# STC SA02467LA - Type: Supplemental type certificate - Status: Current, Amended - Holder: Blackhawk Modifications Inc., United States - Description: Replacement of the original Pratt and Whitney PT6A-114(A) engine and propeller with a Pratt and Whitney PT6A-42A and 4-blade Hartzell Propeller HC-E4N-3P/D9900(K) propeller or 3-blade Hartzell Propeller HC-B3TN-3AE(Y)/T10290N(K)+2, and associated equipment. - Applied: May 30, 2012 - Status date: November 14, 2013 - Product: Aircraft, Small Airplane - Certification basis: Part 21, Part 23, Part 34, Part 36 - Data sheets: [TCDS A37CE](https://openairdocs.org/tcds/A37CE) - Certificate PDF: https://openairdocs.org/files/sha256/e2/c5/e2c5bc49eff4fba503f004b31d2145cc67c58b790c852d8808da62d5a912dbca - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/E349D7F097B1978286257C39006E4B28.0001 - DRS record last changed: December 6, 2025 - Page: https://openairdocs.org/stc/SA02467LA ## ADs that name it (0) None. ## Approved models (1) - Cessna Aircraft Company 208 ([TCDS A37CE](https://openairdocs.org/tcds/A37CE)) ## What the certificate says Read from the PDF's text layer, without the form's printed wording; the layout is lost and the order can differ. The PDF is the record. This Certificate issued to Blackhawk Modifications Inc. 7601 Karl May Drive Waco, Texas 76708 Part 23* of the Federal Aviation Regulations. *Certification basis set forth on continuation sheet 3 Original Product Type Certificate Number : A37CE Cessna 208 Description of Type Design Change : Replacement of the original Pratt and Whitney PT6A -114(A) engine and propeller with a Pratt and Whitney PT6A -42A and 4-blade Hartzell Propeller HC -E4N-3P/D9900(K) propeller or 3 -blade Hartzell Propeller HC -B3TN-3AE(Y)/T10290N(K)+2, and associated equip ment. Optional equipment includes Flightline Systems Checkpoint Engine Trend Monitor System. Installations done in accordance with FAA Approved Master Drawing List 201201-000, Rev A, dated Feb. 15, 2013, or later FAA approved revisions. Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual Supplements, AFMS 201201-1, Rev IR, dated June 21, 2013 and AFMS 201201-2, Rev IR, dated June 21, 2013 or later FAA approved revisions. Blackhawk Modifications Inc. Instructions for Continued Airworthiness document ICA 201201-30, Rev IR, dated June 14, 2013, or later revisions. Limitations and Conditions : The installation should not be incorporated in any aircraft unless it is determined that the interrelationship between this installation and any pre viously approved configuration will not introduce any adverse effect upon the airworthiness of that aircraft. The approval of this modification applies to the above -noted airplane models only. If the holder agrees to permit another person to use this cer tificate to alter the product, the holder shall give the other person written evidence of that permission. (CONTINUED on page 3) Date of application : May 30, 2012 Date of issuance : June 10, 2013 Date amended : November 14, 2013 (Signature) Manager, Propulsion Branch Los Angeles Aircraft Certification Office (Title) Number SA02467LA Limitations and Conditions(continued) • AeroAcoustics Aircraft Systems, Inc., “Aircraft Payload Extender STOL System,” STC SA01805SE is optional as part of this alteration. • This modification is not compatible with Cessna Model 208 Serial Number 2080500 and greater, aircraft equipped with Garmin 1000 installations, and aircraft equ ipped with TKS installation. Certification Basis The certification basis for this modification is as follows: 14 CFR Part 23 of the Federal Aviation Regulations effective February 1, 1965, as amended by Amendments 23-1 through 23-62 for 23.1, 23.21, 23.23, 23.25, 23.33, 23.45, 23.49, 23.51, 23.53, 23.63, 23.65, 23.69, 23.73, 23.75, 23.77, 23.141, 23.143, 23.145, 23.147, 23.153, 23.155, 23.157, 23.161, 23.171, 23.173, 23.175, 23.177, 23.179, 23.181, 23.201, 23.203, 23.221, 23.231, 23.233, 23.251, 23.253, 23.301, 23.303, 23.305, 23.307, 23.321, 23.331, 23.333. 23.335, 23.337, 23.341, 23.361, 23.363, 23.371, 23.421, 23.471, 23.473, 23.479, 23.481, 23.483, 23.485, 23.493, 23.499, 23.507, 23.509, 23.561, 23.572, 23.601, 23.603, 23.605, 23.607, 23.609, 23.611, 23.613, 23.619, 23.623, 23.625, 23.627, 23.629, 23.735, 23.771, 23.831, 23.863, 23.865, 23.867, 23.901, 23.903, 23.905, 23.907, 23.925, 23.929, 23.933, 23.939, 23.955, 23.959, 23.961, 23.991, 23.993, 23.994, 23.999, 23.1011, 23.1017, 23.1019, 23.1021, 23.1023, 23.1027, 23.1041, 23.1043, 23.1045, 23.1091, 23.1093, 23.1103, 23.1111, 23.1121, 23.1123, 23.1141, 23.1163, 23.1165, 23.1181, 23.1183, 23.1193, 23.1203, 23.1301, 23.1305, 23.1308, 23.1309, 23.1321, 23.1322, 23.1327, 23.1329, 23.1331, 23.1337, 23.1351, 23.1357, 23.1359, 23.1365, 23.1381, 23.1416, 23.1431, 23.1501, 23.1507, 23.1519, 23.1521, 23.1525, 23.1527, 23.1529, 23.1541, 23.1543, 23.1547, 23.1549, 23.1551, 23.1555, 23.1557, 23.1581, 23.1583, 23.1585, 23.1587, 23.1589, except 23.1419 as amended by 23-1 through 23-14. 1. Special Condition 23-ACE-3, Dynamic Evaluation, Engine Installation. Factors from this special condition were incorporated into the whirl mode flutter analysis per 14 CFR 23.629(e)(1) and (2) Amendment 23-54, Flutter. 2. 14 CFR 34, effective January 1, 1994, as amended by Amendments 34-1 thru 34-4. 3. 14 CFR 36, effective December 1, 1969, as amended by Amendments 36-1 thru 36-28. -END- ## Every issue (2) - November 14, 2013: Amended, Current. [certificate](https://openairdocs.org/files/sha256/e2/c5/e2c5bc49eff4fba503f004b31d2145cc67c58b790c852d8808da62d5a912dbca) - June 10, 2013: Issued, Historical. [certificate](https://openairdocs.org/files/sha256/0e/31/0e31725ffe6f10485134c5391a585fc9145ad092bde71c5a10720fb1d08d62cd) --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.