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.
