§ 25.114   Applications for space station authorizations.

   (a) A comprehensive proposal must be submitted for each proposed GSO space
   station or NGSO satellite constellation on FCC Form 312, Main Form and
   Schedule S, together with attached exhibits as described in paragraph (d) of
   this section. An application for blanket authority for an NGSO satellite
   constellation comprised of space stations that are not all technically
   identical must provide the information required by paragraphs (c) and (d) of
   this section for each type of space station in the constellation.

   (b) Each application for a new or modified space station authorization must
   constitute a concrete proposal for Commission evaluation. Each application
   must  also  contain  the  formal waiver required by section 304 of the
   Communications Act, 47 U.S.C. 304. The technical information for a proposed
   satellite system specified in paragraph (c) of this section must be filed on
   FCC Form 312, Main Form and Schedule S. The technical information for a
   proposed satellite system specified in paragraph (d) of this section need
   not be filed on any prescribed form but should be complete in all pertinent
   details. Applications for all new space station authorizations must be filed
   electronically through the International Bureau Filing System (IBFS) in
   accordance with the applicable provisions of part 1, subpart Y of this
   chapter.

   (c) The following information shall be filed on FCC Form 312, Main Form and
   Schedule § 

   (1) Name, address, and telephone number of the applicant;

   (2) Name, address, and telephone number of the person(s), including counsel,
   to whom inquiries or correspondence should be directed;

   (3)  Type  of authorization requested (e.g., launch authority, station
   license, modification of authorization);

   (4)(i)  For each space station transmitting and receiving antenna beam
   (including telemetry and tracking beams but not command beams), specify
   channel center frequencies and bandwidths and polarization plan. For command
   beams, specify each of the center frequencies within a 5 MHz range or a
   range of 2 percent of the assigned bandwidth, whichever is smaller, and the
   polarization plan. If the space station can vary channel bandwidth in a
   particular frequency band with on-board processing, specify only the range
   of  frequencies  in  that band over which the beam can operate and the
   polarization plan.

   (ii) Specify maximum EIRP and maximum EIRP density for each space station
   transmitting antenna beam. If the satellite uses shapeable antenna beams, as
   defined  in § 25.103, specify instead maximum possible EIRP and maximum
   possible EIRP density within each shapeable beam's proposed coverage area.
   Provide this information for each frequency band in which the transmitting
   antenna would operate. For bands below 15 GHz, specify EIRP density in dBW/4
   kHz; for bands at and above 15 GHz, specify EIRP density in dBW/MHz. If the
   EIRP density varies over time, specify the maximum possible EIRP density.

   (iii)-(iv) [Reserved]

   (v) For each space station receiving beam other than command beams, specify
   the gain-to-temperature ratio at beam peak. For receiving beams fed into
   transponders, also specify the minimum and maximum saturation flux density
   at beam peak. If the satellite uses shapeable beams, specify the minimum and
   maximum gain-to-temperature ratio within each shapeable beam's proposed
   coverage area, and for shapeable receiving beams fed into transponders,
   specify the minimum and maximum saturation power flux density within the 0
   dB  relative  antenna  gain isoline. Provide this information for each
   frequency band in which the receiving beam can operate. For command beams,
   specify the beam peak flux density at the command threshold;

   (vi)(A) For space stations in geostationary orbit, specify predicted space
   station antenna gain contour(s) for each transmit and receive antenna beam,
   except for beams where the contour at 8 dB below peak falls entirely beyond
   the edge of the visible Earth. These contour(s) should be plotted on an area
   map  at  2  dB intervals down to 10 dB below the peak gain and at 5 dB
   intervals between 10 dB and 20 dB below the peak gain. Applicants must
   present this information in a GIMS-readable format.

   (B) For space stations in non-geostationary orbits, specify for each unique
   orbital plane the predicted antenna gain contour(s) for each transmit and
   receive  antenna  beam for one space station if all space stations are
   identical  in  the  constellation. If individual space stations in the
   constellation  have different antenna beam configurations, specify the
   predicted antenna gain contours for each transmit and receive beam for each
   space station type and orbit or orbital plane requested. The contours should
   be plotted on an area map with the beam depicted on the surface of the earth
   with the space stations' peak antenna gain pointed at nadir to a latitude
   and longitude within the proposed service area. The contour(s) should be
   plotted at 2 dB intervals down to 10 dB below the peak gain and at 5 dB
   intervals between 10 dB and 20 dB below the peak gain. For intersatellite
   links, specify the peak antenna gain and 3 dB beamwidth.

   (C) For space stations with shapeable antenna beams, specify the contours,
   as  defined in paragraph (c)(4)(vi)(A) or (B) of this section, for the
   transmitting beam configuration that results in the highest EIRP density for
   the  beams  listed in paragraph (c)(4)(ii) of this section and for the
   receiving beam configuration with the smallest gain-to-temperature ratio and
   the highest required saturation power flux density for the beams listed in
   paragraph  (c)(4)(v)  of this section. If the shapeable beams are also
   steerable, include the contours that would result from moving the beam peak
   around the limit of the effective beam peak area and the 0 dB relative
   antenna gain isoline. The proposed maximum coverage area must be clearly
   specified.

   (D) For space stations with steerable beams that are not shapeable, specify
   the applicable contours, as defined in paragraph(c)(4)(vi)(A) or (B) of this
   section,  with a description of the area that the steerable beam(s) is
   expected to serve, or provide the contour information described in paragraph
   (c)(4)(vi)(C) of this section.

   (vii) For geostationary satellites with large numbers of identical fixed
   spot beams, other than DBS satellites, applicants may, as an alternative to
   submitting the information described in paragraph (c)(4)(vi) of this section
   with respect to these beams, provide the predicted antenna gain contours for
   one transmit and receive antenna beam, together with one of the following:

   (A) An area map showing all of the spot beams depicted on the surface of the
   Earth;

   (B) A table identifying the maximum antenna gain point(s) in latitude and
   longitude to the nearest 0.1 degree; or

   (C) A map of the isolines formed by combining all of the spot beams into one
   or more composite beams. For non-geostationary satellites with large numbers
   of  identical  fixed  beams  on  each satellite, applicants may, as an
   alternative to submitting the information described in paragraph (c)(4)(vi)
   of this section with respect to those beams, specify the predicted antenna
   gain contours for one transmit and receive beam pointed to nadir, together
   with an area map showing all of the spot beams depicted on the surface of
   the earth with the satellites' peak antenna gain pointed to a selected
   latitude and longitude within the service area.

   (5) For space stations in geostationary orbit:

   (i) Orbital location requested,

   (ii) [Reserved]

   (iii) East-west station-keeping range,

   (iv) North-south station-keeping range, and

   (v) Accuracy to which antenna axis attitude will be maintained;

   (6) For space stations in non-geostationary orbits:

   (i) The number of orbital planes and the number of space stations in each
   plane,

   (ii) The inclination of the orbital plane(s),

   (iii) The orbital period,

   (iv) The apogee,

   (v) The perigee,

   (vi) The argument(s) of perigee,

   (vii) Active service arc(s),

   (viii) Right ascension of the ascending node(s), and

   (ix) For each satellite in each orbital plane, the initial phase angle at
   the reference time;

   (7) The frequency bands, types of service, and coverage areas;

   (8) Calculated maximum power flux density levels within each coverage area
   and energy dispersal bandwidths, if any, needed for compliance with § 25.208,
   for  the angles of arrival specified in the applicable paragraph(s) of
   § 25.208;

   (9) [Reserved]

   (10) Estimated operational lifetime;

   (11) Whether the space station is to be operated on a common carrier basis;

   (12) [Reserved]

   (13) The polarization information necessary for determining compliance with
   § 25.210(a)(1), (a)(3), and (i);

   (d) The following information in narrative form shall be contained in each
   application:

   (1) Overall description of system facilities, operations and services and
   explanation of how uplink frequency bands would be connected to downlink
   frequency bands;

   (2)-(5) [Reserved]

   (6) Public interest considerations in support of grant;

   (7) Applicants for authorizations for space stations in the Fixed-Satellite
   Service  must  also  include  the information specified in § 25.140(a).
   Applicants  for  authorizations  for  space  stations in the 17/24 GHz
   Broadcasting-Satellite Service must also include the information specified
   in § 25.140(b)(3), (b)(4), (b)(5), or (b)(6);

   (8) Applications for authorizations in the Mobile-Satellite Service in the
   1545-1559/1646.5-1660.5  MHz  frequency  bands  shall also provide all
   information necessary to comply with the policies and procedures set forth
   in Rules and Policies Pertaining to the Use of Radio Frequencies in a Land
   Mobile Satellite Service, 2 FCC Rcd 485 (1987) (Available at address in
   § 0.445 of this chapter.);

   (9) Applications to license multiple space station systems in the non-voice,
   non-geostationary mobile-satellite service under blanket operating authority
   shall also provide all information specified in § 25.142; and

   (10)  Applications for space station authorizations in the 1.6/2.4 GHz
   Mobile-Satellite Service must also provide all information required by
   § 25.143(b);

   (11) Applications for space stations in the Direct Broadcast Satellite
   Service must include a clear and detailed statement of whether the space
   station is to be operated on a broadcast or non-broadcast basis;

   (12)  Applications  for  authorizations in the non-geostationary orbit
   Fixed-Satellite Service in the 10.7-14.5 GHz bands must also provide all
   information specified in § 25.146.

   (13) For satellite applications in the Direct Broadcast Satellite Service,
   if  the  proposed system's technical characteristics differ from those
   specified in the Appendix 30 BSS Plans, the Appendix 30A feeder link Plans,
   Annex  5  to  Appendix  30 or Annex 3 to Appendix 30A of the ITU Radio
   Regulations, each applicant must provide:

   (i) The information requested in Appendix 4 of the ITU Radio Regulations.
   Further, applicants must provide sufficient technical showing that the
   proposed system could operate satisfactorily if all assignments in the BSS
   and feeder link Plans were implemented.

   (ii) Analyses of the proposed system with respect to the limits in Annex 1
   to Appendices 30 and 30A of the ITU Radio Regulations.

   (14) A description of the design and operational strategies that will be
   used to mitigate orbital debris, including the following information:

   (i) A statement that the space station operator has assessed and limited the
   amount of debris released in a planned manner during normal operations, and
   has assessed and limited the probability of the space station becoming a
   source of debris by collisions with small debris or meteoroids that could
   cause loss of control and prevent post-mission disposal;

   (ii) A statement that the space station operator has assessed and limited
   the probability of accidental explosions during and after completion of
   mission operations. This statement must include a demonstration that debris
   generation will not result from the conversion of energy sources on board
   the spacecraft into energy that fragments the spacecraft. Energy sources
   include chemical, pressure, and kinetic energy. This demonstration should
   address whether stored energy will be removed at the spacecraft's end of
   life, by depleting residual fuel and leaving all fuel line valves open,
   venting  any  pressurized system, leaving all batteries in a permanent
   discharge state, and removing any remaining source of stored energy, or
   through  other  equivalent  procedures  specifically  disclosed in the
   application;

   (iii) A statement that the space station operator 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. Where a
   space station will be launched into a low-Earth orbit that is identical, or
   very similar, to an orbit used by other space stations, the statement must
   include an analysis of the potential risk of collision and a description of
   what measures the space station operator plans to take to avoid in-orbit
   collisions. If the space station operator is relying on coordination with
   another system, the statement must indicate what steps have been taken to
   contact, and ascertain the likelihood of successful coordination of physical
   operations  with,  the  other  system. The statement must disclose the
   accuracy—if any—with which orbital parameters of non-geostationary satellite
   orbit  space  stations  will be maintained, including apogee, perigee,
   inclination, and the right ascension of the ascending node(s). In the event
   that a system is not able to maintain orbital tolerances, i.e., it lacks a
   propulsion system for orbital maintenance, that fact should be included in
   the  debris mitigation disclosure. Such systems must also indicate the
   anticipated evolution over time of the orbit of the proposed satellite or
   satellites.  Where  a  space  station  requests  the  assignment  of a
   geostationary-Earth orbit location, it must assess whether there are any
   known satellites located at, or reasonably expected to be located at, the
   requested orbital location, or assigned in the vicinity of that location,
   such that the station keeping volumes of the respective satellites might
   overlap. If so, the statement must include a statement as to the identities
   of those parties and the measures that will be taken to prevent collisions;

   (iv) A statement detailing the post-mission disposal plans for the space
   station at end of life, including the quantity of fuel—if any—that will be
   reserved for post-mission disposal maneuvers. For geostationary-Earth orbit
   space stations, the statement must disclose the altitude selected for a
   post-mission disposal orbit and the calculations that are used in deriving
   the disposal altitude. The statement must also include a casualty risk
   assessment if planned post-mission disposal involves atmospheric re-entry of
   the space station. In general, an assessment should include an estimate as
   to whether portions of the spacecraft will survive re-entry and reach the
   surface of the Earth, as well as an estimate of the resulting probability of
   human casualty. Applicants for space stations to be used only for commercial
   remote sensing may, in lieu of submitting detailed post-mission disposal
   plans to the Commission, certify that they have submitted such plans to the
   National Oceanic and Atmospheric Administration for review.

   (v) For non-U.S.-licensed space stations, the requirement to describe the
   design and operational strategies to minimize orbital debris risk can be
   satisfied  by demonstrating that debris mitigation plans for the space
   station(s) for which U.S. market access is requested are subject to direct
   and effective regulatory oversight by the national licensing authority.

   (15)  Each  applicant  for  a  space  station license in the 17/24 GHz
   broadcasting-satellite service shall include the following information as an
   attachment to its application:

   (i)  Except  as set forth in paragraph (d)(15)(ii) of this section, an
   applicant proposing to operate in the 17.3-17.7 GHz frequency band, must
   provide a demonstration that the proposed space station will comply with the
   power flux density limits set forth in § 25.208(w) of this part.

   (ii) In cases where the proposed space station will not comply with the
   power  flux  density  limits set forth in § 25.208(w) of this part, the
   applicant will be required to provide a certification that all potentially
   affected parties acknowledge and do not object to the use of the applicant's
   higher power flux densities. The affected parties with whom the applicant
   must coordinate are those GSO 17/24 GHz BSS satellite networks located up to
   ±6° away for excesses of up to 3 dB above the power flux-density levels
   specified  in § 25.208(w) of this part, and up to ±10° away greater for
   excesses greater than 3 dB above those levels.

   (iii)  An  applicant proposing to provide international service in the
   17.7-17.8 GHz band must demonstrate that it will meet the power flux density
   limits set forth in § 25.208(c) of this part.

   (iv) The information required in § 25.264(a) and (b).

   (16) In addition to the requirements of paragraph (d)(15) of this section,
   each applicant for a license to operate a 17/24 GHz BSS space station that
   will be used to provide video programming directly to consumers in the
   United States, that will not meet the requirements of § 25.225 of this part,
   must  include as an attachment to its application a technical analysis
   demonstrating that providing video programming service to consumers in
   Alaska  and Hawaii that is comparable to the video programming service
   provided to consumers in the 48 contiguous United States (CONUS) is not
   feasible as a technical matter or that, while technically feasible, such
   service would require so many compromises in satellite design and operation
   as to make it economically unreasonable.

   (17)  An applicant seeking to operate a space station in the 17/24 GHz
   broadcasting-satellite service pursuant to the provisions of § 25.262(b) of
   this part, at an offset location no greater than one degree offset from an
   orbital location specified in Appendix F of the Report and Order adopted May
   2, 2007, IB Docket No. 06-123, FCC 07-76, must submit a written request to
   that effect as part of the narrative portion of its application.

   (18) For space stations in the Direct Broadcast Satellite service or the
   17/24 GHz broadcasting-satellite service, maximum orbital eccentricity.

   [ 68 FR 63997 , Nov. 12, 2003, as amended at  69 FR 29901 , May 26, 2004;  69 FR 47794 , Aug. 6, 2004;  69 FR 54587 , Sept. 9, 2004;  72 FR 50027 , Aug. 29, 2007;
    72 FR 60278 , Oct. 24, 2007;  76 FR 50431 , Aug. 15, 2011;  78 FR 8421 , Feb. 6,
   2013;  79 FR 8314 , Feb. 12, 2014]

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