Archer Flashcards
1
Q
engines
A
1
2
Q
Engine manufacturer
A
Lycoming
3
Q
Engine model number
A
IO-360-B4A
4
Q
Takeoff power
A
180
5
Q
Speed RPM
A
2700
6
Q
Engine type
A
Four cylinder, direct drive, horizontally opposed with fuel injection
7
Q
Number of propellers
A
1
8
Q
Propeller Manufacturer
A
Sensenich
9
Q
Propeller model
A
76EM8S14-0-62
10
Q
Number of blades
A
2
11
Q
Propeller Diameter Maximum
A
76 inches
12
Q
Propeller Diameter Minimum
A
76 inches
13
Q
Propeller Type
A
Fixed Pitch
14
Q
Fuel Capacity
A
50
15
Q
Useable fuel
A
48
16
Q
Minimum octane
A
100 Green or 100LL Blue Aviation Grade
17
Q
Oil Capacity
A
8
18
Q
Maximum Ramp Weight
A
Normal: 2558
Utility: 2138
19
Q
Maximum Takeoff Weight
A
Normal: 2550
Utility:2130
20
Q
Maximum Landing Weight
A
Normal: 2550
Utility: 2130
21
Q
Maximum weights Baggage
A
200 pounds
22
Q
Compartment Volume
A
24 feet
23
Q
Entry width
A
22 inches
24
Q
Entry Height
A
20 inches
25
Wing Loading
15 pounds per sq ft
26
Power Loading
pounds per hp 14.2
27
CAS
means the indicated speed of an aircraft, corrected for position and instrument error. Calibrated airspeed is equal to true airspeed in standard atmosphere at sea level
28
KCAS
Calibrated Airspeed expressed in Knots
29
GS
Ground speed is the speed of an airplane relative to the ground
30
IAS
Indicated Airspeed is the speed of an aircraft as shown on the airspeed indicator when corrected for instrument error
31
KIAS
Indicated Airspeed expressed in Knots
32
TAS
True airspeed is the airspeed of an airplane relative to undisturbed air which is the CAS corrected for altitude, temperature and compressibility
33
Vo
Maximum maneuvering speed
113 knots
34
VFE
Maximum Flap extended Speed
102 knots
35
VNE/MNE
Never exceed speed
154 knots
36
VNO
Max structural cruising speed
125 knots
37
Vs
Stalling speed clean configuration
50 knots
38
Vso
Stalling speed landing configuration
45 knots
39
Vx
Best angle of climb is the airspeed which delivers the greatest gain of altitude in the shortest possible horizontal distance
64 knots
40
Vy
Best rate of climb speed is the airspeed which delivers the greatest gain in altitude in the shortest possible time
76 knots
41
ISA
International Standard Atmosphere in which the air is a dry perfect gas; The temperature at sea level is 15 degrees celsius or 59 degrees farenheit. The pressure at sea level is 29.92 inHG
42
OAT: Outside Air Temperature
is the free air static temperature, obtained either from inflight temperature, obtained either from inflight temperature indications or ground meteorological sources, adjusted for instrument error
43
Indicated pressure Altitude
The number read from the altimeter
44
Pressure Altitude
Altitude measured from standard sea level pressure by a pressure or barometric altimeter. It is the indicated pressure altitude corrected for position and instrument error
45
Station pressure
Actual atmospheric pressure at field elevation
46
wind
The wind velocities recorded as variables on the charts of this handbook are to be understood as the headwind or tailwind components of the reported winds
47
Maximum Continuous Power
Maximum power permissible continuously during flight
48
Takeoff power
Maximum power permissible for takeoff
49
EGT
Exhaust Gas Temperature
50
FFLOW
Fuel Flow
51
RPM
Propeller speed
52
1
refers to pilot side
53
2
refers to co-pilot's side
54
ADAHRS
Air data, Altitude and Heading Reference system
55
AFCS
Automatic Flight Control System
56
CAS
Crew Alerting System
57
EBD
Evolution Backing Display (Aspen standby Instrument)
58
EIS
Engine Indication System
59
ESP
Electronic Stability and protection
60
FDE
Fault Detection and Exclusion
61
FOB
Fuel on Board
62
GDL
Garmin Datalink
63
GDU
Garmin Display Unit
64
GEA
Garmin engine/Airframe Processing Unit
65
GFC
Garmin Flight Control System
66
GIA
Garmin Integrated Avionics Unit
67
GMA
Garmin Audio Panel
68
GMU
Garmin Magnetometer Unit
69
GPS
Global position system
70
GSU
Garmin ADAHRS
71
GTX
Garmin Transponder
72
MFD
Multi-Function Display
73
PFD
Primary Flight Display
74
PFT
Preflight Test
75
SBAS
Satellite-Based Augmentation System
76
TAWS
Terrain Awareness and Warning System
77
USP
Underspeed Protection
78
ARM
The horizontal distance from the reference datum to the center of gravity (C.G.) of an item
79
Center of Gravity
The point at which an airplane would balance if suspended. Distance found by dividing the total moment by total weight
80
C.G. Arm
the arm obtained by adding the airplane's individual moments and dividing the sum by the total weight
81
C.G. Limits
The extreme center of gravity locations within which the airplane must be operated at a given weight
82
Datum
An imaginary vertical plane from which all horizontal distances are measured for balance purposes
83
Basic Empty Weight
Standard empty weight plus optional equipment
84
Maximum Landing Weight
Maximum weight approved for the landing touchdown
85
Maximum Ramp Weight
weight approved for ground maneuver
86
Maximum Takeoff weight
Maximum weight approved for takeoff
87
Maximum zero fuel weight
maximum weight exclusive of usable fuel
88
Moment
The product of the weight of an item multiplied by its arm
89
payload
weight of occupants, cargo and baggage
90
standard empty weight
weight of a standard airplane including unusable fuel, full operating fluids and full oil
91
Station
A location along the airplane fuselage usually given in terms of distance from the reference datum
92
unusable fuel
fuel remaining after a runout test has been completed in accordance with government regulations
93
Usable fuel
fuel available for flight planning
94
useful load
difference between takeoff weight, or ramp weight is applicable, and basic empty weight
95
Red line (Never Exceed)
154 knots
96
Yellow Band ( caution range- smooth Air only)
125-154 knots
97
Green band(Normal operating range)
50-125 knots
98
White band (Flap Down)
45-102 knots
99
Max oil temperature
245 degrees
100
Oil pressure
Minimum (red line) 25 PSI
Maximum (red line) 115 PSI
101
Tachometer green arc
500 to 2700 RPM
102
Oil temperature green band
75 degrees- 245 degrees
103
Oil pressure
Green band: 55 PSI
Yellow band: 25 PSI-55 PSI
Yellow band (ground warm-up) 95 PSI-115 PSI
Red line (Minimum) 25 PSI
Red line (Maximum) 115 PSI
104
Alternator
70 AMPS
105
Emergency Battery minimum
23.3 volts
106
Forward Limit inches Aft of Datum
2550= 88.6
2050 (or less)= 82.0
107
Rearward Limit Inches AFT of datum
2550= 93.0
2050 (or less)= 93.0
108
Utility: Forward limit inches aft datum
2130= 83.0
2050 (or less)= 82.0
109
Utility: Rearward limit inches aft of datum
2130= 93.0
2050 (or less)= 93.0
110
Positive load factor (maximum)
Normal= 3.8G
Utility=4.4G
111
Negative Load factor (maximum)
Normal= -1.5G
Utility= -1.7G
112
Placards
Limitations: in full view of the pilot
Maneuvering speed: in full view of the pilot
Demonstrated crosswind
No Smoking: on the cockpit overhead panel
Alternate static source: on lower left portion of instrument panel
Air conditioning warning: in full view of the pilot, in the area of the air conditoner control panel when the air conditioner is installed
Strobe light warning: in full view of the pilot
Engage latch before flight: adjacent to upper door latch
Baggage max 200 pounds: on inside of the baggage compartment door or information split into two placards on aft baggage compartment bulkhead
Maximum allowable combined weight: Above right side aft passenger arm rest:
External power 28 volts:on the right side of the fuselage aft of the wing
AVGAS only: adjacent to the filler caps
113
Engine Fire During Start
Start switch...... Continue to Crank Engine
Mixture.... Idle
Throttle.......Open
Fuel Pump..... OFF
Fuel selector....OFF
114
Engine Fire in Flight
Fuel Selector.....OFF
Throttle......Closed
Mixture......IDLE cut off
Fuel pump.....OFF
Heat/DEF(Defroster)........OFF
If fire persist
Airspeed......Increase in attempt to blow out fire
Proceed with Power off Landing procedure
115
ELECTRICAL FIRE IN FLIGHT
Emergency battery switch......Verify Arm
Battery Master Switch....OFF
Alternator Switch......OFF
Vents........Open
Heat/DEF(Defroster).....OFF
Fire........Extinguish
Emergency descent if needed
116
Engine power loss during takeoff
Airspeed.....Maintain safe airspeed
Landing....Land and Stop straight ahead
brakes......as required
If insufficient runway remains:
Airspeed...... Maintain Safe Airspeed
Flaps....... As required
If sufficient altitude has been gained to attempt a restart
Airspeed.... maintain 76 knots
Fuel selector..... switch to tank containing fuel
Fuel pump...... check on
Mixture....... Rich
ALT AIR.... open
117
Engine power loss in Flight
Airspeed..... Maintain 76 knots
Fuel selector......Switch to tank containing fuel
Fuel Pump.......ON
Mixture......Rich
ALT AIR.........OPEN
Left/Right MAG switches......Turn off then ON one at a time
When power is restored
ALT AIR......Close
Fuel PUMP.......OFF
118
Power off landing
Airspeed....Maintain 76 knots
Air conditioning (if installed).....OFF
Landing pattern.....establish 1000ft above field at downwind position
When committed to landing
Airspeed......66 knots
Flaps..... As Desired
Throttle.......Close
Mixture........Idle Cut-off
Left/Right MAG Switches.......OFF
Battery Master switch......OFF
Alternator Switch........OFF
Fuel selector.........OFF
Seat belt......fastened
119
Oil Pressure
Low Pressure
Throttle.....Minimum
If accompanied by high oil temperature, land as soon as possible
If accompanied by normal oil temperature, land as soon as practical
High oil pressure
Throttle......Minimum
Land as soon as practical
120
Oil Temperature
Throttle.....Minimum
Mixture.....Full Rich
Airspeed.....Increase if practical
Land as soon as possible and investigate the problem. Prepare for Power off Landing
121
Loss of Fuel Flow
If caused by fuel depletion in One Tank
Fuel pump switch.......ON
Fuel Selector..... Selector other tank (Fullest)
Fuel Pump Switch.....OFF
If caused by engine driven fuel pump failure:
Throttle.......Close
Fuel Pump Switch.....ON
Throttle......Re-establish(as required)
Mixture.....Re-establish(as required)
122
Fuel Quantity Low
If one tank has low fuel quantity
Fuel selector....... On Fullest Tank
Land as soon as practical
If both tanks have low fuel quantity
Fuel Selector..... Alternate Tanks to maintain fuel supply to Engine
Land as soon as possible
123
Alternator Failure
Verify Failure......Check ALTR AMPS Indication
ALTR switch......OFF
ALTR circuit breaker (Row 1, Col.13)......Reset if Tripped
ALTR FIEL Circuit Breaker (Row 2, Col.13)....Reset
ALTR switch.....ON
If alternator still failed
ALTR switch......OFF
Electrical Power Remaining......OFF
Electrical power Remaining.......30 minutes or less
Electrical Load.......SHED in less than 3 minutes
NON ESS circuit Breaker (ROW 1, Col. 1).....PULL
Lighting Bus circuit breaker (Row 1, Col,2) PULL
Avionics master switch.....OFF
To ensure 30-minutes of battery life:
Battery discharge....-13 AMPS maximum
pitot heat......14 minutes usage maximum
fuel pump....... 2 mins usage maximum
Land as soon as possible
124
Complete electrical failure
Emergency Batt switch......Verify ARM
Standby flight instrument....Verify operational
Aircraft control.....Use PFD and standby instrument
Batt master switch....OFF
ALTR switch......OFF
Prior to Landing
Landing Light........Inoperative
Approximately 30 minutes of electrical power is available
Land as soon as possible
125
Emergency Battery Voltage
Warning: Complete electrical failure is imminent
Land as soon as possible
126
PFD Failure
Standby instrument....verify operational
Aircraft control....Use standby instrument
Display backup button on audio panel..Push
Aircraft control....Use MFD and standby instrument
COM2....Activate and Tune as necessary
NAV2.....Activate and TUNE as necessary
COM2/MIC...... Select on audio panel
DME......select NAV2 in DME tuning window
Exit and avoid IFR conditions as soon as practical
127
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