STC SA438NW

FAA Form 8110-2 (5/14) Page 1 of 3

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

Number: SA438NW

Part 3 of the Civil Air Regulations, dated May 15, 1956.

Original Product – Type Certificate Number: A7CE Make: Cessna Model: 421C

Addition of Fowler wing flaps, aileron droop system, elevator trim spring and new flap actuation system, all in accordance with the drawings listed on FAA sealed Robertson Aircraft Drawing List No. 25. FAA approved Pilot’s Operating Handbook Supplement 25-1 (POHS 25-1) is required.

Date of Application: March 10, 1977 Date Reissued: 11/8/84; 10/10/86; 9/8/05; 7/31/17 Date of Issuance: April 22, 1977 Date Amended: July 05, 1977

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 3

Transfer the ownership of Supplemental Type Certificate Number: SA438NW

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: SA438NW

FAA Form 8110-2 (5/14) Page 3 of 3

Date of Issuance: April 22, 1977 Date Amended: July 05, 1977 Date of Reissuance: July 31, 2017

The approval of this change in type design applies basically to the above model aircraft only. Th is approval should not be extended to other aircraft of these models on which other previously approved modifications are incorporated unless it is determined by the installer that the interrelationship between this change and any of those other previously approved modifications will introduce no adverse effect upon the airworthiness of these aircraft. A copy of this certificate shall be maintained as part of the permanent records for each aircraft so modified.

The limitations specified on Data Sheet A7CE Section VII remain unchanged except that the C.G. range (landing gear extended) is revised as follows:

6, 7, 8, 9 or 10-Place

(+152.6) to (+158.0) at 7450 lb.

(+148.6) to 6470 lb. or less

Straight line variation between points given.

Landing gear retracted moment change: +917 in-lb

Compatibility of this modification with the Bendix M-4D autopilot and manual electric trim system has been demonstrated. This approval is extended to other previously approved autopilots subject to the limitations established during each autopilot certification test.

-END-

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: SA438NW

FAA Form 8110-2 (5/14) Page 4 of 3