AS350C, AS350D, AS350D1, AS350B, AS350B1, AS350B2, AS350B3 AND AS350BA DGAC/EASA APPROVED ROTORCRAFT FLIGHT MANUAL when equipped with

Transcription

1 Supplement FMS-350(4) FAA/EASA APPROVED ROTORCRAFT FLIGHT MANUAL SUPPLEMENT TO THE EUROCOPTER MODELS AS350C, AS350D, AS350D1, AS350B, AS350B1, AS350B2, AS350B3 AND AS350BA DGAC/EASA APPROVED ROTORCRAFT FLIGHT MANUAL when equipped with EMERGENCY FLOATS ON LOW OR HIGH SKID GEAR REGISTRATION # SERIAL # This supplement must be attached to the DGAC/EASA Approved Rotorcraft Flight Manual when the rotorcraft is modified by the installation of Emergency Float Kit P/N in accordance with STC No. SR00831LA, or EASA I.M.R.S Note: AS350 Models C and D1 are not EASA approved The information contained herein supplements or supersedes the basic manual only in those areas listed herein. For limitations, procedures, and performance information not contained in this supplement, consult the basic Rotorcraft Flight Manual. FAA Approved Manager, Flight Test Branch, ANM-160L Federal Aviation Administration Los Angeles Aircraft Certification Office Transport Airplane Directorate FAA Approved Date Original Approval Date: 21 June 1999

2 Supplement FMS-350(4) RFM Supplement to the LOG OF PAGES (INCLUDING REVISIONS) Rev. No. A A Page No. 1 2 Date Description of Change Delete 101, -102, -103, -104 FAA Approved MGR., FLIGHT TEST BRANCH, FAA, LOS ANGELES ACO, TRANSPORT AIRPLANE DIRECTORATE 7 8 DATE: 9 10 Page i

3 LOG OF PAGES (INCLUDING REVISIONS) Rev No. B Page No. Cvr Date 15 Nov 2005 Description of Change Added EASA I.M.R.S. No. Added Note FAA/EASA Approved all iii 2-5 Added EASA I.M.R.S. No. to headers Revised Table of Contents Reversed Sections 3 and 4 Mgr., Flight Test Br., ANM-160L FAA, Los Angeles ACO, Transport Airplane Directorate 1 Revised Section 1 and Section 2, Type of Operation DATE 2 Revised Weight Limitations 5 Added +/- 100 psi to Temperature chart. Page ii

4 TABLE OF CONTENTS SECTION 1 - INTRODUCTION...1 SECTION 2 - LIMITATIONS...1 Type of Operation...1 Altitude Limitations...2 Airspeed Limitations...2 Weight Limitations...2 SECTION 3 - EMERGENCY PROCEDURES...3 General...3 SECTION 4 - NORMAL PROCEDURES...4 External Checks...4 Operations on Water...7 SECTION 5 - PERFORMANCE DATA...7 Rate of Climb Penalty...7 In Ground Effect Hover Penalty - Stowed Floats...7 In Ground Effect Hover Penalty - Inflated Floats...7 Page iii

5 SECTION 1 - INTRODUCTION The Apical Emergency Float installation consists of emergency floats attached to the low or high skid gear and a mechanical inflation system consisting of two inflation bottles, an inflation handle mounted on the cyclic control and attaching hardware. Low Gear Float Kit P/N L.H. Pilot and R.H. Pilot. High Gear Float Kit P/N L.H. Pilot and R.H. Pilot. The system is designed to allow emergency or precautionary landings to water or prepared hard surfaces if the landing is executed in accordance with Section 3. This rotorcraft flight manual is approved by the FAA on behalf of EASA. Type of Operation SECTION 2 - LIMITATIONS The Emergency Floats shall be used only for emergency or precautionary landings. The emergency floats are not approved for ditching in accordance with the JAR/FAR 27 requirements. If the emergency landing was executed in accordance with Section 3, the reason for the emergency landing is corrected, and inspection of the rotorcraft (in accordance with Section 3) reveals no damage, then FAA/ EASA Approved Date: 15 November 2005 Page 1 of 7

6 Operation with the Emergency Floats inflated is permitted for flight to a servicing facility for repacking and recharging of the system. The ferrying airspeed is limited to 95 kt (109 mph) IAS. The rate of climb shall be limited to 1000 feet per minute. NOTE: Service facility shall inspect electrical components if water entered fuselage. Takeoff from the water is not allowed if any damage to the striker tabs on the tail rotor is evident. Altitude Limitations The maximum altitude for inflation is 6,600 ft above the landing surface. Airspeed Limitations Maximum airspeed with the floats stowed: Maximum airspeed for inflation: Maximum airspeed with floats inflated: no change 75 kt (86 mph) 95 kt (109 mph) Weight Limitations When the outside air temperature is lower then 0 C, the minimum weight should remain greater then 1480 kg (3263 lb.) in order to comply with the minimum rotor rpm upon engine failure. FAA/ EASA Approved Date: 15 November 2005 Page 2 of 7

7 SECTION 3 - EMERGENCY PROCEDURES General In the event of an emergency necessitating a landing on water, carry out the emergency procedure outlined in the basic Flight Manual with the addition of the following: Reduce airspeed to a maximum of 75 kt (86 mph). Inflate the floats by actuating the handle on the cyclic control. Make a normal power on or autorotation approach as required except keep the final flare as level as possible. Recommend maximum speed for water contact is 10 kt or less. For power-on landings, reduce speed after touch down to 5 kt or less before lowering collective. NOTES: 1. Time for complete inflation of the floats is approximately 2-3 seconds. 2. Landings on water must be made with the helicopter as level as possible. One-float-first landings may produce undesirable but controllable yaw. 3. After an emergency water landing, inspect the tail rotor striker tabs. If there is no damage, take-off is permitted in accordance with Section II Limitations. If damage is apparent, take-off is not permitted. FAA/ EASA Approved Date: 15 November 2005 Page 3 of 7

8 SECTION 4 - NORMAL PROCEDURES The Normal Procedures specified in the basic Flight Manual apply with the addition of the following: External Checks Check floats for proper security to skid tubes. Check compartment covers for condition and proper closure. Check inflation tubing for condition and security to cross tubes. Check for correct bottle inflation pressure. FAA/ EASA Approved Date: 15 November 2005 Page 4 of 7

9 Temperature Gauge Pressure Fº Cº +/- 100psi Float Bottle Pressure vs. Temperature A detent pin is provided in the inflation handle. It must be removed prior to flight and re-installed upon landing. See page 4. FAA/ EASA Approved Date: 15 November 2005 Page 5 of 7

10 Detent pin must be removed prior to flight and re-installed upon landing. FAA/ EASA Approved Date: 15 November 2005 Page 6 of 7

11 Operations on Water Water taxi is permitted at a maximum recommended taxi speed of 5 kt or less. Minimize aft cyclic movement to ensure maximum tail rotor to water clearance. During engine shutdown on the water, the helicopter may swing through approximately 90º as directional control is lost. During engine start up on the water, the helicopter may swing through approximately 270º before directional control is attained. During take-off from the water, avoid prolonged low hovering in order to minimize spray on windshield SECTION 5 - PERFORMANCE DATA Rate of Climb Penalty Stowed floats 100 fpm Inflated floats 250 fpm In Ground Effect Hover Penalty - Stowed Floats 34 kg 75 lbs In Ground Effect Hover Penalty - Inflated Floats On hard ground 34 kg 75 lbs On water 40 kg 88 lbs FAA/ EASA Approved Date: 15 November 2005 Page 7 of 7