manualshive.com logo in svg

Learjet 35A, Flight Manual

Share
Download
Learjet 35A Flight Manual Download Page 72

FAA APPROVED 4-30-76

2-15

REISSUED 2-25-81, CHANGE 13

BEFORE STARTING ENGINES (CONT)

c.   Attitude Director Indicator (ADI) flags and Horizontal Situation

Indicator (HSI) flags — Check that flags have disappeared. This
indicates that vertical and directional gyros have been ener-
gized long enough to time-out erection cycles (approx. 90 sec-
onds).

d.

ENG Button — Depress. The ROLL, PITCH and LVL lights
will illuminate. The autopilot will oppose movement of the
flight controls.

e.

TEST Button — Depress and hold.

f.

Control Wheel Trim Switch — Move to LWD without depress-
ing the arming button. ROLL light will extinguish and autopilot
disconnect horn will sound within 5 seconds.

g.

Release TEST switch and trim switch.

h.

Repeat steps d., e., f., and g. except move control wheel trim
switch to the RWD.

i.

Repeat steps d. and e.

j.

Control Wheel Trim Switch — Without depressing arming but-
ton, move switch to the NOSE DN position while holding mod-
erate pull force on control column. PITCH light will go out and
the autopilot disconnect horn will sound within 6 seconds.

Normally, roll axis will disengage along with the pitch.
If such disengagement does not occur, it may be disre-
garded since roll axis disengagement is not required.

k.

ENG Button — Depress.

l.

Control Wheel Master Switch — Depress. Check that autopilot
pitch and roll axis disengage.

23. Yaw Dampers — Check as follows:

a.

Primary Yaw Damper PWR/TEST Button — Depress and
hold. PWR/TEST light and PRI ENG light will illuminate.
Release PWR/TEST button. PWR/TEST light will remain illu-
minated and PRI ENG light will go out.

b.

Secondary Yaw Damper PWR/TST Button — Depress and
hold. PWR/TEST light and SEC ENG light will illuminate.
Release PWR/TEST button. PWR/TEST light will remain illu-
minated and SEC ENG light will go out.

c.

Yaw Force Indicator — Center by rotating control wheel.

d.

SEC ENG Button — Depress.

e.

Depress first one rudder pedal and then the other while hold-
ing control wheel centered. It must be possible to depress each
rudder pedal against the opposition of the yaw damper system.
The Yaw Force Indicator will indicate the direction of input.

◆

◆

◆
◆

◆
◆

◆
◆

NOTE

◆

◆

FAA APPROVED 4-30-76

2-15

REISSUED 2-25-81, CHANGE 13

BEFORE STARTING ENGINES (CONT)

c.   Attitude Director Indicator (ADI) flags and Horizontal Situation

Indicator (HSI) flags — Check that flags have disappeared. This
indicates that vertical and directional gyros have been ener-
gized long enough to time-out erection cycles (approx. 90 sec-
onds).

d.

ENG Button — Depress. The ROLL, PITCH and LVL lights
will illuminate. The autopilot will oppose movement of the
flight controls.

e.

TEST Button — Depress and hold.

f.

Control Wheel Trim Switch — Move to LWD without depress-
ing the arming button. ROLL light will extinguish and autopilot
disconnect horn will sound within 5 seconds.

g.

Release TEST switch and trim switch.

h.

Repeat steps d., e., f., and g. except move control wheel trim
switch to the RWD.

i.

Repeat steps d. and e.

j.

Control Wheel Trim Switch — Without depressing arming but-
ton, move switch to the NOSE DN position while holding mod-
erate pull force on control column. PITCH light will go out and
the autopilot disconnect horn will sound within 6 seconds.

Normally, roll axis will disengage along with the pitch.
If such disengagement does not occur, it may be disre-
garded since roll axis disengagement is not required.

k.

ENG Button — Depress.

l.

Control Wheel Master Switch — Depress. Check that autopilot
pitch and roll axis disengage.

23. Yaw Dampers — Check as follows:

a.

Primary Yaw Damper PWR/TEST Button — Depress and
hold. PWR/TEST light and PRI ENG light will illuminate.
Release PWR/TEST button. PWR/TEST light will remain illu-
minated and PRI ENG light will go out.

b.

Secondary Yaw Damper PWR/TST Button — Depress and
hold. PWR/TEST light and SEC ENG light will illuminate.
Release PWR/TEST button. PWR/TEST light will remain illu-
minated and SEC ENG light will go out.

c.

Yaw Force Indicator — Center by rotating control wheel.

d.

SEC ENG Button — Depress.

e.

Depress first one rudder pedal and then the other while hold-
ing control wheel centered. It must be possible to depress each
rudder pedal against the opposition of the yaw damper system.
The Yaw Force Indicator will indicate the direction of input.

◆

◆

◆
◆

◆
◆

◆
◆

NOTE

◆

◆

Summary of Contents for 35A

Page 1: ...MANUAL ___________________ NOTICE ___________________ This AFM is a revised issue of the original AFM dated 4 30 76 This reissue replaces all of the information in the original issue through Change 13 FM 102 SERIAL NO _______ N ________________ for CHIEF AIRCRAFT CERTIFICATION PROGRAM FAA CENTRAL REGION WlCHITA KANSAS Copyright 1983 GATES LEARJET CORPORATION All rights reserved ...

Page 2: ... the following formats E mailed to learjet squawk aero bombardier com preferred Mailed to Bombardier Learjet Technical Publications using business reply mail see reverse Faxed to 316 946 2002 A User Comment can also be created via http www cic bombardier com Click on User Comments b Today s Date Publication Information Customer Information Title Your Name Rev Chg No Issue Rev Date Dept Title Chap ...

Page 3: ...IT NO 2928 WICHITA KS POSTAGE WILL BE PAID BY ADDRESSEE ATTN TECHNICAL PUBLICATIONS MS 53 LEARJET INC PO BOX 7707 WICHITA KS 67277 9801 1 11 1 1 1 11 11 11 1 1 1 11 11 11 1 FOLD HERE LAST SEAL WITH TAPE DO NOT STAPI E NO POSTAGE NECESSARY IF MAILED IN THE UNITED STATES ...

Page 4: ...no charge for the one Flight Manual assigned to the aircraft and you will receive all changes to the assigned manual at no charge There is however a yearly subscription charge for aD Flight Manuals not assigned to the aircraft AmC S NUMBER ________________________ MAILING ADDRESS FOR CHANGES MAD THIS SHEET TO Gates Learjet Corporation P O Box 7707 WIChita Kansas 67277 Attn Technical Data Control C...

Page 5: ...hg 5 83 17 9 23 83 3 22 Select 100 OXY during emergency descent procedure Removed by Chg 5 Continued Learjet 35A 36A with FC 200 Temporary Changes FM 102 TFM 1 6 23 2008 Change 14 LOG OF TEMPORARY FLIGHT MANUAL CHANGES This list is intended to assist the flight crew in determining the applica ble AFM temporary flight manual changes for Model 35A 36A aircraft equipped with FC 200 autopilot It is th...

Page 6: ...s the list of approved oils Removed by Chg 12 Continued TFM Dated Section or Page Description Status Temporary Changes Learjet 35A 36A with FC 200 TFM 2 FM 102 6 23 2008 Change 14 84 02 3 15 84 1 3 Maximum zero wing and tip fuel weight replaces maximum wing bending weight Removed by Chg 5 85 02 3 8 85 IV Revised FUEL CMPTR light procedure Removed by Chg 6 85 10 1 3 86 2 2 Engine oil and hydraulic ...

Page 7: ...ises Dual Generator Failure procedure Removed by Chg 14 TFM Dated Section or Page Description Status Learjet 35A 36A with FC 200 Temporary Changes FM 102 TFM 3 6 23 2008 Change 14 2001 15 4 13 01 4 44 Revises Single Engine Landing procedure Removed by Chg 13 2007 02 6 14 07 3 46 Revises Stall Warning Activates proce dure Removed by Chg 14 2007 04 6 14 07 4 27 Revises AUG AIL Light Illuminated proc...

Page 8: ...FM 2007 02 TFM 2007 04 TFM 2007 13 and TFM 2007 14 Remove superseded temporary changes from AFM NOTE for MARGARET KLINE MANAGER AIRCRAFT CERTIFICATION OFFICE FEDERAL AVIATION ADMINISTRATION WICHITA KANSAS FAA Approved Date Learjet 35 36 AFM List of Effective Pages FM 102 A FAA APPROVED 4 30 76 REISSUED 2 25 81 CHANGE 14 LIST OF EFFECTIVE PAGES Learjet 35A 36A with FC 200 Autopilot AFM Use this Lis...

Page 9: ...4 37 and 4 38 10 4 39 11 4 40 and 4 41 10 4 42 13 4 43 10 4 44 14 4 45 thru 4 48 11 4 49 and 4 50 13 List of Effective Pages Learjet 35 36 AFM B FM 102 FAA APPROVED 4 30 76 REISSUED 2 25 81 CHANGE 14 LIST OF EFFECTIVE PAGES Cont Learjet 35A 36A with FC 200 Autopilot AFM Page Change Normal Procedures II 1 and II 2 12 II 3 10 II 4 14 2 1 thru 2 7 10 2 8 and 2 9 11 2 10 thru 2 16 13 2 17 10 2 18 13 2...

Page 10: ...and 5 59 6 5 60 thru 5 64 Reissued 5 65 10 5 66 13 5 66A 12 5 67 thru 5 72 Reissued 5 73 and 5 74 10 FM 102 C FAA APPROVED 4 30 76 REISSUED 2 25 81 CHANGE 14 Learjet 35 36 AFM List of Effective Pages LIST OF EFFECTIVE PAGES Cont Learjet 35A 36A with FC 200 Autopilot AFM Page Change Performance Data V 1 10 V 2 12 V 3 13 5 1 9 5 2 Reissued 5 2A 13 5 3 thru 5 5 13 5 6 thru 5 8 10 5 9 Reissued 5 10 6 ...

Page 11: ...s r should be accomplished without the aid I of the checklist Section IV ABNORMAL PROCEDURES containing FAA approved op erating procedures requiring the use of special systemsand oralternate use of regular systems whicli if followed wiD maintain an acceptable level of air worthiness or reduce operational risk resulting from a faiJw e condition Section V PERFORMANCE containing FAA approved data def...

Page 12: ...y will be forwarded to the holder of this manual Revised material will be in the fann of Temporary Right Manual Changes or Nwnbered Changes It is the responsibility of the operator to enswe that the Right Manual is current at all times Therefore it is very important that changes temporary or nwnbered be incorporated in the manual as soon as they are received TEMPORARY FUGHT MANUAL CHANGES Temporar...

Page 13: ... Change supersedes An asterisk next to a page number indicates pages changed added or deleted by the cunent change 3 Numbered Changes do not automatically supersede all outstanding Temporary Right Manual Changes Follow instructions given in Note on Ust of Effective Pages to determine which Temporary Right Manual Changes to remove when incorporating a Numbered Change RETENTION OF FUGHT MANUAL PERFO...

Page 14: ...ferenced in this Airplane Right Manual Such references in this manual are made by number and do not contain any revision indication However such references are to be un derstood as the latest revision AIRPLANE ACCESSORY KITS AAK AAK 77 8 AAK 79 4 AAK 79 10 AAK 80 2 AAK8Q 3 AAK81 1 AAK83 8 AAK86 1 iv Increase T ff Gross Weight to 18 000 Pounds Installation of Conical Fan Spinner for TFE 731 Engines...

Page 15: ...mprovement InstaUation of Emergency Pressure Control Circuit Breaker Replacement of Wmdshield Anti ice Thermostats I ENGINEERING CHANGE RECORDS ECR ECR 1495 18 000 Pounds T O G W ECR 2234 Takeoff Gross Weight Increase REID CHANGE NOTICES FCN FCN 89 1 Increase Altitude Urnitation for Operation of Freon Air Conditioning System SERVICE BULLETINS SB SB 35 36 21 17 SB 35 36 22 4 SB 35 36 27 7 SB 35 36 ...

Page 16: ...1 Rotation Speed VR 1 12 Takeoff Safety Speed V2 1 12 Ambient Temperature Limits Figure 1 4A 1 12 FAA APPROVED 4 30 76 I 1 REISSUED 2 25 81 CHANGE 10 SECTION I LIMITATIONS TABLE OF CONTENTS General Certification Status 1 1 Type of Operation 1 1 Performance Configuration 1 1 Minimum Flight Crew 1 1 Maneuvers 1 1 Weight and C G Limits Maximum Ramp Weight 1 2 Maximum Certified Takeoff Weight 1 3 Maxi...

Page 17: ...re 1 5 1 18C Except Starting Figure 1 6 1 19 Oil Limits Oil Temperature 1 18B Approved Oils 1 18B I 2 FAA APPROVED 4 30 76 REISSUED 2 25 81 CHANGE 13 TABLE OF CONTENTS Cont Takeoff and Landing Operational Limits Temperature Limits 1 13 Maximum Altitude 1 13 Wind Components 1 13 Runway Conditions 1 13 Maximum Nose Wheel Steering Speed 1 13 Tire Limiting Speed 1 13 Tip Tank Fuel 1 13 Minimum Fuel 1 ...

Page 18: ...s 1 22 Emergency Fuel Aviation Gasoline 1 23 Instrument Markings AirspeedlMachmeter 1 25 Trim 1 26 Cabin A1timeter Differential Pressure 1 26 Turbine Speed N2 1 27 Turbine Temperature 1TT 1 27 Fan Speed Nl 1 28 Oil Pressure 1 28 Oil Temperature 1 29 Ammeter 1 29 DC Voltmeter 1 29 AC Voltmeter 1 29 HydrauliC Pressure 1 30 Emergency Air 1 30 Oxygen Pressure 1 30 FAA APPROVED 4 30 76 REISSUED 2 25 81...

Page 19: ...stalls pusher actuations are prohibited above 18 000 feet with flaps and or landing gear extended FAA APPROVED 4 30 76 1 1 REISSUED 2 25 81 CHANGE 13 GENERAL CERTIFICATION STATUS This airplane is certified in accordance with FAR 25 TYPE OF OPERATION This aircraft is approved for VFR IFR day night and icing conditions When icing or frost conditions exist this airplane must be inspected and operated...

Page 20: ...rating AAK 80 2 18 500 Pounds 8 392 kg Serials 36 046 and subsequent 18 500 Pounds 8 392 kg NOTE 1 2 FAA APPROVED 4 30 76 REISSUED 2 25 81 CHANGE 6 WEIGHT AND C G LIMITS MAXIMUM RAMP WEIGHT Ramp Weight shall not exceed Maximum Allowable Takeoff Weight by more than 250 lbs 113 kg MODEL 35A Serials 35 067 and subsequent not incorporating ECR 1495 ECR 2234 AAK 77 8 or AAK 80 2 17 250 Pounds 7 825 kg ...

Page 21: ...uent MAXIMUM ZERO WING AND TIP fUEL WEIGHT 7 711 kg 18 000 Pounds 8 165 kg 18 300 Pounds 8 301 kg 18 300 Pounds 8 301 kg 18 000 Pounds 8 165 kg 18 300 Pounds 8 301 kg 18 300 Pounds 8 301 kg 13 500 Pounds 124 kg All weights in excess of 13 500 pounds must consist of wing and tip tank fuel except as follows 1 The Maximum Zero Wing and Tip Fuel Weight may be increased to 14 000 pounds by adding up to...

Page 22: ...akeoff Weight for obstacle clearance as determined from the applicable TAKEOFF FUGHT PATH and CUMB GRADIENT figures in Section V FAR 121 and 135 as applicable to U S registered aircraft MAXIMUM CERTIFIED lANDING WEIGHT MODEL 35A Serials 35 067 thru 35 344 not incorporating AAKBO 3 Serials 35 067 thru 35 344 when incorporating AAKBO 3 Se als 35 345 and subsequen MODEL 36A Serials 36 018 thru 36 045...

Page 23: ...n F S 366 31 5 MAC for all weights up to and including 10 000 pounds and tapers through ES 375 96 16 66 MAC at 17 000 pounds to ES 376 31 17 09 MAC at 17 250 pounds The aft C G limit is ES 387 00 30 MAC for all weights Refer to Rgure 1 1 Aircraft Certified for 18 000 Pounds Takeoff Weight The for ward C G limit is Fuselage Station F S 366 31 5 MAC for all weights up to and including 10 000 pounds ...

Page 24: ...l fI l 1 t I i k I 11 1 1 12000 1i I i I i h r HI f I rr 1 il I i n tl l j IT 1H 1 tJ 11Il00 j i 1 ll it Ir lfl ih i i iifi ji iii Lt1irn J r 9000 11 fI I J I I L I t l _ J tlHl n ptIrnlg TIl I i r 1 _ i _ I II llllliiill 1 iii I 1 11 I li I qil ii I 1til iil ll wll j mHI liitiioom 4 iii i j r II 12 13 I FUSELAGE l lit Il STATIONS Ii 18 19 ao rl l I I II ll Iii Iii 8 Iii P liiiil iijj 8B8B I ...

Page 25: ... 111111 _ 1 Center of Gravity Envelope FIgUre 1 2 FAA APPROVED 4 30 76 REISSUED 2 25 81 1 II 1 7 ...

Page 26: ...1 8 Center of Gravity Envelope Figure 1 3 FAA APPROVED 4 30 76 REISSUED 2 25 81 ...

Page 27: ...t which the landing gear can be safely extend ed or retracted VLO 202 KIAS NOTE WARNING CAUTION FAA APPROVED 4 30 76 1 9 REISSUED 2 25 81 CHANGE 13 AIRSPEED MACH LIMITS All Airspeed Mach Limits are expressed in terms of in dicated values unless otherwise stated Instrument error is assumed to be zero MAXIMUM OPERATING SPEED VMO MMO Do not extend spoilers or operate with spoilers deployed at speeds ...

Page 28: ... 083 MIl H MMO 0 78 MIl Missing BLE 401 tttl I Itt H l W li f l j j I ttU t I N t rH l i MMO 074 MI Mach Trim 1 1 H I f l l k _Ii i ji j c N tjX f1 and Autopilot Not Operating 30 1l1JHLfHTIlffJBttfifJ 20 llt l jJtUii f lUJil tttU tutt r 1J1tULj J g II i I I I I f2 t or Puller Not Operative 1 tl I l_l iftillJ l oItHttHH tj Itt HjtH Ht ttW t 1t wtH H H H i t I III i I I i d o 100 200 300 400 INDICAT...

Page 29: ...ion of altitude and temperature The speed shown is a max imum which occurs at Sea Level lSOC O F Section V Performance Charts account for the appropriate values VMCA 18 C O F at Sea level 112 KIAS MINIMUM CONfROL SPEED GROUND VMcG VMCG is the minimum speed on the grotmd at which control can be main tained using aerodynamic controls alone when one engine suddenly be comes inoperative and the remain...

Page 30: ...able figure entitled TAKEOFF SAFETY SPEED V2 in Section V AMBIENT TEMPERAlURE UMlTS 1 UUt l NOTE Operation for altitude t 50 and temperature within the I i f t t shaded area is within allowable limits rrHHHH HI l40 o J t 30 20 H J tf tf l I t tW r I so 60 40 20 0 20 40 60 1 12 OUTSIDE AIR TEMPERATURE OAT DC Rgurel 4A FAA APPROVED 4 30 76 REISSUED 2 25 81 CHANGE 10 ...

Page 31: ...imited to paved runways Do not operate if water and or slush accumulation on the runway exceeds 3 4 inch 19 mm MAXIMUM NOSE WHEEL SlEEKING SPEED Maximum 45 KNOTS GROUND SPEED With any two of the foDowing three Anti Skid System lights iUwninated Two inboard and right outboard 10 KNOTS GROUND SPEED 11RE LIMITING SPEED Main Tires 182 KNOTS GROUND SPEED 11P TANK FUEL Maximum tip tank fuel for landing ...

Page 32: ...ATURE UMITS Rgure 1 4A MAXIMUM OPERA11NG AL1111JDE The maximum operating altitude is 45 000 feet This is the highest altitude for which acceptable flight characteristics and systems operation have been demonstrated FUGHT LOAD ACCELERATION UMlTS Raps Up 3 0 9 to 1 0 g Raps Down 2 0 g to 0 0 9 1 14 These acceleration values limit the bank angle in a level coordinated tum to 70 flaps up and 60 flaps ...

Page 33: ...Iuu 36 063 5 31 002 tIuu 31 006 11 55 003 thru 55 136 6 31 007 tIuu 31 087 1255 137 tIuu 55 147 When cabin outflow valve or safety valve has been replaced after January 1 1989 Desaiption of Change Revises Maximum Operating Altitude to 41000 Ft Filing Instructions Insert this Temporary Change in the appropri ate AFM as indicated below and retain until full compliance with SB24 25 21 4 or SB28 29 21...

Page 34: ...ating altitude is limited to 41000 Ft All references to altitudes above 41000 Ft should bedisregarded OVED_ R mUJ L lA ___ DATE Pagelofl for EVERf I1 w Pll IMAN MANAGER AlRCRAFI CERTIFICAnON OFFICE FEDERALAVIAnON ADMINISTRATION WlOiJTA KANSAS 1 1 5 TFM9f 1S ...

Page 35: ...hed in accordance with Section II of this manual TRIM SYSTEMS Pitch trim runaway training that actually involves running the trim in flight to simulate malfunctions is prohibited To assure proper trim systems operation the BEFORE STARTING ENGINES trim systems checks must be successfully completed before each flight IWARN lGt Failure to conduct a complete pitch trim preflight chl ck prior to each f...

Page 36: ... undesir able Iateraklirectional Dutch RoB characteristics These characteristics are improved as the wing tip fuel is consumed The pilot shall observe the NOTE relative to turbulence contained in the APPROACH procedure Section m and increase airspeed as required Yaw damper should be turned off while using rudder trim Reengage yaw damper after trim is established SPOILER Do not extend spoilers with...

Page 37: ...lished whenever an engine start usi11J a starter has been perfonned These chec ks require that both engines be operating to perfOrm the check ENGINE SYNCHRONIZER Engine sync must be OFF for takeoff landing and single engine op eration EXTERNAL POWER The maximum amperage from an external power source Is limited to 1100 amps FREON COOLING SYSTEM On aircraft not incorporating FCN 89 1 the freon cooli...

Page 38: ... plemental oxygen Passenger masks will not provide sufficient oxygen for prolonged operation above 34 000 feet cabin al titude Prolonged operation above 25 000 feet cabin altitude with passengers on board is not recommended Aircraft 35 067 thru 35 112 except 35 107 and aircraft 36 018 thru 36 031 Above Right Level 250 Aircraft with ZMR 100 Series Crew Masks One crew member must wear oxygen mask ar...

Page 39: ...r limitations normal procedures emergency procedures ab normal procedures and performance data 1 18A FAA APPROVED 4 30 76 1 18 A REISSUED 2 25 81 CHANGE 10 SYSTEM LIMITS CONT PRESSURIZATION LIMIT Maximum Differential Pressure 10 0 PSI WINDSHIELD AND RADOME ANTI ICE FLUID Methyl Alcohol Methanol per Federal Specification O M 232 Grade A is required THRUST REVERSERS IF INSTALLED When thrust reverser...

Page 40: ...ING charts in Section V MAXIMUM CONTINUOUS Refer to MAXIMUM CONTINUOUS THRUST tables in Section V 1 18B FAA APPROVED 4 30 76 REISSUED 2 25 81 CHANGE 13 POWERPLANT LIMITS ENGINE SPEED LIMITS If overspeed limit is exceeded contact nearest Honeywell Field Service Propulsion Engine Representative prior to engine removal for overspeed inspection If limit is exceeded reduce thrust to within limits and m...

Page 41: ...E SECONDS INTERSTAGE TURBINE TEMPERATURE ITT C 850 930 860 870 880 890 900 910 920 5 10 0 3 4 2 1 FAA APPROVED 4 30 76 1 18C REISSUED 2 25 81 CHANGE 13 TURBINE TEMPERATURE LIMITS ITT STARTING Abort start Record maximum ITT and time in excess of 860 C in engine log book Determine cause and correct prior to next start Abort start Record maximum ITT and time in excess of 860 C in engine log book Refe...

Page 42: ...S INTERSTAGE TURBINE TEMPERATURE ITT C 810 820 830 840 850 860 870 890 1 800 900 880 2 832 C NOTE FAA APPROVED 4 30 76 1 19 REISSUED 2 25 81 CHANGE 13 TURBINE TEMPERATURE LIMITS ITT EXCEPT STARTING Takeoff Transient Limit Reduce thrust setting to within limits and make electronic computer N1 adjustment before next flight Record maximum ITT and time in excess of limit in engine log book Observe tak...

Page 43: ...oncentration by Volume Minimum Maximum MIL I 27686 0 06 0 15 MIL I 85470 0 10 0 15 NOTE CAUTION 1 20 FAA APPROVED 4 30 76 REISSUED 2 25 81 CHANGE 12 FUEL LIMITS FUEL TEMPERATURE Do not take off with fuels other than JP 4 or equivalent at fuel tempera tures below 29 C 20 F Do not take off with fuel temperature lower than 54 C 65 F UNUSABLE FUEL The fuel remaining in the fuel tanks when the fuel qua...

Page 44: ...ended specific gravity setting in the Engine Log Book for the type of fuel being used If no entry is made in the Engine Log Book the following settings must be observed I Jet A Jet A I JP 5 and JP 8 Position 5 Jet Band JP 4 Position 6 50 or more Aviation Gasoline Position 7 Fuel adjustment knob may be rotated one click either direction from the recommended fuel adjustment of positions 5 6 and 7 to...

Page 45: ...rge must be taken when switch fueling Refer to Addendum FUEL SERVICING Jet A Jet A I Jet B JP 4 JP 5 and JP 8 fuels conforming to Garrett Turbine Engine Company Specifications EMS 53111 EMS 53112 EMS 53113 and EMS 53116 are approved Refer to Addendum FUEL SERVICING for a listing of approved fuels 1 22 FAA APPROVED 4 30 76 REISSUED 2 25 81 CHANGE 12 ...

Page 46: ... below 15 000 feet 3 Both JET PUMPS and both STANDBY PUMPS Switches must be ON and the pumps must be operating Aviation gasoline Mll D 5572D Grades 80 87 100 130 and 115 145 may be used as an emergency fuel and mixed in any proportion with var ious approved jet fuels Aviation gasoline may not be used in excess of 500 gaUons 1892 5 liters per 100 hours of operation per engine FAA APPROVED 4 30 76 R...

Page 47: ...1 24 111 111 INTENTIONAlLY LEFf BlANK FAA APPROVED 4 30 76 REISSUED 2 25 81 CHANGE 12 ...

Page 48: ...7 KlAS Red Line 359 KlAS Red Line 83 MI OR Red Line Red Line Red Line OR 307KIAS 359KlAS 83MJ Red Line 307 KlAS Barber Pole pick up at 359 KIAS OR Red Line Barber Pole pick up at FAA APPROVED 4 30 76 REISSUED 2 25 81 and 83MJ 307KIAS 359KIAS and 83 MJ 1 25 ...

Page 49: ...raft in corporating AAK83 8 111 111 1 CABIN ALnMmR DIFFERENTIAL PRESSURE Aircraft35 067 thru 35 112 except35 107 and 36 018 thru 36 031 Green Arc _ G S 9 PSI Yellow Arc 8 9 9 2 PSI Red Arc 9 2 10 0 PSI Aircraft35 107 35 113 and Subsequent and 36 032 and Subsequent Green Arc 0 9 4 PSI Yellow Arc 9 4 9 7 PSI Red Arc 9 7 10 0 PSI 1 26 FAA APPROVED 4 30 76 REISSUED 2 25 81 CHANGE 5 ...

Page 50: ...een Arc 230 C 832 C Yellow Arc 832 C 860 C Red Line 860 C Refer to Figure 1 5 and Figure 1 6 OR FAA APPROVED 4 30 76 1 27 REISSUED 2 25 81 CHANGE 13 INSTRUMENT MARKINGS CONT TURBINE SPEED N2 Green Arc 48 100 Yellow Arc 100 103 One minute limit Red Line 103 OR TURBINE TEMPERATURE ITT Green Arc 230 C 832 C Yellow Arc 832 C 860 C Red Line 860 C Refer to Figure 1 5 and Figure 1 6 OR CHANGE 13 ...

Page 51: ...en Arc 38 46 PSI Yellow Arc 46 55 PSI Red Line Max 55 PSI OR OIL PRESS PSI L R 25 25 55 55 75 75 1 28 FAA APPROVED 4 30 76 REISSUED 2 25 81 CHANGE 5 INSTRUMENT MARKINGS CONT FAN SPEED N1 Green Arc 24 100 Yellow Arc 100 103 One minute limit Red Line 103 OR OIL PRESSURE Red Line Min 25 PSI Yellow Arc 25 38 PSI Green Arc 38 46 PSI Yellow Arc 46 55 PSI Red Line Max 55 PSI OR OIL PRESS PSI L R 25 25 55...

Page 52: ...Arc 300C 127 C Yellow Arc 127 C 140 C Red lJne 140 C AMMETER Yellow Arc 320 400 AMPS Red lJne 400 AMPS Do not exceed 320 amps during ground operation DC VOLTMEI ER Red lJne 32 VOLTS AC VOLTMETER Green Arc 110 130 VOLTS FAA APPROVED 4 30 76 RElSSUED 2 25 81 CHANGE 8 1 29 I ...

Page 53: ...ory gear extension and braking can still be expected OR Yellow Arc 0 1800 PSI Green Arc 1800 3000 PSI Red Une _ 3000 PSI If air bottle is serviced near high end of yellow arc slightly above 1800 PSG pressure may drop during flight if system cools satis factory gear extension and brakingcan still be expected OXYGEN PRESSURE Green Arc 1550 1850 PSI Yeilow Arc 0 300 PSI Red Une 2000 PSI fli 1I1 ___ p...

Page 54: ...Go Around 2 35 Landing 2 35 After Landing Clearing Runway 2 36 Shutdown 2 37 Quick Turnaround 2 38 Cold Weather Operation 2 40 Preflight Preparation 2 40 Preflight Inspection 2 40 Engine Start 2 41 Taxiing 2 42 Takeoff 2 42 After Takeoff 2 43 Before Landing 2 43 Landing 2 43 After Clearing Runway 2 43 Shutdown and Postflight 2 44 Pressurization System Operation 2 45 Manual Mode Operation 2 45 Land...

Page 55: ...selage Fuel Transfer Model 35A without FUS VALVE Switch 2 59 Model 35A with FUS VALVE Switch and Model 36A 2 59 AUXiliary Fuselage Fuel Transfer Aircraft with RJS VALVE SWitch 2 61 Fuel Crossflow Wing ta Wing Fuel Transfer 2 62 Refueling 2 63 Ice Detection 2 64 Anti Ice Systems 2 66 Exterior Windshield Defog Anti Ice and Rain Removal 2 68 Interior Windshield and Passenger Window Defog 2 72 Radome ...

Page 56: ...5 416 Subsequent and Aircraft 36 048 Subsequent 2 83 Annunciator Panel 2 84 Engine Synchronizer 2 85 FAA APPROVED 4 30 76 II 3 REISSUED 2 25 81 CHANGE 10 TABLE OF CONTENTS Cont Emergency Lighting System If Installed Aircraft 35 067 thru 35 415 and Aircraft 36 018 thru 36 047 2 82 Aircraft 35 416 Subsequent and Aircraft 36 048 Subsequent 2 83 Annunciator Panel 2 84 Engine Synchronizer 2 85 ...

Page 57: ...letion of the QUICK TURNAROUND procedure in this section provides the minimum preflight requirements II 4 FAA APPROVED 4 30 76 REISSUED 2 25 81 CHANGE 14 INTRODUCTION TO NORMAL PROCEDURES The procedures in this section of the manual have been developed by Learjet Inc for certification of this aircraft This section contains those procedures which may be considered routine in day to day operations T...

Page 58: ...111 11 1 EXTERIOR PREFUGHT Walk Around Inspection Figure 2 1 FAA APPROVED 4 30 76 REISSUED 2 25 81 CHANGE 10 2 1 ...

Page 59: ...n or suspected If pitot static drain valves are opened ensure that valve stem returns to the closed position Nose Gear and Wheel Well Hydraulic leakage and condi tion Nose Wheel and TIre Condition and nose gear uplock for ward Chine on nose tire must be a minimum of 3 4 inch 19 mm from ground to operate safely with an aCcumula tion of 3 4 inch 19 mm water on runway surface Radome Alcohol Discharge...

Page 60: ...g flight control surfaces and engine inlet must be free of frost snow and ice d Fuel Crossover Left Wmg Stunp Left Engine Fuel Right Wmg Swnp and Right Engine Fuel Drain Va1ves Drain e Right Main Gear and Wheel WeB Hydraulic fuel leakage and condition f Right Main Gear Landing Ught Condition g Right Main Gear Wheels Brakes and Ttres Condition e a Aircraft 35 279 and subsequent 36 045 and subsequen...

Page 61: ... If preflight oil level checks low start and run engine until stabilized at idle Shut down engine and recheck oU lev el If there is no oil level indication add enough oil to ob tain an indication before starting engine to recheck oil level Right Engine Oil Bypass Valve Indicator Check not extended If red pin indicator protrudes investigate Right Engine Turbine Exhaust Area Condition clear of obstr...

Page 62: ...H Field Antenna if applicable Condition e a Left VOR LOC Antenna Condition b Left ELT Anterma if applicable Condition c Left Fuel Computer Drain Valve Drain e a Ftre Extinguisher Discs Condition b Left Engine Oil Bypass Valve Indicator Check not extended Of red pin indicator protrudes investigate e a Left Engine Turbine Exhaust Area Condition clear of obstructions G a Left Engine Fuel Bypass Valve...

Page 63: ...d prior aircraft incorporating AAK 79 10 or AMK 83 5 Boundary Layer Energizers Condition Other aircraft Vortex Generators Condition G a Left Wing Access Panels underside of wing Check for fuel leakage b c G a b c d 2 6 Left Fuel Vent Underside of Wing Plug remove9 clear of obstructions Aircraft 35 279 and subsequent 36 045 and subsequent and prior aircraft incorporating AAK 79 10 or AMK 83 5 Stall...

Page 64: ... with cabin air damper control knob the auxiliary cabin heater will not operate unless damper control knob is in the closed position On aircraft with cabin blower switch when cabin blower 5 Iitch on blower duct in aft cabin is in the OFF position airflow is diverted above the headliner at all times except during auxiliary heater operation 3 Emergency Exit Aisle clear and handle unobstructed 4 Brie...

Page 65: ...ction and amber EMER PWR light illuminated b EMER BAT Switch On Check attitude gyro operation and amber EMER PWR light illuminated and gteen gear LOCKED ON lights illuminated For thru flight EMER BAT Switch On Check attitude gyro for starting and erection Aircraft with Dual Emergency Battery System a EMER PWR BAT 1 Switch STBY Check attitude gyro for starting and erection b EMER PWR BAT 2 Switch O...

Page 66: ...V light out d PRI INVERTER Switch OFF Check AC VOLTS reading is within green arc NOTE NOTE NOTE NOTE FAA APPROVED 4 30 76 2 9 REISSUED 2 25 81 CHANGE 11 BEFORE STARTING ENGINES CONT f PITCH TRIM Switch PRI g JET PUMP Switches ON h EMER PRESS Switches if installed NORMAL except for takeoff above 8500 feet pressure altitude Aircraft with emergency pressurization override switches installed For takeo...

Page 67: ...FE lights illuminated c Fire Detect System Check 1 TEST Selector Switch Rotate to FIRE DET NOTE 2 10 FAA APPROVED 4 30 76 REISSUED 2 25 81 CHANGE 13 BEFORE STARTING ENGINES CONT e Auxiliary Inverter if installed Check 1 AUX INVERTER ON OFF Switch ON Check AUX INV light not illuminated 2 SEC INVERTER Switch OFF Check AC VOLTS read ing is within green arc f PRI SEC and AUX INVERTER if installed Swit...

Page 68: ...e of attack indicator needle will begin to sweep from the green segment to the red segment NOTE NOTE FAA APPROVED 4 30 76 2 11 REISSUED 2 25 81 CHANGE 13 BEFORE STARTING ENGINES CONT 2 TEST Button Depress FIRE PULL or ENG FIRE PULL T Handle shall illuminate and flash This indicates continu ity of the fire detect systems 3 TEST Button Release It is recommended that one engine be started after Step ...

Page 69: ...PRESSURIZATION AUTO MAN Switch AUTO 4 AIRCRAFT ALT Selector Knob Rotate to cruise altitude NOTE NOTE 2 12 FAA APPROVED 4 30 76 REISSUED 2 25 81 CHANGE 13 BEFORE STARTING ENGINES CONT a As the needle passes the green yellow margin the shaker will actuate and the L STALL warning light shall flash b As the needle advances to the red segment the pusher will actuate briefly then stop L STALL warning li...

Page 70: ...ol Wheel Trim Switch Operate NOSE UP the NOSE DN Trim motion shall not occur d PITCH TRIM Switch OFF FAA APPROVED 4 30 76 2 13 REISSUED 2 25 81 CHANGE 13 BEFORE STARTING ENGINES CONT 5 Cabin RATE Selector Position as desired 6 IN NORMAL OUT DEFOG Knob Push in Aircraft 35 107 35 113 and subsequent and 36 032 and subsequent 1 L and R BLEED AIR Switches Check On 2 CAB AIR Switch OFF 3 PRESSURIZATION ...

Page 71: ...ld will illuminate b TEST Button Depress All lights on the Autopilot Controller will illuminate NOTE 2 14 FAA APPROVED 4 30 76 REISSUED 2 25 81 CHANGE 13 BEFORE STARTING ENGINES CONT e Actuate pilot s and copilot s control wheel trim and trim arm ing switches and pedestal NOSE DN OFF NOSE UP switch Trim motion shall not occur f PITCH TRIM Switch þPRI g Pedestal NOSE DN OFF NOSE UP Switch Operate N...

Page 72: ...pposition of the yaw damper system The Yaw Force Indicator will indicate the direction of input NOTE FAA APPROVED 4 30 76 2 15 REISSUED 2 25 81 CHANGE 13 BEFORE STARTING ENGINES CONT c Attitude Director Indicator ADI flags and Horizontal Situation Indicator HSI flags Check that flags have disappeared This indicates that vertical and directional gyros have been ener gized long enough to time out er...

Page 73: ...stalled Stowed 27 Takeoff Data N1 V1 VR V2 Takeoff Distance Computed and bugs set Refer to Section V 2 16 FAA APPROVED 4 30 76 REISSUED 2 25 81 CHANGE 13 BEFORE STARTING ENGINES CONT f Control Wheel Rotate to full left rudder pedals will deflect to the left Rotate to full right rudder pedals will deflect to the right g SEC ENG OFF Button Depress SEC ENG light will extin guish and yaw damper will d...

Page 74: ...ing AAK 83 8 Figure 2 2 FAA APPROVED 4 30 76 2 17 REISSUED 2 25 81 CHANGE 10 TAKEOFF TRIM CG FUNCTION Aircraft 35 146 subsequent aircraft 36 036 subsequent and prior aircraft incorporating AAK 83 8 Figure 2 2 CHANGE 10 lli hl Rlanllal t t 0 2 C l J 00 C J 1 0 C J C J C J C J 0 C J U 00 E If 1 0 t 0 J 00 1 0 S33H930 9NIJ l3S J J03 v 1 H3ZI1IS v IS 1 17 INOZIHOH ...

Page 75: ...es above 0 F Do not energize SPR switch at any time other than en gine start WARNING CAUTION NOTE 2 18 FAA APPROVED 4 30 76 REISSUED 2 25 81 CHANGE 13 STARTING ENGINES It is recommended that a GPU be used when ambient temperature is 32 F 0 C or below Ensure GPU supply is regulated to 28 VDC has adequate capacity for engine starting and is limited to 1100 amps maximum Airflow into the TFE 731 engin...

Page 76: ...Wait 1 One Minute 2 One Minute 3 Fifteen Minutes 4 One Minute 5 One Minute 6 One Hour The above cycle may then be repeated 12 START GEN Switch GEN at Idle E On aircraft 35 067 thru 35 147 and 36 018 thru 36 035 set BAT 1 or BAT 2 switch to OFF prior to set ting the START GEN switch to GEN Prior to starting the second engine or in the case of single engine taxi when ammeter reads less than 175 amps...

Page 77: ... spoilers slam down Slam down is a quiek spoiler retraction Oess than one second It is markedly different from the normal four second spoiler retraction k SPOILER Circuit Breaker copilot s essential bus Engage Cheek that spoilers extend I SPOILER Switch RET Cheek that spoilers retract fully and symmetrically in approximately 4 seconds and SPOILER light goes out Aircraft 35 143 and subsequent 36 03...

Page 78: ...tions a At Turbine Speed N2 Idle of 55 to 620 41 Check Fan Speed NI 26 to 32 b OIL PRESS Check applicable red L or R LO OIL light extinguished On aircraft with a single red LO OIL PRESS or OIL PRESS light the light will remain U1uminated until both engines are operating On aircraft with red Land R LO OIL lights the ap plicable light will extinguish c FUEL PRESS Ught Check not illuminated This indi...

Page 79: ...p current Iimiter s prior to takeoff 23 On aircraft 35 067 thru 35 389 except 35 370 36 018 thru 36 047 except aircraft incorporating AMK 80 17 or AAK 81 1 Starter Disengagement After both engines are operating check asfoUows a COOL FAN Switch OFF b AUX HT Switch OFF c Battery Switches OFF d AMPS Check total current indication of less than 100 amps If total current is greater than 100 amps shut do...

Page 80: ...correct cause prior to flight b L FUEL CMPTR Switch OFF Note L FUEL CMPTR light illuminated engine RPM may increase or decrease slightly CAUTION I If turbine speed does not respond during the following r steps shut down engine and determine and correct cause prior to flight c Once RPM stabilizes gradually advance thrust lever until an increase in Turbine Speed N2 is observed d Retard thrust lever ...

Page 81: ...ired Do not use strobe lights when taxiing in vicinity of other aircraft Position lights to be turned on for all night op erations 8 ANTI SKID Switch On Check ANTI SKID GEN Lights Out 9 Cabin Check a Passengers Briefed b Swivel Seats Forward or as placarded Seat backs in upright and locked position c Work Tables and Toilet Door Check stowed d Emergency Exit Aisle clear and handle unobstructed 10 N...

Page 82: ...k for normal indication Starter Disengagement Check if second engine is started during taxi Perform Refer to STARTING ENGINES this section Battery Charging Bus Current Umiter Check after both engines are started CAUTION I Failure to successfully complete the following checks in dicates a malfunction Replace 275 amp current limit er s prior to takeoff Aircraft 35 067 thru 35 147 and aircraft 36 018...

Page 83: ...ity through the right current limiter Also the R GEN light will come on and the left generator voltage may be reduced by approximately 2 VDC Aircraft 35 067 thru 35 389 except 35 370 and 36 018 thru 36 047 incorporating AMK 80 17 or AAK 81 1 a L CUR LIMITER and R CUR LIMITER Lights Check extin gUished Aircraft 35 370 35 390 subsequent and aircraft 36 048 subsequent a CUR LIM Light Check extinguish...

Page 84: ...keoff they should be turned On prior to setting takeoff power Windshield Heat As required Maintain minimum RPM required to keep windshield clear b NAC HEAT Switches ON one at a time Check amber ENG ICE lights extinguish by 60 Fan Speed NI c NAC HEAT Switches As required d STAB WING HEAT Switch On Check for slight up rate on Cabin Climb Indicator e STAB WING HEAT Switch As required Monitor WING TEM...

Page 85: ... PITOT HEAT Switch On Note that R PITOT HEAT light goes out For thru light both PITOT HEAT Switches On Check PITOT HEAT light s if installed out STROBE LT and RECOG LT Switches On Do not use strobe lights during flight through fog or clouds 5 LOG LT TAXI Switches On as desired 6 STALL WARNING Switches On 7 8 In a strong crosswind it may be necessary to wait until indication of airspeed is achieved...

Page 86: ...inute prior to gear retraction to throw off as much slush as possible 1 LANDING GEAR Switch UP Landing gear should be fully retracted prior to retracting flaps 2 Yaw Damper PHI or SEC ENG Button Depress 3 Flaps UP prior to VFE 4 Anti Ice Systems As required Even small accumulations of ice on the wing leading edge can cause aerodynamic stall prior to activation of the stick shaker and or pusher The...

Page 87: ...ff at field elevations above 8500 feet pressure altitude refer to PRES SURIZATION SYSTEM OPERATION this section a Cabin Altitude and Cabin Climb Indicators Monito b Cabin RATE Selector As desired 7 lDG LT TAXI Switches OFF 8 Autopilot APPR Ught OUT I 9 HYDRAUUC PRESSURE Check nonnal 10 ANGLE DF ATTACK Indicators Cross check pilot s and copilot s instruments for relative agreement 2 30 FAA APPROVED...

Page 88: ...Switches if installed NORMAL FL 350 Checks 1 COOL FAN Switch FAN or OFF Refer to FREON COOUNG SYSTEM Section I FL 410 Checks Aircraft 35 067 thru 35 112 except 35 107 36 018 thru 36 031 1 Crew and Passenger Oxygen Masks Don above Right Level 410 Ensure lanyards have been pulled CRUISE Once established at cruise altitude CJeW duties consist mainly of monitoring aircraft systems indications and annu...

Page 89: ...red Even smaO accumulations of ice on the wing leading edge can cause aerodynamic stall prior to activation of the stick shakerand or pusher These ice accumulations can also cause angle of attack indicator information to be unreliable Anti ice systems should be turned on prior to flight into visible moisture and Ram Air Temperature of 10 C or below I FL 180 or Transition Level Checks 1 Barometric ...

Page 90: ... It is recommended that if turbulence is anticipated due to gusty winds wake turbulence or wind shear the ap proach speed be increased For gusty wind conditions an increase in approach speed of one half the gust fac tor is recommended 4 Fuel Balance Check 5 Avionics a Avionics Equipment Set for approach b Radio Altimeter Set to approach minimums c Crew Approach Briefing Complete FAA APPROVED 4 30 ...

Page 91: ...ft landing light will not illuminate unless the left main gear is down and locked The right landing light will not illuminate Wlless the right main gear is down and locked 5 ANTI SKID Switch On ANTI SKID GEN Ughts Out 6 ENG SYNC Switch OFF 7 Raps DN 8 HYDRAUUC PRESSURE Gage Check normal 9 AIR IGN Switches On 10 Autopilot Disengage 3 Use control wheel trim switch to disengage autopilot Control whee...

Page 92: ...6 Climb at Approach Climb Speed 7 When clear of obstacles accelerate to VREF 30 and retract flaps 1 SPOll ER Switch EXT after touchdown If upon touchdown one or more ANTI SKID GEN ICAU110N I lights come on anti skid protection for the associated wheel is inoperative and has reverted to manual brake control 2 Brakes As required If not already operating do not tum on cooling system ICAUTION during l...

Page 93: ...STAB WING HEAT Switch As required Monitor WING TEMP and STAB TEMP Indicators to prevent overheat condi tion 5 lDG LT TAXI Ughts and RECOG LT As desired i Do not use strobe lights when taxiing in the vicinity of other aircraft Navigation lights should be on for an night operations 6 Thrust Lever on engine started first CUTOFF optional i Idle engine for 2 minutes prior to thrust lever rutoff 7 SPOn ...

Page 94: ...ERTER Switches OFF Fuel Transfer OFF CROSSFLOW Valve CLOSE 13 On aircraft not incorporating SB 35 36 32 4 Hydraulic Pressure Bleed to zero 0 ICAUTION I Failure to bleed hydraulic pressure from the system be fore setting the battery switches OFF could result in nose gear retraction if the landing gear selector valve malfunctions If the parking brake is set use of flaps to bleed hydrauliC system pre...

Page 95: ...ft incorporating AMK 80 17 or AAK 81 1 a Starter Engaged and CUR UM Ught s Out 8 Circuit Breakers In 9 Avionics As required 10 Coffee Oven Switches if installed As required 11 Anti ice Systems As required The wings vertical and horizontal stabilizers flight con trol surfaces and engine inlets must be free of frost snow and ice Anti ice systems should be turned on prior to flight into visible moist...

Page 96: ...omplete Runway Uneup 1 Parking Brake Released Check PARK BRAKE light if installed Out 2 Transponder On I 3 Both PITOT HEAT Switches On Check PITOT HEAT light s if installed out 4 lights a STROBE LT and RECOG LT Switches On _NOTE Do not use strobe lights during flight through fog or clouds b LOG LT TAXI Switches On as desired 5 STALL WARNING Switches On In a strong crosswind it may be necessary to ...

Page 97: ...free of frost ice and snow before takeoff During periods of precipitation once the airplane has been de iced anti icing is likely to be required to ensure that the airplane remains aerodynamically clean for de parture De icing anti icing must be accomplished at the last possible time prior to takeoff to maximize the time that anti icing will be able to provide protection holdover time Refer to Lea...

Page 98: ...d Turbine Temperature fIT has a tendency to increase more rapidly due to the increased spool up times Additionally higher than normal oil pressure can be expected which may exceed the maximum allowable transients During engine starts in cold conditions If Fan SPeed Nt does not rise with Turbine Speed N2 or stops during the start attempt abort start If Turbine Temperature fIT is rising rapidly and ...

Page 99: ... used with extreme caution on slip pery surfaces and only when absolutely necessary to maintain directional control Do not use thrust reversers if installed if taxiways and ramps are covered with slush ice standing water or snow except in the interest of safety TAKEOFF If anti ice systems are required for takeoff the systems should be energized prior to setting takeoff power Refer to Section Vfor ...

Page 100: ...moderate to heavy braking pressure 3 Prior to touchdown set ANTI SKID switch to ON and check ANTI SKID lights are out LANDING Use normal landing procedures if runway is clean and dry Refer to Section V for landing distance factors to be applied when landing on wet or icy runways AfTER CLEARING RUNWAY During moderate to heavy braking action on patchy snow or ice avoid use of nose wheel steering abo...

Page 101: ... flaps 4 If the aircraft is to be parked for an extended period at ambient tem peratures of 200F 6 7 C or below it is recommended that the crew oxygen masks be stowed in a heated room or the cabin should be warmed to at least 20 F 6 7 C before use 5 If the aircraft is to remain in subfreezing temperatures for an extended period remove water and beverage containers from the aircraft Remove toilet t...

Page 102: ...ontrol to altitude selected on CABIN ALT Controller d CABIN CUMB Speed Indicator Stabilize at zero e RATE Knob Reset to nominal position f AUTO MAN Switch AUTO g CABIN ALT Controller Reset if required to appropriate cabin altitude for flight altitude Aircraft 35 107 35 113 Subsequent and 36 032 Subsequent If cabin altitude should increase to 8750 250 feet or above the automatic pressurization mode...

Page 103: ...rating rules pertaining to the use of oxygen at high cabin altitude must be observed TAKEOFF AT FIElD ELEVATION ABOVE 8500 FEET Aircraft with Emel lency Pressurization Override Switches BEFORE STARTING ENGINES 1 EMER PRESS Switches OVERRIDE 2 BLEED AIR Switches ON 3 CAB AIR Switch OFF 4 AlJTO MAN Switch MAN Applicable operating rules pertaining to the use of oxygen at high cabin altitude must be o...

Page 104: ...atic there is no ram airflow through the heat exchanger and possible damage to air condi tioning components could result Cabin overheating and damage to cabin components may also occur 3 MAN AUTO HOT Knob Rotate out of MAN detent to AUTO and turn to desired temperature In flight the cabin temperature control system will automatically maintain the cabin at the desiJed temperature 4 If satisfactory ...

Page 105: ... 89 1 do not operate cooling system above FL180 On aircraft Incorporating FCN 89 1 do not oper ate cooling system above FL350 Do not turn on cooling system unless Aircraft 35 067 thru 35 147 and 36 018 thru 36 035 1 With one engine operating the ammeter reads below 200 amps 2 With both engines operating each ammeter reads below 250 amps Aircraft 35 148 subsequent and 36 036 subsequent 1 With one e...

Page 106: ...erating the ammeter reads below 150 amps 2 With both engines operating each ammeter reads below 250 amps 1 On aircraft with damper control knob on blower duct in aft cabin Damper Control Knob Rotate to CLOSE Auxiliary heater will not operate unless knob is in CLOSE position On aircraft with cabin blower switch on blower duct in aft cabin Cabin Blower Switch ON 2 AUX HT Switch HI or LO as desired C...

Page 107: ... Switch FAN CABIN BLOWER Rheostat copilot s side panel if installed As desired 2 For additional cockpit air circulation Cockpit Air Control Rotate to desired setting 2 50 If the overhead air outlets are closed the cockpit blower must be turned off to prevent overheating blower motor FAA APPROVED 4 30 76 REISSUED 2 25 81 CHANGE 10 ...

Page 108: ...ed anytime spoilers are ex tended 1 degree or more during normal spoiler operation With flaps lowered beyond 13 and spoiler extended the SPOILER light will flash If the aileron augmentation system malfunctions the AUG AIL light comes on and spoilers retract However actuating the SPOILERON RESET switch will restore normal operation if the system clears itself During Spoileron Spoiler Check if AUG A...

Page 109: ...e in the OFF pOSition no oxygen is sup plied to the cabin 2 With the PASS OXY Valve in the NORM position and the PASS MASK Valve in the AUTO position the passenger oxygen masks will drop from their storage compartments if the cabin altitude reaches 14 000 750 feet Whenever the oxygen masks deploy the upper center panel lights will illuminate to provide maximum visibility for donning masks The pass...

Page 110: ...abin altitudes above 20 000 feet b With NORMAL position control lever up selected on the mask regulator the mask will deliver diluted oxygen When using oxygen at cabin altitudes below 20 000 feet the NOR MAL position should be selected to conserve oxygen and pro vide greater oxygen duration times Operate 6600214 series masks with Robertshaw regula tors as follows a With NORMAL selected on the Pres...

Page 111: ...as foUows a To check for oxygen availability to the mask while stowed depress the PRESS TO TEST buttonlknob on the bottom of mask pressure regulator oxygen will flow while button is held b To don crew oxygen masks c 1 Remove hats and ear muff type headsets Headsets and eyeglasses worn by crew members may interfere with quick donning capabilities 2 Squeeze and hold the red handles on the mask press...

Page 112: ... manual are based on full anti skid braking from first brake application to com plete stop NOTE NOTE FAA APPROVED 4 30 76 2 55 REISSUED 2 25 81 CHANGE 10 OXYGEN SYSTEM CONT d To obtain 100 oxygen at any time depress 100 lever on mask pressure regulator e For emergency operation select EMERGENCY rotate PRESS TO TEST button knob to With the mask pressure regula tor controls in this position the crew...

Page 113: ...continue until either the gear is lowered or one of the above conditions is corrected NOTE NOTE 2 56 FAA APPROVED 4 30 76 REISSUED 2 25 81 CHANGE 13 BRAKE SYSTEMS CONT Anti skid Off Operation When anti skid is inoperative care must be used during brake application and stopping distances will be increased Refer to Section IV for operation of the brake system with anti skid off and Section V for inc...

Page 114: ...tion of any of the amber fuel system valve lights on the fuel control panel except fuel jettison valve lights indicates the corresponding valves are not in the position selected Momentary illumination while the corresponding valve is in transit after switching modes indicates proper op eration On aircraft incorporating SB 35 36 28 11 illumination of the annunciator installed in either STANDBY PUMP...

Page 115: ...2 58 INTENTIONALLY LEFT BLANK FAA APPROVED 4 30 76 REISSUED 2 25 81 CHANGE 12 ...

Page 116: ... point or alternate if fuselage tank fails to transfer 2 FUS TANK XFER ALL Switch OFF after EMPlY light comes on NORMAL FUSElAGE FUEL TRANSFER Model 35A with FUS VALVE Switch and Model 36A CAUTION I Do not energize fuselage fuel transfer system when r wing and tip tanks are full 1 FUS TANK XFER ALL Switch fER when tip tank fuel quantity indicates 760 pounds or less in each tank Model 35A or zero f...

Page 117: ...2 60 INTENTIONALLY LEFT BlANK FAA APPROVED 4 30 76 REISSUED 2 25 81 CHANGE 12 ...

Page 118: ...cted the right fuselage transfer valve and the crossflow valve will open Fuel will gravity flow from the fuselage tank until the wing tank heads are equal E If the crossflow valve fails to open a right wing heavy condition will occur 3 FUS VALVE Switch CLOSE when wing fuel quantity starts to decrease or prior to approach NOrE If the right fuselage transfer valve FUS VALVE is al r lowed to remain o...

Page 119: ...hrough open crossflow valve into opposite wing 1 CROSSFLOW Switch OPEN 2 STANDBY PUMP Switch heavy wing ON 3 STANDBY PUMP Switch light wing Off 4 CROSSFLOW Switch CLOSE after fuel balance is obtained 5 STANDBY PUMP Switches Off 6 If the preceding procedure fails to balance fuel unequal power set tings may be used to balance fuel load 2 62 FAA APPROVED 4 30 76 REISSUED 2 25 81 CHANGE 12 ...

Page 120: ...ling I procedures To prevent fuel filter icing and possible engine flameout anti icing additive must be blended with the fuel in the concentration specified in FUEL UMITS Section I I The electronic fuel computers must be adjusted to the recommended specific gravity position as specified in FUEL UMITS Section I Refer to Addendum FUEL SERVICING for adjustment procedures FAA APPROVED 4 30 76 REISSUED...

Page 121: ...P and STAB TEMP indicators When the indicator pOinter is in the green arc the wing or stabilizer structure is above 35 F 1 7 C and is warm enough so that ice will not adhere to the surface When the pointer is in the yellow area the structure is approaching a too hot condition When the pOinter is in the red arc the structure is below 35 F 1 7 C and indicates the anti ice system should be used if in...

Page 122: ...he out board wing leading edge to enhance visual detection of ice accumu lation The wing inspection light is illuminated by pressing the WING INSP LT switch copilot s dimmer panel The light is extin guished when the switch is released 5 If the presence of ice on the wing leading edge is detect ed the normal approach speeds must be increased per the WING HEAT FAILURE LANDING procedure in Section IV...

Page 123: ...ons remove any accumulated ice prior to next flight In the event of significant ice accumulation or failure of any portion of the anti ice system refer to INADVERTENT ICING ENCOUNTER and or appropriate Anti Ice System Failure procedures in Section IV When using anti ice systems at high altitude the cabin altitude may exceed 8000 feet unless engine speed is increased to compensate for the additiona...

Page 124: ...Switches Energize pitot tube stall warning vane heaters and total temperature probe if installed heaters 4 WSHLD RADOME RADOME or RAD Switch Controls windshield and radome alcohol anti ice system 5 On aircraft 35 067 thru 35 112 except 35 107 36 018 thru 36 031 WSHLD HEAT Switches and IN NORMAL OUT DEFOG Knob Control bleed air to the windshield for defog anti ice and rain removal On aircraft 35 10...

Page 125: ... for reduced defog flow MANUAL OPERATION 1 IN NORMAL OUT DEFOG Knob Pull out 2 WSHLD HEAT AUTO MAN Switch MAN 3 WSHLD HEAT ON OFF Switch Hold ON until the desired amount of airflow is obtained As the valve opens the green WSHLD HT light will illuminate and the defog flow will remain at the level it is when the ON OFF switch is released If the red WSHLD OV HT light comes on the airflow will automat...

Page 126: ... To reduce flow in the event of excessive noise or system cycling a AUTO MAN Switch MAN b ON OFF Switch Hold to OFF until fbw is acceptable Row will remain at the level it is when the ON OFF switch is released MANUAL OPERATION 1 IN NORMAL OUT DEFOG Knob Pullout 2 WSHLD HEAT AUTO MAN Switch MAN 3 WSHLD HEAT ON OFF Switch Hold ON green WSHLD HEAT light will illuminate until the desired amount of air...

Page 127: ... position between ful ly closed and fully open If a change in airflow is desired set switch to OFF or ON until desired airflow is obtained then set switch to HOLD TO ACTIVATE THE SYSTEM 1 WSHLD HT Switch ON The green WSHLD HT light will come on when the control valve begins to open If the red WSHLD OV HT light comes on the overheat shutoff valve will automatically close until the windshield has co...

Page 128: ...eat shutoff valve may cycle to prevent over heating of the windshield When the overheat shutoff valve cycles closed the green WSHLD I IT light will ex tinguish The system will automatically reset green WSHLD HT light will illuminate after the system cools 2 To reduce flow in the event of excessive noise or system cycling WSHLD HT Switch OFF until flow is acceptable then HOLD IF WSHLD OV HT UGI IT ...

Page 129: ...etween the cabin headliner and the fuselage skin to prevent lowering the cabin temperature 2 If operation of the freon cooling system is not desired W S AUX DEFOG HEAT Switch CKPT E Power for the windshield auxiliary defog heat system must be supplied by an engine generator or GPU I FOR MAXIMUM WINDSHIELD DEFOGGING Aircraft incorporating AAK 86 1 or S8 35 36 21 17 1 Approximately 15 minutes prior ...

Page 130: ...will last for approximately 2 hours 9 minutes The ALC AI light will il luminate when alcohol level is low Set WSHLD RADOME RAD switch OFF when alcohol is depleted or clear of icing conditions NOTE Use WSHLD RADOME position of the switch if bleed air for the windshield anti ice has failed or as needed WING AND HORIZONfAL STABIUZER ANTI ICE Wing and horizontal stabilizer anti ice systems utilize eng...

Page 131: ...so energize en gine anti ice CAUTKJN I 2 74 To prevent damage to the engine inlet sensor heating el ement naceUe heat operation should be limited to 30 seconds if the engine is not running Wumination of the L or R ENG ICE lights with the NAC HEAT switches On indicates that bleed air pres sure is not being applied to the naceUe heat anti ice system due to a malfunction Wumination of the L or R ENG ...

Page 132: ... PITOT HEAT light indi cates insufficient current is being applied to a pitot head heating element A failure in either system will cause the light to illuminate The light will also illuminate whenever the BAT switches are On and either PITOT HEAT switch is OFF On aircraft equipped with L R PITOT HEAT lights a failure in a pitot head heating system will illuminate the applicable light The applica b...

Page 133: ...lates pas senger speaker volume while addressing passengers when the Mic Function Selector is in the PASS SPKR position This control does not affect headphone aural warning or microphone audio when the microphone is being used in VHF 1 or 2 HF or INPH on the Mic Function Selector 3 Sidetone Two small holes are provided on the front of the Audio I Control Panel Figure 2 4 for insertion of a screwdr...

Page 134: ...and NAV 2 receivers respectively 3 ADF 1 and ADF 2 Switches These are three position switches The PASS center position provides audio to the passenger speaker when the PASS SPKR VOL ADJ OFF switch is in the PASS SPKR position The up position provides headphone and cockpit speaker audio only When in the up position these switches provide audio from the ADF 1 and ADF 2 receivers respectively The up ...

Page 135: ... Adjust _ Speaker Aural Warn Adjust 2 78 AUF AUF 2 aeeie CIFf SPKRI lIME tIeR Hf PHOfE e e Mixer Switches cFf EIER C 0 _MSS II _Microphone Function Selector PASr 11 AUOIO CONTIOl PILOT S AUDIO CONTROL PANEL Figure 2 4 Sheet 1 of 2 FAA APPROVED 4 30 76 REISSUED 2 25 81 CHANGE 10 ...

Page 136: ...M PANEL CONT Headphone Aural Warning Adjust Headphone Sidetone Adjust Ih I Mixer Switches L Microphone Function Selector COPILOT S AUDIO CONTROL PANEL Figure 2 4 Sheet 2 of 2 FAA APPROVED 4 30 76 REISSUED 2 25 81 CHANGE 10 I 2 79 ...

Page 137: ... these positions are selected microphone inputs are provided for the respective transceiver 2 INPH Position When this position is selected on one AUDIO CONTROL Panel interphone is provided If the opposite Micro phone Function Selector is in the VHF 1 or 2 HF or INPH posi tion audio will be provided to the opposite speaker and headphones If the opposite Microphone Function Selector is in the PASS S...

Page 138: ...ne Function Selector Rotate to desired poSition 4 To provide ADF audio to the PASS SPKR a ADF 1 or ADF 2 if installed Mixer Switch Set to mss position b PASS SPKR VOL ADJ Switch Set to VOL ADJ c PASS SPKR VOL Control Rotate to approximate mid position d Tune in desired station on ADF receiver and adjust cockpit speaker volume utilizing ADF system volume control e PASS SPKR VOL ADJ Switch Set to PA...

Page 139: ...the On position prior to activating any of the EMER IT TEST ARM DIS ARM switch functions Setting the switch to TEST simulates a power failure of the normal electrical system and illuminates the wing inspection light door light and upper center panel lights Setting the switch to ARM will ann the system to illuminate the emergency lights in the event of a power failure of the normal electrical syste...

Page 140: ...rmal electrical system and illuminates the emergency exit light door light and upper center panel lights Setting the switch to ARM will arm the system to illuminate the emergency lights in the event of a power failure of the normal electrical system Setting the switch to DISARM isolates the emergency lights from the emergency power supply The switch should be set to ARM prior to takeoff If the swi...

Page 141: ...ed the light will extinguish Ifthe condition recurs the light will again illuminate Any time a red annunciator light illu minates the MSTR WARN lights on the pilot s and copilot s instrument panel will also illuminate and flash Depressing the MSTR WARN light will extinguish the MSTR WARN light however the annunciator light will re main on as long as the condition exists NOT For aircraft serials 35...

Page 142: ... left engine Fan NI or Turbine N2 speed The indicator indicates fan sync when the ENG SYNC selector switch is in the FAN position and tur bine sync when the selector switch is in the TURB position The indicator can be used to manually synchronize the engine or to monitor operation of the automatic synchronizer The indicator is operative whenever the right fuel computer is On and operative Automati...

Page 143: ...umes 3 31 Flight Controls Control System Jam 3 35 Aileron Jam 3 35 Elevator Jam 3 35 Rudder Jam 3 36 FAA APPROVED 4 30 76 III 1 REISSUED 2 25 81 CHANGE 12 SECTION III EMERGENCY PROCEDURES TABLE OF CONTENTS Electrical Complete AC Power Failure Loss of all Inverters 3 1 Battery Overheat 3 2 Current Limiter Failure Illumination of CUR LIM CUR LIMITER Light in Flight 3 3 DC Power Loss Essential Bus Ai...

Page 144: ...3 45 Landing Both Engines Inoperative 3 46 Stall Warning Activates 3 47 Takeoff Aborted Takeoff 3 48 III 2 FAA APPROVED 4 30 76 REISSUED 2 25 81 CHANGE 14 TABLE OF CONTENTS Cont Overspeed Recovery Overspeed Warning Horn Activates 3 37 Pitch Axis Malfunction 3 38 Roll or Yaw Axis Malfunction 3 41 Fuel FUEL PRESS Light Illuminated 3 42 Landings Ditching 3 43 Emergency Braking 3 45 Emergency Evacuati...

Page 145: ...ristics and the flight manual procedures are essential in the handling of any emergency situation OVERRIDING CONSIDERATIONS In all emergencies the overriding consideration must be to Maintain Airplane Control Analyze the Situation Take Proper Action TERMINOLOGY Many emergencies require some urgency in landing the aircraft The degree of urgencY required varies with the emergency therefore the terms...

Page 146: ...ained 7 INV Circuit Breakers Pull and reset 8 If AC power is not regained the following partial list of equipment will not be usable a Vertical and directional gyros b Autopilot and yaw dampers c Mach Trim System d Avionics displays e Electrical servoed altimeter s f Engine oil pressure indicators g Spoilerons h Spoilers inoperative in flight only Spoilers will operate normally on ground i Nose wh...

Page 147: ...e Maintenance Manual after landing BAT 140 UGHT IlLUMINATED 1 BAT TEMP Indicator Monitor to detennine affected battery 2 Affected Battery Switch OFF 3 Land as soon as practical BAT 160 UGHT IU lJMINATED 1 BAT TEMP Indicator Monitor to detennine affected battery 2 Affected Battery Switch OFF 3 Land as soon as possible 3 2 FAA APPROVED 4 30 76 REISSUED 2 25 81 CHANGE 10 ...

Page 148: ...imits b Continue flight but monitor electrical loads If both 275 amp current limiters have faded Aircraft not incorporating AMK 85 1 a Electrical Load Reduce Electrical power to the essential buses is being supplied by the ship s batteries All nonessential equipment should be turned off or circuit breakers pulled Fully charged batteries should power the minimum electrical equipment for night instr...

Page 149: ... A I I I I I I I II I I I I I I I I Left Essential Bus jH Right Essential Bus II PILOT S CB PANEL L ___ _ JL COPILOTS CB PANEL _ J Figure 3 1 IF AN ESS BUS ClRcurr BREAKER OPENS IN FUGHT Affected Essential Bus 1 ESS BUS Cirruit Breaker copilot s panel Pull if not alrsady open E Do not reset the ESS BUS TIE Circuit Breaker 2 Essential Bus elecbicalload Reduce as follows a AUTOPILOT Switch OFF b Ins...

Page 150: ...ostats OFF if conditions pennit d Restrict operation of the following systems to one at a time 1 Pitch roll and yaw trims 2 Communication transmissions 3 Fuel transfer and standby pumps 4 Raps 5 Landing Gear e Pull the follOwing circuit breakers on the failed essential bus l COMM 2 S WARN HT 3 PITOT HT 4 Yaw damper f Select the following primary or secondary systems for opera tion from the remaini...

Page 151: ...al buses r LOADS ESS A LOADS I k t A II Wt t A I f f I 1__ Left Essential A B Ir Right Essential A tSliJ e I 1 LOADS II ESS B LOADS LESS At BUS A RESS BBUS t TIE t BBUS f I 1__ Left Essential B Bus Ri9ht Essential B I PILOT S CB PANEL L ___ _ JL _ S _ J Rgure 3 2 IF AN ESS BUS CIRCUIT BREAKER OPENS IN FUGHT Affected Essential Bus 1 ESS BUS TIE Circuit Breaker copilot s panel Pull if not already op...

Page 152: ...om systems on opposite essential bus if differences exist and icing conditions are present NOTE FAA APPROVED 4 30 76 3 7 REISSUED 2 25 81 CHANGE 10 DC POWER LOSS ESSENTIAL BUS Aircraft 35 202 thru 35 204 35 206 subsequent aircraft 36 041 subsequent and prior aircraft incorporating AMK 78 13 CONT 4 Restrict operation of the following systems to one at a time a Pitch roll and yaw trims b Fuel transf...

Page 153: ...162 pounds of fuselage fuel will be un usable 12 Land as soon as practical NOTE CAUTION CAUTION NOTE 3 8 FAA APPROVED 4 30 76 REISSUED 2 25 81 CHANGE 14 DUAL GENERATOR FAILURE 1 Electrical Load Reduce a COOL FAN Switch OFF b AUX HT Switch if installed OFF c On aircraft incorporating AAK 86 1 or SB 35 36 21 17 W S AUX HEAT DEFOG Switch OFF 2 L and R IGN ST Circuit Breakers main power bus Check and ...

Page 154: ...hrs 45 min 15 Second EMER PWR Switch if installed On 5 The equipment powered by the second Emergency Power Supply is dependent upon owner preference The operating time for the second Emergency Power Supply will vary with the amount of equipment powemd and the total electrical draw of that equipment 16 The follOwing is a list of conditions that will exist a Hight control trim will remain at its las...

Page 155: ...m valves will remain in their last position g Fuel Quantity Fuel Row and Fuel Counter indicators wiD be inoperative h Mach Trim and stick puller will be inoperative Do not exceed MMo 0 74 MJ i All AC electrical systems will be inoperative j Spoilers will be inoperative k stan warning system will be inoperative Maintain adequate margin above stall speed by reference to the airspeed indicator l Engi...

Page 156: ...sitive rate of c6mb is established I 5 When clear of obstacles accelerate to V2 30 and retract flaps I Lateral control is improved with tip tanks empty If time permits it is recommended that tip tank fuel be jettisoned 6 FUEL JTSN Switch ON Oights on Off prior to touchdown Time to reduce aircraft weight from maximum takeoff weight to maximum landing weight is approximately 40 minutes Time to jet t...

Page 157: ...e 2 Thrust Lever operative engine Increase as required 3 Flaps 20 maximum H aircraft is configured with landing flaps ON r when engine failure occurs thrust increase on operative engine and flap retraction to 20 should be near simultaneous actions 4 Airspeed VREF 10 minimum 5 Rudder Trim As required _NOTE During a coupled approach full rudder trim may be re r quired with an actual engine failure U...

Page 158: ...INTENIlONAlLY LEFT BlANK FAA APPROVED 4 30 76 REISSUED 2 25 81 CHANGE 12 3 13 ...

Page 159: ...d arms the fire extinguishing system c ARMED Light Depress one d If fire continues 1 Depress remaining ARMED light 2 Land as soon as possible 3 Go to step e If fire extinguishes 1 Land as soon as practical 2 Go to step e e AIR IGN Switch OFF f ENG SYNC Switch OFF g Yaw Damper OFF retrim as desired then Yaw Damper Engage h JET PUMP Switch Off STANDBY PUMP Switch Off i START GEN Switch OFF j Electri...

Page 160: ...following an engine faillJJ e which was accompanied by indications of internal en gine damage or fire Do not attempt an airstart without an indication of fan rotation If Turbine Temperature IT11 is approaching the limit and rising rapidly immediately place Thrust Lever in ClITOFF position and abort start At least one inverter must be operating to energize oil pressure indicator If oil pressure is ...

Page 161: ...ed Turbine Speed N2 up to 45 and any altitude up to 30 000 feet Maintaining an airspeed which will maintain a minimum stabilized Tur bine Speed N2 of 15 RPM will enhance airstart capability Do not attempt fuel computer OFF airstart above 20 000 feet 3 16 Figure 3 3 FAA APPROVED 4 30 76 RBSSUED 2 25 81 CHANGE 10 ...

Page 162: ...CROSSFLOW Switch CLOSE c FUS TANK XFER RLL Switch OFF d FUS VALVE Switch if installed CLOSE 5 Electrical Load Reduce 6 NAC HEAT Switch OFF 7 BLEED AIR Switch OFF 8 START GEN Switch START Starter engaged light if installed will illuminate 9 Thrust Lever at minimum 10 Turbine Speed N2 and indication of Fan Speed NI rotation IDLE 10 AIR IGN Ught and FUEL FLOW Check 11 Turbine Temp nT Check rise withi...

Page 163: ...h Engines Are Operating 22 On aircraft 35 067 thru 35 389 except 35 370 and aircraft 36 018 thru 36 047 except aircraft incorporating AMK 80 17 or AAK 81 1 Starter Disengagement Check 3 18 a AUX HT if installed and COOL FAN Switches OFF b Battery Switches OFF c Ammeter Check total current indication is less than 100 amps If total current indication is greater than 100 amps 1 Battery Switches On 2 ...

Page 164: ...set Aircraft 35 148 thru 35 389 except 35 370 and aircraft 36 036 thru 36 047 except aircraft incorporating AMK 80 17 or AAK 81 1 a TEST Selector Switch Rotate to L CUR UM b TEST Button Depress Green current limiter light will illumi nate and remain on while button is held L GEN light will illumi nate and right generator voltage may be reduced approximately 2 vdc c TEST Selector Switch Rotate to R...

Page 165: ...JET PUMP Switch ON b STANDBY PUMP Switch ON c CROSSFLOW Valve CLOSED d FUS TANK FER ALL Switch OFF e FUS VALVE if installed CLOSED 5 START GEN Switch OFF 6 Electrical Load Reduce 7 NAC HEAT Switch OFF 8 BLEED AIR Switch OFF 9 AIR IGN Switch ON check AIR IGN light illuminated 10 Thrust Lever IDLE Check FUEL FLOW indication 11 Turbine Temp ITT Check rise within 5 seconds 12 If light off has not occu...

Page 166: ... Thrust Lever Cutoff 20 AIR IGN Switch OFF 21 Repeat WINDMIWNG A1RSTART FUEL COMPUTER ON or STARTER ASSIST A1RSTART FUEL COMPUTER ON procedure If Engine WiD Not Restart 22 Perform ENGINE SHUTDOWN IN FLIGHT procedure Section IV I FAA APPROVED 4 30 76 REISSUED 2 25 81 CHANGE 12 3 21 ...

Page 167: ...10 seconds to allow fuel to drain from engine 4 Fuel Supply Check a Fuel available from wing tank b ARE PULL or ENG ARE PULL T Handle Push in 5 Fuel Panel Switches As follows a STANDBY PUMP Switch ON b JET PUMP Switch Off c CROSSFLOW Valve CLOSED d FUS TANK XFER FILL Switch OFF e FUS VALVE if installed CLOSED 6 Electrical Load Reduce 7 NAC HEAT Switch OFF 8 BLEED AIR Switch OFF 9 START GEN Switch ...

Page 168: ...uel computer OFF mode of operation 16 BLEED AIR Switch ON 17 NAC HEAT Switch On as required If No Indication of Ught Off is Obtained in 10 Seconds 18 Thrust Lever CUTOFF 19 START GEN Switch OFF 20 Repeat STARTER ASSIST AIRSTART FUEL COMPUTER OFF procedure Not more than three consecutive starter assist airstarts should be attempted to prevent severe battery drain and generator burnout If Engine Wil...

Page 169: ...80 17 or AAK 81 1 a MAIN BUS TIE Circuit Breaker copilot s panel Pull b One START GEN Switch OFF Check ammeter reading on opposite generator approximately doubles then switch back to GEN c Opposite START GEN Switch OFF Check a1TU1 eter read ing on opposite generator approximately doubles then switch back to GEN d MAIN BUS TIE Circuit Breaker Reset Aircraft 35 148 thru 35 389 except 35 370 and airc...

Page 170: ...d aircraft 36 018 thru 36 047 incorporating AMK 80 17 or AAK 81 1 a L CUR UMITER and R CUR UMITER Ughts Check extinguished Aircraft 35 370 35 390 and subsequent and aircraft 36 048 and subsequent a CUR UM Ught Check extinguished FAA APPROVED 4 30 76 REISSUED 2 25 81 CHANGE 10 3 25 ...

Page 171: ...CUTOFF Wait 10 seconds to allow fuel to drain from engine 4 Fuel Supply Check a Fuel available from wing tank b ARE PULL or ENG FIRE PULL T Handle Push in 5 Fuel Panel Switches As follows a JET PUMP Switch Off b STANDBY PUMP Switch ON c CROSSFLOW Valve CLOSED d FUS TANK XFER ALL SWitch OFF e FUS VALVE if installed CLOSED 6 START GEN Switch OFF 7 Electrical Load Reduce S NAC HEAT Switch OFF 9 BLEED...

Page 172: ...ght indicates that engine oil pressure is be law 25 psi Several configurations of the oil pressure light exist Single LO OIL PRESS light on the annunciator panel Illumination of this light indicates oil pressure of either engine is below 25 psi Single OIL PRESS light on the annunciator panel Illumination of this light indicates oil pressure of either engine is below 25 psi L LO OIL and R LO OIL li...

Page 173: ...EED AIR Land BLEED AIR Rlights illuminate the secondary pressure regulator of one of the air modulating valves has failed 1 R BLEED AIR Switch OFF If both lights go out continue flight in this configuration If both lights do not go out proceed to step 2 2 R BLEED AIR Switch On and L BLEED AIR Switch OFF If both lights go out continue flight in this configuration If both lights do not go out procee...

Page 174: ... 45 000 feet to 15 000 feet requires approximately 2 minutes 45 seconds Hats and ear muff type headsets must be removed prior to donning crew oxygen masks The HORN SILENCE switch will mute the cabin alti tude warning horn for 60 seconds 9 Pilot and Copilot OXY MIC Switches ON _NOTE Communication between crew members can be accom I plished by using the INPH function of the AUDIO CON TROL PANEL and ...

Page 175: ... at the interface and do not have white lines If all latch pins are fully engaged and door actuator hook s are disengaged the most probable cause of an illumi nated DOOR light is a latch pin switch malfunction If light was accompanied by evidence of door failure Door failure may be indicated by loud noise pressuriza tion leak or rumble emanating from door area Do not approach door 1 FASTEN SEAT BE...

Page 176: ...ow 8 AUTO MAN Switch MAN 9 UP DN Manual Control red Up maximum 13 000 feet NOTE NOTE FAA APPROVED 4 30 76 3 31 REISSUED 2 25 81 CHANGE 13 CABIN COCKPIT FIRE SMOKE OR FUMES 1 Crew Oxygen Masks Don Select 100 oxygen 2 Smoke Goggles Don if available 3 Pilot and Copilot OXY MIC Switches ON It may be necessary to select EMER or EMERGENCY on 6600214 series or Scott ATO mask regulator if the mask does no...

Page 177: ...d R STALL WARN 26 VAC BUS AUX INV if installed 2ND ROW MAIN BUS TIE R MAIN BUS R IGN ST SEC INV NOTE 3 32 FAA APPROVED 4 30 76 REISSUED 2 25 81 CHANGE 13 CABIN COCKPIT FIRE SMOKE OR FUMES CONT If time and conditions permit 10 Isolate source of smoke or fumes If Bleed Air System is suspected source R BLEED AIR Switch OFF If smoke is reduced continue operation with switch OFF If smoke is not reduced...

Page 178: ... breaker panels is now off Allow time for smoke or fumes to dis sipate If e1ectrical smoke or fumes continue 2 AU BUS TIE Circuit Breakers Leave pulled do not reset 3 All other Copilot Circuit Breakers Reset This procedure reinstates power to the copilot s circuit breaker panel 4 Pilot s Circuit Breaker Panel Pull the following circuit breakers On aircraft 35 067 thru 35 201 35 205 and aircraft 36...

Page 179: ... not reset 12 All Circuit Breakers on panel with power removed Pull 13 One DC BUS Circuit Breaker Reset Then reset circuit break ers powered by that BUS circuit breaker _NOTE Pa after resetting each circuit breaker to deter mine defective system Whenever high electrical loads or smoke or fumes occur pull the last circuit breaker reset Hot wired circuit breakers L and R STALL WARN DOOR ACTR ENTRY L...

Page 180: ...r As required to control roll and track Yaw damper should be on to minimize roll oscilla tions For prolonged flight in a sideslip set CROSSFLOW switch to OPEN and both STANDBY PUMP switch es to ON 2 Rnal Approach Configuration Gear ON Raps 20 3 Rnal Approach Speed VREF 10 4 Maintain power to touchdown and do not flare ELEVATOR JAM 1 Primary Pitch Trim As required for pitch contra 2 Final Approach ...

Page 181: ...prolonged flight in a sideslip set CROSSA OW switch to OPEN and both STANDBY PUMP switches to ON 3 Fmal Approach Configuration Gear DN Raps 20 4 Fmal Approach Speed VREF 10 S Maintain power to touchdown and do not flare 6 After landing maintain directional control with differential braking 3 36 If asymmetric power is used do not retard power until directional control is established FAA APPROVED 4 ...

Page 182: ...ust be smoothly and steadily ap plied to prevent encountering excessiva aileron activity and air ame buffet Beyond MMO a 1 5 g pullup may be sufficient to excite aileron activity and the g level must be limited to that re quired to maintain lateral control IfMach or airspeed is severe or if pitch and or roU attitude is ex treme or unknown 6 Landing Gear Switch Down Lowering the landing gear at hig...

Page 183: ... and steadily applied to pre vent encountering excessive aileron activity and air frame buffet Beyond MMO a 1 5 g pull up may be sufficient to excite aileron activity and the g level must be limited to that required to maintain lateral control Control pressures may be heavy Copilot assistance is recommended with this procedure 1 co iro WheeiMaster Switch MSW Dep a i dhOld Yaw damper and autopilot ...

Page 184: ...ch trim can be restored refer to JAMMED STABILIZER LANDING Section IV NOTE NOTE NOTE FAA APPROVED 4 30 76 3 39 REISSUED 2 25 81 CHANGE 13 PITCH AXIS MALFUNCTION CONT 4 STALL WARNING Switches OFF 5 PITCH TRIM Switch pedestal OFF 6 AUTOPILOT Switch OFF 7 Control Wheel Master Switch MSW Release 8 Yaw Damper PRI or SEC Engage If flight conditions permit isolate malfunction as follows 9 Pitch Trim Syst...

Page 185: ... L STALL use SEC yaw damper If malfunction was isolated to R STALL use PRI yaw damper NOTE NOTE 3 40 FAA APPROVED 4 30 76 REISSUED 2 25 81 CHANGE 10 PITCH AXIS MALFUNCTION CONT 10 Stall Warning System STALL WARNING Switches ON one at a time to isolate malfunctioning system If malfunction recurs set appropriate switch OFF An abrupt nose down control column movement is evidence of a stick pusher mal...

Page 186: ...it Breaker pOot s ess bus PuB affected axis 5 elf malfunction was isolated to yaw damper a Select opposite yaw damper elf malfunction was isolated to autopilot a Do not engage autopilot b Engage yaw damper elf maUunction was isolated to ron or yaw trim system a Use asymmetric thrust and fuel imbalance as mquired to mini mize mistrim b Land as soon as practical A normal approach and landing can be ...

Page 187: ...k wiD not be available above 25 000 feet Below 25 000 feet the engin en fuel pump wiD suction feed sufficient fuel to supply the engine and fuselage fuel transfer can be accom plished Replan flight accordingly 6 FUS VALVE Switch if installed CLOSE 7 JET PUMP Switch ON for tip tank fuel transfer U FUEL PRESS Ught does not extinguish 8 JET PUMP Switch Off U FUEL PRESS light does not extinguish 9 Des...

Page 188: ...g agency c Transponder Emergency 7700 d ELT Switch if installed ON e Ufe vests On E Inform passengers not to inflate life vests while inside aircraft f Brief passengers as required 1 Use of available flotation equipment 2 Location and operation of emergency exits Do not open lower cabin door at any time 3 All loose items secure 4 Emergency landing brace position 5 Several impacts may be felt depen...

Page 189: ... b Moderate Swells Parallel to swells c High Winds Into wind attempting to land on up wind far side of swell 7 Thrust Levers CUTOFF at touchdown 8 FIRE PULL or ENG ARE PULL T Handles Pull 9 Battery Switches OFF 10 Emergency Exit s Open after airplane comes to a complete stop Do not open lower cabin door at any time 3 44 FAA APPROVED 4 30 76 REISSUED 2 25 81 CHANGE 10 ...

Page 190: ...th the landing gear retracted b Aft Cabin Emergency Exit Open and exit using the wing step area NOTE FAA APPROVED 4 30 76 3 45 REISSUED 2 25 81 CHANGE 11 EMERGENCY BRAKING In the event of failure of the normal brake system emergency brakes can be used to stop the airplane When using emergency braking anti skid pro tection is not available and the anti skid OFF corrections presented in Sec tion V w...

Page 191: ... 10 Touch down in normal landing attitude 11 After touchdown Cabin Door and Emergency Exit Open NOTE 3 46 FAA APPROVED 4 30 76 REISSUED 2 25 81 CHANGE 14 LANDING BOTH ENGINES INOPERATIVE Airplane best glide speed in the clean configuration is VREF 60 The still air gliding distance is approximately 2 nm per 1000 feet of altitude 1 If time permits a Transponder Emergency 7700 b Advise controlling ag...

Page 192: ... 2 Thrust Levers Set to takeoff power 3 Level the wings 4 Accelerate out of the stall condition NOTE FAA APPROVED 4 30 76 3 47 REISSUED 2 25 81 CHANGE 14 STALL WARNING ACTIVATES The stall warning computer has sensed a limit angle of attack The red STALL lights will flash the control column stick shaker will activate and the angle of attack indicators will be in the yellow segment If the angle of a...

Page 193: ... a 4 hour waiting period and another visual inspection of the main gear tires wheels and brakes NOTE 3 48 FAA APPROVED 4 30 76 REISSUED 2 25 81 CHANGE 14 ABORTED TAKEOFF 1 Thrust Levers IDLE 2 Wheel Brakes Apply 3 Spoilers EXT 4 Drag Chute or Thrust Reversers if installed Deploy if necessary 5 If rejected takeoff was made at a speed of less than 40 knots one subsequent takeoff attempt may be made ...

Page 194: ...low Aircraft 35 107 35 113 Subsequent and Aircraft 36 032 Subsequent 4 16 Overpressurization 4 17 FAA APPROVED 4 30 76 IV 1 REISSUED 2 25 81 CHANGE 13 SECTION IV ABNORMAL PROCEDURES TABLE OF CONTENTS Anti Icing ALC AI Light Illuminated 4 1 Engine Ice Ingestion 4 1 ENG ICE Light Illuminated 4 2 Inadvertent Icing Encounter 4 3 Pitot Heat Light Illuminated if installed 4 4 Stabilizer Heat Failure 4 4...

Page 195: ...raulic System Failure Alternate Gear Extension 4 35 Low Hydraulic Pressure Light Illuminated 4 36 IV 2 FAA APPROVED 4 30 76 REISSUED 2 25 81 CHANGE 12 TABLE OF CONTENTS Cont Cabin Altitude Exceeds 8500 Feet Aircraft 35 067 thru 35 112 except 35 107 and Aircraft 36 018 thru 36 031 4 18 CAB ALT Light Illuminated or Cabin Altitude Exceeds 8500 Feet Aircraft 35 107 35 113 Subsequent and Aircraft 36 03...

Page 196: ...9 Operation With Nose Wheel Steering Inoperative 4 50 Taxi 4 50 Runway Lineup 4 50 Takeoff 4 50 FAA APPROVED 4 30 76 IV 3 REISSUED 2 25 81 CHANGE 13 TABLE OF CONTENTS Cont Instruments Avionics Pitot Static System Malfunction 4 37 Vertical Gyro Monitor Light Illuminated 4 38 Landing Gear Alternate Gear Extension Electrical Malfunction 4 39 Alternate Gear Extension Hyd Malfunction See Hydraulic Syst...

Page 197: ...plete definitions of the terms land as soon as possible and land as soon as practical IV 4 FAA APPROVED 4 30 76 REISSUED 2 25 81 CHANGE 10 INTRODUCTION TO ABNORMAL PROCEDURES The procedures in this section of the manual have been developed by Learjet Inc for certification of this aircraft This section contains those op erating procedures requiring the use of special systems and or alternate use of...

Page 198: ...ine operation after experiencing foreign object damage from ice in the engine fan Such damage can reduce the compressor stall margin so that the engine could become more sensitive to rapid thrust lever movements inlet pressure profile variation due to ma neuvering and high RPM operation Some compressor stalls will result in engine flameout 1 AIR IGN Switches On Leave On for the duration of the con...

Page 199: ...countered ENG ICE UGHT ILLUMINATED A failure of the nacelle heat system bleed air is indicated by illumination of the amber Lor R ENG ICE light Two types of failures are annunciated with these lights The first is an uncommanded application of nacelle heat and the second is a failure of nacelle heat to activate when commanded Affected Engine 4 2 1 NAC HT Crcuit Breaker Main Bus Pull and or reset U ...

Page 200: ...r some nose pitch may be encoun tered with the flaps full down If heavy ice accumulation has occurred proceed as follows If en route and destination temperatures remain below freezing consideration should be given to landing with ice on the wings If landing with ice on the wings and stabilizer 1 Use landing procedure for a wing and stabilizer heat failure Refer to LANDINGS this section If attempti...

Page 201: ... WING HT Circuit Breaker copilot s main bus Check and reset if necessary 2 Engine RPM Adjust as required to maintain STAB TEMP indica tor in the green range 3 If STAB TEMP indicator remains in the red range a Ay out of icing conditions if possible b Do not extend flaps beyond 20 4 On aircraft 35 067 thrll 35 112 except 35 107 and 36 018 thrll 36 031 if cabin altitude climbs to an unacceptable leve...

Page 202: ...is back in the green range b If overheat condition remains 1 STAB WING HEAT Switch OFF 2 Ay out of icing conditions Even small accumulations of ice on the wing leading edge can cause aerodynamic stall prior to activation of the stick shaker and or pusher These ice accumulations can cause angle of attack indicator information to be unreliable If approach and landing must be made with any ice or sus...

Page 203: ...NG HT Circuit Breaker copilot s main bus Check and reset if necessary 2 Engine RPM Adjust as required to maintain WING TEMP indica tor in the green range 3 If WING TEMP indicator remains in the red range anel or visual indications of ice accumulation remain fly out of icing conditions 4 On aircraft 35 067 thru 35 112 except 35 107 and 36 018 thru 36 031 if cabin altitude climbs to an unacceptable ...

Page 204: ...o be unreliable If approach and landing must be made with any ice or suspected ice during night operations on the wing leading edge refer to lANDINGS this section WINDSHIElD HEAT FAILURE With the windshield heat system activated a failure is indicated by the for mation of ice on the heated portion of the windshield 1 WSHLD HT Circuit Breaker pilot s main bus Check and reset if necessary 2 e Aircra...

Page 205: ... 35 107 35 113 subsequent and 36 032 subse quent WSHLD RAOOME RAD Switch OFF when ALC AI light iIlwninates or clear of icing conditions WSHlD OV Hf UGHT HJ UMlNATED lllumination of the WSHLD OV HT light indicates the bleed air temperature in the windshield nozzles has exceeded the system limits Airflow should au tomatically shut off when the WSHLD OV HT light illuminates If airflow did not shut of...

Page 206: ...GEN RESET Switch Depress momentarily If Generator Does Not Reset 8 START GEN Switch OFF NOTE CAUTION FAA APPROVED 4 30 76 4 9 REISSUED 2 25 81 CHANGE 14 SINGLE GENERATOR FAILURE 1 Electrical Load Reduce a COOL FAN OFF Switch OFF b Shed other loads as required to observe generator limits 2 IGN ST Circuit Breaker main power bus Check and reset 3 START GEN Switch GEN START GEN switch must be set to G...

Page 207: ...ter system after being connected to the failed AC bus indicates a fault on the AC bus NOTE NOTE NOTE 4 10 FAA APPROVED 4 30 76 REISSUED 2 25 81 CHANGE 10 INVERTER FAILURE PARTIAL AC POWER LOSS An inverter system failure is indicated by illumination of the PRI INV SEC INV and or AUX INV if installed lights An INV light will illuminate when ever the associated inverter is on and voltage and or curre...

Page 208: ...gine acceleration with fuel computer inoperative is much slower than with fuel computer on NOTE FAA APPROVED 4 30 76 4 11 REISSUED 2 25 81 CHANGE 13 INVERTER FAILURE PARTIAL AC POWER LOSS CONT If auxiliary inverter system malfunctions a AUX AC BUS Circuit Breaker ac bus associated with failed AC bus Pull b AUX INVERTER Bus Switch Select opposite AC bus c AUX INV Circuit Breaker copilot s ess bus C...

Page 209: ...or for indication of malfunction 2 Investigate cause at earliest possible maintenance NOTE NOTE NOTE 4 12 FAA APPROVED 4 30 76 REISSUED 2 25 81 CHANGE 13 FUEL CMPTR LIGHT ILLUMINATED CONT Affected Engine 1 FUEL COMPTR Circuit Breaker ess bus Check and reset if necessary 2 FUEL CMPTR Switch Cycle once If fuel computer does not come back on line FUEL CMPTR Switch OFF Fan Speed N1 must be 50 to 60 wh...

Page 210: ...ation without fluid available to the pumps may cause damage Therefore the FIRE PULL or ENG FIRE PULL T Han die should not be pulled unless a fuel or hydraulic leak is suspected 3 Rudder Trim As required 4 Yaw Damper Engage 5 AIR IGN Switch OFF 6 START GEN Switch OFF 7 Electrical Load Reduce CAUTION I During single engine operation the COOL FAN switch should be placed to OFF to prevent overloading ...

Reviews:

No comments

Brands by name

Popular brands

Load more brands