STC SA18NW

FAA Form 8110-2 (5/14) Page 1 of 5

Reissued on July 31, 2017 to supersede the original STC, which has been lost or misplaced.

Number: SA18NW

Part 3 of the Civil Air Regulations. See TC Data Sheet A7CE.

Original Product – Type Certificate Number: A7CE Make: Cessna Model: 421, 421A, 421B

Installation of Fowler flaps, flap actuated drooped ailerons, flap actuated elevator trim and anti -servo rudder trim tab in accordance with FAA Sealed Robertson Aircraft Drawing List No. 24. FAA Approved Robertson Aircraft Airplane Flight Manual Supplement is required for the modified aircraft.

Date of Application: March 29, 1972 Date Reissued: 11/8/84; 10/10/86; 9/8/04; 7/31/17 Date of Issuance: November 17, 1972 Date Amended: 4/13/73; 10/10/74

Signature

Title Jim Grigg Manager, Fort Worth A CO Branch, Compliance & Airworthiness Division Sierra Industries, Ltd.

122 Howard Langford Drive Uvalde, TX 78801

FAA Form 8110-2 (5/14) Page 2 of 5

Transfer the ownership of Supplemental Type Certificate Number: SA18NW

To (Name and address of transferee)

From (Name and address of grantor)

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: SA18NW

FAA Form 8110-2 (5/14) Page 5 of 5

Date of Issuance: November 17, 1972 Date Amended: October 10, 1974 Date of Reissuance: July 31, 2017

This approval should not be extended to other aircraft 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 that aircraft. A copy of this Certificate and Addendum No. SA18NW shall be maintained as part of the permanent records for the modified aircraft.

The conditions and limitations of Type Certificate Data Sheet No. A7CE apply except as follows:

This STC Addendum, which is a part of Supplemental Type Certificate No. SA18NW prescribes conditions and limitations under which the product for which the STC was issued meets the airworthiness requirements of the Civil Air Regulations.

A copy of this STC Addendum is required to be maintained as part of the modified aircraft’s permanent records.

SUPPLEMENTAL TYPE CERTIFICATE HOLDER R/STOL SYSTEMS, INC.

IV. Model 421 (Normal Category) Model 421A (Normal Category)

Airspeed Limits (CAS) Flaps Extended 10° 195 MPH Flaps Extended 30° 145 MPH

Control Surface Movements Wing Flaps Down 10° ± 1° Down 3° +1°, -2°

Main Surface Ailerons Flap Droop Aileron Travel Position Neutral From Droop Neutral 0° 0° ± 1° Up 20° +1°, -0° Down 20° +1°, -0° 10° + 1°, -1° 8° ± 2° Up 12° ±2°, Down 28° ±2° 30° + 1°, -2° 8° ± 2° Up 12° ±2°, Down 28° ±2°

Rudder – No change.

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: SA18NW

FAA Form 8110-2 (5/14) Page 5 of 5

Date of Issuance: November 17, 1972 Date Amended: October 10, 1974 Date of Reissuance: July 31, 2017

Tab (Main Surface in neutral, measured normal to rudder hinge line) Rudder

Rudder Position Trim Position Tab Position * 0° 0° 0° 25° + 1° Right 0° 5° ± 1° Right

- 0° 25° + 1° Left 0° 3° ± 1° Left

- 0° 0° Full Right 16° + 1° Left

- 0° 0° Full Left 11° + 1° Right

*Measured from Rudder surface.

VI. Model 421B (Normal Category)

Airspeed Limits (CAS) Same as IV Above

Control Surface Movements Wing Flaps Same as IV Above

Main Surface Ailerons – Same as IV Above

Rudder 32° +1°, -2° Left 32° +1°, -2° Right

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: SA18NW

FAA Form 8110-2 (5/14) Page 5 of 5

Date of Issuance: November 17, 1972 Date Amended: October 10, 1974 Date of Reissuance: July 31, 2017

Tab (Main surface in neutral, measured normal to rudder hinge line)

Rudder:

Rudder Position Trim Position Tab Position * 0° 0° 0° 32° + 1° Right 0° 6° + 1° Right

- 2° - 0° 32° + 1° Left 0° 3° + 1° Left

- 2° - 0° 0° Full Right 18° + 1° Left

- 1° 0° Full Left 13° + 1° Right

*Measured from rudder surface.

NOTE 2. THE PLACARDS SPECIFIED IN THE FAA APPROVED CESSNA AIRPLANE FLIGHT MANUAL

MUST BE DISPLAYED PLUS THE FOLLOWING CHANGES MADE BY THE FAA APPROVED R/STOL SYSTEMS, INC. AIRPLANE FLIGHT MANUAL SUPPLMENT.

A. Maximum Flap Extension Speed 10° Flap: 195 (CAS) 170 KCAS

B. Maximum Flap Extension Speed 30° Flap: 145 (CAS) 126 KCAS

C. Minimum Single Engine Control Speed

421, 421A Flaps 10° 95 MPH CAS (83 KCAS) Flaps Up 106.5 MPH CAS (93 KCAS) Red Radial

421B Flaps 10° 92 MPH CAS (80 KCAS) Flaps Up 100 MPH CAS (87 KCAS) Red Radial

D. Warning – Flaps up prior to opening door. (Except 421B)

-END-

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: SA18NW

FAA Form 8110-2 (5/14) Page 5 of 5