Supplemental Type Certificate for Reims-Cessna F152

service. On future replacement of parts this form will not be required. SERVICING: Under normal conditions, replace filter element PN BA-6108, after 100 hours use or1 year intervals. Under severely dusty conditions, check daily and replace when element is 50% covered with foreign material For Continued Airworthiness, see Form I-194. Instruction Sheet Part No. 5105 Date Rev: 03-04-04 Mfg. by: BRACKETT AERO FILTERS, INC. Kingman, AZ BRACKETT AIR FILTER DOCUMENT I-194 PLACE IN AIRCRAFT RECORDS CONTINUED AIRWORTHINESS INSPECTION REQUIREMENTS AS PER FAR 23.1529 AND GENERAL PROCEDURES OF PART 43 INSPECTION INTERVALS: Pre-flight inspections, engine backfire inspection, 100 hour inspections, annual inspections, filter element replacements. A. B. C. INSPECTION PROCEDURES Pre-flight inspection: Per Pilots Operating Handbook, check filter assembly for security, damage or 50% contamination of element face. If found report to maintenance personnel prior to flight. Engine start-up backfire inspection: Prior to flight, check the entire intake system for security or damage. If a fire was present, the downstream face of the foam element will show erosion. If any irregularities are found see Chart I and also refer to the Aircraft Maintenance Manual for the intake system. At element replacement intervals: With the element removed, inspect the filter grill, filter frame, filter mountings and entire intake system for security, wear and any deformation. Note: On filter assemblies with gaskets, visually inspect inside and outside of frame for any signs of gasket looseness, movement or deterioration. If found refer to Chart I or the proper maintenance manual for your aircraft or component. PART REPLACE REWORK FRAME GASKET X INSTRUCTIONS COMPLETE NEW ASSEMBLY ON FILTER FRAME, REMOVE OLD NEOPRENE GASKET AND ALL TRACES OF ADHESIVE DOWN TO A CLEAN ANODIZED FRAME SURFACE, USE ADHESIVE 3M#847 OR DOW CORNING RTV-732. COAT ENTIRE MATING SURFACE (GASKET TO FRAME). APPLY ADHESIVE FOLLOWING MANUFACTURER'S LABEL DIRECTIONS. WHEN FRAME AND GASKET ARE PLACED TOGETHER, CLAMP OR WEIGHT DOWN AT .75 LB./SQ. IN. OF CONTACT AREA. ALLOW TO CURE 24 HOURS PRIOR TO INSTALLATION. PRIOR TO REINSTALLATION OF FILTER, CHECK AIRBOX MATING SURFACE FOR IRREGULARITIES. IF FOUND, CORRECT PER MANUFACTURER'S REQUIREMENTS. UPON REINSTALLATION CHECK THAT THE GASKET MAKES 100% CONTACT. THE GASKET SHOULD BE COMPRESSED 50% FOR OPTIMUM SEAL. REPLACE WITH NEW GRILL REPLACE UNSERVICEABLE WITH NEW COMPLETE NEW ASSEMBLY GRILL ☑ HARDWARE X SCREEN X SCREEN/GASKET X ELEMENT X COMPLETE NEW ASSEMBLY ( REPLACE ELEMENT ASSEMBLIES USING SCREEN GASKETS PRE 1981; BA-4106, BA-5110 AND BA-8110. DATE: 3-16-94 CHART 1 U.S. Department of Transportation Federal Aviation Administration MAJOR REPAIR AND ALTERATION (Airframe, Powerplant, Propeller, or Appliance) Form Approved Electronic Tracking Number OMB No.2120-0020 2/28/2011 For FAA Use Only INSTRUCTIONS: Print or type all entries. See Title CFR §43.9, Part 43 Appendix B, and AC 43.9-1 (or subsequent revision thereof) for instructions and disposition of this form. This report is required by law (49 U.S.C. §44701). Failure to report can result in a civil penalty for each such violation (49 U.S.C. §46301(a)). 1. Aircraft Nationality and Registration Mark N13391 Serial No. 17262723 Make CESSNA Name (As shown on registration certificate) 2. Owner TY M. MACKEY 4. Type Repair Alteration Unit X AIRFRAME POWERPLANT PROPELLER Type APPLIANCE A. Agency's Name and Address Name EL PASO AERO INC. Manufacturer State TX Country USA Address 7305 BOEING DRIVE City EL PASO Zip 79925 D. Model Series 172M Address (As shown on registration certificate) Address 1933 VALLEYVIEW DRIVE City SAN ANGELO State TX Zip 76904 Country USA 3. For FAA Use Only 5. Unit Identification Make Model (As described in item 1 above) 6. Conformity Statement B. Kind of Agency U.S. Certificated Mechanic Foreign Certificated Mechanic X Certificated Repair Station Certificated Maintenance Organization Serial No. Manufacturer C. Certificate No. CRS# VL1R562K I certify that the repair and/or alteration made to the unit(s) identified in item 5 above and described on the reverse or attachments hereto have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information furnished herein is true and correct to the best of my knowledge. Extended range fuel per 14 CFR Part 43 App. B Signature/Date of Authorized Individual TE TAYLOR CHENAUSKY 11/24/2020 7. Approval for Return To Service FAA Fit. Standards Manufacturer BY Inspector Pursuant to the authority given persons specified below, the unit identified in item 5 was inspected in the manner prescribed by the Administrator of the Federal Aviation Administration and is ☑ APPROVED REJECTED Person Appoved by Canadian Department of Transport (Specify) FAA Designee X Repair Station Maintenance Organization Inspection Authorization Other Certificate or Designation No. Signature/Date of Authorized Individual CRS#VL1R562K A. CHENAUSKY 11/24/2020 FAA Form 337 (10-06) NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. 8. Description of Work Accomplished (If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.) N13391 Nationality and Registration Mark 11/24/2020 Date Removed existing MX-300 #1 NAV/COM, RT359A Transponder and A30 Digitizer. Installed new Garmin GNX375 IFR Navigator/ADS- B Transponder with GI-106A Indicator and GAE Encoder. The installation was in accordance with Garmin International Inc. STC# SA02636SE and the GNX375 AML STC Installation Manual 190-02207-A4 Rev.7 dated 02/20. The GNX375 was installed in the center avionics panel utilizing AN hardware using factory provided installation kit and mil spec wire. The GNX375 was interfaced to the GI-106A Indicator located in the pilot's instrument panel in accordance with the installation manual. The GNX375 was wired to the avionics bus with a mil 22759 22 gauge wire through a 5 amp circuit breaker labeled GPS/XPDR. Installed a new Garmin GA35 GPS antenna on top of the cabin in place of the removed ADF Sense Antenna Feed through utilizing a Garmin Doubler. Complied with system post installation configuration and checkout in accordance with Section 5 of the installation manual. FAA Approved Garmin GNX375 GPS/XPDR Navigation System Flight Manual Supplement p/n 190-02207-A3 Rev. 3 dated 03/03/20 was added to the aircraft Supplemental Flight Manual. Instructions for Continued Airworthiness (ICA) Garmin Documents p/n 190-02207-A2 for GNX375 was added to the aircraft records. Weight and Balance updated. Complied with FAR 91.413 and 91.411(A)(2) and (A)(3). ********************************************************************END******************************************** ******************** ☐ Additional Sheets Are Attached FAA Form 337 (10-06) ATION NOLE United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate Number: SA02636SE This certificate issued to: Garmin International, Inc. 1200 East 151st Street Olathe, KS 66062 certifies that the change in the type design for the following product with the limitations and conditions therefore as specified hereon meets the airworthiness requirements of Part 23 Original Product - Type Certificate Number: Make: of the Federal Aviation Regulations Model: Multiple AML STC Description of Type Design Change: See Approved Model List (AML) SA02636SE for approved aircraft models and applicable airworthiness standards. Installation of Garmin GPS 175 Navigation System, GNX 375 Navigation System with ADS-B In/Out Transponder, and GNC 355 Navigation System with VHF COM Radio, Data required includes Garmin Master Drawing List (MDL) 005-01206-A1 Revision 1, dated March 22, 2019 or later FAA-approved revision; Garmin Airplane Flight Manual Supplement (AFMS) 190-02207-A3 Revision 1, dated March 22, 2019 or later FAA-approved revision; Garmin Maintenance Manual (Includes Instructions for Continued Airworthiness (ICA)) 190-02207-A2 Revision 1, dated March 22, 2019 or later FAA-approved revision. Limitations and Conditions: (1) The installer must determine whether this design change is compatible with previously installed modifications. (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) A copy of this certificate, the approved AFMS, and the approved ICA must be maintained as part of the permanent records for the modified aircraft. (See Continuation Sheet on Page 3) This certificate and the supporting data which is the basis for approval shall remain in effect until surrendered suspended, and revoked or a termination date is otherwise established by the Administrator of the Federal Aviation Administration. Date of Application: June 7, 2018 Date of Issuance: March 22, 2019 Date Reissued: Date Amended: July 25, 2019 By Direction of the Administrator Signature Title DR JR Brownell Brownell ODA STC Unit Administrator ODA-240087-CE Any alteration of this certificate is punishable by a fine of not exceeding $1,000, or imprisonment not exceeding 3 years, or both. This certificate may be transferred or made available to third persons by licensing agreements in accordance with 14 CFR 21.47. Possession of this Supplemental Type Certificate (STC) document by persons other than the STC holder does not constitute rights to the design data nor to after an aircraft, aircraft engine, or propeller. The STC's supporting documentation (drawings, instructions, specifications, flight manual supplements, etc.) is the property of the STC holder. An STC holder who allows a person to use the STC to after an aircraft, aircraft angine, or propeller must provide that person with written permission acceptable to the FAA. (Ref. 14 CFR 21.120). FAA Form 8110-2 (5/14) Page 1 of 3 FEDERAL COMINI AVIATION RATIO STR United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate INSTRUCTIONS: The transfer endorsement below may be used to notify the appropriate FAA Aircraft Certification Office of the transfer of this Supplemental Type Certificate. The FAA will reissue the certificate in the name of the transferee and forward it to him. Transfer Endorsement Transfer the ownership of Supplemental Type Certificate Number: To (Name and address of transferee) From (Name and address of grantor} Extent of Authority (if licensing agreement): Date of transfer. Signature of grantor.. Any alteration of this certificate is punishable by a fine of not exceeding $1,000, or imprisonment not exceeding 3 years, or both. This certificate may be transferred or made available to third persons by licensing agreements in accordance with 14 CFR 21.47. Possession of this Supplemental Type Certificate (STC) document by persons other than the STC holder does not constitute rights to the design data nor to alter an aircraft, aircraft engine, or propeller. The STC's supporting documentation (drawings, instructions, specifications, flight manual supplements, etc.) is the property of the STC holder. An STC holder who allows a person to use the STC to alter an aircraft, aircraft engine, or propeller must provide that person with written permission acceptable to the FAA. (Ref. 14 CFR 21.120). FAA Form 8110-2 (5/14) Page 2 of 3 EDERA NATION DMINISTRATION. Amended: July 25, 2019 United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: SA02636SE Limitations and Conditions (continued): (4) For the GPS 175, a GPS/SBAS antenna must be previously or concurrently installed. (5) For the GNX 375, a GPS/SBAS antenna and a transponder antenna must be previously or concurrently installed. (6) For the GNC 355, a GPS/SBAS antenna and a VHF COM antenna must be previously or concurrently installed. For IFR installations, a second GPS navigator, VHF navigation radio, or VHF COM radio must be previously or concurrently installed. Certification Basis: Based on 14 CFR §§ 21.115 and 21.101, and the FAA policy for significant changes in FAA Order 8110.48A, the certification basis for this change is as follows: a. The certification basis for parts not changed or not affected by this change is shown on the attached AML. b. The certification basis for parts changed or affected by this change is at amendment Original through 23-64. Section 23.301 (a) 23.303 Amdt. 23-48 Section Amdt. 23.1301 (a)(b)(c) 23-62 Section 23.1529 Amdt. 23-26 Original 23.1307 23-49 23.1541 (a)(2)(b) 23-21 23.305 (a)(b) 23-45 23.1309 (a)(b)(c)(d) 23-62 23.1555 (a)(b)(e){2} 23-62 23.307 (a) Original 23.1311 (a)(1)(2)(3)(4)(b) 23-62 23.1559 (c) 23-62 23.337 (a)(b)(c) 23-48 23.1321 (a)(c)(e) 23-49 23.1581 (a)(b)(c)(f) 23-50 23.561 (a)(b)(3) 23-62 23.1322 (a)(b)(c)(d){e} 23-43 23.1583 (h)(m) 23-62 23.601 Original 23.1325 (a)(b)(1)(2) 23-50 23.1585 (j) 23-62 23.603 (a)(b) 23-23 23.1329 (h) 23-49 23.2515 (a)(b) 23-64 23.605 (a) 23-23 23.1331 (a)(b)(1) 23-62 23.2520 (a)(b) 23-64 23.607 (a)(b)(c) 23-48 23.1351 (a)(b) 23-49 23.609 (a)(b) Original 23.1353 (h) 23-62 23.611 23-48 23.1357 (a)(b)(c)(d)(e) 23-43 23.613 (a)(b)(c) 23-45 23.1359 (c) 23-49 23.627 Original 23.1365 (a)(b)(d){e} 23-49 23.771 (a) 23-14 23.1367 (a)(b)(c)(d) Original 23.773 (a)(2) 23-63 23.1381 (a)(b)(c) Original 23.777 (a)(b) 23-62 23.1431 (a)(b)(d)(e) 23-62 23.853 (a) 23-62 23.1501(a)(b) 23-21 23.863 (a)(b) 23-34 23.1523 (a)(b)(c) 23.1525 23-34 23-45 _END__ Any alteration of this certificate is punishable by a fine of not exceeding $1,000, or imprisonment not exceeding 3 years, or both. This certificate may be transferred or made available to third persons by licensing agreements in accordance with 14 CFR 21.47. Possession of this Supplemental Type Certificate (STC) document by persons other than the STC holder does not constitute rights to the design data nor to after an aircraft, aircraft engine, or propeller. The STC's supporting documentation (drawings, instructions, specifications, flight manual supplements, etc.) is the property of the STC holder. An STC holder who allows a person to use the STC to alter an aircraft, aircraft engine, or propeller must provide that person with written permission acceptable to the FAA. (Ref. 14 CFR 21.120). FAA Form 8110-2 (5/14) Page 3 of 3 | FAA Approved Model List (AML) STC SA02636SE Airplane Make (TCDS holder) Aircraft Model (Alias) [common name or previous make] Type Certificate Number TC Certification Basis [1] MDL 005-01206-A1 Approved Rev. [2] AML Amended Date AFMS Part Number AFMS Revision [2] Textron Aviation Inc. (Textron 336 Aviation Inc.) [Cessna Aircraft A2CE CAR 3 Original 190-02207-A3 1 Company] Textron Aviation Inc. (Textron 120, 140 Aviation Inc.) [Cessna Aircraft Company] Textron Aviation Inc. (Textron Aviation Inc.) [Cessna Aircraft Company] Textron Aviation Inc. (Textron Aviation Inc.) [Cessna Aircraft Company] Textron Aviation Inc. (Textron Aviation Inc.) [Cessna Aircraft Company] Textron Aviation Inc. (Textron Aviation Inc.) [Cessna Aircraft Company] 140A A-768 CAR 4a Original 190-02207-A3 1 5A2 CAR 3, CAR 4a 1 Original 190-02207-A3 1 150, 150A, 150B, 150C, 150D, 150E, 150F, 150G, 150H, 150J, 150K, 150L, 3A19 CAR 3 FAR 23 1 Original 190-02207-A3 1 150M, A150K, A150L, A150M, 152, A152 170, 170A, 170B A-799 CAR 3 Original 190-02207-A3 1 172, 172A, 172B, 172C, 172D, 172E, 172F (USAF T- 41A), 172G, 172H (USAF T- 41A), 172I, 172K, 172L, 172M, 172N, 172P, 172Q, 172R, 172S 3A12 CAR 3 FAR 23 1 Original 190-02207-A3 1 Textron Aviation Inc. (Textron Aviation Inc.) [Cessna Aircraft Company] Textron Aviation Inc. (Textron Aviation Inc.) [Cessna Aircraft Company] Issued: March 22, 2019 Amended: July 25, 2019 172RG, P172D, R172E (USAF T-41B) (USAF T-41C or D), R172F (USAF T-41D), R172G (USAF T-41C or D), R172H (USAF T-41D), R172J, R172K, 175, 175A, 175B, 175C 177, 177A, 177B 3A17 CAR 3, FAR 23 Original 190-02207-A3 1 A13CE FAR 23 Original 190-02207-A3 1 Page 14 of 18 AIRCRAFT SPECIFIC INFORMATION GENERAL INFORMATION Date 11 / 23 12020 By: Kevin Hernandez AIRCRAFT AIRCRAFT MAKE: Cessna AIRCRAFT MODEL: 172 m AIRCRAFT SERIAL #: 17262723 AIRCRAFT REG. #: N13391 GPS 175/GNX 375/GNC 355 GARMIN. Unit P/N: 011-04378-00 Unit Model: GNX 375 FLIGHT STREAM 510: ✓ [N/A] Mod Level: 0 Serial #: 56J003488 Unit P/N: Unit Model: Mod Level: Serial #: GAE 12: ― LIN/A] Unit P/N: 011 03080-01 Mod Level: 0 Unit Model: GAE 12 Serial #: 376013092 190-02207-A2 Rev. 2 GPS 175/GNX 375/GNC 355 Part 23 AML STC Maintenance Manual Page A-2 GARMIN GPS 175/GNX 375/GNC 355 PART 23 CONFIGURATION LOG SYSTEM INFORMATION Main Board SOFTWARE VERSIONS Software: 3.10 Boot Code: 3.00 Touch Controller Board Software: 2.00 2.00 Boot Code: GPS WAAS Board Software: 2.00 Transponder Board: [N/A] Software: 2.54 FPGA: 210 Boot Code: 250 FPGA: 2.50 Audio: 250 Region List: 2,00 Configuration: 2.54 COM Board: ✓ [N/A] Software: Boot Code: FPGA: SETUP MENU INTERFACES - ARINC 429 RX Port 1: ✓ [N/A] TX Port 1 Format: Speed: High Low Format: RX Port 2: ✓ [N/A] Format: Speed: High Low INTERFACES - RS-232 (RS-422) Port 1: Format: Aviation output 1 Port 3: ✓ [N/A] Port 2: Format Format: Speed: High Low INTERFACED EQUIPMENT ADS-B SRC: ✓ [N/A] GDU: Selection: Not Present ☐ Present LRU: 190-02207-A2 Rev. 2 GPS 175/GNX 375/GNC 355 Part 23 AML STC Maintenance Manual Page A-3 GARMIN. SETUP MENU - CONTINUED LIGHTING CONFIGURATION Display Source: ✓ Photocell Lighting Bus Display Minimum Level: 0.0 % Keys Source: ✓ Photocell ☐ Lighting Bus 10.0 Keys Minimum Level: % Configure Photocell: Response Time: 2 sec Slope: 50 Offset: 50 Photocell Override: Key Backlight Cutoff: 80 % Photocell Transition: 25 % Configure Lighting Bus: Response Time: 2 sec Slope: 50 Offset: 50 Lighting Bus: 14V DC ✓ 14 28V DC ☐ 5V DC ☐ 5V AC GPS ANTENNA OFFSET Antenna Height: Height above ground: Lateral Offset: Offset: 0.0 Longitudinal Offset: 6.0 FT FT Direction: Right Left Offset from nose: 8.0 FT MAIN INDICATOR (ANALOG) Selected course: Allowed ☐ Ignored Display Orientation: Yaw Offset:_ 190-02207-A2 Rev. 2 0° AHRS Unknown ✓ Aft ☐ Up GPS 175/GNX 375/GNC 355 Part 23 AML STC Maintenance Manual Page A-4 SETUP MENU - CONTINUED Air/Ground Threshold: Fuel Type: ✓ AV Gas 30 KT Jet A ☐ Jet B RF PROC Legs: ✓ Enabled Graphical Edit: ✓ Enabled Bluetooth: ☐ Disabled ☐ Disabled ✓ Enabled Disabled GARMIN. MAIN SYSTEM System ID: GNX 1 GPS Select: ✓ Auto ☐ Prompt Terrain Alerts: ✓ Enabled ☐ Disabled Composite CDI: Enabled ☑Disabled External FPL: ☐ Enabled ✓ Disabled ADS-B Logging: ✓ [N/A] ☐ Enabled ☐ Disabled XPDR - SENSORS Alt Sensor: None Gillham ✓ GAE OAT Sensor: Enabled ✓ Disabled Squat Installed: Enabled Disabled Squat On Ground: ☑ [N/A] ☐ Open Ground (OV) XPDR - AIRFRAME Aircraft Category:_ light Aircraft Width: <= 23.0 Meters Aircraft Length: <= 15 m Meters Max Airspeed: <= 300 KT Stall Speed: 55 KT XPDR - OPTIONS 1090 ES Out Control: Always Disable ✓ Always Enable Pilot Controlled Automatic Moding: ✓ Enabled Disabled XPDR-FLIGHT ID Aircraft Registration: N1 3391 Default Flight ID: [N/A] N13391 ICAO Address: A08A03 VFR Squawk Code: 1200 190-02207-A2 Rev. 2 GPS 175/GNX 375/GNC 355 Part 23 AML STC Maintenance Manual Page A-5 GARMIN. Wire Routing Single Engine The following diagram depicts approximate location of all LRUS and antenna(s) along with the wire routing for the GPS 175/GNX 375/GNC 355 throughout the aircraft structure for a single-engine aircraft. 190-02207-A2 Rev. 2 тру GPS TPX GPS р GPS 175/GNX 375/GNC 355 Part 23 AML STC Maintenance Manual Page A-6