107.1 Define the following terms:

a. IFR - Instrument Flight Rules

Pilots comply wiht IFR procedures when operating their aircraft in weather conditions that are less than Visual Flight Rules minimums. IFR simply means the pilots fly using instruments.

b. VFR - Visual Flight Rules

A pilot operating in VFR conditions is flying in accordance with the see-and-avoid concept. This means the pilot is responsible for his or her own separation from other planes under most circumstances.

c. IMC - Instrument Meteorological Conditions

Weather or meterological conditions expressed in terms of visibility, distance from clouds, and ceiling less than the minimum specified for visual meterological conditions.

d. VMC - Visual Meteorological Conditions

Weather or meterological conditions expressed in terms of visibility, distance from clouds, and ceiling equal to or better than specified minimums.

107.2 Define term "NALO" and state its purpose.

Navy Air Logistics Office -

They act as the principal scheduling authority/activity for all Naval Reserve C-130 airlift and all overseas flights originating or terminating in CONUS, (Continential United States).

107.3 Discuss the adverse effects of cold/hot operational environmental conditions on the aircraft.

Cold:

The effect on aircraft materials such as rubber, plastic, and fabric materials is to stiffen and possibly crack, craze or shatter when loads are applied. Oils and lubricants coagulate. Metals contract differently and icing conditions affect control surfaces and aircraft systems.

Hot:

High humidity results in condensation throughout aircraft. Malfunction of electrical equipment, fogging of instruments, corrosion of metal and the growth of fungus are possible results. Further results may be pollution of lubricants and hydraulic fluids and deterioration of non-metallic materials.

108.1 Discuss the Support Equipment (SE) Training and Licensing Program.

Proper operation of support equipment is the key to safe, efficient aircraft and equipment maintenance. Improper use of SE has resulted in excessive ground handling mishaps, repair and replacement resulting in millions of dollars annually and reduced operational readiness.

The program establishes policy, responsibilities and requirement for SE training and licensing.

108.2 State the purpose of, the routing sequence of and which person initiates the SE misuse/abuse report.

The purpose of a SE Misuse/Abuse report is to inform the IMRL with the reporting responsibilities about the misuse/abuse, then to inform the CO of the command which held responsibility of the item that had the misuse/abuse. Ultimately the purpose is to ensure command accountability for the offense.

The routing sequence is as follows:

- The witness prepares and forwards a SE Misuse/Abuse report to the controlling IMRL, (Individual Material Readiness List)

- The QA of the controlling IMRL shall assign a control number and prepare an official typewritten report for the MO’s signature.

- This report is forwarded to the QA of the receiving command, which will conduct a thorough investigation, reporting recommendations to the CO.

- The CO shall return the report to the originator within 10 working days, with recommendations and actions taken described on the back of the form.

108.3 Identify and discuss the purpose of the following SE:

a. NC-10C –----->

A towed unit that provides 115/200 volts, 3 phase, 400 hertz AC, and 28 volts DC for shore based servicing, starting, and maintenance of aircraft.

b. NC-8 –

Self-propelled unit that provides 115/200 volts, 3 phase, 400 hertz AC, and 28 volts DC power for servicing, starting and maintenance of aircraft.

c. NANCART –----->

A towed unit that provides a mobile source of compressed nitrogen to recharge aircraft nitrogen systems.

d. MMG-1A –

Hangar supported power cart that provides 115/200 volts, 3 phase, 400 hertz AC, and 28 volts DC power for maintenance, calibration and support of aircraft.

108.4 Demonstrate the following standard aircraft handling signals:

a. Fire -

Make a large sleeping figure 8 with one hand and point to the fire area with the other.

b. Hot brakes -

Make rapid fanning motion with one hand in front of face, point to wheel with other hand.

c. Emergency stop -

Arms crossed above the head with hands made into fists.

d. Brakes on/off -

Brakes off, arms above the head with open palms and fingers raised with palms toward aircraft. Brakes on, same thing but hands are closed into fists.

e. Remove chocks -

Arms down, fists closed, thumbs extended outwards, swing arms out.

108.5 State the safety precautions that must be observed during the following operations:

a. Engines –

While engines are turning there shall be a safety observer/fire bottle watch to ensure nobody comes close to the engines, and to inform the person turning the engines if any smoke or fire comes out of the motor nacelles or exhaust.

b. Auxiliary Power Unit (APU) –

While the APU is operating a safety observer will man the fire bottle to ensure no fires start and to ensure nobody goes near the APU exhaust.

Identify the following system component parts and discuss the designated items for each:

201.1.1 Fuselage Sections:

a. Forward:

Fuselage station 0 to fuselage station 245. Most forward part of the aircraft.

b. Mid:---->

Between fuselage station 245 and fuselage station 737. The main cabin areas.

c. Aft:

Fuselage 737 and aft. The ramp and door area in the aircraft.

d. Horizontal stabilizer:

Are the horizontal fins on the empennage. They provide longitudinal stability.

e. Vertical stabilizer---------->

Is the vertical fin on the empennage and provides directional stability.

201.1.2 Wings:

a. Center Wing:

Center wing provides lift, and is located at the center of the fuselage to the outer wing (usually described as the rainbow panels). The center wing also consists of the “box beam” and is the strongest section of the wing; the outer wings attach to it.

This section runs from center wing station 0 to center wing station 214.

b. Outer wing:

Outer wing provides lift, outer wings attach to the center wing. The outer wing runs from outer wing station 0 to outer wing station 576.

201.1.3 Flight controls/surfaces:

a. Flaps:

Flaps increase lift at slower speeds, located in the trailing edge of the wing.

b. Ailerons:

Ailerons provide roll, attached to the trailing edge of the outboard wing.

c. Rudder:

Rudder provides yaw, attached to the aft edge of the vertical stabilizer.

d. Elevator:

Elevators provide pitch, attached to the trailing edge of the horizontal stabilizer.

e. Trim tabs:

Trim tabs provide minor corrections to maintain flight stability, attached to the trailing edge of the primary flight controls.

201.1.4 Landing gear:

a. Strut----------->

Struts absorb shocks from landing, 2 struts on each main and one on the nose.

b. Brakes:

Brakes slow, and stop the aircraft. Mounted on each main landing gear strut.

Modes of operation: normal and emergency.

c. Wheels: Two wheels on the nose strut, one on each main. Total of 6 wheels.

201.1.5 Hydraulics:

a. Utility hydraulics system--------->

Runs half of all the flight controls, nosegear steering, normal brake operation and is located on the forward section, port side of the main landing gear. Operated by engines 1, and 2.

b. Booster hydraulic system------->

Runs half of all the flight controls. Located on the forward section, starboard side of the main landing gear. Operated by engines 3, and 4.

c. Auxiliary hydraulic system:

Runs the cargo door, ramp, and emergency brakes. Portside aft of paratroop door. Operates in manual or electric mode. Can also be used for troubleshooting/operational checkout of flight controls on deck, in conjunction with the Ground Test Checkout Valve.

d. Ground test checkout valve

Will allow the connection of the auxiliary hydraulic system to the utility hydraulic system, so that you may operate the flight controls on deck without the use of other support equipment. Located aft of the portside main landing gear, just forward of the port paratroop door.

When this handle is lowered, auxiliary system pressure is directed through the utility system. When this handle is in the up and pinned position, system pressure flows normally.

201.1.6 Airframe components:

a. Radome:

Houses the radar, it forms the nose of the aircraft. Do not work in this area unless the radome is up and in a safe lock position.

b. Paratroop doors:

Aft of the main landing gear wheel wells. These doors are very heavy and work on a counterbalance system. Use caution when opening and closing the doors. Never slam the paratroop doors shut, serious damage may occur. When these doors are open (up) they must be pinned.

c. Cargo door and ramp system:

Allows for the quick loading and off-loading of cargo, equipment, and personnel.

Located in the empennage. The cargo door should never be operated when personnel are working above it, and the ramp should not be lowered without first checking the area around it for clearance.

The cargo door and ramp have two modes of operation, manual, and electric hydraulic pump.

d. Crew Entrance door:

Location: On the port side of the forward fuselage

Modes of operation: Opened, closed, and emergency jettison

Safety precaution: Always stand to the side when opening the door, and don’t allow the door to free-fall

e. Emergency Exits:

Functions: Allows emergency egress from the aircraft

Location: Three overhead hatches, 1 in each section of the aircraft.
2 emergency exits both port and starboard, forward of the inboard engines.

f. Air deflector doors:

Functions: Deflect air for paratroops. Location: From the aft part of the main landing gear fairing. Modes of operation: Opened, closed, or in hold.

201.1.7 Air Conditioning system:

a. Flight station:

Function: Cools, and heats the flight station, also provides 1/3 of the aircraft pressurization.

Location: Starboard, forward of the 245 bulkhead

Modes of operation: OFF, AUX VENT, NO PRESS, AUTO PRESS, and MAN. PRESS.

b. Cargo compartment:

Function: Cools, and, heats the cargo compartment, also provides 1/3 of the aircraft pressurization.

Location: Starboard, forward of the main landing gear

Modes of operation: Auxiliary vent, aircraft auto press

c. Cargo compartment under floor heating:

Function: To heat the cargo floor, and provides 1/3 of the aircraft pressurization at 35,000 feet.

Location: A ducting system under the cargo compartment floor.

201.1.8 Cabin Pressurization system:

a. Cabin pressure controller:

Location: On the pressurization control panel

Function: Regulate pressure in flight in auto or manual.

Modes of operation:

AUTO
MANUAL
NO PRESS
AUX VENT.

Safety precautions:
Do not force CABIN ALT knob below -1000 or above 10,000.
(AD1 Leininger pulling the Emergency Depressurization Switch)

b. Outflow valve----->

Function: Regulate pressure between aircraft interior and atmospheric pressure.

Location: Starboard side the aircraft near the navigation position.

c. Safety valve

Function: Electrically controlled and pneumatically opened in a non-pressure condition or for emergency depressurization.

Location: Cargo door.

Mode of operation: Open and closed.

Safety precautions: Don’t obstruct safety valve.

d. Emergency depressurization hatch------>

Function: For emergency depressurization.

Location: Center emergency escape hatch.

Modes of operation: Pull down on handle above the pilots’ seat.

Safety precautions: Don’t open during normal pressurization

201.1.9 Oxygen sources:

a. Walk around bottle------->

Quantity: 4

Function: Provide portable oxygen

Location: 1 next to pilot, 1 next to copilot, 1 on the backside of 245 bulkhead, and 1 aft of starboard main landing gear.

Next to each bottle is a hose used for recharging the bottles to approximately 300 psi pressure.

b. Liquid oxygen:

Function: Provide oxygen source to aircrew.

Location: Starboard side nose landing gear wheel well

Safety precautions: Ensure no oil, grease, or fuels are in the area, make sure clothing, hands, and all equipment are clean prior to servicing.

201.1.10 Anti-icing and de-icing systems:

a. Anti-Icing: Prevent icing on critical areas.

b. De-icing: Remove ice after it has formed.

c. Ice Detector:

Functions: Automatic control of anti-icing and de-icing control system.

Location: Inside the intake of #2 and #3 engine. Safety precaution: 30 seconds is the maximum time you can operate the ice detector on the deck.

d. Engine Inlet Anti-Icing: Function: To prevent icing of engine inlet, and air duct anti-icing Location: In the engine, all 4 interconnected to ice detection in #2 & #3 engines.

Safety precaution: Excessive bleed air can damage structures and leading edges.

e. Propeller anti-ice/de-ice:

Function: Anti-ice and de-icing of the propeller

Location: Forward section of the spinner and propeller afterbody.

Safety precautions: Do not operate propeller anti-icing or de-icing for an engine that is not running when the aircraft is on the ground.

f. Wing and empennage anti-icing:

Function: To keep the wing and empennage from icing.

Location: Leading edge of the wing, and empennage.

Safety precautions: The leading edge anti-icing system must not be used to remove ice from surfaces when the aircraft is on deck. If operated for testing, constant monitoring of the temperature indicators must be maintained and the system must not remain on for more than 30 seconds.

g. Wind shield anti-icing:

Function: Windshield anti-icing.

Location: 3 center windshields, 2 windows each, on both sides of the center windshields, and the 2 lower windows in front of the pilot.

Safety precautions: Operation of NESA anti-icing when outside air temperature is above 27 degrees C will increase the possibility of delamination within the NESA panels.

h. Pitot tube------>

Function: Prevent icing on the pitot tube. This tube is heated to prevent ice from forming on it.

Location: Nose of the aircraft, below windows.

Safety precautions: Do not touch with bare hands, as the tube is heated.