Attachment Narrative

This document pretains to SAT-LOA-20121002-00173 for Application to Launch and Operate on a Satellite Space Stations filing.

IBFS_SATLOA2012100200173_968173

                                    Before the
                      FEDERAL COMMUNICATIONS COMMISSION
                               Washington, D.C. 20554


In the Matter of Application of               )
                                              )
SES Americom, Inc.                            )      File No. SAT-LOA-__________
                                              )
For Authority to Launch and Operate an        )
Expansion Satellite at 129.1° W.L.            )

                         APPLICATION OF SES AMERICOM, INC.

               SES Americom, Inc. (“SES Americom,” doing business as “SES”), hereby applies

for authority under the Communications Act of 1934, as amended, and the Federal

Communications Commission’s regulations thereunder, to launch and operate a conventional

Ku-band1 expansion satellite at the nominal 129° W.L. orbital location,2 to be designated SES-

129W. A completed FCC Form 312 is attached, and technical information relating to the

proposed spacecraft is provided on Schedule S and in narrative form pursuant to Section 25.114

of the Commission’s Rules.

               In a decision released last week, the Commission announced that it was making

the Ku-band spectrum at the nominal 129° W.L. orbital location available for filing.3 This

application is being filed in response to that announcement. SES-129W will make Ku-band

satellite capacity available for a range of high quality video, broadband and data services,

including direct-to-home (“DTH”) services. Grant of this application is in the public interest




1
    The “conventional Ku-band” refers to the 11.7-12.2 GHz and 14.0-14.5 GHz frequencies.
2
   To facilitate joint stationkeeping with collocated spacecraft, SES proposes to operate SES-
129W at a slight offset from 129° W.L., specifically at 129.1º W.L.
3
   See Intelsat Licensee LLC, Memorandum Opinion and Order, DA 12-1532, File No. SAT-
MSC-20100628-00160 (Sat. Div. rel. Sept. 25, 2012) at ¶ 18.


because it will permit SES to make new capacity available to customers at the nominal 129° W.L.

orbital location.


                                        INTRODUCTION

                SES Americom is a pioneer and leading provider of satellite services in the

United States. Headquartered in Princeton, New Jersey, SES Americom and its affiliates provide

U.S. and international satellite services through a fleet of over 50 geosynchronous

communications satellites. SES Americom (then known as RCA American Communications,

Inc.) launched its first domestic communications satellite in December 1975. Today, SES and its

affiliates operate two dozen satellites with coverage of the United States, providing satellite

capacity for broadcast and cable video distribution, VSAT data networks, remote

communications, and the U.S. government.

                Broadcasters, cable systems and programmers use SES satellites both to distribute

programming and for specialized satellite newsgathering services. SES established one of the

first cable satellite “neighborhoods” more than 20 years ago, and today distributes cable

television programming for the major cable networks. Virtually every U.S. cable and Direct

Broadcast Satellite (“DBS”) household receives some of its programming via the SES fleet. SES

also has one of the largest satellite “neighborhoods” for the U.S. radio programming industry.

                Dozens of specialized satellite-based communication networks have been

designed, installed, maintained and serviced by SES for government organizations as diverse as

the Department of State, NASA, NOAA, and the U.S. Armed Forces.4 The company’s satellites

are also used to help provide basic voice, data and Internet communications to remote areas. As



4
   Government services are provided by SES Americom’s wholly-owned subsidiary,
Americom Government Services, Inc., d/b/a SES Government Solutions.


                                                 2


the demand increases for high-quality telecommunications, SES technical experts continue to

develop innovative and cost-effective solutions to address customers’ evolving needs.


                   INFORMATION REQUIRED BY SECTION 25.114(c)

               The information required by Section 25.114(c) is contained in the Schedule S

database being submitted with this application, as supplemented by the narrative Technical

Appendix.


                   INFORMATION REQUIRED BY SECTION 25.114(d)

               The information required by Section 25.114(d) is contained herein and in the

narrative Technical Appendix being submitted with this application.


                          PUBLIC INTEREST CONSIDERATIONS

               Launch and operation of SES-129W will serve the public interest by enabling

SES to make Ku-band satellite capacity available for a variety of high-quality video, broadband

and data services to the North American market. Among other things, SES-129W would enable

SES to augment the DBS capacity on Ciel-2 at 128.85° W.L. (operated by SES’s Canadian

affiliate, Ciel Satellite L.P.) with conventional Ku-band DTH capacity.5 Grant of authority for

SES-129W is therefore consistent with Commission precedent and with policies designed to

maximize the efficient use of spectrum and orbital resources.

               Like other satellites in the SES Americom fleet, SES will commercialize the

satellite capacity on SES-129W on a non-common carrier basis by negotiating contracts

individually with its customers.

5
     See SES Americom, Inc., Order and Authorization, 18 FCC Rcd 16589 (Int’l Bur. 2003) at
¶ 1 (authorizing the use of SES Americom’s fleet for DTH would “promote fair and increased
competition in the provision of satellite service in the United States” and would “provide benefits
to the public by maximizing consumer choice.”).


                                                3


                                         CONCLUSION

               SES is requesting here, and in the related materials attached hereto, authority to

launch and operate the SES-129W expansion satellite at the nominal 129º W.L. orbital location

in order to permit SES to introduce new service to customers. SES submits that the public

interest, convenience, and necessity will be served by a grant, in accordance with this

Application, of authority to launch and operate the proposed satellite.

                                              Respectfully submitted,

                                              SES AMERICOM, INC.

                                              By: /s/ Daniel C.H. Mah

Of Counsel                                       Daniel C.H. Mah
Karis A. Hastings                                Regulatory Counsel
SatCom Law LLC                                   SES Americom, Inc.
1317 F Street, N.W., Suite 400                   Four Research Way
Washington, D.C. 20004                           Princeton, NJ 08540
Tel: (202) 599-0975

Dated: October 2, 2012




                                                 4


                                ATTACHMENT A




      TECHNICAL APPENDIX


IN SUPPORT OF SES-129K (129.1W.L.)




                 1


                              TECHNICAL APPENDIX

1.0     Overall Description
The SES Americom satellite SES-129K is a Ku-band communications satellite designed for
operations from the 129.1° W.L. orbital location with coverage of the Contiguous USA, Alaska,
Hawaii, Mexico, and parts of Canada and the Caribbean.


The spacecraft will operate in the standard Ku-band frequencies with downlink frequencies from
11.7 to 12.2 GHz and uplink frequencies from 14.0 to 14.5 GHz.


Dual linear polarization is used in the uplink and downlink direction, and the downlink can also
be operated in circular polarization.


Table 1 shows the frequency plan of the satellite. The frequency bands are divided into 24 Ku-
band transponders of 36 MHz bandwidth each.

2.0     Schedule S

The Schedule S database is attached as an electronic file.
The following items supplement the information provided in Schedule S.
      1. Transponder frequency plan.
Sections S9 and S10 of Schedule S show the transponder frequency plans. Beams with IDs
KRV, KTV, KRH, KTH, KTR and KTL provide coverage over CONUS, Mexico, Alaska,
Hawaii, and parts of Canada and the Caribbean.
Transponders K01 to K24 connect beams KRH and KTV, and beams KRV and KTH, while
transponders K25 to K48 connect beams KRH to KTR and beams KRV to KTL.




                                                 2


                 Table 1: Ku-band Frequency Plan
Channel    Receive      Polarization      Transmit   Polarization
          Frequency                      Frequency
            (MHz)                          (MHz)
   1        14020            H             11720       V/RHC
   2        14040            V             11740       H/LHC
   3        14060            H             11760       V/RHC
   4        14080            V             11780       H/LHC
   5        14100            H             11800       V/RHC
   6        14120            V             11820       H/LHC
   7        14140            H             11840       V/RHC
   8        14160            V             11860       H/LHC
   9        14180            H             11880       V/RHC
  10        14200            V             11900       H/LHC
  11        14220            H             11920       V/RHC
  12        14240            V             11940       H/LHC
  13        14260            H             11960       V/RHC
  14        14280            V             11980       H/LHC
  15        14300            H             12000       V/RHC
  16        14320            V             12020       H/LHC
  17        14340            H             12040       V/RHC
  18        14360            V             12060       H/LHC
  19        14380            H             12080       V/RHC
  20        14400            V             12100       H/LHC
  21        14420            H             12120       V/RHC
  22        14440            V             12140       H/LHC
  23        14460            H             12160       V/RHC
  24        14480            V             12180       H/LHC




                                 3


   2. TWTA redundancy.
   Ku-band
The communications receivers are configured in a 4-for-2 redundancy (as a minimum) with
cross-strapping between polarizations and coverage beams such that any two receivers can
complete the mission. Each transponder has a useable bandwidth up to 36 MHz, and is operated
using single or dual Traveling Wave Tube Amplifiers (TWTAs) of 150W output power. The
spacecraft carries a total of 64 payload TWTAs operated with 48 active/16 spares in dual TWTA
mode.


   3. Saturation Flux Density values.
SFD values can be obtained by using the expression:
   SFD = -94 – (G/T) +Transponder Gain Setting, dBW/m2


   4. Transponder frequency response.
The frequency response and total group delay, specified over the transponder bandwidth, are
provided in Tables 2 and 3 below.



                    Table 2: Ku-band Transponder Frequency Response
                                            Frequency Offset (MHz)     dB p-p
                                                     ±14                1.2
                36 MHz channel                       ±16                1.5
                                                     ±18                3.6



                      Table 3: Ku-band Transponder Total Group Delay
                                Frequency Offset (MHz)      Relative Group Delay (ns p-p)
                                           0                             6.0
                                          ±8                             9.0
     36 MHz channel                      ±12                            16.0
                                         ±16                            45.0
                                         ±18                            85.0




                                               4


    5. Telemetry and Telecommand (TT&C) frequencies and beams.
Table 4 shows the TT&C carrier center frequencies and bandwidths.

                              Table 4: TT&C Carrier Frequencies1
                                       Frequency, MHz                Nominal polarization
                          Command carriers (bandwidth: 800 kHz)
          Ku-band                       14499.0                               H
                          Beacons/Telemetry (bandwidth: 400 kHz)
        Ku-band pair                    11701.0                              H/LHC
                                        12199.0                              V/RHC

    5.1 Command carrier characteristics and link budgets
    1. Bandwidth (2-sided): 800 kHz
    2. Capture range (2-sided): 2.0 MHz
    3. Transmit earth station sidelobe envelope: 29 – 25 log , dB
    4. Uplink power flux at the satellite:
        -92 dBW/m2 to -60 dBW/m2


Table 5 shows the command carrier link budgets in the Ku-band.


                       Table 5: Ku-band Command Carrier Link Budget

                     S13.d.                                      K_TC
                     Tx ES dia (typical), m                           8.4
                     Tx ES gain, dBi                                  60.2
                     Tx ES antenna input power, dBW                    10
                     Tx ES EIRP, dBW                                  70.2
                     Link loss, dB                                   207.5
                     Satellite G/T, dB/K                                3
                     Command carrier bandwidth, MHz                   0.8
                     Tx ES antenna input power density, dBW/Hz        -50
                     Carrier-to-Noise Ratio, dB                       35.3
                     Required CNR, dB                                  10
                     Margin                                           25.3




1
       SES Americom will advise the Commission of any changes to these frequencies after
coordination has been completed.

                                                5


5.2 Telemetry/Beacon carrier link budgets
Table 6 shows telemetry link budgets, with a typical EIRP of 19 dBW in the coverage area.


                              Table 6: Ku-band Telemetry Link Budget

                     S13.d.                                         K_TM
                     EIRP, dBW                                        19
                     Carrier bandwidth, MHz                           0.4
                     EIRP density, dBW/4kHz                          -1.00
                     Tx ES dia (typical), m                           5.7
                     Rx ES antenna gain, dB                          55.0
                     Rx ES G/T, dB/K                                 34.6
                     Rain fade, dB                                     8
                     CNR, dB                                         11.18
                     CNR (required), dB                                9
                     Margin, dB                                       2.2

3.0   Satellite Antenna Gain Contours

Annex 1 shows the antenna gain contours for the 6 different antenna beams: transmit and
receive beams, H- and V-polarizations for Ku-band, and also LHCP and RHCP polarizations for
Ku-band transmit beams. Table 7 shows the correspondence between peak gains of the antennas
and maximum EIRP or G/T values.

                     Table 7: Maximum Co-pol Gain, EIRP and G/T Values
                                                   Ku-band          Ku-band
                                               H-pol V-pol LHCP- RHCP-
                                                                 pol      pol
            Transmit beam Gain (max.), dBi      33.5     33.5   33.5      33.5
                             EIRP (max.), dBW   54.8     54.8   54.8      54.8
            Receive beam     Gain (max.), dBi    35       35     n/a       n/a
                             G/T (max), dB/K     7.6      7.6    n/a       n/a

These files with co-pol data are also provided as gxt files in Schedule S:

       1.   KRH.gxt (H-pol, Ku-band receive beam)
       2.   KTH.gxt (H-pol, Ku-band transmit beam)
       3.   KRV.gxt (V-pol, Ku-band receive beam)
       4.   KTV.gxt (V-pol, Ku-band transmit beam)
       5.   KTL.gxt (LHCP-pol, Ku-band transmit beam)
       6.   KTR.gxt (RHCP-pol, Ku-band transmit beam)



                                                 6


4.0   Emission Designators and Link Budgets

The services provided by SES-129K will be wide ranging, including digital TV and digital
transmission services ranging from 56 KBPS to high-speed. Sample link budgets for these
services follow. Table 8 provides the characteristics of the earth stations used for this analysis
and estimated link margins for Ku-band carriers. Table 9 shows analog TV/FM (emission
designator 36M0F3F) link budgets for Ku-band.




                                                 7


                           Table 8: Ku-band Link Budgets for 7 Typical Links
S13.c.                                K_A        K_B          K_C      K_D        K_E        K_F        K_G
                                     Digital TV Digital TV                                           Digital TV
                                       MCPC       MCPC     Digital TV Digital TV                       MCPC
                                      40 Mbps    32 Mbps     SCPC       SCPC      56 Kbps 1.544 Mbps  50 Mbps
Parameter                           QPSK ¾ RS QPSK ¾ RS QPSK ¾ RS QPSK ¾ RS QPSK ¾ RS QPSK ¾ RS 8PSK ⅔ RS
Carrier designation                 36M0G7W 27M0G7W 6M95G1W 5M00G1W              100KG1W  1M60G1W 36M0G7W
Data Rate (dB-Hz)                        76         75         69        67.6       47.5     61.9        77
Throughput rate (Mbps)                   40         32          8          6       0.056     1.544       50
Symbol rate (Msps)                      28.8       22.9       5.7         4.2      0.041     1.117      27.2
Uplinks:
Transmit Power (dBW)                    20         20           8.9      8.9        -2          8         20
Transmit Loss (dB)                     -2.5       -2.5         -2.5     -2.5       -2.5       -2.5       -2.5
Antenna diameter (m)                    6.1        6.1          3.7      3.7        1.8        1.8        6.1
Antenna Gain (dBi)                     57.3       57.3         53.0     53.0       46.7       46.7       57.3
Ground Station EIRP (dBW)              74.8       74.8         59.4     59.4       42.2       52.2       74.8
Uplink Rain Loss (dB)                   -2         -2           -2       -2         -2         -2         -2
Free Space Loss (dB)                   -207       -207         -207     -207       -207       -207       -207
Satellite G/T (dB/K)                     3          3            3        3          3          3          3
Boltzmann’s Constant (dBW/K-Hz)       -228.6     -228.6       -228.6   -228.6     -228.6     -228.6     -228.6
Eb/N0 (dB)                             21.4       22.4         13.0     14.4       17.3       12.9       20.4
Eb/I0 (dB)                              18         18           16       16         16         16         18
Total Eb/(N0 + I0) (dB)                16.4       16.7         11.2     12.1       13.6       11.2       16.0
Downlinks:
Satellite Carrier EIRP (dBW)           52.5       51.3         42.4     40.9       23.9       36.0       52.5
Interference bandwidth (MHz)            36         27          6.95       5         0.1        1.6        36
Satellite EIRP density (dBW/4KHz)      12.96      12.96        9.96     9.96       9.96       9.96       12.96
Downlink Rain Loss (dB)                 -3         -3           -3       -3         -3         -3         -3
Free Space Loss (dB)                  -205.4     -205.4       -205.4   -205.4     -205.4     -205.4     -205.4
Ground station antenna dia (m)          1.2        1.2          2.4      2.4        1.2        2.4        2.4
Ground Station G/T (dB/K)              20.9       20.9         26.9     26.9       20.9       26.9       26.9
Eb/N0 (dB)                             17.6       17.4         20.5     20.5       17.5       21.2       22.6
C/IM (dB)                                                       18       18         18         18
Eb/Imo (dB)                                                    16.6     16.6       16.6       16.6
C/I (dB)                                15         15           15       15         15         15        15
Eb/I0 (ASI) (dB)                       13.6       13.6         13.6     13.6       13.6       13.6      12.3
Eb/I0 (dB)                             13.6       13.6         13.6     13.6       13.6       13.6      12.3
Eb/(N0 + I0) (dB)                      12.1       12.1         11.3     11.3       10.8       11.4      12.0
Total Up/Down Eb/(N0+Io)(dB)           10.8       10.8          8.2      8.7        9.0        8.3      10.5
Required Eb/N0 (dB)                     5.4        5.4          5.4      5.4        5.4        5.4       7.2
Margin (dB)                             5.4        5.4          2.8      3.3        3.6        2.9       3.3




                                                          8


 Table 9: Ku-band Link Budgets for TV/FM

S13.d.                              K_H
                                    Ku-band
                                    Typical
Parameter                         TV/FM link
Carrier designation                36M0F3F
Uplinks:
Transmit Power (dBW)                  22
Transmit Loss (dB)                    -1
Antenna diameter (m)                  6.1
Antenna Gain (dBi)                   57.3
Ground Station EIRP (dBW)            78.3
Uplink Rain Loss (dB)                 -2
Free Space Loss (dB)                 -207
Satellite G/T (dB/K)                   3
Bandwidth (dB-Hz)                    75.6
Boltzmann’s Constant (dBW/K-Hz)     -228.6
C/N, uplink (dB)                     25.4
Downlinks:
Satellite Carrier EIRP (dBW)         52.5
Downlink Rain Loss (dB)               -3
Free Space Loss (dB)                -205.4
Ground station antenna dia (m)        1.2
Ground Station G/T (dB/K)            20.9
C/N, DL (dB)                         18.0
C/I ASI (dB)                          18
C/Ntot, dB                           15.0
Required (dB)                         11
Margin (dB)                           4.0




                      9


5.0     Power Flux Density limits

FCC Part 25.208 does not specify power flux density limits in the 11.7-12.2 GHz frequency
band.

6.0     Cessation of Emissions

Each TWTA is commandable to apply or remove RF drive of the associated amplifier as
required under § 25.207. Each TWTA can also be commanded on and off, although they are
normally powered for the entire mission, after the satellite arrives on station.

7.0     Interference Analysis

Annex 2 shows the results of an interference analysis for operations in a 2-degree spacing
environment.

8.0     Maximum Operational Levels

SES-129K will be operated consistently with coordination agreements with adjacent satellites.
In any case, in the Ku band frequencies, the downlink EIRP density of the SES-129K digital
carriers will not exceed -19 dBW/Hz in the 11.7-12.2 GHz band; and the input power density of
the uplink digital carriers of earth stations operating with SES-129K in the 14.0-14.5 GHz band
will not exceed -47 dBW/Hz.

9.0     Mitigation of Orbital Debris

This section provides the information required under Section 25.114(d)(14) of the Commission’s
Rules.


§ 25.114(d)(14)(i): SES Americom has assessed and limited the amount of debris released in a
planned manner during normal operations of SES-129K. During the satellite ascent, after
separation from the launcher, no debris would be generated. As with all recent SES Americom
satellite launches, all deployments would be conducted using pyrotechnic devices designed to
retain all physical debris. No debris is generated during normal on-station operations, and the
spacecraft will be in a stable configuration. On-station operations require stationkeeping within
the +/- 0.05 degree N-S and E-W control box, thereby ensuring adequate collision avoidance
                                                 10


distance from other satellites in geosynchronous orbit. In the event that co-location of this and
another satellite is required, use of the proven Inclination-Eccentricity (I-E) separation method
can be employed. This strategy is presently in use by SES to ensure proper operation and safety
of multiple satellites within one orbital box.


SES Americom has also assessed and limited the probability of the space station becoming a
source of orbital debris by collisions with small debris or meteoroids that could cause loss of
control and prevent post-mission disposal. The design of SES Americom's recent spacecraft
locates all sources of stored energy within the body of the structure, which provides protection
from small orbital debris. SES Americom requires that spacecraft manufacturers assess the
probability of micrometeorite damage that can cause any loss of functionality. This probability
is then factored into the ultimate spacecraft probability of success. Any significant probability of
damage would need to be mitigated in order for the spacecraft design to meet SES Americom’s
required probability of success of the mission. SES Americom has taken steps to limit the
effects of any collisions through shielding, the placement of components, and the use of
redundant systems.


§ 25.114(d)(14)(ii): SES Americom has assessed and limited the probability of accidental
explosions during and after completion of mission operations. As part of the Safety Data
Package submission for SES Americom spacecraft, an extensive analysis is completed by the
spacecraft manufacturer, reviewing each potential hazard relating to accidental explosions. A
matrix is generated indicating the worst-case effect, the hazard cause, and the hazard controls
available to minimize the severity and the probability of occurrence. Each subsystem is analyzed
for potential hazards, and the Safety Design Package is provided for each phase of the program
running from design phase, qualification, manufacturing and operational phase of the spacecraft.
Also, the spacecraft manufacturer generates a Failure Mode Effects and Criticality Analysis for
the spacecraft to identify all potential mission failures. The risk of accidental explosion is
included as part of this analysis. This analysis indicates failure modes, possible causes, methods
of detection, and compensating features of the spacecraft design.


The design of the SES-129K spacecraft is such that the risk of explosion is minimized both
during and after mission operations. In designing and building the spacecraft, the manufacturer
takes steps to ensure that debris generation will not result from the conversion of energy sources
                                                 11


on board the satellite into energy that fragments the satellite. All propulsion subsystem pressure
vessels, which have high margins of safety at launch, have even higher margins in orbit, since
use of propellants and pressurants during launch decreases the propulsion system pressure. Burst
tests are performed on all pressure vessels during qualification testing to demonstrate a margin of
safety against burst. Bipropellant mixing is prevented by the use of valves that prevent
backwards flow in propellant and pressurization lines. All pressures, including those of the
batteries, will be monitored by telemetry.


At the end of operational life, after the satellite has reached its final disposal orbit, all on-board
sources of stored energy will be depleted or secured, and the batteries will be discharged.


§ 25.114(d)(14)(iii): SES Americom has assessed and limited the probability of the space station
becoming a source of debris by collisions with large debris or other operational space stations.
Specifically, SES Americom has assessed the possibility of collision with satellites located at, or
reasonably expected to be located at, the requested orbital location or assigned in the vicinity of
that location.


Regarding avoidance of collisions with controlled objects, in general, if a geosynchronous
satellite is controlled within its specified longitude and latitude stationkeeping limits, collision
with another controlled object (excluding where the satellite is collocated with another object) is
the direct result of that object entering the allocated space.


The instant application seeks authority for operation of SES-129K at the 129.1° W.L. orbital
location. SES Americom is not aware of any other FCC- or non-FCC licensed spacecraft that are
operational or planned to be deployed at the nominal 129° W.L. or to nearby orbital locations
such that there would be an overlap with the requested stationkeeping volume of SES-129K.
Ciel 2 operates at 128.85° W.L. and Galaxy-12 operates at 129.0° W.L., both with a
stationkeeping box of 0.05°.


SES uses the Space Data Center (“SDC”) system from the Space Data Association to monitor the
risk of close approach of its satellites with other objects. Any close encounters (separation of
less than 5 km.) are flagged and investigated in more detail. If required, avoidance maneuvers
are performed to eliminate the possibility of collisions.
                                                   12


During any relocation, the moving spacecraft is maneuvered such that it is at least 30 km away
from the synchronous radius at all times. In most cases, much larger deviation from the
synchronous radius is used. In addition, the SDC system is used to ensure no close encounter
occurs during the move.


When de-orbit of a spacecraft is required, the initial phase is treated as a satellite move, and the
same precautions are used to ensure collision avoidance.


§ 25.114(d)(14)(iv): Post-mission disposal of the satellite from operational orbit will be
accomplished by carrying out maneuvers to a higher orbit. The upper stage engine remains part
of the satellite, and there is no re-entry phase for either component. The fuel budget for
elevating the satellite to a disposal orbit is included in the satellite design.


SES Americom plans to maneuver SES-129K to a disposal orbit with a minimum perigee of
288.9 km above the normal operational altitude. The proposed disposal orbit altitude complies
with the altitude resulting from application of the IADC formula based on the following
calculation:


        Area of the satellite (average aspect area): 66.0 m2
        Mass of the spacecraft: 2346.0 kg
        CR (solar radiation pressure coefficient): 1.15


Therefore the Minimum Disposal Orbit Perigee Altitude, as calculated under the IADC formula
is:


36,021 km + (1000 x CR x A/m) = 36074.9 km, or 288.9 km above the GSO arc (35,786 km)


SES Americom intends to reserve 28.8 kg of fuel in order to account for post-mission disposal of
SES-129K. SES Americom has assessed fuel gauging uncertainty and has provided an adequate
margin of fuel reserve to address the assessed uncertainty.




                                                   13


   ANNEX 1



COVERAGE MAPS




      14


Figure 1. Ku-band, Transmit beam, LHCP-pol (KTL)
 EIRP max. 54.8 dBW, Antenna gain max. 33.5 dBi

                                                                            -20.00

          -8.00
        -10.00
                                    -6.00                                       -20.00
                                               -15.00                                          -10.00
                                                                        -8.00




                                            -2.00                                              -10.00 -20.00
                                                                                     -2.00
                                                                             0.00
                                                                                              -15.00
                                                                -4.00
                          -20.00                                                                  -20.00
                       -6.00                                -2.00
                  -15.00
                      -4.00-20.00
                    -10.00                                          -2.00             -6.00
                                                                                   -8.00
                                                         -4.00
                      -8.00
                  -20.00                                -15.00
                                                               -20.00




                                     15


Figure 2. Ku-band, Transmit beam, RHCP-pol (KTR)
 EIRP max. 54.8 dBW, Antenna gain max. 33.5 dBi

                                                                            -20.00

          -8.00
        -10.00
                                    -6.00                                       -20.00
                                               -15.00                                          -10.00
                                                                        -8.00




                                            -2.00                                              -10.00 -20.00
                                                                                     -2.00
                                                                             0.00
                                                                                              -15.00
                                                                -4.00
                          -20.00                                                                  -20.00
                       -6.00                                -2.00
                  -15.00
                      -4.00-20.00
                    -10.00                                          -2.00             -6.00
                                                                                   -8.00
                                                         -4.00
                      -8.00
                  -20.00                                -15.00
                                                               -20.00




                                     16


Figure 3. Ku-band, Receive beam, H-pol (KRH)
 G/T max 7.6 dB/K, Antenna Gain max 35 dBi

                                                                          -20.00

        -8.00
      -10.00
                                  -6.00                                       -20.00
                                             -15.00                                          -10.00
                                                                      -8.00




                                          -2.00                                              -10.00 -20.00
                                                                                   -2.00
                                                                           0.00
                                                                                            -15.00
                                                              -4.00
                        -20.00                                                                  -20.00
                     -6.00                                -2.00
                -15.00
                    -4.00-20.00
                  -10.00                                          -2.00             -6.00
                                                                                 -8.00
                                                       -4.00
                    -8.00
                -20.00                                -15.00
                                                             -20.00




                                   17


Figure 4. Ku-band, Receive beam, V-pol (KRV)
 G/T max 7.6 dB/K, Antenna Gain max 35 dBi

                                                                          -20.00

        -8.00
      -10.00
                                  -6.00                                       -20.00
                                             -15.00                                          -10.00
                                                                      -8.00




                                          -2.00                                              -10.00 -20.00
                                                                                   -2.00
                                                                           0.00
                                                                                            -15.00
                                                              -4.00
                        -20.00                                                                  -20.00
                     -6.00                                -2.00
                -15.00
                    -4.00-20.00
                  -10.00                                          -2.00             -6.00
                                                                                 -8.00
                                                       -4.00
                    -8.00
                -20.00                                -15.00
                                                             -20.00




                                   18


Figure 5. Ku-band, Transmit beam, H-pol (KTH)
EIRP max 54.8 dBW, Antenna Gain max 33.5 dBi

                                                                          -20.00

        -8.00
      -10.00
                                  -6.00                                       -20.00
                                             -15.00                                          -10.00
                                                                      -8.00




                                          -2.00                                              -10.00 -20.00
                                                                                   -2.00
                                                                           0.00
                                                                                            -15.00
                                                              -4.00
                        -20.00                                                                  -20.00
                     -6.00                                -2.00
                -15.00
                    -4.00-20.00
                  -10.00                                          -2.00             -6.00
                                                                                 -8.00
                                                       -4.00
                    -8.00
                -20.00                                -15.00
                                                             -20.00




                                   19


Figure 6. Ku-band, Transmit beam, V-pol (KTV)
EIRP max 54.8 dBW, Antenna Gain max 33.5 dBi

                                                                          -20.00

        -8.00
      -10.00
                                  -6.00                                       -20.00
                                             -15.00                                          -10.00
                                                                      -8.00




                                          -2.00                                              -10.00 -20.00
                                                                                   -2.00
                                                                           0.00
                                                                                            -15.00
                                                              -4.00
                        -20.00                                                                  -20.00
                     -6.00                                -2.00
                -15.00
                    -4.00-20.00
                  -10.00                                          -2.00             -6.00
                                                                                 -8.00
                                                       -4.00
                    -8.00
                -20.00                                -15.00
                                                             -20.00




                                   20


       ANNEX 2

INTERFERENCE ANALYSIS
IN SUPPORT OF SES-129K




          21


                                    Two-degree Spacing Analysis


The only operational Ku-band satellite adjacent to the 129.1° W.L. position is SPTVJSAT/Intelsat’s
Horizons 1 at 127° W.L. with more than 2° geocentric separation. There is not a Ku-band satellite
at 131° W.L. SES Americom will assess the coordination status of the US ITU filing at 129° W.L.
and commence coordination discussions with SPTVJSAT/Intelsat as needed. It is expected that any
outstanding coordination with SPTVJSAT/Intelsat will be concluded without major problems.


Satellite transponders of SES-129K will be operated at power levels no higher than that allowed by
the FCC, or generally coordinated with adjacent satellite operators.


The following analysis will demonstrate that the SES-129K network is compatible with a co-
coverage, co-frequency satellite, spaced 2 degrees away. This analysis has been performed for
digital signals in both networks. Analog TV/FM signals are coordinated on a case-by-case basis
with nearby spacecraft, and are therefore not addressed in this analysis. Digital signals are more
robust and operate typically down to much lower C/N ratios than analog signals. They are therefore
more tolerant of interference, thereby improving the ability to coordinate at 2º orbital spacing.


1      Uplink analysis
This scenario addresses uplink interference between digital carriers in both the wanted and victim
satellite networks. The analysis assumes that the transponder gains can be matched to give similar
wanted input signal spectral density levels at the two satellites. The Uplink C/I will be a function of
the difference between the gain of the transmitting earth station antennas at boresight and the gain at
the off-axis (topocentric) angle.


1.1   Ku-band uplink C/I estimates


The topocentric angle for a geocentric separation of 2º is approximately 2.2º. The sidelobe
envelope at 2.2º off boresight for an antenna that meets the 29-25 log () reference pattern is
20.9 dBi. The boresight gain will be a function of the size of the transmitting earth station antenna.
The following Table A.1 lists the boresight gain, the off-axis gain and the corresponding C/I that
would result in this interference scenario:


                                                  22


                  Table A.1: Ku-band uplink C/I for 2-degree geocentric spacing
               Antenna size (m)      On-axis gain (dBi)     Off-axis gain      C/I (dB)
               1.2                   43.04                  20.94              22.09
               1.8                   46.56                  20.94              25.61
               2.4                   49.06                  20.94              28.11
               4.5                   54.52                  20.94              33.57
               6.0                   57.02                  20.94              36.07


Assuming that the minimum (i.e., threshold) C/N for a digital service is 8 dB, the effect of the C/I
(22.09 dB) from the 1.2 meter earth station in Table A.1 above would only degrade the C/N by
0.17 dB, equivalent to an increase of 3.9% in the victim system’s noise temperature. This is less
than the ITU coordination trigger criteria; i.e., internationally, if a 6% increase in noise temperature
is not exceeded, then coordination is not triggered between the concerned networks.


2      Downlink analysis
This scenario addresses downlink interference between digital carriers in both the wanted and
victim satellite networks. The analysis assumes that the EIRPs of the two satellites are either
similar, or the wanted network has an EIRP of 2 dB lower than SES-129K. Similar to the uplink,
the downlink C/I will be a function of the difference between the gain of the receiving earth station
antennas at boresight and the gain at the off-axis angle, as well as any difference in EIRP between
the two networks.


The topocentric angle for a geocentric separation of 2º is approximately 2.2º. The gain at 2.2º off
boresight for an antenna that meets the 29-25 log () reference pattern is 20.9 dBi. The boresight
gain will be a function of the size of the receiving earth station antenna.


The following tables list the boresight gain, the off-axis gain and the corresponding C/I that would
result in this interference scenario, where the EIRP of the two networks is similar (Table A.2) and
where the EIRP of the two networks is different by 2 dB (Table A.3):




                                                   23


                   Table A.2: Ku-band downlink C/I for 2-degree geocentric spacing
                       EIRP of the wanted and interfering satellites is the same

       Antenna size (m)       On-axis gain (dBi)     Off-axis gain      Off-axis       C/I (dB)
                                                                        discrimination
                                                                        (dB)
       1.2                    41.70                  20.94              20.75          20.75
       1.8                    45.22                  20.94              24.27          24.27
       2.4                    47.72                  20.94              26.77          26.77
       4.5                    53.18                  20.94              32.23          32.23
       6.0                    55.68                  20.94              34.73          34.73


                 Table A.3: Ku-band downlink C/I for 2-degree geocentric spacing
             EIRP of the wanted satellite is 2 dB lower than that of the interfering satellite

       Antenna size (m)       On-axis gain (dBi)     Off-axis gain      Off-axis       C/I (dB)
                                                                        discrimination
                                                                        (dB)
       1.2                    41.70                  20.94              20.75          18.75
       1.8                    45.22                  20.94              24.27          22.27
       2.4                    47.72                  20.94              26.77          24.77
       4.5                    53.18                  20.94              32.23          30.23
       6.0                    55.68                  20.94              34.73          32.73


Again, assuming that the minimum (i.e., threshold) C/N for a digital service is 8 dB, the effect of
the C/I (18.75 dB) into the 1.2 meter earth station in Table A.3 above would only degrade the C/N
by 0.35 dB, equivalent to an increase of 8.4% in the victim system’s noise temperature. Although
this does exceed the normal criteria of 6% by a small amount, the victim system’s link degradation
is still less than 0.5 dB, which is significantly less than the likely link margin.


3.      Additional examples of C/I estimates based on Horizons 1
Tables A.4 to A.7 show some examples of single-entry C/I analysis for typical carriers on the
satellite networks. The adjacent satellite is assumed to be Horizons 1 at 127 W.L., but the same




                                                    24


results apply to a theoretical 131 W.L neighbor also. Basic carrier information and earth station
antenna sizes for Horizons 1 were pulled from data on file with the Commission.2


Tables A.4 and A.5 show downlink C/I estimates into SES-129K and into the adjacent satellite
carriers, respectively. The C/I values of the adjacent carriers are at least 18 dB.


Tables A.6 and A.7 show uplink C/I estimates into SES-129K and into the adjacent satellite
carriers, respectively. The C/I values of the adjacent carriers are minimally about 21 dB.




2
 See Horizons Satellite LLC, File No. SAT-PDR-20030210-00015, Petition for Declaratory Ruling,
Appendix A Exhibit A-1.

                                                   25


  Table A.4: Downlink C/I into SES-129K carriers at 129.1 W.L. from Horizons 1 at 127 W.L.


Downlink C/I analysis            Adjacent into SES                              SES Carriers
Ku-band                                                                         Emission                       36M0G7W 6M95G1W 5M00G1W 1M60G1W                 100KG1W
                                                                                Bandwidth                        30.00   5.79    4.17    1.33                     0.08
Orbital Position : SES Americom       129.1                                     Receive Earth Station (m)         1.2     1.2     1.2     1.2                      1.2
Orbital Position Adjacent Satellite   127.0                                     Satellite EIRP                   54.8    54.8    54.8    54.8                     54.8
Geocentric Separation                  2.0                                      Downlink EIRP density            -20.0   -23.8   -23.8   -23.8                   -23.8
Topocentric Separation                 2.2                                      RX Earth Station Gain            41.7    41.7    41.7    41.7                     41.7
                                                                                Sidelobe Characteristic          29.0    29.0    29.0    29.0                     29.0
                                                                                Off-axis Gain                    20.4    20.4    20.4    20.4                     20.4

Adjacent Satellite Carriers
Emission             Satellite   Bandw. (MHz)     Downlink Receive Earth        Sidelobe        Off-axis         C/I          C/I          C/I         C/I       C/I
                     EIRP                         EIRP     Ant. (m) Station     Charact.         Gain
                                                  density           Gain
36M0G7W                 51.8          30.0          -23.0    1.8      45.2           29          20.4            24.3         20.5         20.5        20.5      20.5
6M00G7W                 51.8           5.0          -26.8    3.7      51.5           29          20.4            28.0         24.3         24.3        24.3      24.3
1M45G7W                 51.8           1.2          -26.8    1.8      45.2           29          20.4            28.0         24.3         24.3        24.3      24.3
200KG7W                 51.8           0.2          -26.8    2.4      47.7           29          20.4            28.0         24.3         24.3        24.3      24.3
100KG7W                 51.8           0.1          -26.8    2.4      47.7           29          20.4            28.0         24.3         24.3        24.3      24.3
400KG7W                 51.8           0.3          -26.8    6.1      55.8           29          20.4            28.0         24.3         24.3        24.3      24.3



         Table A.5: Downlink C/I into Horizons 1 at 127 W.L. from SES-129K at 129.1 W.L.
Downlink C/I analysis                   SES Americom into Adjacent                   SES Carriers
Ku-band                                                                              Emission                    36M0G7W 6M95G1W 5M00G1W 1M60G1W 100KG1W
                                                                                     Bandwidth                     30.00   5.79    4.17    1.33     0.08
Orbital Position : SES Americom               129.1                                  Receive Earth Station (m)      1.2     1.2     1.2     1.2     1.2
Orbital Position Adjacent Satellite           127.0                                  Satellite EIRP                54.8    54.8    54.8    54.8     54.8
Geocentric Separation                          2.0                                   Downlink EIRP density         -20.0   -24.8   -24.8   -24.8   -24.8
Topocentric Separation                         2.2                                   RX Earth Station Gain         41.7    41.7    41.7    41.7     41.7
                                                                                     Sidelobe Characteristic       29.0    29.0    29.0    29.0     29.0
                                                                                     Off-axis Gain                 20.4    20.4    20.4    20.4     20.4

Adjacent Satellite Carriers
Emission             Satellite EIRP     Bandw.        Downlink Receive Earth         Sidelobe       Off-axis            C/I         C/I          C/I     C/I      C/I
                                        (MHz)         EIRP     Ant. (m) Station      Charact.        Gain
                                                      density           Gain
36M0G7W                      51.8             30.0       -23.0     1.8        45.2         29           20.4           21.8         26.6     26.6       26.6     26.6
6M00G7W                      51.8             5.0        -26.8     3.7        51.5         29           20.4           24.2         29.0     29.0       29.0     29.0
1M45G7W                      51.8             1.2        -26.8     1.8        45.2         29           20.4           18.0         22.8     22.8       22.8     22.8
200KG7W                      51.8             0.2        -26.8     2.4        47.7         29           20.4           20.5         25.3     25.3       25.3     25.3
100KG7W                      51.8             0.1        -26.8     2.4        47.7         29           20.4           20.5         25.3     25.3       25.3     25.3
400KG7W                      51.8             0.3        -26.8     6.1        55.8         29           20.4           28.6         33.4     33.4       33.4     33.4




                                                                                     26


     Table A.6: Uplink C/I into SES-129K carriers at 129.1 W.L. from Horizons 1 at 127 W.L.

Uplink C/I analysis                             Adjacent into SES                  SES Carriers
Ku-band                                                                            Emission                         36M0G7W   6M95G1 5M00G1W 1M60G1W 100KG1W
                                                                                   Bandwidth (MHz)                    30.00      W
                                                                                                                               5.79    4.17    1.33     0.08
                                                                                   Satellite FTS                      -87.0    -87.0   -87.0   -87.0   -87.0
                                                                                   Uplink EIRP                        76.0     64.1    62.6    57.7     45.6
Orbital Position : SES Americom                    129.1                           Uplink Power (max) (feed inp.)     18.7     11.1    15.9    11.0      2.5
Orbital Position Adjacent Satellite                127.0                           Uplink Power density (feed)        -56.1    -56.5   -50.3   -50.3   -46.8
Geocentric Separation                               2.0                            Uplink Earth Station (m)            6.1      3.7     1.8     1.8      1.2
Topocentric Separation                              2.2                            Earth Station Gain                 57.3     53.0    46.7    46.7     43.2
                                                                                   Upl. EIRP density                   1.2      -3.6    -3.6    -3.6    -3.6
                                                                                   Sidelobe Characteristic            29.0     29.0    29.0    29.0     29.0
                                                                                   Off-axis Eirp density              -35.6    -36.1   -29.8   -29.8   -26.3


Adjacent Satellite Carriers
Emission             Bandw.      Satellite      Uplink EIRP    Uplink     Transm. Earth      Sidelobe   Off-axis       C/I     C/I     C/I     C/I     C/I
                     (MHz)       FTS                           Eirp       Ant. (m) Station   Charact.   Eirp
                                                               density             Gain                 density
36M0G7W                 30.0          -86.0         77.0           2.2       6.1     57.3         29        -34.6     35.9     31.1    31.1    31.1    31.1
6M00G7W                  5.0          -86.0         64.4          -2.6       6.1     57.3         29        -39.4     40.7     35.9    35.9    35.9    35.9
1M45G7W                  1.2          -86.0         58.3          -2.6       6.1     57.3         29        -39.4     40.7     35.9    35.9    35.9    35.9
200KG7W                  0.2          -86.0         49.7          -2.6       6.1     57.3         29        -39.4     40.7     35.9    35.9    35.9    35.9
100KG7W                  0.1          -86.0         46.6          -2.6       6.1     57.3         29        -39.4     40.7     35.9    35.9    35.9    35.9
400KG7W                  0.3          -86.0         52.7          -2.6        3      51.1         29        -33.3     34.5     29.7    29.7    29.7    29.7




             Table A.7: Uplink C/I into Horizons 1 at 127 W.L. from SES-129K at 129.1 W.L
Uplink C/I analysis                           SES into Adjacent                   SES Carriers
Ku-band                                                                           Emission                          36M0G7W 6M95G1W 5M00G1W 1M60G1W 100KG1W
                                                                                  Bandwidth (MHz)                     30.00   5.79    4.17    1.33     0.08
                                                                                  Satellite FTS                       -87.0   -87.0   -87.0   -87.0   -87.0
                                                                                  Uplink EIRP                         76.0    68.1    66.6    61.7     49.6
Orbital Position : SES Americom                  129.1                            Uplink Power (max) (feed inp.)      18.7    15.1    19.9    15.0     6.5
Orbital Position Adjacent Satellite              127.0                            Uplink Power density (feed)         -56.1   -56.5   -50.3   -50.3   -46.8
Geocentric Separation                             2.0                             Uplink Earth Station (m)             6.1     3.7     1.8     1.8     1.2
Topocentric Separation                            2.2                             Earth Station Gain                  57.3    53.0    46.7    46.7     43.2
                                                                                  Upl. EIRP density                    1.2     -3.6    -3.6    -3.6    -3.6
                                                                                  Sidelobe Characteristic             29.0    29.0    29.0    29.0     29.0
                                                                                  Off-axis Eirp density               -35.6   -36.1   -29.8   -29.8   -26.3

Adjacent Satellite Carriers
Emission             Bandw. Satellite Uplink EIRP             Uplink     Transm. Earth       Sidelobe   Off-axis      C/I      C/I      C/I     C/I    C/I
                     (MHz) FTS                                Eirp       Ant. (m) Station    Charact.   Eirp
                                                              density             Gain                  density
36M0G7W                 30.0     -88.0            75.0            0.2       6.1     57.3          29        -36.6     35.9     36.3    30.1    30.1    26.5
6M00G7W                 5.0      -88.0            62.4           -4.6       6.1     57.3          29        -41.4     31.1     31.5    25.3    25.3    21.8
1M45G7W                 1.2      -88.0            56.3           -4.6       6.1     57.3          29        -41.4     31.1     31.5    25.3    25.3    21.8
200KG7W                 0.2      -88.0            47.7           -4.6       6.1     57.3          29        -41.4     31.1     31.5    25.3    25.3    21.8
100KG7W                 0.1      -88.0            44.6           -4.6       6.1     57.3          29        -41.4     31.1     31.5    25.3    25.3    21.8
400KG7W                 0.3      -88.0            50.7           -4.6        3      51.1          30        -34.3     31.1     31.5    25.3    25.3    21.8




                                                                                             27


                                      Engineering Declaration
                                DECLARATION OF Kimberly Baum


       I, Kimberly Baum, hereby certify under penalty of perjury that I am the technically qualified
person responsible for preparation of the technical information contained in the foregoing exhibit;
that I am familiar with the technical requirements of Part 25; and that I either prepared or reviewed
the technical information contained in the exhibit and that it is complete and accurate to the best of
my knowledge, information and belief.


                               _/s/_Kimberly M. Baum___________________
                               Vice President, Spectrum Management & Development Americas
                               SES Americom, Inc.


Dated: October 2, 2012




                                                  28



Document Created: 2012-10-01 13:04:32
Document Modified: 2012-10-01 13:04:32

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