archer POH Flashcards
(112 cards)
1
Q
engine manufacturer
A
lycoming
2
Q
fuel injected
A
IO-360-B4A
3
Q
takeoff power (BHP)
A
180
4
Q
engine displacement (in^3)
A
361
5
Q
engine type
A
four cylinder, direct drive, horizontally opposed with fuel injection
6
Q
prop manufacturer
A
sensenich
7
Q
prop type
A
fixed pitch
8
Q
fuel capacity
A
50 gal
9
Q
useable fuel
A
48 cal
10
Q
fuel minimum octane
A
100 green or 100LL blue aviation grade
11
Q
oil capacity
A
8 qts
12
Q
oil type
A
20W-50
13
Q
max ramp weight
A
2558 lbs
14
Q
max takeoff weight
A
2550 lbs
15
Q
max landing weight
A
2550 lbs
16
Q
max weight in baggage comp
A
200 lbs
17
Q
wing loading
A
15 lbs per sq ft
17
Q
power loading
A
14.2 lbs per hp
18
Q
navigation system
A
garmin G1000 integrated avionics GNSS long range navigation system
19
Q
SBAS
A
satellite based augmentation system
20
Q
how many GNSS systems
A
when fully operational, G1000 has two independent GNSS long range navigational systems
21
Q
GNSS
A
global navigation satellite system
22
Q
how can you determine FDE/RAIM availability
A
using the garmin RAIM/fault detection and exclusion prediction tool available on the garmin website
23
Q
CAS
A
calibrated airspeed; indicated airspeed corrected for position and instrument error; equal to true airspeed in standard atmosphere at sea level
24
IAS
indicated airspeed; airspeed indicated on the ASI when corrected for instrument error
25
TAS
true airspeed; airspeed relative to undisturbed air which CAS corrected for altitude, temp, and compressibility
26
Vfe
max flap extended speed; 102
27
Vne
never exceed speed; 154
28
Vno
max structural cruising speed; 125
29
Vso
stall speed at which airplane is controllable in the landing configuration; 45
30
Vx
best angle of climb; 64
31
Vy
best rate of climb; 76
32
ISA
international standard atmosphere; air is a dry perfect gas, temp at sea level is 15 deg celsius, pressure at sea level is 29.92 inches of mercury (1013.2 millibars)
33
OAT
outside air temperature; free air static temperature
34
indicated pressure altitude
number actually read from an altimeter when baro sub scale has been set to 29.92 inches of mercury 1013.2 millibars)
35
pressure altitude
indicated pressure altitude corrected for position and
instrument error
36
EGT
exhaust gas temperature
37
FFLOW
fuel flow
38
RPM
prop speed
39
ADAHRS
air data, attitude and heading reference system
40
AFCS
automatic flight control system
41
EIS
engine indicating system
42
FDE
fault detection and exclusion
43
FOB
fuel on board
44
GPS
global positioning system
45
GSU
garmin ADAHRS
46
GTX
garmin transponder
47
MFD
multifunction display
48
PFD
primary flight display
49
climb gradient
demonstrated ratio of change in height during a portion of a climb, to the horizontal distance traversed in the same time interval
50
arm
horizontal distance from reference datum to CG
51
CG
center of gravity; point at which the airplane would balance if suspended; total moment/total weight
52
CG arm
obtained by adding the airplane's individual moments and dividing the sum by the total weight
53
datum
imaginary vertical plane from which all horizontal distances are measured for balance purposes
54
basic empty weight
standard empty weight plus optional equipment
55
max zero fuel weight
max weight exclusive of usable fuel
56
payload
weight of occupants, cargo, and baggage
57
useable fuel
fuel remaining after runout test as been completed in accordance with governmental regulations
58
useful load
difference between takeoff weight and basic empty weight
59
max prop speed
2700 rpm
60
max oil temp
245 deg F
61
minimum oil pressure
25 PSI
62
maximum oil pressure
115 PSI
63
PSI
pounds per inch^2
64
alternator limitation
70 amps
65
emergency batt minimums
23.3 volts
66
approved operations
day VFR, night VFR, day IFR, night IFR, non icing, person operating aircraft must wear a headset while in flight
67
data link wx display
limited to supplemental use only and may not be used in lieu of an official wx data source
68
landing final approach speed (flaps 40)
66 KIAS
69
max demonstrated crosswind velocity
17 kts
70
can you keep the EMERG BATT switch on during normal operation?
yes; switch can remain ON while using external power; emergency bus does not receive power from external power source due to a relay in the circuit
71
why should you avoid prolonged idling at low rpm?
it may result in fouled spark plugs
72
during runup, what is the maximum amount of time you should operate on one mag?
do not exceed 10 seconds
73
what is the enroute climbing speed
87 KIAS; will produce better forward speed and increased visibility over the nose during a climb
74
when is best economy mixture reached?
moving the mixture control aft until peak EGT is reached
75
when is best power mixture reached?
leaning to peak EGT and then enriching until the EGT is 100 deg F rich of the peak value
76
during cruise why should you keep the electrical fuel pump on OFF?
so any malfunction of the engine driven fuel pump is immediately apparent
77
when does fuel vapor occur?
can occur in the fuel system during ground operations when high ambient temperatures are present
78
what are some symptoms of fuel vapor?
fluctuation of idle speed and fuel flow, poor engine response to throttle movement, engine will not operate when throttle is closed, high rpm drop (greater than 175 rpm) during mag check
79
if during ground operation you suspect fuel vapor, what should you do?
(a) Advance the throttle to an engine speed of 1800 to 2000 RPM. Continue
at this power setting for - 1-2 minutes or until smooth engine operation.
Make sure oil temperature stays within limits.
(b) Return throttle to idle and check for smooth operation.
(c) During taxi, lean mixture and operate at as high a power setting (1200
RPM max) as practical.
(d) Prior to takeoff, sel the mixture lo the full rich position (for high
elevation fields, mixture leaning could be necessary for smooth engine
operation).
(e) Prior to initiation of takeoff roll, set full throttle and verify smooth
engine operation.
80
what does the standard empty weight include?
full oil capacity and 2.0 gallons of unusable fuel
81
describe the engine
powered by a four-cylinder, direct drive, horizontally opposed fuel injected engine rated at 180 horsepower at 2700 rpm; it is furnished with a starter, 70 ampere 28-volt alternator, shielded ignition wires, a fuel pump, and a dry, automotive type induction air filter
82
describe the exhaust system
The exhaust system is made entirely from stainless steel and is equipped with a single dual muffler; a heater shroud around the muffler is provided to supply heat for the cabin and windshield defrosting
83
describe the induction system
incorporates an avstar RSA-5AD1 type fuel injector; based on the principle of differential pressure which balances air pressure against fuel pressure; the regulated fuel pressure established by the
servo valve when applied across a fuel control (jetting system) makes the fuel
flow proportional to airflow; fuel pressure regulation by the servo valve causes a
minimal drop in fuel pressure throughout the metering system; metering pressure
is maintained above most vapor forming conditions while fuel inlet pressure is
low enough to allow use of a diaphragm pump; the servo system feature also
checks vapor lock and associated starting problems
84
what does fuel injected mean?
the fuel is injected directly into the cylinders, or just ahead of the intake valve; fuel injectors mix the fuel and air immediately before entry into each cylinder or injects fuel directly into each cylinder
85
what are the advantages to a fuel injected induction system?
Reduction in evaporative icing
Better fuel flow
Faster throttle response
Precise control of mixture
Better fuel distribution
Easier cold weather starts
86
describe the alternate air induction system
the induction airbox assembly contains a valve that can open and allow airflow into the engine in the event of blockage of the primary induction air source; the air provided through the alternate air source is heated, which will also provide induction system icing protection; as this alternate air source is not filtered, the primary air source should always be used for takeoff; control of the alternate air valve is through a lever located to the right of the engine control lever quadrant
87
describe the flight controls
dual controls are provided as standard equipment with a cable system used between the controls and the surfaces
88
describe the horizontal tail
the horizontal tail (stabilator) is of the all moveable slab type with a trim tab mounted on the trailing edge
89
describe the flaps
single slot manually operated flaps
90
what are single slot flaps?
most commonly used flaps today; they increase wing camber (curve of the wing) and when extended they open a slot between the wing and the flap; by opening a slot between the wing and the flap, high pressure air from the bottom of the wing flows through the slot into the upper surface; this adds energy to the wing's boundary layer, delays airflow separation, and produces less drag
91
describe the landing gear
three landing gear use Parker 6.00 x 6 wheels; mains are equipped with single hydraulically operated external caliper and disk brake assembly
92
what is the hydraulic fluid we use?
petroleum hase; MIL-PRE-5606; red color
93
describe the brake system
consists of dual toe brakes attached to the rudder pedals and a hand brake lever located below, behind, and to the left of the throttle quadrant; toe and hand brakes have their own master brake cylinders, but
they share a common reservoir; the brake fluid reservoir is installed on the top left front face of the firewall; the parking brake is incorporated in to the hand lever master cylinder
94
AHRS
attitude and heading reference system; uses GPS, rate sensors, air data, and magnetic variation to provide pitch and roll attitude, sideslip, and heading information; incorporates internal monitors to determine validity to its parameters; 2 magnetometers (one for PFD/MFD one for standby), inclinometers, accelerometers, rate sensors
95
ADC
air data computer; provides airspeed, altitude, vertical speed, and air temperature; also used for FMS and traffic system; incorporates internal monitors to determine validity of its parameters; pitot static instruments provide information
96
what kind of transponder do we have
GTX345R
97
what are some of the capabilities of our transponder?
ADSB-in, ADSB-out, TAS, timers, static OAT display, internal GPS, PA and DA display
98
what happens to the standby during complete electrical failure of the alternator, primary, and emergency batt
G5 standby will revert to its internal battery allowing for 4 hours of additional operation
99
describe the electrical system
28 volt electrical system includes a 24 volt primary battery, a 70 ampere 28 volt alternator, a single external power connector and an isolated 24 volt emergency battery; the electrical system is capable of supplying sufficient current to all the required equipment for day/night IFR and day/night VFR operations
100
what does the primary battery do?
provides for electric power to the equipment when the engine is not running and for engine starting; when energized by the battery master switch the primary battery supplies electrical power to the starter as well as all items on the Essential Bus, Non-Essential Bus and Lighting Bus; if
it becomes necessary to charge the battery by an external source, it should be removed from the airplane prior to charging
101
describe the alternator
belt driven directly from the engine; once engine is running and ALTR switch is activated the alternator becomes the primary source of electrical power for the aircraft; primary batt provides stored electrical power to back up the alternator; batt is charged by alternator
102
what is a voltage regulator?
designed to regulate the electrical system bus voltage to 28 volts and to prevent damage to the electrical and avionics equipment by removing the alternator from the circuit if its output exceeds 32 volts
103
describe the emergency battery
provides electrical power to emergency bus; with EMERG BATT in ARM position power is applied to emergency bus automatically if electrical power is removed from primary electrical system; provides minimum duration of 30 minutes of electrical power to emergency bus equipment
104
what functions are available via the emergency bus
all standby instrument functions, PFD functions (nav/comm1 only), and the audio panel
105
how can you ensure that you have the full 30 minutes of power from emergency batt
only available if its voltage is greater than 23.3 volts prior to flight
106
what role does the diode serve regarding the emergency battery
the emergency battery is also isolated from the electrical power generating system
via a diode in the circuit; this diode will allow the generating system to charge
the emergency battery during normal operations but prevents discharge of the
emergency battery when operating with the alternator off
107
what happens when the alternate static is engaged?
altimeter, vertical speed indicator, and airspeed indicator on the PFD and standby will use cabin air for static pressure
108
what do you have to do during alternate static operation?
storm window and cabin vents must be closed and cabin heat and defrost must be on
109
when do you have to replace the ELT
batt replacement date marked on the transmitter; batt must be replaced before or on this date or if the transmitter has been used in an emergency situation or accumulated test time exceeds one hour
110
ELT test transmission
should be conducted only in the first 5 minutes of any hour and limited to three audio sweeps
111
