STC SH504GL

Part 6 of the Civil Air R egulations. (See page 3 for complete certification basis).

Original Product --Type Certificate N umber :

Description of Ty pe Design Change:

Installation of Lycoming V0-435-A1F engine modified in accordance with STC SE144GL and associated changes in accordance with FAA stamped Tom-Cat Helicopters, Inc. modification instructions dated September 3, 1980, (23 pages), or later FAA approved revisions.

This certificate and the supporting data, which is the basis for approval, shall remain in effect until surrendered, suspended, revoked or a termination date is other wise established by the A dministrator of the F ederal A viation A dministration.

Scott’s-Bell 47, Inc.

100 Minnesota Avenue Le Sueur, MN 56058

2H3 M ake : Bell Helicopter Textron M odel : 47G-3B and 47G-3B-1 Date of application : September 03, 1980

Date of issuance : February 18, 1981 Date reissued : January 27, 2004; December 15, 2010;

August 7, 2014

B y directio n of the A dministrator

Original Signed By:

Karol Mordasiewicz (Signature) Karol Mordasiewicz Manager, Airframe and Administrative Branch Chicago Aircraft Certification Office

(Title)

FAA FORM 8110-2-1(10-69) PAGE 2 of 3 PAGES

N umber SH504GL

FAA FORM 8110-2-1(10-69) PAGE 3 of 3 PAGES

Number SH504GL Date of Issuance: February 18, 1981 Date of Reissuance: August 7, 2014 Limitations and Conditions (Continued) :

1. The installer must determine whether this design change is compatible with previously approved modifications.

2. If the holder agrees to permit another person to use this certificate to alter a product, the holder must give the other pers on written evidence of that permission.

The limitations and conditions shown on Type Certificate Data Sheet Number 2H3 for Bell Model 47G-3B and 47G-3B-1 Rotorcraft remain applicable except:

Engine Lycoming VO-435-A1F modified in accordance with Supplemental Type Certificate SE144GL Fuel 100/130 Minimum grade aviation gasoline Engine Limits Maximum continuous (sea level) 24.1 in. Hg., 3200 rpm (220 hp.)

Takeoff (2 minutes) 27.7 in. Hg., 3200 rpm (260 hp.)

Carburetor Marvel-Schebler MA4-5AA with setting No. 10-4025-12 Rotor Limits & Power Off (Rotor Tach.) Power On (Engine Tach.)

operational Maximum 370 rpm Maximum 3200 rpm engine limits Minimum 333 rpm Minimum 3000 rpm Airspeed limits S. L. to 6000 ft., 105 m.p.h. (91.5K). Reduce 5 m.p.h.(4K) per 1000 ft. above 6000 ft.

C. G. Range (-3.0) to (+4.0) Empty wt. C.G. See required Rotorcraft Flight Manual Supplement Range Maximum Weight 2850 lbs Fuel Capacity 43 gal. (+5) (useable 41 gal.)

Oil Capacity 3 gal. (+12) (useable 1 gal.) including 2.3 lb.

Undrainable oil at (+15)

FAA Approved Rotorcraft Flight Manual Supplement dated February 18, 1981, is required with this installation.

------------End-----------