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Jason's Work Stuff > G-280 Aircraft General > Flashcards

G-280 Aircraft General Flashcards

1
Q

When did the G-280 design begin?

A

“In 2005, Gulfstream and IAI (Israel Aerospace Industries) began designing a follow-on aircraft to the Gulfstream G-200 (formerly known as the IAI Galaxy - or the “Astra Galaxy” - but was rebranded the Gulfstream G-200 when Gulfstream Aerospace purchased Galaxy Aerospace in 2001, it was produced from 1999 thru 2011). The new model, named “G-250”, was launched in 2008 (maiden flight was on December 11, 2009 in Tel Aviv, Israel). In July 2011, the G-250 was renamed “G-280” because in Mandarin language, the number 250 can be translated as “stupid” or “idiotic”. Full certification was on September 4, 2012.”

(Wikipedia)

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2
Q

Civilian products of Israel Aerospace Industries (IAI)

Civilian Aircraft Produced

A

> IAI Westwind (1965-1987):
* 1121 Jet Commander (1964), 1123 Commodore Jet (1971), 1124 Westwind I (1976), 1124A Westwind II (1980).
Gulfstream G-100 (1985-2016):
* 1125 Astra (1985), 1125 Astra SP (1990), G-100 (Astra SPX) (1996), G-150 (2005.
Gulfstream G-200 (Galaxy) (1997-2011).
Gulfstream G-280 (2011-present).
Arava (medium sized STOL transport aircraft, no longer in production).
IAI Avocet ProJet (Very Light Jet - cancelled in 2005).

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3
Q

G-280 Design

A

“The aerodynamic design of its wing and empennage, and design of the interior were performed by Gulfstream; detailed design was performed by IAI to Gulfstream’s requirements. It is a Gulfstream designed aircraft under a new type certificate.”
“The fuselage, empennage and landing gear are manufactured by IAI, the wing by Spirit AeroSystems (now Triumph Group), and the aircraft is assembled in Israel. It is then ferried to Dallas, Texas, for interior finishing and painting.”
Its wing is a new design, using the Gulfstream G-550 airfoil, and has a larger area of 495 square feet versus 369 square feet of the G200. This allows it to climb directly to 43,000. Cruise is M 0.80 versus M 0.75 for the G200. At FL410 and Mach 0.82 each engine burns 900 pounds per hour.”
(Wikipedia)

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4
Q

When was the G-280 certified?

A

“The G280 was provisionally certified in December 2011 by Israel. In July 2012, the U.S. FAA released a report with conditions to ensure no security gaps in the G280’s electronic systems. It received full certification from Israel and the U.S. on September 4, 2012.”

(Wikipedia)

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5
Q 
What class of business jet is the G-280?
What are the different classes of business jets?
A 
The G-280 is a Super Mid-Size
The different classes are:
>  Very Light Jets.
>  Light Jets.
>  Mid-Size Jets.
>  Super Mid-Size Jets.
>  Large Jets.
>  VIP Airliners.
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6
Q

AFM Approval

A

> Approved by the Civil Aviation Authority of Israel (CAAI) on behalf of the European Aviation Safety Agency (EASA), using the working arrangement between the CAAI and the EASA.

> The AFM is FAA Approved for U.S. registered airplanes in accordance with the provision of CFR section 21.29, and as required by FAA Type Certificate Data Sheet No. A61NM.

(AFM Issue 2, 10 Nov 2016)

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7
Q

Serial Numbers

A

> Issue 1:
* 2001-2105, 2107-2109, 2111-2113.
(111 total - 2001 to 2113 except 2106 and 2110).

> Issue 2:
* 2106, 2110, 2114-subsequent.

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8
Q

G-280 Range

A

“After the flight test program, the G280 demonstrated a range of 3,600 NM at Mach 0.80 with four passengers and NBAA IFR reserves in 2011. It can fly from London to New York or Singapore to Dubai.”
(Wikipedia)
(AOM 2A-06-40, 7)

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9
Q

Length, Width, and Height

A

Length:
66.8 Feet (802 in. or 66 feet, 10 inches)
66.66 Feet
(AOM 2A-06-40, 8)

Width:
63 Feet (756 inches)
61.69 Feet
(AOM 2A-06-40, 8)

Height:
21.29 Feet
(255.43 in. or 21 feet, 3 and 7/16 inches)
21 Feet, 4 inches
(Wikipedia)
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10
Q

Wing Sweep and Dihedral

A

Leading Edge Sweep: 30.68 degrees
Dihedral: 2.061 degrees
(PTH page 1-5, rev 2.1)*

  • These values are from page 1-5 in the PTH rev 2.1, however, the Operating Manual (2A-06-10, page 1) says this (last paragraph on page 1):
    “The aircraft wings are swept back twenty-seven degrees (27) and are cantilevered with a three degree (3) dihedral.”
    Also, the AOM (2A-06-40, 8) says: “Wing Sweep Angle (1/4 Chord) 27 degrees”.
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11
Q

Max Number of Occupants

A

19

> Limited by emergency exit requirements.
An approved seating arrangement must be installed.
Typical cabin configurations are set up to accommodate up to 10 passengers (8-10).
Also, notice that this is the maximum number of OCCUPANTS (not max passengers).
Also, there are 19 cabin windows and there are 19 static discharge wicks.
Minimum Flight Crew is pilot and copilot.

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12
Q

When shall the operator comply with the “Cold Weather Operations” (starting on page IV-87 of the AFM)?

A

Anytime the airplane has been exposed to temperatures colder than -20 degrees C (-4 degrees F) on the ground for more than 10 hours.

(AFM 1-03-20)

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13
Q

Maximum Temperature on the Ground

A

ISA +35 degrees C

AFM 1-03-20; and page V-92

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14
Q

Aircraft Danger Area

A

> 200 feet aft from trailing edge of engine nacelle.
42 feet wide (21 feet left and right of center).
Region is valid only for ground idle operation.
Also, 15 foot radius from nacelle inlets.
(OM 2A-06-20, page 6 - figure 3)

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15
Q

Max Zero Fuel Weight

A

28,200 Pounds
(AFM 1-03-60)
(OM 2A-06-20, 2)

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16
Q

Max Ramp Weight

A

39,750 Pounds
(AFM 1-03-60)
(OM 2A-06-20, 2)

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17
Q

Max Takeoff Weight

A

39,600 Pounds
> Unless restricted by climb performance, brake energy, or tire speed for approved altitudes and ambient temperature or by field length. (Maximum structural weight for takeoff - cannot be exceeded).

(AFM 1-03-60)
(OM 2A-06-20, 2)

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18
Q

Max Landing Weight

A

32,700 Pounds
> Unless restricted by climb requirements.

(AFM 1-03-60)
(OM 2A-06-40, 7)

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19
Q

Minimum Flight Weight

A

23,000 pounds
> (AFM 1-03-60)
> MFW (Minimum Flight Weight) is the Minimum authorized flight weight of an aircraft. It may be changed as a function of the relevant center of gravity.
(AFM page VI-4 and page VI-M-4)

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20
Q

Zero Fuel Weight CG

A

Zero Fuel Weight CG must be within the allowable zero fuel weight CG envelope. The fueled airplane CG will then be within limits for all fuel loads.
(AFM 1-03-70)

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21
Q

Aft CG limit for ground handling during any stage of ground handling operations

A

50% MAC

AFM 1-03-70

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22
Q

Payload

A

4,050 Pounds
> Max payload with Full Fuel is 1,000 pounds.

(Wikipedia)

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23
Q

Max Nose Wheel Turning Angle

Left or Right of Center

A

> Nose Wheel Steering Control — 60 +/-2.5 degrees
Rudder Pedals — 3 degrees
Tow Bar — 100 degrees
(Tow-Bar-Less is 90-95 degrees)
(+/- 80 degrees should not be exceeded, if it is the towing crew warning horn will sound. If tow angle of +/- 93 degrees is reached, the NWS Oversteer CAS caution will appear when power is applied).

(Nose wheel steering unit torque links must be disconnected prior to towing aircraft.  Rotation of nose wheels beyond their normal limits - 80 degrees - can cause serious damage to the nose wheel steering unit.  With steering unit torque links disconnected, the nose wheels are free to rotate 360 degrees).

(AOM 2A-32-50 and 09-01-20)

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24
Q

Angles for Nose Wheel Steering

A

> Rudder Pedals: —- 3 degrees.
Tiller: —- 60 +/-2.5 degrees.
(Turn Radius 51.6 feet at 60 degrees and 49.5 at 62.5 degrees).
Should Not Be Exceeded: —- 80 +/-4 degrees.
(Towing, towing crew warning horn will sound).
Towing (Max) “Tow-Bar-Less”: —- 90-95 degrees.
NWS Oversteer Flag and amber “NWS OVERSTEER” CAS message: —- 93 degrees.
Max Tow Bar: —- 100 degrees.

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25
Q

Minimum Radius for a 180 Degree Turn

A
  1. 5 feet (with a steering angle of 62.5 degrees nominal).

51. 6 feet (with a steering angle of 60.0 degrees nominal).

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26
Q

Max Runway Slope

A

+ or - 2% for takeoff or landing

AFM 1-02-10

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27
Q

Max Tailwind Component for Takeoff and Landing

A

10 knots

AFM 1-02-10

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28
Q

Max Demonstrated Crosswind

For Takeoff and Landing

A

25 knots

AFM V-13

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29
Q

Minimum Holding Speed in Icing Conditions

A

185 KIAS

AFM 1-03-40

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30
Q

Max Certified Altitude
and
Minimum Operating Altitude

A

> Max Operating Altitude = 45,000 feet
Minimum Operating Altitude = -1,400 feet

(AFM 1-03-30)

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31
Q 
Maneuvering Speed (Va)
Sea Level to 20,000 Feet
A 
215-225 KIAS
>  Avoid rapid and large alternating control inputs, especially in combination with large changes in pitch, roll, or yaw (e.g. large side slip angles), as they may result in structural failures at any speed, including below Va.
>  20,000 to 35,000 feet = 225-264 KIAS
>  35,000 to 39,000 feet= 264 KIAS
>  39,000 to 45,000 feet = 0.85 Mi

(AFM 1-03-40)

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32
Q 
Maneuvering Speed (Va)
20,000 to 35,000 Feet
A

225-264 KIAS
> Avoid rapid and large alternating control inputs, especially in combination with large changes in pitch, roll, or yaw (e.g. large side slip angles), as they may result in structural failures at any speed, including below Va.
> Sea Level to 20,000 feet = 215-225 KIAS
> 35,000 to 39,000 feet = 264 KIAS
> 39,000 to 45,000 feet = 0.85 Mi

(AFM 1-03-40)

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33
Q 
Maneuvering Speeds (Va)
35,000 to 39,000 Feet
A

264 KIAS
> Avoid rapid and large alternating control inputs, especially in combination with large changes in pitch, roll, or yaw (e.g. large side slip angles), as they may result in structural failures at any speed, including below Va.
> Sea Level to 20,000 feet = 215-225 KIAS
> 20,000 to 35,000 feet = 225-264 KIAS
> 39,000 to 45,000 feet = 0.85 Mi

(AFM 1-03-40)

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34
Q 
Maneuvering Speed (Va)
39,000 to 45,000 Feet
A

0.85 Mi
> Avoid rapid and large alternating control inputs, especially in combination with large changes in pitch, roll, or yaw (e.g. large side slip angles), as they may result in structural failures at any speed, including below Va.
> Sea Level to 20,000 feet = 215-226 KIAS
> 20,000 to 35,000 feet = 225-264 KIAS
> 35,000 to 39,000 feet = 264 KIAS

(AFM 1-03-40)

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35
Q

Maneuvering Speeds (Va)

A

> Sea Level to 20,000 Feet = 215-225 KIAS
20,000 to 35,000 feet = 225-264 KIAS
35,000 to 39,000 feet = 264 KIAS
39,000 to 45,000 feet = 0.85 Mi

(AFM 1-03-40)

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36
Q

Max Flap Extended Speed (Vfe) for:

  • 10 Degrees Flaps,
  • 20 Degrees Flaps, and
  • LAND
A

10 degrees flaps = 250 KIAS
20 degrees flaps = 220 KIAS
LAND = 180 KIAS

(AFM 1-03-40)

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37
Q

Max Tire Speeds

Main Landing Gear and Nose Landing Gear

A

> Main Landing Gear = 195 knots
Nose Landing Gear = 182 knots

(AFM 1-03-40)

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38
Q

Max Landing Gear Operation and Gear Extended Speeds (Vlo / Vle)

A

195 KIAS
> Gear doors opened or closed.

(AFM 1-03-40)

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39
Q

Max Emergency Landing Gear Extension Speed

A

175 KIAS
> After Landing Gear is down and locked, speed can be increased up to 195 KIAS.

(AFM 1-03-40)

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40
Q

Max Operating Altitude for Extending Landing Gear or Flying With Landing Gear Extended

A

20,000 feet MSL

AFM 1-03-30

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41
Q

Max Operating Altitude for Extending Flaps or Flying With Flaps Extended

A

20,000 feet MSL

AFM 1-03-30

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42
Q

Minimum Control Speed Air (Vmca)

A

98 KIAS (Flaps 10 or 20)

Landing (Vmcl) = 98 KIAS
GROUND (Vmcg) = 95 KIAS

> Minimum Control Speeds in flap 0 configuration (abnormal for takeoff and landing) not established since it is lower than the airspeed at Stick Pusher activation in this configuration and is never a limiting factor for selection of takeoff and landing speeds.

(AFM 1-03-40)

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43
Q

Minimum Control Speed Landing (Vmcl)

A

98 KIAS (Flaps 10, 20 and LND)

Air (Vmca) = 98 KIAS
Ground (Vmcg) = 95 KIAS

(AFM 1-03-40)

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44
Q

Minimum Control Speed Ground (Vmcg)

A

95 KIAS (Flaps 10 or 20)

Air (Vmca) = 98 KIAS
Landing (Vmcl) = 98 KIAS

(AFM 1-03-40)

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45
Q

Minimum Control Speeds

A

Ground (Vmcg) = 95 KIAS (Flaps 10 or 20)
Air (Vmca) = 98 KIAS (Flaps 10 or 20)
Landing (Vmcl) = 98 KIAS (Flaps 10, 20 or LND)

(AFM 1-03-40)

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46
Q

Maximum Operating Speed (Vmo / Mmo)

Sea Level to 10,000 Feet

A

300 KCAS

10,000 to 20,000 feet = 300-330 KCAS
20,000 to 28,000 feet = 340 KCAS
28,000 to 45,000 feet = 0.85 Mi

(AFM 1-03-40)

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47
Q

Maximum Operating Speed (Vmo / Mmo)

10,000 to 20,000 Feet

A

300-330 KCAS

Sea Level to 10,000 feet = 300 KCAS
20,000 to 28,000 feet = 340 KCAS
28,000 to 45,000 feet = 0.85 Mi

(AFM 1-03-40)

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48
Q

Maximum Operating Speed (Vmo / Mmo)

20,000 to 28,000 Feet

A

340 KCAS

Sea Level to 10,000 feet = 300 KCAS
10,000 to 20,000 feet = 300-330 KCAS
28,000 to 45,000 feet = 0.85 Mi

(AFM 1-03-40)

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49
Q

Maximum Operating Speed (Vmo / Mmo)

28,000 to 45,000 Feet

A

0.85 Mi

Sea Level to 10,000 feet = 300 KCAS
10,000 to 20,000 feet = 300-330 KCAS
20,000 to 28,000 feet = 340 KCAS

(AFM 1-03-40)

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50
Q

Maximum Operating Speeds (Vmo / Mmo)

A

Sea Level to 10,000 feet = 300 KCAS
10,000 to 20,000 feet = 300-330 KCAS
20,000 to 28,000 feet = 340 KCAS
28,000 to 45,000 feet = 0.85 Mi

(AFM 1-03-40)

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51
Q

Turbulence Penetration Speed (Vra)

Sea Level to 13,000 Feet

A

230 KIAS

13,000 to 20,000 feet = 250 KIAS
20,000 to 35,000 feet = 270 KIAS
35,000 to 45,000 feet = 0.80 Mi

(AFM 1-03-40)

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52
Q

Turbulence Penetration Speed (Vra)

13,000 to 20,000 Feet

A

250 KIAS

Sea Level to 13,000 feet = 230 KIAS
20,000 to 35,000 feet = 270 KIAS
35,000 to 45,000 feet = 0.80 Mi

(AFM 1-03-40)

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53
Q

Turbulence Penetration Speed (Vra)

20,000 to 35,000 Feet

A

270 KIAS

Sea Level to 13,000 feet = 230 KIAS
13,000 to 20,000 feet = 250 KIAS
35,000 to 45,000 feet = 0.80 Mi

(AFM 1-03-40)

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54
Q

Turbulence Penetration Speed (Vra)

35,000 to 45,000 Feet

A

0.80 Mi

Sea Level to 13,000 feet = 230 KIAS
13,000 to 20,000 feet = 250 KIAS
20,000 to 35,000 feet = 270 KIAS

(AFM 1-03-40)

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55
Q

Turbulence Penetration Speeds (Vra)

A

Sea Level to 13,000 feet = 230 KIAS
13,000 to 20,000 feet = 250 KIAS
20,000 to 35,000 feet = 270 KIAS
35,000 to 45,000 feet = 0.80 Mi

(AFM 1-03-40)

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56
Q

Yaw Damper Inoperative:
> Maximum Speed
> Maximum Altitude

A

250 KIAS / 25,000 feet

AFM 1-03-40

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57
Q

Mach Trim Inoperative Speed

A

340 KIAS / 0.77 Mi

> With Mach Trim functions inoperative, the maximum Operating limit speed is 340 KIAS / 0.77 Mi.

(AFM 1-03-40 and 1-27-11)

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58
Q

Alternate Stabilizer Trim Speed Limitation

A

Mmo = 0.77 Mi

AFM 1-03-40

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59
Q

Maneuvering Flight Load Factors

A

> Flaps Up = -1.0 G to 2.6 G for all weights up to maximum takeoff weight.

> Flaps Down = 0 G to 2.0 G for all weights up to maximum takeoff weight.

(AFM 1-03-50)

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60
Q

Maximum Baggage Compartment Loading Weight and Floor Loading Limitation

A

1980 pounds max loading weight.

120 pounds per square foot max floor loading.

(AFM 1-03-60)

Also, note that there is 154 cubic feet of space (usable volume) in the Baggage Compartment (notes from slide #33 in FSI G-280 Initial Aircraft General PPT, the reference is Gulfstream’s website).
The FSI PTH (page 1-5 in rev. 2.1) says the volume is 120 cubic feet.

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61
Q

Internal Baggage Door Limitations

A

> Must be closed during taxi, takeoff and landing. (Either MOD aircraft).

> In-Flight access to the baggage compartment above 40,000 feet is prohibited except by flight crewmembers for emergency purposes only. (Pre MOD G25-10066).

> In-Flight, access to the baggage compartment above 44,000 feet is prohibited except by flight crewmembers for emergency purposes only. (Post MOD G25-10066).

(AFM 1-21-20)

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62
Q

Max Tailwind Component for Takeoff and Landing

A

10 knots

AFM 1-02-10

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63
Q

Max Airport Pressure Altitude for Takeoff and Landing

A

> AFM Issue 1 Aircraft = 10,000 Feet

> AFM Issue 2 Aircraft = 14,000 Feet

(AFM 1-02-20)

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64
Q

Minimum and Maximum Operating Altitude

A

-1,400 feet (min), and
45,000 feet (max)

(AFM 1-03-30)

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65
Q

Terrain Awareness Warning System (TAWS) Limitation

A

> The terrain awareness display feature shall be selected OFF (TERRAIN INHIBIT Switch - ON) when within 15 NM of landing at an airport when:

1) The airport has no published instrument approach procedures,
2) The longest runway is less than 3,500 feet in length,
3) The airport is not in the database,
4) QFE altimeter setting are used for approach and landing on subsequent takeoff without the availability of geometric altitude.

NOTE: Obstacles that are less than 1,000 ft AGL are not displayed as obstacle symbols on the MAP display. These obstacles are included as part of the terrain display.

(AFM 1-34-42)

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66
Q

QNH Altimeter Setting

A

Altimeter set to the local Barometric Pressure, altimeter will read you altitude with airplane on the runway surface.

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67
Q

QNE Altimeter Setting

A

Altimeter set to the International Standard Atmosphere (ISA) (e.g. 29.92 in. Hg), altimeter will read your Flight Level.

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68
Q

QFE Altimeter Setting

A

Altimeter set so it reads your height - when airplane is on the runway surface the altimeter will read zero (0) feet.

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69
Q

QNH, QNE and QFE Altimeter Settings

A

> QNH: Altimeter set to the local Barometric Pressure, altimeter will read your altitude with airplane on the runway surface.

> QNE: Altimeter set to the International Standard Atmosphere (ISA) (e.g. 29.92 in. Hg), altimeter will read your Flight Level.

> QFE: Altimeter set so it reads your height - when airplane is on the runway surface the altimeter will read zero (0) feet.

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70
Q

Climbing through what altitude will the Landing Lights automatically extinguish?

A

18,000 feet

> They will automatically illuminate on descent through 18,000 feet if the crew has left the switches in the ON position.
The PULSE option remains operable above 18,000 feet.
This prevents bulb failure caused by thermal shock at high altitudes.

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71
Q

Extended Overwater Flight

A

Extended over-water operation means:
For other than helicopters, an operation over water at a horizontal distance of more than 50 nautical miles from the nearest shoreline.

(AFM 1-03-10, #5 - “Types of Airplane Operations Permitted”)

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72
Q

Max Fuel Weight

A

14,620 pounds (2179.1 gallons)

Total usable fuel weight when gravity refueling is: 9,760 pounds.

Gravity refueling only fills the wing and feed tanks and can take a significantly longer time.

(AFM 1-28-10)

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73
Q

Initial Cruise Altitude

A

FL410

OM 2A-06-40, 7

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74
Q

Cabin Altitude at FL450

A

7000 feet

OM 2A-06-10

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75
Q

Seat Dependent Tasks Training

Right Seat

A

The FSB has found the following right seat dependent tasks for the G280:

> Passenger Oxygen System activation (right seat).
Emergency Landing Gear extension (ELG Handle).

(FSB Report, (rev. 4), 5.2.4)

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76
Q

Main Entrance Door (MED)

Dimensions and Weight

A

> 33 in. x 72 in. (2 feet and 9 inches by 6 feet).

> Approximately 161 pounds.

(AOM 2A-06-30)

77
Q

What provides the hydraulic pressure for the Main Entrance Door actuator?

A

The Left Electric Motor Pump(EMP), which is controlled by the door operating switches.

78
Q

Usable Storage Space in the Baggage Compartment

A

154 cubic feet

FSI Aircraft General, slide 33 notes - Gulfstream’s website

79
Q

G-280 Floorplans

A

> Hallmark: 10 passengers. Club seating forward and an aft four-place conference grouping opposite a two-place divan. Berthing for five.

> Universal: 9 passengers. In a four-place club setting forward and two facing seats, and a three-place divan positioned across the aisle in the aft cabin. Berthing for four.

> Executive: 8 passengers. Two club settings that can be configured to offer berthing for four.

(There are, of course, other possible plans)

80
Q

External Baggage Compartment Door Dimensions and Door Seal Description

A

> 31 x 33 inch plug type door (OM 2A-06-30, figure 6).

> Door Seal: When the door is closed and locked, a pnuematically inflated door seal fills the space between the baggage door and door frame on the fuselage, allowing the compartment to be pressurized and climate controlled so that it may be entered during flight … When the cabin is pressurized, the door is pushed against the seal, which is compressed further, till the door is stopped physically by means of ten (10) adjustable stoppers and pads located on the door frame. (OM 2A-52-40).

81
Q

Baggage Compartment Weight Limitation

A

> 1980 pounds.

> 120 pounds per square feet (120 lb. / sq. ft.)

(AFM 1-03-60)

82
Q

Internal Baggage Compartment Access In-Flight Limitation

A

Internal baggage door must be closed during taxi, takeoff and landing. In flight, access to the baggage compartment above 40,000 feet (for Pre MOD G25-10066), or above 44,000 feet (for Post MOD G25-10066), is prohibited except by flight crew members for emergency for emergency purposes only.

(AFM 1-21-20)

83
Q

Lavatory Door Limitations

A

Lavatory door must be closed for taxi, takeoff and landing (the door being open, and then slamming shut may cause damage to the door jam and potentially ground the aircraft if the door cannot be secured).

Lavatory not approved as a “occupied seat” during taxi, takeoff and landing.

84
Q

Function of the FMS

A

POSITION - GUIDANCE - PERFORMANCE

POSITION: (Where Am I?) Develops composite position using multiple sensor inputs.

GUIDANCE: (Where Am I Going?) Calculates lateral and vertical navigation guidance for display and coupling to the Flight Guidance System.

PERFORMANCE: (Can I Get To Where I Am Going?) Calculates all performance information.

85
Q

Type of HUD

A

Rockwell Collins HGS-6250 Head-Up Display

86
Q

Type of EFVS

A

Kollsman EVS II Cooled-FLIR (EVS)

87
Q

Powerplant Type

A

Honeywell HTF 7250G
> HTF 7250G Integrated PowerPlant System (IPPS) with an AS907-2-1G advanced technology turbofan engine.
> Static Takeoff Thrust (sea level): 7,624 lb.
> Maximum Continuous Thrust: 7,240 lb.
(Why couldn’t it have been 7,250?)
> Engine Bypass Ratio: 4.2:1
> Engine Pressure Ratio: 16.0:1

(AFM 1-71-00)

88
Q

Static Takeoff Thrust of Powerplant

A

7,624 lb. (sea level)

AFM 1-71-00

89
Q

Maximum Continuous Thrust of Powerplant

A

7,240 lb.
(Why couldn’t it have been 7,250?)

(AFM 1-71-00)

90
Q

Engine Bypass Ratio

A

4.2:1

AFM 1-71-00

91
Q

Engine Pressure Ratio

A

16.0:1

AFM 1-71-00

92
Q

APU Type

A

Honeywell GTCP36-150
* GTCP means Gas Turbine Compressor Power.
* Operational up to FL400.
* Can be started as high as FL350.
* Requirements for start:
> DC power from the #2 battery (right),
> Fuel supply, and
> Control input signals from the computer.
* Max altitude for APU bleed air is 20,000 feet.
* Max permissible EGT:
> During start below 50% RPM: 974 C (transient).
> Running: 718 C.
> Bleed air in use: 666 C.

93
Q

Max Operational Altitude for APU

A

FL400

94
Q

Max Starting Altitude for APU

A

FL350

95
Q

Max Altitude for APU Bleed Air

A

20,000 feet

96
Q

Max APU EGT During Start Below 50% RPM

A

974 C (transient)

97
Q

Max APU EGT Running

A

718 C

98
Q

Max APU EGT with Bleed Air in Use

A

666 C

99
Q

Nosewheel Steering Angles for:
> Tiller
> Rudder Pedals
> Towing

A

> Tiller: 60 degrees +/- 2.5
Rudder Pedals: 3 degrees
Towing: 100 degrees (with a tow-bar)
(90-95 tow-bar less)

(OM 2A-32-50)

100
Q

Minimum Taxiway Width for a 180 Degree Turn

A

Approximately 52 feet
> 51.6 feet (60 degree steering angle)
> 49.5 feet (62.5 degree steering angle)

(OM 2A-06-20)

101
Q

Nosewheel Steering (NWS) Alert Horn and Oversteer Flag

A

> Alert Horn: Activated at 80 degrees of turn. If the NWS horn sounds during towing, immediately reduce the towing angle. (80 degrees +/- 4), (power for the horn is from the Left Hot Bus).

> NWS Oversteer Flag: Activates at 93 degrees of steering, and activates an amber “NWS OVERSTEER” CAS message. If these are set, a maintenance reset and inspection are required. Also, steering unit hard stops may be sheared and a red overtravel warning indicator will pop up on the steering unit collar.

(OM 09-01-20)

102
Q

Crew Requirements for Aircraft Towing

A

> Minimum for towing is 2 people: Brake Rider and a Tow Vehicle Operator.

> Towing in a confined area requires a minimum of 5 people: Brake Rider and a Tow Vehicle Operator, plus 2 Wing Walkers and a Tail Walker.

(OM 09-01-20, 3B (3) and (8))

  • Prior to towing the aircraft, the nosewheel steering shall be selected to the OFF position.
103
Q

Minimum Parking Brake Accumulator Pressure for Setting the Parking Brake

A

Either 1,700 psi or 1,300 psi

> OM (09-01-20, 3B (5)): “Check parking brake accumulator pressure on the brakes or hydraulics synoptic for available pressure. The indicator should read 3000 psi for full charge to 1700 psi minimum for Setting the parking brake. If below 1700 psi, charge the accumulator using the AUX pump.”

> AFM (Before Starting Engines checklist, Note for item#4): “If hydraulic accumulators pressure is less than 1300 psi, operate associated EMPs until pressure is 2900 psi.” (Also in QRH).

104
Q

Minimum Parking Brake Accumulator Pressure for Setting the Parking Brake

A

Either 1,700 psi or 1,300 psi

> OM (09-01-20, 3B (5)): “Check parking brake accumulator pressure on the brakes or hydraulics synoptic for available pressure. The indicator should read 3000 psi for full charge to 1700 psi minimum for Setting the parking brake. If below 1700 psi, charge the accumulator using the AUX pump.”

> AFM (Before Starting Engines checklist, Note for item#4): “If hydraulic accumulators pressure is less than 1300 psi, operate associated EMPs until pressure is 2900 psi.” (Also in QRH).

105
Q

Windows in the Passenger Cabin

A

> 19 elliptical windows, 9 on left and 10 on right.
Size is approximately 12 x 15 inches.
Watertight, constructed from 2 acrylic layers bonded together with a resin.
8th window back on right side is a Type III emergency exit door and opens inward (can be opened from either the inside or outside), but cannot be opened when the aircraft is pressurized.
Emergency exit has a lock (with a flag assembly) for securing the aircraft (essential at foreign airports and Security Identification Display Areas - SIDA - normally, the flight ramp and other sensitive operational areas).

106
Q

Location of Life Vests, Life Raft, and First Aid Kit

A

Life Vests: Under seats in the main cabin.

Life Raft and First Aid Kit: Storage closet on the left hand side of aircraft just aft of the entry door (in accordance with the buyer selected / Gulfstream approved design package).

107
Q

APU Fuel Burn

A

Loaded: 150 pounds per hour.
(Also, remember that coincidentally, the APU model is the Honeywell GTCP 36-150, and the APU weight is about 150 pounds).

Unloaded: 60 pounds per hour.

108
Q

Items on the Powerplant Accessory Gear Box

A

Remember: “3 Pumps, 2 Electrics”

Pumps: Oil, Hydraulic, Fuel.

Electric: Generator, PMA.

109
Q

Maximum Tailwinds and Crosswinds for:
> Engine Start (On Ground), and
> Takeoff and Landing

A

Remember: “10-15-20-25”

10: Max Tailwind (Takeoff & Landing)
15: Max Tailwind (Engine Start - Ground)
20: Max Crosswind (Engine Start - Ground)
25: Max Crosswind (Takeoff & Landing)

110
Q

G-280 Fire Extinguishers

A

Cabin / Cockpit:
3 Halon 1211
1 Water

Engine Nacelles:
2 Halon 1301 bottles

111
Q

QRH Normal Checklists

Dark Cockpit to Landing Sequence

A 
>  First Flight of the Day (NA-1)
    *  FLOW:  Starting APU
>  Cockpit Preflight Inspection (NA-2)
>  Exterior Inspection (NA-4)
>  APU Start (On Ground) (NB-1)
>  Before Starting Engines (NC-1)
>  Engine Start (NC-5)
>  After Start (ND-1)
>  Taxi / Before Takeoff (ND-9)
>  Line Up (NE-1)
>  Climb (NF-1)
>  Cruise (NF-1)
>  Before Descent (NF-3)
>  Descent Transition (NF-4)
>  Before Landing (NF-5)
112
Q

Maximum Wing Fuel Imbalance for:

  • Takeoff, and
  • In Flight, Approach and Landing
A

Takeoff: 450 pounds

In Flight, Approach and Landing: 900 pounds

(AFM 1-03-80)

113
Q

Hydraulic Fluids

A

Preferred Fluid:
Skydrol LD IV (Monsanto Co.)

Hydraulic Fluids conforming to the G-280 Aircraft Maintenance Manual:
Fire Resistance Phosphate Ester SAE 1421 Type IV Class 1

(AFM 1-12-10)

114
Q

Maximum Cabin Pressure Differential Permitted

A

9.2 psi

(Max for taxi, takeoff or landing is 0.2 psi)

(AFM 1-21-10)

115
Q

Maximum Cabin Pressure Differential Permitted for Taxi, Takeoff or Landing

A

0.2 psi

(Max cabin pressure differential Permitted is 9.2 psi)

(AFM 1-21-10)

116
Q

Autopilot Limitations

A

Minimum Engage Height:
200 feet.

Minimum Disengage Height from an ILS, LPV or LNAV / VNAV Approach:
80 feet.

Maximum Demonstrated Altitude Loss for a Coupled Go-Around:  
61 feet (DDA addition is 70 feet).

CAT II operation is not approved for single engine operations.

(AFM 1-22-30)

117
Q

Autopilot Minimum Engage Height

A

200 feet

AFM 1-22-30

118
Q

Autopilot Minimum Disengage Height from an ILS, LPV or LNAV / VNAV Approach

A

80 feet

AFM 1-22-30

119
Q

Maximum Demonstrated Altitude Loss for a Coupled Go-Around

A

61 feet (DDA addition is 70 feet)

AFM 1-22-30

120
Q

Engine Generator and APU Starter / Generator Limitations

A

Ground and flight operations:
100% maximum continuous.

(AFM 1-24-10 and 1-24-20)

121
Q

Maximum Indicated Battery Charge Current for Takeoff

A

> APU GEN Available: 20A.

> APU GEN Unavailable: 8A.

NOTE: APU Generator Available means it is operable, if needed, and not deferred per MEL. The APU does not have to be running to be considered available.

(AFM 1-24-30)

122
Q

Takeoff Flaps Setting Limitation

A

> The selected takeoff flaps setting must be confirmed by both pilots as the takeoff flaps setting for which takeoff performance has been calculated.

> WARNING: Failure to verify the flap setting for takeoff may result in takeoff rotation at an incorrect Vr speed with potential loss of controlled flight.

(AFM 1-27-20)

123
Q

Total Usable Fuel Volume,
Total Usable Fuel Weight, and
Total Usable Fuel Weight when Gravity Refueling

A

> Total usable fuel volume: 2179.1 US gallons.

> Total usable fuel weight: 14,620 lb. (at 6.7 lb. / US gallon).

> Total usable fuel weight when gravity refueling: 9,760 lb. (at 6.7 lb. / US gallon).
(Gravity refueling only fills the wing and feed tanks and can take a significantly longer time).

(AFM 1-28-10)

124
Q

Total Usable Fuel Volume

A

2179.1 US gallons

AFM 1-28-10

125
Q

Total Usable Fuel Weight

A

14,620 lb. (at 6.7 lb. / US gallon)

AFM 1-28-10

126
Q

Total Usable Fuel Weight when Gravity Refueling

A

9,760 lb. (at 6.7 lb. / US gallon)

(Gravity refueling only fills the wing and feed tanks and can take a significantly longer time)

(AFM 1-28-10)

127
Q

Fuel Tank Temperature Limitation

A

> Flight is prohibited when indicated fuel tank temperature is outside the minimum or maximum specified below:

Jet A:
Min Temp = -38 C.
Max Temp = 57 C.

Jet A-1 and JP-8:
Min Temp = -46 C.
Max Temp = 57 C.

(AFM 1-28-20)

128
Q

Left and Right Brake Accumulator Pre-Charge Pressure

A

700 +/- 30 psi at 70 F (21 C)

(+/- 25 psi for each increment of 10 F (5 C))

(AFM 1-29-10)

129
Q

Emergency Gear Bottle Pre-Charge Pressure

A

2600 to 3000 psi at 70 F (21 C)
(+/- 25 psi for each increment of 10 F (5 C))

(AFM 1-29-10)

130
Q

Hydraulic Pressure Limitations

Normal Operation and Maximum

A

> Normal Operation = 2700 to 3250 psi

> Maximum = 3500 psi

(AFM 1-29-20)

131
Q

Maximum Hydraulic Temp

A

95 C

> A temp sensor activates a CAS message (amber “HYD Reservoir Hot, L-R”) at temperatures above 221 F (105 C)* and inhibits automatic electric motor pump operation, manual selection still available.
(OM 2A-29-20, 2C)

  • Note: This temperature (221 F / 105 C) is listed as 95 C in the AFM and QRH.

> If both systems reach 135 C (275 F), Right Engine shut-down is recommended.
(AFM 111A-184)

(AFM 1-29-30)

132
Q

Electric Motor Pump (EMP) Operation Limitation

A

Operation above 39,000 ft. is limited to 10 minutes.

AFM 1-29-30

133
Q

Icing Conditions Exist When …

A

… the Static Air Temperature (SAT) on the ground and for takeoff, or TAT in flight is 10 C (50 F) or below, and visible moisture in any form is present (such as clouds, fog with visibility of one mile or less, rain, snow, sleet and ice crystals).
Also, when the SAT on the ground and for takeoff is 10 C (50 F) 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.

  • For wing anti-icing, “the icing envelope is defined as +10 C TAT to -40 C TAT with visible moisture present.”

(AFM 1-30-10 and 1-30-20)

134
Q

The use of Wing Anti-Ice is not recommended …

A

Above +10 C TAT or below -40 C TAT

AFM 1-30-10 and 1-30-20

135
Q

Ice and Rain Protection:

Takeoff is prohibited with …

A

… frost, ice, snow, or slush adhering to the wings, horizontal and vertical stabilizer, control surfaces, engine inlets, or other critical surfaces (top of the fuselage as well should be clean, may accrete a lot of ice).

(AFM 1-30-10)

136
Q

Operation of wing anti-icing is required if …

A

… icing conditions are imminent, or immediately upon detection of ice formation on wings, winglets or windshield edges.

(AFM 1-30-20)

137
Q

Operation of wing anti-ice system is prohibited …

A

… above 26,000 ft. with a single Bleed source.

AFM1-30-20

138
Q

Wing anti-ice must be ON for …

A

… takeoff if in icing conditions or icing conditions are anticipated.

Warning: Minute amounts of ice or other contamination on the leading edges or wing upper surfaces can result in a stall without warning, leading to loss of control on takeoff.

(AFM 1-30-20)

139
Q

Probe Heat OVRD Limitation

A

Probe Heat operation in OVRD mode on ground for more than 30 seconds is prohibited.

(AFM 1-30-21)

140
Q

Engine anti-ice is required …

A

… for taxi and takeoff when the Static Air Temperature (SAT) is 10 C (50 F) or below and in-flight when the Total Air Temperature (TAT) is 10 C (50 F) or below, and visible moisture in any form is present such as clouds, fog with visibility of one mile or less, rain, snow, sleet and ice crystals.

(AFM 1-30-30)

141
Q

Flaps in Icing Conditions Limitations

A

> Use of flaps in icing conditions is restricted to takeoff, approach and landing only.

> Holding in icing conditions is limited to 0 degree flaps (Flaps UP) only.

(AFM 1-30-40)

142
Q

CAS Aural Inhibit Limitation

A

The use of CAS aural inhibit to disable CAS aural alert is prohibited unless called for through specific AFM abnormal procedure related to failure of the crew alerting system itself.

(AFM 1-31-10)

143
Q

Universal Serial Bus (USB) Data Loading Limitations

A

1) Access to Universal Serial Bus (USB) data loading port is limited to flight crew and other authorized personnel only.
2) USB port data loading actions limited to dedicated computer(s) that are isolated from the internet, and dedicated USB memory stick(s).

(AFM 1-31-20)

144
Q

Terrain Awareness Warning System (TAWS) Obstacles On MAP Display

A

NOTE: Obstacles that are less than 1000 ft. AGL are not displayed as obstacle symbols on the MAP display. These obstacles are included as part of the terrain display.

(AFM 1-34-42)

145
Q

When shall the terrain awareness display feature be selected OFF (TERRAIN INHIBIT Switch - ON)?

A

When within 15 NM of landing at an airport when:

  • The airport has no published instrument approach procedure,
  • The longest runway is less than 3500 ft.,
  • The airport is not in the database,
  • QFE altimeter settings are used for approach and landing on subsequent takeoff without the availability of geometric altitude.

(AFM 1-34-42)

146
Q

FMS Limitation

V speeds and Performance Data, and FMS Calculated Takeoff and Landing Weights

A

> V speeds and performance data is advisory and must be verified against the performance data contained in Section V - Performance.

> The flight crew is required to verify FMS calculated takeoff and landing weights before posting the V speeds using the SMC display for fuel quantity data.

(AFM 1-34-60)

147
Q

FMS Holding Entry Limitation

A

When entering a holding pattern via a direct entry that requires greater than 180 degrees of turn, select the Heading mode (HDG) immediately after sequencing the hold fix to turn to the outbound leg. Once stablished on the outbound leg, FMS lateral guidance (LNAV) can be re-selected.

(AFM 1-34-60)

148
Q

FMS Holding Exit Limitation

A

When exiting a hold with a course reversal that is not part of a published procedure the aircraft may turn in a direction opposite the turning arrow. Therefore, pilot is required to monitor the turning direction of the aircraft or manually fly the turn after the exit.

(AFM 1-34-60)

149
Q

APPR Mode for LOC Approaches Limitation

A

APPR mode for LOC approaches should be selected only when within 60 degrees of approach course.

(AFM 1-34-60)

150
Q

ETP (Equal Time Point function) Limitation

A

Use of ETP function in the FMS for calculation of the Equal Time Point is prohibited.

(AFM 1-34-60)

151
Q

Electronic Checklist Limitation

A

Electronic checklist normal procedures only are approved for operational use.

(AFM 1-34-130)

152
Q

Crew and passenger oxygen masks are not approved for use above what altitude?

A

Above 40,000 ft. Cabin Altitude

  • Also, hats and “earmuff” type headsets must be removed prior to donning crew oxygen masks.

NOTE: Headsets and eyeglasses worn by crewmembers may interfere with quick-donning capabilities.

(AFM 1-35-10)

153
Q

When is prolonged operation with passengers on board not recommended?

A

Above 25,000 Cabin Altitude

AFM 1-35-10

154
Q

Operation of OMS (Onboard Maintenance System) Limitation

A

Operation of the OMS in flight is limited to altitudes at or above 10,000 ft.

(AFM 1-45-00)

155
Q 
Powerplant EICAS Indications and
General EICAS Range Markings Colors for:
*  Normal Range Values,
*  Caution Range Values, and
*  Warning Range Values
A

> Normal Range Values = White

> Caution Range Values = Amber (Inverse Video)

> Warning Range Values = Red (Inverse Video)

(AFM 1-45-10 and 1-45-20)

156
Q

Fuel Tank Temperature Indications (EICAS) for:

  • Normal Range Values,
  • Abnormal Values, and
  • Low Temperature
A

> Normal Range Values = White

> Abnormal Values = Inverse Video

> Low Temperature = Amber (Minimum fuel temperature at the fuel filter is 3 C, AFM 1-73-10)

(AFM 1-45-30)

157
Q

APU EICAS Indications (for APU RPM) for:

  • 106% and above,
  • 104% to 105%, and
  • 0% to 103%
A

> 106% and above = Red Digits
104% to 105% = Amber Digits
0% to 103% = White Digits

(AFM 1-45-40)

158
Q

CAS Messages for Dispatch Limitation

A

> Amber CAS messages are normally DO NOT DISPATCH messages as the systems that generate these messages are required for flight.

> Cyan maintenance messages allow dispatch as the systems that generate these messages are fault tolerant. Referencing to the AFM procedure may provide a solution to the system problem, but if any message remains, reference the MEL for dispatch.

(AFM 1-45-50)

159
Q

Maximum Altitude for:

  • APU Start,
  • APU Operation, and
  • APU Bleed Air Use
A

> APU Start = 35,000 feet

> APU Operation = 40,000 feet

> APU Bleed Air Use = 20,000 feet

(AFM 1-49-10)

160
Q

If the right fire extinguisher has been activated, what limitation applies?

A

Do not operate APU if right fire extinguisher has been activated.

(AFM 1-49-10)

161
Q

Is the APU approved for unattended operations?

A

Yes
(On The Ground only, of course)

(AFM 1-49-10)

162
Q

APU Start Limitation

A

Allow 2 minutes cool down periods between APU starts or between shutdown and next APU start. After 3 consecutive starts, allow 30 minutes cool down period.

START - 2 MIN -
START - 2 MIN -
START - 30 MIN

(AFM 1-49-10)

163
Q

APU Operation Fuel Supply Limitation

A

Operate APU only if right standby fuel pump is operative or right engine is operative.

(AFM 1-49-10)

164
Q

APU Approved Fuels and Oils

A

Same as main engine

AFM 1-49-10

165
Q

APU Limitation for Ground Aircraft De-Icing

A

APU must be off with door closed

AFM 1-49-10

166
Q

APU Generator Load Limits
and
APU Maximum Rotor Speed

A

Generator Load Limits = 100%

Maximum Rotor Speed (all conditions) = 108%

(AFM 1-49-10)

167
Q

APU Maximum Permissible EGT for:

  • Start,
  • Running, and
  • Bleed Air in Use
A

> Start = Maximum Transient EGT during APU Start, below 50% RPM is 974 C.

> Running = 718 C.

> Bleed Air in Use = 666 C.

(AFM 1-49-10)

168
Q

Powerplant Type and Thrust Ratings for:

  • Maximum Continuous, and
  • Takeoff
A

> Type = Honeywell HTF 7250 G

> Maximum Continuous Thrust = 7240 lb. (Why couldn’t it have been 7250?).

> Takeoff = 7624 lb.

(AFM 1-71-00)

169
Q

Maximum Crosswind for Engine Start
and
Maximum Tailwind for Engine Start

A

> Crosswind = 20 kt.

> Tailwind = 15 kt.

(AFM 1-71-10)

170
Q

Maximum ITT During Ground Start

A

> N2 at or below 40% = 650 C.

> N2 above 40% = 950 C.

(AFM 1-71-10)

171
Q

Engine Ground Operations Limitations

A

> N1 is limited to 50% if tailwind component is more than 15 kt.

> When monitoring is required, it shall commence within 3 minutes after shutdown is commanded (fuel control switch to STOP).

> If landing with use of thrust reversers causes ITT to exceed limits, see “ENGINE MOTORING IN HOT WEATHER CONDITIONS (PRE MOD G25-20113)”, in AFM (page IV-64).

(AFM 1-71-20)

172
Q

Maximum N1, N2 and ITT Values for:

Max Continuous

A

> N1 (%) = 96.5

> N2 (%) = 98.0

> ITT (C) = 950

(AFM 1-71-30)

173
Q

Maximum N1, N2 and ITT Values for:

Takeoff (TO)

A

> N1 (%) = 96.8

> N2 (%) = 98.0

> ITT (C) = 955

(AFM 1-71-30)

174
Q

Maximum N1, N2 and ITT Values for:

Automatic Performance Reserve (APR)

A

> N1 (%) = 96.8

> N2 (%) = 98.5

> ITT (C) = 955

(AFM 1-71-30)

175
Q

Maximum N1, N2 and ITT Values for:

Transient (20 sec. max)

A

> N1 (%) = 98.0

> N2 (%) = 99.9

> ITT (C) = 970

(AFM 1-71-30)

176
Q

Maximum N1 (%) for:

  • Max Continuous,
  • Takeoff (TO),
  • Automatic Performance Reserve (APR), and
  • Transient (20 sec. max)
A

> Max Continuous = 96.5 %

> TO = 96.8 %

> APR = 96.8 %

> Transient = 98.0 % (20 sec. max)

(AFM 1-71-30)

177
Q

Maximum N2 (%) for:

  • Max Continuous,
  • Takeoff (TO),
  • Automatic Performance Reserve (APR), and
  • Transient (20 sec. max)
A

> Max Continuous = 98.0 %

> TO = 98.0 %

> APR = 98.5 %

> Transient = 99.9 % (20 sec. max)

(AFM 1-71-30)

178
Q

Maximum ITT (C) for:

  • Max Continuous,
  • Takeoff (TO),
  • Automatic Performance Reserve (APR), and
  • Transient (20 sec. max)
A

> Max Continuous = 950 C

> TO = 955 C

> APR = 955 C

> Transient = 970 C (20 sec. max)

(AFM 1-71-30)

179
Q

Takeoff Thrust is Limited to __ Minutes With All Engines Operating (AEO)

A

5 Minutes

AFM 1-71-30

180
Q

APR (Automatic Performance Reserve) is Limited to __ Minutes With an Inoperative Engine (OEI)

A

10 Minutes

  • Any APR or MPR activation must be logged for maintenance.

(AFM 1-71-30)

181
Q

Engine Fuel Temperature Limitation

A

Minimum fuel temperature at the fuel filter is:
3 C

(AFM 1-73-10)

182
Q

Thrust Reverser Limitations:

  • Reverse Idle by Speed, and
  • Power Back Limitations
A

> Cancellation of reverse thrust should be initiated so as to be at the reverse idle position by 40 KIAS.
* PM calls “70 knots” on landing rollout (FSI profile).

> Use of thrust reverser(s) for power back is not approved.

(AFM 1-78-10)

183
Q

Oil Inlet Temperature Before Engine Start Limitation

A

-40 C minimum

AFM 1-79-20

184
Q

Oil Inlet Temperature Continuous Operation Above Ground Idle Limitation

A

5 C minimum

AFM 1-79-20

185
Q

Oil Inlet Temperature Operation Above Climb Thrust Limitation

A

15 C minimum

AFM 1-79-20

186
Q

Oil Inlet Temperature Steady State Operation Limitation

A

138 C minimum

AFM 1-79-20

187
Q

Oil Inlet Temperature Transient Operation Limitation

A

154 C (not to exceed 2 minutes)

AFM 1-79-20

188
Q

AOA Indications for Approaching a Stall

A

> 0.78 = Amber UNDERSPEED CAS message

> 0.80 = PLI (Pitch Limit Indicator) appears

> 0.90 = Stick Shaker

> 1.0 = Stick Pusher

189
Q

Automation Setup for Approaches

Simplified - Quick Reference

A

DA = APP + VNAV + MINS
(Set MAA after vert mode is VGP or GS)

MDA = Make all MDAs a DDA (except Circle)
(* MDA + 70 feet in FLT REF)

DDA = APP + VNAV + Set Zero
(Last button after NAV to NAV transfer is LNAV for LOC, LOC B/C, or LDA)

Circle = Use MDA

Jason's Work Stuff (9 decks)

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