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Rudder Boost..............................................................................................On
EN ROUTE
Maximum Pressure Altitude ..................................................... 51,000 feet
Ambient Temperature .................................................. Refer to Figure 1-3
Fuel Load ............................ Wings balanced within 200 pounds (91 kg)
LANDING
Maximum Pressure Altitude.......................................................14,000 feet
Ambient Temperature ........................ Refer to Figure 1-3 and Section V
Tailwind Component ...................................................................... 10 knots
Runway Conditions:
Landing is limited to paved runways.
Runway water............................................................3/4 inch (19 mm)
Pressurization ......................................................... Cabin not pressurized
Fuel Load ..............................Wings balanced within 200 pounds (91 kg)
EICAS........................................................................ SUMRY or FLT PAGE
LIMIT MANEUVERING LOAD FACTORS
- Flaps Up.......................................................................... +2.9 g to -1.0 g
- Flaps Down ......................................................................+2.0 g to 0.0 g
These acceleration values limit the bank angle in a
level coordinated turn to 70° (flaps up) and 60° (flaps
down).
EICAS or MFD
SUMRY or FLT page must be selected for takeoff and landing.
FLAPS
Do not extend flaps above 18,000 feet.
NOTE
Limitations
1-8 FM-132
FAA Approved 9-24-2004
OPERATIONAL LIMITS/REQUIREMENTS (Cont)
GEAR
Do not extend gear above 18,000 feet.
MANEUVERS
No aerobatic maneuvers, including spins, are approved.
Intentional stalls are prohibited above 18,000 feet.
SEAT BELTS AND SHOULDER HARNESSES
Seat belts must be worn by all occupants during takeoff and landing.
When a seat is equipped with a shoulder harness, it must be worn by
the occupant during takeoff and landing.
The lavatory seat is certified for takeoff and landing
using the seat belt only. This seat is not equipped
with a shoulder harness.
AMBIENT TEMPERATURE LIMITS
Figure 1-3
NOTE
-100
0
10000
20000
30000
40000
50000
-75 -50 -25 0 25 50 75
STATIC AIR TEMPERATURE (SAT) — C
PRESSURE ALTITUDE — FEET
45-1328
TAKEOFF
AND
LANDNG
Limitation
FM 132 1 9
FAA Approved 9-24-2004
Change 2
OPERATIONAL LIMITS/REQUIREMENTS (Cont)
GROUND OPERATING TEMPERATURE
If the aircraft is cold soaked on the ground for an extended period of
time at an ambient temperature colder than -23° C (-9° F), the aircraft
and its components must be warmed to -23° C (-9° F) or above prior to
start.
The cabin temperature must be -15° C (+5° F) or warmer prior to takeoff.
SYSTEM LIMITS
AIR DATA SYSTEM
Air data systems (ADC 1 and 2) must be selected normal (NORM) for
takeoff.
To assure proper air data system operation, the ADC Check of the Before
Starting Engines procedure must be accomplished in accordance
with Section II, this manual.
Reduced Vertical Separation Minimums (RVSM) — This aircraft has
been shown to meet the airworthiness requirements for operation in
Reduced Vertical Separation Minimum (RVSM) airspace between
29,000 and 41,000 feet inclusive. This does not constitute an operational
approval.
ATTITUDE HEADING REFERENCE SYSTEM (AHRS)
Attitude heading reference systems (AHRS 1 and AHRS 2) must be selected
normal (NORM) for takeoff.
AUTOPILOT/FLIGHT DIRECTOR
Autopilot must be off for takeoff and landing.
Do not intentionally overpower the autopilot.
Autopilot Minimum Use Height:
- Climb, En Route or Descent ....................................... 500 feet AGL
- Approach....................................................................... 200 feet AGL
Autopilot and flight director are approved for Category I approaches.
Limitation
1 10 FM 132
FAA Approved 9-24-2004
SYSTEM LIMITS (Cont)
PRESSURIZATION
Delta P.......................................................................... +9.9 psid to -0.5 psid
Do not land with the cabin pressurized.
ENVIRONMENTAL CONTROL SYSTEM
HI FLOW must be off with takeoff power selected, or for landing, antiice
operations, and flight above 30,000 ft.
PRIMUS 1000 INTEGRATED AVIONICS SYSTEM
The appropriate Honeywell PRIMUS 1000 Integrated Avionics System for
the Learjet Model 45/40 Pilot’s Manual (Pub. No. A28-1146-165-XX dated
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