# STC SA38NW

- Type: Supplemental type certificate
- Status: Current, Issued
- Holder: Jenkins, J. S., United States
- Description: Installation of a Pratt and Whitney R985-AN3 engine, Hamilton Standard 2D30/6101A-12 propeller, BE-18 exhaust collector and carburetor heat system, Beech 18 oil cooler, oil tank (5 gallon) and BT-13 wheels and brakes
- Applied: July 14, 1972
- Status date: April 16, 1973
- Product: Aircraft, Small Airplane
- Certification basis: Part 21
- Data sheets: [TCDS A-743](https://openairdocs.org/tcds/A-743)
- Certificate PDF: https://openairdocs.org/files/sha256/80/7f/807f80aea8269dc2449d63e6c26a331893c332c8a452d0d576227bd7db8d2723
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/646561C38BD9B1D086257AE10065F683.0001
- DRS record last changed: December 5, 2025
- Page: https://openairdocs.org/stc/SA38NW

## ADs that name it (0)

None.

## Approved models (1)

- Boeing Airplane Company Wichita Division IB75A ([TCDS A-743](https://openairdocs.org/tcds/A-743))

## What the certificate says

This is OCR from the scanned FAA certificate. OCR can misread letters and numbers.

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate Number 5A3814 This certificate issued to: J. Stan Jenkins Purt La of the CiViL Air Regulations.

Original Product -Type bertificate Number: 27/43 Make: Boeing (Stearman) Model: IB75A Description of Type Design Change:

Installation of a Pratt and Whitney R985-AN3 engine, Hamilton Standard 2D30/6101A-12 propeller, BE-18 exhaust collector and carburetor heat system, Beech 18 oil cooler, oil tank (5 gallon) and BT-13 wheels and brakes. Also installed type PT-22 front and rear windshield.

Data not suitable for reproduction in other aircraft; therefore, they are satisfactory for Boeing IB75A on a one-only airplane basis for Serial Number 75-2443 with Registration N56208.

Date of Application: 14 JULY 1972 Date Reissued:

Date of Issuance: 16 April 1973 Date Amended:

FEDERAL AVIATION By Direction of the Administrator ( Signature ) ¡MINISTRATO Acting Chief, Engineering and Manufacturing Branch ( I itle )

United States of America Department of Transportation Federal Aviation Administration applemental T one Certificate (Continuation Sheet) Number: SA38M1 Supplemental Type Certificate ADDENDUM NO. SA38NW The conditions and limitations of the original specification apply except as follows:

This Addendum, which is part of Supplemental Type Certificate No. SA38NW, prescribes conditions and limitations under which the product for which the ST was issued and meets the airworthiness requirements of Civil Air Regulations 4a. A copy of this Addendum shall be maintained as part of the modified aircraft permanent records.

Supplemental Type Certificate HOLDER: J. Stan Jenkins MODEL IB75A BOEING (LANDPLANE ONLY, NORMAL, CATEGORY) AS MODIFIED BY STC SA38NW Engine: Pratt & Whitney R985-AN3 Fuel: 87 Minimum Grade Aviation Gasoline Engine Limits: (Takeoff) 450 hp. @ 2300 rpm - 1 minute (Meto) 310 hp. @ 1950 rpm Airspeed Limits: Level flight or climb 125 mph true ind.

Glide or dive 150 mph true ind.

Propeller and Hamilton Standard 2D30/6101A-12 Propeller Limits: Diameter: 9'0" maximum 8'3 7/8" minimum C.G. Range: -2.1 to 4.0 @ 3200 Maximum Weight: (Takeoff) NC certification, 3200# Fuel Capacity: 46 gallons Oil Capacity: 5 gallons Power Plant Instrument Markings: Tachometer: 2300 rpm (Red Line) Oil Temp.: 200°F (Red Line) Oil Pressure: Minimum 50 psi (Red Line) Maximum 100 psi (Red Line) Green Arc between 70 and 90 psi Yellow Arc between 50 and 70 psi Control Surface Movements Elevator up 28° down 22° SERIAL NUMBERS ELIGIBLE: 75-2443 ONLY REQUIRED EQUIPMENT: In addition to the equipment and applicable by the original type certificate, the items as specified below apply to this STC.

(Continued)

**FAA FORM 8110-2-1 (10-69) PAGE 3 OF 4 PAGES FAA AC 72-4435**

NOTE 1. Current weight and balance report including list of equipment included in the certificate empty weight, must be in the aircraft.

NOTE 2. The following PLACARDS must be installed in the rear cockpit and in clear view of the pilot:

**1. METO POWER NOT TO EXCEED 310 HP. (1950 RPM).**

**2. INTENTIONAL SPINS PROHIBITED.**

**3. SOLO FROM THE REAR SEAT ONLY.**

Page 4 of I Pages

## Every issue (1)

- April 16, 1973: Issued, Current. [certificate](https://openairdocs.org/files/sha256/80/7f/807f80aea8269dc2449d63e6c26a331893c332c8a452d0d576227bd7db8d2723)

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