107 Afloat Aviation Operations Fundamentals

107. Afloat Aviation Operations Page 1 of 41

107. AFLOAT AVIATION OPERATIONS FUNDAMENTALS

References:

[a] Local Directives and Standard Operating Procedures

[b] NAVAIR 00-80T-106, LHA/LHD/MCS NATOPS Manual

[c] NAVAIR 00-80T-109, Aircraft Refueling NATOPS Manual

[d] OPNAVINST 5100.19D, Navy Occupational Safety and Health (NAVOSH) Program

Manual for Forces Afloat

[e] NAVAIR 00-80T-120, CV Flight/Hangar Deck NATOPS Manual

.1 Identify the embarked aircraft types and their special aircraft handling characteristics. [ref. a]

1. H-60 Aircraft

1. General

1. When locking/unlocking the tail wheel locking pin, the tow bar attached shall not be moved more than 2 feet to either side of centerline, as any more than that will snap the locking pin.

2. Care shall be exercised while handling the tail wheel and related components. A weak design point, it is not stressed for excessive sideward or downward pressure and cannot withstand repeated abrupt stops/rapid starts.

3. When spotting/landing an H-60, it shall be positioned far enough from the deckedge to allow blade-walkers to remain outboard of the blades during the folding or spreading cycle.

4. The Auxiliary Power Unit (APU) is referred to as the No. 3 engine. The noise level is hazardous within 5 feet of the exhaust port when the unit is operating. The APU shall be started prior to shutting down; this enables the pilot to monitor engine instruments when the final engine is shut down.

5. The aircraft is self-starting; however, if the APU is down, the aircraft can be started with a “huffer.” The H-60 has a crossbleed capability for starting the second engine.

6. Electrical/battery power shall be maintained on the H-60 when folding the tail pylon. Failure to do so can result in uncontrolled tail rotor wind milling.

7. An ALBAR tow bar (longer than a standard tow bar) shall be used when towing the aircraft on the flight deck.

8. The tail wheel strut shall be extended prior to sending aircraft to the hangar deck to allow enough clearance to attach spotting dolly.

Note: Blade spread for all helicopters on the hangar deck shall be performed only with a hydraulic cart/electrical power.

2. EA-6B Aircraft

1. General

1. The EA-6B aircraft has special antennas requiring additional care in spotting. The arc of swing of the horizontal stabilizer is deceiving and requires extremely slow left and right movements of the nose to prevent rapid opposite movement of the tail.

2. The extendable equipment platform (“bird cage”) and boarding ladder shall be stowed before towing due to minimum deck clearance and possible contact with mobile handling equipment.

3. In order to accomplish electronics maintenance in the “bird cage” area, the aircraft shall be spotted in such a manner that the hatch will swing over the deck when opened.

4. Launch aircraft shall be spotted near a 115-volt, three-phase, 400-Hz electrical power source.

5. Crossover bleed starts require additional caution due to the high engine rpm (75 percent) required on the running engine in order to provide the necessary air for engine start.

6. The canopy is of the clamshell design and shall not be operated with winds in excess of 60 knots.

7. The landing gear of an EA-6B shall not be pinned until one of the two engines is shut down. This is due to the unique over-center locking mechanism on the landing gear.

8. Jury struts shall be installed when the wings are full of fuel and when the aircraft is raised or lowered on an elevator. This is to prevent damage to the wing fold mechanism.

9. The EA-6B is equipped with nose wheel steering, but a tog lock disengages the steering when the nose wheel is turned past 56_ from the center position. Additional power and differential braking are required to re-center the nose wheel and to re-engage the tog lock. When high power settings are prohibited, a tow bar shall be attached to manually center nose wheel.

2. Maintenance/Servicing

1. The wings shall be spread for hot refueling due to the close proximity of wing dump lines to hot engine exhaust when wings are folded. The only exception is during CQ evolutions. At CQ fuel weight, if the wings are folded for hot refueling, the wing tanks shall remain empty.

3. F-14 Aircraft

1. General

1. The F-14 horizontal tail, which, when level, is 4-1/2 feet from the deck, has an unusually large throw. The quick movement presents the possibility of personnel injury. In addition, when the leading edge goes down, there is sufficient room for a man to walk between the fuselage and inner edge of the slot and be scissored when the tail returns to neutral. Extreme caution shall be exercised when operating in proximity to the tail.

2. At low power, the intake suction danger reaches almost to the nose wheel.

3. When running, the port engine scavenges a 55-gallon overflow (vent) tank in the tail. During refueling, as each fuel tank fills, small amounts of fuel may flow into the vent tank. In the event of hardware failure, large quantities of fuel could drain into the vent tank and overflow from the vent drain forward of the tail hook. If this is observed, refueling shall cease immediately to minimize the fuel spill.

4. A maximum power steering range of 70 degree either side of center is available. Do not exceed 90 degree (maximum available nose wheel swivel angle) during parking or towing, as damage to steering damper unit will result.

5. The F-14 can be towed from either the nose wheel or aircraft tow fittings incorporated in the lower structure of each engine nacelle near the rear of the aircraft.

CAUTION:Extreme care shall be exercised when taxiing or towing the F-14 while the ship is rolling or turning. The F-14 shall be kept fore and aft until the ship is out of the turn.

Note: During heavy weather, it is recommended that two tractors, one in front, one in rear, be used at the same time. If a spotting dolly is to be used, it is recommended that the F-14 be partially de-fueled.

6. The aux brake and parking brake accumulator pressure indicators shall be pumped into the green bands prior to breaking down and moving an aircraft without combined hydraulic pressure. AUX brake and park brake pressures shall be maintained in the green whenever an aircraft is not chained down to ensure sufficient pressure exists at all times to lock the wheels. Brake accumulators shall be fully charged (3,000 psi) when conditions are severe (greater than a 4-degree deck roll, wet deck, etc). Braking force is proportional to the available pressure. Approximately 13 to 14 full dual brake applications are available in the aux mode with a fully charged accumulator (3,000 psi), and approximately 5 aux mode applications remain when the pressure reaches the red band (1,900 psi).

Warning: Under normal circumstances with a level deck, 1,900 psi (in the red band) is sufficient to hold brakes locked with the aircraft stationary. However, rolling motions greatly increase brake pressure requirements. Accumulator pressures of 2,100 psi may normally be sufficient to stop a moving aircraft during a 4-degree deck roll; but, a fully-charged (3,000 psi) accumulator may not be sufficient to stop a moving aircraft during deck rolls of greater than 6-degrees, especially when the deck is wet and/or other adverse conditions exist.

7. Do not use the SD-1 or SD-2 spotting dolly when the aircraft nose landing gear strut is in the kneel position (distance between ALQ-100 antenna and deck is reduced to 24 inches).

8. When aircraft is in kneel, nose wheel steering is limited left or right 10 degree.

9. Wings will not sweep if flaps are down or any other interlock is present. There is a slight delay (15 seconds) before the wings will go into oversweep angle (68 to 75_). Aircraft hydraulic power is required to sweep/unsweep the wings. Both aircraft hydraulic and electrical power are required to enter/exit the oversweep position. Flight deck personnel shall ensure adequate clearance prior to unsweeping the wings.

10. The aircraft may be taxied or towed in the strut kneeled position, except for the nuisance trip of the launch bar at greater than 10 degree steering angle.

a. The F-14 has a crossbleed capability for starting at idle; however, caution is necessary due to intake suction hazards present even at idle RPM settings.

b. Maintenance/Servicing

(1) Canopy open/close system requires nitrogen charging for operation, and particular aircraft system tightness dictates frequency of charging.

(2) Aircraft is immobile with engine bay doors open or ventral fins removed.

(3) Maximum allowable wind on the nose of the aircraft when conducting engine trim settings (afterburner) is 15 knots.

(4) Aircraft shall not be fueled with starboard engine turning.

4. F/A-18A/B/C/D Aircraft

1. General

1. Two 28-volt, lead acid batteries provide internal electrical power (dc). These batteries provide power for canopy operation and APU starting. The batteries are located behind doors 10L and 10R (10L&R).

2. Canopy operations and external power can be applied through door 9. The F/A-18 A/B/C/D, will accept three-phase, 400-Hz ac power.

3. When external fuel stores are installed, the SD-1/SD-2 spotting dolly’s rotation is restricted.

Warning: Aircraft with wing station drop tanks present a hazardous situation for plane handlers. Plane handlers shall be positioned outboard of the drop tanks during aircraft movement. Route all refueling hose parallel to the A/C fwd of main landing gear to prevent inadvertent exposure to APU exhaust.

4. In the event that emergency forward towing is required, e.g., locked brakes, the tow bar shall be supplemented with chains or cables attached from the tractor to tie down rings on the main landing gear to avoid exceeding design limitations of the nose wheel strut.

5. Tail towing can be accomplished, utilizing the NT-4 towbar. Make sure the tow pins are in the normal tow position, spread the tow bar tubes apart, and attach to the tie down fittings on the rear of the main landing gear. Rearward towing shall not be attempted if nose strut is 11 degree inches or higher, this will cause A/C to rock back onto tail. (All models of F/A-18).

CAUTION: When towing rearward with the aircraft in a tail-heavy condition (gun and/or radar removed and low fuel state), sudden stops may cause aircraft to rock backwards.

2. Brake System

Make sure emergency brake accumulator pressure gauge indicates green and/or 2000-3000 PSI before towing.

3. Starting Requirements

The on-board batteries provide electrical power. External power can also be applied. Air can be used from any standard unit that provides 5:1 or 3.6:1 air pressure. The external air connector on the aircraft is located in the right-hand wheel well.

CAUTION: During crossbleed starts the operating engine advances to 80 percent, increasing Jet Blast and FOD ingestion potential.

5. F/A-18E/F Aircraft

1. The F/A-18E/F stands approximately 2½ inches higher than the F/A-18C/D statically.

2. Two 28-volt, lead acid batteries provide internal electrical power (DC). These batteries provide power for canopy operation and APU starting. The batteries are located behind doors 10L and 10R (10L&R).

3. External power can be applied through door 8. The F/A-18 E/F will accept three-phase, 400-Hz ac power.

4. Brake System

The emergency/park brake handle, located on the L/H vertical console controls parking brakes. Make sure emergency brake accumulator pressure gauge indicates green before towing.

5. Starting Requirements

The on-board batteries provide electrical power. External power also can be applied. Air can be used from any standard unit that provides 5:1 or 3.6:1 air pressure. The external air connector on the aircraft is located in the right-hand wheel well. Crossbleed starts can be done by advancing the operating engine to 80 percent and select to start the opposite engine.

6. Handling

1. When external fuel stores are installed, the SD-1/SD-2 spotting dolly’s rotation is restricted. Aircraft with wing station drop tanks present a hazardous situation for plane handlers. All plane handlers shall be positioned outboard of the drop tanks during aircraft movement. While hot refueling, stand clear of the STBD intake, due to the downward exhaust route and APU location.

2. Plane handlers shall take care when installing tie downs due to the position of the upper plaining link.

3. The boarding ladder is lowered with the electrical activation switch that can be found inside door 8, along with canopy release switch and external power receptacle. The boarding ladder is raised and lowered with the use of hydraulic pressure. The activation switch can be found under door 8, along with the canopy release switch and external power receptacle.

5. Tail towing can be accomplished using the NT-4 tow bar. Make sure the tow pins are in the normal tow position, spread the tow bar tubes apart, and attach to the tie down fittings on the rear of the main landing gear.

CAUTION: When towing rearward with the aircraft in a tail-heavy condition (gun and/or radar removed and low fuel state), sudden stops may cause aircraft to rock backward.

6. E-2/C-2 Aircraft

1. Extreme caution shall be used while working in the area near E-2/C-2 propellers. There is not enough room between propeller and fuselage for personnel to pass. Serious injury or death may occur if E-2/C-2 aircraft are improperly approached while propellers are turning. Approach and exit shall be made at 90 degree to the main mount and aft of propellers. Plane handlers shall never approach turning aircraft without signal from the aircraft director.

2. The brakes shall be pumped up prior to moving the E-2/C-2 aircraft. When pumped to the “full” position, 12 applications are available through the rudder pedals and 3 through the emergency brake handle. A handle in the cockpit recharges the system.

3. Launch E-2 aircraft shall be spotted near two 115-volt, three-phase, 400-Hz electrical power outlets and shall also be accessible to a SINS outlet.

4. Due to the large sail area with the wings folded, the E-2/C-2 may slide sideways when taxied 90_ to a wind of 30 knots or more. Caution, therefore, shall be used when pulling E-2s from spot or when taxiing them crosswind upon clearing the arresting gear. E-2/C-2 aircraft shall not be towed with propellers turning. T-56 engine RPM decay or flameout can result from ingestion of turbojet/turbofan exhaust. E-2/C-2 aircraft shall not be recovered (including touch and go) when turbojet/turbofan aircraft are spotted on or along the No. 2 catapult (4 Row) or along the foul deck line forward of the waist catapults with the turbojet/turbofan exhaust blowing to the port side. This includes aircraft in the de-arm area blowing turbojet/turbofan exhaust to port. These restrictions apply only to exhaust from turbojet/turbofan aircraft.

Note: Commanding Officer’s approval is required for E-2/C-2 movements with winds in excess of 40 knots.

5. When towing or backing the C-2, ensure the tail ramp is in the up position.

6. The E-2/C-2 may be backed into a final spot under its own power. Limited “backing” also is permitted on clear decks. Emergency stops shall be avoided when backing since propeller thrust shall be used to stop aircraft; use of brakes will cause aircraft to swerve or rock back on its tail.

7. A maximum power steering range of 63_ either side of center is available.

8. In case of a flat tire in the landing area, it is desirable that the E-2/C-2 be towed clear vice taxied. Flat nose or main gear tires restrict maneuverability.

9. E-2/C-2 aircraft shall not be fueled with STBD engine turning.

10. When starting the C-2 with a ground turbine cart, ensure the cart, personnel, and support equipment are positioned clear of both prop arcs. Either the port or starboard engine may be started with ground turbine cart attached to either engine nacelle.

11. C-2 aircraft shall be spotted for ease of loading/unloading in case of need for emergency egress.

12. With crew and/or passengers on board, the C-2 shall not be spotted on the flight deck with the tail over the side.

13. When securing E-2/C-2 aircraft, install four TD-1A/B chains to the main mounts, secure both engines, then install two nose TD-1A chains or appropriate chain to achieve required tie down condition.

14. Maintenance/Servicing

High-power turnup requires 18-point tie downs and a high-power hold back chain.

7. S-3 Aircraft

1. The S-3 aircraft is equipped with a parking brake. The brake accumulator gauge shall be in the green area to ensure eight brake applications (gauge is in cockpit below pilot’s MPD, to the left of parking brake handle). Eight to ten brake applications are available if both the brake/APU accumulators are fully charged.