What it approves
Installation of an Allison 250-C30M engine, an engine scavenge oil filter, a redesignated exhaust stack (RMH configuration) and engine cowling(carbon fiber), an option of deleting an auxiliary oil cooler (P/N 20006A), and a relocation of the engine ignition exciter box on the engine compartment deck.
What the certificate says
From the PDF’s text layer, without the form’s printed wording. Layout and order may differ; the PDF is the record.
United States of America Department of Transportation_Federal Aviation Administration Supplemental Type Certificate Number SH3324NM This certificate, issued to Soloy, LLC 450 Pat Kennedy Way, SW Oly mpia, WA 98501 Part 27 of the Federal Aviation Regulations.
Original Product⎯Type Certificate Number: H9EU Make: Eurocopter-Aerospatiale Model: AS-350B, AS-350D, AS-350BA
Description of the Type Design Change: Installation of a Rolls Royce (formerly Allison) 250-C30M engine in accordance with Soloy Master Drawing List 350-100, dated December 21, 2000, FAA approved January 30, 2001, or later FAA approved revision.
Limitations and Conditions: Approval of this change in type design applies to the above model rotorcraft only. This approval should not be extended to other rotorcraft of these models on which other previously approved modifications are incorporated unless it is determined that the relationship between this change and any of those other previously approved modifications, including changes in type design, will introduce no adverse effect upon the airworthiness of that rotorcraft. A copy of this Certificate and FAA approved Rotorcraft Flight Manual AS-350BA, dated March 11, 1992 and Rotorcraft Flight Manual Supplements No. 9, Second Edition, approved January 30, 2001, or No. 350FMS-035, Second Edition, approved January 30, 2001, or later FAA approved revisions must be maintained as part of the permanent records for the modified rotorcraft.
(See Continuation Pages 3 and 4)
If the holder agrees to permit another person to use this certificate to alter the product, the holder shall give the other person written evidence of that permission.
Date of application: June 13, 1984 Date reissued: 7/6/90; 3/16/95; 12/15/99; 11/10/04
Date of issuance: February 6, 1986 Date amended: 2/12/90; 5/3/91; 2/20/92;
1/30/01; 4/18/01, 11/15/02, 11/10/04
(Signature) Acting Manager, Seattle Aircraft Certification Office (Title)
United States of America Department of Transportation_Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number SH3324NM Soloy Corporation Reissued: 7/06/90; 3/16/95; 12/15/99; 11/10/04 Amended: 2/12/90; 5/3/91; 2/20/92; 1/30/01; 4/18/01; 11/15/02, 11/10/04
Limitations and Conditions: (Cont’d) Certain limitations and conditions shown on Type Certificate Data Sheet No. H9EU for Models AS-350B, AS-350D and AS-350BA remain applicable. The following list contains those limitations and conditions which have been modified, and certain unmodified ones which are listed for clarity.
Model: AS-350B, AS-350D, and AS-350BA as modified by this STC (normal category rotorcraft)
Engine: Allison Model 250-C30M
Engine Limits: Power Ratings (Sea Level, ISA)
Take off 650 s.h.p.
Max. Continuous 600 s.h.p.
Gas Generator Speed, N1 (100% = 51,000 RPM)
Max. Overspeed (10 Seconds) 54,060 RPM (106%) Max. Continuous 53,550 RPM (105%)
Power Turbine Speed, N2
Max. Overspeed (15 seconds) Varies linearly from 119% at flight autorotation to 109% at takeoff power.
Max. Continuous Varies linearly from 114% at flight autorotation to 107.1% at takeoff power.
Exhaust Gas Temperatures
Takeoff 1414 °F (768°C) Max. Continuous 1320 °F (716°C) Max. Transient 1414 °F to 1600°F (768°C to 871°C) not to exceed 12 seconds Max. Starting 1414° F to 1700°F (768°C to 927°C) not to exceed 10 seconds
For AS350B and AS350D Rotorcraft:
Transmission Maximum Takeoff Power Torque = 100% (531 s.h.p.)
Limits: Maximum Continuous Torque = 100% (531 s.h.p.)
Helicopter Maximum Takeoff Power Torque = 100% (531 s.h.p.)
Limits: Maximum Continuous Torque = 100% (531 s.h.p.)
For AS-350B, AS-350D, or AS-350BA Rotorcraft with BA performance:
Transmission Maximum Takeoff Power < 40 Kt Torque = 106% (564 s.h.p.)
Limits: Maximum Continuous Power > 40 Kt Torque = 100% (531 s.h.p.)
FAA FORM 8110-2- 1 (10-69) PAGE 3 OF 4 PAGES
United States of America Department of Transportation_Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number SH3324NM Soloy Corporation Reissued: 7/06/90; 3/16/95; 12/15/99; 11/10/04 Amended: 2/12/90; 5/3/91; 2/20/92; 1/30/01; 4/18/01; 11/15/02, 11/10/04
Limitations and Conditions: (Cont’d)
For AS-350B, AS-350D, or AS-350BA Rotorcraft with BA performance:
Helicopter Maximum Takeoff Power < 40 Kt Torque = 106% (564 s.h.p.)
Limits: Maximum Continuous > 40 Kt Torque = 100% (531 s.h.p.)
Fuel: Normal Fuels
MIL-T-5624, JP-4, or JP-5 ASTM-D-1655, Jet A, A1, or B JP-1 conforming to ASTM-D-1655, Jet A or A1 MIL-T-83133, grade JP-8
Emergency Fuels
MIL-G-5572C (aviation gasoline), any grade, is permitted for a maximum of 6 hours per turbine overhaul period. MIL-G-5572C fuel containing TRICRESYLPHOSPHATE (TCP) shall not be used. See Rotorcraft Flight Manual Supplement for operation procedures (Fuel Specifications).
Lubricating Oil: MIL-L-7808G and subsequent Revision OR MIL-L-23699.
Certification Basis: FAR 21.29 and FAR 27, effective February 1, 1965, plus amendments 27-1 through 27-10, plus FAA Special Conditions No. 27-79-EU-23, dated August 31, 1977.
Equipment: The basic required equipment as prescribed in the applicable airworthiness regulations (See Certification Basis) must be installed in the helicopter for certifications.
NOTE 1: Information essential to the proper maintenance of the helicopter is contained in the manufacturer’s maintenance manual provided with each helicopter. Life limited components and associated retirement times are presented in the manuals and components must be replaced in accordance therewith.
NOTE 2: FAA approved Rotorcraft Flight Manual Supplement No. 9, Second Edition, approved January 30, 2001, or later FAA approved revision required for AS-350D or B rotorcraft modified without the incorporation of the AS-350BA performance.
NOTE 3 FAA approved Rotorcraft Flight Manual AS- 350BA, dated March 11, 1992, and Rotorcraft Flight Manual Supplement No. 350FMS-035, Second Edition, approved January 30, 2001, or later FAA approved revision required for AS-350D, or B rotorcraft modified with the incorporation of AS-350BA performance and the AS-350BA rotorcraft.
NOTE : The rotorcraft must be maintained in accordance with the AS-350BA Master Service Recommendations (MSR) and Airworthiness Limitations.
- END -
FAA FORM 8110-2- 1 (10-69) PAGE 4 OF 4 PAGES
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