STC SA2324SO

Part 25 of the Federal Aviation Regulations. (See Type Certificate Data Sheet Number A20WE for complete certification basis).

Installation of a cargo handling system in accordance with Aeronautical Engineers, Inc. Drawing List Report No. R-619, Rev. “F”, dated April 15, 1989, or later FAA approved revisions.

1) The installer must determine whether this design change is compatible with previously approved modifications.

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

(Continued on page 3)

Telair US LLC 500 Gateway Drive Goldsboro, NC 27534 A20WE Make : Boeing Model : 747-100, 747-200B Date of application : March 17, 1988

Date of issuance : May 5, 1988

Date reissued : September 14, 1989; March 26, 2015

Date amended : September 14, 1989; June 3, 1991;

August 19, 1994

By direction of the Administrator Original Signed By:

Karol Mordasiewicz

(Signature) Karol Mordasiewicz Manager, Airframe & Administrative Branch Chicago Aircraft Certification Office

(Title)

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

Number SA2324SO

Date Amended: September 14, 1989; June 3, 1991; August 19, 1994 Date Reissued: September 14, 1989; March 26, 2015

LIMITATIONS AND CONDITIONS: (Continued from Page 1 of 3)

3) For the Model 747-100, installation of this STC is limited to those aircraft modified in accordance with STC’s SA2322SO and SA2323SO. Weight and Balance Manual Supplement, Report No. R-648, dated April 20, 1988, is a required part of this STC.

When installed, this STC must maintain a minimum aisle width of 16 inches between the cargo containers and the fuselage to ensure access to the cargo door for the purpose of visual inspection of the cargo door latching/locking mechanism.

4) For the Model 747-200, installation of this STC is limited to those aircraft modified in accordance with STC SA4227NM -D.

When installed, this STC must maintain a minimum aisle width of 16 inches between the cargo containers and the fuselage to ensure access to the cargo door for the purpose of visual inspection of the cargo door latching/locking mechanism.

5) This modification is permitted to be operated with specific missi ng, broken, inoperable or malfunctioning restraint hardware only in strict compliance to Report Number BPS 584, Revision A, dated April 9, 1990, or later FAA approved revisions.

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