Boeing 737 Exam Questions Type Rating

Which panels are classified as electronic panels in the flight compartment of the 737?. Only the P1 (Captain) and P3 (First Officer) panels. Panels such as P1, P3, and P9 are considered electronic panels. The P5 overhead panel and P8 pedestal panel.

What is the exact number of display units on the main instrument panels (P1 and P3)?. Six display units. Two display units (one on P1, one on P3). Four display units (two on P1, two on P3).

Which panel contains the most standby instruments and engine displays?. The P5 upper overhead panel. The main instrument panel (P1/P3). The P8 aft electronic panel.

Which display is uniquely found on the P9 forward electronic panel compared to P2?. The standby altitude indicator. The Control Display Unit (CDU). Specific CDS (Common Display System) components.

What action is required to check identification and configuration information in the maintenance BITE (Built-In Test) main menu?. Access through the CDU MENU → SYSTEM → STATUS sequence. Access through the CDU MENU → INDEX → IDENT sequence. Access through the CDU BITE → CONFIG → DISPLAY sequence.

What must be selected to display a specific system's maintenance page in the BITE menu?. Press the “NEXT PAGE” key until the system is found. Type the system name on the CDU scratchpad. Press the INDEX key followed by the relevant system key.

What condition must be true for the CDU MENU phase to be displayed when accessing system maintenance?. The aircraft must be on the ground. The aircraft must be in flight, above 10,000 feet. The APU generator must be the only power source.

Which four main AC power sources can provide electrical power to the 737?. Two Integrated Drive Generators (IDGs), APU generator, and external power. Two IDGs, the main battery, and the APU. External power, APU generator, and two Transformer Rectifier Units (TRUs).

What is the function of the Standby Power Control Unit (SPCU)?. It controls the frequency and voltage of the IDGs. It manages and distributes standby electrical power during main system failure. It serves as the primary computer for the APU generator.

How many generator control breakers (GCBs) and bus tie breakers (BTBs) are identified as main electrical power system breakers, and which unit receives their position?. 2 GCBs and 2 BTBs; monitored by the Bus Power Control Unit (BPCU). 4 GCBs and 2 BTBs; monitored by the Generator Control Units (GCUs). 2 GCBs and 1 BTB; monitored by the Standby Power Control Unit (SPCU).

Which relay allows DC Bus 1 to receive power through TRU 2 or 3 if necessary?. The Bus Tie Relay. The Main DC Bus Relay. The Standby Power Relay.

What function does the BPCU perform to protect AC sources from overload?. It monitors current and phase balance; opens contactors in case of overcurrent. It automatically sheds galley loads if voltage drops. It routes power through the SPCU to reduce load.

Which modules provide Built-In Test Equipment (BITE) capabilities for AC/DC system health monitoring?. The Transformer Rectifier Units (TRUs) only. The main and APU batteries. GCUs and the Electrical Metering Panel modules.

What conditions must be met for the BPCU to close the external power contactor?. Battery switch ON, external power quality good, no bus tie power, external power selected ON. APU running, battery switch OFF, external power selected ON. Both engines off, external power quality good, external power selected ON.

What does the amber external power connection indicator denote?. External power is connected and supplying power to the aircraft. Indicates external power available but not yet connected. ) External power is connected but the quality (voltage/frequency) is poor.

Which condition requires the IDG to be removed and disassembled to reset?. ) A momentary frequency fluctuation. ) A “Gen Off” bus light indication. Excessive torque on the input shaft protection for the engine accessory gearbox.

Which component reduces the pressure of oxygen supplied to the flight crew?. The pressure transducer. The pressure regulator. The chemical oxygen generator.

What is the power source for the oxygen indicator circuit?. 115V AC from Transfer Bus 1. 28V DC from the battery bus. (Correct). 28V DC from the main DC bus.

What type of oxygen supply is used for passengers?. Pressurized cylinders, same as the crew. Chemical oxygen generators. A central liquid oxygen (LOX) converter.

Which component measures and transmits oxygen cylinder pressure to the cockpit?. The pressure regulator. The flow indicator. Pressure transducer/sensor.

Which indicator shows oxygen flow by a yellow cross symbol?. The pressure gauge in the cockpit. The flow indicator on the crew oxygen mask. A BITE status message on the CDU.

What mechanism releases the passenger oxygen masks?. A manual lever pulled by the flight crew. A pressure switch sensing low cabin air pressure. Door solenoid release triggered by 28V DC.

Which component ignites the percussion cap in the passenger oxygen generator?. An electrical squib powered by the battery bus. The door release solenoid. Firing pin mechanism activated when the mask is pulled.

What is the function of the J23 junction box in the oxygen system?. It mixes ambient air with generated oxygen. It controls and distributes electrical power to passenger oxygen deployment circuits. It measures the oxygen cylinder pressure.

Which component collects data from avionics and airframe systems and distributes it via coax cables to the display units?. The Display Electronic Unit (DEU). The Control Display Unit (CDU). The Standby Power Control Unit (SPCU).

What is the function of “program pins” within each display unit?. They store fault codes for BITE. They define the configuration and identity of each display. They connect the coax cables from the DEU.

Where are coax couplers 1 and 3 located?. In the main avionics (E&E) bay, on the E1 rack. Behind the P9 forward electronic panel. Inboard side near captain’s rudder pedals.

What is the function of hold-up voltage from the 28V DC battery bus to the DEU?. Keeps displays active for more than 1 second during transient power loss. (Correct). Provides primary power to the DEUs when engines are off. Powers the BITE circuitry for the displays.

What inputs control automatic brightness for the DEUs?. The CDU “BRT” knob only. The time of day as set in the FMC. Photocell sensors, manual dimmer controls, and ambient light sensors.

What unique feature exists in the coax coupler design between the graphic generator and display unit?. It converts digital signals to analog. It acts as a 1-to-6 signal splitter. It requires 28V DC power to operate.

How does the display unit protect itself from overheating?. It uses bleed air from the pneumatic system for cooling. It will dim the display to 50% brightness. Automatic thermal shutdown, then auto-reset when temperature normalizes.

On the cargo fire control panel, what indicates a non-functioning smoke detector during a test?. A red “FAULT” light illuminates. No light illumination during test position. The fire bell rings continuously.

Which power source operates the engine and APU fire extinguishing squib circuits?. 28V DC from the hot battery bus. 115V AC from Transfer Bus 1. 28V DC from the main DC bus.

What is the function of the filter dryer in the cargo fire extinguishing system?. It mixes the extinguishing agent with nitrogen. It prevents the bottle from discharging too quickly. Removes moisture and debris, ensuring proper bottle discharge sequence.

What key indication confirms an engine fire detection test is successful?. The “BOTTLE DISCHARGE” light illuminates. The fire bell rings and the master “FIRE WARN” lights flash. ENG 1 and ENG 2 OVERHEAT lights illuminate.

What is the temperature range of the lavatory fire extinguisher indicator strip, and what happens when exceeded?. 100–150°F; strip turns red. 180–250°F (82–121°C); strip turns black when overheated. 200–220°F; strip turns yellow.

What must be done after pulling the illuminated APU bottle handle?. Nothing, pulling the handle automatically discharges the bottle. Discharge the bottle or follow the checklist to complete fire-extinguishing sequence. Manually shut down the APU via the overhead panel.

Which maintenance light stays on during faults and alarms but turns off after erasure?. The FAULT light. The “CODE 99” light. The “TEST IN PROG” light.

Which code represents a completed local test?. Code 00. Code 01. Code 99 (Correct).

What is the function of repeatedly pressing the local test switch before the display goes blank?. To erase the fault codes. To cycle through all fault codes until none remain. To increase the brightness of the test display.

What happens if the voice recorder switch is set to “ON” before engine start?. The recorder enters a standby mode and waits for oil pressure. A “CONFIG” warning is generated in the cockpit. The recorder starts recording immediately.

Where is the RIPS (Recorder Interface and Power Supply) located, and what is its function?. Located in the cockpit; provides 28V DC power to the crew microphones. Located in the avionics bay; filters, amplifies, and channels audio from crew mics to the CVR. Located near the CVR (in the tail); erases the CVR upon landing.

What does RIPS stand for?. Recorder Input Power System. Remote Interface and Playback System. Recorder Interface and Power Supply.