STC SA01984SE

United States of America Department of Transportation_Federal Aviation Administration Supplemental Type Certificate Number SA01984SE This certificate, issued to AeroAcoustics Aircraft Systems, Inc.

9802 29 th Ave. W, Hangar B-104 Everett, WA 98204 Part 23 of the Federal Aviation Regulations.

Original Product⎯Type Certificate Number: See attached approved Model List (AML) Make: No. SA01984SE for a list of approved aircraft models Model: and applicable airworthiness regulations.

Description of the Type Design Change: Installation of AeroAcoustics Aircraft Systems (AASI) Payload Extender XL gross weight increase system in accordance with AASI Document AA2030, Revision B, dated October 22, 2009, and manufactured in accordance with AASI document Master Drawing List AA2031, Revision C, dated October 22, 2009, or later FAA-approved revisions 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 this model 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. A copy of this Certificate and FAA-approved Aircraft Flight Manual Supplement (see Page 3) 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.

(See Continuation Page 3)

This certificate and the supporting data which is the ba sis for approval shall remain in effect until surrendered, suspended, revoked, or a termination date is otherwise established by the Administrator of the Federal Aviation Administration.

Date of application: December 19, 2009 Date reissued:

Date of issuance: March 26, 2009 Date amended: August 24, 2009, December 23, 2009

(Signature) Manager, Seattle Aircraft Certification Office (Title)

Number SA01984SE AeroAcoustics Aircraft Systems, Inc.

Reissued:

Amended: August 24, 2009; December 23, 2009 Limitations and Conditions: (cont’d) This continuation sheet, which is part of STC SA01984SE, prescribes the conditions and limitations under which the product for which the STC was issued complies with the Federal Aviation Regulations.

The conditions and limitations of Type Certificate Data Sheet Number A4CE apply except where amended by the following:

Limitations for Eligible Land Planes Only Applicability: This modification is applicable to the following aircraft equipped with the Flint Aero Maximum Takeoff Weight Increase in accordance with STC No. SA4366WE only:

Model: Serial Number U206F/TU206F U206-1701 to U206-3521 U206G/TU206G U206-3522 to U206-7020 206H 206-8001 and On T206H T206-8001 and On Required Cessna 206F, G & H Landplane Series Aircraft (Turbo or Non Turbo Version) Flight Manual Document No. AFMS-C206-1 dated 12/23/09 Supplement: or later FAA approved revision.

Cessna 206G & H Landplane Series Aircraft equipped with Soloy Mark I Turbine Conversion (STC SA2353NM) Document No. AFMS-C206-9 dated 12/23/09 or later FAA approved revision.

Cessna 206H Landplane Series Aircraft equipped with Soloy Mark II Turbine Conversion (STC SA01878SE) Document No. AFMS-C206-10 dated 12/23/09 or later FAA approved revision.

CG Range Takeoff and flight Forward 33 inches aft of datum at 2500 pounds or less.

44.4 inches aft of datum at 3800 pounds Aft 49.7 inches aft of datum at 3800 pounds or less Straight line variation between points given.

Maximum Ramp: 3817 pounds (Turbo or Turbine Version) Weights: 3814 pounds (Non-Turbo Version) Takeoff: 3800 pounds Landing: 3800 pounds Zero Fuel: 3600 pounds Placards: The placard shown below must be located on each main landing gear wheels:

“TIRE INFLATION – 50 PSIG”

FAA FORM 8110-2- 1 (10-69) PAGE 3 OF 4 PAGES

Number SA01984SE

AeroAcoustics Aircraft Systems, Inc.

Reissued:

Amended: August 24, 2009, December 23, 2009

Limitations and Conditions: (cont’d) This continuation sheet, which is part of STC SA01984SE, prescribes the conditions and limitations under which the product for which the STC was issued complies with the Federal Aviation Regulations.

The conditions and limitations of Type Certificate Data Sheet Number A4CE apply except where amended by the following:

Limitations for Eligible Amphibious and Seaplane Equipped Airplanes Only

Applicability: This modification is applicable to the following aircraft equipped with the Flint Aero Maximum Takeoff Weight Increase in accordance with STC No. SA4366WE or SA3232NM only:

Model: Serial Number U206F/TU206F U206-1701 to U206-3521 U206G/TU206G U206-3522 to U206-7020

Required Cessna 206F & G Floatplane or Amphibian Series Aircraft Flight Manual AASI Document AFMS-C206-8, dated December 23, 2009, or later Supplement FAA-approved revision.

CG Range Takeoff and flight Forward 34 inches aft of datum at 2600 pounds or less.

40.0 inches aft of datum at 3800 pounds Aft 47.4 inches aft of datum at 3800 pounds or less Straight line variation between points given.

Maximum Takeoff: 3800 pounds Weights: Landing:(Water Only) 3725 pounds Landing (Land Only) 3600 pounds Zero Fuel: 3600 pounds

Limitations Pertaining to all Eligible Models

Limit Factor Flaps up: +3.8, -1.52 Limits (g’s) Flaps down (all settings): +2.00 0.0

- END -

FAA FORM 8110-2- 1 (10-69)