STC SA01180SE

Number SA01180SE

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

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

Part 23 of the Federal Aviation Regulations.

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

Description of the Type Design Change: Manufacturing of AeroAcoustics Aircraft System (AASI) Aircraft Payload Extender II gross weight increase system in accordance with AASI Master Drawing List No. AA1662, Revision G, dated January 20, 2010, or later Federal Aviation Administration (FAA)-approved revision; and installation of Aircraft Payload Extender II gross weight increase system in accordance with AASI Installation Manual No. AA1663, Revision F, dated December 20, 2009, or later FAA-approved revision.

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 this model on which other previously approved modifications are incorporated unless it is determined by the installer, that the relationship between this change and any other previously approved modifications, including changes in type design, will introduce no adverse effect upon the airworthiness of that aircraft. (See Continuation Sheets on Pages 3, 4, and 5)

A copy of this certificate and appropriate FAA-Approved Flight Manual Supplement (AFMS), 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: November 20, 2002 Date reissued: Xxxxxxx ##, #### Date of issuance: February 25, 2003 Date amended: August 20, 2003; February 16, 2007;

August 03, 2009; April 13, 2010

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

Number SA01180SE

AeroAcoustics Aircraft Systems, Inc.

Issued: February 25, 2003 Amended: August 20, 2003; February 16, 2007; August 03, 2009; April 13, 2010

This continuation sheet, which is part of STC SA01180SE, 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

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 Number 208 20800061 and up

Limitation for Eligible Land Planes Only:

Required Flight Manual Supplement: Aircraft with PT6A-114 (600 SHP Engine) Document No. AFMS-C208-19, dated March 26, 2010, or later FAA-approved revision

Aircraft with PT6A-114A (675 SHP Engine) Document No. AFMS-C208-20, dated March 26, 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”

Maximum Weights: Maximum Ramp Weight 8397 lbs Maximum Takeoff Weight 8362 lbs Maximum Landing Weight 7800 lbs

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

Number SA01180SE

AeroAcoustics Aircraft Systems, Inc.

Issued: February 25, 2003 Amended: August 20, 2003; February 16, 2007; August 03, 2009; April 13, 2010

Limitations for Eligible Amphibious Float Equipped Airplanes Only (Increased MTOW Only) Required Flight Manual Supplement: Amphibious Float Equipped Aircraft with PT6A-114A (675 SHP) Engine Document No. AFMS-C208-32, dated August 20, 2003, or later FAA-approved revision

Amphibious Float Equipped Aircraft with PT6A-114 (600 SHP) Engine Document No. AFMS-C208-41, dated February 16, 2007, or later FAA-approved revision

Seaplane Floats Equipped Aircraft with PT6A-114A (675 SHP) Engine Document No. AFMS-C208-33, dated March 26, 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 variation between 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: Maximum Ramp Weight: 8397 lbs.

Maximum Takeoff Weight 8362 lbs.

Maximum Landing Weight 7800 lbs.

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

Number SA01180SE

AeroAcoustics Aircraft Systems, Inc.

Issued: February 25, 2003 Amended: August 20, 2003; February 16, 2007; August 03, 2009; April 13, 2010

Limitations for Eligible Amphibious Float Equipped Airplanes Only (Increased Maximum Takeoff Weight and Maximum Landing Weight on Water):

Required Flight Manual Supplement: Amphibious Float Equipped Aircraft with PT6A-114A (675 SHP) Engine Document No. AFMS-C208-57, dated July 27, 2009, or later FAA-approved revision

Amphibious Float Equipped Aircraft with PT6A-114 (600 SHP) Engine Document No. AFMS-C208-56, dated July 27, 2009, or later FAA-approved revision

Seaplane Floats Equipped Aircraft with PT6A-114A (675 SHP) Engine Document No. AFMS-C208-60, dated March 26, 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 variation between 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: Maximum Ramp Weight: 8397 lbs.

Maximum Takeoff Weight 8362 lbs.

Maximum Landing Weight (On Land) 7800 lbs.

Maximum Landing Weight (On Water) 8000 lbs.

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

- END -

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