Enclosure (2) H-65 Data.pdf

Enclosure (2) H-65 Data

This attachment provides information about the H-65 aircraft. The limits listed here pertain to aircraft operation. This data is provided for information only. Design parameters for an ECS will be provided in a specification

Critical Frequencies

The frequencies of most concern are the main rotor blade pass frequencies and 2, 3 and 4 time multiples of the main rotor frequencies. The main rotor revolutions per minute RPM varies with altitude from 355 - 360 RPM from sea level to 5740 ft pressure altitude. The pilot can also command rotor speed to a fixed 365 RPM regardless of altitude. The aircraft has a 10 bladed shrouded tail rotor assembly.

Main Rotor RPM/Hz, Blade Pass (4) Tail Rotor RPM/Hz, Blade Pass (10)

Normal Sea Level 355/5.92, 23.67 3717.8/61.96, 619.6 Normal at Altitude 360/6.00, 24.00 3770.1/62.84, 628.4 High setting 365/6.08, 24.33 3822.5/63.71, 637.1

Armament The aircraft is outfitted with a M-240D machine gun in a door pintle mount configuration. The M-240D is belt fed and has three rates of fire: 650 rounds per minute (10.8 Hz), 750 (12.5 Hz), 950 rounds per minute (15.8 Hz). Only the lower rate of fire is used in H-65 operations (650 rounds per minute (10.8 Hz)).

Crash Load Design Factors Equipment installed in the cabin area of either aircraft will be designed for the following load factors:

20 g’s forward and aft 10 g’s on the rotors 20 g’s on the helicopter bottom 10 g’s on either side

Modifications to the H-65 must be designed to meet or exceed the requirements of 14 Code of Federal Regulations CFR 29 Airworthiness Standards: Transport Category Rotorcraft.

Pulley There is a pulley mounted on the tail rotor drive shaft that turns either a Sanden SD510HD or SD7H15 or other air conditioning compressor at 3200 RPM.

H-65 General Description

The USCG H−65 Short Range Recovery (SRR) helicopter, a product of Aerospatiale Helicopter Corporation (now Airbus Helicopters), is designed for short range search and rescue operations.

Secondary mission roles are patrol and observation, passenger transport, and cargo hook operations. It is capable of operating from prepared and unprepared areas in visual and instrument flight conditions, day or night and is configured with Night Vision Goggle (NVG) compatible cockpit lighting. The main sections of the fuselage are the forward section consisting of the cockpit, cabin area and baggage compartment, and the aft (tail boom) section. The forward section is constructed primarily of longitudinal, aluminum alloy beams and non−metallic honeycomb, laminated with fiberglass cloth. The aft section consists of a truncated cone of composite honeycomb fiberglass with a metal covering which supports the vertical fin and a fixed horizontal stabilizer. Cockpit entrance is through two hinged doors located forward of the cabin next to the pilot’s and copilot’s stations. Entrances to the passenger area are a hinged door on the left side of the cabin aft of the copilot’s station and a sliding door on the right side of the cabin aft of the pilot’s station. A baggage compartment door is located on the right side aft of the cabin for exterior access to the baggage compartment. The side−by−side cockpit arrangement is equipped with dual flight controls augmented by an Automatic Flight Control System (AFCS).

Each station has a full instrument panel and controls for the avionics systems. Refer to figure 5−1 for general cockpit arrangement. The passenger−cargo area is designed to accommodate a rescue basket, litter configurations, and a hoist operator station. Seats may be installed for five passengers and a crew of three. The propulsion system, consisting of two turbo shaft engines and a drive system, is mounted above the fuselage on a platform located above the aft cabin area. The engines and drive systems are enclosed by a cowling which may be swung open or removed for access. The rotor system consists of a single 4−blade main rotor, which may be folded for shipboard parking or storage, and a multi−bladed shrouded tail rotor located within the vertical fin. Two independent hydraulic systems provide power for the flight controls, retractable landing gear, wheel brakes, and a 600 pound capacity rescue hoist. The electrical system includes dual AC and DC generating systems: two 10.5 KVA alternators to supply 400 Hz AC power (115V single phase), and two starter/ generators for 28 VDC power. In addition, each engine has a dual channel alternator to run its Full Authority Digital Engine Control (FADEC) computer. Electrical power can also be supplied by an internal battery or transformer/rectifier for emergency DC power, or AC and DC external sources. A Common Avionics Architecture System (CAAS) Avionics Management System integrates multiple communications, navigation and mission subsystems, automatic cockpit management, and flight guidance and control through selection of special sensors, and use of data stored in on−board Control Display Units (CDU). The Flight Director System (FDS) may be coupled to the AFCS to enhance airborne control of the helicopter. Additional equipment includes weather and search radar, an Environmental Control System (ECS), emergency pop−out flotation system, a 2,000 pound capacity cargo hook, and a controllable searchlight. The maximum unrestricted gross weight of the helicopter is 8,900 pounds. Restricted operations may be conducted up to a maximum weight of 9,480 pounds.