Learjet 20 Series Installation guide

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LEARJET 20 SERIES
PILOT TRAINING
MANUAL
VOLUME 2
AIRCRAFT SYSTEMS
SECOND EDITION
FlightSafety International, Inc.
Marine Air Terminal, LaGuardia Airport
Flushing, New York 11371
[phone]
www.flightsafety.com

Courses for the Learjet 20 and other Learjet aircraft are taught at the following
FlightSafety learning centers:
Wichita Learning Center
Two Learjet Way
Wichita, KS 67209
[phone]
Fax: [phone]
Tucson Learning Center
1071 E. Aero Park Blvd.
Tucson, AZ 85706
[phone]
Fax: [phone]
Copyright © 2005 by FlightSafety International, Inc.
All rights reserved.
Printed in the United States of America.

INSERT LATEST REVISED PAGES, DESTROY SUPERSEDED PAGES
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Dates of issue for original and changed pages are:
Second Edition ....... 0.......... April 2005
Revision............... .01........... July 2005
NOTE:
For printing purposes, revision numbers in footers occur at the bottom of every page
that has changed in any way (grammatical or typographical revisions, reflow of pages,
and other changes that do not necessarily affect the meaning of the manual).
THIS PUBLICATION CONSISTS OF THE FOLLOWING:
*Zero in this column indicates an original page.
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NOTICE
The material contained in this training manual is based on information obtained from the
aircraft manufacturer’s pilot manuals and maintenance manuals. It is to be used for famil-
iarization and training purposes only.
At the time of printing it contained then-current information. In the event of conflict between
data provided herein and that in publications issued by the manufacturer or the FAA, that
of the manufacturer or the FAA shall take precedence.
We at FlightSafety want you to have the best training possible. We welcome any sugges-
tions you might have for improving this manual or any other aspect of our training program.
FOR TRAINING PURPOSES ONLY
FOR TRAINING PURPOSES ONLY

CONTENTS
Chapter 1 AIRCRAFT GENERAL
Chapter 2 ELECTRICAL POWER SYSTEMS
Chapter 2A ELECTRICAL POWER SYSTEMS
Chapter 3 LIGHTING
Chapter 4 MASTER WARNING SYSTEM
Chapter 5 FUEL SYSTEM
Chapter 5A FUEL SYSTEM
Chapter 6 AUXILIARY POWER UNIT
Chapter 7 POWERPLANT
Chapter 8 FIRE PROTECTION
Chapter 9 PNEUMATICS
Chapter 10 ICE AND RAIN PROTECTION
Chapter 10A ICE AND RAIN PROTECTION
Chapter 11 AIR CONDITIONING
Chapter 12 PRESSURIZATION
Chapter 12A PRESSURIZATION
Chapter 13 HYDRAULIC POWER SYSTEMS
Chapter 14 LANDING GEAR AND BRAKES
Chapter 15 FLIGHT CONTROLS
Chapter 16 AVIONICS
Chapter 17 MISCELLANEOUS SYSTEMS
WALKAROUND
APPENDIX
ANNUNCIATOR PANEL
INSTRUMENT PANEL POSTER

1-i
CHAPTER 1
AIRCRAFT GENERAL
CONTENTS
Page
INTRODUCTION ................................................................................................................... 1-1
GENERAL............................................................................................................................... 1-1
STRUCTURES ........................................................................................................................ 1-2
General ............................................................................................................................. 1-2
Fuselage ........................................................................................................................... 1-7
Wing............................................................................................................................... 1-15
Empennage..................................................................................................................... 1-15
AIRPLANE SYSTEMS ........................................................................................................ 1-16
Electrical Power systems ............................................................................................... 1-16
Lighting.......................................................................................................................... 1-16
Fuel System.................................................................................................................... 1-16
Powerplant ..................................................................................................................... 1-16
Ice and Rain protection .................................................................................................. 1-17
Air Conditioning and Pressurization.............................................................................. 1-17
Hydraulic Power Systems .............................................................................................. 1-17
Landing Gear and Brakes .............................................................................................. 1-17
Flight Controls ............................................................................................................... 1-17
Pitot-Static System......................................................................................................... 1-17
Oxygen System .............................................................................................................. 1-18
Static or Lightning Strike Protection ............................................................................. 1-18
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1-iii
ILLUSTRATIONS
Figure Title Page
1-1 Learjet 25.................................................................................................................. 1-2
1-2 Airplane Dimensions................................................................................................ 1-3
1-3 Airplane Turning Radii............................................................................................. 1-4
1-4 Danger Areas ............................................................................................................ 1-5
1-5 Fuselage Sections ..................................................................................................... 1-6
1-6 Nose Section............................................................................................................. 1-7
1-7 Cockpit Layout (Typical) ......................................................................................... 1-8
1-8.Cabin Interior (Typical)............................................................................................ 1-9
1-9 Passenger-Crew Door ............................................................................................... 1-9
1-10 Door Locking Pin Hole .......................................................................................... 1-10
1-11 Emergency Exit ...................................................................................................... 1-11
1-12 Windshield (Typical).............................................................................................. 1-12
1-13 Passenger Windows (Typical) ................................................................................ 1-13
1-14 Tailcone Entry Door ............................................................................................... 1-13
1-15 Wing ........................................................................................................................ 1-14
1-16 Empennage............................................................................................................. 1-15
1-17 Static Wicks (Typical) ............................................................................................ 1-18
TABLE
Table Title Page
1-1 Learjet 20 Series Models and Serialization.............................................................. 1-2
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INTRODUCTION
This training manual provides a description of the major airframe and engine systems
installed in the Learjet 20 series airplanes. The information contained herein is intended
only as an instructional aid. This material does not supersede, nor is it meant to substi-
tute for, any of the manufacturer’s maintenance or operating manuals. The material pre-
sented has been prepared from the basic design data. All subsequent changes in airplane
appearance or system operation will be covered during academic training and subsequent
revisions to this manual.
Chapter 1 covers the structural makeup of the airplane and gives an overview of the sys-
tems. The “Walkaround” section also contains a pictorial walkaround of the airplane.
The “Annunciator Panel” section (located at the back of Volume 2) displays all light in-
dications and should be folded out for reference while reading this manual.
GENERAL
The Learjet 20 series airplanes are all-metal,
low-wing, twin-engine jet airplanes with re-
tractable landing gear. They are powered by
General Electric CJ610 series turbojet en-
gines rated at either 2,850 or 2,950 pounds of
thrust. The airplanes are pressurized and seat
8 to 10 people including the crew.
The 20 series airplanes are certificated under FAR
Part 25 (except Model 23 which is certificated
CHAPTER 1
AIRCRAFT GENERAL
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under CAR 3) as two-pilot transport category
aircraft. They are certified for operation to an
altitude of 41,000, 45,000, or 51,000 feet, de-
pending on serial number and equipment in-
stallation. Figure 1-1 shows a Learjet 25.
The terms “early” and “late” are frequently
used in the chapters of this training manual
with reference to airplane models. This is to
simplify explanations for the two basic groups
of airplanes. Table 1-1 lists the early- and
late-model groups by airplane serial number
for reference.
STRUCTURES
GENERAL
Most of the airplane structures are fabricated of
high-strength aluminum alloy, with steel, glass
fiber, and other materials used as needed. During
testing, all load-bearing members and surfaces
demonstrated the capability to carry 90% of the
“G” forces with an adjacent structural compo-
nent failed. The airplane structure consists of
fuselage, wings, and empennage. The discussion
on the fuselage includes the doors and windows.
General dimensions are shown in Figure 1-2.
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Figure 1-1. Learjet 25
Table 1-1. LEARJET 20 SERIES MODELS AND SERIALIZATION
MODEL MODELSERIAL BLOCK SERIAL BLOCK
LATEEARLY
23
24
24B
25
24D
24E
24F
25B
25C
25D
23-003 THROUGH 23-099
24-100 THROUGH 24-180
24-181 THROUGH 24-229 EXCEPT 24-218
25-002 THROUGH 25-064 EXCEPT 25-061
24-218, 24-230 THROUGH 24-328
24-329 AND SUBSEQUENT
24-329 AND SUBSEQUENT
25-061, 25-070 THROUGH 25-205
25-061, 25-070 THROUGH 25-205
25-206 AND SUBSEQUENT

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41 FT
43 FT 3 IN.
14 FT 8 IN.
8 FT 3 IN.
34 FT 1 IN.
35 FT 7 IN.
45 FT
47 FT 7 IN.
12 FT
3 IN.
12 FT
3 IN.
MODELS 23 AND 24
ALL MODELS
MODEL 25
Figure 1-2. Airplane Dimensions

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A
B
C
MODELS
23 AND 24
MODEL
25
A 27 FT 10 IN. 31 FT 3 IN.
B 34 FT 4 IN. 37 FT 6 IN.
C 31 FT 11 IN. 35 FT 1 IN.
NOTE:
THE VALUES SHOWN REFLECT NORMAL
NOSEWHEEL STEERING. SHORTER TURNS CAN
BE EFFECTED WITH THE USE OF A TOW BAR.
Figure 1-3. Airplane Turning Radii

Figures 1-3 and 1-4 show the airplane turning
radii and the danger areas from the weather
radar and engine intakes and exhausts.
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FOR TRAINING PURPOSES ONLY
45°
30 FT
30 FT
WEATHER
RADAR
OPERATING
12 FT
12 FT
600°F
600°F 150°F
40 FT
40 FT
150°F
WEATHER RADAR OPERATING
EXHAUST DANGER AREAS SHOWN
FOR IDLE RPM. VALUES APPROXIMATELY
DOUBLE FOR TAKEOFF RPM.
Figure 1-4. Danger Areas
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NOSE
SECTION
PRESSURIZED
SECTION
FUEL
SEC
FUEL
SEC
25C
TAILCONE
SECTION
NOSE
SECTION
FRAME
1FRAME
5
FRAME
10
FRAME
13
FRAME
22
FRAME
24
PRESSURIZED
SECTION
TAILCONE
SECTION
FUEL
SEC
FORWARD
PRESSURE
BULKHEAD
AFT
PRESSURE
BULKHEAD
TAILCONE DOOR NOTE:
MODEL 24E DOES NOT HAVE A FUSELAGE TANK.
MODELS 23 AND 24
MODEL 25
FRAME
1
FRAME
5FRAME
10
FRAME
13
FRAME
18
FRAME
22
FRAME
25
FORWARD
PRESSURE
BULKHEAD
AFT
PRESSURE
BULKHEAD
25C
AFT
PRESSURE
BULKHEAD
25, 25B, AND D
TAILCONE DOOR
Figure 1-5. Fuselage Sections

FUSELAGE
General
The fuselage is constructed of stressed all-
metal skin with transverse frames and
stringers. It employs the area rule design to re-
duce aerodynamic drag and has four basic sec-
tions (Figure 1-5). They are as follow:
•The nose section extends from the radome
aft to the forward pressure bulkhead.
•The pressurization section, which in-
cludes the cockpit and passenger areas,
extends aft to the rear pressure bulkhead.
•The fuselage fuel section starts just aft
of the rear pressure bulkhead and ex-
tends to the tailcone.
• The tailcone section extends aft of the
fuel section.
The fuselage incorporates attachments for
the wings, tail group, engine support pylons,
and the nose landing gear. In addition to the
pressurized cockpit and passenger compart-
ments, the fuselage includes the nose wheel
well, an unpressurized nose compartment, and
a tailcone compartment used for equipment
installation.
Nose Section
The nose of the fuselage (Figure 1-6) is formed
by the radome. Aft of the radome is the nose
compartment.
The nose compartment access panels are on top
of the fuselage forward of the windshield. The
panels must be removed for access to various
electronic components, oxygen bottle (when
installed in the nose), emergency air bottle, and
the alcohol anti-icing reservoir.
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Figure 1-6. Nose Section
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Pressurized Section
General
The pressurized center section includes the
cockpit and passenger cabin. Interior arrange-
ments vary with airplane model and customer
preference. Typically, the cockpit is separated
from the cabin by a partition. A typical instru-
ment panel is shown in Figure 1-7.
Seating Arrangement
A typical seating arrangement in a Learjet is
two crew seats, four reclinable adjustable pas-
senger seats, and a three-passenger seat at the
rear of the cabin. Each individual passenger
seat is equipped with an adjustable headrest
and two armrests. The outboard armrest is
fixed, and the aisle armrest is of a swing-away
design for ease of entry and exit. An ashtray
and a reading light are also standard for each
passenger seat. The standard seats are track
mounted to allow movement fore and aft and
are reversible for a foursome arrangement.
Optional lateral tracking seats that also move
inboard are available. Safety belts are in-
stalled on all seats. Figure 1-8 depicts a typ-
ical cabin interior arrangement.
Safety belts and shoulder harnesses with self-
adjusting inertia reels are installed on the pilot
and copilot seats. The inertia reels allow the
shoulder harness to extend or retract during nor-
mal movement; however, the strap locks se-
curely in place under sharp forward force. To
check the function of the reel, tug sharply on
the strap. The reel should lock under this test
and prevent the strap from extending.
Immediately forward of the aft pressure bulk-
head is the baggage compartment. It is limited
to 500 pounds in all models. Optional folding
tables, storage cabinets, and refreshment cen-
ters are available, as well as toilet facilities.
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Figure 1-7. Cockpit Layout (Typical)

Passenger-Crew Door
The primary entrance and exit for passengers
and crewmembers is through the clamshell
door located on the left side of the forward
fuselage (Figure 1-9). The standard entrance
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Figure 1-8. Cabin Interior (Typical)
door is 36 inches wide, but an optional 24-inch
door is available. The upper door serves as an
emergency exit, and the lower door has integral
entrance steps.
Figure 1-9. Passenger-Crew Door

The upper portion of the door has both outside
and inside locking handles connected to a
common shaft through the door. Rotating ei-
ther of these handles to the closed position
drives six locking pins into holes in the fuse-
lage frame (Figure 1-10) (three pins forward
and three aft) and two pins through interlock-
ing arms that secure the two door halves to-
gether.
The lower door has a single locking handle on
the inside. Rotating the lower door handle to
the closed (forward) position drives two pins
into holes in the fuselage frame (one forward
and one aft). There are a total of 10 locking
pins on the two door sections.
To facilitate engagement of the upper door
locking pins during closing, an electric actu-
ator motor, torque tube assembly, and one or
two hooks are installed in the lower door which
engage rollers installed on the upper door. The
actuator motor is operated from inside the air-
plane by a toggle switch on the lower door, and
from the outside by a key switch. Excluding
those airplanes subsequent of SNs 24-294 and
25-170 and those with replacement motors,
should the motor fail, the hook(s) can still be
operated manually from inside. Access is pro-
vided to the torque-tube mechanism through a
panel in the lower door, and a ratchet handle
provided in the airplane tool kit can be used to
operate the torque tube manually.
NOTE
One hook is used on 24-inch doors,
while two hooks are used on 36-
inch doors.
A secondary safety latch is installed on the
lower door and is separate from the door lock-
ing system. It consists of a notched pawl at-
tached to the door. The pawl engages a notched
striker plate attached to the frame when the
door is closed. This engagement holds the lower
door closed while the locking handle is being
positioned to the locked position.Additionally,
it prevents the door from falling open as soon
as the door handle is opened. The latch is re-
leased by depressing the pawl.
When closing the doors from the inside, close
and latch the lower door first. Then, close the
upper door and actuate the door motor switch
to the closed position. This engages the hook(s)
over roller(s) in the upper door, and cinches
the upper door down tight while allowing the
locking pins to line up properly and meet the
microswitches as the upper door handle is ro-
tated to the closed position. The DOOR light
will remain illuminated until the hook(s) are
backed away from the upper door rollers by re-
verse operation of the door motor switch.
When the door handles are in the closed posi-
tion, the pins all contact microswitches. If any
of the switches is not actuated, a red DOOR
light illuminates on the annunciator panel (see
“Annunciator Panel” section). If the light illu-
minates while the door is closed, the pilot can
visually check through inspection ports for
proper alignment between the white lines on
the latch pins and on the door structure. The
two latch pins which connect the upper and
lower doors are visible through the upholstery
gap at the interface and do not have white lines.
Cables and hydraulic dampers are provided to
stabilize the lower door when lowering it and
when using it as a step. The 24-inch door has
one cable and a hydraulic damper. The 36-
inch door has two cables and may have an op-
tional hydraulic damper. The cables are
connected to takeup reels in the lower door and
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Figure 1-10. Door Locking Pin Hole

are also used to pull the door closed from in-
side the airplane.
The key switch is used to secure the door from
the outside. By inserting a key into the switch
and turning it in one direction, the actuator
motor drives the hooks to engage the upper
door. Turning it in the other direction releases
the hooks to permit opening the door.
NOTE
Anytime the airplane is occupied
with the entry doors locked, the
hooks must be released. This per-
mits opening the upper door for
emergency egress.
The red DOOR light illuminated means:
•Any one of the 10 latch pins is not en-
gaged with its respective microswitch.
•The hooks are not disengaged from the
door and fully retracted.
•The door may be unsafe for takeoff.
A hollow neoprene seal surrounds the door-
frame; the seal has holes to allow the entry of
pressurized cabin air, forming a positive seal
around the door.
Emergency Exit
A hatch near the right rear of the cabin serves
as an emergency exit on all Learjet 20 models
(Figure 1-11).
The hatch can be opened from the inside on all
models by a latch handle located at the top cen-
ter of the window. The latch must be pulled in-
ward to unlock; a continued inward pull
releases the hatch from the lower retainers.
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Figure 1-11. Emergency Exit

The method of opening the hatch from the ex-
terior varies with airplane model:
•On 23 models, exterior opening requires
that the top center screw be removed
and punched out. The hatch then can be
pushed inside.
•On 24, 24B, and 25 models, the exterior
latch must be raised up, then pushed in
to release the hatch. The hatch then can
be pushed inside.
•On 24D, E, F, and 25B, C, and D mod-
els, exterior opening is accomplished
by depressing a PUSH button above the
window, which releases a handle. The
handle must then be turned in the direc-
tion of the arrow stamped on the handle.
The hatch then can be pushed inside.
Windows
Windshield—23 Model
The windshield is divided into two sections—
the pilot’s and copilot’s halves—and consists
of two panes of acrylic plastic (Figure 1-12).
The outer pane is .460 inches thick and the
inner pane is .188 inches thick, with an air sep-
aration between the panes. A dehydrator lo-
cated under the copilot’s seat removes moisture
from conditioned cabin air before it is routed
between the panes. The dehydrator and plastic
line must be kept in proper operating condition
to prevent moisture, dust, or smoke from col-
lecting on the inner surfaces of the panes.
Windshield—All 24 and 25 Models
The windshield is divided into two sections—
the pilot’s and copilot’s halves—and consists
of three laminated layers of acrylic plastic. The
windshield is approximately one-inch thick.
It is impact resistant and was tested against
four-pound bird strikes at 350 knots.
Passenger Windows—23, 24, 24B
Models
Three large, dual-pane, acrylic plastic win-
dows are installed in the airplane. The right rear
window serves as an emergency exit. The panes
are held apart and sealed airtight by a spacer.
Passenger Windows—All Other Models
Six to nine small, dual-pane, acrylic plastic
windows are installed in the airplane, including
the emergency exit hatch window (Figure 1-13).
Cleaning of Windows
The following precautions should be taken
when cleaning airplane windows:
•Remove loosely adhering dirt and grit from
the window by flushing with clean water.
•Wash with nonabrasive soap and water.
A soft, thoroughly clean cloth, sponge,
or chamois may be used in washing, but
only as a means of carrying the soapy
water to the plastic. Go over the surface
only with the bare hand so that any abra-
sive can be quickly detected and re-
moved before it scratches the plastic
surface.
•Remove oil and grease by rubbing lightly
with a cloth wetted with aliphatic naptha.
•Dry the surface with a clean, damp cham-
ois. A clean, soft cloth or tissue may be
used if care is taken not to rub the plas-
tic after it is dry.
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Figure 1-12. Windshield (Typical)

NOTE
•All rubbing operations on acrylic
plastics shall be done with as light
a pressure as possible.
•Rubbing the plastic surface with a
dry cloth will cause scratches and
build up an electrostatic charge
which attracts dust particles.
•Do not use the following materials
on acrylic plastics: gasoline, alco-
hol, benzene, hexane, xylene, ace-
tone, carbon tetrachloride, fire
extinguisher or deicing fluids, lac-
quer thinners, or window cleaning
sprays because they soften the plas-
tic and/or cause crazing.
Fuel Section
The fuselage fuel section is located immedi-
ately aft of the rear pressure bulkhead. (See
Figure 1-5.)
The fuel section is located as follows:
•Frames 22 to 24: Models 23, 24, 24B, D,
F, and 24E, when installed
•Frames 22 to 25: Models 25, 25B, and D
•Frames 18 to 25: Model 25C, which has
long-range tanks installed
Tailcone Section
The tailcone section extends aft from the fuel
section to the empennage. The tailcone entry
door (Figure 1-14) is located at the bottom of
this section. On some airplanes, the door is
hinged at the forward edge and drops down
when released by quick-release thumb latches,
allowing access to the batteries, electrical
components, fuel filters, refrigeration equip-
ment, engine fire extinguishers, and hydraulic
components. On airplanes without hinges, the
door is secured by camlock fasteners.
There is no cockpit indicator to warn the pilot
if the door is open.
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Figure 1-13. Passenger Windows (Typical)
Figure 1-14. Tailcone Entry Door