So one good way to review limitations is to write them dowm, at least that works for me. Here are the limitations of the Lear 60. These limitations come from the manual that is provided be Flight Safety and is labeled FOR TRAINING PURPOSES ONLY.
GENERAL
Type of operation.
This aircraft is approved for:
VFR
IFR
Day
Night
Icing -- Icing conditions exist when outside air temperature (OAT) on the ground and for takeoff is 10 C ( 50 F) or below, or the static air temperature (SAT) in flight is 10 C to -40 C, and visible moisture in any form is present ( such as clouds, foog with visibility of one mile or less, rain, sleet, snow, or ice crystals )
Minimum Flight Crew:
Pilot and co-pilot
WEIGHTS LIMITS
Maximum Ramp Weight:
23,750 lbs.
Maximum Certified Takeoff Weight:
23,500 lbs.
Maximum Zero Fuel Weight:
17,000 lbs.
Maximum Allowable takeoff Weight:
The takeoff weight is limited by the most restictive of the following requirements:
Maximun certified takeoff weight.
The maximum takeoff weight with anti-skid OFF or antiskid protection for any wheel inoperative is 18,500 lbs.
Maximum takeoff weight (climb or brake energy limited) for altitude and temperature as determined from the applicable figure entitled Takeoff Weight Limits.
Maximum takeoff weight for the runway and ambient conditions as determined from the applicable figure entitled Takeoff Field Length
Maximum Certified Landing Weight:
19,500 Lbs.
Maximum Allowable Landing Weight:
The landing weight is limited by the most restrictive of the following requirements:
Maximum certified landing weight.
Maximum landing weight for the runway and ambient conditions as determined from the Actual Landing Distance chart.
Maximum landing weight (approach climb or brake energy limited) for altitude and temperature as determined from theapplicable figure entitled Landing Weight Limits
AIRSPEED/MACH LIMITS
Maximum Operating Speed Vmo/Mmo
Primary Instruments:
Vmo
- Up to 8000 feet.................... 300 KIAS
- 8,000 to 20,000 ft............... 340 KIAS
- 20,000 to 23,000 ft............. 340 to 330 KIAS
- 23,000 to 26,750 ft.............. 330 KIAS
Mmo
- 26,750 to 37,000 feet........... 0.81 Mach
- 37,000 to 43,000 feet.......... 0.81 to 0.78 Mach
- 43,000 feet and Above........ 0.78 Mach
- With Mach Trim inoperative and autopilot disengaged......0.77 Mach
Standby Instruments:
Vmo
- Up to 8000 feet.................... 298 KIAS
- 8,000 to 20,000 feet........... 338 KIAS
- 20,000 to 23,000 feet......... 338 to 329 KIAS
- 23,000 to 26,750 feet.......... 329 to 330 KIAS
Mmo
- 26,750 to 37,000 feet.......... 0.81 Mach
- 37,000 to 43,000 feet......... 0.81 to 0.78 Mach
- 43,000 feet and Above....... 0.78 Mach
- With Mach Trim inoperative and autopilot disengaged.......0.77 Mach
Maximum Landing Gear Operating Speed Vlo:
200 KIAS
Maximum Landing Gear Extended Speed Vle:
260 KIAS
Maximum Flap Extended Speed Vfe:
- Flaps 8 ..........250 KIAS
- Flaps 20.........200 KIAS
- Flaps 40.........165 KIAS
Minimum Control Speed Vmca:
- Flaps 8...........120 KIAS
- Flaps 20.........110 KIAS
Minimum Control Speed Groung Vmcg:
- Rudder Boost ON..........95 KIAS
- Rudder Boost OFF........116 KIAS
OPERATIONAL LIMITS AND REQUIREMENTS
TAKEOFF
Maximum Pressure Altitude:
13,700 feet
Ambient Temperature:
Refer to Ambient Temperature Limits Chart
Tailwind Component:
10 Knots
Runway Conditions: Takeoff is limited to paved runways. Runway Water/Slush Accumulation:
3/4 inch ( 19 mm )
Engine Sync:
Off
Trim:
All Axes Set For Takeoff
Fuel Load:
Wings balanced within 200 pounds
The must be checked and operational:
- Trim Systems
- Both ADC Systems
- Standby Altitude Indicator
- Stall Warning Systems
- Autospoilers
- Rudder Boost
ENROUTE
Maximum Pressure Altitude:
51,000 Feet
Fuel Load:
Wings balanced within 500 pounds
LANDING
Maximum Pressure Altitude:
13,700 feet
Ambient Temperature:
Refer to Ambient Temperature Limits Chart
Tailwind Component:
10 Knots
Runway Conditions: Landing limited to paved runways. Runway Water/Slush Accumulation:
3/4 Inch ( 19 mm )
Pressurization:
Cabin Not Pressurized
Engine Sync:
Off
Fuel Load:
Wings Balanced within 200 Pounds
LIMIT MANEUVERING LOAD FACTORS
- Flaps up............. +3.0 to -1.0 G
- Flaps Down....... +2.0 to 0.0 G
MANEUVERS
No aerobatic maneuvers, including spins, are approved.
Intentional stalls are prohibited above 18,000 feet with flaps and/or landing gear extended.
TURNAROUND LIMITS
If the turnaround weight limit for brake energy is exceeded during a landing or rejected takeoff, the following limitationsmust be observed:
- The aircraft must be parked for a minimum waiting period of 20 minutes before the next takeoff attempt can be made
- After the waiting period is observed, a visual inspection of the mair gear tires, and brakes for condition must be made
SYSTEM LIMITS
AIR DATA SYSTEM
Both air data systems must be operative and the onside system selected for takeoff.
All air data flags on the PFDs must be retracted for takeoff.
To assure proper air data system operation, the "Before Starting Engines" overspeed warning system check must be accomplished in accordance with "Normal Procedures"
ATTITUDE HEADING REFERENCE SYSTEM
The onside attitude heading system must be selected and the comparator annunciators must be extinguished for takeoff.
AUTOMATIC PERFORMANCE RESERVE
Manual selection of APR during a two-engine takeoff is limited to emergency conditions.
AUTOPILOT/FLIGHT DIRECTOR
The autopilot/flight director system is approved for Catagory I ILS approaches.
When using the autopilot, the pilot or copilot must be in their respective seat with their seatbelt fastened.
Operation of the auopilot with the red TRIM fail light illuminated is prohibited.
Autopilot pitch and roll axes must not be used for takeoff and landing. Do not intentionally overpower the autopilot.
The minimum altitude for use of the autopilot is:
- Approach configuration................ 200 feet AGL
- Enroute Configuration.................. 1,000 feet AGL
CABIN PRESSURIZATION
For takeoffs and landings above 8,000 feet, the automatic pressurization mode must be used.
Do not land with the cabin pressurized.
Maximum Differential Pressure:
9.8 PSI
ELECTRONIC FLIGHT INSTRUMENT SYSTEM (EFIS)
A minimum of three large flight displays must be operational for takeoff and the following conditions must be satisfied:
- Each outboard PFD display must be operational.
- At least one inboard display must be operational.
The standby attitude indicator must be operational for takeoff.
ENGINE SYNCHRONIZER
Engine sync must be OFF for takeoff, landing, and single-engine operation.
EXTERNAL POWER
The maximum amperage from an external power source must be limited to 1,500 amps.
COOLING SYSTEM
The cooling system must be OFF or the cabin temperature control must be in the manual mode with full cold selected for takeoff and landing.
GENERATOR LIMITS
Generator output is limited as follows:
Ground operations
- Continuous-325 amps.
- Transient-higher transient loads for cross-starts and battery charging, up to maximum generator output are authorized.
Flight operations
Continuous
- 400 amps up to 31,000 feet
- 325 amps from 31,000 to 46,000 feet
- 300 amps from 46,000 to 51,000 feet
HYDRAULIC SYSTEM
Do not exceed auxiliary hydraulic pump duty cycle of three minutes ON, then 20 minutes OFF.
NACELLE HEAT
Nacelle heat must be ON during ground or flight operations when icing conditions may exist.
Nacelle heat must be on during descent into visible moisture even if the SAT is below -40 C ( -40 F )
Ground Operations
- Do not operate nacelle heat system for more than five seconds when the associated engine is not running.
- Do not operate nacelle heat system for more than 30 seconds when static air temperature is above 15 C ( 59 F )
- Except for takeoff, do not operate nacelle heat system when engine rpm is greater than 65 % N1
RUDDER BOOST SYSTEM
If the rudder boost system is to be used, the rudder boost system check must be accomplished in accordance with Section II of the AFM
SPOILERS/AUTOSPOILERS/SPOILERONS
Spoilers
If the spoilers are inoperative during flight, the maximum operating altitude is limited to 38,000 feet.
Do not extend spoilers with flaps extended while airborne.
Do not extend spoilers, or operate with spilors deployed, at speeds above Vmo/Mmo.
Autospoilers
If autospoliers are to be armed, the autospoiler check must be accomplished in accordance with the "Normal procedures".
Do not arm the autospoilers for takeoff if SPOILERON circuit breaker is open.
Do not arm autospoilers for trianing maneuvers where where engine failure will be simulated above V1 speed or for touch-and-go landings.
Spoilerons
Spoilerons may be inoperative.
STALL WARNING SYSTEM
To assure proper stall warning system operation, the stall warning operation checks must be accomplished in accordance with the "Normal Procedures".
The angle-of-attack indicators and the appraoch and low-speed awareness cues may be used as a reference but do not replace the airspeed indicators as primary reference.
STARTER LIMITS
The following cooling periods must be observed between consecutive uses of the starter during ground operations:
After Start Attempt / Wait
1 ------ 3 minutes
2 ------ 15 minutes
3 ------ 30 minutes
THRUST REVERSERS
Thrust reverse system use is limited to ground operations on paved surfaces and attempts to deploy shall not be made in flight.
Thrust reverse must not be used to back up the aircraft.
If successful completion of the thrust reverser operational check per the "Normal Procedures" chapter of this manual has not been accomplished, the thrust reversers must be pinned per the Learjet 60 Maintenance Manual prior to takeoff.
Thrust reverser curcuit breakers must not be intentionally pulled while in fligh, except as specified in Emergency and/or Abnormal Procedures.
Thrust reversers must not be used for touch-and-go landings.
Use of reverse thrust is limited as follows:
- Below 50 KIAS-----------Limited to idle
- 50 KIAS and above-------From idle to maximum
ENGINE OPERATING LIMITS
Too much information for this blog
ENGINE SPEED LIMITS
Too much info for this blog
TIRES
Main Tire Limiting Speed:
182 Knots
POWERPLANT LIMITS
Engine Type:
Pratt and Whitney Canada PW305A turbofan engines.
Approved Fuels:
JP-5, JP-8, Jet A-1 fuels conforming to Pratt and Whitney Canada CPW204 and SB24004 are approved.
Aviation Gasoline:
The use of aviation gasoline is prohibited.
And that is the little list of most of the stuff that I must remember for Flight Safety's limitations for the Lear 60.
