Attachment EngineeringStatement

This document pretains to SAT-MOD-20160201-00009 for Modification on a Satellite Space Stations filing.

IBFS_SATMOD2016020100009_1124756

Engineering Statement 1 Introduction Intelsat License LLC (“Intelsat”) seeks authority in this application to operate the satellite designated as Intelsat 16 from 58.1° W.L. The characteristics of the Intelsat 16 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 the remainder of this Engineering Statement, which updates the gain contours and the operational frequency ranges and beams. In all other respects, the characteristics of Intelsat 16 are the same as those described in SAT-MOD-20150105-00003. 2 Spacecraft Overview Intelsat 16 is an Orbital Star-2 spacecraft that is capable of operating in Ku-band frequencies listed below. Direction Frequency 13750 – 14500 MHz Uplink 12750 – 13250 MHz 10700 – 11450 MHz Downlink 11700 – 12200 MHz The spacecraft provides the following coverage: Beam Coverage Mexico Mexico, Central America, the Caribbean, Puerto Rico, U.S. Mexico 2 Mexico, Central America Brazil Eastern Brazil Global Global 2.1 Spacecraft Characteristics Intelsat 16 is a three-axis stabilized type spacecraft that has a rectangular outer body structure. Intelsat 16 utilizes two deployable solar array wings and a number of deployable and non- deployable antennas. The Intelsat 16 spacecraft is composed of the following subsystems:  Thermal Page 1 of 9

 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 16 provides mechanical support for all subsystems. The structure supports the communication antennas, solar arrays, and the thrusters. It also provides a stable platform for preserving the alignment of critical elements of the spacecraft. 2.2 Communication Subsystem Intelsat 16 provides active communication channels at Ku-band frequencies. The Ku-band payload employs channels having a bandwidth of 36 MHz. The Intelsat 16 frequencies, polarization, and channel plan are provided in the Schedule S. The coverage contours and performance characteristics of all Intelsat 16 beams are provided in the Schedule S. Exhibits 1 and 2 provide the beam parameters for the Intelsat 16 uplink and downlink beams, respectively. 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 16 command and telemetry channel frequencies are shown in Exhibit 3. The coverage patterns of the 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. The Intelsat 16 command and telemetry subsystem performance is summarized in Exhibit 3. Page 2 of 9

2.4 Uplink Power Control Subsystem Intelsat 16 utilizes two Ku-band channels for uplink power control (“ULPC”), antenna tracking, and ranging. The coverage patterns of the ULPC beam has 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 this beam are not required to be provided and the associated GXT file has not been included in Schedule S. The Intelsat 16 ULPC frequencies and subsystem performance are summarized in Exhibit 3. 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 16 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 users, the transponders on Intelsat 16 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 10950 – 11200 MHz band are contained in Section 25.208 of the Commission’s rules. With respect to the frequency band 10700 - 11450 MHz, there are PFD limits specified in No. 21.16 of the ITU Radio Regulations. Neither the Commission’s rules nor the ITU Radio Regulations specify any PFD Page 3 of 9

limits for the 11700 – 12200 MHz band applicable to geostationary satellites operating in the fixed satellite service. The maximum PFD levels for the Intelsat 16 transmissions were calculated for the 10700– 11450 MHz bands. Since the Intelsat 16 telemetry and ULPC carriers are in the 11700 – 12200 MHz band where no PFD limits specified, PFD levels for this band were not calculated. The results are provided in Schedule S and show that the downlink power flux density levels of the Intelsat 16 carriers do not exceed the limits specified in Sections 25.208 of the Commission’s rules or the limits specified in No. 21.16 of the ITU Radio Regulations. 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 16 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 16 emissions. 6 Orbital Location Intelsat requests that it be assigned the 58.1° W.L. orbital location for Intelsat 16. The 58.1° W.L. location satisfies Intelsat 16 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 Coordination with Co-frequency Space Stations The Intelsat 16 transmissions will comply with the levels contained in Sections 25.212(c) of the Commission’s rules, as applicable, unless higher levels are coordinated with affected adjacent satellite operators within ±6. In any case, the uplink power density of the Intelsat 16 digital carriers will not exceed the levels specified below: a) 13750 – 14500 MHz: -44.8 dBW/Hz b) 12750 – 13250 MHz: -46.5 dBW/Hz The downlink EIRP density of Intelsat 16 digital carriers will not exceed the levels specified below: a) 10700 – 10950 and 11200 - 11450 MHz: -20.1 dBW/Hz b) 10950 – 11200 MHz -22.0 dBW/Hz c) 11700 – 12200: -19.6 dBW/Hz Page 4 of 9

8 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. 8.1 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. 8.2 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. Intelsat will ensure the removal of all stored energy on the spacecraft by depleting all propellant tanks, venting all pressurized systems, and turning off all active units. 8.3 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. Once relocated to 58.1° W.L., Intelsat 16 will not be located at the same orbital location as another satellite or at an orbital location that has an overlapping station-keeping volume with another satellite. During the relocation of Intelsat 16, Intelsat will take all the necessary steps to coordinate the move with other operators to minimize the risk of collision or interference between Intelsat 16 and any other 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 16. Intelsat is also not aware of any system with an overlapping station-keeping volume with Intelsat 16 that is the subject of an ITU filing and that is either in orbit or progressing towards launch. 8.4 Post Mission Disposal At the end of the mission, Intelsat expects to dispose of the spacecraft by moving it to a planned minimum altitude of 300 kilometers above the geostationary arc. This altitude exceeds the minimum altitude established by the Inter-Agency Space Debris Coordination Committee Page 5 of 9

(“IADC”) formula. Intelsat has reserved 6.8 kilograms of fuel for this purpose. The reserved fuel figure was determined by the spacecraft manufacturer and is provided for in the propellant budget. This figure was calculated taking into account the expected mass of the 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. In calculating the disposal orbit, Intelsat has used simplifying assumptions as permitted under the Commission’s Orbital Debris Report and Order.1 For reference, the effective area to mass ratio (Cr*A/M) of the Intelsat 16 spacecraft is 0.04 m2/kg, resulting in a minimum perigee disposal altitude under the IADC formula of at most 280.4 kilometers above the geostationary arc. Accordingly, the Intelsat 16 planned disposal orbit complies with the FCC’s rules. 9 TC&R Control Earth Stations Intelsat will conduct TC&R operations through one or more of the following earth stations: Castle Rock, Colorado and Fillmore, California. Additionally, Intelsat is capable of remotely controlling Intelsat 16 from its facilities in McLean, VA. 1 Mitigation of Orbital Debris, Second Report and Order, IB Docket No. 02-54, FCC 04-130 (rel. June 21, 2004). Page 6 of 9

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/ Candice DeVane January 21, 2016 Candice DeVane Date Intelsat Manager, Spectrum Policy Page 7 of 9

EXHIBIT 1 COMMUNICATION SUBSYSTEM UPLINK BEAM PARAMETERS Beam Name Ku-Band Linear Ku-Band Linear Ku-Band Linear Ku-Band Linear Schedule S Beam ID BHUL BVUL MHUL MVUL Frequency Band 13750 – 14500 & 13750 – 14500 & 13750 – 14500 & 13750 – 14500 & (MHz) 12750 – 13250 12750 – 13250 12750 – 13250 12750 – 13250 Polarization Horizontal Vertical Horizontal Vertical Beam Peak Gain 38.4 38.4 38.6 38.6 (dBi) G/T (dB/K) 11.3 11.3 11.5 11.5 Minimum SFD-- -108.3 -108.3 -108.5 -108.5 (dBW/m2) EXHIBIT 2 COMMUNICATION SUBSYSTEM DOWNLINK BEAM PARAMETERS Beam Name Ku-Band Linear Ku-Band Linear Ku-Band Linear Ku-Band Linear Ku-Band Linear Schedule S Beam ID BHDL BVDL MHDL MVDL M2DL Frequency Band 10700 – 11450 & 10700 – 11450 & 10700 – 11450 & 10700 – 11450 & 10700 – 11450 & (MHz) 11700 – 12200 11700 – 12200 11700 – 12200 11700 – 12200 11700 – 12200 Polarization Horizontal Vertical Horizontal Vertical Vertical Peak Antenna Gain 36.9 36.9 36.6 36.6 39.6 (dBi) EIRP (dBW) 54.5 54.5 54.2 54.2 57.2 Page 8 of 9

EXHIBIT 3 TC&R SUBSYSTEM CHARACTERISTICS Command Command Command Command Beam Name Omni Wide Coverage Global Global Schedule S Beam ID CMDO CMDW CMDH CMDV 13997.5 & 13997.5 & Frequencies (MHz) 13997.5 14499.5 14499.5 14499.5 Polarization LHCP LHCP Horizontal Vertical Peak Antenna Gain (dBi) 3.0 13.0 20.3 20.3 Telemetry Telemetry Telemetry Beam Name Wide ULPC ULPC Omni Global Coverage Schedule S Beam ID TLMO TLMW TLMH UPCH UPCV 12198.25 & 12198.25 & 12198.25 & Frequencies (MHz) 12119.75 11701.25 12198.75 12198.75 12198.75 Polarization RHCP RHCP Horizontal Horizontal Vertical Peak Antenna Gain (dBi) 3.0 13.0 21.3 21.0 21.0 Maximum Channel EIRP (dBW) 6.4 13.4 13.1 15.6 15.6 Note: RHCP: Right Hand Circular Polarization, LHCP: Left Hand Circular Polarization Page 9 of 9


Document Created: 2016-02-01 15:16:42
Document Modified: 2016-02-01 15:16:42
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