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78 Cards in this Set

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Take-Off and Landing Pressure Altitude Operational Envelope
-1000 ft to 8000 ft.
Temperature Operational Envelope
-40 degrees C to ISA +35 degrees C
Max. Altitude (PA)
37,000 ft
Max. Operating Temp.
ISA + 35 degrees C
Min. Operating Temp.
-54 degrees C to 25,000 ft.
-65 degrees C at 37,000 ft.
TAT in cruise above ______ is limited to ______
25,000 ft.
-45 degrees C
VLO (Retraction)
200 KIAS
VLO (Extension)
250 KIAS
VLE (Extended)
250 KIAS
Maximum Operating VMO/MMO
0 to 8000 ft. 250 KIAS
10,000 to 26,000 ft. 320 KIAS
26,000 to 37,000 ft. .78 Mach
Maneuvering VA
200 KIAS
Flap Extended VFE
Flaps 9 250 KIAS
Flaps 22 200 KIAS
Flaps 45 145 KIAS
Tailwind
10 Knots Maximum for Take-off and Landing
Direct Vision Window
Max to Remove: 140 KIAS (AFM)
Windshield Wiper
Max for Operation: 170 KIAS (AFM)
Turbulent Air Penetration (AFM)
At or below 10,000 ft. 200 KIAS
Above 10,000 ft. 250 KIAS/0.63 M
Whichever is lower
Load Factor Limit
Flaps Up -1.00 G to 2.50 G
Flaps Down (9, 22, 45)
0 G to 2.00 G
Maximum Ramp Weight
48,722 lbs
Maximum Take-Off Weight
48,501 lbs
Maximum Landing Weight
42,549 lbs
Maximum Zero Fuel Weight
39,462 lbs.
Maximum Aft Cargo Weight
2646 lbs.
Fuel
Specification: JET A, JET A-1, JP-8
Tank Temperature: -40 C to 52 C
Max Imbalance 800 lbs
Maximum Useable Quantity each Tank
844.9 US Gal. (5717 lbs.)
Unusable Quantity each Tank
5.8 US Gal. (39 lbs.)
Note 1 Fuel
Unusable fuel increases to 365 lbs. in each tank if any of the associated electric fuel pumps is inoperative.
Note 2 Fuel
When performing pressure refueling, the usable fuel quantity in each tank may be reduced by 13.2 US Gal.
Note 3 Fuel
The values above have been determined for an adopted fuel density of 6.767 lb/US Gal.
APU Model T-62-40C11 Parameters
Temperature Min -54 C
Altitude for start 25,000 ft or 30,000 ft (2)
Operational altitude 37,000 ft
Rotor Speed 108%
Start 884 C (1)
Continuous 680 C (6)
APU Model T-62T-40C14 Parameters
Altitude for start 30,000 ft.
Operational Altitude 37,000 ft.
Rotor Speed 108%
Start 884 C
Continuous 680 C (6)
Note 1 APU
May be exceeded up to 925 C above 25,000 ft. during 10 seconds
Note 2 APU
For airplanes Post-Mod. SB 145-0010 or equipped with an equivalent modification factory incorporated. In this case, the minimum temperature for APU start is -54 C up 30,000 ft.
Note 3 APU
Minimum battery temperature for APU start is -20 C
Note 4 APU
Refer to Fuel Tank Temperature limitations for other APU starting related limits.
Note 5 APU
The APU Model T-62T-40C14 will automatically be shut down at 104% rotor speed.
APU Note 6
The APU EGT may be exceeded up to 717 C for 5 minutes maximum
APU Starter Limits
Cooling period between each starting attempt:
Between three consecutive attempts...1 minute off
Between two series of three consecutive attempts... 30 minutes off
Engine Starter Limits on Ground:
Starting or Dry Motoring... Up to 5 minutes on, 5 minutes off OR
First to Fourth Cycles... 1 minute on, 1 minute off
Following Cycles.... 1 minute on, 5 minutes off
Engine Starter Limits in Flight
Maximum Continuous Operation Time.... 5 minutes on
Note.... No cool down time is required should an in-flight start be reattempted
ATTCS
Must be operative for ALT T/O-1 Mode
Reversers
Do not go-around after reverser deployment
AE3007A1 (LR)
N1, N2 Maximum parameters
100%
102.4%
ITT Start / Takeoff Mode Maximum limits
800 C
948 C (1)
Oil Pressure
Below 88% N2
Minimum 34 PSI
Maximum 110 psi (2) (7)
At or above 88% N2
Minimum 50 psi (9)
Maximum 110 psi (7)
Oil Temperature
Minimum 21 C (3)
Maximum 126 C
Fuel Temp
Minimum -54 C
Maximum 52 C
Vibration
LP Spool Maximum 1.8 IPS (4)
HP Spool Maximum 1.1IPS (4)
Engine Parameter Note 1
Takeoff Thurst is time limited to 5 minutes
Engine Parameter Note 2
May be exceeded during starts if oil temp. is below 21 C. The engine must remain at IDLE until the pressure is less than 110 psi.
Engine Parameter Note 3
Minimum oil temperature for starting is -40C for lubrication oil specified by MIL-L-23699D
Engine Parameter Note 4
Vibration in the amber range below 2.5 IPS is time limited to 5 minutes during the takeoff or go-around phases or 10 seconds during the remainder of the flight phases.
Engine Parameter Note 5
Any engine exceedance or peak must be monitored and logged by the crew.
Engine Parameter Note 7
Operation in oil pressure amber range between 111 and 115 psi is permitted in all operational modes and time limited to 5 minutes, or between 116 and 155 psi in all operational modes time limited to 2 minutes. Total time above 110 psi may not exceed 5 minutes.
Engine Parameter Note 8
For airplanes Pre-Mod. SB 145-73-0030 the N2 limit is 102.5%
Engine Parameter Note 9
While this is an abnormal condition, operation between 50 and 34 psi is permitted during takeoff and go around phases (for AE 3007A engines only).
Engine Warm-Up
Prior to take-off, the engines must be allowed to run at low thrust to stabilize the engine temperatures before take-off thrust is adjusted. After start, the engines must run at idle or taxi thrust during at least 4 minutes for cold engines (shut down for more than 90 minutes) or 2 minutes for warm engines. To increase N2 above 83% the engine oil temperature must be at 40 C minimum. In lieu of this limit, it is acceptable to either run the engine for at least 8 minutes or complete a static run-up to 88% N2, stabilize, and check to ensure that oil pressure is equal to or less than 83 psi
Engine Cool-Down
The engines must run for at least 1 minute at idle or taxi thrust before shut-down
Minimum/Maximum Temp for A/I operation
-40 C
10 C
Holding configuration icing conditions
Landing Gear.....UP
Flaps..... UP
Min. Airspeed....200 KIAS
Single-engine or single bleed in icing conditions
Max Altitude 15,000 ft.
SAT and TAT in icing
Use SAT on ground or for takeoff operations and TAT for operations in flight
Max. load on main generator
400 amps
Max. Load on APU generator
400 amps below 30,000 ft.
300 amps above 30,000 ft.
Max. Battery Temp.
70 C
Max Differential Pressure
7.8 psi
Max Differential Overpressure
8.1 psi
Max Differential Negative Pressure
-0.3 psi
Max. Altitude to Extend Flaps
20,000 ft.
Maximum Airpseed after Take-off/During Climb without Re-trimming
160 KIAS
Integrated Standby Instrument System (ISIS)
Maximum duration of ISIS when operating on batteries is only 40 minutes
Note: The maximum duration of battery power can be extended to 45 minutes if the Pitot 3 Sensor Heating Button is turned off when not operating in icing conditions
Airplane must not be moved during power-up initialization. Do not cage attitude in turning flight.
Electromechanical Gust Lock
Each time electromechanical gust lock lever is set to unlocked position elevator movement must be checked. This check must be performed at least 10 seconds after positioning the gust lock lever to the unlocked position by moving the control column from the full up stop to the full down stop and back to the full up stop position.
Cockpit Security Door
On airplanes equipped with a cockpit security door, two crewmembers must be in the cockpit during all flight phases.
If one of the pilots leaves the flight deck, he must be replaced in the cockpit by another crewmember.
Positive identification of the person wishing to enter the flight deck must be obtained before opening the door.
The security cockpit door must be kept closed and locked at all times during flight except to permit access and egress according to GOM procedures 6-1.2.1 for opening, closing, and locking the door.
Anytime that cockpit door is opened in flight, a challenge and response closing and locking verification procedure must be used to verify that the door is closed and locked.
Autopilot Min Altitude Coupled to ILS
200 ft.
Autopilot Min. Engagement Height After Takeoff
500 ft.
Autopilot single-engine go-around
prohibited
Max Recommended Crosswind (Non-AFM)
Dry Runway..........30 knots
Wet Runway........30 knots
Runway with compacted snow.... 25 knots
Runway with Standing Water or Slush.... 20 knots
Runway with Ice (no melting) 10 knots
Bleed / Pack Condition
Maximum operating altitude when one bleed or one pack is closed is 25,000 ft. (AFM).
When operating with APU bleed supplying pack 1 (Eng. 1 bleed - closed) and engine 2 supplying Pack 2 (crossbleed closed), maximum operating altitude is 37,000 ft. (Non-AFM)