Learjet 31A AFM Limitations - SmartCockpit · 2012. 6. 27. · Learjet 31A AFM Limitations FM-121 1-1 FAA Approved 7-25-91 Change 28 GENERAL CERTIFICATION STATUS This airplane is

Learjet 31A AFM Limitations

FM-121 I-1FAA Approved 7-25-91Change 14

SECTION I — LIMITATIONSTABLE OF CONTENTS

General

Certification Status .................................................................................... 1-1Type of Operation ..................................................................................... 1-1Performance Configuration ..................................................................... 1-1Minimum Flight Crew.............................................................................. 1-1

Weight and C.G. Limits

Maximum Ramp Weight.......................................................................... 1-2Maximum Certified Takeoff Weight ...................................................... 1-2Maximum Zero Fuel Weight ................................................................... 1-2Maximum Allowable Takeoff Weight.................................................... 1-2Maximum Certified Landing Weight..................................................... 1-3Maximum Allowable Landing Weight .................................................. 1-3Center-of-Gravity ...................................................................................... 1-3Center-of-Gravity Envelope

Standard 15,500 Lb Takeoff Weight (Figure1-1)............................... 1-4Optional 16,500 Lb Takeoff Weight (Figure 1-2) .......................... 1-4AOptional 17,000 Lb Takeoff Weight (Figure 1-2A) ........................... 1-5

Airspeed/Mach Limits

Airspeed/Mach Limits (Figure 1-3)........................................................ 1-6Airspeed/Mach Limits ............................................................................. 1-7Maximum Operating Speed VMO/MMO ............................................... 1-7Maneuvering Speed VA............................................................................ 1-7Maximum Landing Gear Operating Speed VLO................................... 1-8Maximum Landing Gear Extended Speed VLE .................................... 1-8Maximum Flap Extended Speed VFE ..................................................... 1-8Minimum Control Speed, Air VMCA ...................................................... 1-8Minimum Control Speed, Ground VMCG .............................................. 1-9Critical Engine Failure Speed V1............................................................. 1-9Rotation Speed VR..................................................................................... 1-9Takeoff Safety Speed V2 ........................................................................... 1-9

Operational Limits/Requirements

Takeoff ...................................................................................................... 1-10Enroute...................................................................................................... 1-10Landing..................................................................................................... 1-10

Change 14

Limitations Learjet 31A AFM

I-2 FM-121FAA Approved 7-25-91

Change 28

TABLE OF CONTENTS (Cont)

Flight Load Acceleration Limits ........................................................... 1-11Demonstrated Crosswind...................................................................... 1-11Maneuvers................................................................................................ 1-11Seat Belts and Shoulder Harnesses....................................................... 1-11Ambient Temperature Limits (Figure 1-4) .......................................... 1-12

System Limits

Air Data System ...................................................................................... 1-13Attitude Heading Reference System .................................................... 1-13Autopilot/Flight Director...................................................................... 1-13Cabin Pressurization .............................................................................. 1-13Electronic Flight Instrument System (EFIS) ........................................ 1-14Engine Synchronizer............................................................................... 1-14External Power ........................................................................................ 1-14Cooling System........................................................................................ 1-14Generator Limits ..................................................................................... 1-15Hydraulic System.................................................................................... 1-15Nose Wheel Steering .............................................................................. 1-15Oxygen System........................................................................................ 1-16Rudder Boost System ............................................................................. 1-16Single-Point Refuel System (If Installed) ............................................. 1-16Spoilers ..................................................................................................... 1-16Stall Warning System ............................................................................. 1-17Thrust Reversers (If Installed)............................................................... 1-17Tires........................................................................................................... 1-17Trim Systems ........................................................................................... 1-17VHF COMM/VHF NAV ....................................................................... 1-17Windshield Alcohol Anti-ice................................................................. 1-17

Powerplant Limits

Engine Type ............................................................................................. 1-18Engine Speed ........................................................................................... 1-18Engine Operating Temperatures .......................................................... 1-18

Turbine Temperature Limits (ITT)Starting (Figure 1-5)...................................................................... 1-18AExcept Starting (Figure 1-6)............................................................ 1-19

Airstart Envelope .................................................................................... 1-18

Oil Limits

Oil Temperature Limits.......................................................................... 1-20Oil Pressure Limits ................................................................................. 1-20Approved Oils ......................................................................................... 1-20

Change 28


FM-121 I-3FAA Approved 7-25-91

TABLE OF CONTENTS (Cont)

Fuel Limits

Fuel Load/Balance .................................................................................. 1-21Unusable Fuel .......................................................................................... 1-21Fuel Temperature .................................................................................... 1-21Digital Electronic Engine Control (DEEC) Specific Gravity ............. 1-21Approved Fuels ....................................................................................... 1-22Aviation Gasoline.................................................................................... 1-22Anti-icing Additive ................................................................................. 1-23Biocide Additive ...................................................................................... 1-23

Instrument Markings

Airspeed/Mach Indicator (Pilot’s & Copilot’s) .................................. 1-24Airspeed/Mach Indicators (Standby) .................................................. 1-24Cabin Altimeter/Differential Pressure ................................................ 1-24Oil Pressure .............................................................................................. 1-24Turbine Speed (N2) ................................................................................. 1-25Turbine Temperature (ITT).................................................................... 1-25Fan Speed (N1) ......................................................................................... 1-25Oil Temperature ...................................................................................... 1-25Pitch Trim ................................................................................................. 1-26Electric Power Monitor........................................................................... 1-26

AC Voltage ........................................................................................ 1-26DC Voltage ........................................................................................ 1-26DC Amperes...................................................................................... 1-26

Oxygen Pressure...................................................................................... 1-27Hydraulic Pressure.................................................................................. 1-27Emergency Air ......................................................................................... 1-27

TFM 2006-02 Page 1 of 1

FAAAPPROVED DATE

for MARGARET KLINE, MANAGERAIRCRAFT CERTIFICATION OFFICE

FEDERAL AVIATION ADMINISTRATIONWICHITA, KANSAS

TEMPORARY FLIGHT MANUAL CHANGE

Publication Affected: Model 31A FAA Approved AFM (FM-121)

Description of Change: Revises wording of Icing approval.

Filing Instructions: Insert this Temporary Flight Manual Change in theLimitations Section of the affected AFM adjacentto page 1-1 and retain until further notice.

Replace existing Icing approval with the following:• Icing

When icing or frost conditions exist, this airplane must be in-spected and operated in accordance with the Cold Weather Op-eration procedures of Section II. These procedures include therequirement to assure that all critical surfaces of the airplane(wing, vertical and horizontal stabilizers, flight control surfaces,spoilers and flaps) are free of frost, ice and snow for takeoff. Con-ducting only a visual inspection may not detect very small levelsof contamination; therefore, a tactile (hand on surface) check ofthe wing leading edge and adjacent wing upper surface is re-quired when the ambient temperature is less than 10°C (50°F).


FM-121 1-1FAA Approved 7-25-91Change 28

GENERAL

CERTIFICATION STATUSThis airplane is certified in accordance with FAR 25.

TYPE OF OPERATIONThis airplane is approved for:

• VFR (Visual)• IFR (Instrument)• Day• Night• Icing

Icing conditions exist when outside air temperature (OAT) onthe ground and for takeoff is 10°C (50°F) or below, or the staticair temperature (SAT) in flight is 10°C (50°F) to -40°C (-40°F), andvisible moisture in any form is present (such as clouds, fog withvisibility of one mile or less, rain, snow, sleet, or ice crystals).

Icing conditions also exist when the OAT on the ground and fortakeoff is 10°C (50°F) or below when operating on ramps, taxi-ways, or runways where surface snow, ice, standing water, orslush may be ingested by the engines, or freeze on engines, na-celles, or engine sensor probes.

When icing or frost conditions exist, this airplane must be in-spected and operated in accordance with the Cold Weather Op-eration procedures of Section II. These procedures include therequirement to assure that all critical surfaces of the airplane(wing, vertical and horizontal stabilizers, flight control surfaces,spoilers and flaps) are free of frost, ice and snow for takeoff. Con-ducting only a visual inspection may not detect very small levelsof contamination; therefore, a tactile (hand on surface) check ofthe wing leading edge and adjacent wing upper surface is re-quired when the ambient temperature is less than 10°C (50°F).

This airplane is not approved for ditching under FAR 25.801.

PERFORMANCE CONFIGURATIONThe airplane configuration must be as presented under Standard Per-formance Conditions in Section V.

MINIMUM FLIGHT CREWThe minimum flight crew shall consist of pilot and copilot.

Change 28

FM080307

Text Box

TFM 2006-02 IN EFFECT


1-2 FM-121FAA Approved 7-25-91

Change 17

WEIGHT AND C.G. LIMITS

MAXIMUM RAMP WEIGHT• Standard .................................................................... 15,750 Pounds

7,144 kg• Optional .................................................................... 16,750 Pounds


7,802 kg

MAXIMUM CERTIFIED TAKEOFF WEIGHT• Standard .................................................................... 15,500 Pounds



7,711 lkg

Refer to Takeoff Weight Limit placard installed onthe airplane instrument panel.

MAXIMUM ZERO FUEL WEIGHT ......................................... 13,500 Pounds6,123 kg

All weights in excess of Maximum Zero Fuel Weightmust consist of fuel.

MAXIMUM ALLOWABLE TAKEOFF WEIGHTThe takeoff weight is limited by the most restrictive of the following re-quirements:

• Maximum Certified Takeoff Weight.• Maximum Takeoff Weight (Climb or Brake Energy Limited) for

altitude and temperature as determined from the applicable fig-ure entitled TAKEOFF WEIGHT LIMITS in Section V.

• Maximum Takeoff Weight for the runway and ambient condi-tions as determined from the applicable figure entitled TAKE-OFF DISTANCE in Section V.

• Maximum Takeoff Weight for obstacle clearance as determinedfrom the applicable TAKEOFF FLIGHT PATH and CLIMBGRADIENT figures in Section V, if required.

NOTE

NOTE

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WEIGHT AND C.G. LIMITS (Cont)

MAXIMUM CERTIFIED LANDING WEIGHT• Aircraft 31-035 thru 31-190, and 31-192 not modified by

SB 31-8-1 ......................................................................15,300 Pounds6,940 kg

• Aircraft 31-191, 31-193 and subsequent, and prioraircraft modified by SB 31-8-1......................................16,000 Pounds

7,258 kg

MAXIMUM ALLOWABLE LANDING WEIGHT

The landing weight is limited by the most restrictive of the followingrequirements:

• Maximum Certified Landing Weight.

Perform Hard or Overweight Landing Inspection(Chapter 5, Learjet 31/31A Maintenance Manual) ifMaximum Certified Landing Weight is exceeded.

• Maximum Landing Weight for the runway and ambient condi-tions as determined from the ACTUAL LANDING DISTANCEand FACTORED LANDING DISTANCE (if applicable) charts inSection V.

• Maximum Landing Weight (Approach Climb or Brake EnergyLimited) for altitude and temperature as determined from theapplicable figure entitled LANDING WEIGHT LIMITS in Sec-tion V.

CENTER-OF-GRAVITY

The center of gravity of the airplane, as loaded for flight, must be main-tained within the CENTER-OF-GRAVITY ENVELOPE defined inFigure 1-1, 1-2 or 1-2A as applicable.

NOTE

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Change 17 Change 17

CENTER-OF-GRAVITY ENVELOPEStandard 15,500 Lb (7031 Kg) Takeoff Weight

Forward Flight Limit — F.S. 368.29 (4.0% MAC) for all weights up to and in-cluding 12,000 pounds (5443 kg) and tapers through F.S. 376.00 (13.63%MAC) at 15,500 pounds (7031 kg) to F.S. 376.55 (14.32% MAC) at 15,750pounds (7144 kg).

Aft Flight Limit — F.S. 381.11 (20.0% MAC) for all weights up to and including9,000 pounds (4082 kg), tapers to F.S. 388.95 (29.8% MAC) at 12,500 pounds(5670 kg), and remains at F.S. 388.95 (29.8% MAC) up to and including15,750 pounds (7144 kg).

Figure 1-1

95 10 15 20 25 30 35

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CENTER-OF-GRAVITY — % MAC

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Max Ramp WeightMax Takeoff Weight

Max Zero Fuel Weight

13.63% MACF.S. 376.00

29.8% MACF.S. 388.95

4.0% MACF.S. 368.29

14.32% MACF.S. 376.55


FM-121 1-4AFAA Approved 7-25-91Change 17

CENTER-OF-GRAVITY ENVELOPEOptional 16,500 Lb (7484 Kg) Takeoff Weight



Figure 1-2

95 10 15 20 25 30 35

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16.38% MACF.S. 378.21

29.8% MACF.S. 388.95

4.0% MACF.S. 368.29

17.07% MACF.S. 378.76

Change 17



CENTER-OF-GRAVITY ENVELOPEOptional 17,000 Lb (7711 Kg) Takeoff Weight



Figure 1-2A

95 10 15 20 25 30 35

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17.76% MACF.S. 379.31

29.8% MACF.S. 388.95

4.0% MACF.S. 368.29

18.31% MACF.S. 379.75

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Change 14

AIRSPEED/MACH LIMITS

Figure 1-3

Change 14



AIRSPEED/MACH LIMITS

All Airspeed/Mach Limits are expressed in terms ofindicated values unless otherwise stated. Instrumenterror is assumed to be zero.

MAXIMUM OPERATING SPEED VMO/MMO

VMO/MMO may not be deliberately exceeded in any regime of flight(climb, cruise, or descent) unless a higher speed is authorized for flighttest.

VMO ...........................................................................................325 KIAS

MMO • Up to 43,000 feet ............................................................... 0.81 MI

• 43,000 to 46,000 feet ............................................ 0.81 to 0.80 MI

• 46,000 to 47,000 feet ............................................ 0.80 to 0.79 MI

• 47,000 feet and above ...................................................... 0.79 MI

• With both the Mach Trim inoperativeand Autopilots disengaged ............................................. 0.78 MI

• With any missing Boundary Layer Energizers ............ 0.77 MI

The MMO limits expressed above are based uponcompressibility effects. Refer to OVERSPEED RE-COVERY procedure in Section III — EMERGENCYPROCEDURES.

Refer to the figure entitled AIRSPEED/MACH LIMITS, this section.

MANEUVERING SPEED VA

Avoid rapid and large alternating control inputs, es-pecially in combinations with large changes in pitch,roll or yaw, as they may cause structural failure atany speed, including below VA.

Refer to figure entitled AIRSPEED/MACH LIMITS, this section, for VA.

Maneuvers involving full application of rudder and aileron controls, aswell as maneuvers that involve angles of attack near stall should beconfined to speeds below VA.

NOTENOTE

NOTENOTE

CAUTION

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AIRSPEED/MACH LIMITS (Cont)

MAXIMUM LANDING GEAR OPERATING SPEED VLO

VLO is the maximum speed at which the landing gear can be safely ex-tended or retracted.

VLO .............................................................................................. 200 KIAS

MAXIMUM LANDING GEAR EXTENDED SPEED VLE

VLE is the maximum speed at which the aircraft can be safely flownwith the landing gear extended.

VLE .............................................................................................. 260 KIAS

MAXIMUM FLAP EXTENDED SPEED VFE

VFE is the maximum speed permissible with the wing flaps in a pre-scribed extended position.

VFE • Flaps 8° ............................................................................. 250 KIAS• Flaps 20° ........................................................................... 200 KIAS• Flaps 40° ........................................................................... 150 KIAS

MINIMUM CONTROL SPEED AIR VMCA

VMCA is a function of altitude and temperature. During flight tests, theaircraft was controllable down to stall speed. The speed shown is thecritical minimum control speed which occurs at the maximum thrustpoint (Sea Level, 68° F [20° C]). Section V Performance Charts accountfor the appropriate values.

VMCA

• Flaps 8° .............................................................................. 93 KIAS• Flaps 20° ............................................................................ 87 KIAS


FM-121 1-9FAA Approved 7-25-91

AIRSPEED/MACH LIMITS (Cont)

MINIMUM CONTROL SPEED GROUND VMCG

VMCG is a function of altitude and temperature. The speed shown is amaximum, which occurs at the maximum thrust point (Sea Level, 68° F[20° C]). Section V Performance Charts account for the appropriatevalues.

VMCG (Rudder Boost System Off)............................................... 109 KIASVMCG (Rudder Boost System On) ............................................... 100 KIAS

CRITICAL ENGINE FAILURE SPEED V1

Refer to applicable figure entitled TAKEOFF SPEEDS in Section V.

ROTATION SPEED VR


TAKEOFF SAFETY SPEED V2


Publication Affected:1. 24D (FM-009)2.24E (FM-011)3.24F (FM012)4. 25B/C (FM-016)5. 25D/F (FM-018)

Aircraft Affected:

Thefollowing aircraft serials are affected :

* Whencabin outflow valve or safety valve has been replaced afterJanuary 1, 1989 .

Description of Change: Revises Maximum Operating Altitude to41000 Ft.

Filing Instructions:

TEMPORARYFLIGHTMANUAL CHANGE

Thefollowing Learjet AFM's are affected:6.28/29 (FM100)

11.35A/36A (FM-102)7.31 W-112)

12. 35A/36A(FM-108)8.31 Singapore (FM-122) 13.55 (FM103)9. 31A (FM-121)

14.55B (Fm-no)10 . 35/36 (FM-019)

15.55C (FM-114)

Insert this TemporaryChange in the appropri-ate AFM as indicated below and retain untilfull compliance with SB24/25-21-4, or SB28/29-21-8, or SB31-21-6, or SB35/36-21-19, orSB55-21-10 (as applicable).

Insert Adjacent Insert AdjacentAFM to Page AFM to Page

1. 24D 1-4 9.31A 1-102.24E 1-3A 10.35/36 1-183.24F 1-4 11 . 35A/36A (FC-200) 1-144. 25B/C 1-4 12 35A/36A(FC-530) 1-125. 25D/F 1-12 13.55 1-106.28/29 1-11 14.55B 1-97.31 1-10 15.5K 1-108.31 Singapore 1-9

1. 24-218,24-230 thru 24-357* 7. 35-002 thru 35-645*2.25-061,25-067 thru 25-373* 8. 35-646 thru 35-6763.28-001 thru 28-005* 9. 36-002 thru 36-058*4.29-001 thru 29-004* 10. 36-059 thru 36-0635.31-002thru 31-006* 11 . 55-003 thru 55-136*6.31-007thru 31-087 1255-137 thrn 55-147

Addthefollowing text to the affected AFM's.

Maximum operating altitude is limited to 41000 Ft. All referencesto altitudes above 41000 Ft. should be disregarded.

FAA JAPPROVED

forEVERETTWPTrfMAN, MANAGERAIRCRAFT CERTIFICATIONOFFICE

FEDERALAVIATIONADMINISTRATIONWICfIITA, KANSAS

Page 2 of 2

TFM.94-15



Change 21

OPERATIONAL LIMITS/REQUIREMENTSTAKEOFFMaximum Pressure Altitude ...................................................... 10,000 feetAmbient Temperature ................................................... Refer to Figure 1-4Tailwind Component....................................................................... 10 knotsRunway Conditions

Takeoff is limited to paved runways.Runway water/slush accumulation....................... 3/4 inch (19 mm)

Fuel Computers....................................................................................ON ❶Engine Sync.............................................................................................. OFFTrim ........................................................................ All axes set for takeoffFuel Load............................................Wings balanced within 200 pounds

The following must be checked and operational:

ENROUTEMaximum Pressure Altitude

• With spoilers operative..................................................... 51,000 feet• With spoilers inoperative ................................................. 41,000 feet

Ambient Temperature ................................................... Refer to Figure 1-4On aircraft 31-035 thru 31-190, Cooling System...........OFF above FL 350Fuel Load............................................Wings balanced within 500 pounds

LANDINGMaximum Pressure Altitude ...................................................... 10,000 feetAmbient Temperature ................................................... Refer to Figure 1-4Tailwind Component....................................................................... 10 knotsRunway Conditions

Landing is limited to paved runways.Runway water/slush accumulation....................... 3/4 inch (19 mm)

Pressurization ...........................................................Cabin not pressurizedEngine Sync.............................................................................................. OFFFuel Load............................................Wings balanced within 200 pounds

❶ Both fuel computers must be ON and operative except for ferry flight aspermitted by applicable regulations.

❷ Required only if system is to be used.❸ Airplane may dispatch with two symbol generators provided separate

symbol generators are selected for pilot’s and copilot’s displays.

• Trim Systems • Stall Warning System• Standby Attitude Gyro • 3 Symbol Generators ❸• Both ADC Systems • Both EADI’s and EHSI’s• Rudder Boost ❷ • Both AHS Systems

Change 21

localadmin

Text Box

TFM 94-15 IN EFFECT


FM-121 1-11FAA Approved 7-25-91

OPERATIONAL LIMITS/REQUIREMENTS (Cont)

FLIGHT LOAD ACCELERATION LIMITS

These acceleration values limit the bank angle in a level coordinatedturn to 70° (flaps up) and 60° (flaps down). In addition, pullups andpushovers must be limited to these values.

• Flaps Up .................................................................. +3.0 g to -1.0 g• Flaps Down .............................................................. +2.0 g to 0.0 g

DEMONSTRATED CROSSWIND

Refer to METEOROLOGICAL DEFINITIONS in Section V —PERFORMANCE.

MANEUVERS

No aerobatic maneuvers, including spins, are approved.

Intentional stalls are prohibited above 18,000 feet with flaps and/orlanding gear extended.

SEAT BELTS AND SHOULDER HARNESSES

Seat belts and shoulder harnesses must be worn during takeoff andlanding.



AMBIENT TEMPERATURE LIMITS

Figure 1-4

-60 -40 -20 0 20 40 60STATIC AIR TEMPERATURE, SAT ~ °C

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-80

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50NOTE: Operation for altitudeand temperature within theshaded area is within allowablelimits.



SYSTEM LIMITS

AIR DATA SYSTEM

Both air data systems must be operative and the onside system selected(ADC 1 for pilot’s side and ADC 2 for copilot’s side) for takeoff.

All flags on airspeed/Machmeters and altitude/vertical speed indica-tors must be retracted for takeoff.

To assure proper air data system operation the BEFORE STARTINGENGINES air data system check must be accomplished in accordancewith Section II of this manual.

Reduced Vertical Separation Minimums (RVSM) (Aircraft 31-213,31-222 & Subsequent and prior aircraft modified by SB 31-34-11) — This air-craft has been shown to meet the airworthiness requirements for oper-ation in Reduced Vertical Separation Minimum (RVSM) airspacebetween 29,000 and 41,000 feet inclusive. This does not constitute anoperational approval.

ATTITUDE HEADING REFERENCE SYSTEM

The onside attitude heading system must be selected (i.e., AHS 1 for pi-lot’s side and AHS 2 for copilot’s side) for takeoff.

AUTOPILOT/FLIGHT DIRECTOR

The Bendix/King KFC 3100 Pilot’s Guide (No. 006-08486-0000) must beimmediately available to the flight crew.

The autopilot/flight director system is approved for category I ILS ap-proaches.

When using autopilot, the pilot or copilot must be in their respectiveseat with their seat belt fastened.

Autopilot pitch and roll axes must not be used for takeoff and landing.

The minimum altitude for use of the autopilot is:• Approach Configuration ............................................ 200 feet AGL• Enroute Configuration ............................................. 1000 feet AGL

CABIN PRESSURIZATION

Do not takeoff or land with the cabin pressurized.

Maximum Differential Pressure ......................................................10.0 PSI

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Change 21

SYSTEMS LIMITS (Cont)

ELECTRONIC FLIGHT INSTRUMENT SYSTEM (EFIS)

The Bendix/King EFS 50 Electronic Flight Instrument System Pilot’sGuide (No. 006-08485-0000) must be immediately available to the flightcrew. The pilot’s guide must be of a revision level compatible with thelevel of software installed.

Airplane performance and operation must not be predicated on the useof the multifunction display as the source of required performance andoperational data.

Whenever a symbol generator (SG) or EFIS control panel is removedand replaced, the reversionary modes must be verified prior to flight.

Both EADI’s, both EHSI’s and the standby attitude gyro must be oper-ational for takeoff.

A minimum of two symbol generators must be operational for takeoff.The pilot’s and copilot’s displays must be sourced by separate symbolgenerators.

On the copilot’s side, the reversionary EADI down mode may only beused in conjunction with the composite (CMPST) mode.

ENGINE SYNCHRONIZER

Engine sync must be OFF for takeoff, landing, and single-engine oper-ation.

EXTERNAL POWER

The maximum amperage from an external power source must be limit-ed to 1000 amps.

COOLING SYSTEM

Do not switch the cooling system ON or OFF during takeoff or landing.

On aircraft 31-035 thru 31-190, the cooling system must be OFF aboveFL350.

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SYSTEM LIMITS (Cont)

GENERATOR LIMITS

Generator output is limited as follows:

• 325 amps maximum for any altitude and Turbine Speed (N2)except as noted below.

• 400 amps for: ° S. L. — 25,000 Ft for Turbine Speed (N2) of 80% or above.

° 25,000 Ft — 41,000 Ft for Turbine Speed (N2) of 86% or above. ° 41,000 Ft — 51,000 Ft for Turbine Speed (N2) of 93% or above.

For single generator operation on the ground, the gener-ator output is limited to approximately 220 amps to pro-tect the 275-amp current limiters. If more electrical loadis applied, the current will be drawn from the aircraftbatteries and will not be shown on the DC AMPS dis-play. If this occurs, DC voltage will be reduced. A DCvoltage of 26 volts or less indicates a heavy drain on theaircraft batteries.

HYDRAULIC SYSTEM

Do not exceed auxiliary hydraulic pump duty cycle of 3 minutes ON,then 20 minutes OFF.

Only hydraulic fluid conforming to MIL-H-5606 is approved.

NOSE WHEEL STEERINGAircraft 31-035 thru 31-054 not incorporating SB 31-32-2

Maximum Ground Speed............................................................... 45 knots

Maximum Ground Speed with any two of the followingthree ANTI-SKID lights illuminated: Left and rightinboard and right outboard ......................................................... 10 knots

NOTENOTE

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Change 16


OXYGEN SYSTEMThe following aircraft certification requirements are in addition to therequirements of applicable operating rules. The most restrictive re-quirements (certification or operating) must be observed.

Above Flight Level 250, crew masks must be in the quick-donning po-sition which allows donning within 5 seconds.

On aircraft with inflatable harness crew masks, hats and “ear-muff” typeheadsets must be removed prior to donning crew oxygen masks.

Headsets and eyeglasses worn by crew membersmay interfere with quick-donning capabilities.

Crew and passenger oxygen masks are not approved for use above40,000 feet cabin altitude.

• Passenger masks are intended for use during anemergency descent to an altitude not requiringsupplemental oxygen.

• Passenger masks will not provide sufficient oxy-gen for prolonged operation above 34,000 feetcabin altitude. Prolonged operation above 25,000feet cabin altitude with passengers on board is notrecommended.

RUDDER BOOST SYSTEMIf rudder boost is to be used, the BEFORE STARTING ENGINES rudderboost check must be accomplished in accordance with Section II of thismanual.

SINGLE-POINT REFUEL SYSTEM (IF INSTALLED)Use of single-point refuel system is limited to aircraft equipped withfuel heaters.

SPOILERSDo not extend spoilers with flaps extended while airborne.

If the spoilers are inoperative in flight, the maximum operating altitudeis limited to 41,000 feet.

NOTE

WARNING

Change 16




STALL WARNING SYSTEMTo assure proper stall warning system operation, the BEFORE START-ING ENGINES stall warning system operation checks in Section II ofthis manual must be completed on each flight.

The angle-of-attack indicators may be used as a reference but do not re-place the airspeed indicators as primary instruments.

THRUST REVERSERS (IF INSTALLED)When thrust reversers are installed, refer to the applicable Thrust Re-verser Supplement for limitations, normal procedures, emergency pro-cedures, abnormal procedures, and performance data.

TIRESMain Tire Limiting Speed (Ground Speed) .............................. 182 knots

TRIM SYSTEMSTo assure proper trim systems operation, the BEFORE STARTINGENGINES trim systems checks in Section II of this manual must besuccessfully completed before each flight.

The complete TRIM SYSTEMS OPERATIONAL CHECK in Section II ofthis manual shall be successfully completed a minimum of once every10 hours of airplane flight operation.

Failure to conduct a pitch trim preflight check priorto each flight increases the probability of an undetec-ted system failure. An additional single failure in thetrim system could result in a trim runaway.

VHF COMM/VHF NAVThe use of VHF COMM frequency 119.00 MHz is prohibited whenevera VHF NAV frequency of 116.00 MHz is in use.

If the above combination of frequencies is used, key-ing the COMM causes the NAV to flag.

WINDSHIELD ALCOHOL ANTI-ICEMethyl alcohol (Methanol) per Federal Specification O-M-232, GradeA, is required.

The alcohol reservoir shall be refilled after each use.

WARNING

NOTE

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POWERPLANT LIMITS

ENGINE TYPEHoneywell TFE731-2-3B turbofan propulsion engine, part number:

3073610-x -3 (with fuel heaters)-1 (without fuel heaters)

ENGINE SPEED

❶ If overspeed limit is exceeded, contact nearest Honeywell FieldService Propulsion Engine Representative prior to engine remov-al for overspeed inspection.

❷ If limit is exceeded, reduce thrust to within limits and make nec-essary fuel control adjustment prior to next flight.

❸ Thrust settings above performance chart values may exceed en-gine rated thrust.

ENGINE OPERATING TEMPERATURESRefer to TURBINE TEMPERATURE LIMITS (Figure 1-5 and Figure 1-6).

AIRSTART ENVELOPERefer to AIRSTART ENVELOPE (Figure 4-1) in Section IV.

CONDITION LIMITOVERSPEED ❶ 105% N1 or N2

TRANSIENT ❷

5 SECONDS1 MINUTE

103-105% N1 or N2

100-103% N1 or N2

TAKEOFF ❸Refer to TAKEOFF THRUST (N1) charts in Section V.

MAXIMUM ❸

CONTINUOUSRefer to MAXIMUM CONTINUOUSTHRUST (N1) tables in Section V.

{

Change 28


FM-121 1-18AFAA Approved 7-25-91Change 28

Change 28

TURBINE TEMPERATURE LIMITS (ITT)STARTING

Figure 1-5

F31-011500-000-01TIME-SECONDS

INT

ER

ST

AG

E T

UR

BIN

E T

EM

PE

RA

TU

RE

(IT

T)

~ °C

850

930

860

870

880

890

900

910

920

5 100

3 4

21

1 Abort start. Record maximum ITT and time in excess of 860°C in engine logbook. Determine cause and correct prior to next start.

2 Abort start. Record maximum ITT and time in excess of 860°C in engine logbook. Refer to Honeywell Engine Light Maintenance Manual for static takeoffpower check.

3 Abort start. Record maximum ITT and time in excess of 880°C in engine logbook. Refer to Honeywell Engine Light Maintenance Manual for static takeoffpower check.

4 Abort start. Record maximum ITT temperature and time in excess of 880°Cin engine log book. Refer to Honeywell Engine Light Maintenance Manual forhot section inspection before further engine operation.



TURBINE TEMPERATURE LIMITS (ITT)EXCEPT STARTING

Figure 1-6

F31-011500-000-02

10 50

TIME-SECONDS TIME-MINUTES

INT

ER

ST

AG

E T

UR

BIN

E T

EM

PE

RA

TU

RE

(IT

T)

~ °C

810

820

830

840

850

860

870

890

1

800

900

8802

832°C

1 Takeoff Transient Limit. Reduce thrust setting to within limits and make elec-tronic computer N1 adjustment before next flight. Record maximum ITT andtime in excess of limit in engine log book. Observe takeoff ITT limit.

2 Record maximum ITT and time in excess of limit in engine log book. Refer toHoneywell Engine Light Maintenance Manual for hot section inspection.

Maximum continuous limit is 832°C. For greatestengine life it is recommended that, under normalconditions, engine thrust be reduced to an ITT of795°C or less after 30 minutes of maximum contin-uous operation.

NOTE

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OIL LIMITS

OIL TEMPERATURE LIMITSSea Level to 30,000 feet ................................................................... 127°CAbove 30,000 feet ............................................................................ 140°CTransient (2 minutes max.) ................................................................. 149°C

OIL PRESSURE LIMITSMinimum .......................................................................................... 25 PSIIdle Range ............................................................................... 25 to 46 PSINormal Operating Range ...................................................... 38 to 46 PSIMaximum Transient (3 minutes max.) .......................................... 55 PSI

APPROVED OILSOils conforming to Garrett specification EMS 53110, Type II are ap-proved. Refer to Addendum II — OIL SERVICING for a listing of ap-proved oils.



FUEL LIMITS

FUEL LOAD/BALANCEDo not takeoff or land with wing fuel unbalance greater than 200pounds.

During flight, wing fuel balance must be maintained within 500pounds.

UNUSABLE FUELThe fuel remaining in the fuel tanks when the fuel quantity indicatorreads zero is not usable in flight.

FUEL TEMPERATUREJP-5, JP-8, JET A, JET A-1 or equivalent fuels: Do not take off with fueltemperatures below -29°C (-20°F).

Prolonged operation at ambient temperatures belowthe freeze point of the fuel used may result in a re-duction in usable fuel because of fuel freezing ifproper fuel management procedures are not used.Refer to FUEL MANAGEMENT procedures in Sec-tion II - Normal Procedures.

DIGITAL ELECTRONIC ENGINE CONTROL (DEEC) SPECIFICGRAVITY

Engine surge may occur if the recommended specificgravity adjustment is not adhered to for the type offuel being used. If surge is encountered, refer to theEngine Maintenance Manual.

A decrease in the specific gravity setting, on the fuelcomputer, without a change in fuel specific gravity,results in higher turbine temperatures in start, accel-eration, and deceleration.

NOTE

WARNING

CAUTION

Change 2



Change 2

FUEL LIMITS (Cont)

The digital electronic engine control must be adjusted to the recom-mended specific gravity setting in the Engine Log Book for the type offuel being used. If no entry is made in the Engine Log Book, the follow-ing setting must be observed:

• Jet A, Jet A-1, JP-5, and JP-8 ................................................................ 5

APPROVED FUELSThe mixing of fuel types is allowed.

Jet-A, Jet-A1, JP-5, and JP-8 fuels conforming to Garrett SpecificationsEMS 53111, EMS 53112, and EMS 53116 are approved. Refer to Adden-dum I — FUEL SERVICING for a listing of approved fuels.

AVIATION GASOLINEThe use of aviation gasoline is not approved.



FUEL LIMITS (Cont)

ANTI-ICING ADDITIVEOn aircraft equipped with fuel heaters, anti-icing additive is not a re-quirement. However, for microbial protection, it is recommended thatfuel containing either an approved biocide additive or an anti-icing ad-ditive conforming to MIL-I-27686 be used at least once a week for air-craft in regular use and whenever a fueled aircraft will be out of servicefor a week or more.

On aircraft not equipped with fuel heaters, anti-icing additive con-forming to MIL-I-27686 or MIL-I-85470 is required. The additive con-centrations by volume shall be as follows:

Anti-icing conforming to MIL-I-85470 does not in-hibit microbial growth. For microbial protection, it isrecommended that fuel containing either an ap-proved biocide additive or an anti-icing additiveconforming to MIL-I-27686 be used at least once aweek for aircraft in regular use and whenever a fu-eled aircraft will be out of service for a week or more.

Refer to Addendum I — FUEL SERVICING for additional informationand the proper anti-icing additive blending procedure.

On aircraft not equipped with fuel heaters, lack of anti-icing additive may cause fuel filter icing and subse-quent engine flameout.

BIOCIDE ADDITIVEBiobor JF is approved for use as a biocide additive when premixed inthe fuel supply facility. Additive concentration is not to exceed 270ppm. Refer to Addendum I — FUEL SERVICING for additional infor-mation.

AdditiveType

Concentration by Volume

Minimum Maximum

MIL-I-27686 0.06% 0.15%

MIL-I-85470 0.10% 0.15%

NOTE

CAUTION

Change 16



Change 12

INSTRUMENT MARKINGS

PILOT’S AND COPILOT’SAIRSPEED/MACH INDICATORSBarber Pole pick-up at .......... VMO/MMO

STANDBYAIRSPEED/MACH INDICATORRed Line ...................................... 325 KIASBarber Pole .................................... 0.78 MI

CABIN ALTIMETER/DIFFERENTIAL PRESSURE

Green Arc ................................ 0 to 9.4 PSIYellow Arc ............................ 9.4 to 9.7 PSIRed Line .............................. 9.7 to 10.0 PSI

OIL PRESSURE

Red Line (Min.) ............................... 25 PSIYellow Arc ............................... 25 to 38 PSGreen Arc ............................... 38 to 46 PSIYellow Arc .............................. 46 to 55 PSIRed Line (3 Minutes Max.) ........... 55 PSI

160

KNOTS

60

80

100

120

140180

200

250

300

350

400

MACH

IAS

BENDIX/KING

0 610

12

1416

2025

30

3540

.8

.5

.7.6

.9

DIFF2

3

456

78

910 5

10

152025

30

4050

1000FT

CABINALT

PRESS

OILOILPRESSPRESS

PSIPS I

L R

25 25

55 55

75 75

40 40

Change 12



TURBINE SPEED (N2)Green Arc ................................ 48% to 100%Yellow Arc .......................... 100% to 103%

(One minute limit)Red Line ............................................ 103%

TURBINE TEMPERATURE (ITT)Green Arc ......................... 230°C to 832°CYellow Arc .......................... 832° to 860°CRed Line ........................................... 860°C(Refer to Figure 1-5 and Figure 1-6)

FAN SPEED (N1)Green Arc .............................. 24% to 100%Yellow Arc ............................ 100% to 103%

(One minute limit)Red Line ............................................ 103%

OIL TEMPERATUREGreen Segment .................. 30°C to 127°CYellow Segment .............. 127°C to 140°CRed Line ........................................... 140°C

Do not exceed 127°Cbelow 30,000 feet.

OILOILTEMPTEMP

C C

L R

80808080

130130

180180

3030 3030

180180

130130

NOTE

Change 28



PITCH TRIM

Takeoff Range ...................... 5.75° to 8.75°

ELECTRIC POWER MONITOR

AC VOLTAGE

Normal Range ................................................................. 110 to 130 VOLTSAmber Range .................................................................... 90 to 109 VOLTS

and 131 to 134 VOLTSRed Range ...................................................................... Below 90 VOLTS

and Above 135 VOLTS

DC VOLTAGE

Normal Range ................................................................ 22 to 29.5 VOLTSAmber Range ................................................................... 18 to 21.9 VOLTS

and 29.6 to 31.5 VOLTSRed Range ........................................................................ Below 18 VOLTS

and Above 31.5 VOLTS

DC AMPERES

Normal Range ..................................................................... 0 to 325 AMPSAmber Range .................................................................. 326 to 400 AMPSRed Range ...................................................................... Above 400 AMPS

9

7

5

NDN

NUP

PITCHTRIMT.O.

AFT

FWD

VDC

AMP2 5 0 2 5 0

VAC 115115

2 8 . 5



OXYGEN PRESSURE

Green Segment .............. 1550 to 1850 PSIYellow Segment .................... 0 to 300 PSIRed Line ....................................... 2000 PSI

HYDRAULIC PRESSURE

Yellow Segment .................. 0 to 1000 PSIGreen Segment .............. 1000 to 1750 PSIRed Line ....................................... 1750 PSI

EMERGENCY AIR

Yellow Segment .................. 0 to 1800 PSIGreen Segment .............. 1800 to 3000 PSIRed Line ....................................... 3000 PSI

If air bottle is servicednear the high end of yel-low segment (slightlyabove 1800 psi), pres-sure may drop duringflight as the systemcools; satisfactory gearextension and brakingcan still be expected.

0

30 155185

200

PSI x 10

OXYGENPRESSURE

HYD

PRESS

AIR

EMERG

2

1

1

2

3

4

NOTE

Change 4

Documents

Learjet 31A AFM Limitations - SmartCockpit · 2012. 6. 27. · Learjet 31A AFM Limitations FM-121 1-1 FAA Approved 7-25-91 Change 28 GENERAL CERTIFICATION STATUS This airplane is