Trans States Limitations

Front 1

Take-Off and Landing Pressure Altitude Operational Envelope

Back 1

-1000 ft to 8000 ft.

Front 2

Temperature Operational Envelope

Back 2

-40 degrees C to ISA +35 degrees C

Front 3

Max. Altitude (PA)

Back 3

37,000 ft

Front 4

Max. Operating Temp.

Back 4

ISA + 35 degrees C

Front 5

Min. Operating Temp.

Back 5

-54 degrees C to 25,000 ft.
-65 degrees C at 37,000 ft.

Front 6

TAT in cruise above ______ is limited to ______

Back 6

25,000 ft.
-45 degrees C

Front 7

VLO (Retraction)

Back 7

200 KIAS

Front 8

VLO (Extension)

Back 8

250 KIAS

Front 9

VLE (Extended)

Back 9

250 KIAS

Front 10

Maximum Operating VMO/MMO

Back 10

0 to 8000 ft. 250 KIAS
10,000 to 26,000 ft. 320 KIAS
26,000 to 37,000 ft. .78 Mach

Front 11

Maneuvering VA

Back 11

200 KIAS

Front 12

Flap Extended VFE

Back 12

Flaps 9 250 KIAS
Flaps 22 200 KIAS
Flaps 45 145 KIAS

Front 13

Tailwind

Back 13

10 Knots Maximum for Take-off and Landing

Front 14

Direct Vision Window

Back 14

Max to Remove: 140 KIAS (AFM)

Front 15

Windshield Wiper

Back 15

Max for Operation: 170 KIAS (AFM)

Front 16

Turbulent Air Penetration (AFM)

Back 16

At or below 10,000 ft. 200 KIAS
Above 10,000 ft. 250 KIAS/0.63 M
Whichever is lower

Front 17

Load Factor Limit

Back 17

Flaps Up -1.00 G to 2.50 G
Flaps Down (9, 22, 45)
0 G to 2.00 G

Front 18

Maximum Ramp Weight

Back 18

48,722 lbs

Front 19

Maximum Take-Off Weight

Back 19

48,501 lbs

Front 20

Maximum Landing Weight

Back 20

42,549 lbs

Front 21

Maximum Zero Fuel Weight

Back 21

39,462 lbs.

Front 22

Maximum Aft Cargo Weight

Back 22

2646 lbs.

Front 23

Fuel

Back 23

Specification: JET A, JET A-1, JP-8
Tank Temperature: -40 C to 52 C
Max Imbalance 800 lbs

Front 24

Maximum Useable Quantity each Tank

Back 24

844.9 US Gal. (5717 lbs.)

Front 25

Unusable Quantity each Tank

Back 25

5.8 US Gal. (39 lbs.)

Front 26

Note 1 Fuel

Back 26

Unusable fuel increases to 365 lbs. in each tank if any of the associated electric fuel pumps is inoperative.

Front 27

Note 2 Fuel

Back 27

When performing pressure refueling, the usable fuel quantity in each tank may be reduced by 13.2 US Gal.

Front 28

Note 3 Fuel

Back 28

The values above have been determined for an adopted fuel density of 6.767 lb/US Gal.

Front 29

APU Model T-62-40C11 Parameters

Back 29

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)

Front 30

APU Model T-62T-40C14 Parameters

Back 30

Altitude for start 30,000 ft.
Operational Altitude 37,000 ft.
Rotor Speed 108%
Start 884 C
Continuous 680 C (6)

Front 31

Note 1 APU

Back 31

May be exceeded up to 925 C above 25,000 ft. during 10 seconds

Front 32

Note 2 APU

Back 32

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.

Front 33

Note 3 APU

Back 33

Minimum battery temperature for APU start is -20 C

Front 34

Note 4 APU

Back 34

Refer to Fuel Tank Temperature limitations for other APU starting related limits.

Front 35

Note 5 APU

Back 35

The APU Model T-62T-40C14 will automatically be shut down at 104% rotor speed.

Front 36

APU Note 6

Back 36

The APU EGT may be exceeded up to 717 C for 5 minutes maximum

Front 37

APU Starter Limits

Back 37

Cooling period between each starting attempt:
Between three consecutive attempts...1 minute off
Between two series of three consecutive attempts... 30 minutes off

Front 38

Engine Starter Limits on Ground:

Back 38

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

Front 39

Engine Starter Limits in Flight

Back 39

Maximum Continuous Operation Time.... 5 minutes on
Note.... No cool down time is required should an in-flight start be reattempted

Front 40

ATTCS

Back 40

Must be operative for ALT T/O-1 Mode

Front 41

Reversers

Back 41

Do not go-around after reverser deployment

Front 42

AE3007A1 (LR)
N1, N2 Maximum parameters

Back 42

100%
102.4%

Front 43

ITT Start / Takeoff Mode Maximum limits

Back 43

800 C
948 C (1)

Front 44

Oil Pressure
Below 88% N2

Back 44

Minimum 34 PSI
Maximum 110 psi (2) (7)

Front 45

At or above 88% N2

Back 45

Minimum 50 psi (9)
Maximum 110 psi (7)

Front 46

Oil Temperature

Back 46

Minimum 21 C (3)
Maximum 126 C

Front 47

Fuel Temp

Back 47

Minimum -54 C
Maximum 52 C

Front 48

Vibration

Back 48

LP Spool Maximum 1.8 IPS (4)
HP Spool Maximum 1.1IPS (4)

Front 49

Engine Parameter Note 1

Back 49

Takeoff Thurst is time limited to 5 minutes

Front 50

Engine Parameter Note 2

Back 50

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.

Front 51

Engine Parameter Note 3

Back 51

Minimum oil temperature for starting is -40C for lubrication oil specified by MIL-L-23699D

Front 52

Engine Parameter Note 4

Back 52

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.

Front 53

Engine Parameter Note 5

Back 53

Any engine exceedance or peak must be monitored and logged by the crew.

Front 54

Engine Parameter Note 7

Back 54

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.

Front 55

Engine Parameter Note 8

Back 55

For airplanes Pre-Mod. SB 145-73-0030 the N2 limit is 102.5%

Front 56

Engine Parameter Note 9

Back 56

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).

Front 57

Engine Warm-Up

Back 57

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

Front 58

Engine Cool-Down

Back 58

The engines must run for at least 1 minute at idle or taxi thrust before shut-down

Front 59

Minimum/Maximum Temp for A/I operation

Back 59

-40 C
10 C

Front 60

Holding configuration icing conditions

Back 60

Landing Gear.....UP
Flaps..... UP
Min. Airspeed....200 KIAS

Front 61

Single-engine or single bleed in icing conditions

Back 61

Max Altitude 15,000 ft.

Front 62

SAT and TAT in icing

Back 62

Use SAT on ground or for takeoff operations and TAT for operations in flight

Front 63

Max. load on main generator

Back 63

400 amps

Front 64

Max. Load on APU generator

Back 64

400 amps below 30,000 ft.
300 amps above 30,000 ft.

Front 65

Max. Battery Temp.

Back 65

70 C

Front 66

Max Differential Pressure

Back 66

7.8 psi

Front 67

Max Differential Overpressure

Back 67

8.1 psi

Front 68

Max Differential Negative Pressure

Back 68

-0.3 psi

Front 69

Max. Altitude to Extend Flaps

Back 69

20,000 ft.

Front 70

Maximum Airpseed after Take-off/During Climb without Re-trimming

Back 70

160 KIAS

Front 71

Integrated Standby Instrument System (ISIS)

Back 71

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.

Front 72

Electromechanical Gust Lock

Back 72

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.

Front 73

Cockpit Security Door

Back 73

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.

Front 74

Autopilot Min Altitude Coupled to ILS

Back 74

200 ft.

Front 75

Autopilot Min. Engagement Height After Takeoff

Back 75

500 ft.

Front 76

Autopilot single-engine go-around

Back 76

prohibited

Front 77

Max Recommended Crosswind (Non-AFM)

Back 77

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

Front 78

Bleed / Pack Condition

Back 78

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)