STC SH657NW

J.!llliteb ~httell Q)f Ci\mcricll JElcpartmcnt of 'illransportation - JIfcocraI J\biation J\oministration ~uppl£m£ntal COIrlP£QI£rtifirat£ ./!0//ufe,r< SH657NW yZ) 'CC;",'uj{;w/"i)Jlm//r< Siam Hiller Holdings, Inc.

925 M Street Firebaugh, California 93622 (,f'd,y1('" ad/-?r/tL/1Y'1'Vbd WN' rk"~/b /0/'d /'t:0It"V1Y'/Y'I.,dH/ IPi/£ d tt/bikLU~VId a/ld' cc',Itrdt'uYId //£,,,,r;4/, 1/" Yb('r,y1('//-?"w'/b//bf'(,?; d IZU'It"N,d;,Y'"" "'f'Y'IN/W/bf'/b?J#a/'/ * I/d /i!7tt,iI:.78,/- .'76~f7t/hkl'/ld I//tr/ .f}7;(.'f''''I;;/.AI'uduw.'76Ytth/uvld. * See page 6 of this STC for certification basis.

(j;'fYt;'bI,I~-N.lttr/ .~bI' '6c;"'Ufr-~d'"./P;;"It&",'..2H3 .J&N/',/ 47G-2A, 47G-2A-l, 47G-3B, 47G-3B-l, 47G-3B-2, 47G-3B-2A, 47G-4, 47G-4A, 47G-5, 47G-5A !!Yfr"C/;/butVb I;/~N' !!Yfr"fj//b Y?/t//1Y'I\' Installation of an Allison 250-CIOD (T63-A-700), 250-CISA, 250-CISC, 250-C20, or 250-C20B engine and related changes in accordance with Hiller Aircraft Corporation Master Drawing List 660-100 reissued on March 22, 1991, November 30, 1995, and January I, 1999, or later FAA approved reVISIOns; or Soloy Corporation Master Drawing List 660-100 dated August 1, 1979, or later FAA approved revisions. (See Note 9 of STC Addendum SH657NW).

2?thHH;;U{VW I//tr/ 'I/t'/tr/?U{',IId.' Approval of this change in type design applies basically to the above model rotorcraft only. This approval should not be extended to other rotorcraft of this model on which other previously approved modifications are incorporated unless it is determined that the interrelationship between this change and any of those other previously approved modifications will introduce no adverse effect upon the airworthiness of these rotorcraft. A copy of the STC and Addendum No. SH657NW must be included in the permanent records for the modified rotorcraft. 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 .

.~ rf''''?~/;;/(, Iml/ /-?Jt~YH'dv1Y' ddlZ. tP£«£tj /-?to<J.0/0/'I~YI",(,('I;;,f J/tdl'm'/HU;'b Vb#c.ft//U£ JIt'/'/WtrkL'f'I/. JttYINtrk/t! L'I't.'I,,,f!tW!I'L'a ?f'/'///,,;''''LUt'/bI,t/L?(,,j rl-?n.",jl' f'"kLtftiJ-?a! {Yd .Aa:;/b,/b.0k-t;;k'/' t/ d .9;/k,,'IZ/. AI'?~db{W .A/~/N;'b.0k'IZ.UtVb.

!!!/Ja/I'/'f'';;JIt'f'd 03/22/91; 11/30/95; 06/17/99;

08/19/05; 04/15/09; 5/15/09 September 7, 1978 !!iJ;d(,(L//bf'/trk£l! 09/15/78; 11/16/78; 01/03/79;

02/05/79; 04/10/79; 05/03/79; OS/28/79; 11128/79;

OS/20/80; 02/11/81; 03/09/81; 02/15/91; 03/22/91;

05/09/95; 08/07/95; 06/30/99 (Signalll f Supervisor, Tec ical & Administrative Support Staff, Los Angeles Aircraft Certification Office (Title) jlllY a{teratwll of tfiis certificate is punisfia6f'e6) afine of Tlote:(ceeaiTlg$1,000, or imprisonmeTltTlote:x:reemTlg3 years, or 60tfi.

FAA Form 8110-2 (10-68) 1 of 8 'lTiiscertificate may 6e transferredin accordaTlcewitfi 'F)l1J(21.47.

TRANSFER ENDORSEMENT Transfer the ownership of the Supplemental Type Certificate Number _ to (:Nameof transferee), _ (J1.ddressof transferJ _ (J'fum6eraM Jtreet) (City, State, aM Zip coac) from (:Nameofgrantor)(Pn'nt or type) _ (J1.ddressofgrantor) (J'fum6eraM Jtreet) (City, State, aM Zip coac) Extent of Authority (if licensing agreement): _ Date of Transfer: _ Signature of grantor (In int<.): _ Page 2 of 8

;UllitClI ~tlltC5 (J)f cAmcriClt JEl.epartm.ent of Wransportatinn - JIfcbcral cA.&iatinn J\bministratinn ~ufrplem£ntal 'QI~p£QI£rtifi.cat£ (QIontinuation ~~ed) .£/7b&~ SH657NW ADDENDUM The limitations and conditions of Type Certificate Data Sheet 2H3 apply except as follows:

This STC Addendum, which is part of Supplemental Type Certificate No. SH657NW, prescribes limitations and conditions under which the product for which the STC was issued meets the airworthiness requirements of the certification basis stated herein. A copy of this STC Addendum is required to be maintained as part of this modified rotorcraft permanent records.

SUPPLEMENTAL TYPE CERTIFICATE HOLDER: Siam Hiller Holdings, Inc.

Bell 47G Series as modified by this STC (normal category) Engine Fuel Oil Allison 250-CI0D (T63-A-700), 250-CI8A, 250-CI8C, 250-C20, 250- C20B MIL-T-5624 grade JP-4 or JP-5, aviation turbine fuels ASTM D1655 Jet A or A-I (or Allison spec. EMS) or Jet B. See FAA approved Rotorcraft Flight Manual for alternate cold weather and emergency fuels.

Engine MIL-L-7808G or MIL-L-23699B and subsequent revisions thereto.

Transmission MIL-L-6082 grade 100, 80, 60, or 40 (See RPM).

Engine Rating (5 minutes) With 600 series Transmission

260.6 H.P.

See Note 3 for applicable conditions.

With 900 series Transmission

270.0 H. P.

Engine Limits Gas producer (N]) Max. continuous Transient overspeed (15 seconds) 250-CI0D (T63-A-700) 250-C 18A/C 18C 104% (53,165 RPM) 105% (53,676 RPM) 250-C20/C20B 105% (53,518 RPM) 106% (54,028 RPM) }IllY a{teratwll of tfiis certificate ispUIlisfia6fe6y afille of Ilot eXIeeaillg $1,000, or imprisollmelltIlot eXIeeaillg3years, or 60tli.

FAA Form 8110-2 (10-68) 3 of 8 'I1iiscertificate may 6e traTlsferreaiTlaccoraaTlcewitfi 'F}l1J(21.47.

~lllilco ffi'lllics Q)f Ci\mcriCll glepartment of 'Qtransportatioll - JIfeoeral J\&iation J\oministration ~UfJplcmcntal '<.TI~pcQIcrtifiratc (QIontinuation ~lre£t) ./f0/?u1~]/<SH657NW Engine Limits Output shaft (N2) For all steady state conditions 100% 6000 RPM for 250-ClOD (T63-A-700), C250-C18A/C18C 6016 RPM for 250-C20/C20B) Transient overspeed (15 seconds) 250-C20D (T63-A-700), 250-C18A/C18C:

Varies from 110% (6600 RPM) at idle to 105% (6300 RPM) at takeoff.

250-C20/C20B: Varies from 113% (6900 RPM) at idle to 105% (6411 RPM) at takeoff.

Torque (5 minutes) Sea level to 14,000 feet 16,000 feet With 600 Series Transmission 250-C 1OD(T63-A-700) 250-C 18A/C18C 250-C20/C20B 78 psi 63.0 psi 73 psi 59.0 psi Straight-line variation between points given.

With 900 Series Transmission 250-C10D (T63-A-700) 250-C18A/C18C 250-C20/C20B 81 psi 65.0 psi 75 psi 60.0 psi (Max. Cont.)

Sea level to 16,000 feet 66 psi 50.5 psi 66 psi 50.5 psi Turbine Outlet Temperature Max. cant.

Takeoff (5 min.)

Transient (6 sec.)

250-C10D (T63-A-700) 250-CI8A/CI8C 693°e (1280°F) 749°e (1380°F) 843°e (1550°F) 250-C20 737°e (1359°F) 793°e (l460°F) 843°C (1550°F) 250-C20B 738°e (1360°F) 8100e (1490°F) 843°e (1550°F) Oil Inlet Temperature Engine:

Transmission:

Maximum Maximum 225°F 1300e (266°F) Minimum flllY afteratioll of tliis certijUate ispUllislia6fe6y afille of 1I0te){Jeeding$1,000, or imprisonmellt 1I0t e.\f:eedillg3years, or 60tfi.

FAA Form 8110-2 (10-68) 4 of 8 'ITziscertijUate may 6e trallSferreaill accoraallcewitli 'Ffl'1{21.47.

~llIitdl ~tlltCS <DfC:\.lI1CriCIl JElcpartmcnt of '@raltsportatiolt - JIfcocral J\biatiolt J\omiltistratiolt ~ufrpI£m£ntaI 'QJtlP£QI£rtifirat£ (QIontinuation ~4£et) A0/n&/~SH657NW Rotor Limits Airspeed Limits Altitude Limit C. G. Range Maximum Weight Number of Seats Power on - N2 Tach Maximum Minimum Power off - Rotor Tach Maximum Minimum Skid Gear - CAS Sea level to 4,000 ft.

4,000 ft. to 16,000 ft.

16,000 feet Gross Weight 29501bs.

23001bs.

21001bs.

29501bs.

3 (pilot and 2 passengers)

355.5 rpm (100%) 348 rpm (98%) 370 rpm (104%) 322 rpm (90.6%) 105 mph decrease VNE 5mph per 1,000 ft.

Longitudinal (-2.0) to (+2.5) (-2.0) to (+4.0) (-2.0) to (+4.0) (-30) Maximum Baggage Fuel Capacity See loading instructions in FAA approved Rotorcraft Flight Manual.

61.6 Gal. (+5) (usable 57.5 Gal.) See Note 1.

Oil Capacity Engine Transmission

5.5 quarts 5 quarts Rotor Blade and Control Movements (Rigging): For rigging information, refer to Bell Model 47G -3B-l maintenance manual for the turbine converted model rotorcraft listed on this certificate except where superseded by Hiller Aircraft Corporation Service Bulletin 01-660 dated November 14, 1978, or later FAA approved revision, or Soloy Conversions, Ltd Service Bulletin 01-660 dated November 14, 1978, or later FAA approved revision.

Serial Numbers Eligible same as shown on Type Certificate Data Sheet 2H3.

Data Pertinent to All Models Datum Same as shown on Type Certificate Data Sheet 2H3.

)lny a{terationojtfiiscertificateispunisfia6fe6yafine ojnote~eed"ing$1,000, orimprisomnentnote~mfing3years,or60tfi.

FAA Form 8110-2 (10-68) 5 of 8 rrTziscertificatemay6etransjerredinaccordancewitfi(F)'ICJ(21.47.

;UuiteD ~tlltes <DfJ\lI1ericll ~cpartmcnt of Wransportation - JIfcoer'll J\&iation J\oministration ~UfJplem.ental WtrP.eQI.ertifirat.e (<1Iontinuation ~4cet) Certification Basis Equipment

1. Civil Air Regulation (CAR) 6 effective December 20, 1956, including amendment 6-1, 6-3, 6-4 (Exemption No. 70 for Model 47G-3 and Exemption No. 2950 for all those turbine powered models listed in this STC with the extended skid gear modification installed).

2. The following paragraphs of Federal Aviation Regulations part 27:

27.33(b)(3) (Amdt. 27-2), 27.45 thru 27.79 (Amdt. 27-1),27.143 (Amdt. 27-1), 27.361(a) (Amdt. 27-1), 27.901 thru 27.991 (Amdt. 27-1), 27.993 (Amdt. 27-2), 27.995 thru 27.1091 (Amdt. 27-1), 1093(b)(I) (Amdt.27-9), 27.1121 thru 27.1145 (Arndt. 27-1), 27.1163 (Amdt. 27-2), 27.1183 thru 27.1193 (Amdt. 27-1), 27.1194 (Arndt. 27-2), 27.1195 (Amdt. 27-5),27.1301 thru 27.1309 (Amdt. 27-1), 27.1337 (Amdt. 27-1),27.1351 (Amdt.

27-1),27.1353 (Amdt. 27-1), 27.1521 (Amdt. 27-1), 27.1549 thru

27.1559 (Amdt. 27- 1), 27.1583(b) and (f) (Arndt 27-1),27.1587 (Arndt. 27-1), 27.1589 (Arndt. 27-1).

The following must be installed in the rotorcraft for airworthiness certification subsequent to the incorporation of this STC.

1. The basic required equipment as prescribed in the applicable airworthiness regulations (see certification basis outlined above).

2. FAA approved Hiller Aircraft Corporation Rotorcraft Flight Manual dated November 4, 1998, or later FAA approved revision, or Soloy Corporation Rotorcraft Flight Manual dated September 6, 1978, which is required in lieu of that specified for the basic unmodified Bell 47G series.

NOTE: Equipment items approved for the basic Bell 47G series are not eligible with this STC unless such items are also shown in the above noted flight manual.

3. Ballast must be installed in accordance with Hiller Aircraft Corporation Drawing List 660-100 dated January 1, 1999, or Solay Corporation Drawing 660-100 dated August 1, 1979, or later FAA approved drawings.

finy a{terationoftfiiJ certificateiJpuniJfia6t:e6yafine of note:(ceeaing$1,000, orimprisomnelltnoteJ;fwfing3 years,or6otfz.

FAA Form 8110-2 (10-68) 6 of 8 'TTiiseertifU:atemay 6etramferreain accoraallccwitfzTfi'1{.21.47.

NOTE 1.

NOTE 2.

NOTE 3.

NOTE 4.

;tll1itcb J5'tlltC13Q)£ c-i\mcricll Jflepartment of Wransportation - JJjeaeral J\&iation J\aministration ~upplcmcntaI m~pc QIcrtifiratc (QIontinuation ~4e£t) ./f0/ntfff SH657NW Current weight and balance data, including alist of equipment included inthe certificated empty weight and loading instructions when necessary, must be provided atthe time of airworthiness certification for return to service. The certificated empty weight and corresponding center of gravity location must include unusable fuel and undrainable oil as follows:

Fuel: 13.9 lbs. (+5) Oil: Negligible Refer tothe applicable FAA approved Rotorcraft Flight Manual forrequired placards and instrument markings.

The rating shown for the Allison 250-C20 and 250-C20B engines isbased on zero ram, dry inlet air, no accessory loads, and no bleed air; and isavailable at sea level to approximately ISA +40°F. See Powercheck Charts for power available from CI0/C18 series engines inRFM Supplement No. 10.

Except where superseded or supplemented by the items listed below, the retirement times forthe modified Bell 47G series rotorcraft are unchanged from that listed inType Certificate Data Sheet 2H3. These additional/superseded times are as follows:

Component Adapter plate Drive shaft Engine mount (basket) Part Number Soloy660-2101 Soloy 660-2408 Bell 47-612-171-123 Replacement Period Hours 3750 4000 2500 NOTE 5.

NOTE 6.

Bell PIN 47-130-110-1 main rotor thrust bearing isnot eligible foruse onBell 47 rotorcraft incorporating this turbine conversion.

Information essential tothe maintenance and servicing of rotorcraft modified in accordance with this STC iscontained inthe pertinent model Bell Helicopter Company maintenance and overhaul instructions and inthe Soloy Corporation supplements to these documents.

External load operations under part 133must be conducted within the limitations and inaccordance with the requirements of the FAA Approved Rotorcraft Flight Manual Supplement forthe Hiller or Soloy cargo hook support system. Models equipped with )1IlYafteratioll if this certificate ispUIlisha6fe6y afine of Ilot eJ(!eedillg$1,000, orimprisollmelltIlot eJ(!eecfillg3years, or 60th.

FAA Form 8110-2 (10-68) 7 of 8 71iiscertificate may 6e trallsferredinaccordancewitn 'F)1'1(21.47.

NOTE 7.

NOTE 8.

NOTE 9.

;1:111ilc~~hllt's (J)f c-i\llIcricu glcpadmcnt of 'QIranspodation - JIfcocral J\&iation J\oministration ~uppl£m£ntal WtlP£QI£rtifirat£ (Q1ontinuation ~4ect) the 900 series transmission meet the structural requirements of the certification basis for external load operations at3200 pounds maximum gross weight provided the weight in excess of2950 pounds isnot imposed on the landing gear.

For Allison 250-CI 00 (T63-A-700), 250-C18A/C18C, and 250-C20/C20B engine installations, ahydraulic pump drive gearbox and pump iseligible tobe installed in accordance with appropriate data contained in Soloy Drawing List 660-100 dated August 1, 1979, or later, foruse with various hydraulic powered equipment installations.

This gearbox and pump may be installed on rotorcraft tobe operated innorn1al category provided deactivation procedures contained inHiller or Soloy Service Instruction 66002 have been complied with. Limitations and conditions tobe subsequently evaluated aspart of the installation and operation of these various items of hydraulically powered equipment (spray systems, etc,) are also contained inthis abovementioned Service Instruction. An Allison 250-C 18A/C18C, 250-C20/C20B fuel line modification must be accomplished inaccordance with Hiller or Soloy STC SH769NW prior to installation of the above discussed Hydraulic Pump Drive Gearbox and Pump, Hiller or Soloy Service Instruction 66002.

The Soloy Turbine Converted Bell 47G series rotorcraft with the 900 series transmission has demonstrated satisfactory operation inthe restricted category agriculture special purpose at3200 lbs. gross weight with the limitations specified in the FAA approved Flight Manual Supplement for the Cargo Hook/Load Support Kit.

Ifoperations are conducted which involve imposing 3,200 lbs. on the landing gear, the rotorcraft must be inspected inaccordance with Hiller or Soloy Service Bulletin No.

16-660 and found satisfactory before itisreturned tothe standard category. Agriculture systems approved for installation must provide adump capability tobe eligible for gross weight operation inexcess of2,950 lbs.

Installation of an Allison 250-C 100 (T63-A-700), 250-C 18A, or 250-C 18C engine must be inaccordance with Hiller Aircraft Master Drawing List 660-100 revised January 1, 1999, or later FAA approved revisions; or Soloy Master Drawing List 660-100 revision dated March 27,1989, or later FAA approved revisions.

-END- )1n] a{terationof tfziscertificate ispunisfza6Ce6]afine of not eJ;JwiinB $1,000, orimprisonmelltnot eJ;JwiinB3years, or 60tfz.

FAA Form 8110-2 (10-68) 8 of 8 'l1iiscertificate lIlay6e transferreain accoraancewitfz 'F)1'1(21.47.