STC SA1689WE

FAA Form 8110-2 (5/14) Page 1 of 4

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

Number: SA1689WE

Part 3 of the Civil Air Regulations, effective November 1, 1949, and as amended by 3-1 thru 3-12.

Original Product – Type Certificate Number: 3A12 Make: Cessna Model: 172 Landplane only; 172A thru 172P Landplanes and Floatplanes (see limitations below)

Installation of drooped ailerons in flaps down mode, contoured wing leading edge (except for 172M, 172N, and 172P), and wing stall fences in accordance with FAA sealed Robertson Aircraft Drawing List Number 10.

Date of Application: May 12, 1967 Date Reissued: 8/22/73; 1/15/69; 8/4/69; 11/8/84; 10/10/86;

7/21/05; 7/31/17 Date of Issuance: May 23, 1968 Date Amended: 3/23/69; 2/2/70; 11/30/70; 2/26/71; 8/22/73;

5/11/77; 5/19/80; 5/27/82

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 4

Transfer the ownership of Supplemental Type Certificate Number: SA1689WE

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: SA1689WE

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

Date of Issuance: May 23, 1968 Date Amended: May 27, 1982 Date of Reissuance: July 31, 2017

1. Floatplane Models 172A thru 172H are only eligible with Franklin Engines 6A-350-C1 per STC SA340NW (215HP) or 6A-350-C2 per STC SA1334WE (180 HP).

2. Fixed tabs as shown on R/STOL Systems, Inc. Drawing 10-100 required on Floatplane Model 172E. The remaining 172 Series Floatplane Models must have either the same fixed tab or R/STOL Systems, Inc. rudder trim system per STC SA1431WE.

3. The approval of this change in type design applies basically to the above model aircraft only. Th e 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. This determination should include consideration of significant changes in weight distribution such as an increase in the fixed disposable weight in the fuselage.

SUPPLEMENTAL TYPE CERTIFICATE ADDENDUM NO. SA1689WE

The limitations and conditions of Type Certificate Data Sheet No. 3A12 apply except as follows:

This STC Addendum, which is part of Supplemental Type Certificate No. SA1689WE, 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 and Addendum are required to be maintained as part of the modified aircraft’s permanent records.

SUPPLEMENTAL TYPE CERTIFICATE HOLDER: R/STOL SYSTEMS, INC.

I. MODEL 172 4PCLM (NORMAL CATEGORY), 2PCLM (UTILITY CATEGORY)

Control Surface Movements:

Ailerons

Flap Droop from Setting Neutral ±2° UP (± 2°) Down (± 2°)

0° 0° 20° 14° 10° 8° 11° 21° 20° 13° 6° 25° 30° 15° 4° 26° 40° 12.5° ± 0° 6° 24°

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: SA1689WE

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

Date of Issuance: May 23, 1968 Date Amended: May 27, 1982 Date of Reissuance: July 31, 2017

NOTE: Control Surface Movements for ailerons are the same as above for all models listed in the following Sections II thru VIII.

II. MODEL 172A 4PCL-SM (NORMAL CATEGORY), 2PCLM (UTILITY CATEGORY) MODEL 172B 4PCL-SM (NORMAL CATEGORY), 2PCLM (UTILITY CATEGORY)

III. MODEL 172C 4PCL-SM (NORMAL CATEGORY), 2PCLM (UTILITY CATEGORY)

IV. MODEL 172D 4PCL-SM (NORMAL CATEGORY), 2PCLM (UTILITY CATEGORY) MODEL 172E 4PCL-SM (NORMAL CATEGORY), 2PCLM (UTILITY CATEGORY) MODEL 172F (USAF T-41A, 4PCL-SM (NORMAL CATEGORY), 2PCLM (UTILITY CATEGORY) MODEL 172G 4PCL-SM (NORMAL CATEGORY), 2PCLM (UTILITY CATEGORY) MODEL 172H (USAF T-41A, 4PCL-SM (NORMAL CATEGORY), 2PCLM (UTILITY CATEGORY)

V. MODEL 172I 4PCL-SM (NORMAL CATEGORY), 2PCLM (UTILITY CATEGORY) MODEL 172K 4PCL-SM (NORMAL CATEGORY), 2PCLM (UTILITY CATEGORY)

VI. MODEL 172L 4PCL-SM (NORMAL CATEGORY), 2PCLM (UTILITY CATEGORY)

VII. MODEL 172M 4PCL-SM (NORMAL CATEGORY), 2PCLM (UTILITY CATEGORY)

VIII. MODEL 172N 4PCL-SM (NORMAL CATEGORY), 2PCLM (UTILITY CATEGORY)

IX. MODEL 172P 4PCL-SM (NORMAL CATEGORY), 2PCLM (UTILITY CATEGORY)

Control Surface Movements:

Ailerons

Flap Droop from Setting Neutral ± 2° Up (± 2°) Down (± 2°) 0° 0° 20° 14° 10° 8° 11° 21° 20° 13° 6° 25° 30° 15° 4° 26°

NOTE 1 and 2:

For Weight and Balance information, required PLACARDS and instrument markings, refer to Robertson Aircraft Drawing No. 10-100 “MAJOR ASSEMBLY AND INSTALLATION – WING”.

-END-

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: SA1689WE

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