TCDS H12EU

Page No. 1 2 3 4 5 6 7 8 9 10 Rev. No. 7 7 7 7 7 7 7 7 7 7 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION H12EU Revision 7 WESTLAND 30 Series 100 Series 100-60 July 11, 2000 NOTE 13. This type certificate is canceled effective July 11, 2000 and is not valid for aircraft manufactured after this date. This cancellation also invalidates, and precludes issuance of, any U.S. Certificates of Airwothiness TYPE CERTIFICATE DATA SHEET No. H12EU This data sheet which is part of Type Certificate No. H12EU prescribes conditions and limitations under which the product for which the Type Certificate was issued meets the airworthiness requirements of the Federal Aviation Regulations. Type Certificate Holder Westland Helicopters Limited Yeovil, Somerset England I. Model Westland 30 series 100 (Transport Helicopter, Category A and B), Approved December 1, 1982. (See NOTE 5) Engine Two Rolls Royce LTD GEM Mk 510 free turbine engines. Fuel Refer to Westland 30 Flight Manual for approved fuels and additive specifications. Installed Engine Limits (See NOTE 8) Output Shaft Output Shaft Gas Horsepower RPM Generator Turbine (Torque) Maximum RPM Inlet Normal Operation Take off ( 5 min.) 938 per engine 6287 44,000 660 (115%, 784 ft-lb) Maximum Continuous 938 per engine 6287 43,400 635 (115%, 784 ft-lb) One Engine Inoperative 2 1/2 Min Power 1131 6226 44,600 690 (140% 954 ft-lb) 30 Min Power 1039 6256 44,300 675 (128% 872 ft-lb) Maximum Continuous 938 6287 43,400 635 (See NOTE 9) 115% 784 ft-lb) Starting Momentary 720 Rotor Limits H12EU 2 Power Off Power On Maximum (Steady State) 355 (108.9%) 348 (106.8%) Maximum (Transient) 383 (117.5%) 359 (110.3%) Minimum (Steady State) 300 (92.0%) 316 (97.0%) Minimum (Transient) 250 (76.7%) 250 (76.7%) Airspeed Limits Never-exceed-speed 120 knots IAS at sea level, and 12,350 lbs gross weight. See Helicopter Flight Manual for speed limit decrease with weight and altitude. H12EU C.G. Range Longitudinal: ROTOR CL INCHES FORWARD OF ROTOR INCHES AFT OF ROTOR 12350 1b AUW 11000 10000 9000 8000 8.0 Minimum Operating Weight 7800 1b ADW 7000 FORWARDIC. G. LIMIT AFT C.G. LIMIT 3.5 in UP TO 11000 lb 6.5 in UP TO 9750 lb THEN REDUCING THEN REDUCING LINEARLY TO 2.75 in LINEARLY TO AT 12350 1b 4.25 in AT 12350 lb Lateral Lateral C.G. positions for all normally attainable loading are cleared. Empty Weight C.G. Range See Rotorcraft Flight Manual. Datum Rotor center line. Leveling Means Three plates on the left side of transmission support platform. Maximum Weight 12,350 lb. Minimum Crew 1 pilot, VER; 2 pilots IFR (See NOTE 5). Maximum Passengers 19 Maximum Baggage See Rotorcraft Flight Manual. Fuel Capacity Forward Tank Aft Tank Maximum 175.7 (-81.7) 175.6 (62.3) Usable 171.6 (-81.7) 173.7 (62.3) Residual 1.2 (-81.7) 1.2 (54.0) H12EU 4 Unusable 2.9 (-81.7) 0.7 (54.0) 5 H12EU Oil Capacity US gals (moment arm in.) Engine 2x1.2 (34.5) Main gearbox 6.7 (14.0) Intermediate gearbox 0.2 (196.0) Tail rotor gearbox 0.3 (317.7) Maximum Operating Altitude See Rotorcraft Flight Manual. Rotor Blades and Control For rigging information, refer to the Maintenance Manual. Movements II. Model Westland 30 series 100-60 (Transport Helicopter, Category A and B), Mod ZY 688 (See NOTE 5), Approved August 27, 1984 Engine Two Rolls Royce Ltd GEM Mk 530 (FAA Type Certificate Ref. # E19NE) Fuel Refer to Westland 30 Flight Manual for approved fuels and additive specifications. Installed Engine Limits (See NOTE 8) Output Shaft Output Shaft Gas Horsepower RPM Generator Turbine (Torque) Maximum RPM Inlet Normal Operation Take off (5 min.) 947 per engine 6348 35,980 686 (94%, 784 ft-lb) Maximum Continuous 947 per engine 6348 35,650 680 (94%, 784 ft-lb) One Engine Inoperative 2 1/2 Min Power 1142 6287 36,800 708 (114% 954 ft-lb) 30 Min Power 1047 6306 35,980 686 (104.5% 872 ft-lb) Maximum Continuous 947 6348 35,650 680 (See NOTE 9) (94% 784 ft-lb) Starting Momentary 720 Rotor Limits Power Off Power On Maximum (Steady State) 355 (108.9%) 336 (103%) Maximum (Transient) 383 (117.5%) 359 (110%) Minimum (Steady State) 300 (92.0%) 319 (98.0%) Minimum (Transient) 250 (77%) 250 (77%) Airspeed limits Never-exceed-speed 120 knots IAS at sea level, and 12,350 lbs gross weight. See KTS IAS Helicopter Flight Manual for speed limit decrease with weight and altitude. H12EU C.G. Range Longitudinal: INCHES FORWARD OF ROTORC ROTOR CL INCHES AFT OF ROTOR 4 - 2.75 12350 1b AUW → 4.25 12000 11000 10000 10000 8000 - → - . Minimum Operating Weight 7800 1b ADW 7000 FORWARD CG LIMIT AFT CG LIMIT 3.5 in UP TO 11000 1b 6.5 in UP TO 9750 1b THEN REDUCING THEN REDUCING LINEARLY TO 2.75 in LINEARLY TO AT 12350 lb 4.75 in AT 12350 1b Lateral Lateral C.G. positions for all normally attainable loadings are cleared. Empty Weight C.G. Range See Rotorcraft Flight Manual. Datum Rotor center line. Leveling Means Three plates on the left side of transmission support platform. Maximum Weight 12,350 1b. Minimum Crew 1 pilot, VFR; 2 pilots IFR (See NOTE 5). Maximum Passengers 19 Maximum Baggage See Rotorcraft Flight Manual. Fuel Capacity US Gals (moment arm in.) Fuel to ASTM D1655: Forward Tank Aft Tank Maximum 175.7 (-81.7) 175.6 (62.3) Usable 171.6 (-81.7) 173.7 (62.3) Residual 1.2 (-81.7) 1.2 (54.0) Unusable 2.9 (-81.7) 0.7 (54.0) 7 H12EU Oil Capacity US gals (moment arm in.) Engine 2x1.2 (34.5) Main gearbox 6.7 (14.0) Intermediate gearbox 0.2 (258.3) Tail rotor gearbox 0.3 (317.7) Maximum Operating Altitude See Rotorcraft Flight Manual Rotor Blades and Control For rigging information, refer to the Maintenance Manual. Movements III. Model Westland 30 Series 100-60 (Transport Helicopter, Category A & B), Mod. ZY 689, Approved December 6, 1985. Engine Two Rolls Royce Gem Mk. 530 (FAA Type Certificate Ref. E19NE) Fuel Refer to Westland 30 Flight Manual for approved fuels and additive specification. Installed Engine Limits (See NOTE 8) Output Shaft Output Shaft Gas Horsepower RPM Generator Turbine (Torque) Maximum RPM Inlet Normal Operation Take off (5 min.) 1009 per engine 6349 36,180 686 (100%, 835 ft-lb) Maximum Continuous 1009 per engine 6349 35,850 680 (100%, 835 ft-lb) One Engine Inoperative 2 1/2 Min Power 1383 6349 37,800 708 (137% 1144 ft-lb) 30 Min Power 1276 6349 36,180 686 (126.5% 1056 ft-lb) Maximum Continuous 1276 6349 35,850 680 (See NOTE 9) (126.5% 1056 ft-lb) Starting Momentary 720 Rotor Limits Power Off Power On Maximum (Steady State) 355 (108.9%) 336 (103%) Maximum (Transient) 383 (117.5%) 359 (110%) Minimum (Steady State) 300 (92.0%) 319 (98%) Minimum (Transient) 250 (77%) 250 (77%) H12EU C.G. Range Longitudinal: INCHES FORWARD OF ROTOR ROTOR CL - 2.5 p 12800 lb AUW lb 12000 111000 10000 9000 18000 8.0 - -- _. _ 1---1---+--1 Minimum Operating Weight 7800 1b ADW 17000 FORWARD CG LIMIT AFT CG LIMIT 6.5 in -3.5 in UP TO 11000 lb UP TO 9750 1b THEN THEN REDUCING REDUCING LINEARLY LINEARLY TO -2.75 in TO 3.9 in AT AT 12800 LB 12800 lb Empty Weight C.G. Range See Rotorcraft flight Manual Datum Rotor center line Leveling Means Three plates on the left side of transmission support platform. Maximum Weight 12800 1b. Minimum Crew 2 pilots Maximum Baggage 19 Fuel Capacity US gals (moment arm in.) Fuel to ASTM D1655: Forward Tank Maximum 175.7 (-81.7) 175.6 (62.3) Usable 171.6 (-81.7) 173.7 (62.3) Residual 1.2 (-81.7) 1.2 (54.0) Unusable 2.9 (-81.7) 0.7 (54.0) 9 H12EU Oil Capacity US gals (moment arm in.) Engine 2x1.2 (34.5) Main gearbox 6.7 (14.0) Intermediate gearbox 0.2 (258.3) Tail rotor gearbox 0.3 (317.7) Maximum Operating Altitude See Rotorcraft Flight Manual Rotor Blades and control For rigging information, refer to the Maintenance Manual Movements Certification Basis FAR 21.29 and FAR 29 effective February 1, 1965 plus Amendments 29-1 through 29-14 and para. 29.1353 (c) of Amendment 29-15. In addition, applicant elected to comply with FAR 29 amendments 29-15 through 29-20 except for FAR 29.1529 as concerns Appendix A A29.4. The Airworthiness criteria for Instrument Flight dated December 15, 1978 for IFR Certification. Ditching approval in accordance with FAR 29.801 except FAR 29.1415 requirement. Equivalent safety findings: see NOTE 4. Type Certificate No. H12EU issued December 1,1982. Date of Application for Type Certificate : January 20, 1978. Serial Nos. Eligible See Import Requirements. Import Requirements A U.S. Standard Airworthiness Certificate may be issued on the basis of a United Kingdom Certificate of Airworthiness for Export signed by a representative of the United Kingdom Civil Aviation Authority containing the following statement: - "The Helicopter covered by this Certificate has been examined, tested and found to conform to the type design approved under Type Certificate No. H12EU, and to be in a condition for safe operation." Caution: The United Kingdom Civil Aviation Authority notified the FAA that the Service Difficulty information on the W30 helicopter may be out of date. For the latest information on service difficulties prior to certifying a W30, please contact the Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas, 76193, telephone (817 )222-5111, Fax (817)222-5961. Service Information "Service bulletins, structural repair manuals, aircraft flight manuals, and overhaul and maintenance manuals, which contain a statement that the document is CAA of the U.K. and Northern Ireland approved, are accepted by the FAA and are considered FAA approved. These approvals pertain to the type design only." Equipment The basis required equipment as prescribed in the applicable airworthiness regulations (See Certification Basis) must be installed in the helicopter for certification. Westland Report No. WER141-30-00497 lists required and optional equipment for the helicopter. In addition, the following item of equipment is required: H12EU 10 United Kingdom CAA - approved Rotorcraft Flight Manuals: Series 100 RFM ref. WD6.2, approved December 1, 1982 Series 100-60 RFM ref. WD6.4, approved August 27, 1984 (12,350 lbs maximum AUW weight) Series 100-60 RFM ref. WD6.6, Revision No. 2, approved December 6, 1985 (12,800 lbs maximum AUW weight) 11 H12EU There may be approved rotorcraft Flight Manual (RFM) amendments or supplements issued after the original type certificate, that are required to operate the helicopter when additional equipment is installed and/or when certain modifications are embodied. The helicopter owner/operator should ensure that the correct approved rotorcraft Flight Manual (RFM) amendments or supplements are incorporated in the ap proved RFM, for the approved model. NOTES NOTE 1. Current weight and balance report including loading instructions and list of equipment included in the certificated empty weight, must be provided for each helicopter at the time of original certification. When changes are made to the helicopter which affect the weight and balance, refer to the Flight Manual Weight and Balance Appendix for instructions. NOTE 2. All placards indicated in the Rotorcraft Flight Manual must be installed in the appropriate location. NOTE 3. Information essential to the proper maintenance of the helicopter is contained in the Manufacturer's Westland 30 Series 100 and 100-60 Maintenance Manual provided with each helicopter. Life-limited components and associated retirement times are presented in Chapter 05, Section 05-10-00 Table 2 of the Maintenance Manual, and must be replaced in accordance therewith. For Rolls-Royce engines the life limited parts and accountability methods are identified in Rolls-Royce Gem Engine Service Bulletin Numbers 6000 for Gem Mk.510 and 72-1 for MK.530. The instructions for continued airworthiness, "Airworthiness Limitation" are presented in chapter 05, section 05 - 10 - 00 table 5 of the Maintenance Manual must be complied with and may not be changed without FAA-approval. NOTE 4. 30 Series 100 30 Series 100-60 Equivalent Safety Findings: FAR 29.903(b) Speed Select Control Speed Select Control (Mechanical Link) (Ganged Potentiometer) FAR 29.921 & 29.1151 Rotor Brake Warning Rotor Brake Warning FAR 29.1305(b)2 Fuel Pressure Indicator Fuel Pressure Indicator FAR 29.991(b) Fuel System Pumps Fuel System Pumps FAR 29.923 Rotor drive System Test-Post Mod. ZY 689 NOTE 5. The Westland 30 Series 100 and Series 100-60 are eligible for IFR 2 pilot operation when Westland Modification ZY 505 is incorporated. H12EU 12 NOTE 6. The Gem Mk. 510 engine control is of the proportional governing type which necessitates accurate and consistent control rigging; refer to the Maintenance Manual for instructions. Figure 1 presents the limits for rotor speed (power turbine speed) vs torque. NOTE 7. The paint scheme for the Tail Rotor Blades is given in Drawing WK 3039-0102, maintenance instructions for them are contained in Chapter 64-10 of the Maintenance Manual. NOTE 8. Engine Definitions - The output shaft speed and torque (percent) for each rating, are based on the maximum speed select limit as shown on page 1 for the Gem Mk. 510 engine and page 3 and 5 for the Gem. Mk. 530 engines. For computation purposes the following definitions have been established: Engine Type Torque Power Turbine Speed lb.ft R.P.M. Gem Mk. 510 100 681.5 100 6164 Gem Mk. 530 100 835 100 6164 NOTE 9. For Series 100 and 100-60 (MOD ZY688 Standard) rotorcraft at 12,350 lb. maximum all up weight, this emergency rating can be used for single engine demonstration/training purposes. For series 100-60 (MOD ZY689 Standard) rotorcraft at 12,800 lb. maximum all up weight, the weight and transmission torque limits specified in Revision No. 3 to R.F.M. WD6.6 shall be used for single engine training. NOTE 10. For Series 100-60 no dispatch deficiencies are permitted in the Engine Electronic Control (EEC) system. System includes 2 DC generators, 1 battery and EEC units for each engine. 13 H12EU NOTE 11. Westland 30 Series 100 and Series 100-60 rotorcraft may be equipped with a CAA-UK approved Electronic Flight Instrument System (E.F.I.S.) in accordance with Westland Helicopters Modification KX.400 and a CAA-UK approved Flight Manual Supplement No. 1 to W.D. 6.4. H12EU 14 NOTE 12. Westland 30 Series 100-60 (MOD ZY689 Standard) rotorcraft are eligible for operations with AFCS Part No. NDN 8919-02 and CAA-UK approved Flight Manual Supplement No. 2 to R.F.M . WD6.6. NOTE 13. This type certificate is canceled effective July 11, 2000 and is not valid for aircraft manufactured after this date. This cancellation also invalidates, and precludes issuance of, any U.S. Certificates of Airwothiness ...END...