Attachment Engineering Statemt

This document pretains to SAT-MOD-20180103-00002 for Modification on a Satellite Space Stations filing.

IBFS_SATMOD2018010300002_1323349

Engineering Statement 1 Introduction Intelsat License LLC (“Intelsat”) seeks authority in this application to operate the satellite designated as Intelsat 1R (Call Sign S2368) from 157.1° E.L.1 The characteristics of the Intelsat 1R spacecraft, as well as its compliance with the various provisions of Part 25 of the Federal Communication Commission’s (“FCC or “Commission”) rules, are provided in this Engineering Statement, which updates the beam gain contours. In all other respects, the characteristics of Intelsat 1R are the same as those described in SAT-MOD- 20160219-00019. 2 Spacecraft Overview Intelsat 1R is a Boeing 702MP spacecraft that is capable of operating in the C-band and Ku-band frequencies listed below. Direction Frequency 5925 – 6425 MHz Uplink 13750 – 14500 MHz 3700 – 4200 MHz Downlink 10950 – 11200 MHz 11450 – 11950 MHz The spacecraft provides the following coverage: Band Beam Asia-Australia C-band East Pacific Global Asia Australia Ku-band East Pacific Combined Uplink Asia and East Pacific 1 Intelsat 1R currently is operating at 157.1° E.L. pursuant to STA. See Policy Branch Information; Actions Taken, Public Notice, Report No. SAT-01263, IBFS File No. SAT-STA-20170822- 00120 (Aug. 25, 2017). Page 1 of 12

2.1 Spacecraft Characteristics Intelsat 1R is a three-axis stabilized type spacecraft that has a rectangular outer body structure. Intelsat 1R utilizes two deployable solar array wings and a number of deployable and non- deployable antennas. The Intelsat 1R spacecraft is composed of the following subsystems:  Thermal  Power  Attitude Control  Propulsion  Telemetry, Command and Ranging  Uplink Power Control  Communications These subsystems maintain the correct position and attitude of the spacecraft; ensure that all internal units are maintained within the required temperature range; and ensure that the spacecraft can be commanded and controlled with a high level of reliability from launch to the end of its useful life. The spacecraft design incorporates redundancy in all of the various subsystems in order to avoid single-point failures. The structural design of Intelsat 1R provides mechanical support for all subsystems. The structure supports the communication antennas, solar arrays, and thrusters. It also provides a stable platform for preserving the alignment of critical elements of the spacecraft. 2.2 Communication Subsystem Intelsat 1R provides active communication channels at C-band and Ku-band frequencies, each having a bandwidth of 36 MHz. The Intelsat 1R frequencies, polarization, and channel plan are provided in Schedule S. The performance characteristics of all Intelsat 1R beams are provided in Schedule S. The coverage contours of all Intelsat 1R beams, except for those with their -8.0 dB contour extending beyond the edge of the Earth, are provided with Schedule S. Exhibit 1 provides the Schedule S beam designation for all beams. Exhibits 2 and 3 provide the beam parameters for the Intelsat 1R uplink and downlink beams, respectively. All of the bandwidth in each communication beam can be connected in loopback, wherein uplink channels in each uplink beam are connected to downlink channels in the downlink beam serving the same geographic area. Additionally, some C- or Ku-band channels in each beam can be interconnected with some C- or Ku-band channels in each of the other beams. Page 2 of 12

2.3 Telemetry, Command and Ranging Subsystem The telemetry, command and ranging (“TC&R”) subsystem provides the following functions: 1) Acquisition, processing and transmission of spacecraft telemetry data; 2) Reception and retransmission of ground station generated ranging signals; and 3) Reception, processing, and distribution of telecommands. The Intelsat 1R command and telemetry channel frequencies and performance are shown in Exhibit 4. The coverage patterns of the on-station command and telemetry beams are provided in the Schedule S. The coverage patterns of the bi-conical emergency command and telemetry beams have gain contours that vary by less than 8 dB across the surface of the Earth and accordingly the gain at 8 dB below the peak falls beyond the edge of the Earth. Therefore, pursuant to Section 25.114(c)(4)(vi)(A) of the FCC’s rules, contours for these beams are not required to be provided and the associated GXT files have not been included in Schedule S. 2.4 Uplink Power Control Subsystem Intelsat 1R utilizes one C-band channel and one Ku-band channel for uplink power control (“ULPC”), antenna tracking, and ranging. The coverage patterns of the ULPC beams have gain contours that vary by less than 8 dB across the surface of the Earth, and accordingly the gain at 8 dB below the peak falls beyond the edge of the Earth. Therefore, pursuant to Section 25.114(c)(4)(vi)(A) of the Commission’s rules, contours for these beams are not required to be provided and the associated GXT files have not been included in Schedule S. The Intelsat 1R ULPC frequencies and subsystem performance are summarized in Exhibit 4. 2.5 Satellite Station-Keeping The spacecraft will be maintained within 0.05° of its nominal longitudinal position in the east- west direction. Accordingly, it will be in compliance with Section 25.210(j) of the Commission’s rules. The attitude of the spacecraft will be maintained with accuracy consistent with the achievement of the specified communications performance, after taking into account all error sources (i.e., attitude perturbations, thermal distortions, misalignments, orbital tolerances and thruster perturbations, etc.). 3 Services Intelsat 1R is a general purpose communications satellite and has been designed to support various services offered within the Intelsat satellite system. Depending upon the needs of the Page 3 of 12

users, the transponders on Intelsat 1R can accommodate television, radio, voice, and data communications. Typical communication services include: a) Compressed digital video b) High speed digital data c) Digital single channel per carrier (“SCPC”) data channels Emission designators and allocated bandwidths for representative communication carriers are provided in Schedule S. 4 Power Flux Density The power flux density (“PFD”) limits for space stations operating in the 3700–4200 MHz, 10950–11200 MHz, and 11450-11700 MHz bands are contained in Section 25.208 of the Commission’s rules. Neither the Commission’s rules nor the ITU Radio Regulations specify any PFD limits for the 11700 – 11950 MHz band applicable to geostationary satellites operating in the Fixed Satellite Service. The maximum PFD levels for the Intelsat 1R transmissions were calculated for the 3700–4200 MHz, 10950–11200 MHz, and 11450-11700 MHz bands. The results are provided in Schedule S and show that the downlink power flux density levels of the Intelsat 1R carriers do not exceed the limits specified in Sections 25.208 of the Commission’s rules. 5 Emission Compliance Section 25.202(e) of the Commission’s rules requires that the carrier frequency of each space station transmitter be maintained within 0.002% of the reference frequency. Intelsat 1R is designed to be compliant with the provisions of this rule. Intelsat will comply with the provisions of Section 25.202(f) of the Commission’s rules with regard to Intelsat 1R emissions. 6 Orbital Location Intelsat requests that it be assigned the 157.1° E.L. orbital location for Intelsat 1R. The 157.1° E.L. location satisfies Intelsat 1R requirements for optimizing coverage, elevation angles, and service availability. Additionally, the location also ensures that the maximum operational, economic, and public interest benefits will be derived. 7 ITU Filings Intelsat 1R’s operations in the 3700-4200 MHz, 5925-6425 MHz, 10950-11200 MHz, 11450- 11950 MHz, and 14000-14500 MHz frequency bands have been notified under the Page 4 of 12

Administration of the United States’ International Telecommunication Union (“ITU”) filing INTELSAT7 157E. Intelsat 1R’s operations in the 13750-14000 MHz frequency band are being notified under the Administration of Papua New Guinea’s ITU filing NEW DAWN 47. Intelsat respectfully requests that the United States Administration state its non-objection to Papua New Guinea’s use of Intelsat 1R for purposes of bringing into use and maintaining the NEW DAWN 47 filing. 8 Coordination Statement and Certifications The downlink EIRP density of Intelsat 1R’s transmissions in the conventional C-band will not exceed 3 dBW/4kHz for digital transmissions or 8 dBW/4kHz for analog transmissions, and associated uplink transmissions will not exceed applicable EIRP density envelopes in Sections 25.218 or 25.221(a)(1) unless the non-routine uplink and/or downlink operation is coordinated with operators of authorized co-frequency space stations at assigned locations within six degrees of Intelsat 1R at 157.1° E.L. The downlink EIRP density of Intelsat 1R’s transmissions in the conventional and extended Ku- band will not exceed 14 dBW/4kHz for digital transmissions or 17 dBW/4kHz for analog transmissions, and associated uplink transmissions will not exceed applicable EIRP density envelopes in Sections 25.218, 25.222(a)(1), 25.226(a)(1), or 25.227(a)(1) unless the non-routine uplink and/or downlink operation is coordinated with operators of authorized co-frequency space stations at assigned locations within six degrees of Intelsat 1R at 157.1° E.L. Further, Intelsat will operate Intelsat 1R in compliance with all existing or future coordination agreements for 157.1 E.L. 9 Orbital Debris Mitigation Plan Intelsat is proactive in ensuring safe operation and disposal of this and all spacecraft under its control. The four elements of debris mitigation are addressed below. 9.1 Spacecraft Hardware Design The spacecraft is designed such that no debris will be released during normal operations. Intelsat has assessed the probability of collision with meteoroids and other small debris (<1 cm diameter) and has taken the following steps to limit the effects of such collisions: (1) critical spacecraft components are located inside the protective body of the spacecraft and properly shielded; and (2) all spacecraft subsystems have redundant components to ensure no single-point failures. The spacecraft does not use any subsystems for end-of-life disposal that are not used for normal operations. Page 5 of 12

9.2 Minimizing Accidental Explosions Intelsat has assessed the probability of accidental explosions during and after completion of mission operations. The spacecraft is designed in a manner to minimize the potential for such explosions. Propellant tanks and thrusters are isolated using redundant valves and electrical power systems are shielded in accordance with standard industry practices. At the completion of the mission and upon disposal of the spacecraft, Intelsat will ensure that all active units are turned off. However, due to the design of Intelsat 1R, Intelsat will not be able to vent all pressurized systems. Intelsat previously received waiver of Section 25.283(c) of the Commission’s rules, 47 C.F.R. § 25.283.2 9.3 Safe Flight Profiles Intelsat has assessed and limited the probability of the space station becoming a source of debris as a result of collisions with large debris or other operational space stations. At 157.1°E.L., Intelsat 1R will not be located at an orbital location that has an overlapping station-keeping volume with another satellite. Intelsat is not aware of any other FCC licensed system, or any other system applied for and under consideration by the FCC, that will have an overlapping station-keeping volume with Intelsat 1R. Intelsat is also not aware of any system with an overlapping station-keeping volume with Intelsat 1R that is the subject of an ITU filing and that is either in orbit or progressing towards launch. 9.4 Post Mission Disposal At the end of the mission, Intelsat will dispose of the spacecraft by moving it to an altitude of at least 297.4 kilometers above the geostationary arc. Intelsat has reserved 30.035 kilograms of xenon for that purpose. In calculating the disposal orbit, Intelsat has used simplifying assumptions as permitted under the Commission’s Orbital Debris Report and Order.3 The effective area to mass ratio (Cr*A/M) of the Intelsat 1R spacecraft is 0.0625 m2/kg, resulting in a minimum perigee disposal altitude under the Inter-Agency Space Debris Coordination Committee formula of 297.4 kilometers above the geostationary arc. Accordingly, the Intelsat 1R planned disposal orbit complies with the FCC’s rules. The reserved fuel figure was determined by the spacecraft manufacturer and provided for in the propellant budget. This figure was calculated taking into account the expected mass of the 2 See PanAmSat Licensee Corp. Application to Modify License for Intelsat 1R, IBFS File No. SAT- MOD-20090720-00073, ¶ 8 (stamp grant issued by Steve Duall on Aug. 5, 2010). 3 Mitigation of Orbital Debris, Second Report and Order, 19 FCC Rcd. 11567 (2004). Page 6 of 12

satellite at the end of life and the required delta-velocity to achieve the desired orbit. The fuel gauging uncertainty has been taken into account in these calculations. 10 TC&R Control Earth Stations Intelsat will conduct TC&R operations through one or more of the following earth stations: Kumsan, South Korea; Mingenew, Australia; and Paumalu, Hawaii. Additionally, Intelsat is capable of remotely controlling Intelsat 1R from its facilities in McLean, VA. Page 7 of 12

Certification Statement I hereby certify that I am a technically qualified person and am familiar with Part 25 of the Commission’s rules. The contents of this engineering statement were prepared by me or under my direct supervision and to the best of my knowledge are complete and accurate. /s/ Alexander Gerdenitsch January 3, 2018 Alexander Gerdenitsch Date Intelsat Manager, Spectrum Policy, Americas Page 8 of 12

EXHIBIT 1 Beam Polarizations and GXT File Names Schedule S Beam GXT File Names Linear Polarization Circular Polarization Beam Description Uplink Uplink Downlink Downlink Uplink Uplink Downlink Downlink (H-Pol.) (V-Pol.) (H-Pol.) (V-Pol.) (LHCP) (RHCP) (LHCP) (RHCP) C-Band Beams Global Beam GCHU* ---- ---- GCVD* ---- ---- ---- ---- Asia-Australia ACHU ACVU ACHD ACVD ---- ---- ---- ---- East Pacific ---- ECVU ECHD ---- ---- ---- ---- ---- ULPC (Global) ---- ---- ---- ---- ---- ---- UPCR* Ku-Band Beams NKHD Asia NKHU NKVU NKVD ---- ---- ---- ---- NKHE Australia SKHU SKVU SKHD S1VD ---- ---- ---- ---- Australia ---- ---- ---- S2VD ---- ---- ---- ---- EKVD East Pacific EKHU EKVU EKHD ---- ---- ---- ---- EKVE Asia & E. Pacific ---- CKVU ---- ---- ---- ---- ---- ---- Telemetry ---- ---- TLMB* TLMC* ---- ---- TLMP* ---- Command CMDC* CMDB* ---- ---- CMDP* ---- ---- ---- ULPC (Global) ---- ---- ---- ---- ---- ---- UPCL* ---- * GXT files are not provided for the indicated beams because their -8 dB gain contours extend beyond the edge of the Earth. Page 9 of 12

EXHIBIT 2 COMMUNICATION SUBSYSTEM UPLINK BEAM PARAMETERS Beam Asia & Australia East Pacific Global Schedule S Beam ID ACHU ACVU ECVU GCHU Frequency Band (MHz) 5925 – 6425 5925 – 6425 5925 – 6425 5925 – 6425 Polarization Horizontal Vertical Vertical Horizontal G/T (dB/K) 1.4 1.3 1.2 -8.2 2 Minimum SFD-- (dBW/m ) -99.3 -98.4 -94.9 -88.8 Maximum SFD-- -69.3 -68.4 -64.9 -58.8 (dBW/m2) Beam Asia Australia Schedule S Beam ID NKHU NKVU SKVU SKHU Frequency Band (MHz) 13750 – 14500 13750 - 14500 13750 - 14500 13750 - 14500 Polarization Horizontal Vertical Vertical Horizontal G/T (dB/K) 6.8 6.8 6.5 6.1 2 Minimum SFD-- (dBW/m ) -104.8 -104.2 -104.6 -104.1 Maximum SFD-- -74.8 -74.2 -74.6 -74.1 (dBW/m2) Asia & East Beam East Pacific Pacific Schedule S Beam ID EKHU EKVU CKVU Frequency Band (MHz) 13750 - 14500 13750 - 14500 13750 - 14500 Polarization Horizontal Vertical Vertical G/T (dB/K) 6.6 4.8 6.5 Minimum SFD-- -104.9 -102.9 -104.3 (dBW/m2) Maximum SFD-- -74.9 -72.9 -74.3 (dBW/m2) Page 10 of 12

EXHIBIT 3 COMMUNICATION SUBSYSTEM DOWNLINK BEAM PARAMETERS Beam Asia & Australia East Pacific Global Schedule S Beam ID ACHD ACVD ECHD GCVD Frequency Band (MHz) 3700 - 4200 3700 - 4200 3700 - 4200 3700 - 4200 Polarization Horizontal Vertical Horizontal Vertical Maximum Beam Peak EIRP (dBW) 43.7 43.4 41.9 34.6 Maximum Beam Peak EIRP Density 4.6 4.3 2.8 -4.5 (dBW/4kHz) Maximum Beam Peak EIRP Density -31.4 -31.7 -33.2 -40.5 (dBW/Hz) Beam Asia Australia Schedule S Beam ID NKHD NKHE NKVD SKHD Frequency Band (MHz) 10950 – 11200 11450 – 11700 10950 – 11200 11700 - 11950 Polarization Horizontal Horizontal Vertical Horizontal Maximum Beam Peak EIRP (dBW) 50.9 50.9 50.3 52.9 Maximum Beam Peak EIRP Density 11.8 11.8 11.2 13.8 (dBW/4kHz) Maximum Beam Peak EIRP Density -24.2 -24.2 -24.8 -22.2 (dBW/Hz) Beam Australia Australia East Pacific Schedule S Beam ID S1VD S2VD EKHD Frequency Band (MHz) 11700 - 11950 11450 - 11700 11450 - 11700 Polarization Vertical Vertical Horizontal Maximum Beam Peak EIRP (dBW) 53.0 52.1 52.3 Maximum Beam Peak EIRP Density 13.9 13 13.2 (dBW/4kHz) Maximum Beam Peak EIRP Density -22.1 -23 -22.8 (dBW/Hz) Beam East Pacific Schedule S Beam ID EKVD EKVE Frequency Band (MHz) 10950 – 11200 11450 – 11700 Polarization Vertical Vertical Maximum Beam Peak 50.3 50.3 EIRP (dBW) Maximum Beam Peak 11.2 11.2 EIRP Density (dBW/4kHz) Maximum Beam Peak -24.8 -24.8 EIRP Density (dBW/Hz) Page 11 of 12

EXHIBIT 4 TC&R SUBSYSTEM CHARACTERISTICS Command Command Command Beam Name East Asia Bicone Pipe Schedule S Beam ID CMDC CMDB CMDP Center Frequencies (MHz) 13995.0 13995.0 14498.5 Command Carrier Bandwidth (MHz) 1.0 1.0 1.0 Polarization Horizontal Vertical LHCP Peak Flux Density at Command -122.9 -100.1 -103.0 Threshold (dBW/m2-Hz) Telemetry Telemetry Telemetry Beam Name ULPC ULPC East Asia Bicone Pipe Schedule S Beam ID TLMC TLMB TLMP UPCR UPCL 11696.0 & 11696.0 & 11696.0 & Frequencies (MHz) 11699.0 11699.0 11697.0 11697.0 11697.0 Polarization Vertical Horizontal LHCP RHCP LHCP Maximum Channel EIRP (dBW) 15.0 11.8 10.7 11.2 11.2 Channel Bandwidth (MHz) 0.5 0.5 0.5 .025 .025 Maximum Beam Peak EIRP -6 -9.2 -10.3 3.2 3.2 Density (dBW/4kHz) Maximum Beam Peak EIRP -42 -45.2 -46.3 -32.8 -32.8 Density (dBW/Hz) Note: RHCP: Right Hand Circular Polarization, LHCP: Left Hand Circular Polarization Page 12 of 12


Document Created: 2018-01-03 11:56:53
Document Modified: 2018-01-03 11:56:53
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