§  25.114   Applications for space station authorizations.

   Link to an amendment published at  85 FR 52450 , Aug. 25, 2020.

   (a)(1) A license application filed pursuant to § 25.110(b)(2) for a GSO
   space station or NGSO space station or space-station constellation must
   comprise a comprehensive proposal and must be submitted on FCC Form
   312, Main Form and Schedule S, with attached exhibits required by
   paragraph (d) of this section.

   (2) An application for blanket authority for an NGSO constellation 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 station in the constellation.

   (3) For an application filed pursuant to the two-step procedure in
   § 25.110(b)(3), the filing pursuant to § 25.110(b)(3)(iii) must be
   submitted on FCC Form 312, Main Form and Schedule S, with attached
   exhibits as required by paragraph (d) of this section, and must
   constitute a comprehensive proposal.

   (b) Each application for a new or modified space station authorization
   must contain the formal waiver required by 47 U.S.C. 304.

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

   (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 a space station with steerable beams that are not shapeable,
   specify the applicable contours, as defined in paragraph (c)(4)(vi)(A)
   or (c)(4)(vi)(B) of this section, with a description of a proposed
   coverage area for each steerable beam or provide the contour
   information described in paragraph (c)(4)(vi)(C) of this section for
   each steerable beam.

   (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, except for an NGSO FSS applicant certifying
   compliance with PFD limits under § 25.146(a)(1);

   (9) [Reserved]

   (10) Estimated operational lifetime;

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

   (12) [Reserved]

   (13) And the polarization information necessary to determine compliance
   with § 25.210(i).

   (d) The following information in narrative form shall be contained in
   each application, except space station applications filed pursuant to
   § 25.122 or § 25.123:

   (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, including applicants proposing feeder links
   for space stations operating in the 17/24 GHz Broadcasting-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);

   (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) An application for space station authorization in the 1.6/2.4 GHz
   or 2 GHz Mobile-Satellite Service must include 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) The information required by § 25.146, if the application is for an
   NGSO FSS system authorization within the 10.7-30 GHz band.

   (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) If the applicant proposes to operate in the 17.3-17.7 GHz frequency
   band, a demonstration that the proposed space station will comply with
   the power flux density limits in § 25.208(w) unless the applicant
   provides a certification under paragraph (d)(15)(ii) of this section.

   (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) If the applicant proposes to provide international service in the
   17.7-17.8 GHz frequency band, a certification that the proposed space
   station will comply with the power flux density limits in § 25.208(c).

   (iv) Any information required by § 25.264(a)(6), 25.264(b)(4), or
   25.264(d).

   (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) [Reserved]

   (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;  81 FR 55326 , Aug.
   18, 2016;  82 FR 59984 , Dec. 18, 2017;  83 FR 34489 , July 20, 2018;  85 FR 43733 , July 20, 2020]

   Effective Date Note: At  85 FR 52450 , Aug. 25, 2020, § 25.114 was amended
   by revising paragraph (d)(14). This amendment contains information
   collection and recordkeeping requirements and will not become effective
   until approval has been given by the Office of Management and Budget.
   For the convenience of the user, the revised text is set forth below:

   § 25.114   Applications for space station authorizations.

*   *   *   *   *

   (d) *  *  *

   (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. Where applicable, this statement must include an orbital
   debris mitigation disclosure for any separate deployment devices,
   distinct from the space station launch vehicle, that may become a
   source of orbital debris;

   (ii) A statement indicating whether the space station operator has
   assessed and limited the probability that the space station(s) will
   become a source of debris by collision with small debris or meteoroids
   that would cause loss of control and prevent disposal. The statement
   must indicate whether this probability for an individual space station
   is 0.01 (1 in 100) or less, as calculated using the NASA Debris
   Assessment Software or a higher fidelity assessment tool;

   (iii) A statement that the space station operator has assessed and
   limited the probability, during and after completion of mission
   operations, of accidental explosions or of release of liquids that will
   persist in droplet form. 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;

   (iv) A statement that the space station operator has assessed and
   limited the probability of the space station(s) becoming a source of
   debris by collisions with large debris or other operational space
   stations.

   (A) Where the application is for an NGSO space station or system, the
   following information must also be included:

   (1) A demonstration that the space station operator has assessed and
   limited the probability of collision between any space station of the
   system and other large objects (10 cm or larger in diameter) during the
   total orbital lifetime of the space station, including any de-orbit
   phases, to less than 0.001 (1 in 1,000). The probability shall be
   calculated using the NASA Debris Assessment Software or a higher
   fidelity assessment tool. The collision risk may be assumed zero for a
   space station during any period in which the space station will be
   maneuvered effectively to avoid colliding with large objects.

   (2) The statement must identify characteristics of the space
   station(s)' orbits that may present a collision risk, including any
   planned and/or operational space stations in those orbits, and indicate
   what steps, if any, have been taken to coordinate with the other
   spacecraft or system, or what other measures the operator plans to use
   to avoid collision.

   (3) If at any time during the space station(s)' mission or de-orbit
   phase the space station(s) will transit through the orbits used by any
   inhabitable spacecraft, including the International Space Station, the
   statement must describe the design and operational strategies, if any,
   that will be used to minimize the risk of collision and avoid posing
   any operational constraints to the inhabitable spacecraft.

   (4) The statement must disclose the accuracy, if any, with which
   orbital parameters 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, e.g.,
   its propulsion system will not be used for orbital maintenance, that
   fact must 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. All systems must describe the
   extent of satellite maneuverability, whether or not the space station
   design includes a propulsion system.

   (5) The space station operator must certify that upon receipt of a
   space situational awareness conjunction warning, the operator will
   review and take all possible steps to assess the collision risk, and
   will mitigate the collision risk if necessary. As appropriate, steps to
   assess and mitigate the collision risk should include, but are not
   limited to: Contacting the operator of any active spacecraft involved
   in such a warning; sharing ephemeris data and other appropriate
   operational information with any such operator; and modifying space
   station attitude and/or operations.

   (B) Where a space station requests the assignment of a geostationary
   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 or touch. If so, the statement must include a statement as to
   the identities of those satellites and the measures that will be taken
   to prevent collisions;

   (v) A statement addressing the trackability of the space station(s).
   Space station(s) operating in low-Earth orbit will be presumed
   trackable if each individual space station is 10 cm or larger in its
   smallest dimension, excluding deployable components. Where the
   application is for an NGSO space station or system, the statement shall
   also disclose the following:

   (A) How the operator plans to identify the space station(s) following
   deployment and whether space station tracking will be active or
   passive;

   (B) Whether, prior to deployment, the space station(s) will be
   registered with the 18th Space Control Squadron or successor entity;
   and

   (C) The extent to which the space station operator plans to share
   information regarding initial deployment, ephemeris, and/or planned
   maneuvers with the 18th Space Control Squadron or successor entity,
   other entities that engage in space situational awareness or space
   traffic management functions, and/or other operators.

   (vi) A statement disclosing planned proximity operations, if any, and
   addressing debris generation that will or may result from the proposed
   operations, including any planned release of debris, the risk of
   accidental explosions, the risk of accidental collision, and measures
   taken to mitigate those risks.

   (vii) A statement detailing the disposal plans for the space station,
   including the quantity of fuel—if any—that will be reserved for
   disposal maneuvers. In addition, the following specific provisions
   apply:

   (A) For geostationary orbit space stations, the statement must disclose
   the altitude selected for a disposal orbit and the calculations that
   are used in deriving the disposal altitude.

   (B) For space stations terminating operations in an orbit in or passing
   through the low-Earth orbit region below 2,000 km altitude, the
   statement must disclose whether the spacecraft will be disposed of
   through atmospheric re-entry, specifying if direct retrieval of the
   spacecraft will be used. The statement must also disclose the expected
   time in orbit for the space station following the completion of the
   mission.

   (C) For space stations not covered by either paragraph (d)(14)(vii)(A)
   or (B) of this section, the statement must indicate whether disposal
   will involve use of a storage orbit or long-term atmospheric re-entry
   and rationale for the selected disposal plan.

   (D) For all space stations under paragraph (d)(14)(vii) (B) or (C) of
   this section, the following additional specific provisions apply:

   (1) The statement must include a demonstration that the probability of
   success of the chosen disposal method will be 0.9 or greater for any
   individual space station. For space station systems consisting of
   multiple space stations, the demonstration should include additional
   information regarding efforts to achieve a higher probability of
   success, with a goal, for large systems, of a probability of success
   for any individual space station of 0.99 or better. For space stations
   under paragraph (d)(14)(vii)(B) of this section, successful disposal is
   defined as atmospheric re-entry of the spacecraft within 25 years or
   less following completion of the mission. For space stations under
   paragraph (d)(14)(vii)(C) of this section, successful disposal will be
   assessed on a case-by-case basis.

   (2) If planned disposal is by atmospheric re-entry, the statement must
   also include:

   (i) A disclosure indicating whether the atmospheric re-entry will be an
   uncontrolled re-entry or a controlled targeted reentry.

   (ii) An assessment as to whether portions of any individual spacecraft
   will survive atmospheric re-entry and impact the surface of the Earth
   with a kinetic energy in excess of 15 joules, and demonstration that
   the calculated casualty risk for an individual spacecraft using the
   NASA Debris Assessment Software or a higher fidelity assessment tool is
   less than 0.0001 (1 in 10,000).

   (E) 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.

   (viii) 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.

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