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Republic E170 > SOP > Flashcards

SOP Flashcards

1
Q

What situations require the donning of oxygen masks?

A
  1. Loss of cabin pressure (aircraft altitude above 10,000’)
  2. Use of fire extinguisher
  3. First indication of noxious fumes/smoke
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2
Q

When is the speed reduction for holding initiated?

A

3 minutes or less from clearance limit so that the aircraft will cross the fix, initially, at or below the maximum holding airspeed

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3
Q

Where are the minimum holding speeds found?

A

Chapter 9 of the Aircraft Performance Manual

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4
Q

Max holding speed - min holding alt through 6,000 ft

A

200 KIAS

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5
Q

Max holding speed - 6,001 ft through 14,000 ft

A

230 KIAS (may be restricted to 210 KIAS)

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6
Q

Max holding speed - above 14,000 ft

A

265 KIAS

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7
Q

When is windshear detection activated?

A

between 10 and 1500 ft radio altitude during the initial takeoff, go-around and final approach phases of flight

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8
Q

When is windshear escape guidance mode engaged?

A

Manually: pressing the Go Around Button while a windshear is detected
Automatically: operating in go-around or takeoff mode and a windshear condition is detected
Automatically when thrust levers position is above 78 degrees and a warning windshear condition is detected

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9
Q

When will windshear conditions not be detected?

A

if either EGPWS or the Radar Altimeter is unavailable

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10
Q

Windshear recovery maneuver actions and callouts (PF)

A
  • Autothrottles disconnect, “FIREWALL THRUST”, press TO/GA, set thrust
  • Autopilot disconnect, roll wings level
  • Rotate toward 15 degrees pitch then follow FD (if EGPWS inop rotate to 15 degrees or PLI, whichever is lower)
  • Respect stick shaker, do not alter gear/flap configuration until terrain clearance is assured
  • Resume normal flight path, retract gear/flaps
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11
Q

Windshear recovery maneuver actions and callouts (PM)

A

monitor and call out information on flight path (“300 FEET DESCENDING; 400 FEET CLIMBING”), advise ATC

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12
Q

The windshear escape maneuver should be performed whenever the following happens:

A
  • a warning windshear is annunciated during approach or after lift-off
  • a caution windshear is annunciated during approach and the captain decides to perform the recovery
  • a caution windshear is annunciated after lift-off
  • Whenever the captain decides to perform the recovery techniques
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13
Q

When must an EGPWS recovery be initiated?

A

If a “PULL UP” or “TERRAIN, TERRAIN PULL UP” alert occurs at night or in IMC

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14
Q

EGPWS recovery action and callouts (PF)

A
  • Autothrottles disconnect, “FIREWALL THRUST”, set firewall thrust
  • Autopilot disconnect, roll wings level, rotate to 15 degrees, respect stick shaker/buffet
  • Confirm speedbrakes stowed, do not alter gear/flap configuration until terrain clearance is assured
  • Climb to a safe altitude, resume normal flight
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15
Q

EGPWS recovery action and callouts (PM)

A
  • verify all actions complete, monitor radio altimeter and callout flight path information (“300 FEET DESCENDING, 400 FEET, CLIMBING)
  • call out the safe altitude “MSA IS 3,400 FEET”, advise ATC
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16
Q

Resolution advisory (RA) action

A

press and hold TCS and follow RA PFD guidance, respect stall, GPWS, or windshear warnings, perform go around with CLIMB RA and in landing configuration

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17
Q

Stall recovery technique (PF)

A
  • autothrottle disconnect, “FIREWALL THRUST”, set firewall thrust
  • autopilot disconnect, roll wings level
  • adjust pitch as required, respect stick shaker/buffet
  • confirm speedbrakes stowed, do not alter gear/flap configuration
  • resume normal flight, retract gear/flaps as required
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18
Q

Stall recovery technique (PM)

A

verify all actions have been complete, monitor and call out flight path information “300 FEET DESCENDING, 400 FEET CLIMBING”

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19
Q

Fly By Wire Power Up Built-In Test (PBIT) consists of:

A
  1. a 3 minute electrical test
  2. a one minute hydraulic test
    Perform PBIT test if “FLT CTRL BIT EXPIRED” EICAS message is displayed
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20
Q

When will an electrical PBIT test be interrupted?

A
  1. any hydraulic pump is running
  2. the Flight Control Mode Panel switches are cycled
  3. The AC power supply is interrupted
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21
Q

When do the PBIT tests activate?

A

electrical - automatically upon power up
hydraulic - all three hydraulic systems are pressurized for at least one minute and the reservoir temperature is greater than 10C

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22
Q

When will a hydraulic PBIT test be interrupted?

A

any flight control surface is moved while the test is running

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23
Q

When must the hydraulic systems warm-up procedure be accomplished?

A

before starting engines in case of reservoir temperatures below -18C

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24
Q

Which lights are turned on for the preflight inspection?

A

RED BCN and NAV lights

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25
Q

Static dischargers per wing

A

3 on the aileron and 6 on the winglet

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26
Q

Static dischargers on tail

A

3 on each elevator and 4 on the rudder/vertical stabilizer

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27
Q

Stabilized engine indications

A 
N1...27%
ITT...460C
N2...62%
Fuel Flow...Approximately 480 lbs/hr
Oil Pressure...Greater than 25 psi
28
Q

Engine start procedure

A

Start/Stop…START, then RUN
Observe N2 increasing
7% N2…IGN A or B displayed
20% N2…N1 increasing, fuel flow increasing
at lightoff (within 5 s after fuel flow)…ITT increasing
at approx. 50% N2…IGN A or B extinguishes, oil pressure positive

29
Q

Engine warm up time

A

Before applying takeoff thrust, allow the engines to warm up for two minutes (begins at ITT red line rescheduling)

30
Q

Abnormal engine start conditions

A
  1. no oil pressure indication at idle N2
  2. oil pressure stabilizes below the engine limits
  3. hung start (stagnant N1 or N2)
  4. hot start (rapid ITT rise or ITT above red line)
  5. no ITT rise within 5 seconds on ground or 30 seconds in flight after fuel flow is started
  6. an intermittent electrical pneumatic or starter malfunction occurs before the starter disengagement
31
Q

Normal straight ahead taxi speed should not exceed

A

30 knots

32
Q

Tail tip (max) turning radius E170

A

54 ft. 3 in.

33
Q

Winglet (max) turning radius E175/upgrade winglet

A

57 ft. 9 in.

34
Q

Single engine taxi is not authorized when:

A
  1. ice accretion is anticipated
  2. contaminated surface and/or braking action less than good
  3. RVR less than 1200 ft
  4. 2 min warm up cannot be accomplished
  5. stations use power-out taxi
35
Q

minimum duct pressure for external air start

A

33 psi (based on 54C OAT)

36
Q

PSI range for crossbleed start

A

40 to 45 psi

37
Q

Takeoff briefing for taxi checklist items

A

Initial - heading, altitude, fix;
Unique - airport advisory information, noise abatement, engine failure procedures;
Significant - terrain/obstacles, and weather conditions

38
Q

When “TOGA” is called the PM will verify:

A
  • TO and AT annunciate green
  • ATTC status (green ARMED)
  • Takeoff N1
39
Q

Approved takeoff flap settings (ERJ170)

A

1, 2, and 4

40
Q

Engine severe damage is initially identified by:

A
  • decreasing engine N1/N2 and vibration indications
  • vibration/noise from affected engine
  • yaw
  • surge/stall
41
Q

Engine severe damage can be confirmed after airborne by:

A
  • seized N1 or N2
  • zero oil pressure
  • ITT rise
  • vibration indications
42
Q

After confirming engine severe damage follow:

A
  • normal climb profile except fly the runway heading or follow the applicable route manual “engine failure - takeoff” procedure
  • QRC “Engine fire, Severe Damage, or Separation” procedure
43
Q

3 types of compressor/engine stalls:

A
  • single or multiple compressor/engine stalls prior to self recovery
  • multiple compressor/engine stalles requiring pilot action to recovery
  • a non-recoverable compressor/engine stall
44
Q

Compressor/engine stalls are initially identified by:

A
  • loud bang and yaw
  • vibration
  • engine instrument fluctuation
  • ITT rise
  • flames from inlet and tailpipe
45
Q

Compressor/engine stalls can be confirmed after airborne for:

A

single/multiple with self recovery - engine returns to normal
multiple requiring pilot action - stall symptoms cease when the thrust lever is retarded
non recoverable - stall symptoms do not cease until engine is shut down or fails

46
Q

After confirming compressor/engine stalls follow:

A
  • normal climb profile except fly the runway heading or follow the applicable route manual “engine failure - takeoff” procedure
  • QRC “Engine fire, Severe Damage, or Separation”
47
Q

Engine failure initial callout

A

The first pilot recognizing the engine failure will make the callout “Engine Failure”, but will not identify the engine.

48
Q

Recommended max angle of climb

A

Vfs

49
Q

Recommended max rate of climb

A

Vfs+50 or Mach 0.60

50
Q

How to adjust VAPP for surface wind

A

add one half of the steady headwind component and all of the gust factor to the VREF

51
Q

Minimum and maximum VREF adjustment

A

min - 5 knots
max flaps 5 - 20 knots
max flaps full - 15 knots

52
Q

Recommended landing flaps setting

A

Flaps 5 unless braking conditions are less than FAIR then use FULL

53
Q

Automation usage for all precision approaches with visibility less than 3/4 miles or 4,000 RVR

A

autopilot shall be engaged from at least the FAF until the “Landing” callout by the PF

54
Q

A missed approach must be executed if any of the following conditions occur after passing the Final Approach Fix during a CAT II ILS:

A
  • approach becomes unstable
  • no Approach 2 annunciated by 500’ AGL
  • a malfunction occurs rendering the airplane unable to complete a CAT II approach
  • inability to acquire required visual references to descend below DH and/or 100 feet above TDZE
  • any reason either crew member thinks a go-around is the safest course of action
55
Q

For all non-precision approaches, if the ceiling is less than 1,000 feet and/or the visibility is less than 3 miles…

A

the autopilot shall be engaged from at least the FAF until the “Landing” callout by the PF

56
Q

Lateral modes for VOR approach

A

PF - LNAV (pink), PM - VOR (green or pink preview)

57
Q

Lateral modes for LOC, LDA (non-prec), LOC (BC) approach

A

PF - LOC (green), PM - LOC (green or pink preview)

58
Q

Lateral and vertical modes for RNAV/GPS LNAV/VNAV (DA)

A

PF - LNAV (pink)/VGP, PM - LNAV (pink)/VGP

59
Q

Lateral and vertical modes for RNAV/GPS LNAV (MDA)

A

PF - LNAV (pink)/FPA, PM - LNAV (pink)/FPA

60
Q

How to calculate VDP using milage

A

HAT / 300

61
Q

Weather mins for circling approach

A

ceiling - at least 1,000 ft or the charted minimum descent altitude for the procedure to be flown, whichever is greater
visibility - at least 3 miles or the charted visibility minimums for the procedure to be flown, whichever is greater

62
Q

Mandatory flap setting for single engine approaches

A

flaps 5

63
Q

For instrument and visual approaches the PF may call “Landing” when:

A
  • the aircraft is cleared to land
  • the aircraft is in position to land safely
  • the runway environment will remain in sight until touchdown
64
Q

Wing tip or engine nacelle strike occurs at what bank angle?

A

18 degrees or 16 degrees with gear struts compressed

65
Q

Engine cool down before shutdown

A

2 minutes

66
Q

Tail tip (max) turning radius E175

A

57 ft 3 in

67
Q

Min runway for turn around 170/175

A

170 - 54 ft 8 in

175 - 59 ft 2 in

Republic E170 (22 decks)

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