Bt. Bp. Mecatronica

Pakistan Military Consortium :: www.PakDef.info
Westland Lynx HAS 3.
DESIGN FEATURES: Compact design suited to hunter-killer ASW and missile-armed anti-ship naval roles from frigates or larger ships (superseding ship-guided helicopters), armed/unarmed land roles with cabin large enough for squad, or other tasks; manually folding tail pylon on naval versions; single four-blade semi-rigid mainrotor (foldable), each blade attached to main rotor hub by titanium root plates and flexible arm; rotor drives taken from front of engines into main gearbox mounted above cabin ahead of engines; in flight, accessory gears (at front of main gearbox) driven by one of two through shafts from first stage reduction gears; four-blade tail rotor, drive taken from main ring gear; single large window in eachmain cabin sliding door; provision for internally mounted armament, and for exterior universal flange mounting each side for other weapons/stores. Super Lynx has maximum T-O weight of 5,125 kg (11,300 lb); all-weather day/night capability; extended payload/range; advanced technology swept-tip (BERP) composites main rotor blades offering improved speed and aerodynamic efficiency and reducedvibration; and reversed direction tail rotor for improved control.
Westland Sea King Mk 45.
DESIGN FEATURES: Based on Sikorsky S-61/SH-3 airframe and rotor system; Rolls-Royce Gnome turboshaft engines; specialised equipment to UK requirements; composites rotor blades; new six-blade tail rotor for increased capability in side wind; unbraced tail stabiliser; increased fuel capacity. Automatic main rotorblade folding and spreading is standard; for shipboard operation the tail pylon can also be folded.
SYSTEMS: Three main hydraulic systems. Primary and auxiliary systems operate main rotor control. System pressure 103.5 bars (1,500 lb/sq in); flow rate 22.7 litres/min at 88 bars (6 US gallons; 5 Imp gallons/min at 1,275 lb/sq in). Unpressurised reservoir. Utility system for main landing gear,sonar and rescue winches, blade folding and rotor brake. System pressure 207 bars (3,000 lb/sq in); flow rate 41 litres/min at 186 bars (10.8 US gallons; 9 Imp gallons/min at 2,700 lb/sq in). Unpressurised reservoir. Electrical system includes two 20 kVA 200 V three-phase 400 Hz engine-driven generators, 26 V single-phase AC supply fed from aircraft's 40 Ah Ni/Cd battery through an inverter, and DCpower provided as secondary system from two 200 A transformer-rectifier units.
CH-53 Patch/Fix - The simFlight Network Forums
"10. BLADE AND PYLON FOLD SYSTEM
The system is designed to position the main rotor blades for either blade or pylon folding first before folding. Each may be selected and folded separatelly, but the main rotor blades can not be folded if the pylon has already been folded.Hydraulic pressure for folding is provided by the utility hydraulic system, the fold system can be controlled from the panel
Page 15/40
Nemeth Designs Sikorsky CH-53E Operation Manual System Descriptions
marked BLADE/PYLON FOLD. Manual fold and spread of the tail rotor pylon may be accomplished by using the hydraulic handpump mounted forward on the right side of the cabin, electrical power isnot required for manual operation. The cyclic stick position indicator on the instrument panel permits the pilot to establish the necessary blade pitch position required for blade folding."
In addition to my last post and after playing around with a few things I have found that the following has to be carried out BEFORE the blades/pylon can be folded.

1. Turn APP Circuit Breaker Control SwitchOn.
2. Move the APP Control Lever Forward then back to Centre.
3. Swith On Generator 1 Switch.
4. Go to Overhead Panel 1 (Shift 2) then Blade/Pylon Switches and then fold blades and pylon.
5. Turn off Gen 1 switch, Move APP Control Lever to left, switch off APP CB Con Switch.

It does not mention anywhere in the manual stage 1 through 3 before attempting to fold blades/pylon :( hense, a...