STC SA02042SE

Number SA02042SE

This certificate, issued to: AeroAcoustics Aircraft Systems, Inc.

9802 29th Avenue W., Hangar B-104 Everett, WA 98204

Part 23 of the Federal Aviation Regulations.

Original Product⎯Type Certificate Number: A37CE Make: Cessna Model: 208, 208A

Description of the Type Design Change: Fabrication of AeroAcoustics Aircraft Systems (AASI) Aircraft Payload Extender STOL system in accordance with AASI Master Drawing List No. AA2034, Revision B, dated December 15, 2009, and installation in accordance with AASI Installation Manual No. AA2014, Revision B, dated January 06, 2010, or a later FAA-approved revision to either of these documents.

Limitations and Conditions: Approval of this change in type design applies to the above model aircraft only.

This approval should not be extended to other aircraft of these models on which other previously approved modifications are incorporated unless it is determined that the relationship between this change and any of those other previously approved modifications, including changes in type design, will introduce no adverse effect upon the airworthiness of that aircraft. (See Continuation Sheet on Page 3 of 5)

A copy of this certificate and the appropriate FAA-approved Aircraft Flight Manual Supplement (see Page 3), or later FAA-approved revision, must be maintained as part of the permanent records for the modified aircraft.

If the holder agrees to permit another person to use this certificate to alter the product, the holder shall give the other person written evidence of that permission.

Date of application: October 24, 2008 Date reissued:

Date of issuance: January 06, 2010 Date amended: January 29, 2010

(Signature) Acting Manager, Seattle Aircraft Certification Office (Title) Original Signed by Ronald F. May

Number SA02042SE

AeroAcoustics Aircraft Systems, Inc Issued: January 06, 2010 Amended: January 29, 2010

Limitations and Conditions continued: This continuation sheet, which is part of STC SA02042SE, prescribes the conditions and limitations under which the product for which the STC was issued complies with the Federal Aviation Regulations.

Applicability:

Model: Serial Number

208 20800001 through 20800060 (eligible only if modified with Cessna Kit SK-208-12)

208 20800061 and up

208A All

This modification is also applicable to the above aircraft that have been modified with Wipaire, Inc. STC No. SA149CH (675 SHP PT6A-114A Engine Installation).

This modification is also applicable to the following aircraft equipped with Wipline Model 8000 amphibious floats in accordance with STC No. SA1311GL only.

Model: Serial Numbers

208 20800061 and up

Limitations for Eligible Land Planes Only

Required Flight Manual Aircraft with PT6A-114 (600 SHP engine) Supplement: Document No. AFMS-C208-46, dated January 06, 2010, or later FAA-approved revision

Aircraft with PT6A-114A (675 SHP engine) Document No. AFMS-C208-45, dated January 06, 2010, or later FAA-approved revision

CG Range: Takeoff and Flight Forward: 162.41 inches aft of datum at 4200 lbs. or less

175.68 inches aft of datum at 8362 lbs.

Aft: 184.35 inches aft of datum at 8362 lbs. or less Straight line variation between the points given.

Placards: On each side of nose strut fairing near tow limit marking:

“DO NOT JACK OR TOW THIS AIRCRAFT AT GROSS WEIGHTS ABOVE 8035 LB”

FAA FORM 8110-2-1 (10-69) PAGE 3 OF 5 PAGES

Number SA02042SE

AeroAcoustics Aircraft Systems, Inc Issued: January 06, 2010 Amended: January 29, 2010

Maximum Weights: Ramp: 8397 lbs Takeoff: 8362 lbs Landing: 8362 lbs

Limitations for Eligible Float Planes Equipped Airplanes Only (Increased MTOW and MLW on water)

Required Flight Manual Amphibious Float Equipped Aircraft with PT6A-114A (675 SHP) engine Supplement: Document No. AFMS-C208-55, dated January 06, 2010, or later FAA-approved revision

Amphibious Float Equipped Aircraft with PT6A-114 (600 SHP) engine Document No. AFMS-C208-54, dated January 06, 2010, or later FAA-approved revision

Seaplane Float Equipped Aircraft with PT6A-114A (675 SHP) engine Document No. AFMS-C208-61, dated January 28, 2010, or later FAA-approved revision

CG Range: Takeoff and Flight Forward: 165.47 inched aft of datum at 5200 lbs. or less

173.64 inches aft of datum at 8000 lbs.

175.63 inches aft of datum at 8210 lbs.

179.07 inches aft of datum at 8362 lbs.

Aft: 182.68 inches aft of datum at 8362 lbs. or less Straight line variati on between the points given

Placards: On the outboard side of each float aft of the leading edge bumper and above the chine:

“DO NOT JACK OR TOW THIS AIRCRAFT AT GROSS WEIGHTS ABOVE 8035 POUNDS”

Maximum Weights: Ramp: 8397 lbs.

Takeoff: 8362 lbs.

Landing on Land: 7800 lbs.

Landing on Water: 8000 lbs.

FAA FORM 8110-2-1 (10-69) PAGE 4 OF 5 PAGES

Number SA02042SE

AeroAcoustics Aircraft Systems, Inc Issued: January 06, 2010 Amended: January 29, 2010

Limitations Pertaining to all Eligible Models

Limit Speeds (IAS): Maneuvering Speed at 8362 lbs. 143 Kt

Load Factor Flaps Up: +3.41, -1.36 Limits (g’s): Flaps Down (all settings): +2.00

Placards: Near the airspeed indicator so as to cover the existing airspeed limitation placard.

“143 KIAS”

- END -

FAA FORM 8110-2-1 (10-69) PAGE 5 OF 5 PAGES