20690 Catmen Loop, Suite# 102.. ' ~ FAA APPROVED ROTORCRAFT FLIGHT MANUAL SUPPLEMENT FOR THE: SIKORSKY MO:OELS S61-A, L, N & V HELICOPTERS AND CROMAN CORPORATION MODEL SH3H RFMS NO. REGISTRATION NO. ----- - - - - SERIAL NO. - ----- ---- - - This supplement must be attached to the FAA approved Rotorcraft Flight Manual when an auxiliary hydraulic system as described in STC# SR01288SE is installed. The information contained in this document supplements or supersedes the basic manual only in those areas listed. For limitations, procedures, and performance information not contained in this supplement, consult the basic Rotorcraft Flight anual. Manager-Seattle Aircraft Certification Office Revision: D
20690 Catmen Loop, Suite# 102. LIST OF ACTIVE PAGES PAGE NO. REV. LEVEL EFFECTIVITY COVER D ALL 1 c ALL 2 c ALL 3 c ALL 4 c ALL 5 c ALL 6 c ALL 7 c ALL 8 c ALL 9 c ALL 10 c ALL 11 c ALL 12 c ALL 13 c ALL 14 FAA Approved: NOV 3 0 2006 2
SUPPLEMENT REVISION LOG REV. AFFECTED REVISION DESCRIPTION LEVEL PAGES 0 ALL Initial Release A 6, 10, 12 Description and instruction regarding addition of "HYD OIL TEMP" indicator light. Title change includes use for models S61 A, L, & N B Cover Sheet Title change includes use for Croman Corporation Model SH3H c ALL Report number change from AASI- MM-631 to KATI-MM-631. Company name and Address change (Kawak Aviation Technologies 20690 Carmen loop, Suite# 102 instead of Ag-Air Systems 373 S.E. Bridgeford Blvd.) FAA APPROVED. DATE D Cover Sheet Title change includes use for Model S61-V NOV 3 0 2006 FAA Approved: 3
TABLE OF CONTENTS SECTION 1......... 5 1.0 GENERAL INFORMATION...... 5 1.1 TERMINOLOGY................ 5 1.2 AUXILIARY HYDRAULIC SYSTEM DESCRIPTION........ 6 SECTION 2............ 9 2.0 LIMITATIONS......... 9 2.1 AUXILIARY HYDRAULIC SYSTEM... 9 2.2 PLACARDS................................. 9 2.3 APPROVED AUXILIARY HYDRAULIC SYSTEM OILS........... 10 2.4 WEIGHT AND CENTER OF GRAVITY LIMITS... 10 2.5 #2 AC GENERATOR ELECTRICAL LOADS................. 10 SECTION 3.............................. 11 3.0 NORMAL PROCEDURES...................... 11 3.1 PREFLIGHT CHECKS AND PROCEDURES....... 11 3.2 AUXILIARY HYDRAULIC SYSTEM OPERATION (General)... 12 3.3 AUXILIARY HYDRAULIC SYSTEM OPERATION (Fire tank system)... 12 3.4 AUXILIARY HYDRAULIC SYSTEM OPERATION (Implement)...... 13 SECTION 4...... 14 4.0 EMERGENCY PROCEDURES... 14 SECTION 5.................. 15 5.0 PERFORMANCE CHANGE...... 15 SECTION 6.......................................................... 16 6.0 DOCUMENT CROSS REFERENCE.............................................. 16 FAA Approved: NOV 3 0 2006 4
20690 Ca1men Loop, Suite# 102. SECTION 1 1.0 GENERAL INFORMATION This flight manual supplement is divided into six sections as follows: Section 1 provides information on definitions and terminology used in the flight manual supplement. It also describes the fundamental design and operation ofthe auxiliary hydraulic system. Section 2 tbru 5 contains FAA approved data necessary to operate the auxiliary hydraulic system in a safe and efficient manner. Section 6 lists the other associated manuals for the installation of and maintenance of the auxiliary hydraulic system. 1.1 TERMINOLOGY Warnings, cautions, and notes are used throughout this manual to emphasize important and critical instructions and are used as follows: ***WARNING*** An operating procedure, practice, or etc., which, if not correctly followed, could result in personal injury or loss of life. **CAUTION** An operating procedure, practice, etc., which, if not strictly observed, could result in damage or destruction of equipment. *NOTE* An operating procedure, condition, which is essential to highlight. FAA Approved: NOV 3 Q?006 Revised: November I 0, 2006 5
KA TI-FM-631 1.2 AUXILIARY HYDRAULIC SYSTEM DESCRIPTION The Kawak Aviation Technologies auxiliary hydraulic system is designed to provide a 26 horsepower auxiliary power source for the utilization of hydraulic powered implements such as agricultural, forestry, and firefighting equipment. The Kawak Aviation Technologies auxiliary hydraulic system is a self contained system that only requires power from an accessory drive pad on the aircraft's transmission and electrical power for the operation of the hydraulic control valve that modulates the hydraulic flow to the installed hydraulic implement. The hydraulic pump is driven by an auxiliary reduction gearcase installed between the #2 generator and the generator pad on the accessory gear case of the transmission. Since the electrical loads on the #2 generator typically are small (except with the #1 generator offline) the available surplus power is used to drive the auxiliary hydraulic system. The auxiliary drive system is isolated from the primary aircraft power train by a shear coupling located between the drive pad on the transmission and the auxiliary reduction gearcase. The hydraulic reservoir mounts aft of the transmission in conjunction with the ships hydraulic reservoirs in the structure used to house the ships hydraulic reservoirs, oil cooler, etc. The sealed reservoir assembly includes intemal isolation baffling, retum oil diffusion, venting features, along with oil level sight glasses, reservoir relief, and a predetermined air space to accommodate thermal expansion of the oil. Also located in the compartment aft ofthe transmission is a fan driven hydraulic oil cooler and the control valve for activating the auxiliary hydraulic system. FAA Approved: NOV 3 0?DCJ.S 6
A supplemental control panel for the auxiliary hydraulic system is installed in the center instrument panel. The panel contains a digital pressure gauge for monitoring the pressure of the auxiliary hydraulic system, a toggle switch (MANUAL 0/R) to activate the system, and amber warning lights for high hydraulic oil temperature and low reservoir oil. Circuit breakers for the auxiliary hydraulic system are located in overhead console supplied from the main aircraft electrical bus. It is also typical to integrate the cockpit control for the auxiliary hydraulic system with the existing cyclic implement control switch for the spray, firefighting, or bucket system. It is then possible to activate the auxiliary hydraulic system simultaneous to the operation of the implement. For normal operation, the hydraulic pump draws oil from the reservoir and delivers the oil to the hydraulic control valve. With the system in the "OFF" position, all oil is bypassed directly through the valve to the oil cooler, thru the 10 micron hydraulic filter and back to the reservoir at a minimal operating pressure. When either the "MANUAL 0/R" switch on the panel is activated or the implement controller supplies power to the control valve, a bypass circuit in the control valve closes directing all oil to flow to the implement. Return flow from the hydraulic implement goes to the control valve and then back through the cooler and filter. All hydraulic oil under any operating condition must pass through the 10 micron filter before returning to the reservoir. The filter head is equipped with a 25 psi bypass valve. The hydraulic manifold also incorporates a pressure relief valve set at 2400 psi. If the system is activated with no implement connected or the pressure requirements to operate the implement exceed 2400 psi, the relief valve will open limiting the system pressure by bypassing the oil directly to the return side of the system. FAA Approved: NOV 3 0 ~'CCJ(i 7
20690 Carmen Loop, Suite# 102. The "P 1" and "Rl" ports of the control valve that supply oil to and from the hydraulic accessory are terminated in the form of quick disconnect couplings located inside the helicopter aft of the transmission opening. If using an implement suspended from the cargo hook that is jettisonable, provisions must be made for breakaway hydraulic connections under the aircraft. The auxiliary hydraulic system shares the available power at transmission accessory pad with the #2 AC generator. The normal electrical draw on the #2 AC generator is typically very low (less than 1 KV A) with no cabin heater operating. The residual power available at the pad is used for driving the hydraulic system with the hydraulic pump and system relief valve setting designed to work within the limits of the power available. Should the main (#1) AC generator go offline and require the #2 AC generator to assume the primary electrical supply requirements of the aircraft, the auxiliary hydraulic system must be turned off. The auxiliary hydraulic system must also be turned off when using the cabin heater as the combined electrical loads on the #2 AC generator and the auxiliary hydraulic system when operating at full capacity exceed the drive pad limits on the transmission. FAA Approved: NOV 3 0 ;(J06 8
SECTION2 2.0 LIMITATIONS 2.1 AUXILIARY HYDRAULIC SYSTEM 2.1.1 The auxiliary hydraulic system must be turned "OFF" in the following conditions: a. Engine start. b. When using an implement with a "closed center" control manifold with all functions "OFF". c. When operating the aircraft with no hydraulic accessory attached to the hydraulic system. d. During auto-rotation (See page 11 ). e. If the # 1 AC generator goes offline and the #2 AC generator has to assume the AC power supply requirements of the aircraft. f. Ifthe cabin heater is "ON". 2.2 PLACARDS 2.2.1 The following placards must be installed in plain view of the pilot: "AUXILIARY HYDRAULIC SYSTEM MUST BE OFF DURING ENGINE START" "AUXILIARY HYDRAULIC SYSTEM MUST BE OFF IF #2 AC GENERATOR IS USED FOR PRIMARY GENERATOR" FAA Approved: NOV 3 0 2006 Revised: November 10. 2006 9
20690 Catmen Loop, Suite# 102. 2.3 APPROVED AUXILIARY HYDRAULIC SYSTEM OILS 2.3.1 Hydraulic reservoir MIL-H-5606E 2.4 WEIGHT AND CENTER OF GRAVITY LIMITS The auxiliary hydraulic system including oil adds 108.3 lbs. to the empty weight of the helicopter. The e.g. of the installation is: STA 308.25 WL 206.5 BL ll.or 2.5 #2 AC GENERATOR ELECTRICAL LOADS 2.51 The total connected load to the #2 AC generator must be limited to. 7 KV A or less (with cabin heater off). FAA A d NOV 3 0 rl(l f'\t " pprove : (JJO 10
20690 Catmen Loop, Suite# 102. KA TI-FM-631 SECTION3 3.0 NORMAL PROCEDURES 3.1 PREFLIGHT CHECKS AND PROCEDURES While conducting the preflight checks for the aircraft as described in the rotorcraft flight manual, simultaneously check the condition of the auxiliary hydraulic system. AUXILIARY HYDRAULIC SYSTEM- Roof mounted components a. Auxiliary hydraulic reservoir - Check for proper fluid level. Oil should be visible in sight glasses. Full level is top of the uppermost sight glass. * NOTE * If an implement is installed utilizing accumulators such as a fire tank, oil level must be checked with the accumulators in the discharged state. b. Reduction gearcase - Check for proper fluid level in the sight glass located on the outboard side of the gearcase. Oil should be at the top of the sight glass. c. Hydraulic hoses, components, and electrical connections- Inspect for evidence of leaks and chafing. AUXILIARY HYDRAULIC SYSTEM- Cockpit controls d. With aircraft master "ON", check digital auxiliary hydraulic system pressure indicator for proper reading. e. Check to make sure hydraulic cooler fan is operational. f. Insure the "MANUAL 0/R" switch is in the "OFF" position. g. Insure the implement control switch on the cyclic is in the "OFF" position. FAA Approved: NO\/ 3 0 /i;~ ;;) 11
h. Push-to-test the "LOW OIL" indicator light to check for proper operation. 1. Push-to-test the "HYD OIL TEMP" indicator light to check for proper operation. 3.2 AUXILIARY HYDRAULIC SYSTEM OPERATION (General) 3.2.1 Prior to engine start: "MANUAL 0/R" switch- "OFF" 3.2.2 Auxiliary hydraulic pressure indicator will indicate bypass pressure when the system is in the "OFF" position and aircraft is running. **CAUTION** Do not activate the auxiliary hydraulic system with the "MANUAL 0/R" switch on the instrument panel with no implement connected to the system. Hydraulic system overheating will occur. 3.3 AUXILIARY HYDRAULIC SYSTEM OPERATION (Fire tank system) *NOTE* The auxiliary hydraulic system is interconnected with the controller for the fire tank. When a tank/unction (doors open/closed or hover refill) is initiated, the auxiliary hydraulic system will activate automatically. **CAUTION** Do not activate the auxiliary hydraulic system with the "MANUAL 0/R " switch on the instrument panel when operating the fire tank system. Hydraulic system overheating will occur. 3.3.1 The digital pressure indicator will indicate hydraulic pressure required for fire tank operation when fire tank controller is actuated. FAA Approved: NOV 3 0 ' l\i;} 12
20690 Ca1men Loop, Suite# 102. 3.4 AUXILIARY HYDRAULIC SYSTEM OPERATION (Implement) Implement requiring constant hydraulic flow - open center system. 3.4.1 Activate the auxiliary hydraulic system using the "MANUAL 0/R" switch on the instrument panel. 3.4.2 Use the implement control switch on the cyclic to operate the implement as required. 3.4.3 When implement use is complete, turn "MANUAL 0/R" switch "OFF". FAA Appro ed: Revised: ove mber 10, 2006 NOV 3 0 ~UUc 13
SECTION 4 4.0 EMERGENCY PROCEDURES 4.0.1 In the event of a hydraulic system malfunction such as a damaged hydraulic hose, or "LOW OIL" indicator light, tum the auxiliary hydraulic system "OFF" via the cyclic implement control switch. If the system is operating in the manual mode, tum the instrument panel "MANUAL 0/R" switch to "OFF". Land as soon as practicable and investigate. 4.0.2 If an auto-rotate maneuver should be required for any reason, insure that the auxiliary hydraulic system is "OFF" via the implement control, or via the "MANUAL 0/R" switch if the auxiliary system is operating in the manual mode. This will minimize power consumption on the rotor system. 4.0.3 In the event of an engine or electrical related malfunction, tum the auxiliary hydraulic system "OFF" via the implement control or the "MANUAL 0/R" switch. 4.0.4 If the "HYD OIL TEMP" warning light illuminates, insure that the hydraulic system is in the "OFF" position if no implement is attached. If the system had been inadvertently left on, tum the control "OFF". Insure that "AUX HYD FAN" circuit breaker is pushed in. Arm the circuit breaker if it was pulled. If the oil temp light does not extinguish within one minute, land as soon as practicable and investigate. If the "HYD OIL TEMP" light illuminates during normal operation, tum the system "OFF". If the light does not extinguish within one minute, land as soon as practicable and investigate. FAA Approved: NOV 3 0 14
SECTIONS 5.0 PERFORMANCE CHANGE No change. FAA Approved: NOll 3 0 ' 1 \~:] 15
SECTION6 6.0 DOCUMENT CROSS REFERENCE 6.1 For maintenance information regarding the auxiliary hydraulic system, refer to Rotorcraft Maintenance Manual Supplement No. KATI-MM-631. 6.2 For installation details and information, refer to Installation Manual No. KATI-Thi-631. NOV 3 0 FAA Approved: Revised: November I 0, 2006 16