TCDS H10WE

Page No. 1 2 3 4 5 6 7 Rev. No. 18 16 16 18 18 17 18 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION H10WE REVISION 18 ROBINSON R22 R22 ALPHA R22 BETA R22 MARINER April 03, 2024 TYPE CERTIFICATE DATA SHEET NO. H10WE This data sheet, which is a part of Type Certificate No. H10WE, prescribes conditions and limitations under which the product for which the type certificate was issued meets the airworthiness requirements of Title 14 of the Code of Federal Regulations. Type Certificate Holder: Robinson Helicopter Company 2901 Airport Drive Torrance, California 90505 I. Model R22 Helicopter (Normal Category), Approved March 16, 1979 Engine Lycoming O-320-A2B or O-320-A2C or O-320-B2C (See NOTES 5 & 6) Fuel See Rotorcraft Flight Manual (RFM) Engine Limits for all operations 124 hp at 2652 rpm (104%) See RFM for manifold pressure limit corresponding to 124 hp and ambient conditions. Rotor Limits Power Off (Rotor Tach) Power On (Rotor Tach) Maximum (110%) 561 rpm (104%) 530 rpm Minimum (90%) 459 rpm (97%) 495 rpm Airspeed Limits (CAS) 98 KCAS Power On and Off VNE (never exceed) at sea level. See RFM for reduction of VNE with altitude and temperature. Altitude Limits Density Altitude Limit - 14,000 feet CG Range See RFM Maximum Gross Weight 1300 lbs. No. Seats 2 (See NOTE 1) Minimum Weight 920 lbs. Maximum Baggage 50 pounds of baggage and installed equipment in either baggage compartment, except combined seat load plus baggage and equipment not to exceed 240 pounds. H10WE Page 2 of 7 I. Model R22 Helicopter (Normal Category), Approved March 16, 1979, (cont'd) Fuel Capacity Tank Tanks Without Bladders Tanks With Bladders Location (STA) Capacity (gal.) Usable (gal.) Capacity (gal.) Usable (gal.) Main 19.8 19.2 18.3 16.9 108.6 Auxiliary N/A N/A 9.7 9.4 103.8 Oil Capacity Engine Oil, 6 qt. at STA 104.8; Transmission oil, 1.2 qt. at STA 100. Rotor Blade and Control Movements For rigging information refer to R22 Maintenance Manual Serial Nos. Eligible 0002 thru 0300 0302 thru 0349 0352 thru 0356 II. Model R22 ALPHA Helicopter (Normal Category), Approved October 12, 1983 Engine Lycoming O-320-B2C Fuel See RFM Engine Limits for all operations 124 hp at 2652 rpm (104%) See RFM for manifold pressure limit corresponding to 124 hp and ambient conditions. Rotor Limits Power Off (Rotor Tach) Power On (Rotor Tach) Maximum (110%) 561 rpm (104%) 530 rpm Minimum (90%) 459 rpm (97%) 495 rpm Airspeed Limits 98 KCAS Power On and Off VNE (never exceed) at sea level. See RFM for reduction of VNE with altitude and temperature. Altitude Limits Density Altitude Limit - 14,000 feet CG Range See RFM Maximum Gross Weight 1370 lbs. No. Seats 2 (Pilot Location STA 78.0) Minimum Weight 920 lbs. Maximum Baggage 50 pounds of baggage and installed equipment in either baggage compartment, except combined seat load plus baggage and equipment not to exceed 240 pounds. Fuel Capacity Tank Tanks Without Bladders Tanks With Bladders Location (STA) Capacity (gal.) Usable (gal.) Capacity (gal.) Usable (gal.) Main 19.8 19.2 18.3 16.9 108.6 Auxiliary 10.9 10.5 9.7 9.4 103.8 Oil Capacity Engine oil, 6 qt. at STA 104.8; Transmission oil, 1.2 qt. at STA 100. Rotor Blade and Control Movements For rigging information refer to R22 Maintenance Manual. Serial Nos. Eligible 0301, 0350, 0351, 0357 thru 0500, excluding 0364 H10WE Page 3 of 7 III. Model R22 BETA Helicopter (Normal Category), Approved August 12, 1985 The R22 BETA Helicopter includes a 131 hp. takeoff rating. A larger oil cooler and associated installation changes were made to permit the 131 hp. takeoff rating with the O-320 engine. Engine Lycoming O-320-B2C or O-360-J2A (See NOTE 11) Fuel See RFM Engine Limits for all operations Maximum continuous: 124 hp at 2652 rpm (104%) Takeoff (5 minutes): 131 hp at 2652 rpm (104%) See RFM for manifold pressure limit corresponding to hp. rating and ambient conditions. Rotor Limits Power Off (Rotor Tach) for O-320-B2C and O-360-J2A Power On (Rotor Tach) for O-320-B2C Power On (Rotor Tach) for O-360-J2A Maximum (110%) 561 rpm (104%) 530 rpm (104%) 530 rpm Minimum (90%) 459 rpm (97%) 495 rpm (101%) 515 rpm Airspeed Limits (CAS) 98 KCAS Power On and Off VNE (never exceed) at sea level. See RFM for reduction of VNE with altitude and temperature. Altitude Limits Density Altitude Limit - 14,000 feet CG Range See RFM Maximum Gross Weight 1370 lbs. No. Seats 2 (Pilot Location STA 78.0) Minimum Weight 920 lbs. Maximum Baggage 50 pounds of baggage and installed equipment in either baggage compartment, except combined seat load plus baggage and equipment not to exceed 240 pounds. Fuel Capacity Tank Tanks Without Bladders Tanks With Bladders Location (STA) Capacity (gal.) Usable (gal.) Capacity (gal.) Usable (gal.) Main 19.8 19.2 18.3 16.9 108.6 Auxiliary 10.9 10.5 9.7 9.4 103.8 Oil Capacity Engine oil, 6 qt. at STA 104.8; Transmission oil, 1.2 qt. at STA 100. Rotor Blade and Control Movements For rigging information refer to R22 Maintenance Manual. Serial Nos. Eligible 0501 and subsequent H10WE Page 4 of 7 IV. Model R22 MARINER Helicopter (Normal Category), Approved September 12, 1985 The R22 MARINER helicopter includes two inflatable floats, additional corrosion protection, 131 hp. takeoff rating, tailcone with nose-up horizontal stabilizer mounting angle and float stabilizer in place of the tail skid. The helicopter can be used with or without floats. See NOTE 9 for R22 MARINER-specific limitations. Engine Lycoming O-320-B2C or O-360-J2A (See NOTE 11) Fuel See RFM Engine Limits for all operations Maximum continuous: 124 hp at 2652 rpm (104%) Takeoff (5 minutes): 131 hp at 2652 rpm (104%) See RFM for manifold pressure limit corresponding to hp. rating and ambient conditions. Rotor Limits Power Off (Rotor Tach) for O-320-B2C and O-360-J2A Power On (Rotor Tach) for O-320-B2C Power On (Rotor Tach) for O-360-J2A Maximum (110%) 561 rpm (104%) 530 rpm (104%) 530 rpm Minimum (90%) 459 rpm (97%) 495 rpm (101%) 515 rpm Airspeed Limits (CAS) With Floats Installed 91 KCAS Power On VNE (never exceed) at sea level. 77 KCAS Power Off VNE (never exceed) at sea level. See RFM for reduction of VNE with altitude and temperature. Without Floats Installed 98 KCAS Power On and Off VNE (never exceed) at sea level. See RFM for reduction of VNE with altitude and temperature. Altitude Limits Density Altitude Limit - 14,000 feet CG Range See RFM Maximum Gross Weight 1370 pounds No. Seats 2 (Pilot Location STA 78.0) Minimum Weight 920 pounds Maximum Baggage 50 po unds of baggage and installed equipment in either baggage compartment, except combined seat load, plus baggage and equipment not to exceed 240 pounds. Fuel Capacity Tank Tanks Without Bladders Tanks With Bladders Location (STA) Capacity (gal.) Usable (gal.) Capacity (gal.) Usable (gal.) Main 19.8 19.2 18.3 16.9 108.6 Auxiliary 10.9 10.5 9.7 9.4 103.8 Oil Capacity Engine oil, 6 qt. at STA 104.8; Transmission oil, 1.2 qt. at STA 100. Rotor Blade and For rigging information refer to R22 Maintenance Manual. Control Movements Serial No. Eligible 0364, 0501 and subsequent (Suffix "M" added to all MARINERs.) H10WE Page 5 of 7 DATA PERTINENT TO ALL MODELS Datum 100 inches forward of main rotor centerline. Leveling Means Refer to the Weight and Balance Section of the R22 Rotorcraft Flight Manual. Certification Basis 14 CFR Part 27 dated February 1, 1965, including Amendments 27-1 through 27-10. § 27.1559 of Amendment 27-21 is an option for all S/Ns. For S/N 4815 and subsequent: 14 CFR §§ 27.952(a), 27.952(c), 27.952(f), 27.952(g), 27.963(g) (except with a minimum puncture force of 250 pounds), and 27.975(b) as amended by Amendment 27-30 (see Note 13). For helicopters with B375-2 Symmetric Horizontal Stabilizer Installed: 14 CFR Part 36, dated December 1, 19 69, Amendment 36 -1 through 36 -31, Appendix J. National Environmental Act of 1969 Noise Control Act of 1972 Equivalent Safety Finding: Number TD10352LA-R/S-1 14 CFR Part 27.1401(d), Anticollision Light System For S/N 4815 and subsequent: Number AT17316LA-R/P-1 14 CFR Part 27.952(c)(1)(i) Breakaway coupling separation load (see Note 13) The certification basis for areas changed or affected by B375-2 Symmetric Horizontal Stabilizer Installation includes the following later amendments: 14 CFR § 27.1323 at Amendment 27-13 14 CFR § 27.613, 27.629, and 27.663 at Amendment 27-26 14 CFR § 27.427 at Amendment 27-27 14 CFR § 27.351 and 27.391 at Amendment 27-34 14 CFR § 27.49, 27.71, and 27.75 at Amendment 27-44 14 CFR § 27.610 at Amendment 27-46 Production Basis Production Certificate No. 424WE, dated March 6, 1981 Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (See Certification Basis) must b e installed in the heli copter for certification. In addition, the following FAA-approved Rotorcraft Flight Manual is required: R22 R22 Rotorcraft Flight Manual dated March 16, 1979, or later revision. R22 ALPHA R22 Rotorcraft Flight Manual dated March 16, 1979, with revisions through October 12, 1983 or later (see NOTE 8). R22 BETA with O-320-B2C R22 Rotorcraft Flight Manual dated March 16, 1979, with revisions through August 7, 1985 or later (see NOTE 8). R22 BETA with O-360-J2A R22 Rotorcraft Flight Manual dated March 16, 1979,with revisions through August 7, 1985 or later. For R22 Rotorcraft Flight Manual with revisions prior to October H10WE Page 6 of 7 13, 2000, Flight Manual Supplement 7 dated January 31, 1996, or later revision, is required (see NOTE 8). R22 MARINER with O-320-B2C R22 Rotorcraft Flight Manual dated March 16, 1979, with revisions through August 7, 1985 or later, and Flight Manual Supplement 4 dated September 9, 1985, or later revision. R22 MARINER with O-360-J2A R22 Rotorcraft Flight Manual dated March 16, 1979, with revisions through August 7, 1985 or later, and Flight Manual Supplement 4 dated September 9, 1985, with revisions through October 13, 2000 or later. For R22 Rotorcraft Flight Manual with revisions prior to October 13, 2000, Flight Manual Supplement 8 dated January 31, 1996, or later revision, is required in place of Flight Manual Supplement 4. ALL MODELS If fuel tanks with bladders are installed: R22 Rotorcraft Flight Manual dated March 16, 1979, with revisions through February 15, 2013 or later. R22 Mariners also require Flight Manual Supplement 4 as noted above. Also see Note 8. GENERAL NOTES NOTE 1. Current weight and balance report, including list of equipment included in certificated empty weight , and loading instructions, when necessary, must be provided for each helicopter at the time of original certification and at all times thereafter (except in the case of operators having an approved weight control system). Pilot Location STA 79.0 for helicopter S/Ns 0002 thru 0 255 and STA 78.0 for helicopter S/Ns 0256 and subsequent and helicopters in which Robinson P/N se ats A466-1 and A467 -1 have been replaced by Robinson P/N seats A932-1 and A928-1. NOTE 2. One of the following placards must be installed in clear view of the pilot: "THE MARKINGS AND PLACARDS INSTALLED ON THIS HELICOPTER CONTAIN OPERATING LIMITATIONS WHICH MUST BE COMPLIED WITH WHEN OPERATING THIS ROTORCRAFT. OTHER OPERATING LIMITATIONS WHICH MUST BE COMPLIED WITH WHEN OPERATING THIS ROTORCRAFT ARE CONTAINED IN THE ROTORCRAFT FLIGHT MANUAL." Or: "THIS ROTORCRAFT APPROVED FOR DAY AND NIGHT VFR OPERATIONS" For the R22 MARINER: "THIS ROTORCRAFT APPROVED FOR DAY AND NIGHT VFR OPERATIONS WITHOUT FLOATS INSTALLED OR DAY VFR OPERATIONS ONLY WITH FLOATS INSTALLED." For additional placards, see R22 Rotorcraft Flight Manual. NOTE 3. Information e ssential to the proper maintenance of the helicopter, including retirement time of critical components, is contained in the Robinson R22 Maintenance Manual and Instructions For Continued Airworthiness (RTR 060). Retirement times are listed in the "AIRWORTHINESS LIMITATIONS" section. NOTE 4. Deleted as of April 11, 1988. NOTE 5. Lycoming O-320-A2C, with Retard Magneto Starting System, eligible on S/Ns 0002 thru 0300, 0302 thru 0349, and 0352 thru 0356 helicopters. NOTE 6. Lycoming O-320-B2C installed o n S/Ns 0175 and 0200 thru 2570 in production. It may be installed in prior S/N helicopters if the following parts are changed; Robinson P/Ns B193 -2 (Window Plate - Instrument Cluster), A145-3 (Engine), A600-2 (Manifold Pressure Gauge), and A654-40 & -41 (Decals). NOTE 7. Deleted as of April 25, 2001. NOTE 8. The R22 "Police Helicopter" configuration requires Flight Manual Supplement 3, dated March 27, 1984 or later. H10WE Page 7 of 7 NOTE 9. The R22 MARINER with floats installed is limited to daylight VFR operation only. The B375-2 Horizontal Stabilizer is not eligible for installation on the R22 MARINER with floats. NOTE 10. R22 ALPHA S/N 0364 was converted to an R22 MARINER by the manufacturer. The original R22 ALPHA dataplate was removed and replaced with an R22 MARINER data plate S/N 0364M. NOTE 11. Lycoming O-360-J2A installed on S/N 2571 and subsequent in production. Retrofit installation of the O-360-J2A engines may only be accomplished at the Robinson Helicopter Company factory. NOTE 12. Deleted as of May 24, 2018. NOTE 13. To operate in U.S. airspace, the following helicopter serial numbers must meet the crash resistant fuel system certification basis requirements per section 44737 of Title 49 U.S.C.: Model R22 BETA, S/N 4815 and subsequent. .....END.....