References:

[a] Boeing C-40A Aircraft Maintenance Manuals, Part 1, System Description Section
[b] C-40A Operations Manual, Vol. 2

203.1 SYSTEM COMPONENTS AND COMPONENT PARTS

Referring to a standard print of this system or the actual equipment, identify the following system components and component parts and discuss the designated items for each:

A. What is its function?
B. Where is it located?

203.1.1 Communication equipment:

Public Address (PA) system

Function and Location:

The passenger address (PA) system supplies audio to the passenger cabin and flight compartment for flight crew announcements, and chimes.

b. Ultra High Frequency (UHF)

Function and Location:

The satellite communication (SATCOM) system uses ground stations and satellites to transmit and receive data and voice messages. The SATCOM system supplies higher quality data and voice message signals for passengers and crew over longer distances than VHF and HF communication systems.
A control panel is provided on the flight deck aft electronic panel.

a. Very High Frequency (VHF)

Function and Location:

The very high frequency (VHF) communication system gives communication between airplanes or between ground stations and airplanes. The VHF frequency range of 118.000 MHz to 136.975 MHz. VHF antennas are on the top and the bottom of the airplane fuselage on the centerline.

d. High Frequency (HF)

Function and Location:

The high frequency (HF) communication system supplies voice communication over long distances. The HF system operates in the aeronautical frequency range of 2 MHz to 29.999 MHz.

e. Satellite Communications (SATCOM)

Function and Location:

The satellite communication (SATCOM) system uses ground stations and satellites to transmit and receive data and voice messages. These components for the SATCOM system are in the aft cargo compartment on the E6 rack:

f. Arinc Communications Addressing and Reporting System

Function and Location:

The aircraft communications addressing and reporting system (ACARS) is a datalink communication system. It lets you transmit messages and reports between an airplane and an airline ground base. The ACARS is a voice and data communication system to manage flight plan data and maintenance data between the airplane and the airline.

g. Identification Friend or Foe (IFF)

Function and Location:

The Identification Friend or Foe (IFF) accessory unit receives a PTT from the transceiver. The IFF/TCAS control panel is on the P8 aft electronics panel.

h. Voice recorder

Function and Location:

The voice recorder continuously records flight crew communications and flight compartment sounds. The cockpit voice recorder panel is on the overhead panel. The captain clock is on the captain instrument panel. The voice recorder unit is in the aft cargo compartment.

i. Flight recorder

Function and Location:

The flight data recorder system (FDRS) stores airplane parameters and system data for the last 25 hours of operation.
The flight data recorder (FDR) is in the aft cabin overhead.

j. Emergency Locator Transmitter (ELT) A B

Function and Location:

The emergency locator Transmitter (ELT) system automatically sends emergency signals when it senses a large change in the airplane velocity.
The ELT sends homing signals to search and rescue crews on the VHF and UHF emergency channels.
The ELT also sends emergency signals to satellite receivers.
The ELT control panel is on the aft overhead panel.
The ELT transmitter is above an access panel in the aft passenger cabin ceiling at station 770.

203.1.2 Navigation equipment:

a. Air Data Inertial Reference System (ADIRS)

Function and Location:

The air data inertial reference system (ADIRS) has two primary functions: Air data reference (ADR), and Inertial reference (IR). The ADIRS components are located in the flight compartment as well as the electronic equipment compartment.

b. Tactical Air Navigation (TACAN)

Is located in the flightdeck.

c. Global Positioning System (GPS)

Function and Location:

The global positioning system (GPS) uses navigation satellites to supply airplane position to airplane systems and to the flight crew. There are two GPS systems. Antenna 1 receives satellite signals and sends them to multimode receiver (MMR) 1. Antenna 2 connects to MMR 2. GPS sensor units are in the multi mode receivers (MMR). The MMRs are in the electronic equipment compartment. MMr 1 is on the E1-2 shelf. MMR 2 is on the E1-4 shelf.

d. Automatic Direction Finder (ADF)

Function and Location:

The automatic direction finder (ADF) system is a navigation aid. The ADF receiver uses amplitude modulated (AM) signals from ground stations to calculate the bearing to the ADF station from the airplane longitudinal axis.
The ADF control panel is on the P8 aft electronics panel.
ADF receiver 1 and ADF receiver 2 are in the electronic equipment compartment on the E3-1 shelf.

e. Traffic Collision Avoidance System (TCAS)

Function and Location:

The traffic alert and collision avoidance system (TCAS) helps the flight crew maintain safe air traffic separation from other ATC or IFF transponder equipped The TCAS computer is in the electronic equipment compartment on the E1-1 shelf.

f. Heads Up Display (HUD)

Function and Location:

The head-up display (HUD) system uses electronics and optics to calculate and show flight information. The HUD system control panel is on the P8 aft electronics panel.
The heads-up guidance annunciator panel is on the P3-3 first officer instrument panel.

g. Flight Management Computer System

Function and Location:

The flight crew uses the flight management computer system (FMCS) to enter route and vertical performance flight plan data for a flight. The FMCS components on the P9 forward electronics panel in the flight compartment:

h. Weather radar

Function and Location:

The weather radar (WXR) system supplies these visual indications:

Weather conditions
Wind shear events
Land contours
The weather radar control panel is on the P8 aft electronic panel in the flight compartment.

Ground Proximity Warning System (GPWS)

Function and Location:

The ground proximity warning system (GPWS) alerts the flight crew of an unsafe condition when the airplane is near the terrain. It also supplies a warning for wind shear conditions.
The ground proximity warning computer (GPWC) and the GPWS program switch module are in the electronic equipment compartment on the E1-1 shelf.

j. Autopilot Flight Director System (AFDS)

Function and Location:

The autopilot flight director system (AFDS) is a dual system consisting of two individual flight control computers (FCC) and a single mode control panel.
The AFDS components are located in the flight compartment.

203.1.3 Power distribution system: [ref. a] a. Aircraft battery

Function and Location:

The main battery has these functions:

Supply power to critical airplane systems (AC and DC standby buses), if the normal power sources are not available
Backup power supply for the AC system control and protection
Power supply for APU start.

The auxiliary battery helps the main battery supply power to the critical airplane systems (AC and DC standby buses).

The batteries are in the EE compartment, under the E3 rack. The auxiliary battery is forward of the main battery.

b. Generators

Function and Location:

The generator drive makes three-phase, 115/200v ac, 400 Hz power for use by the electrical power system.
The components of the generator drive are on the engine and in the flight compartment.

c. Transformer Rectifier Units (TRU)

Function and Location:

To create DC power from the normal AC source, the DC system uses transformer-rectifier units (TRU).
The TRUs are in the EE compartment. TRU 1 is on the E2 rack. TRU 2 and TRU 3 are on the E4 rack.

d. Battery chargers

Function and Location:

The main battery charger and auxiliary battery charger give a DC voltage output to charge their respective battery.
The main battery charger is on the E2 rack. The auxiliary battery charger is on the E3 rack.

203.1.4 Aircraft lighting systems:

a. Position lights

Function and Location:

The position lights show this information to persons in other airplanes or on the ground:

Airplane position
Direction
Attitude

There are position lights in the tip of each wing. These lights are in the leading and trailing edge of the wing tip.
The control switch for the position lights is on the P5 forward overhead panel.

b. Wing landing lights

Function and Location:

The landing lights help the pilots to see the runway during takeoff and landing.
The fixed landing lights are in the wing root area of each wing.

c. Taxi and runway turnoff lights A B

Function and Location:

Taxi and runway turnoff lights let the pilots see the taxiway or runway during taxi.
The taxi light is on the front of the nose landing gear strut. It is below the nose wheel steering actuator.

d. Anticollision lights

Function and Location:

The anti-collision lights make the airplane easier to see in the air and on the ground.
One red anti-collision light is on the top and bottom of the fuselage.
There are three white anti-collision lights, one on each wing tip and one on the tail cone of the airplane.

e. Interior/exterior emergency evacuation lights

Function and Location:

The aisle lights supply light to the general aisle area. They help passengers and crew see in an emergency. The aisle lights are in the bullnose ceiling panel areas throughout the passenger cabin.
The slide lights supply light to the exit areas around the airplane. The lights are on the outer surface of the airplane. They are aft of each exit. The forward passenger door slide light is on the main cargo door.
The floor proximity lights supply light at the floor level to show the passengers and crew the direction to all of the exits. There are sidewall mounted EXIT lights near the airplane exits. Seat mounted floor proximity lights are on the seats, left side (port side isle seat).

203.1.5 Master warning/caution system

Function and Location:

The system status information is on the flight compartment panels. The master warning and caution lights provide a central location for information for the crew about alarms and faults for various systems.

203.1.6 Common Display System (CDS)

Function and Location:

The common display system (CDS) shows performance, navigation and engine information in many different formats on six display units in the flight compartment.
The display electronics units (DEUs) are on the E3-1 shelf in the EE compartment.

203.2 PRINCIPLES OF OPERATION

None to be discussed.

203.3 PARAMETERS/OPERATING LIMITS

None to be discussed.

203.4 SYSTEM INTERFACE

None to be discussed.

203.5 SAFETY PRECAUTIONS

203.5.1 What safety precautions must be observed when operating:

a. Weather radar

Function and Location:

When removing or installing the weather radar r/t, card should be taken to avoid damage to the captain pilot air data module flexible hose.
Do not operate the weather radar while fuel is added or removed from the airplane. Do not transmit RF energy while fuel is added or removed in an area 300 feet or less in front of the antenna. This can cause an explosion.
Make sure no persons are in the area 15 feet or less from the antenna when it transmits RF energy. RF energy can cause injuries to persons.
Make sure no large metallic objects are closer than 300 feet for the 180-degree area in front of the airplane when the radar operates. Large metal objects can include hangars, trucks, or other airplanes. Damage to the transceiver could occur if objects are in this area. This does not apply when the weather radar operates in the test mode.

b. HF radio

Function and Location:

Make sure personnel stay a minimum of ten feet away from the vertical stabilizer when the HF system transmits. RF energy from the HF communication antenna can cause injuries to personnel.
Do not operate the HF system while the airplane is refueled or defueled. An explosion can cause injuries to personnel and damage to the airplane.