Learjet 60 study guide.

                   
                                               






                                                       LEARJET 60 STUDY GUIDE







The following is a study guide based on Bombardier's flight manual for the Learjet 60.
It should be used for training purposes only, and most importantly, all the information here contained should be verified with a Lear 60 instructor.

The purpose of this study guide is solely to serve as a quick reference to Lear 60 Crews that wish to review aircraft basic knowledge before an initial/recurrent training, or simply to keep this info fresh in their mind.


Having said this, I really hope this material helps, Please let me know if you have any suggestions, comments, etc....


Enjoy,

Luis E. Rojas

      

        

      Lear Jet 60 Study Guide

Specifications:

Minimum crew: 2

Passengers: Max. 8

Powerplants: 2Pratt&Whitney Canada PW305A @ 4,600 pounds of thrust each

Two engine rate of climb: 4,500 fpm @ 23,500 lbs, Sea level, standard temp.

Single engine rate of climb: 1,240 fpm at sea level, standard temp.

Speed: Maximum speed Mach 0.81/479 kts.

Service ceiling: 51,000 feet.

Fuel capacity: 7,900 lbs

Range: 2,400NM

Empty weight: 15,000 lbs

Max takeoff weight: 23,500 lbs

Wingspan: 43’10”

Length: 58’8”

Height: 14’7”

Questions and answers:

1.     Turn radius of Learjet 60 nose wheel:

60 degrees.

2.     Maximum weight external baggage compartment can hold:

300 Lbs.

3.     How many locking pins are there on the main entry doors:

12 pins.

4.     With a dual generator failure, and Emer bus selected. What do batteries power?

Battery buses, DC emergency buses, DC voltmeters, stby pitot tube, and hydraulic pump.
4.1 Main batt 1 hot wired items: -Tailcone inspection light.
                                                               -Toilet service receptacle.

       Main batt 2 hot wired items: -Cabin entry lights.

                                                                             -Cockpit dome lights in remote position and  

                                                                               entry lights on.

4.2 failure of a DC bus can be identified: L or R DC1: L or R N1 Ind.

                                                                              L or R DC2: L or R Fuel flow ind.
                                                                              L or R DC3: L or R oil ind.

5.     What items become inoperative during a complete AC power failure?

Mach trim, Nose wheel steering, Nose fan.

5.1 Left AC bus powers: -Mach trim.
                                               -Left windshield defog.

       Right AC bus powers: -Spoileron.
                                                 –Nose steering.
                                                 –Right windshield defog .
                                                 -Nose fan.

5.2 A blown current limiter can be identified by turning on recognition light, amps will rise on the good side, lower amps can be observed on the failed side.

6.     What items are automatically loadshed when a generator fails?

Air conditioner, Floor board heater, External baggage heater, cabin power bus.

7.     If only one main battery is connected, the EPM will indicate:

Battery voltage on DC voltmeter + flashing red light due to inverters being off.

8.     The minimum voltage required to connect the main battery to the system is:

16 Volts.

8.1 If battery voltage reads between 22 and 24 volts, GPU is required; If
       voltage drops below 22, battery has to be replaced.

9.     Indications of a failed generator:

Generator switch on.

Generator fail light.

EPM reads 0 amps.

Not being able to bring it back online.

10. Selecting BCN/STROBE on the ground activates:

Red flashers on the ground, and white flashers when airborne.

11. Which system runs a 30 sec. self test during the glareshield test?

The cabin smoke detector, and you should see a steady cabin fire light.

A flashing light indicates a real fire.

12. How can you reactivate a white annunciator light that was cancelled in flight?

Depressing the light glareshield test button will reactivate cancelled lights after 10 seconds.
12.1 Spoiler extended light is the only light that can be cancelled on the
         ground.

13. Which fuel pump automatically energizes when fuel level is low?

Scavenge pumps, which are also activated with glareshield tests.

14. Rapid fuselage fuel transfer to the wings is accomplished by:

Activating Normal + Aux transfer simultaneously.

15. Which fuel indication must be used for flight planning, range, and endurance?

The total fuel quantity reading on the ground.

16. Which switch controls the right side transfer system?

Aux transfer switch.
16.1 fuel quantity in wings must be below 1,200 lbs to transfer fuel from
         fuselage.

16.2 Low fuel press light activates below 2.75psi, and extinguishes at 3.75psi.

16.3 Normal transfer occurs at 50psi, rapid transfer at 100psi.

16.4 There are a total of 9 fuel probes in the system.

16.5 There must be at least 50 lbs of fuel in the left wing for density compensation to work.

16.6 At 410 lbs of fuel in each wing, low fuel indication activates, scavenge pump starts working.

16.7 For fill ops, press and hold fill button for 2 to 3 seconds.

16.8 Green fuel sys flashes when fuselage tank is either full or empty.

16.9 Fuel imbalance is detected through the 3 deg. Flap switch. Imb flashing indication can be cancelled with the mute button on RH thrust lever.

16.10   All fuel valves are DC, in case of electrical failure, they stay in last position.

16.11   Drain #7 is the lowest point in the fuel system.

16.12   If engine filter light illuminates during taxi, one of your 3 filters is clogged.

16.13   Stby. Fuel pump must come on when start is selected.

16.14   Normal transfer uses the high level flow switches, which shutoff the transfer leaving the xflo valve open until level in wing decreases and normal transfer resumes.

16.15   Aux transfer does not use high level flow switches, excessive fuel returns to fuselage tank

16.16   Fuselage transfer pumps work on emergency bus.

16.17   Jet pump off light will flash if stuck in intermediate position.

16.18   Squat swich in air mode cancels fill operation.

16.19   Unusable fuel qty. with no motive flow: 350 lbs.

17. To use both thrust reversers in single engine operations:

Move the failed engine lever from cutoff to idle, and deploy TR buckets, full range of reverse is only available on operating engine.

18. What power source needs to be available for oil pressure and oil temperature to function?

DC power

19. When is it possible to get a TR amber light but no warning horn?

When only the secondary latches fail.

20. What is the minimum speed at which max reverse thrust is available?

50 Knots.

21. How can you get maximum thrust?

Pushing both levers to the APR detent.

22. When will the APU automatically kick off?

When the aircraft goes weight off wheels.

23. How will a break in the loop affect the fire detection system in flight?

System will function normally.

24. What happens when a single T-handle is pulled?

Main fuel, hydraulic, and bleed air are closed, and both extinguishers are armed.

25. When does the left bleed light illuminate?

When temperature in the bleed air duct or pylon exceeds it’s predetermined limit.

26. If landing altitude is set at 2,500 feet, emergency pressurization will activate at: 9,500 ft.

27. When airplane is on the ground, air circulation will be provided by: Crew and cabin fans

28. Freon system is used only for ground ops. And must be off for takeoff and landing, or manual full cold.

29. A system that can be turned on by battery power is: cabin fans

30. At what altitude does cab alt warning horn sound?

: 10,100 ft. +- 250.

31. Which valves open at landing to dump residual cabin press?

: Both outflow valves.

32. Both bleed air lights illuminate simultaneously in flight when: tailcone temperature exceeds 255 degrees F.

  

33. A full Oxygen bottle is indicated by: 1,850 PSI.

34. If normal is selected on crew masks, automatic pressure breathing starts at: 37,000 ft.

35.  If start sequence is not initiated within 9 secs. Of pressing APU’s master switch: Fault light will illuminate on APU.

36. Both engines area of danger of intake extends to 35 ft of the intakes.

37. APU is started and there is a green light (Running) on APU control panel, if there is a 0 amp reading on GPU: It means APU is still running.

38. Max transient temperature for takeoff: 825 degrees for 20 seconds.

39. Maximum continuous ITT: 785 Degrees.

40. Minimum permitted ground idle N2 is: 52% (or EEC will power from batteries)

41. Max continuous gen am limit from 46,000 to 51,000 ft.

42. Immediate engine airstart may be attempted before N2 drops below 25%.

43. Which item is operative during Emer Batt operation on all aircraft?

: Landing gear indicator lights.

44. When performing an aborted takeoff:
        -Brakes apply.
        -Power to idle.

        -Spoilers extend.

45. If cabin fire lights illuminate, what is the first immediate action required:

Crew masks on.

46. Use a started assisted airstart when: n2 is less than 7%.

           

              47. During dual generator fail approach the Emer bus switch is returned to 

                     normal to regain: antiskid.

48. Which is not a memory item for aborted takeoff: Thrust reversers.

49. Which items are heated by bleed air?

:Nac heat, Engine interstater vanes and spinner.

50. After selecting nac heat, proper indication is: Illuminated green nac  

Heat.

51. During aircraft electrical failure with emmer batts functioning, which antiice continue working?
: Nac heat, Interstater heat(Between fan and high press compressor), and spinner.

          

             52. In the event of a hydraulic system failure inflight:
                     Refer to hydraulic system failure checklist.

             53. If DC power is applied to airplane, and residual hydraulic press is 1,300
                    PSI: Aux hydraulic pump will not operate until pressure drops below
                    1,000 PSI.

             54. Which subsystems cannot be operated with aux hydraulic pump?
                    : Spoilers and Thrust reversers.

             55. Three gear unsafe lights illuminate and gear warning horn when:
                     60%N1, 170 Kias, and alt below 16,300 ft.

  

             56. If a green gear down light is inop. Gear down can be confirmed by:
                    illumination of corresponding landing light.

             57. Gear warning horn sounds without gear indications when: Gear is up, and
                    flaps go below 25 degrees.

            58. Maximum certified weight: 19,500 Lbs.

59. Max allowable Vfe:

                   8 degrees: 250 kias.
                   20 degrees: 200 kias.
                   40 degrees: 165 kias.

60. Do not exceed maximum fuel truck pressure of: 60 PSI.

61. Minimum truck delivery pressure necessary for single point refueling: 20
       PSI.

62. when DC power is applied to aircraft, each AHS performs a self test that
       lasts: 70 secs.

63. SDU is a repeater of AHS 1, so if AHS 1 fails, SDU fails.

64. Only one yaw damper is installed, and aircraft can be dispatched with yaw
       damper inop.

65. If PFD is transferred to MFD, Nav or Approach mode has to be reengaged
       since it defaults to heading mode during transfer.

66. With loss of heading input, on SDU, the display will: display a green heading in a box with an X through it.

67. Which radios are available during emmer batt operation?
        : All Number one radios only.

68. What happens if both pilots select AHS Xside at the same time?

        : Pilot’s side will get cross side, copilot’s side will not.

69. Brightness of RTU’s & SDU display is controlled by: individual dim control
       knobs in upper left or right corners of units.

70. Rtu1 failure: RTU1 has to be turned off.

71. How does an AHS failure affect yaw damper and autopilot?
       : They will be inop until AHS is restored.

72. Both ADC’s have to be operative for departure.

73. SDU heading information comes from: Left AHS.

           
            74. Selecting ADC cross side on Efis control panel changes PFD and MFD
                  information to the other side’s.

       

75. With all RTU systems activated normally, it is possible to:
       Turn off RTU by selecting RTU off on the Efis control panel which allows
       you to use opposite RTU ½ button to change frequencies in both crew
       positions.

76. Failure of AHS is indicated by: Boxed red ATT & MAG flags.

77. A letter M in a square on the FMS screen, means a menu is available.

78. FPL – Menu – Pge2 – Approach plan – Pge2: Gives vertical info for GPS
       approach.

79. Turning off all DC power with FMS’ on: Allows pilot to recover FMS
       functions within 7 minutes.

80. With GPS in highlighted area, press enter key to enter a GPS position.

81. Last step of the Airstart checklist reads Fms Initialize:
       :Go to last fuel page function and reset fuel flow on the re-started engine.

82. To activate a manually entered holding pattern in FMS which is not in the
       database, press DTO hold.

83. FMS cannot be used in dead reckoning mode

84. If either stall warning system is inoperative, airplane must not be flown.

85. In the event of a runaway trim, trim selector must be disabled by:
       Moving the trim selector to off.

86. An illuminated amber spoiler monitor light indicates:

       A spoiler or spoileron malfunction.

87. Maximum permitted operating airspeed with mach trim inop & autopilot
       disengaged: .77 mach.

88. Minimum altitude allowable for using autopilot on an approach: 200 ft.

89. Sensor display unit may be inop if:

       Both MFD’s are operative, and magnetic compass is operative.

90. If a component is inoperative prior to departure and item is not on MEL:
       If item is not on MEL, it has to be operating. Aircraft can only be
       dispatched after maintenance has corrected malfunction.

91. If both manual and automatic pressurization are inop, aircraft can be
       flown unpressurized at or below 9,000.

92. According to the Aircraft manual, the only authorized use of APR with both
       engines running is: During a windshear encounter.

93. On the Learjet 60, the second segment climb gradient required must be
       2.4% with one engine inoperative.

94. If max brake energy landing weight is exceeded during landing by using

       maximum effort braking, it is required to perform: High energy stop

       inspection.

95. A rolling take off requires: adding 300 ft of runway to take off field length.

96. Criteria that limit max allowable take off weight: Climb or brake energy
       requirements.

97. Flaps setting in the approach climb phase must be 8 degrees to meet test

       data.

98. Hydraulic system failure resulting in loss of flaps, spoilers, Reversers:
       Multiply landing distance X 3

Notes.

-       Starter turns into generator at 45% N2.

-       APR adds a max of 11% power to the operating engine, maximum of 4,600lbs.)

-       If Engine computer white light illuminates, it indicates a minor problem in one or both channels, most likely a software problem.

-       Amber engine computer light indicates a more serious problem.

-       Amber + White light indicate a problem on both computer channels.

-       Fadec is composed by: TLS+EEC+HFCU.

-       Each engine contains 24 fuel nozzles.

-       If engine cannot be cutoff with Thrust lever, use T-Handle, it will use the backup overspeed solenoid.

-       As a safety feature engine will shut down at 110% N1 or N2.

-       Engine chip light + Engine filter light indicate that oil filters are clogged.

-       To check oil, wait 10 minutes after engine shutdown.

-       Maximum reverse available with ADC’s inop is 65% N1.

-        A TR unlock amber light but no engine rollback indicates a secondary latch failure.

-       APU requires  100 lbs of fuel on the left wing.

-       APU has a fire bell alarm.

-       APU will shut down after bell has rang for 15 seconds.

-       Above 255 degrees F both bleed air lights will illuminate

-       A dual bleed air light illumination could be the indication of a fire in the tailcone area.

-       Emergency pressurization valves require electrical power.

-       Bleed shutoff valve depowers to on position.

-       Emergency bleed valves work with low pressure air (300 deg. F).

-       With both emergency valves open, windshield and wing antiice are not available.

-       Automatic emergency pressurization turns on at 8,300 ft.

-       Pulling either emer bleed valve CB when both valves are open will enable antiice.

-       Oxygen mask between FL300-FL370 use diluted oxygen.

-       Oxygen masks above FL370 use 100% O2.

-       Formula to compute the right cabin altitude: (altitude-3000)/6.

-       Hydraulic reservoir capacity 4 ½ - 5 gals.

-       Metal ball in the middle of reservoirs sight glass indicates wrong kind of hyd. Fluid is being used.

-       Gear and brake air nitrogen bottles are located on the airplane’s nose.

-       Hydraulic fluid moves to pumps via shutoff valves controlled by T-handles.

-       Engine driven hydraulic pumps pump 10GPH

-       Aux hydraulic pump pumps 1gph (limit 3 mins on 20 mins off)

-       There is no indication for engine driven hydraulic pump failure.

-       Hydraulic pressure light illuminates below 150psi.

-       Dual hydr. Pressure light illumination indicates a dual engine driven pump failure.

-       Minimum nitrogen precharge: 750 psi.

-       With antiskid inop. Max takeoff weight is 18,500lbs.

-       If the steering armed light extinguishes, press and hold MSW button to gain 25 degree steering.

-       Steering armed light also indicates nose gear is down.

-       If 2 of the 3 speed sensors are lost steering will disconnect.

-       When landing without antiskid, double landing distance.

-       Efis rheostat on pilot’s light panel dims PFD and MFD simultaneously.

-       Half bank activates automatically above FL410.

-       Six items that activate Takeoff warning horn:
1. Flaps not set for takeoff.

2. spoilers not retracted.

3. Pitch trim not in takeoff position.

4. Reversers deployed or unlocked.

5. Parking brake not released.

6.Parking brake light blown.

-Pressurization protection and warning feature schedule landing at 8,000 ft
  or less.

8,600 ft+-250: -Pressurization control automatically reverts to manual mode.
                             -PRESS SYS annunciator illuminates.

                             -Fault annunciator illuminates.

8,750ft+-250: - If MANUAL has been previously selected on the pressurization
                              control panel, the PRESS SYS annunciator illuminates.

9,500ft+-250: -Emergency pressurization(automatic) is activated, directing
                              bleed air directly into the cabin.

                            -Emer press annunciator illuminates.

10,100ft+-250: -Cabin altitude warning sounds.
                              *Initiate emergency descent.

                              *Mute horn with mute switch.

                              -Cabin alt HI light will illuminate.

13,700ft+-500: -Cabin altitude limiters close outflow valves.

14,500ft+-250: -Passenger oxygen masks deploy.

                              -Cabin overhead panel lights illuminate

-Pressurization protection and warning feature schedule landing above
  8,000 ft.

-Prerequisites:

1)In automatic mode on controller.

2)Destination landing altitude set above 8,000 feet.

3)Aircraft has descended 1,000 feet.

4)Aircraft is below 25,000 feet.

13,700ft+-500: -Cabin altitude limiters close outflow valves.

14,500+-250:  -Passenger oxygen masks deploy.

                            -Cabin overhead panel lights illuminate.

                            -Cabin altitude warning sounds.

                            -Emergency pressurization activates.

                            -EMER PRESS annunciator illuminates.

                            -Fault annunciator illuminates.

                            -Pressurization control reverts to manual mode.

                            -PRESS SYS annunciator illuminates.

    

LIMITATIONS

1.     Icing conditions exist when outside air temperature (OAT) o the ground and for takeoff is 10 degrees C (50F) or below, or the static air temprerature (SAT) in flight 10C(50F) to -40, and visible moisture in any form is present (such as clouds, fog with visibility of one mile or less, rain, snow, sleet or ice crystals).

2.     Icing conditions also exist when the OAT on the ground and for takeoff is 10C(50F) or below when operating on ramps, taxiways or runways where surface snow, ice, standing water, or slush may be ingested by the engines, or freeze on engines, nacelles or engine sensor probes.

3.     Maximum ramp weight (optional): 23,750 lbs/10,773 kg

4.     Maximum certified takeoff weight: 23,500 lbs/10,660 kg

5.     Maximum zero fuel weight: 17,000 lbs/7,711 kg

6.     Maximum allowable takeoff weight with anti-skid protection for any wheel inoperative is: 18,500lbs/8,391 kg       

7.     Maximum certified landing weight: 19,500lbs/8,845 kg   

8.     WARNING Do not extend spoilers, or operate with spoilers deployed, at speeds above Vmo/Mmo due to significant nose-down pitching moment associated with spoiler deployment.

9.     MAXIMUM OPERATING SPEED Vmo/Mmo primary instruments:
-26,750 to 37,000 feet……0.81 MI
-With mach trim inoperative and
  Autopilot disengaged……0.77 MI

10. Maximum landing gear operating speed Vlo: 200 KIAS

11. Maximum landing gear extended speed Vle: 260 KIAS

12. Maximum flap extended speed Vfe:
-Flaps 8……250 KIAS
-Flaps 20……200 KIAS
-Flaps 40……165 KIAS

13. Minimum control speed air Vmca
Flaps 8……120 KIAS
flaps 20……110 KIAS

14. Minimum control speed ground Vmcg
-Rudder boost ON……95 KIAS
-Rudder boost OFF……116 KIAS

15. Takeoff limits:
-Tailwind component……10KTS
-Runway conditions:
  *Takeoff is limited to paved runways.
  *Runway water/slush accumulation ¾ inch (19mm)
  *Fuel load…Wings balanced within 200 lbs (91kg)

16. Enroute limits:
-Maximum pressure altitude: 51,000 ft.
-Fuel load: Wings balanced within 500 lbs (227 kg)        

17. Landing limits:
-Tailwind component: 10 KTS.
-Runway conditions:
 *Runway water/slush accumulation: ¾ inch (19mm)
 *Fuel load: Wings balanced within 200 lbs (91kg)

18. Limit maneuvering load factors:
-Flaps up……+3.0 g to -1.0 g
-Flaps down……+2.0 g to 0.0 g

19. Maneuvers:
-No aerobatic maneuvers, including spins are approved.
-Intentional stalls are prohibited above 18,000 ft with flaps and/or landing
 gear extended.

20. Turn-around limits:
If the turn-around weight limit for brake energy, as determined from the applicable LANDING WEIGHT LIMIT chart in section V, is exceeded during a landing or rejected takeoff, the following limitations must be observed:
-The aircraft must be parked for a minimum waiting period of 20 minutes
  before the next takeoff attempt can be made.  
-After the waiting period is observed, a visual inspection of the main gear tires, wheels and brakes for condition must be made.

21. Nacelle heat must be on during descent into visible moisture even if SAT is below -40C(-40F).
-CAUTION: To reduce the probability of engine damage, select NAC HEAT   
  “ON” at least two minutes prior to entering icing conditions(either in flight
  or prior to taxi).

22. Nacelle heat ground operations:
-Do not operate nacelle heat system for more than 5 seconds when the
 associated engine is not running.                   
-Do not operate nacelle heat system for more than 30 seconds when static air
 temperature is above 15C(59F).
-Except for takeoff, do not operate nacelle heat system when engine RPM is
 greater than 65% N1.

23. Air data system:
-Both air data systems (ADC1 and 2 ) must be operative and the onside system selected (I.E., ADC 1 for pilot’s side and ADC 2 for copilot’s side) for takeoff.

24. Attitude heading reference system (AHS)
The onside attitude heading system must be selected(I.E., AHS 1 for pilot’s side and AHS 2 for copilot’s side) and the comparators must be extinguished for takeoff.

25. Autopilot/Flight director:
-Operation of the autopilot with the red trim fail light illuminated is
 prohibited.    

-Do not intentionally overpower the autopilot.
-The minimum altitude for use of the autopilot is:
 *Approach configuration: 200 ft AGL.
 *En route configuration: 1,000 ft AGL.

26. Electronic flight instrument system (EFIS):
       A minimum of three large flight displays must be operational for takeoff and
       the following conditions must be satisfied:
       *Each outboard PDF display must be operational.
       *At least one inboard display must be operational.
       *The standby attitude indicator must be operational for takeoff.

27. Flight Management System:
       The minimum altitude for autopilot coupled VNAV operation is 400 feet AGL
        or minimum descent altitude (MDA), whichever is higher.

28. Engine System Limits:
       -Power setting APR or T/O:
       *Time limit: 5 Mins.
       *N1%: 102.
       *Max ITT C: 785.
       *N2%: 102
       *Oil Press PSI: 36 to 80
       *Oil Temp C: 10 to 135

29. Engine system limits:
       -Power setting MCT or MCR:
       *Time limit: Continuous.
       *N1%: 102.
       *Max ITT C: 785.
       *N2%: 102
       *Oil Press PSI: 36 to 80
       *Oil Temp C: 10 to 135

30. Engine system limits:
       -Power setting GOUND IDLE:

       *Time limit: Continuous.
       *N1%: -.
       *Max ITT C: N/A.
       *N2%: 52
       *Oil Press PSI: 20 to 80
       *Oil Temp C: 10 to 135

31. Engine system limits:
       -Power setting FLIGHT IDLE:

       *Time limit: Continuous.
       *N1%: -.
       *Max ITT C: N/A.
       *N2%: 65
       *Oil Press PSI: 20 to 80
       *Oil Temp C: 10 to 135

32. Engine system limits:
       -Power setting STARTING:

       *Time limit:
       *N1%: -
       *Max ITT C: 950.
       *N2%: -
       *Oil Press PSI: 20 to 220
       *Oil Temp C: -40

33. Engine system limits:
       -Engine synchronizer must be off for takeoff, landing and single engine
        operation.
       -External power: The maximum amperage from an external power source
        must be limited to 1,500 amps (500 amps[minimum]).
34. Engine system limits:
       -Ground operations:
       *Continuous – 325 amps.
       -Flight operations:
       *Continuous
         *400 amps up to 31,000 feet.
         *325 amps from 31,000 to 46,000 feet.
         *300 amps from 46,000 to 51,000 feet.

35. Starter limits:

       AFTER START ATEMPT/ WAIT
      -1/ Three minutes.
      -2/ Fifteen minutes.

      -3/ Thirty minutes.

36.Thrust reverser limitations:
      -Below 50 KIAS/ Limited to Idle
      -50 Kias and Above/ From Idle to Maximum.

37. Cabin pressurization:
       For takeoffs and landings above 8,000 feet, the automatic pressurization
       mode must be used.
       * Maximum differential pressure……9.8PSI

38. Cooling system:
       The cooling system must be off or the cabin temperature controls must be in
       the manual mode with full cold selected for takeoff and landing.

39. Fuel load and balance:
       -Do not takeoff or land with wing fuel unbalance greater than 200 lbs (91kg).
       -During flight, fuel balance must be maintained within 500 lbs (227 kg).

40. Approved fuels/Aviation gasoline:
       -The mixing of fuel types is allowed.
       -JP-5, JP-8, Jet A and Jet A1 fuels conforming to Pratt & Whitney Canada
        CPW204 and SB 24004 are approved.
       -The use of aviation gasoline is prohibited.

41. Fuel system limits:
       -Anti-icing additives
        Anti-icing additive is not a requirement.

       -Biocide additive
         Biocide additive is not a requirement.

42. Hydraulic system limits:
       -Do not exceed auxiliary hydraulic pump duty cycle of 3 minutes on, then 20
         minutes OFF.
         *NOTE: When SAT is below -25C(-13F), engines must be operated 3 minutes
         prior to takeoff in order to bring the hydraulic system up to normal
         operating temperature.

43. TIRES:
       -Main tire limiting speed(ground speed): 182 KTS.
       -The nose and main tire pressures must be checked within 96 hours (not
         flight hours) prior to takeoff.

44. Tire pressure according to maximum certified takeoff weight:
        -Nose tire all weights: 104-114psig/718-785kPa.
        -Main tires for 22,750lbs (10,319kg) and 23,100 lbs (10,478kg):
          205-215psig/1413-1481kPa.
        -main tires for 23,500 lbs (10,660 kg): 209-219 psig (1441-1508kPa).

45. Spoilers:
       -If spoilers are inoperative during flight, the maximum operating altitude is
        limited to 38,000 feet.
       -Do not extend spoilers with flaps extended when airborne.

       -Do not extend spoilers, or operate with spoilers deployed, at speeds above
         Vmo/Mmo.

46. AC Voltage:
       -Normal range: 110-130 Volts.
       -Amber light: 90-109 Volts, and 131-134 Volts.

       -Red light: Below 90 Volts, and above 135 Volts.

47. DC Voltage:
       -Normal range: 22-29 Volts.
       -Amber light: 18-21.9 Volts, and 29.6-31.5 Volts.

       -Red light: Below 18 Volts, and above 31.5 Volts.

48. DC Amperes:

       -Normal range: 0-325 Amps.
       -Amber light: 326-400Amps.

       -Red light: Above 400 Amps.

49. Oxygen Pressure:

       -Green segment: 1550 – 1850 PSI.
       -Yellow segment: 0 – 300 PSI.
       -Red line: 2000 PSI.

50. Hydraulic pressure:
       -Yellow segment: 0-1000 PSI.
       -Green segment: 1000-1750 PSI.

       - Red line: 1750PSI

51. Gear air/Brake air:
       -Yellow segment: 0-1800 PSI.
       -Green segment: 1800-3000 PSI.
       -Red line: 3450 PSI.

52. Static wicks: There are 19 static wicks installed,
       5 of them can be missing meeting the following criteria:
       a)Only one per winglet.

       b)Position light wick can be missing.

       c) The inner most wick on each elevator can be missing.
       d) Wicks on Delta Fins CANNOT BE MISSING

               MEMORY ITEMS

1. Engine failure during takeoff below V1:
     1. Wheel brakes…..Apply
     2. Thrust levers……Idle
     3. Spoilers……Extend

2. Engine failure during takeoff above V1:

     1. Rudder and ailerons……As required for directional controls.

     2. Accelerate to VR. Keep nose on the runway.
     3. Rotate at VR; Climb at V2.

     4. Clear of obstacles……V2+20, Flaps up.

3. Engine failure during approach:

     1. Control wheel master(MSW)……Depress & release

     2. Thrust lever(operative eng.)…… Increase as required 
     3. Flaps……………………………………….20 degrees max

     4. Airspeed………………………………….1.3 Vs (Flaps 20) min

4. Engine fire-shutdown:
     Affected engine:
     1. Thrust lever……Idle (Unless critical thrust situation exists)
     2. If fire continues more than 15 seconds or there are other indicaitions of fire:
     a. Thrust lever……Cutoff
     b. Engine fire pull handle……Pull

     c. Engine ext armed light……Depress one

5.Immediate engine airstart:
    -An immediate engine airstart may be attempted before engine decelerates
     below 25% N2:
     Affected engine:
     1.Thrust lever……Idle.
     2. Ignition………….ON

6. Cabin altitude warning horn,

     Cabin altitude exceeds 10,000 ft or

     Cab alt hi light(If applicable)
     (Emergency descent):

     1. Crew Oxygen masks……Don & Select 100% Oxygen
     2. Thrust levers………………Idle

     3. Autopilot…………………….Disengage

     4. Spoiler………………………Ext

     5. Descend at Mmo/Vmo, but not below minimum safe altitude.

     6. Passenger oxygen……….Deploy

7. Cabin fire light or cabin/ cockpit fire, smoke, or fumes:

    1. Crew oxygen masks……Don, select 100% Oxygen

    2. Smoke goggles…………...Don
    3. Emer depress……Lift guard & depress
    4.Pilot and copilot norm mic/oxy mic switches…..oxy mic

8. Overspeed recovery- Overspeed horn sounds:

    1. Thrust levers……Idle

    2. Autopilot……Disengage

    3. Identify aircraft pitch and roll attitude.
    4. Wings………... Level

    5. Elevator and pitch trim……Nose up, as required.
    If mach or airspeed is severe, or if pitch and/or roll
    attitude is extreme or unknown:
    6. Landing gear……...Down (do not retract)

9. Pitch axis malfunction

     1. Control wheel master(MSW)……Depress & hold

     2. Attitude control……………………As required
     3. Thrust levers……………………….As required
     4. Pitch trim (pedestal)…………….Off

10. Roll or Yaw axis malfunction:

       1. Control wheel master(MSW)………Depress & hold

       2. Attitude control…………..As required

       If control force continues:
       3. Airspeed………...Reduce

11. Emergency braking:

       -Anti-skid protection is not available during emergency braking.
       1. Emer brake handle……..Pull out of recess

       2. Emer brake handle……..Push downward

12. Emergency evacuation:

       1.Stop the aircraft.

       2. Parking brake……Set

       3.Thrust levers……..Cutoff

       4.Emer depress……Lift guard & depress

      APU: Auxiliary power unit:

a)    Stop……Depress

b)   Master……Depress

       5.Notify controlling agency

       6.If an engine fire is suspected:

          a) Applicable ENG FIRE PULL Handle……Pull

          b) Either ENG EXT ARMED light………Depress

          c) Other ENG FIRE PULL handle……Pull

          d)Battery 1&2…………………….………..Off

          e) Emer bat 1,2&3 (If installed)…….Off

          f) Evacuate the aircraft

       7. If engine fire is not suspected:
            a) Both ENGINE FIRE PULL handles……Pull

            b) Battery 1&2…………………….………..Off

            c) Emer bat 1,2&3 (If installed)…….Off

            d) Evacuate the aircraft

13. Stall warning activates:

     1. Lower pitch attitude to reduce angle of attack.

     2. Thrust levers………………..Takeoff power.

     3. Wings…………………………...Level

     4. Accelerate out of the stall condition.

14. Aborted takeoff:
     1. Wheel brakes……..Apply

     2. Thrust levers……...Idle

     3. Spoilers……………..Ext

15. Inadvertent stow of thrust reverser after
       a crew-commanded deployment.

       1.Maintain control with rudder, aileron, nosewheel steering, and brakes

       2.Both thrust reverser levers……..Stow

16. Inadvertent thrust reverser deployment during takeoff:

       Below V1 speed:

1.     Wheel brakes……..Apply

2.     Thrust levers…….Idle

3.     Spoiler……………...Ext

17. Inadvertent thrust reverser deployment during takeoff:
       Above V1 speed:

       1. Rudder & Ailerons……….As required for directional control

       2. Accelerate to VR. Keep nose on the runway.

       3. Rotate at VR, Climb at V2.

       4. Positive rate of climb stablished…..Gear up

       5. Clear of obstacles……………… V2+20 Flaps up

    

                                 FUEL NUMBERS

VALUE             DESCRIPTION

20-60                                   Min/Max fuel truck pressure.

50                                        Fuel min for left wing compensator probe.

50                                        Fuel flow rate lbs/min – electric pumps.

200                                      Max fuel imbalance for takeoff or landing.

200                                      Unusable fuel – fuselage tank with no motive flow.

299                                      Fuel error <-2 degrees or >+6 degrees each wing with mod.

350                                     Unusable fuel – fuselage using gravity transfer.

400                                     Unusable fuel - wing with no motive flow.

410                                     Wing low fuel light / Scavenge pumps / stop fill ops.

450                                     Total fuel error without fuel mod using AHS.

500                                     Max fuel imbalance for cruise.

800                                     Max wing fuel during cold weather ops.

1200                                   Max wing fuel for powered fuel transfer.

1400                                   Max wing fuel - S.P.P.R.

1449                                   Max wing fuel - packed.

5000                                   Max fuselage fuel - S.P.P.R.

5012                                   Max fuselage fuel - packed.

FUEL INDICATOR ERROR CODES

CODE                 FAULT DEFINITION                         DESCRIPTION

0                            Internal indicator error.                      Internal indicator errors such as interprocessor

                                                                                  communications, memory test failures, or gauging

                                                                                                  hardware errors.

1                          probe capacitance out of range.          Tank probe capacitance out of range(beyond
                                                                                                    tolerance.)

2                         Tank probe/line or hi-z line                  Tank line, Hi-Z line or the probe(array) shorted to
                            grounded or open.                                    Ground, shorted across the parallel plates or
                                                                                                    open.

3                        Compensator capacitance out of              10 percent above wet capacitance and 2
                           range.                                                                Picofarads below dry capacitance(out of range.)

4                        Grounded or open compensator              Compensator shorted to ground, shorted across

                           probe line.                                                       the parallel plates or open.

5                        Fuel contaminated.                                       Compensator or tank leakage

6                       Open DC input.                                               Loss of one DC power input- available on system
                                                                                                      initialization only.

7                      Tank calibration parameters.                     Calibration performed outside of dry tank /
                                                                                                      compensator specifications or corrupted

                                                                                                      calibration data.

8                      Loss of aircraft pitch information.

9                      Oscillator failure.

10                    Reference failure.