Enstrom F-28F/280F Series Maintenance Manual Supplement 1

System Description ......................................................................... 4-1 Airworthiness Limitations ................................................................. 4-2 Servicing.......................................................................................... 4-3 Troubleshooting .......................................................................... 4-3 Periodic Inspections.................................................................... 4-3 System Maintenance ....................................................................... 4-4 Electrical Diagram ........................................................................... 4-7 Chapter 5 Attitude Indicator and Directional Gyro System Description ......................................................................... 5-1 Airworthiness Limitations ................................................................. 5-2 Servicing, Troubleshooting, and Periodic Inspections ..................... 5-3 System Maintenance ....................................................................... 5-4 Figures and Electrical Diagrams ..................................................... 5-5 Chapter 6 KX 165A COMM/NAV System System Description ......................................................................... 6-1 Airworthiness Limitations ................................................................. 6-2 Servicing, Troubleshooting, and Periodic Inspections ..................... 6-3 System Maintenance ....................................................................... 6-4 Figures and Electrical Diagrams ..................................................... 6-5 Chapter 7 GTX 330 with ADS-B Out System Description ......................................................................... 7-1 Airworthiness Limitations ................................................................. 7-2 Servicing, Troubleshooting, and Periodic Inspections ..................... 7-3 System Maintenance ....................................................................... 7-5 Figures and Electrical Diagrams ................................................... 7-11 Chapter 8 GTN 650 System Description ......................................................................... 8-1 Airworthiness Limitations ................................................................. 8-2 Servicing, Troubleshooting, and Periodic Inspections ..................... 8-3 System Maintenance ....................................................................... 8-4 Figures and Electrical Diagrams ..................................................... 8-5 Chapter 9 Dual Start Collective Control Installation System Description ......................................................................... 9-1 Airworthiness Limitations ................................................................. 9-1 Servicing, Troubleshooting, and Periodic Inspections ..................... 8-1 System Maintenance ....................................................................... 8-2 Figures and Electrical Diagrams ..................................................... 8-2 ENSTROM F-28F/280F SERIES MAINTENANCE MANUAL SUPPLEMENT 1 Rev. 9 xi Apr 30/2020 EFFECTIVE PAGE LIST Page Date Page Date i Apr 30/2020 ii Nov 11/11 iii Jan 9/14 iv Jan 9/14 v Apr 30/2020 vi Jan 15/19 vii Apr 30/2020 viii Aug 28/17 ix Jan 15/19 x Jan 15/19 xi Apr 30/2020 xii Apr 30/2020 INTRO-1 Jan 15/19 INTRO-2 Apr 30/2020 INTRO-3 Aug 28/17 INTRO-4 Aug 28/17 1-1 Jan 9/14 1-2 Apr 30/2020 1-3 Jan 9/14 1-4 Nov 18/08 1-5 Nov 18/08 1-6 Nov 18/08 1-7 Nov 18/08 1-8 Nov 18/08 2-1 Nov 21/08 2-2 Apr 30/2020 2-3 Nov 21/08 2-4 Nov 21/08 2-5 Nov 21/08 2-6 Nov 21/08 2-7 Nov 21/08 2-8 Nov 21/08 3-1 Dec 8/08 3-2 Apr 30/2020 3-3 Dec 8/08 3-4 Dec 8/08 3-5 Dec 8/08 3-6 Dec 8/08 3-7 Dec 8/08 3-8 Dec 8/08 4-1 Dec 8/08 4-2 Apr 30/2020 4-3 Dec 8/08 4-4 Dec 8/08 4-5 Dec 8/08 4-6 Dec 8/08 4-7 Dec 8/08 4-8 Dec 8/08 5-1 Nov 11/11 5-2 Apr 30/2020 5-3 Nov 11/11 5-4 Nov 11/11 5-5 Nov 11/11 5-6 Nov 11/11 5-7 Nov 11/11 5-8 Nov 11/11 6-1 Jan 9/14 6-2 Apr 30/2020 6-3 Jan 9/14 6-4 Jan 9/14 6-5 Jan 9/14 6-6 Jan 9/14 6-7 Jan 9/14 6-8 Jan 9/14 6-9 Jan 9/14 6-10 Jan 9/14 7-1 Apr 15/15 7-2 Apr 30/2020 7-3 Apr 15/15 7-4 Apr 15/15 7-5 Apr 15/15 7-6 Apr 15/15 7-7 Apr 15/15 7-8 Apr 15/15 7-9 Apr 15/15 7-10 Apr 15/15 7-11 Apr 15/15 7-12 Aug 28/17 7-13 Apr 15/15 7-14 Apr 15/15 7-15 Apr 15/15 7-16 Apr 15/15 7-17 Apr 15/15 7-18 Apr 15/15 8-1 Jan 15/19 8-2 Jan 15/19 8-3 Jan 15/19 8-4 Aug 28/17 8-5 Jan 15/19 8-6 Jan 15/19 ENSTROM F-28F/280F SERIES MAINTENANCE MANUAL SUPPLEMENT 1 Rev. 9 xii Apr 30/2020 EFFECTIVE PAGE LIST Page Date Page Date 8-7 Jan 15/19 8-8 Aug 28/17 8-9 Jan 15/19 8-10 Jan 15/19 8-11 Jan 15/19 8-12 Jan 15/19 8-13 Aug 28/17 8-14 Aug 28/17 8-15 Apr 30/2020 8-16 Apr 30/2020 8-17 Apr 30/2020 8-18 Apr 30/2020 8-19 Apr 30/2020 8-20 Apr 30/2020 8-21 Apr 30/2020 8-22 Apr 30/2020 8-23 Jan 15/19 8-24 Jan 15/19 9-1 Apr 30/2020 9-2 Apr 15/15 9-3 Apr 15/15 9-4 Apr 15/15 10-1 Aug 28/17 10-2 Apr 30/2020 10-3 Aug 28/17 10-4 Aug 28/17 10-5 Aug 28/17 10-6 Aug 28/17 10-7 Aug 28/17 10-8 Aug 28/17 10-9 Apr 30/2020 10-10 Apr 30/2020 10-11 Apr 30/2020 10-12 Apr 30/2020 11-1 Apr 30/2020 11-2 Aug 28/17 11-3 Aug 28/17 11-4 Aug 28/17 11-5 Aug 28/17 11-6 Aug 28/17 11-7 Aug 28/17 11-8 Aug 28/17 11-9 Jan 15/19 11-10 Jan 15/19 12-1 Jan 15/19 12-2 Jan 15/19 12-3 Jan 15/19 12-4 Jan 15/19 12-5 Jan 15/19 12-6 Apr 30/2020 12-7 Jan 15/19 12-8 Jan 15/19 12-9 Jan 15/19 12-10 Jan 15/19 12-11 Jan 15/19 12-12 Jan 15/19 13-1 Jan 15/19 13-2 Jan 15/19 13-3 Jan 15/19 13-4 Jan 15/19 13-5 Jan 15/19 13-6 Jan 15/19 13-7 Jan 15/19 13-8 Jan 15/19 13-9 Jan 15/19 13-10 Jan 15/19 ENSTROM F-28F/280F SERIES MAINTENANCE MANUAL SUPPLEMENT 1 Rev. 8 INTRO-1 Jan 15/19 INTRODUCTION Avionic System(s) Effectivity A. The data presented in this supplement is applicable to the optional avionic systems listed in the following table: Avionic System(s) Avionic System Enstrom Part Number Attitude Indicator 28-22062-( ) Collective Control Installation (Dual Start) 28-16080-101 Directional Gyro 28-22062-( ) GDL 69/69A 28-22082-( ) GMA 350Hc 28-22048-5 GNC 255A 28-22063-5 GNS 430W 28-22037-( ) GNS 530W 28-22050-( ) GTN 650 28-22112-3 GTX 330 28-22028-1 GTX 345 28-22028-3 KX 165A COMM/NAV 28-22063-( ) MD200-306 VOR/LOC/GS Indicator 28-22095-1 MD200-706 VOR/LOC/GS Indicator 28-22095-3 SAE5-35 Altitude Data System 28-22090-( ) SL30 28-22069-1 Aircraft Effectivity A. The data presented in this F-28F/280F Series Maintenance Manual Supplement is applicable to all Enstrom F-28F and 280F series model helicopters. Supplemental Changes and Revisions A. Subsequent to the publication of the initial issue of this supplement, changes in the avionics equipment, support concepts and procedures, as well as information developed by experience may affect the contents of this supplement. To ensure that coverage in the supplement continues to reflect such changes, revised information is released by one of the following methods: 1. Revision - A revision alters portions of the manual by replacement, addition, and/or removal of pages. 2. Reissue - A reissue of this supplement will occur when the amount of changes warrants complete reissue. ENSTROM F-28F/280F SERIES MAINTENANCE MANUAL SUPPLEMENT 1 Rev. 9 INTRO-2 Apr 30/2020 3. Service Directive Bulletins – Used to direct the owner/operator and/or maintenance personnel to make mandatory changes, improvements, or inspections to the aircraft applicable to the entire fleet or a segment of the fleet that are typically safety/airworthiness related. The information provided in the Service Directive Bulletins will be incorporated in the maintenance manual as needed at a later date. At the time of incorporation, the Service Directive Bulletin is superseded by the maintenance manual, and accomplishment or sign-off of the Service Directive Bulletin in the maintenance records book is no longer required. A detailed entry should be made in the maintenance records to indicate that the Service Directive Bulletin is superseded by the maintenance manual. 4. Service Information Letters – Used to transmit information, recommendations, and general service instructions to the aircraft owner/operator and/or maintenance personnel applicable to the entire fleet or a segment of the fleet. The information provided in the Service Information Letters will be incorporated into the maintenance manual as needed at a later date. 5. Service Instructions – Used to provide the owner/operator and/or maintenance personnel with information that is applicable to specific aircraft and does not meet the criteria of a Service Information Letter or Service Directive Bulletin. Service Instructions will not be distributed to the entire fleet. Enstrom distributes maintenance manual supplement revisions and reissues in electronic form via the Enstrom Helicopter website: www.enstromhelicopter.com (follow the applicable link under the Technical Publications section of the Technical Support page). Revision update notices are sent via email to owners and operators who are registered with Enstrom. Registration to receive publication mailing notifications can be coordinated through the Enstrom Technical Publications Administrator. A complete manual hardcopy may be ordered through Enstrom Customer Service. Service Information Letters and Service Directive Bulletins incorporated into the maintenance manual are logged in the Service Information Letter Index or the Service Directive Bulletin Index (as appropriate) located on the Enstrom Helicopter website: www.enstromhelicopter.com (follow the applicable link under the Technical Publications section of the Technical Support page). Each index numerically lists all Service Information Letters and Service Directive Bulletins, respectively, and identifies those which have been incorporated into the maintenance manual. All Service Information Letters and Service Directive Bulletins are also located under the Technical Publications section of the website. Notice of recently released Service Information Letters and Service Directive Bulletins is provided via email notification. Registration to receive publication mailing notifications can be coordinated through the Enstrom Technical Publications Administrator. ENSTROM F-28F/280F SERIES MAINTENANCE MANUAL SUPPLEMENT 1 Rev. 4 1-1 Jan 9/14 CHAPTER 1 SL30 NAV COM SECTION 1 SYSTEM DESCRIPTION 1-1. System Description A. The SL30 NAV/COM unit is a VHF Navigation/Communications Transceiver utilizing high performance Digital Signal Processing (DSP) filtering. It includes a 760- channel VHF Com transceiver and a 200-channel VOR/LOC/GS navigation receiver. B. Functions and features of the SL30 include automatic decoding of the Morse code station identifier for VOR/LOC, memory storage for most-used frequency, built-in course deviation indicator, standby Com and Nav frequency monitoring, Nav receiving for both VOR and LOC navigation signals, and built in Glideslope receiver. C. The components of the SL30 system include the panel mounted SL30 unit and nav and com antennas. The SL30 provides output to a VOR/LOC/GS Indicator and to either a VOX ICS or an audio panel. D. Power to the SL30 unit is provided via the COM circuit breaker (CB27) (5 Amp) and the NAV circuit breaker (CB39) (2 Amp) located on the left side of the center pedestal. E. Refer to the 280FX Rotorcraft Flight Manual Supplement and the current vendor operating manuals/instructions for operation of the SL30 system. 1-2. Vendor Publications A. The SL30 is to be operated and maintained I/A/W the current vendor’s instructions to ensure the continued airworthiness of the aircraft. The applicable vendor manuals are listed in Table 1-1. Table 1-1. Vendor Manuals Component Publication Vendor SL30 SL30 Nav Com Pilot’s Guide Garmin International 1200 E. 151 st Street Olathe, KS 66062 ENSTROM F-28F/280F SERIES MAINTENANCE MANUAL SUPPLEMENT 1 Rev. 9 1-2 Apr 30/2020 SECTION 2 AIRWORTHINESS LIMITATIONS 2-1. Airworthiness Limitations A. The Airworthiness Limitations Section is FAA approved and specifies inspections and other maintenance required under 14 CFR §§ 43.16 and 91.403 of the Federal Aviation Regulations unless an alternative program has been FAA approved. B. For EASA approval, the Airworthiness Limitations Section is approved and variations must also be approved. C. All components of the SL30 system are “on condition”. ENSTROM F-28F/280F SERIES MAINTENANCE MANUAL SUPPLEMENT 1 Rev. 1 2-1 Nov 21/08 CHAPTER 2 SANDIA SAE5-35 ALTITUDE DATA SYSTEM SECTION 1 SYSTEM DESCRIPTION 1-1. System Description A. The Sandia SAE5-35 is a solid state altitude data system (blind encoder) that converts pressure altitude into a digital output. The data output is referenced to 29.92 in Hg (1013 Millibars). B. The Sandia SAE5-35 outputs altitude data via Gillham Grey Code or two independent RS232 digital outputs to Mode C transponders. The transponders utilized include the Bendix/King KT73, KT76A, and KT76C; and the Garmin GTX327 and GTX330. C. Two configurations of the Sandia SAE5-35 system are available. They are part numbers 28-22090-1 and 28-22090-3. P/N 28-22090-1 is the standard system installation and P/N 28-22090-3 is the standard system with the “Altitude In-Flight Monitoring” function. D. Power to the Sandia SAE5-35 encoder is provided via the ENCDR circuit breaker (CB) (2 Amp) located on the lower left side of the center pedestal. E. Refer to the 280FX Rotorcraft Flight Manual Supplement and the current vendor operating manuals/instructions for operation of the Sandia SAE5-35 altitude data system. 1-2. Vendor Publications A. The Sandia SAE5-35 is to be operated and maintained I/A/W the current vendor’s instructions to ensure the continued airworthiness of the aircraft. The applicable vendor manuals are listed in Table 2-1. Table 2-1. Vendor Manuals Component Publication Vendor Sandia SAE5-35 1. SAE5-35 Pilot’s Guide, Document 305221 2. SAE5-35 Altitude Data System Installation Manual, Document 305186 Sandia Aerospace, Inc. 3700 Osuna Rd. NE, Suite 171 Albuquerque, NM 87109 ENSTROM F-28F/280F SERIES MAINTENANCE MANUAL SUPPLEMENT 1 Rev. 9 2-2 Apr 30/2020 SECTION 2 AIRWORTHINESS LIMITATIONS 2-1. Airworthiness Limitations A. The Airworthiness Limitations Section is FAA approved and specifies inspections and other maintenance required under 14 CFR §§ 43.16 and 91.403 of the Federal Aviation Regulations unless an alternative program has been FAA approved. B. For EASA approval, the Airworthiness Limitations Section is approved and variations must also be approved. C. All components of the Sandia SAE5-35 system are “on condition”. ENSTROM F-28F/280F SERIES MAINTENANCE MANUAL SUPPLEMENT 1 Rev. 2 3-1 Dec 8/08 CHAPTER 3 GNS 430W/530W GPS/WAAS NAVIGATOR SECTION 1 SYSTEM DESCRIPTION 1-1. System Description A. The 430W/530W GPS/WAAS Navigator is a panel-mounted product that contains a GPS/WAAS receiver for GPS approved primary navigation under TSO C146a, and also VHF Com and VHF Nav radios in an integrated system unit with a moving map and color display. The graphical display is used to depict traffic, weather, or terrain data. B. Four configurations of the 430W installation are available. They are part numbers 28-22037-5, 28-22037-7, 28-22037-9, and 28-22037-101. Four configurations of the 530W installation are available. They are part numbers 28-22050-5, 28-22050-7, 28- 22050-103, and 28-22050-105. The dash numbers differentiate between installations with or without VOR/LOC/GS activation and between installations that are upper or lower panel mounted. C. The 430W/530W provides optional output to a VOR/LOC/GS Indicator and to either a VOX ICS or an audio panel. D. Power to the 430W/530W unit is provided via the COMM/NAV GPS (28-22037- 5 or 28-22050-5) or the COMM GPS (28-22037-7 or 28-22050-7) circuit breaker (CB40) (5 Amp) and the COMM TX circuit breaker (CB41) (5 Amp) located on the left side of the lower panel. E. Refer to the 280FX Rotorcraft Flight Manual Supplement and the current vendor operating manuals/instructions for operation of the 430W/530W. 1-2. Vendor Publications A. The 430W/530W is to be operated and maintained I/A/W the current vendor’s instructions to ensure the continued airworthiness of the aircraft. The applicable vendor manuals are listed in Table 3-1. Table 3-1. Vendor Manuals Component Publication Vendor GNS 430W GNS 530W 1. 400W Series Pilot’s Guide and Reference 2. 400W Series Installation Manual 1. 500W Series Pilot’s Guide and Reference 2. 500W Series Installation Manual Garmin International 1200 E. 151 st Street Olathe, KS 66062 ENSTROM F-28F/280F SERIES MAINTENANCE MANUAL SUPPLEMENT 1 Rev. 9 3-2 Apr 30/2020 SECTION 2 AIRWORTHINESS LIMITATIONS 2-1. Airworthiness Limitations A. The Airworthiness Limitations Section is FAA approved and specifies inspections and other maintenance required under 14 CFR §§ 43.16 and 91.403 of the Federal Aviation Regulations unless an alternative program has been FAA approved. B. For EASA approval, the Airworthiness Limitations Section is approved and variations must also be approved. C. All components of the GNS 430W/530W are “on condition”. ENSTROM F-28F/280F SERIES MAINTENANCE MANUAL SUPPLEMENT 1 Rev. 2 4-1 Dec 8/08 CHAPTER 4 GDL 69/69A XM SATELLITE WEATHER/RADIO SECTION 1 SYSTEM DESCRIPTION 1-1. System Description A. The GDL 69/69A unit is a remote datalink receiver that delivers XM WX Satellite Weather™ to a Garmin navigation system such as the GNS 430W/530W. B. Two configurations of the GDL 69/69A installation are available. They are part numbers 28-22082-5 and 28-22082-7. Part number 28-22082-5 provides continuous XM Weather coverage and also XM Satellite Radio for audio entertainment. Part number 28- 22082-7 provides XM Weather only. C. The GDL 69A interfaces with the cockpit audio panel control to provide XM Satellite Radio audio entertainment through the aircraft’s audio system. D. Power to the GDL 69/69A unit is provided via the XM DL circuit breaker (CB42) (5 Amp) located on the left side of the lower panel. E. Refer to the 280FX Rotorcraft Flight Manual Supplement and the current vendor operating manuals/instructions for operation of the GDL 69/69A. 1-2. Vendor Publications A. The GDL 69/69A is to be operated and maintained I/A/W the current vendor’s instructions to ensure the continued airworthiness of the aircraft. The applicable vendor manuals are listed in Table 4-1. Table 4-1. Vendor Manuals Component Publication Vendor GDL 69/69A 400W/500W Series Pilot’s Guide Addendum for Optional Displays GDL 69/69A Installation Manual Garmin International 1200 E. 151 st Street Olathe, KS 66062 ENSTROM F-28F/280F SERIES MAINTENANCE MANUAL SUPPLEMENT 1 Rev. 9 4-2 Apr 30/2020 SECTION 2 AIRWORTHINESS LIMITATIONS 2-1. Airworthiness Limitations A. The Airworthiness Limitations Section is FAA approved and specifies inspections and other maintenance required under 14 CFR §§ 43.16 and 91.403 of the Federal Aviation Regulations unless an alternative program has been FAA approved. B. For EASA approval, the Airworthiness Limitations Section is approved and variations must also be approved. C. All components of the GDL 69/69A are “on condition”. ENSTROM F-28F/280F SERIES MAINTENANCE MANUAL SUPPLEMENT 1 Rev. 3 5-1 Nov 11/11 CHAPTER 5 ATTITUDE INDICATOR AND DIRECTIONAL GYRO SECTION 1 SYSTEM DESCRIPTION 1-1. System Description A. The Attitude Indicator Installation, P/N 28-22062-( ), provides an indication of the aircraft’s attitude relative to the earth by means of an electrically powered gyroscope. The unit is mounted in the instrument panel. Power to the attitude indicator is provided via the HRZN GYRO circuit breaker (CB23) located on the left side of the center pedestal. This installation consists of several configurations depending on the manufacturer (refer to Figure 5-1). B. The Directional Gyro Installation, P/N 28-22062-( ), provides a heading indication displayed on a rotating compass card by means of an electrically powered gyroscope. The unit is mounted in the instrument panel. Power to the directional gyro is provided via the DIR GYRO circuit breaker (CB24) located on the left side of the center pedestal. This installation consists of several configurations depending on the manufacturer (refer to Figure 5-1). C. Each gyro contains internal lighting and a power monitor indication. The attitude indicator contains a slip indicator attached to the base of the display bezel. 1-2. Vendor Manuals A. The following components listed in Table 5-1 are to be operated and maintained I/A/W the current vendor’s instructions to ensure the continued airworthiness of the aircraft. Table 5-1. Vendor Manuals Component Publication Vendor Attitude Gyro RCA 26 Series Installation/Operation Guide, Publication No. 1403 Kelly Manufacturing Company 555 South Topeka Wichita, KS 67202 www.kellymfg.com Slip Indicator for Model 300-14E(L) Part Number 6648-1009- 0901 Field Replacement or Installation of Inclinometer, 0050-1002, latest revision Castleberry Instruments & Avionics, Austin, TX www.ciamfg.com ENSTROM F-28F/280F SERIES MAINTENANCE MANUAL SUPPLEMENT 1 Rev. 9 5-2 Apr 30/2020 SECTION 2 AIRWORTHINESS LIMITATIONS 2-1. Airworthiness Limitations A. The Airworthiness Limitations Section is FAA approved and specifies inspections and other maintenance required under 14 CFR §§ 43.16 and 91.403 of the Federal Aviation Regulations unless an alternative program has been FAA approved. B. For EASA approval, the Airworthiness Limitations Section is approved and variations must also be approved. C. All components of the gyro systems are “on condition”. ENSTROM F-28F/280F SERIES MAINTENANCE MANUAL SUPPLEMENT 1 Rev. 4 6-1 Jan 9/14 CHAPTER 6 KX 165A NAV/COM SECTION 1 SYSTEM DESCRIPTION 1-1. System Description A. The KX 165A is a VHF NAV/COM transceiver. The KX 165A NAV/COM installation, P/N 28-22063-( ), includes the KX 165A NAV/COM unit, COM and NAV antennas, and the wiring interface to a VOR/LOC/GS indicator and an audio panel or VOX ICS. B. One of two configurations may be installed; P/N 28-22063-1 (760 channel COM, 25 kHz increments) and P/N 28-22063-3 (2280 channel COM; 8.33 kHz increments). C. Power to the KX 165A NAV/COM installation is provided via the COM1/NAV1 (or COM2/NAV2) circuit breaker (CB35, 7 ½ A) located on the upper left side of the center pedestal. D. Refer to the Rotorcraft Flight Manual Supplement for operation of the KX 165A. 1-2. Vendor Manuals A. The following component listed in Table 6-1 is to be operated and maintained I/A/W the current vendor’s instructions to ensure the continued airworthiness of the aircraft. Table 6-1. Vendor Manuals Component Publication Vendor KX 165A NAV/COM Installation Manual, Manual Number 006-10542-0003, Revision 3, or later approved revision Bendix/King (by Honeywell) 9201-B San Mateo Blvd. NE Albuquerque, New Mexico 87112 Support US & Canada: 855-250-7027 Support International: 602-365-7027 techsupport@bendixking.com ENSTROM F-28F/280F SERIES MAINTENANCE MANUAL SUPPLEMENT 1 Rev. 9 6-2 Apr 30/2020 SECTION 2 AIRWORTHINESS LIMITATIONS 2-1. Airworthiness Limitations A. The Airworthiness Limitations Section is FAA approved and specifies inspections and other maintenance required under 14 CFR §§ 43.16 and 91.403 of the Federal Aviation Regulations unless an alternative program has been FAA approved. B. For EASA approval, the Airworthiness Limitations Section is approved and variations must also be approved. C. All components of the KX 165A NAV/COM system are “on condition”. ENSTROM F-28F/280F SERIES MAINTENANCE MANUAL SUPPLEMENT 1 Rev. 5 7-1 Apr 15/15 CHAPTER 7 GTX 330 TRANSPONDER WITH ADS-B OUT SECTION 1 SYSTEM DESCRIPTION 1-1. System Description A. The GTX 330 with ADS-B Out is installed as part number 28-22028-1. The components of the GTX 330 installation include the panel-mounted GTX 330 unit and a bottom- mounted antenna. NOTE When combined, the Garmin GTX 330 with Extended Squitter (ES) and the Garmin GTN 650 GPS/NAV/COM have been shown to fully comply with AC 20-165A and 14 CFR 91.227 when installed in accordance with Garmin’s installation instructions. This configuration will be compliant with the 2020 ADS-B Out mandate defined in 14 CFR 91.225. B. For ADS-B Out system functionality, the GTX 330 is configured with the extended squitter (ES) feature and is interfaced with the GTN 650 for position input and the A-30 altitude encoder for barometric altitude input. The GTX 330 performs the following ADS-B Out functions: Transmission of ADS-B Out data on 1090 extended squitter (1090ES) (1090 MHz), Integration of data from internal and external sources to transmit data as required per 14 CFR 91.227, and Pressure Altitude Broadcast Inhibit. C. The GTX 330 may also be interfaced to other equipment such as an audio panel or VOX ICS and an OAT probe. D. Power to the GTX 330 installation is provided via the XPNDR circuit breaker (CB33) (5 Amp) located on the left side of the center pedestal. E. Refer to the F-28F/280FX Rotorcraft Flight Manual Supplement 28-AC-070 for GTX 330 with ADS-B Out limitations and basic operation instructions. F. The following component listed in Table 7-1 is to be operated and maintained I/A/W the current vendor’s instructions to ensure the continued airworthiness of the aircraft. Table 7-1. Vendor Manuals Component Publication Vendor GTX 330 Transponder GTX 330 Installation Manual, Document No 190-00207-02, latest revision Garmin International, Inc. 1200 East 151 st Street Olathe, KS 66062 Tele: (913) 397-8200 Fax: (913) 397-8282 www.garmin.com GTX 330 Pilot’s Guide, Document No. 190- 00207-00, latest revision GTX 330/D Maintenance Manual, Document No. 190-00207-05, latest revision ENSTROM F-28F/280F SERIES MAINTENANCE MANUAL SUPPLEMENT 1 Rev. 9 7-2 Apr 30/2020 SECTION 2 AIRWORTHINESS LIMITATIONS 2-1. Airworthiness Limitations A. The Airworthiness Limitations Section is FAA approved and specifies inspections and other maintenance required under 14 CFR §§ 43.16 and 91.403 of the Federal Aviation Regulations unless an alternative program has been FAA approved. B. For EASA approval, the Airworthiness Limitations Section is approved and variations must also be approved. C. All components of the GTX 330 with ADS-B Out system are “on condition.” No component- level overhaul is required for the GTX 330 with ADS-B Out installation. ENSTROM F-28F/280F SERIES MAINTENANCE MANUAL SUPPLEMENT 1 Figure 8-4. GTN 650 Configuration Set-Up (Ref. 28-19079-9 Rev. H) (NOTE: Refer to Paragraph 4-1-4 for SW applicability) (Sheet 1 of 3) Rev. 9, Apr 30/2020 8-15/8-16 Blank ENSTROM F-28F/280F SERIES MAINTENANCE MANUAL SUPPLEMENT 1 Figure 8-4. GTN 650 Configuration Set-Up (Ref. 28-19079-9 Rev. H) (NOTE: Refer to Paragraph 4-1-4 for SW applicability) (Sheet 2 of 3) Rev. 9, Apr 30/2020 8-17 ENSTROM F-28F/280F SERIES MAINTENANCE MANUAL SUPPLEMENT 1 Figure 8-4. GTN 650 Configuration Set-Up (Ref. 28-19079-9 Rev. H) (NOTE: Refer to Paragraph 4-1-4 for SW applicability) (Sheet 3 of 3) Rev. 9, Apr 30/2020 8-18 ENSTROM F-28F/280F SERIES MAINTENANCE MANUAL SUPPLEMENT 1 Diagram 8-1. GTN 650 Interface (Ref. 28-19079-9 Rev. H) (Sheet 1 of 2) Rev. 9, Apr 30/2020 8-19/8-20 Blank ENSTROM F-28F/280F SERIES MAINTENANCE MANUAL SUPPLEMENT 1 Diagram 8-1. GTN 650 Interface (Ref. 28-19079-9 Rev. H) (Sheet 2 of 2) Rev. 9, Apr 30/2020 8-21/8-22 Blank ENSTROM F-28F/280F SERIES MAINTENANCE MANUAL SUPPLEMENT 1 Rev. 9 9-1 Apr 30/2020 CHAPTER 9 DUAL START COLLECTIVE CONTROL INSTALLATION SECTION 1 SYSTEM DESCRIPTION 1-1. System Description A. The collective control with dual start installation option is part number 28-16080-101. B. The dual start feature allows the rotorcraft to be started from either the pilot or copilot positions. This is achieved with a momentary switch in the starboard-side collective stick. The switch is connected in parallel to the standard starting switch located in the port-side collective stick. The switch, when activated, closes the starter relay which then engages the starter motor. C. When configured with the dual start collective control installation, the starboard-side collective stick is not equipped with a quick disconnect feature. Installation of both port- and starboard-side collective sticks is identical. D. Refer to the applicable F-28F or 280FX Rotorcraft Flight Manual for limitations and basic operation instructions. SECTION 2 AIRWORTHINESS LIMITATIONS 2-1. Airworthiness Limitations A. The Airworthiness Limitations Section is FAA approved and specifies inspections and other maintenance required under 14 CFR §§ 43.16 and 91.403 of the Federal Aviation Regulations unless an alternative program has been FAA approved. B. For EASA approval, the Airworthiness Limitations Section is approved and variations must also be approved. C. All components of the collective control with dual start installation are “on condition.” SECTION 3 SERVICING, TROUBLESHOOTING, AND PERIODIC INSPECTIONS 3-1. Servicing, Troubleshooting, and Periodic Inspections A. Refer to the F-28F/280F Series Maintenance Manual for servicing, troubleshooting, and periodic inspection procedures for the flight controls and electrical systems. ENSTROM F-28F/280F SERIES MAINTENANCE MANUAL SUPPLEMENT 1 Rev. 5 9-2 Apr 15/15 SECTION 4 SYSTEM MAINTENANCE NOTE Removal or installation of equipment will change the aircraft empty weight and empty weight c.g. These changes will be recorded on Form F-511-5, Basic Weight and Balance Record, as required (reference Enstrom F-28F/280F Series Maintenance Manual). 4-1. Dual Start – Starboard-Side Collective Control (Figure 9-1) 4-1-1. Removal A. Remove the fiberglass seat deck. B. Disconnect the starter button wires at the connector terminals. C. Cut the safety wire and remove bolt (3) and washer (4) from the top of the collective stick socket (2). D. Remove the collective stick (1) from the collective stick socket (2). 4-1-2. Installation A. Install the collective stick (1) into the collective stick socket (2) and align holes. B. Install washer (4) and bolt (3). Torque bolt (50 in-lbs/5.7 Nm) and safety wire with MS20995C32. C. Connect the wire terminals for the starter button. D. Cycle the collective stick up and down and rotate the throttle to check freedom of movement. E. Install fiberglass seat deck. 4-2. Figures and Diagrams A. The dual start collective control installation is shown in Figure 9-1. B. The dual start collective control wiring interface is shown in Diagram 9-1. ENSTROM F-28F/280F SERIES MAINTENANCE MANUAL SUPPLEMENT 1 Rev. 7 10-1 Aug 28/17 CHAPTER 10 GNC 255A SECTION 1 SYSTEM DESCRIPTION 1-1. System Description A. The GNC 255A is a VHF communications transceiver combined with 200-channel VOR, LOC, and GS navigation receivers. The com radio operates from 118.000 to 139.975 MHz in either 25 kHz or 8.33 kHz channel spacing. Transmitting power is 10W. B. The GNC 255A installation part number is 28-22063-5. C. The components of the GNC 255A include the panel mounted GNC 255A unit and Nav and Com antennas. The GNC 255A may be interfaced with a CDI, slaved compass system, EHSI, or an EFIS system and may also be interfaced to either a VOX ICS or an audio panel. D. Power to the GNC 255A is provided via the COM circuit breaker (CB27) (5 Amp) and the NAV circuit breaker (CB39) (2 Amp) located on the left side of the lower instrument panel console. If equipped with a second transceiver unit (such as the GTN 650), power is provided via the COM 1 or COM 2 circuit breaker and NAV 1 or NAV 2 circuit breaker. The NAV circuit breaker may also provide power to the CDI. E. Refer to F-28F/280FX Rotorcraft Flight Manual Supplement 28-AC-074 for GNC 255A limitations and basic operation instructions. 1-2. Vendor Manuals A. The following components listed in Table 10-1 are to be operated and maintained I/A/W the current vendor’s instructions to ensure the continued airworthiness of the aircraft. Table 10-1. Vendor Manuals Component Publication Vendor GNC 255A GTR 255/GNC 255 Installation Manual, Document No. 190-01182-02, latest revision Garmin International, Inc. 1200 East 151 st Street Olathe, KS 66062 Tele: (913) 397-8200 Fax: (913) 397-8282 www.garmin.com GNC 255A/255B Pilot’s Guide, Document No. 190-01182-01, latest revision ENSTROM F-28F/280F SERIES MAINTENANCE MANUAL SUPPLEMENT 1 Rev. 9 10-2 Apr 30/2020 SECTION 2 AIRWORTHINESS LIMITATIONS 2-1. Airworthiness Limitations A. The Airworthiness Limitations Section is FAA approved and specifies inspections and other maintenance required under 14 CFR §§ 43.16 and 91.403 of the Federal Aviation Regulations unless an alternative program has been FAA approved. B. For EASA approval, the Airworthiness Limitations Section is approved and variations must also be approved. C. All components of the GNC 255A installation are “on condition.” ENSTROM F-28F/280F SERIES MAINTENANCE MANUAL SUPPLEMENT 1 Figure 10-2. GNC 255 Configuration Set-Up (Ref. 28-19069-103 Rev. D) Rev. 9, Apr 30/2020 10-9/10-10 Blank