STC SA01124DE

SA01124DE Peregrine 7385 S. Peoria St, Unit C4 Englewood, CO 80112 Part 23 Title 14 of the Code of Federal Regulations A00072CE Pilatus PC-24

1. The installer must determine whether this design change is compatible with existing installed approved modifications.

See continuation sheet 3 through end.

10/27/25 6/17/26 Lynn Bailey ODA Administrator ODA (AIR)-834328-NM 4

1. Installation of an Gogo Galileo HDX on Pilatus PC-24 series aircraft. Approved configurations are defined in Master Data List (MDL) E-CT-25-0002, Revision C dated May 5, 2026 or later approved FAA revisions.

See continuation sheet 3 throught end.

SA01124DE 06/17/26 4

SA01124DE 06/17/26 Description of Type Design Change: (continued)

2. ICA. Comply with FAA accepted Instructions for Continued Airworthiness (ICA) E-CT-25-0008 Rev IR or later FAA accepted revisions.

3. AFMS. Comply with FAA approved Aircraft Flight Manual Supplement (AFMS) E-CT-25-0009 Rev A or later FAA approved revisions.

Limitations and Conditions: (continued)

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

3. This STC is applicable to Pilatus Models PC-24 (all serial numbers).

4. The installation does not allow for interface with any Pilatus PC-24 communication equipment necessary for flight or with a Cockpit Voice Recorder.

5. STE Antenna must be installed in lightning attachment location zone 2A of the aircraft in accordance with (SAE) ARP5414B.

6. This STC does not provide instructions or approval to interface the ASNRT equipment with a Cabin Management System (CMS) or In-Flight Entertainment (IFE) system.

7. If an AVANCE SCS system is not installed with this STC, an AVANCE L3 or L5 system must be previously installed on the aircraft.

SA01124DE 06/17/26 Certification Basis:

1. Based on 14 CFR §§21.101 and 21.115, and the FAA policy for non-significant changes in FAA Order 8110.48, the certification basis for the Pilatus PC-24 for this design change modification is as follows:

a. The type certification basis for this aircraft is shown on Type Design Data Sheet (TCDS) A00072CE for parts not altered not affected by the design change.

b. The certification basis for parts altered by the design change is based on Part 23 as amended through Amendments 23-0 through 23-62.

Regulations at the amendment level in the TCDS: 14 CFR §§

23.251(a)(b)(c) [Amdt 23-62], 23.301(a)(b)(c) [Amdt 23-48], 23.303 [Amdt 23-0], 23.305 [Amdt 23-45], 23.307(a) [Amdt 23-0], 23.337(a)(1)(b)(1) [Amdt 23-48], 23.341(c) [Amdt 23-48], 23.365 [Amdt 23-0], 23.473 [Amdt 23-48], 23.561(b)(2) [Amdt 23-62], 23.571(c)(d) [Amdt 23-62], 23.573(b) [Amdt 23-48], 23.601 [Amdt 23-0], 23.603(a) [Amdt 23-23], 23.605

(a) [Amdt 23-23], 23.609 [Amdt 23-0], 23.611 [Amdt 23-48], 23.613(a)(b) [Amdt 23-45],

23.619 [Amdt 23-7], 23.625(a)(b)(c) [Amdt 23-7], 23.627 [Amdt 23-0], 23.771(a) [Amdt 23-14], 23.773(a)(1)(2) [Amdt 23-45], 23.777(a) [Amdt 23-62], 23.853(a)(d)(3) [Amdt 23-62],

23.867 [Amdt 23-49], 23.1301 [Amdt 23-62], 23.1309(a)(c) [Amdt 23-62], 23.1322(d)(e) [Amdt 23-43], 23.1351(a)(b)(1) [Amdt 23-49], 23.1357(a)(c) [Amdt 23-43], 23.1359(c) [Amdt 23-49], 23.1365(a)(d)(e) [Amdt 23-49], 23.1367 [Amdt 23-0], 23.1419(a) [Amdt 23-43],

23.1431(a)(b) [Amdt 23-62], 23.1529 [Amdt 23-26], 23.1581(a)(b)(1) [Amdt 23-50], 23.1585(a) [Amdt 23-62] ---END--- 4 4 Add Page