Learjet 60 Pilots Manual

2-41 .............................................O 2-42 ............................................. 5 2-43 .............................................O 2-44 thru 2-50 ............................ 4 Hydraulics & Landing Gear III-1 .............................................O 3-1 thru 3-3 ................................ 2 3-4 ............................................... 4 3-5 ...............................................O ge 6 Pilot’s Manual Learjet 60 B PM-123 Change 6 LIST OF EFFECTIVE PAGES (Cont) Page Change 3-6................................................4 3-7 thru 3-13.............................. O 3-14..............................................2 3-15 thru 3-20............................ O Electrical & Lighting IV-1 and IV-2..............................5 4-1 thru 4-3................................ O 4-4................................................2 4-5/4-6 ........................................4 4-7/4-8 ....................................... 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O 4-24 thru 4-28.............................4 4-28A...........................................4 4-29..............................................4 4-30..............................................5 4-31..............................................4 * 4-32 .............................................6 4-33 thru 4-35.............................3 Flight Control Systems & Avionics V-1 thru V-3................................4 V-4 ...............................................5 5-1 ...............................................4 5-2 and 5-3................................. O 5-4 thru 5-9.................................4 5-10............................................. O 5-11 ..............................................4 5-12 and 5-13............................. O 5-14..............................................2 5-15............................................. 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O 6-17 and 6-18..............................4 6-18A...........................................5 6-18B and 6-18C ........................4 6-19 thru 6-23.............................4 6-24..............................................2 6-25............................................. O 6-26..............................................3 6-27 and 6-28............................. O Learjet 60 AFM List of Effective Pages PM-123 C Change 6 LIST OF EFFECTIVE PAGES (Cont) Page Change 6-29 ............................................. 3 6-30 ............................................. 5 6-31 and 6-32 ............................. 4 6-32A .......................................... 4 6-33 and 6-34 .............................O 6-35 thru 6-41 ............................ 4 Interior Equipment VII-1 ........................................... 4 VII-2 ........................................... 5 7-1 ............................................... 4 7-2 thru 7-4 ................................ 1 7-5/7-6 ....................................... 2 7-7 and 7-8 ................................. 2 7-9 thru 7-11 .............................. 4 7-12 ............................................. 1 7-13 ............................................. 2 7-14 ............................................. 1 7-15 ............................................. 4 7-16 ............................................. 2 7-17 ............................................. 4 7-18 ............................................. 2 7-19 and 7-20 ............................. 4 7-21 ............................................. 2 * 7-22 ............................................. 6 7-23 thru 7-33 ........................... 4 * 7-34 ............................................. 6 7-35 ............................................. 5 * 7-36 ............................................. 6 7-37 ............................................. 4 * 7-38 and 7-39 ............................. 6 7-40 ............................................. 4 Flight Characteristics & Operational Planning VIII-1 and VIII-2 ....................... 1 8-1 thru 8-10 .............................. 1 8-11/8-12.................................... 1 8-13 ............................................. 1 8-14 ............................................. 5 8-15 thru 8-25 ............................ 1 8-26 ............................................. 3 8-27 thru 8-105 .......................... 1 8-106 ........................................... 4 Learjet 60 Pilot's Manual INTRODUCTION The information in this manual is intended to augment the information in the Learjet 60 FAA Approved Airplane Flight Manual and in no man- ner supersedes any Flight Manual limitations, procedures, or perfor- mance data. In the event that any information in this manual should conflict with that in the FAA Approved Airplane Flight Manual, the FAA Approved Airplane Flight Manual shall take precedence. THE MANUAL Sections I through VII of this manual are intended to provide the oper- ator of the Learjet 60 with a basic description of the aircraft operating systems from the cockpit controls and indicators to the actuating mech- anisms in the systems. No attempt has been made to establish a specific standard aircraft due to the numerous customer options . Therefore, the illustrations and descriptions within this manual are for a "typical" air- craft and may not match a specific aircraft . Specific serialization is shown only when more than one version of the same system is incor- porated into production on a nonretrofit basis. Section VIII of this manual contains tabular performance and fuel con- sumption data derived from the Flight Manual and flight testing. This data may be used by the operator for flight planning . REVISING THE MANUAL Periodically, Numbered Changes may be issued against this manual . Pages included in Numbered Changes supersede like numbered pages in the Pilot's Manual . Each page of a Numbered Change will contain a "Change" number located at the lower inside margin of the page. Por- tions of the text affected by the change are indicated by a vertical bar at the outer margin of the page. The vertical bars may not appear on pages that contain graphs or tables. Additionally, when a "changed" page oc- curs as the result of a rearrangement of material due to a change on a previous page, no vertical bar will appear . PM-123 Original Pilot's Manual Learjet 60 REVISING THE MANUAL (CONT) The List of Effective Pages provides the user with a guide to establish the current effective date of each page in the Pilot's Manual and may be used as an instruction sheet for incorporating the latest Numbered Change into the Pilot's Manual . Information included in the List of Ef- fective Pages states the current "Change" number for each page and the dates of Original issue and Numbered Changes. An asterisk (') next to a page number indicates the page was changed, added, or de- leted by the current change . ADDRESSES Your comments and suggestions concerning this manual are solicited and should be forwarded to: Learjet, Inc. P.O. Box 7707 Wichita, Kansas 67277-7707 Attn: Technical Publications PM-123 Original LexetG0 Pilot's Manual ~ ~y~~Y~'8UYy'8YY U ENERAu~y~ DESCRIPTION TABLE OF CONTENTS Opening Cabin Door (From Outside) (Figure 1-3) ............... ....... 1-6 Closing Cabin Door (From Inside) (Figure 1-7 Emergency Exit/Baggage Door Operation E)O.D](lBS Light..... .. ... ...... ........... 142 7bDcoze Baggage Compartment .................. .................. ............. ....... ... 1-12 1-13 144 Instrument Panel (Typical) (Figure 1-l0) .... .. .................... ................. .. I-l5 Pedestal (Typical) (Figare 1'1l) ....... ...................... .. ........... ................. .. I-l7 Pilot's Circuit Breaker Panel . .- .. ......... .... ..1-l9 Circuit Breaker Panel (Figure 1-21 Learjet 60 Pilot's Manual AIRCRAFT GENERAL DESCRIPTION SEC F#O n% 0 GENERAL DESCRIPTION The Learjet Model 60 aircraft, manufactured by Learjet, Inc., is an all metal, pressurized, low-wing, turbofan-powered monoplane . The high-aspect ratio, fully cantilevered, swept-back wings with winglets are of conventional riveted construction except for the upper section of the winglets, which is full-depth honeycomb core bonded to the outer skin. The fuselage is of "area rule" design and semi-monocoque construction . Two inverted "V" ventral fins (delta fins) are fitted to the aft section of the tailcone to provide the aircraft with favorable stall recovery characteristics and additional lateral/directional stabili- ty. Thrust is provided by two pod-mounted PW305A turbofan en- gines manufactured by Pratt and Whitney Canada, Inc. Independent fuel systems supply fuel to the engines with fuel storage available in wing and fuselage tanks. Engine-driven hydraulic pumps supply hy- draulic power for braking, extending and retracting the landing gear, wing flaps, and spoilers. The landing gear system is a fully retractable tricycle-type gear with dual main-gear wheels, anti-skid braking, and nose-wheel steering . The flight controls are manually controlled through cables, bellcranks, pulleys, and push-pull tubes. Lateral and directional trim is accomplished by means of electrically-actuated trim tabs installed on the left aileron and on the rudder. Longitudinal trim is accomplished by changing the angle of incidence of the hori- zontal stabilizer with an electrically-operated linear actuator. Aircraft air conditioning systems provide heating, cooling, and pressurization for the crew, passenger, and cabin baggage compartments. PM-123 1-1 Original Pilot's Manual Learjet 60 NOTE: All dimensions shown for aircraft in static position. AIRPLANE THREE-VIEW Figure 1-1 PM-123 Change l Learjet 60 1 . Fwd Avionics Compartment 2. Stall Warning Vane 3. Pitot-Static Tube 4. Lower Cabin Entry Door 5. Upper Cabin Entry Door 6. Inboard Wing Stall Fence 7. Boundary Layer Energizers 8. Outboard Wing Stall Fence 9. Wing Fuel Filler Cap 10 . Wing Navigation Light 11 . Aft Baggage Compartment Door 12 . Tailcone Compartment Access Door 13 . Rudder 14 . Elevator 15 . Tail Navigation Light 16 . Tail Strobe/Beacon 17 . Recognition Light 18 . Ram Air Inlet 19 . Fuselage Fuel Cell 20 . Flap 21 . Spoiler/Spoileron 22 . Aileron 23 . Emergency Exit/Baggage Door is-223C GENERAL ARRANGEMENT - EXTERIOR Figure 1-2 Pilot's Manual PM-123 1- 3/1- 4 (Blank) Change 1 Leaijet 60 Mars Manual CABIN ENTRY DOOR The cabin door consists of an upper portion that forms a canopy when open and a lower portion with integral steps. On some aircraft the upper portion has a torsionbar to provide opening assistance. On other aircraft the upper portion has gas-charged struts (gas springs) installed to assist in door opening. A latch, when over centered, retains the door in the position. A door release handle, located on the aft door frame, echanically releases the latch to allow the upper door to close. On aircraft a damper is attached to the torsion bar linkage to soften door opening and closing movements. On other aircraft the gas-charged struts provide a dampening effect to soften door opening and closing movement . The lower portion of the door incorporates a torsion bar tern to provide closing assistance . Cables attached to take-up reels installed on the forward and aft lower door structure to aid in closing and prevent damage ifthe door is inadvertently allowed to drop open. A self-contained hydraulic damper is also attached to the lower door as an additional protection against dropping the door. Each door halfhas a locking handle which, when rotated, drives a series of locking pins into am fuselage structure and through interlocking arms secure the halves together. When the pins are engaged, the door becomes a rigid structural member. Mere is a secondary safety latch installation on the lower door separate from the door locking system. This installation will hold the lower door against the door frame seal, and align the locking pins with the pin holes. When the lower door is unlocked, the safety latch will keep the door from falling open. This latch may be operated from either inside or outside the aircraft. A key lock is provided on the upper door to secure the aircraft from the outside. Rotating the key lock will move a lockingbar over the inside upper door handle, preventing it from rotating to the open position . ENTRY DOOR LIGHT At red HMO( WKS warning light is installed on the glareshield an- nunciator panel to provide the crew with visual indication of cabin door security. The light will illuminate and flash to indicate that one or more of the locking pins is not fully engaged or that the key lock is in the locked position. Me light 011 illuminate steady when the entry door is hall open and power is on the aircraft . If all pins are fully engaged, and the locking bar is recessed, the most probable cause for illumination is a switch malfunction or misalignment . Pilot's Manual Learjet 60 CABIN DOOR OPERATION To open the cabin door from the outside: 1. Insert key in key lock and rotate . The key lock will retract the upper door handle locking bar . 2. Insert finger in the handle finger pull door and pull out handle halves. Rotate the handle halves clockwise to the stop. 3. Raise upper door to the full open position . 4. Reach inside and rotate lower door locking handle to OPEN po- sition . 5. Release safety catch, located on forward side of middle step, from the inside, or outside using exterior button. 6. Gently lower door to the full down position. OPENING CABIN DOOR (FROM OUTSIDE) Figure 1-3 1-6 PM-123 Change 2 Learjet 60 Pilot's Manual CABIN DOOR OPERATION (CONT) To close cabin door from inside : 1. Raise lower door, using forward cable knob, until safety latch fully engages. 2. Rotate lower door locking handle to the locked position. 3. Release upper door with door release handle on aft door frame. 4. With the upper door locking handle in OPEN position, pull door tightly against door seal and rotate locking handle to the locked position. (If preparing for flight, check ENTRY DOOR warning light extinguished .) A CLOSING CABIN DOOR (FROM INSIDE) Figure 1-4 PM-123 1-7 Change 2 Pilot's Manual Learjet 60 CABIN DOOR OPERATION (CONT) To open cabin door from the inside : 1. Lift upper door locking handle to the OPEN position. 2. Push upper door outward and up to the full open position. 3. Rotate lower door locking handle to OPEN position. 4. Release safety latch, located on forward side of middle step. 5. Gently lower the lower door to full down position using the forward cable knob. OPENING CABIN DOOR (FROM INSIDE) Figure 1-5 1-8 PM-123 Change 2 Learjet 60 Pilot's Manual CABIN DOOR OPERATION (CONT) To close and lock cabin door from the outside : 1. Raise lower door until the safety latch fully engages . 2. Reach inside and rotate lower door locking handle to the locked position. 3. Release upper door with door release handle on aft door frame. 4. With upper door locking handle in the OPEN position, gently lower upper door and push tightly against door frame. 5. Rotate exterior handle halves counterclockwise to the stop and ensure each half recesses into door structure . 6. Insert key in key lock and rotate. This will extend the upper door locking bar over the locking handle . CLOSING CABIN DOOR (FROM OUTSIDE) Figure 1-6 PM-123 1-9 Change 2 Pilot's Manual Learjet 60 EMERGENCY EXIT/BAGGAGE DOOR The emergency exit/baggage door, located on the aft right side of the cabin, serves a dual function. It provides egress from the cabin during emergencies and access from the outside to the aft cabin baggage area. The door is attached to the airframe by hinges at the top and se- cured by locking pins at the side and lower edge. The door structure incorporates a window similar to those installed in the cabin. Gas- charged struts (gas springs) are installed to assist in door opening and closing and to hold the door open when fully extended . For security on the ground, the inner door latching handle has a red streamered locking pin installed through a hole in the handle to restrict move- ment. This pin must be removed before every flight . AFT CAB DOOR LIGHT To provide cockpit visual indication as to the flight status of the emer- gency exit/baggage door, a red AFT CAB DOOR warning light is in- stalled on the glareshield annunciator panel . The light will illuminate and flash if the locking pins are not fully engaged, the handle mecha- nism is not in the latched position, or the red streamered locking pin has not been removed for flight . The light will illuminate steady when the handle is at the full open position. If all components are found to be properly positioned, a switch malfunction or misalignment is the probable cause for illumination . EMERGENCY EXIT/BAGGAGE DOOR OPERATION To open the emergency exit1baggage door from the inside : 1. Remove red streamered locking pin . 2. Rotate locking handle to the OPEN position. 3. Push door outward and up to the full open position . To close the emergency exit/baggage door from the inside : 1. With the door locking handle in the OPEN position, gently low- er the door. 2. Pull door tight against door seal and rotate the locking handle to the locked position . 3. If preparing for flight, no further action is required except to check AFT CAB DOOR warning light extinguished. If securing door on the ground, rotate pin cover knob and insert red strea- mered locking pin . 1-10 PM-123 Change l Learjet 60 PM-123 Change 2 Pilot's Manual EMERGENCY EXIT/BAGGAGE DOOR OPERATION Figure 1-7 1-10A Learjet 60 Pilot's Manual To open emergency exit/baggage door from the outside : 1. Insert finger in the handle finger pull door and pull out handle halves. Rotate the handle halves clockwise to the stop. 2. Raise door upward to the full open position. N-, Stand clear if there is a chance the cabin is still pres- surized . EMERGENCY EXIT/BAGGAGE DOOR OPERATION Figure 1-7A To close the emergency exit/baggage door from the outside : 1. With the door locking handle in the OPEN position, gently low- er the door and push tightly against door frame. 2. Rotate exterior handle halves counterclockwise to the stop and ensure each half recesses into door structure . 3. If preparing for flight, no further action is required except to check AFT CAB DOOR warning light extinguished. PM-123 1- 11 Change 2 Pilot's Manual Learjet 60 EXTERNAL DOORS External doors are installed to provide for baggage loading and mainte- nance access . The nose area forward of the cockpit is accessible through four doors -two on the left side and two on the right side. The tailcone is accessible through the tailcone access door and aft baggage door, both located on the left side . Two doors provide access to the single-point pressure refueling system. These doors are located side by side on the right side of the fuselage beneath the right engine . Access to the external servicing' provisions for the toilet is through a door on the underside of the fuselage below the potty. EXT'DOORS LIGHT Illumination of the red EXT DOORS warning light, located on the glareshield annunciator panel, indicates the tailcone access door and/or the aft baggage door is not properly closed and latched. The primary purpose of the light is to indicate a door open condition prior to takeoff. If the doors were properly latched prior to takeoff and the light illumi- nates in flight, the most probable cause is a switch failure. TAILCONE BAGGAGE COMPARTMENT The tailcone baggage compartment is accessed through a door located under the left engine pylon. A slight pressure differential (0.25 psi) is maintained to prevent fluids from entering the compartment. The pres- sure is provided by ram air entering the dorsal inlet. An outflow valve, located on the top of the baggage compartment, controls the pressure . 1-12 PM-123 Change 4 Learjet 60 Pilot's Manual NOTE : Turning radius expressed above is based upon 60° nose wheel travel (full-authority/low-speed steering). Limited authority steering provides 24° of nose wheel travel. Turning radius will increase accordingly . TURNING RADIUS Figure 1-8 PM-123 1-13 Change 2 Pilot's Manual Learjet 60 WEATHER RADAR 760 F (24° C) 2 feet (0 .6 m) i 240 feet (73.2 m) DANGER AREAS Figure 1-9 PM-123 Change 2 Learjet 60 16-125B PM-123 Change l INSTRUMENT PANEL (TYPICAL) Figure 1-10 Pilot's Manual 1-15/1-16 (Blank) 1 . Pilot's Switch Panel 8. Standby Instruments 2. Pilot's Audio Control Panel 9. Copilot's Flight Instruments & Controls 3. Pilot's Flight Instruments & Controls 10 . Copilot's Audio Control Panel 4. Engine Instruments 11 . Copilot's Switch Panel 5. Annunciator Panel 12 . Landing Gear Control Panel 6. Flight Control Panel (FCP) 13. Center Switch Panel 7. Fuel Quantity Indicator 14. Electric Power Monitor Learjet 60 Pilot's Manual ' E)8eef300 0 00©000000 ©OBOgg©e©0 ®00000000 000008@e0® @ 0 0(3000- DW0 e0013 0 (Seeea000` ©000000000 e00000©I©©© ®0@0©©0000 ©®0 0080®0 ® PEDESTAL (TYPICAL) Figure 1-11 1 . Thrust Levers 2. Thrust Reverser Lev- ers 3. APR Switch (Recessed) 4. Flap Switch 5. Course & Heading Panel 6. CVR Controls 7. #2 Control Display Unit 8. Fuel Control Panel 9. Passenger Briefer Controls 10 . HF Comm Control Head 11 . Trim Control Panel 12 . #1 Control Display Unit 13 . Nose Steer Switch 14 . Parking Brake Handle 15 . Engine Sync Switches 16 . Emergency Brake Handle 17 . Spoiler Lever PM-123 1 -17/1-18 (Blank) Change 2 Learjet 60 PM-123 Change 2 0 Denotes DC circuit breakers aDenotes AC circuit breakers Denotes circuit breakers on the emergency bus I* Denotes unused circuit breaker positions PILOT'S CIRCUIT BREAKER PANEL (TYPICAL) Figure 1-12 Pilot's Manual 1-19/1-20 (Blank) 060000060 ED 0006 Goo 000 0 0 0 000 0 0 z P 11' i 1i k 11 111) ED ED 10 COD ED 40 a Im, 0 ED ED ED ED ED JE inn Qwl - 00 ff~ gR :E '~ ~~ ~>~ m< ~> ~ ~ ~~ $ ~' ~ ~ 3~ s 00000000 00 0 0 0 000 0 0 0 0, 0000000000 0 *@@G @G ED 0 0 0 0 0 0 0 0 0 !111111 i law Lealet 60 0 Denotes AC circuit breakers Denotes DC circuit breakers Denotes circuit breakers on the emergency bus 0 Denotes unused circuit breaker positions COPILOT'S CIRCUIT BREAKER PANEL (TYPICAL) Figure 1-13 Pilot's Manual PM-123 1-21/1-22 (Blank) Change 2 110 Sh Sh 010 Hot 9,000 0 0 0 0 000 0 0 -'Lo-i WN C-5 X-'(D o o a CD 11 co co 11111 111)111) 00 00 00 OD a) III oil OD is) lie 3r3 a~ 1. 0 0 ED 510 .00 IN 111111111 i U. illy a) f 111.1 al ED Ili hi 4h oil 4110; ED h h A ED ED ED 00 0 00 0 0 000 0 ED ED I F jr ED 41 ED ED ED ED ED ED ED ED ED ED oil ED ED ED IS re) 0 0 WJ ay 10 Leojet6U PROM Mann TABLE OF CONTENTS ENGINES ~~ V~ FUEL 9 . .. .. .................... .. ..... ......... ...... ........ 2-1 Engine Fuel and Control .... ....... .. ..... ....... .. .... .............. .. .. .... .. ...... 2-1 Engine Control Logic System Diagram (Figure 2-1)......... .. ....... ....... .. .... .. ...... 2-2 Thrust Levers . .. .... ..... ............... ............. ....... ....... ...... ........ ..... .... ...... .. .... 2-3 Fuel Pump....... ...................... ..... ........ ..... ............. .... .... 2-3 Fuel Control Unit . .. .. .... ..... ...... ....... ......... ...... .. .... 2-3 Full Authority Digital Electronic Control .... .. .. ..... ............................ .. 2-4 6NG CMfrTR Switches ...... .. .... .................. ......... .. ....... .. ....... ...... ...2-4A BNG C&&ITR Lights .--...---.. .._... ._-- .-. . .2-5 Variable Inlet Guide \htnes oral\arbabbe Stator Vanes .. .. .... .. ......... .. 2-5 Surge Bleed Control .................. .... .. ........... ... .. .. ......... ....... .. ...... ........... .. 2-S Automatic Performance Reserve (AJ,R) . .. ....... ........... .. .... .. ...... ......... .... 2-6 APR Switch .... .. .. ................. ..... .. .... ......... .. .. ......... .. ..... .. ....... ...... ......... .... 2-6 APR ARM Light ............. ........... .... .. ....... .. .. ..... ... ......... ..... ................. .... 2-6 APR (}?J Light .- ........... . .... ....... .. ......... ....... .. ............. .. .. ......... 2-7 Engine Synchronizer ._.-_ . .- ..-..-_--.__ .-.._ .2-7 ENG SYNC Switches ....... .. ............. ......... .. .. ....... .. ..... .. ......... ...... .. ......... 2-7 EM, SWC Light ...- .-...-- ..--_.._- ..- .....2-8 Ground Idle System .-.....-.._- ... ....-.- .-.-.- . .-2-8 Engine (DR .. .... ..... System _ ...... ...... ... .. ..... ........... ...................... .... .. .....2'8 Pressure System ...... ......... .. ...... ......... .... ......... ....... .. ....... ............. .. .. .. ..... 2-8 Engine Oil Schematic System 2-2) . ....... .. ........................ ....... 2-9 Scavenge System . .. .. ........... .. .... ................. ... .... .............. .. .... ............. ... 2-10 Breather System ...._..-... ......... .. ......... .. .................. .. .. .. ....... .. ... 2' 0 Engine Ignition Systeum _-- ._..._....-..-_ ....--.2-10 IGNITION Switches ..-. .. .. ..._ .-.---_ .- ...--.2'11 Ignition Lights -..._ .. .. ................. ... ....... ......... ...... ..... .. ........... ... 2-ll Engine Indicating -.-..... ....-_-.- .. ..-.-..-- .-. 2'l1 Engine Oil Indicator (Pressure and Temperature) .............. ........ .. .. 2-11 Oil Pressure Lights ..._. ..-...._..- ..--- ...-_ . .-.2-l2 Engine Chip Lights . ......... .... .. .... .. ............. .. ... .... ..... .. .. .... ....... .. ........ .. .. 2-12 BNG FILTERS Light .... ... .. .. .. .... ...... ............. . ..... ....... ...... ....... .......... .. .. 2-]2 ENG VDB Lights. .....-... -.-- .----- .-- - ..2-1Z FUEL FLOW Indicator 243 Pilot's Manual Learjet 60 TABLE OF CONTENTS (Cont) Ni Indicators . .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. ........ .. .......... .. .......... .. ..... 2-13 N2 Indicators . .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .... .. .......... .. .......... .. ..... 2-14 ITT Indicators .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .... .. .. ........ .. .......... .. ..... 2-15 Engine Diagnostic System .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .... .. .......... .. .......... .. ..... 2-15 Engine Diagnostic Unit .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. ........ .. .......... .. .......... .. ..... 2-15 Engine Diagnostic System (Figure 2-3) .. ...... .. ......... .. ...... .. .. .. .. .. .. .. .. . 2-16 Isolation Units . .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .... .. .. ........ .. .......... .. ..... 2-17 Control Display Unit .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .... .. .......... .. .......... .. ..... 2-17 EDS FAULT Annunciator .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .... .. .. .. .. .... .. .. .. .. .. .. .. .. .. . 2-17 EDS Record Switch. .. .. .. ...... .. .. .. ...... .. .. .. .... .. .. .. .. .... .. .. .. .. .... .. .. .. .. .. .. .. .. .. . 2-17 Engine Fire Detection System .. .. ...... .. .. .. .... .. .. .. .. .... .. .. .. .. .... .. .......... .. ..... 2-19 SYSTEM TEST Switch - Fire Detection Function .. .... .. .. .. .. .... .. ..... 2-19 ENG FIRE PULL Light .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .... .. .. .. .. .... .. .......... .. ..... 2-19 Engine Fire Extinguishing System ....... .. .... .. .. .. .. .... .. .. .. .. .... .. .. .. .. .... .. .. .. . 2-19 Fire Extinguishing System (Figure 2-4) ....... .. .......... .. .... .. .. .. .. .. .. .. .. .. . 2-18 ENG FIRE PULL Handle and ENG EXT ARMED Lights .. .... .. .. .. . 2-20 Fire Extinguisher Discharge Indicators ....... .. .......... .. .... .. .. .. .. .. .. .. .. .. . 2-20 Thrust Reverser System .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .... .. .. .. .. .... .. .. .. .. .... .. .. .. . 2-21 Thrust Reverser System Schematic (Figure 2-5) .. .. .. .... .. .. .. .. .... .. .. .. . 2-23 Thrust Reverser Assembly .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .... .. .. .. .. .... .. .. .. .. .... .. .. .. . 2-25 Thrust Reverser Lever . ...... .. .. .. ...... .. .. .. .... .. .. .. .. .... .. .. .. .. .... .. .. .. .. .. .. .. .. .. . 2-25 Throttle Balk Solenoid . ............ ...... .. .. .. .... .. .. .. .. .... .. .. .. .. .... .. .. .. .. .... .. .. .. . 2-26 Hydraulic Control Unit ..... .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .... .. .. .. ...... .. .......... .. ..... 2-26 Thrust Reverser Relay Box .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .... .. .. .. .. .... .. .......... .. .. 2-26A Aircraft Fuel System .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .... .. .. .. .. .... .. .. .. .. .... .. .. . 2-26B Wing Tanks .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .... .. .. .. .. .... .. .. .. .. .... .. .. . 2-26B Fuselage Tank .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .... .. .. .. .. .... .. .. .. .. .... .. .. .2-26B Fuel System Schematic (Figure 2-6) . .. .......... .. .......... .. .... .. .. .. .. .. .. .. .. .. . 2-27 Fuel Control Panel Switches and Annunciators .. .. .. .... .. .. .. .. .. .. .. .. .. . 2-29 JET PUMP Switches .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .... .. .. .. .. .... .. .. .. .. .... .. .. .. . 2-29 STBY PUMP Switches . .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .... .. .. .. .. .... .. .. .. .. .... .. .. .. . 2-29 XFLO VALVE Switch .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .... .. .. .. .. .... .. .. .. .. .... .. ..... 2-29 NORM XFR Switch . .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .... .. .. .. .. .... .. .. .. .. .... .. .. .. . 2-30 AUX XFR Switch . .. ...... .. .. ........ .. .. ........ .. .. ........ .. .. .. .. .... .. .. .. .. .... .. .. .. . 2-31 Fuel Control Panel (Figure 2-7) ... .. .......... .. .... .. .. .. .. .... .. .. .. .. .... .. .. .. . 2-31 GRVTY XFR Switch. ...... .. .. .. ...... .. .. .. .... .. .. .. .. .... .. .. .. .. .... .. .. .. .. .. .. .. .. .. . 2-32 FILL Switch .. .... .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .... .. .. .. .. .... .. .. .. .. .... .. .. .. . 2-33 Fuselage Tank Switch Priority ..... .. .... .. .. .. .. .... .. .. .. .. .... .. .. .. .. .... .. ..... 2-33 Fuselage Tank Full Light .... .......... .. .... .. .. .. .. .... .. .. .. .. .... .. .. .. .. .... .. .. ... 2-33 Fuselage Tank Empty Light ....... .. .. .... .. .. .. .. .... .. .. .. .. .... .. .. .. .. .... .. .. .. . 2-34 LO FUEL PRESS Lights .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .... .. .. .. .. .... .. .. .. .. .... .. .. .. . 2-34 II-2 PM-123 Change 5 Leaqe6V PHofs Manual TABU: CW 0011TENTS (Cont) Fuel .. .. ..-. ._.__ ..-.- ..-.. ..... .. .. ._.2-35 Fuel Indicator .......... ..... .. ............. ............................ .. .... ....... 2-J5 Fuel Quantity Probes . ........... ....... .. ....................................... .. ............. 2-35 Total Indicator (SP9R) .. .............................. .. ......... .. .... ....... 2'35 Foe Glar*sldeldliibts ..................... ........ ......... ...... .......2-36 FUEL PRESS Lights . .... ..... .... .. ....... ............. ................. .. ....... .. ...... ....... 2-36 LOW FUEL Light ..._....-__..-- .-. ... .._- .. ...._..2-36 FUEL SYSLight ................. ...... ....... ............. .... ....... ...... ........... ...... ....... 2-38 RazuAirFuel Vent ....... ....... ........... .... .... ............. ........... ...... .......2'37 Pressure Refuel (SPPI .) System ...... . ...- ..-.2-37 WING and BUS PRBCfIECK Wee ... .... .. .........2-38 Refuel Seledor Switch ...._.... . .... .... .. ................... ......... .... ....... 2-38 Refuel System Schematic (Figure 2-8) ........... .. ...........2-39 SppR BA%3'Switch ............ .... ......... ............... .. ................. ..... .... .... .......2-4l FlJS FULL Light . .. ..._... ......... ......... ............... ...... ................. .......24I VENT OPEN Light ._.... ._._.-..-..-...--- . ..2-41 Fuel Anti-Icing Additive .... .. ...................... .......... ..... ............... .. .. ...........242 Refueling ..._. .. ..~- ...... .--_. .-___,_.--___ .2`42 Fuel Drains 2-9) ....... .... .. ....... ............... ......... ....................... .. .....2-43 Auxiliary Power Unit (APD) ........... .................................. ....... ...... .. .....2-44 AI9JContnol Panel ........... .... ......... ............... ......... ..............................2-45 APDCnntrol Panel (Figure :010) ... ............... ............. .. ............... .. .....245 A}1IABUS lxiuatoz . .. ...... ............... .. ....... .. ...... .... ....... ...... .....2-45 APDIgRE . . ...-........... ......... ............... ........... ...... .... ....... ...........2-45 APU Switch ..... .... ........... ........... ...... .... ...... ............2-46 /Qq]RUNONING/SIART Switch ........... .. ................. ........ . .... .......2-46 APTJh1U3TER Svvitcdh --- ....... ....... .-.-_...246 APL[C)N Indicator ..... ...... ............. ........... .. ......... ...... ............... .. .....2-46 APU SYSTEM TEST Switch ..... .. .. ............. ............... .. .. ...... ............2-46 APU Relay Panel...-.- .. ._-- ...... ..__ .. .-.....2-47 APU Relay Panel 2-1l ..... .................................. .. ........... .. .....2-47 FIRE I]ET BITE Indicator ......... .. .. ........... .. ......... .... .. .. ....................2-47 GEN FAULT BITE Indicator ................... .. ............... .. .. ....... .... .......2-47 FAULT Reset Switch.. ........ ........... ........... .. ............... .. ........ ....... .....2-47 APlJBITE AnnozciaiozBon ........................ .. ................. .. ........... .. .....2-40 APDBITE AxxzociatorBox(Figure 2-12)... ................. .. ...... ....... .....2-48 APU Generator ..._. ..--- ... ........ ....... .. ............... .... ..................2-48 APU Operating Procedures ... ............... ....... .. .. ............... .. ...... ..... .. .....2-49 APU Pre-Start Check . ....-. ._..- .-... .--- .,2-49 APU . ..- ..-... .- ._---_ .-.--_.._..2-49 APU Shutdown .... .__ . ............... .. ................. .. ...... ............2-5U APU Shutdown Features (Autonzubc .. .. ................. .. ....... ...... .....2-50 nAT123 cbanme 4 Learjet 60 Pilot's Manual ENGINES ENGINES & FUEL The Learjet Model 60 is powered by two PW305A Pratt and Whitney two-spool, front-fan engines. Each engine is rated at 4600 pounds thrust at sea level. A spinner and an axial-flow fan, located at the forward end of the en- gine, are driven by the low-pressure rotor. The low-pressure rotor consists of an axial-flow fan (low-pressure compressor) and a three- stage low-pressure axial turbine, mounted on a common shaft. The high-pressure rotor consists of a high-pressure compressor (four axial stages and a single centrifugal stage) and a two-stage high-pressure axial turbine, mounted on a common shaft. The rotor shafts are con- centric, so that the low-pressure rotor shaft passes through the high- pressure rotor shaft. The high-pressure rotor drives the accessory gearbox through a driveshaft geared to the N2 rotor shaft. An annular duct serves to bypass fan air for direct thrust and also di- verts a portion of the fan air to the high-pressure compressor. The by- pass ratio (bypass flow to core flow) is 4.55 : 1. Air from the low- pressure compressor flows through variable inlet guide vanes and first-stage variable stator vanes to the high-pressure compressor and is discharged into the annular combustor . Combustion products flow through the high- and low-pressure turbines and are discharged ax- ially through the exhaust duct to provide additional thrust. ENGINE FUEL AND CONTROL SYSTEM The engine fuel and control system pressurizes fuel routed to the en- gine from the aircraft fuel system, meters fuel flow, and delivers ato- mized fuel to the combustion section of the engine. The system also supplies high-pressure motive-flow fuel to the aircraft fuel system for jet pump operation. The major components of the system are the thrust levers, the engine-driven fuel pump, the hydro-mechanical fuel control unit (HFCU), the full authority digital electronic control (FA- DEC), variable inlet guide vanes, variable stator vanes, and the surge bleed control . PM-123 2- 1 Original Pilot's Manual Learjet 60 Pilot Select and Aircraft Discretes ENGINE CONTROL LOGIC DIAGRAM Figure 2-1 2-2 PM-123 Original Learjet 60 Pilot's Manual THRUST LEVERS Two thrust levers (one for each engine) are located on the upper por- tion of the pedestal, and operate in a conventional manner with the full forward position being maximum thrust. Stops at the IDLE posi- tion prevent inadvertent reduction of the thrust levers to CUT-OFF. The IDLE stops can be released by lifting a finger lift on the outboard side of each thrust lever. Detents are provided for CUT-OFF, IDLE, maximum cruise (MCR), maximum continuous thrust (MCT), takeoff (TO), and automatic performance reserve (APR). Each thrust lever is mechanically linked to a rotary variable differential transformer (RVDT) position transducer. The RVDT provides dual electrical sig- nals to the FADEC which correspond to the thrust lever angle (TLA). A switch, which actuates in the CUT-OFF position, provides a dis- crete signal to the FADEC to initiate the normal shutdown sequence. ENGINE-DRIVEN FUEL PUMP The engine-driven fuel pump provides high-pressure fuel to the en- gine fuel control system as well as motive-flow fuel for operation of the aircraft jet pumps. The pump consists of a low-pressure pump ele- ment, high-pressure pump element, relief valve, and motive flow pro- visions. The pump itself is housed in the hydro-mechanical fuel con- trol unit. Fuel from the low-pressure element passes through a filter before it enters the high-pressure element . In the event the pressure differential across the fuel filter increases to a preset level, the im- pending bypass indicator will actuate and the white ENG FILTERS light will illuminate. If the pressure differential continues to increase, due to clogging, the filter bypass valve will open to allow fuel to by- pass the filter . HYDRO-MECHANICAL FUEL CONTROL UNIT The hydro-mechanical fuel control unit (HFCU) mounts to the perma- nent magnet alternator on the aft side of the accessory gearbox . The HFCU's main function is to control fuel flow to the engine's fuel noz- zles. Fuel flow is regulated in response to commands from the FA- DEC which computes the necessary settings for the existing condi- tions. The HFCU also provides servo pressure to the variable guide vane actuator, houses the engine-driven fuel pump, and provides fuel pressure regulation. PM-123 2-3 Original Pilot's Manual Learjet 60 FULL AUTHORITY DIGITAL ELECTRONIC CONTROL A full authority digital electronic control (FADEC), is installed in a bracket on each engine . Each FADEC has two channels (A and B) each capable of controlling the engine . During normal operation (ENG CMPTR switch in AUTO), the most capable channel is automatically selected to control the engine . FADEC functions include : " Thrust Management " Overspeed Protection " Bleed-Off Valve Control Automatic Performance Reserve Inlet Guide Vane& Inlet Stator Vane e Ignites Operation le to control the engine through the FADEC by changing TLA input to change desired thrust level. The FADEC receives input from several engine sensors and the aircraft's air data computers and together with the TLA input it determines the appropriate signals to send to the HFCU, the inlet guide vane and stator vane actuator, and the bleed-off valve solenoid to achieve the desired engine operation. outers provide inlet static pressure (PAAxWj) signals to the FADEC. PAMB and Mach by the FADEC transducer but used only as a backup to the air data computer signals . Sensors on the eng provide inlet total temperature (Tro) signals to the FADEC. A TM signal is provided by the air data computer, but used only as a backup to the engine sensor signals . Electrical power is supplied by an engine-driven permanent-magnet alternator. Backup power and power for starting is provided through the EETNAG CH A and ENG CH B circuit breakers an the pilot's and copilot's circuit breaker panels. On aircraft 6 60-128 not modified by SB 60-76-2 (Replacement of LH and RH FADEC Wiring Harness), backup power is available to channel B-during EMER BUS mode. On aircraft 61129and subsequent and prior aircraft modified by SB 60-76-2, backup power is available to channel A during EMER BUS ode . raft's ad data co and Mach number as pri number are also " Surge Protection " Fault Detection " Ni Bug Setting " Engine Synchronization " Starting & Shutdown Control " Digital ITT LearjeM PHM Manual ENG CMPTR SWITCHES Two switches, one for each engine, on the center switch panel labeled ENG CMPTR CH. A/AUT0/CH. B enable the flight crew to select the EC channel (A or B) to be used to control the engine . Normally, the switches are left in the AUTO position which allows the EADEC to au- tomatically select the most capable channel. During abnormal situa- tions, the crew may use this switch to force the desired channel to take control of the engine . On aircraft 60-001 thru MAP not modified Qj SB 60-76-1 (Removal ofEn- gine FADEC Reset Switch), a single ENG CMPTR RESET switch, on the center switch panel, is used to clear malfunctions and reset the FADEC. To reset the FADEC, the switch is held left or right (as applicable) for approximately 2 seconds. If the malfunction clears, the ENG CMPTR light(s) will extinguish . The reset switch is not operational on the ground . On aircraft 60-129 and subsequent and prior aircraft modified Inj SB 60-76-1, the ENG CMPTR RESET switch has been removed. PM-123 Change 4 24A Learjet 6U Pilot's Manual ENG CMPTR LIGHTS Two ENG CMPTR lights are provided for each engine and reside in the iator panel. Coe blot is white and one is amber. Illumination of a white light indicates a minor malfunction in one or both channels of fated FADEC. Illumination of an amber light indicates a major malfunction in one channel of the associated FADEC. Illumination of both the white and amber lights indicates a malfunction in both chan- nels of the associated FADEC. Dispatch is not permitted withanywhite or amber light i Ituminated. VARIABLE INLET GUIDE VANES AND VARIABLE $TAT The engine is equipped with variable inlet guide vanes to direct air into the first stage axial compressor and variable stator vanes 13 direct a into the second cage axial compressor. This feature permits peak com- pressor efficiency throughout various operating conditions. A variable guide vane actuator is used to simultaneously position the guide vanes and stator vanes. The FADEC computes the desired vane position and commands the HFCU to provide servo pressures (fuel) to the actuator which positions the vanes. A rotary variable differential transformer (RVDT) position transducer, mounted on the actuator, sends an electri- cal feedback signal to the FADEC. SURGE BLEED CONTRO Each engine has a surge bleed control system which allows surge free operation throughout various operating conditions and improves en- gine starting characteristics. The system consists of a solenoid control valve and three bleed-off valves (103VI Two valves bleed compressor air from station 2.5 while the third valve bleeds air from station 2.8. osition is controlled by the FADEC via the solenoid control valve. Compressor discharge air (P3) is used to provide servo pre to close the bleed-offvalveMTFhe solenoid control valve applies P3 pres- sure to be BOVs to close them and vents P3 pressure to open them. In the event a solenoid control valve fails, the bleed-off valves will go to open posithiomn. VANES Pilot's Manual Learjet 60 AUTOMATIC PERFORMANCE RESERVE (APR) The APR system provides for an automatic change from the takeoff Ni rating to the APR rating for the operative engine in the event of loss of thrust from one engine during takeoff. The amount of thrust change will depend on ambient conditions. Since the engines in- stalled on the Learjet 60 are flat rated, the difference between takeoff and APR thrust will be very small under some ambient conditions. The system consists of an APR switch on the forward pedestal, APR ARM and APR ON lights on the glareshield, and associated aircraft wiring . To detect loss of thrust, the Full Authority Digital Electronic Control (FADEC) continuously monitors the opposite engine's Ni and N2 signals. Loss of thrust is defined by the FADEs as meeting one or more of the following criteria : " The Ni of one engine differs more than 15% from the Ni of the other engine. " The N2 of one engine differs more than 7.5% from the N2 of the other engine. " The Ni of one engine differs more than 4% from the Ni of the other engine and Ni is decreasing at a rate greater than 5% per second . " The N2 of one engine differs more than 2% from the N2 of the other engine and N2 is decreasing at a rate greater than 2% per second . APR SWITCH APR system automatic operation is pilot controlled through the APR ARM-OFF switch located on the right side of the pedestal adjacent to the thrust levers. The switch is recessed to prevent inadvertent APR activation. The switch has two positions: OFF and ARM. For automat- ic operation the switch is set to ARM . When ARM is selected, the APR ARM light will illuminate provided no faults exist which affect the APR function. When a loss of thrust is detected by one of the FA- DECs, an uptrim of the operative engine is commanded . The FADEC checks that the change to the appropriate APR N1 setting has been triggered and if it has, the APR ON light will illuminate. Should auto- matic activation of APR fail to occur, APR thrust can be manually ob- tained by setting the thrust lever to the APR detent . In this case, the APR ON light will not illuminate. Once invoked, the APR thrust schedule will remain active until the APR switch is set to OFF. APR ARM LIGHT The green APR ARM light on the glareshield annunciator panel will illuminate when the APR switch is in the ARM position provided no faults exist which affect the APR function . 2- 6 PM-123 Change 2 Learjet 60 Pilot's Manual APR ON LIGHT If APR is activated automatically by the FADEC, the amber APR ON light on the glareshield annunciator panel will illuminate once APR thrust has been achieved . The APR ON light will not illuminate if APR thrust is obtained manually using the thrust lever detent . ENGINE SYNCHRONIZER The engine synchronizer system consists of two ENG SYNC switches, an amber ENG SYNC light, and engine synchronizer circuits within the FADECs. During flight, the engine synchronizer, if selected, will maintain the two engines' Ni or N2 in sync with each other. The en- gine synchronizer must not be used during takeoff, landing, or single- engine operations. Engine synchronization is not available on the ground or whenever APR is armed. Electrical power for the engine synchronizer is 28 VDC supplied through the 1-amp ENGINE SYNC circuit breaker on the pilot's circuit breaker panel. Synchronization is accomplished by maintaining the speed of the slave engine in sync with the speed of the master engine. The master engine is determined and so designated during installation . The fol- lowing criteria must be satisfied before the system will operate : " The ENG SYNC switch is set to SYNC. " The difference between the N1 speed of each engine is no more than 5% . " Thrust levers are in the range from IDLE to MCT. " Thrust reversers are stowed. " APR is disarmed . Deviating from any of these criteria will cancel engine synchroniza- tion. The system will raise flight idle of the master engine by a maxi- mum of 1% Ni when activated . ENG SYNC SWITCHES Two ENG SYNC switches are installed on the pedestal immediately below the thrust levers. The ENG SYNC control switch is labeled SYNC-OFF and the ENG SYNC selector switch is labeled N1-N2. When moved to the SYNC position, the control switch will activate the engine synchronizer and remove Ni Indicator compensation; therefore, the Ni and Ni bug presentations will reflect actual Ni speed. When SYNC is selected, Ni or N2 synchronization is selected by moving the ENG SYNC selector switch to Ni or N2 as desired . PM-123 Change 2 2- 7 Pilot's Manual Learjet 60 ENG SYNC LIGHT The amber ENG SYNC light on the glareshield annunciator panel will be illuminated when the nose gear is not up and the SYNC-OFF switch is in the SYNC position . GROUND IDLE SYSTEM The ground idle system provides reduced engine idle speeds for ground operations. When the thrust lever is in the IDLE detent and the squat switch is in the ground mode, idle speed is reduced from approximately 65% N2 (flight idle) to approximately 52% N2 (ground idle). In flight, the idle speed setting is selected to ensure adequate transient response to full takeoff power. The system incorporates a 10-second delay after touchdown before ground idle is activated . ENGINE OIL SYSTEM The engine oil system provides lubrication and cooling for the main- shaft bearings, all accessory drive gears and all accessory bearings . The system consists of a pressure system, a scavenge system, and a breather system . PRESSURE SYSTEM The oil tank is an integral part of the engine intermediate case. Oil is drawn from the tank by a gear-type pressure pump. Pump output is directed through a pressure adjusting valve which bleeds excess pres- sure back to the pump inlet. From there, oil passes through an oil fil- ter and fuel/oil heat exchanger before being routed to the mainshaft bearings, accessory drive gears, and accessory bearings. A cold-start valve diverts oil from the pump outlet into the accessory gearbox sump if pressure exceeds 200 psi during cold weather operation . The oil filter incorporates a bypass valve allowing oil to bypass the fil- ter should it become clogged . An impending bypass indicator pro- vides both a pop-up type visual indicator and an electrical signal to activate the ENG FILTERS light in the cockpit . To avoid false indica- tions at engine start-up with cold oil, a thermal lockout inhibits the impending bypass indication if oil temperature is below 38° C (100° F). An anti-siphon device is incorporated to prevent oil from being si- phoned out of the oil tank following engine shutdown. The device contains a small hole drilled through to the expansion space at the top of the oil tank. This breaks the siphon action caused by the oil tank level being higher than the main bearing oil jets. 2- 8 PM-123 Change 2