107.1 Discuss the corrosion prone areas of the C-9B/DC-9 aircraft.

A. On the middle fuselage these areas include:

- seams on the exterior skin and around fasteners. - around window frames - around antenna mounting areas - light covers - overwing emergency exits

B. In the Main landing gear and wheel wells these areas include:

- around cables, pulleys, etc. - around doors and spray deflectors. - around wheels and wheel assemblies. - around all hydraulics and hydraulic components.

C. On the wings these areas include:

- on seams and around fasteners. - on the slats - around the leading edge structure. - around all access doors and panels. - around the wing tips and lights - around the fuel filler cover - around the rear spar - around all control cables and hydraulic lines - around the doors and hinges - near the flaps, spoilers, ailerons, trim tabs - around all static discharge wicks

D. Aircraft Interior

- main cargo door actuator and locks - storage areas - flooring, tracks and floor attachment fittings - overwing exits and frames - around all doors - around the toilets - around all crew seats adjustment mechanisms - rudder pedal adjustment mechanism - around all windows and adjacent areas

107.2 Discuss the purpose of the Aircraft Automatic Flight Control System (AFCS).

Better known as the "autopilot," it controls the aircraft in vertical speed, attitude, and heading to reduce workloads on the flightcrew and to provide improved flight comfort and stability. It takes over to control the aircraft in pitch, yaw and roll maneuvering axes. When engaged in a climbing or descending turn, the autopilot will roll the aircraft to a wings-level attitude and hold the vertical speed existing at the time of engagement. Since the autopilot receives VHF navigation, tacan and inertial navigation signals through the pilot flight director navigation selector, VOR/ILS, TAC or INS, as applicable, must be selected on the pilot flight director navigation selector input to the autopilot.

107.3 State the type and model of the C-9B/DC-9 engine.

The aircraft is powered by two-axial flow, bypass, turbofan, Pratt and Whitney JT8D-9A engines flat rated at 14,500 pounds of thrust.

107.4 Discuss the purpose of the constant speed drive.

The constant speed drive (CSD) transmission is a hydromechanical transmission located on the aft side of the engine accessory drive section, at the bottom center line of the engine. It is used to drive an ac generator at a constant speed of 6000 rotations per minute regardless of the engine speed.

107.5 Discuss the types of aircraft fueling methods.

Fueling can be accomplished by pressure or gravity method, with or without power, utilizing conventional ground support equipment. Pressure fueling is accomplished through a fueling adapter located under the right wing. Gravity fueling is accomplished through an overwing fill adapters located on both wings.

107.6 Define and discuss the term "EPR."

EPR stands for Engine Pressure Ratio. The EPR indicators receive sensing signals from the respective engine air inlet pressure probe and the turbine discharge pressure probes, and indicate the engine pressure ratio. This is a measure of the thrust being developed by the engine.

107.7 State the four classifications of fuel leaks.

Class "A" is a slow seep of about 0 to 1/4 inch of leaking fuel.

Class "B" is a seep of greater than 1/4 to 3/4 of an inch of leaking fuel.

Class "C" is a heavy seep of 3/4 to 6 inches, without dripping for JP-4 or 8 inches and/or 4 drops per minute for JP-5 or JP-8.

Class "D" is a running leak. Fuel is greater than 6 inches for JP-4 or 8 inches for JP-5/8; Runs from the surface for both fuels.

107.8 Define the maximum acceptable hydraulic fluid contamination levels for Navy aircraft and related support equipment.

Navy standard class five for aircraft and equipment standard class three for support equipment as defined in the Aviation Hydraulics Manual, NA 01-1A-17, or cleaner contamination level shall be maintained.

107.9 Discuss the safety considerations to be observed when approaching an aircraft with hot brakes.

Park the aircraft in an isolated location and allow the assembly to cool in ambient air. Do not use agents to accelerate the cooling as it exposes personnel to danger. If necessary use spray water fog to the brake side of the wheel. Approach the wheels fore and aft, due to the possibility of the rim exploding.

107.10 Discuss the procedure and responsibilities of the Emergency Reclamation Team.

The team will minimize further damage the aircraft parts and components due to crash, exposure to firefighting chemicals, and salt water. Procedures include: Ensuring the aircraft is safe for maintenance. Removing components from affected areas. Open, loosen, or remove covers, access panels, etc. Allow accumulated salt water to drain off whenever possible. Remove gross amounts of contaminants by flushing with fresh water and draining. Remove components and process them in accordance with the Command Priority List and NAVAIR 01-1A-509.

107.11 Discuss the warnings involved with pressurizing/depressurizing the hydraulic system.

The left and right hydraulic systems are pressurized independently. Doorkeepers must be installed when personnel are working in the wheel wells. Keep the wing flap area clear of personnel and equipment whenever the hydraulic system is depressurized with the flaps in the up position. The flaps could drop rapidly to the full down position.
Before pressurizing or using the hydraulic system, make certain that thrust reversers, flaps, spoilers, elevators, rudder, forward upper cargo door, leading edge slats, rudder pedals, and control columns are clear of obstructions and personnel. The landing gear control lever is in the down position and that the landing gear lockpins have been installed.

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