the below B. STAB is not trimmed in T.O. range C. SB or spoilers are extended D. SlatsIFlaps are not set for T . 0

42. ASYM LT on SFPI indicates a slat or flaps asymmetric condition: A.* True B. False

43. LO SPD AIL LT comes on when either LSA disagrees with the slatslflaps control lever position: A:. True B. False

44. With jamming of any control surfaces, all SERVOS retract the actuating ARM upon any detected failure: A.: True B. False

Revised: 11/17/92


1- i

There are independent AIR DATA SYSTEMS : A: Two(2) B. Three (3) C. Four (4) D. Five (5)

2. ADC 1 relates to the CAPTAIN PITOTISTATIC while ADC 2 relates to the FIRST OFFICER PITOTISTATIC: A.r True B. False

3. STBY PITOTISTATIC only supplies data to the STBY instruments and is not used by an ADS: A? True B. False

4. ADC 1 is powered by the: A. AC Essential Bus B.*-* AC Emergency Bus C. A C B u s 2 D. AC Bus 1

5 . If an ADC fails: A. ADS and FLAG INST lights on MWP illuminate B. SSG sounds C. Related instrument flags are displayed Da - All of the above

6. The ADS TEST switches can be used to test the systems: A. Inflight B. Inflight or on the ground CF-- Only on the ground D. Only with the engines operating

Revised: 11/17/92 [REF: TP4389.2171

Airbus Service Company, Inc., / Training Center (Miarni, Florida) a

7. Attitude information is supplied by: A. 3INSs B. 2 ONSs C. 3 I N S s a n d I H A S D.-- 2 TNSs and 1 HAS

8. The HAS operates to supply attitude and heading in case an INS fails: A z a True B. False

9. TAT gets its information from ADC 2: 2- A. True B = False

10. STALL WARNING SYSTEM will warn the pilot of an excessive angle of attack by: 1 1

z A. Horn and light on MWP B. Cricket Aural Warning - +z C. Stick Shaker on control column -

Da.-+ Both B and C

11. To recover lost flight instruments on the Captain's panel, the transfer SW. should be moved LEFT: k f True B. False

12. The AD1 G FLAG will be in view if the proper ILS frequency is not selected: -

A. True F,;~~ ; .= -

.? 2 F*-* ,s. p -.:am.-* -~, *,-- -- , ** . -- i = -8- .- &.-y=r.- - ..s",,.i- $:rpz, .%*7L3 -?.2*: P i --:<- ~. s .-7 -+ .-- -, -

B.? False .. -*, . C - j-

-.-., ii ii-

# .T . -5 'T- - l i

13. The HSI glideslope index is out of view if: A. The red GS flag is displayed BP' The ILS freq. is not selected C. ILS is in BB mode

I D. Any of the above /'

J .

Revised: 11/17/92 44 of 73 [REF: TP-0389.2171

Airbus Service Company, Inc., / Training Center (kliani, Florida) 1 L

14. The Flight Recorder will start to record when: A. - One engine oil pressure is normal or CM3 turns on FLT RCDR SW B. Ignition is energized C. A/C starts to taxi D. T . 0 power is set > 97%

15. The vertical speed indicator will indicate: A. - 100 to +6,000 ft/min X i

- 3 B: Oto6,000ft/min a;",

C. -1,000 to 4,000 ft/rnin D. -500 to 6,000 ftfmin

6 Set VMOIMMO switches above 153T (approximately 333.6000#) to (M. 0.82): A; True B. False

F e

17. The amber autothrottle speed index is set to - -=<for T.0: A. VR B. V1 -

C:. V2 D. Automatically

18. A black flag on the altimeter indicates: A Below sea level B. Negative altitude C. ADC fadure D .' Below alert height

19. A blue light ON the FLT RCDR indicates the system has failed: A. True B..- False

20. The AD1 red A?T light will illuminate: A. If ADIs differ by more than 4.5" B. If ADIs differ by more than 3.5: C. When test is pressed +>

Dr- Both B and C

Revised: 1 1/17/92 45 of 73 [REF: TP-0389.2171

Airbus Service Company, lac., / Training C e n t ~ r (itIiami, Florida) 3

2 1. To erase the CVR with parking brake on, hold ERASE for: A. 3 seconds B. 5 seconds C . 7 seconds D. 10 seconds

22. The standby horizon is powered by the: A. DC Normal Bus B. AC ESS Bus C: ' DC ESS Bus D. AC EMERG Bus

Revised: 1 1/17/92

Airbus Sentice Company, Inc., / Training Center (Miami, Rorida)

1. Fuel is stored in two tanks in each wing and one center tank: A. True 3. False

2. Normal tank capacity (6.7 lblgal) is about: A. 102,7001bs B. - 104,700 lbs C. 107,700 lbs D. 109,700 lbs

3. A jettison system will jettison fuel from which tanks? A. 1, 2, 1A and 2A B. lA, center and 2A C ts 1, center and 2 D. lA, 1 and center

~=- - & = " c : - y . '

4. ~ormal'fuel feed is outboards, inner, then center tank fuel A. 5 True B . & it. False

5 . With fuel in all tanks and al l pumps on, the MAX jettison rate is: A. 900 lblmin B. 1,000 Ib/min C. - 1,0501blmin D.3- 1,400 lb/min

-

6. How many fuel pumps are in each tank? A. One (1) B.3- Two(2) C. Three (3) D. Four (4)

7. All fuel pumps operate with different pressures to permit proper sequencing of tank operation: A. True B3-4 False

47 of 73 [REF: TP-0389.2171 Revised: 11/17/92

Airbus Service Company, Inc., / Training Center (itfiami, Ho&) 3

8. Center tank pumps will not shut off automatically when the center tank is empty: A. True B.- False

9. During an engine failure, fuel may be transferred from the opposite wing via the fuel crossfeed line: A; - True B. False

10. The fuel reserve light illuminates when the fuel remaining is about: A,".* 900kg or 2,0001bs B. 450kg or 1,0001bs C. 700kg or 1,5001bs D. 1,100kg or 2,5001bs

&MFK 11. with$urnp sw ON or AUTO, low pressure is indicated on the INDICATOR "OFF1' light

by: A. PUMP PRESS LO LT B. PUMP PRESS MI amber C. FUEL LT on MWP with SSG DILL--* All of the above

12. The FUEL JE'ITISON panel PRIMARY and SECONDARY switches control: A. Jettison pumps in each tank B-:.#* Primary and secondary motors of the jettison valves C. The crossfeed valves D. None of the above

13. Maximum fuel pressure for refueling is 50psi: A?' True B. False

14. FUEL USED indicators show fuel used by each engine and also the APU: A,-. True

i B. False .i

Revised: 11/17/92

Airbus Service Company, Inc., 1 Training Center (itIiami, Florida) 4 1

k SYSTEM - Cont'd

15. With the Center Tank Pump Switch ON, the TOTAL W and TOTAL FUEL indicator will illuminate when: A. Indicator fails B. - ZFW knob is pulled out C. ZFW knob is pushed in D. CG out of limits

16. TANK-TO-ENGINE fuel feel is used: A. Start, taxi, takeoff B. Takeoff C: Start, taxi, takeoff, approach, go-around, landing D. After takeoff

17. Fuel pump pressure with engines not running is: A. 20psi (all pumps) B. 20psi (1, 2, center) C. 4@si (all pumps) D: 20psi (lA, 2A), 40psi (1, 2, center)

Revised: 11/17/92

Airbzs Service Company, Inc., / Training Center (Miami, Florida)

HYDWAmIC POWER

1. Hydraulic power is required for: A. All Flight Controls B. AP, Yaw Damper and Cargo Doors. C. Gear, Brakes, and Nose Wheel Steering D AU of the above.

Hydraulic pressure is provided by three systems: A. Orange, blue, yellow Be:-* Blue, green, yellow C. Blue, orange, green D. Orange, green, yellow

System pressure is normally: A. 2,500 psi B. 2,800psi C: 3,000 psi D. 3,500 psi

How many EDPs are on each engine? A. One (1) B;-. Two (2) C. Three (3) D. Four (4)

5. To prevent cavitation, hydraulic tanks are pressurized by: A. Engine 2 B. - Engine 1 or Pneumatic System C. Engine 2 or Pneumatic System D. An accumulator pump

6. PTUs will transfer fluid from the green system to the blue or yellow: . A. True B . False

Revised: 1 1/17/92


7 . Which system can be powered by the RAT? . A. Blue

B Green C.. - Yellow D. None of the systems

8. Supply off shut off valves close and shut off fluid to the EDP: A. Automatically - p - B.: When ENG PUMP SW or fire handle is activated C. Only by fire handle D. Only by ENG PUMPS SW.

9. Hyd. LEVEL LO light indicates quantity is: A. Below outer green arc B. Above outer green arc - ,- C. At or below red dot, below 5 liters -; "- - - D. Below 2 quarts in system

10. The electric pumps produce 500 psi less pressure than the EDPs: A. True B . - False

11. The blue system can be pressurized by: A. Left EDP on Engine 2 B. Right EDP on Engine 1 C: - Left EDP on Engine 1 and PTU D. An electric pump

12. The accumulator electric pump can be used to: A. Pressurize parking and emergency brakes B. Open the cargo doors C. Pressurize yellow system on the ground D: Both A and B

13. Yellow system elec. pumps x e used for ground operation or inflight in case of EDP failure: A. True B. False

Revised: 11117192 51 of 73

Airbus Service Company, Inc., / Training Center (Miami, F7orida)

HYDRAULIC POWER - Cont'd

14. The RAT is deployed: A. Automatically when yellow system fails B. by Dual generator failure C. Manually with RAT handle on center pedestal D Manually with RAT handle on pilot's side consoles.

15. RAT will pressurize yellow system above: A. 120 knots B -130 knots C. 140 knots D. 150 knots

~ 16. Both PTUs can be used at the same time: A. True B . False

A. One (1) B. Two(2) C. Three (3) DL Four (4)

18. Does Hydraulic fluid ever flow from one system to other? A. Yes B.: No

19. The four engine pumps maintain 3,000 Ibs of system pressure while the electric pumps only hold 2,500 psi: A. True B.-- False

20. Hydraulic pumps switches, when moved to DUMP position, will continue to lubricate the pump and prolong the life of the pump:

%

-srr A: True B. False


21. Yellow system should be used to pump up the pressure in the accumulator. This pressure should be: A. 2,000psi B. 2,500 psi CP. 3,OOOpsi D. 3,500 psi

22. Priority valves will supply power to the following systems even if the hydraulic pressure drops below 1,885 psi: A. Flight controls and spoilers B. Normal and emergency brakes C . Autopilot and stabilizer D; All of the above

[REF TP-0389 2171

- - - - - --


ICE AND RAIN PROTECTION

1. Ice protection is accomplished by using: A. Pneumatic air (hot air) B. Hydraulics C. Electric D.;- BothAandC

2. Electrical heating protects the following systems except: A. Windshields B. Pilot and static ports Ci Leading edge of wings D. WasteIWater drains

3. Wing de-ice protection is supplied from: A. Electric system B. ~ ~ d r a u l i c system Ct- Air bleed system '

D. Fuel system

4. The wing DE-ICE VALVES DISAGREE LT will come on with the following conditions, , except:

A. During valve transit B. Valve disagree with control position CS - When the OAT is below 8 "C D i When fire handle is pulled

5. Wing RHILH Supply switches normally operate VALVE NQ

l: A;i; True B. False

6. Nacelle anti-ice get its hot air from the 10th stage of the engine compressor: As True B .- False

Revised: 11/17/92


ICE AND RAIN PROTECTION - Cont'd

7. Window heat is provided by electric power and has one heating level in flight and two levels on the ground: A. True BS " False

8. TRANSF rotary selectors should always be moved toward the f d e d system of windshield heating : A: " True B. False

9. FAULT LT comes on when (WINDSHIELD or window heat): A. Control unit power fails B. Temp. sensor fails C. Control sw. is off D: " *- All of the above

10. When turning on probe heat (CM3), only the TAT cannot be heated on the ground: A:' '* True B. False

11. LAVIGalley water waste drains are electrically heated when the LAVIGalley SW. is placed on: A. True B. False

12. Rain repellent should not be used as a windshield washer: A. True B. False

Revised: 11/17/92 [REF: TP-0389.2171

~ Airbus Service Company, Inc., / Training Center (Miami, Florida)

i

LANDING GEAR

Landing gear is operated by (normally): A. Electrically controlled, pneumatically operated B. Manual control, hydraulic operated C . Hydraulic controlled, electrically operated D- Electrically controlled, hydraulically operated

Moving the gear handle to NEUTRAL position removes the hydraulic power from the system: z A r -- True B. False

The gear handle can normally be moved to the UP position on the ground: A. True B: . False

= L

4. In the air the LEVER LOCK SW. will override all safety features and allow the gear to be retracted: A: True B. False

5. How many turns on the crank are required to lower the gear by GRAVITY extension? A. Three (3) B. Ten (10) C. -- Twenty (20) D. Twenty-five (25)

6. Slats, flaps and throttle position will activate a horn and red warning light if the handle is down and the gear is not down and locked: A . True B. False

7. Two separate sets of brake pistons provide power for the brakes on the main landing gear powered from: A. Alternate (gravity) from the yellow system B. Parking brake from Yellow system C. Normal Brakes from Green system D. All of the above

Revised: 1 1/17/92 56 of 73 [REF: TP-0389.2171

-


LANDING GEAR - Cont'd

8. The four braking capacities using hydraulic pressure are NORMAL, ALTERNATE -%' EMERGENCY and PARKING BRAKE. <..gp i-

L

A . True B. False

@ P r :4 ' -'

i &? w- 9. ALTERNATE braking will have no ANTI-SKID protection:

A. True B False

10. Brakes are applied after takeoff using the following system: A. Nose gear by rubbing pads.- B. Nose gear by hydraulics. C. Main gear by electric/hydraulic actuation - DP? Both A and C

" $x~*>%:* *' rU

11. Autobrakes are available with: AH Normal B. Alternate C. Emergency D. Parking Brake

12. ANTI-SKID, will not provide: A. Touchdown protection B j;- TireIBrakes overheat protection C. Locked wheel protection D. Tire wear protection

13. The ANTI-SKID system compares the nose wheel speed with the speed of the eight main gear wheels: A.. True B. False

14. AN "R" in the overhead ANTI-SKID panel indicates that the system has faded while braking upon landing : A. True B. False

Revised: 11/17/92

I

i Airbus Service Company, Inc., / Training Center (Miami, Florida)

EAWDH\;TG GEAR - Cont'd

15. Nose Wheel Steering is mechanically operated and hydraulically actuated from the cockpit: A. ' True B. False

16. Nose wheel steering will move the nose wheel a maximum of: A. Rudder pedals 3", handwheel 45" B. -. Rudder pedals 6", handwheel 65 " C. Rudder pedals 6", handwheel 75" D. Rudder pedals lo0 , handwheel 45 "

17. Moving the nose wheel handwheel will also move the rudder pedals: A. True B:. False

18. A visual check of the gear can be made to ensure that the gear is down by: A. Red pin on the upper wing slan for main gear B. Windows located in avionics compartment for nose gear C. Red pin in avionics compartment .- . D>- Both A a n d B

19. Will the green hydraulic pressure for the normal brakes or anti-skid be indicated on the brake pressure indicator? A. Yes B; No

20. Autobraking always begins upon touchdown with the autobrake selected to MIN or MED: A. True * ..

=

B: False

Revised: 11/17/92


NAWGAmON SYSTEM

1. Attitude information is supplied by: A. 2 ILS computers, 2 VOR receivers B. 2 COMPASS COUPLERS C. 1 INS and 2 HAS D 2 INS and 1 HAS

2. MAG. HDG is supplied by two compass couplers getting information from one flex valve and the INS: A. True B - False

3. The two VIL INS NAV switches allow the pilot to select either mag heading (VOR/LOC) or true heading (INS) on his: A. VOWDME B. AD1 c HSI D. RADIO ALT

4. In the event of a COMPASS failure, the remaining compass can supply all heading instruments by means of a COMPASS selector: A$&+ True B. False

/ I -- c-- a

2-, <+z; s-- -.i,- k-

a

< - 5 . INS provide magnetic heading to the AIC systems:

6 W

A True B. False

6. Should the Captain's ATTITUDE FAIL, moving the ATTITUDE switch to the left will -

cause which component to supply attitude information? A. INS 2 -*- 'e

B"- HAS f*.;d_;?$'_ 2- ,1-5 . -

C. VOR1 D. ADF1

Revised: 11/17/92

~ Airbus Service Company, Ine., 1 Daining Center (Miami, Florida)

NAVIGATION SYSTEM - Cont'd

7. In the event of a lure, switching 1 compass infohation to be supplied from the same system: A >$22:--T- True

B. False

8. In the event of an ADF failure, ADFIRMI pointers would: A. Remain in their present position B. Point 45" to the nose of the aircraft CW- Turn 90" to the right D. Turn 90" to the left

9. VOR-RMT course deviation and TOIFROM information wiU be displayed on the: - A * . AD1 B. VORIRMI IND C. COMPASS is^'^ HSI

10. In case of magnetic heading failure (all FLAGS in view), would the VOR magnetic BEARING still be valid?

Yes B. No

11. Moving the VORIILS switch to the right on the SWITCHING panel would put both pilots on the N

Q

1 VOR system: +

AZzdi" True B. False

12. OVRD position on the DME operates in a range of: A. 0-100 nm B. 0-150 nm C. 0-200 nm DW<& .+ 0-399 nm

13. The APIFD computers must be turned on in order to test the DMEs: A. True B .f /= False

Revised: 11/17/92 60 of 73 [REF: TP-0389.2171

I Airbus Service Company, Znc., / Training Center (Miami, Horida)

- >


pL7-=-;>*< -4 -* 14. The A300 has only qne-madce? receiver and two sets of indicators:

A;-" True

B. False

I

15. MARKER LIGHTS are dimmed by turning the instrument lights down: I

1 A. True Be:-" False

16. RADIO ALTIMETERS will indicate from: A.

* -500 to +2,500 ft

B,", 0 to +2,500 ft C. 0 to -5,000 ft D. -1,000 to +5,000 ft

17. On the RADIO ALT, a BLUE TAPE indicates a system failure, while a BLACK TAPE m a s that the indicator has failed, but AFCS data is still available: A. True B . 'False

18. On WEATHER RADAR on a digital radar scope, the most intense precipitation would be shown in which color? A. Black B. Green C. , e Yellow D;-- Red

19. Antennae tilt can be moved on the WX RADAR from: A. 5" up to 10" down B. 10" up to 10' down c .:.* - 15" up to 15" down

D. 20" up to 20' down

20. During TEST on the WX RADAR, the bands of colors seen on scope from the center of the scope wiU be: A. Yellow, green, red B. Blue, black, red c,*-= " Red, then green, then yellow D.+ - G r e n , then yellow, then red

Revised: 11/17/92 6 1 of 73 [REF: TP-0389,2171

I Airbus Service Company, Inc., / Training Center (Miami, Florida)

~


21. How many modes of operation does the GPWS activate? A. Two(2) B. Three (3) C. Four (4) DZ-* " Five ( 5 )

22. The FLAP OVRD switch is provided on the AIC to inhibit mode 4 (Approach to terrain with Flaps/LG ~ - not in Landing Configuration): - A"- -7' True B. False

23. The INS on the A/C provide the following information in the NAV mode: A. Pitch and Roll Attitude B. MAG and true heading C. Nav, dab and a steering signal to AFCS A

D.Z*+,.~* All of the above

24. In ATT mode, what information will the INS provide? A. Pitch and Roll Attitude B. Magnetic Heading C. Navigation data D$ -*'- A and B of the above

25. The HAS provides what information in case one INS fails? A. Pitch and Roll Attitude B. Navigation data C. Platform heading Df - A and C of the above

26. The Pilots will receive TRUE heading when operating in the INS NAV position: True

B. False

27. A green light on the MSU indicates that the INS has automatically shut down: A. True

i.

B: Fdse

Revised: 11/17/92 62 of 73 [REF: TP-0389.2171

Airbus Service Company, k c . , / Training Center (Miami, Florida)

28. INS NAVIGATION can only be accomplished in the following position: A. STBY B. ALIGN C. ATT D," NAV

29. On the INS CDU, the HOLD KEY will: A. Put the A/C into a holding pattern B . ~ T ' Freeze the present data display C. Withhold information to the HSI D. Eliminate the next waypoint

30. The REMOTE KEY may be used to insert present position into POS when leaving an airport: A. True B:--- False

3 1. The ALERT LT comes on steady two minutes before reaching a waypoint: A?: '. True B. False

Revised: 1 1/17/92


1. Pneumatic System supplies air to all systems below except: A. Air Conditioning and Pressurization B. Wing anti-ice C. Engine start and reverse D : ' Windshield heat

2. Compressed air is obtained from all sources below except: A. Main engine bleeds B.- RAT C. M U D. Ground HP air

- *r -y-&- Fa*- $?-q --*--r-

" Ypdi= e : - a- . - '= *. -

3. Anti-icing for the engine air intake comes from the 14th stage compressor of Engine 1: A. True B ~ " * False

4. The crossfeed duet pressurizes the green hydraulic tyks: A .&i-'' True B. False

5 . If IP (intermediate pressure) is not sufficient to meet demands, the HP (high pressure) bleed valve opens to allow more pressure into the system: A? -@ * True B. False

6. The HP bleed valve maintains a constant pressure of: A.- 25 psi J3 ,$&A+- 36 psi

C. 46 psi D. 50 psi

7. With TEMP HI LT and PNEU LT on MWP, bleed valve will automatically close: A<"/+ % . e True B. False

Revised: 11/17/92 [REF: TP-0389.2171

I 1 i Airbus Service Company, Znc., / Training Center (Miami, Rorida)

PWEWTHCS - Conzt'd

8. The CROSS (X BLEED VALVE) bleed valve is controlled by how many electrical motors when positioned? A. One (1)

i

B.- Two (2) C. Three (3) D. Four (4)

9. PNEU LT and XBLEED FAULT LT comes on when valve position disagrees with the manual or selected position: A;" --" True

B. False

10. TEMP HI LT will automatically close the BLEED VALVE when it comes on amber: A"" " True

B. False

11. REGUL FAULT LT will automatically close the BLEED VALVE when it comes on amber: A. True B_:- False

12. The following three things occur when the APU BLEED selector switch is moved to

B. Engine bleed valves clos C. XBleed valves open D. APU N1 increases

13. How many loops protect the PYLON and APU ducts against overheat? A 5,- I. one ("j -=

B. Two(2) C. Three (3) D. Four (4)

Revised: 11/17/92

Airbus Service Company, Inc., / Training Center (Miami, Florida) . -

PNEUMATICS - Cont'd

14. How many OVERHEAT loops protect the center fuselage and in each wing? A. 1 B.5:- *2 C. 3 D. 4

15. When an OVERHEAT condition is detected in a manifold, the following occurs except: Q---

A. MANIFOLD LT illuminates on AIR BLEED VALVE B. PNEU LT on MWP and SSG C.g- Valves must be manually closed D. Valves automatically close all concerned ducts

16. In case of a false warning, it will not be possible to override any closed valves: A. True B - False

17.. Loops may be tested by pressing associated MANIFOLD FAULT LT: A

ATw- ' True B. False

18. If an APU MANIFOLD LT and ENG 1 MANIFOLD LT come on at the same time, it would indicate: A. Duct from APU is l h g B. Duct in pylon is leaking Cb '^ BLEED AIR or ANTI-ICING duct in wing or CTR fuselage is leaking D. Duct from HP hot air is failed hot.

19. A ventilation system is provided to avoid over-heating near bleed air and anti-ice ducts in the leading edge and is controlled by a switch on the overhead panel: A. True

.+-

B . False

20. On the ground, air is supplied to the wing vents by and electric fan: A.? ' True B. False

Revised: 1 1/17/92 66 of 73 [REF: TP-03 89.2 171

Airbus Service Company, Inc., / Training Center (Miami, Hoiida) b-, < :

1. Thrust on the A300 engines is rated at: A. 56,500 lbs B. 46,500 lbs C. 48,500 lbs D: 52,500 lbs

2. Maximum N1 rotor speed is: A. 109.5% +F' ? =

B. 119% C. 115.5% D. 103.2%

3. Flight Idle increases the thrust about how many percent? A. 100% B. 200% c; " 300%' D. 400%

4. The high stage of the GE CF6-50 engines has a 14 stage compressor and 2 stage fans: A. True BL- False

5. The low pressure spool has a four stage turbine and a fan with a three stage booster: A : True B. False

6. Fuel is heated by passing it through: A. Hot air from the pneumatic air B. Ambient air from the anti-ice system C.' Fuel/oil heat exchanger D. Ducting through the cargo compartment

Revised: 11/17/92


BQWEIPPLmT - Cont'd

7. The engine control systems which powers and controls the stator vanes and variable bleed vanes are:

i A. Electric B. HydrauLic C. Mechanical Df - " Hydromechanical

- ?L

; 8. Flight and ground idle speeds are scheduled and controlled automatically by the landing gear position: A>+ True B. False

9. The fxe handle will mechanically close the low pressure fuel valves: A.z+/" True B. False

10. The basic control engine parameter is the: A. N2 B;- =* Nl C. EGT D. Fuel Flow

11. There are six modes for operating the N1 computer. They are T. O., FLEX, CLIMB, CRUISE, MAX CONTINUOUS, and GA: A:- -- True B. False

12. FLEX T.O. may be used when actual T.O. wt is lower than the max. permissible TOW for the actual temperature: A?- True B. False

13. The N1 LIM computer also has the following temp gauge: A. Actual OAT B. SAT

- TAT D. Flex Temp

Revised: 11/17/92

1 Airbus Service Company, Inc., / Training Center (Miami, Florida) - I ,

14. The engine start valve should close when the engine reaches: A. 45% N1 B. , 40% N1 C2" 45 % N2

D. 4 0 % N 2

15. When the ARM-START ABORT SW is moved to ARM, the airconditioning pack valves close: A, True B. False

16. In the CRANK mode, with the IGNITION SELECTOR SW, the ignition system is not energized : A $-" True B. False

17. Engine oil pressure either higher or lower than normal indications would be in which arc on the gauges? A. Red B. Blue c . yellow 1' D. Green

s A +- - + F 2 dX- 7-

18. Air bleed from the , - engine stage pneumatically operates the reversers: A. 4th stage B. 8th stage C. 10th stage D. 14th stage?:

19. Reverse levers can only be actuated when the throttles are in idle: A . l True B. False

20. Reverse levers should be returned to idle position by: A. 120 knots B. 130 knots C F . 60 knots

D. 80knots

Revised: 11/17/92

Airbus-Service Company, k c . , / Training Center (Miami, FloPida)

WATER WASTE SYSmM

1. It is safe to drink water from the lavatory wash basins and galley faucets: ,

A. True B. False

2. All excess water and waste water is released directly into the air through a waste drain mast during fight:

- True B. False

3. Air for pressurizing the water system is taken from the bleed air crossfeed line and may be pressurized either by the engines or APU: A:." True B. False

Revised: 11/17/92


1. Warning systems will always accomplish the following except: A. Indicate a system malfunction or a dangerous situation

I

B.:- Initiate shutdown of the defective system C. Identify the malfunctions clearly D. Direct the appropriate corrective action

2. Three types of warnings are given to the pilots of the A300, including: A:- All of the below B. Tactile C. Audio D. Visual

3. An example of TACTILE warning would be the stick shaker when approaching stall: A;.,. True B. False

4. Which of the following PBs or switches will not cancel the fire warning? A. FIRE BELL CANCEL PB

% = pee- B.-- GEAR HORN OFF PB *? "-- $- % - - C. AUDIO CANCEL PB D. EMERG AUDIO CANCEL SW

5. m c h switch or ,PB cancels all audio warnings? A. FIRE BELL CANCEL PB B. GEAR HORN OFF PB C. AUDIO CANCEL PB D;- EMERG AUDIO CANCEL SW

6. A impending stall will sound the: A. Clacker B.. Cricket C. Cavalry charge D. SSG

7. A continuous BELL always indicates an engine or APU fxe condition: A:- True B. False

Revised: 11/17/92 71 of 73 PSF: TP-0389.2171


-.

I WABNING SYSTEMS - Comt'd

8. A "CLICK, CLICK, CLICK" will indicate: I

A. Impending stall Bz*? ChangeinAFCScapability C. Change in GROUND PROX warnings D. Overspeed

9. A continuous buzzer would indicate: A. Overspeed B. Gear not down

Call from the cabin D. Altitude alert

- ->- & "-*-- --

a&-* '-" 7 -.-

10. A single stroke gong SSG indicates that any system has a system ~ E D warning: A. True B.+r False

11. Any horn will be associated with: A. Electrical failures or abnormalities B. Pneumatic problems C. Doors not in the proper position Dz- - Landing gear or configuration problems

12. Lights which may be dimmed by pressing the light will have a small "D" in the right hand comer: A.";i-- True B?-7 False

13. A "T" on a light indicates that the light may be pressed to check integrity in the circuit: A .2" True B. False

14. CABIN PRESS LT comes on M W , when cabin altitude reaches: A. 8,600feet B 9,200feet C. 10 ,500 feet D. 1 4 , 0 0 0 feet

Revised: 11/17/92 72 of 73

Airbus Service Company, Inc., / Training Center (Miomi, FloPida)

W G SYSTEMS - Csnt'd

15. SMOKE LT on MWP can be turned on by smoke in how many systems? A. TWO (2) -.- B. Three (3) C. Four (4) D. Five (5)

16. Horns always indicate fire problems while bells are associated with gear or flaps: A. True B. False

Revised: 11117192 [REF: TP-0389.2171

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