STC SA2312CE-D

FAA Form 8110-2 (5/14) Page 1 of 3 Number: SA2312CE-D This certificate issued to: Honeywell International Inc.

21111 N 19th Ave Phoenix, Arizona 85027 Part 3 of the Civil Air Regulations.

Original Product – Type Certificate Number: Make: Beech 3A16 Model: E55 Description of Type Design Change:

Configuration A: Installation of Bendix/King EHI 40 Electronic Horizontal Situation Indicator System.

REQUIRED DATA: 1. Master Drawing List 155-9506-00, Rev. 2, dated 12-20-88 and 2. Airplane Flight Manual Supplement 006-0481-00 dated 1-13-89 or later FAA approved revision to 1 or 2.

1. This approval included an eval uation and finding of acceptance of the interface between the Bendix/King EHI 40 Electronic Horizontal Situation Indicator System and the Bendix/King KFC 325 Automatic Flight Control System (SA2055CE-D) and between the Bendix/King EFS 40 Electronic Flight Instrument System and the Bendix/King KFC 325 Automatic Flight Control System.

(Continued on Continuation Sheet) 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: 1-27-88 Date Reissued: 2-28-95; 2-28-00; 4-1-20 Date of Issuance: 1-13-89 Date Amended: 6-22-90 By Direction of the Administrator Signature Richard B. Sleigh Title ODA Administrator, ODA-602216-NM

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

To (Name and address of transferee) From (Name and address of grantor) Extent of Authority (if licensing agreement):

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: SA2312CE-D

FAA Form 8110-2 (5/14) Page 3 of 3 Description of Type Design Change: (continued) Configuration B: Installation of Bendix/King EFS 40 Electronic Flight Instrument System.

DATA REQUIRED: 1. Master Drawing List 155-09610-0000, Rev. 1, dated 4-26-90 and 2. Airplane Flight Manual Supplement 006-0481-01 dated 6-22-90 or later FAA approved revisions to 1 or 2.

Limitations and Conditions: (continued)

2. This approval should not be extended to other specific airpl anes 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 airplane.

3. A stand by attitude indicator must be installed and operational in accordance with the provisions of this approval.

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