Table of Contents
Introduction ............................................................................................ 2
737-300 Airplane General Description .................................................. 4
Towing And Taxi Clearances................................................................. 6
Airplane Servicing.................................................................................. 8
Aircraft Overview ................................................................................. 10
Flight Compartment ............................................................................. 12
Captains Instrument Panel (P1) .......................................................... 14
Center Instrument Panel (P2) And Lightshield (P7) ............................ 16
First Officers Instrument Panel (P3) .................................................... 18
Pilots Overhead Panel (P5) ................................................................. 20
Pilots Aft Overhead Panel (P5 Aft) ...................................................... 22
Control Stand (P8) ............................................................................... 24
Pilots Electronics Panel (P8/P9).......................................................... 26
Master Caution System Components .................................................. 28
Electronic Equipment Compartment .................................................... 30
General: Review Questions................................................................. 32
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INTRODUCTION
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Horizontal Stabilizer Dimensions
General Description
• Height
41ft. 8 in.
The Boeing 737-300 twin engine airplane is designed for short to medium range
operation. The airplane is a metal, low-wing monoplane, with full cantilever
wing and tail surfaces, semi-monocoque fuselage and fully retractable tricycletype landing gear.
• Area
338 sq. ft.
Vertical Stabilizer Dimensions
• Height
20ft. 2 in.
• Area
224 sq. ft.
Digital Flight Control System
The aircraft is equipped with a Digital Flight Control System (DFCS)
which includes:
Landing Gear
• Dual Channel CAT IIIA Autopilot
• Main Wheel Tread
17ft. 2 in
• Integrated Full-Range Autothrottle
• Wheel Base
40ft. 10 in.
Performance
• Two Flight Directors
• Altitude Alert System
Certification is for CAT IIIA restricted (50-foot decision height) automatic
coupled approach and landing.
Overall Dimensions
• Maximum Taxi Weight
130,500 lbs.
• Maximum Takeoff Weight
130,000 lbs.
• Maximum Landing Weight
114,000 lbs.
• Maximum Zero Fuel Weight (ZFW) 105,000 lbs.
• Length
109 ft. 7 in.
• Span
94ft. 9 in.
• Height
36ft. 6 in.
Body Dimensions
• Length
105ft. 7 in.
• Width
12ft. 4 in.
• Height
13ft. 2 in.
• Fuel Capacity
5311 gal.
35,584 lbs.
• Cruise Speed
.74/.76 Mach
• VMO/MMO
340/.82
• Range (with full Pass. Load)
IFR 1600 miles
VFR 2400 miles
• Maximum Cruise Altitude
37,000 ft.
INTRODUCTION
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737-300 AIRPLANE GENERAL DESCRIPTION
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There are two cargo compartment doors on the lower right side of the fuselage,
one servicing each cargo compartment.
General
The fuselage is divided into four production or manufacturing sections:
• Section 41 forward contains the radar antenna behind a fiberglass fairing
which is hinged at the top. Aft of the pressure bulkhead, above the floor
are the control cabin and forward entry and service doors. Below the floor
are the nose gear wheel well and electrical/electronic equipment
compartment.
• Section 43 contains the passenger compartment, with windows between
the frames. Below the floor is the forward cargo compartment with a door
on the right side.
The lower nose compartment access door is located forward of the nose wheel
well.
The electronic equipment compartment access door is located in the lower
fuselage, aft of the nose wheel well.
The section 48 interior access door is located in the lower lobe, left hand side.
Engines
Two CFM-56 powerplants are located on short struts below and forward of the
wings.
Passenger Cabin
• Section 46 is the center and aft portion of the passenger cabin with
windows between the frames, two overwing emergency exits and aft entry
and service doors. Below the floor is the wing center section (fuel tank),
two air conditioning bays, main wheel well, hydraulic bay and aft cargo
compartment with a door on the right side. This section terminates at the
aft pressure bulkhead.
• Section 48 contains the auxiliary power unit (APU) and horizontal stabilizer
truss. Access to this section is through a door on the left side, aft of which
is the APU access door and APU exhaust.
Access Door Locations
Doors allow access to the passenger cabin, airstairs and cargo and service
areas.
There are two entry doors on the left side of the airplane, one forward and one
aft. There are two galley service doors on the right side, one forward and one
aft. All the doors operate the same way.
Emergency exit hatches are located one on each side of the fuselage over the
wing area.
It has a capacity to carry up to 149 passengers in a single class or up to 128
passengers in a mixed class configuration.
• Seating - 128 seats (8 first class / 120 tourist) on aircrafts 201-213 and
251-254.
• Seating - 122 seats (8 first class / 114 tourist) on aircrafts 221-242.
737-300 AIRPLANE GENERAL DESCRIPTION
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TOWING AND TAXI CLEARANCES
Towing
The airplane is normally towed or pushed by a towbar attached to the nose
gear. Maximum normal towing turning limits are indicated by red strips on the
nose gear doors.
Precautions
The following precautions must be observed:
• Maximum towbar movement 78deg. either side.
• Wing Tip clearances require special care during the turn.
• Brakes should not be used during turns except in emergencies.
• Airplane should be moving before turning the nose wheel.
• Airplane nose wheel should be fore and aft (Straight ahead) prior to
parking.
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TOWING AND TAXI CLEARANCES
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AIRPLANE SERVICING
Servicing
The airplane servicing for a turnaround or a through stop is accomplished form
the right side of the fuselage.
The electrical power and pneumatic power can be provided by ground units, or
alternately by the Auxiliary Power Unit located in the aft section of the fuselage.
See Figure A (Below) for aircraft servicing on the B737-300.
Locations
See Figure B (Below) for Ground Service locations and the approximate height
from ground.
FT
IN
A
B
C
D
AIR CONDITIONING
AUX POWER UNIT OIL TANK
ELEC RECEPTACLE - AC
ENGINE OIL TANK (2)
3
12
5
3
4
0
4
3
E
F
G
H
J
K
L
M
N
0
P
R
S
HYDRAULIC FLUID RESERVOIR
OVERWING FUEL FILLER (2)
PNEUMATIC CONNECTION
POTABLE WATER
PRESSURE FUELING/DEFUELING
DEFUELING VALVE
TOILET PANEL, AFT
TOILET PANEL, FWD
AIR CYCLE MACHINE (2) &TURBO-FAN (2) OIL FILL
ELEC RECEPTACLE - DC
CONSTANT SPEED DRIVE (2)
STARTER (2)
CREW OXYGEN SERVICE
4
9
3
6
8
8
7
5
4
4
3
3
5
5
4
8
4
0
0
0
10
2
3
3
3
10
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AIRPLANE SERVICING
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AIRCRAFT OVERVIEW
Flight Station
There are provisions for the Captain, First Officer, and observer in the flight
station, which is also called the Control Cabin.
Passenger Compartment
There are two different passenger seating configurations:
• 128 seats (8 first class, 120 tourist) for aircrafts 201-213 and 251-254
• 122 seats (8 first class, 114 tourist) for aircrafts 221-242
There are two galley units:
• one in forward right end of cabin for first class.
• one in aft end of cabin for tourist service.
There are three Lavatories:
• one in the forward left-hand cabin
• two in the rear of the cabin
There are four doors:
• one entry door on the forward left side of the cabin
• one entry door on the aft left side of the cabin
• one service door on the forward right side of cabin
• one service door on the aft right side of cabin
There are provisions for four flight attendants. Double flight attendant seats are
located at forward left-hand entry door and aft left-hand service door.
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AIRCRAFT OVERVIEW
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FLIGHT COMPARTMENT
General Description
There are provisions for the Captain, First Officer, and observer in the flight
station, which is also called the Control Cabin.
Typical Boeing panel placement and identification are standard on the -300
model. Panels P1 through P18 are found in the Flight Compartment.
Panels
Most of these panels are shown later in this chapter:
• P-1 is located in front of the captain.
• P-2 is located in the middle in front of both the captain and first officer.
• P-3 is located in front of the first officer.
• P-5 is located above the flight crew members.
• P-6 is located behind the first officer.
• P-7 is the light shield located under the forward windows above P-2.
• P-8 is the aft center pedistal.
• P-9 is located forward of the P-8 panel below the P-2 panel.
• P-18 is located behind the Captain.
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FLIGHT COMPARTMENT
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CAPTAINS INSTRUMENT PANEL (P1)
General Description
ADI
Elec Alt
EMASI
FMA
GMT
HSI
INSTR COMP
RAI
RDDMI
STBY ASI/ALT
TAVSI
Attitude Director Indicator
Electronic Altimeter
Electronic Mach Airspeed Indicator
Flight Mode Annunciator
Greenwich Mean Time
Horizontal Situation Indicator
Instrument Comparator TEST/RESET Switch
Radio Altimeter Indicator
Radio Digital Distance Magnetic Indicator
Standby Airspeed Altimeter Indicator
Traffic Avoidance Vertical Speed Indicator
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CAPTAINS INSTRUMENT PANEL (P1)
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CENTER INSTRUMENT PANEL (P2) AND LIGHTSHIELD (P7)
General Description
A/P
A/T
ALT
CMD
CWS
FF
F/D
HSI
HDG SEL
IAS/MACH
LNAV
LVL CHG
MCA
MCP
SHI
VIB
VNAV
Autopilot
Autothrottle
Altitude
Command
Control Wheel Steering
Fuel Flow
Flight Director
Horizontal Situation Indicator
Heading Select
Indicated Airspeed / Mach
Lateral Navigation
Level Change
Master Caution Annunciator
Mode Control Panel
Standby Horizon Indicator
Engine Vibration Indicator
Vertical Navigation
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CENTER INSTRUMENT PANEL (P2) AND LIGHTSHIELD (P7)
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FIRST OFFICERS INSTRUMENT PANEL (P3)
General Description
ADI
Elec Alt
EMASI
FMA
GMT
GP
HSI
RA
RDDMI
TAT/SAT/TAS
TA/VSI
Attitude Director Indicator
Electronic Altimeter
Electronic Mach Airspeed Indicator
Flight Mode Annunciator
Greenwich Mean Time
Ground Proximity Warning System Test Panel
Horizontal Situation Indicator
Radio Altimeter Indicator
Radio Digital Distance Magnetic Indicator
True Airspeed / Static Air Temperature / Total Air
Temperature
Traffic Avoidance / Vertical Speed Indicator
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FIRST OFFICERS INSTRUMENT PANEL (P3)
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PILOTS OVERHEAD PANEL (P5)
General Description
Flight Control Panel
Instrument Switching Panel
Fuel Control Panel
DC / AC Electrical Indication Panel
Constant Speed Panel
Electrical Control Panel
Auxiliary Power Unit Panel
Equipment Cooling Panel
Emergency Exit Lights Panel
No Smoking / Fasten Seat Belt Panel
Attendant / Ground Crew Call Panel
Windshield Wiper Panel
Anti-Ice Panel
Hydraulic Control Panel
Door Warning Indication
Cockpit Voice Recorder Control Panel
Pressurization Monitoring Panel
Temperature Control Panel
Bleed Air / Air Conditioning Control
Pressurization Panel
Landing Lights / Taxi Lights Control Panel
Engine Start Control Panel
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PILOTS OVERHEAD PANEL (P5)
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PILOTS AFT OVERHEAD PANEL (P5 aft)
General Description
Ground Proximity Warning System
Windshear Warning Speaker
Altitude Alert Speaker
Leading Edge Devices Indicator
Inertial System Display Unit
Inertial Reference System Mode Select Panel
Service Interphone Control Switch
Observer Audio Selector Panel
Engine Reverser Fault Lights
Power Management Control Panel
Engine Idle Fault Light
Crew Oxygen Indicator
Passenger Oxygen Override Switch
Flight Recorder Control Panel
Mach / Airspeed Warning Test Panel
Stall Warning System Test Panel
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PILOTS AFT OVERHEAD PANEL (P5 AFT)
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CONTROLSTAND (P8)
General Description
Engine Control Levers
Engine Start Levers
Flap Control Lever
Parking Brake Control
Speed Brake Lever
Stabilizer Trim Cutout Switch
Stabilizer Trim Indicators
Stabilizer Trim Wheels
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CONTROLSTAND (P8)
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PILOTS ELECTRONICS PANEL (P8/P9)
General Description
Airline Communications and Reporting System Control Unit
Automatic Direction Finder
Aileron Trim Switches
Cargo Detection/Fire Protection Panel
Audio Selector Panels
Column Switching Module Override Switch
Communication Radio Control Panels
Fire Control Panel
Flight Management Control Display Unit
Navigation Radio Control Panels
Radar Control Display Unit
Rudder Trim Control Knob
Transponder / Traffic Collision Avoidance System Control Panel
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PILOTS ELECTRONICS PANEL (P8/P9)
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MASTER CAUTION SYSTEM COMPONENTS
General
The purpose of the Master Warning and Caution lights is to inform the pilots that
a system fault indicator light has illuminated on the P5 panel, P5 aft overhead
panel, or on the P8-1 Engine and APU Fire Control Module.
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If a selected system fault occurs and causes its fault annunciator to illuminate, it
also causes the associated Master Caution annunciator section to illuminate as
well as both Master Caution lights.
There are three features to the Master Caution System:
• Push to Test - Pressing either caution annunciator causes all twelve
sections to illuminate as long as either caution annunciator is pressed.
Locations
Two DC circuit breakers are located on the land control center right (P6-3).
• Push to Recall - When the annunciator is released the recall function is
initiated. If any fault still remains, the corresponding section of the caution
annunciator will remain illuminated and all other sections will extinguish.
The Master Test Relay (R33), the Auxiliary Master Relay (R87) and the
background lights and diodes module (M580) are located in the load control
center right (P6-4).
• Push to Reset - resets the Master Caution System on the P7 while the
associated light that turned the master caution ON may be still illuminated.
The annunciation and dimming module (M469) is located in the forward
electronics panel (P9) under the electronics panels.
The master dim and test switch is located on the Center Instrument Panel (P2).
Individual system annunciators which provided inputs to the Master Caution
System are located on the forward and aft overhead panels (P5) and the fire
protection panel (P8-1).
The Master Caution Lights (left and right) and the Master Caution Annunciators
(left and right) are located on each side of the P7 glareshield.
The Master Caution Lights will also illuminate when the caution annunciator is
pressed and will remain illuminated if any fault still exists. Certain system faults,
such as the Fuel Boost Pump Low Pressure lights do not cause a fault if only
one system fails. The recall function can then be used and the Master Caution
lights will illuminate.
Each section of the Master Caution Annunciators has two incandescent lights.
The lights are replaced by pulling out the Master Caution annunciator. The
lights are mounted on the removable annunciator. There are keying pins on
each annunciator so that they cannot be installed upside down. The keying
for each Master Caution Annunciator is different to eliminate switching the left
to the right side.
Master Caution Annunciators
CAUTION:
NOTE:
The two Master Caution Annunciators are often called (Six
Packs), due to having Six System locator annunciators.
The two Master Caution Annunciators are amber. Each annunciator is divided
into six sections. Each section operates independently of the other eleven
sections. Each section is tied to selected system fault annunciators on the
overhead panels or to the fire protection panel (P8).
THE LEFT AND RIGHT MASTER CAUTION ANNUNCIATORS
ON THE -300 AIRCRAFT ARE NOT INTERCHANGEABLE
WITH THE -200 AIRCRAFT, DUE TO ADDITIONAL
INFORMATION PRESENTED ON THE LEFT AND RIGHT
ANNUNCIATORS (I.E. IRS ON LEFT, AND ENG ON THE
RIGHT.
MASTER CAUTION SYSTEM COMPONENTS
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ELECTRONIC EQUIPMENT COMPARTMENT
General Description
The E & E compartment contains three racks containing electronic equipment
necessary for control, communication and general operation of the aircraft.
Racks, containing shelves, are numbered one through three, with three or four
shelves each:
• E1-1, E1-2, and E1-3
• E2-1, E2-2, E2-3, and E2-4
• E3-1, E3-2, E3-3, and E3-4
• E3-5
Equipment Cooling is integrally provided within the shelves with the resulting
warm air used for forward cargo compartment heat.
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ELECTRONIC EQUIPMENT COMPARTMENT
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CHAPTER13 GENERAL: REVIEW QUESTIONS
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4) Some of the -200 aircraft have airstairs located under the Ll entry door. Are
there any airstairs on the -300 aircraft, and where are they located?
1) On Delta's -200 aircraft, the seating configuration is approximately 105 for a
mixed class and 119 for a single class configuration (Delta Express). Delta's
configuration -300 aircraft seats
2) The -200 aircraft use Pratt and Whitney JT8D-15A engines, What type
engines are used on the -300 aircraft.
3) The -200 aircraft has two drain mast: one for the APU fuel shroud drain
which is for looking for a fuel line leak (If no leaks, no fuel should come out this
drain), and one on the APU access door for drainage e of leaks. How many
drain masts are on the -300 aircraft and what are their purposes?
5) The -200 aircraft uses a Performance Data Computer (PDC) for fuel
economy to assist the flight crew and helps Maintenance trouble shoot the
Autopilot and Autothrottle using BITE. What does the -300 use?
6) The -200 aircraft uses Vertical Gyros for Attitude information and Directional
Gyros for navigational purposes. They are located in the E&E compartment.
The -300 aircraft use what for Attitude and Direction information?
CHAPTER13 GENERAL: REVIEW QUESTIONS
9) The -200 aircraft is approximately 93 feet from wing tip to wing tip. What is
the length of wingspan on the -300?
7) On the -300 aircraft, where is the Potable Water Tank located?
8) The -200 fuselage length is approximately 96 feet 11 inches. What is the
fuselage length of the -300 aircraft?
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10) The -200 aircraft has two lavatories. How many does the -300 have?
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