14 CFR Part 420 — License to Operate a Launch Site

PART 420—LICENSE TO OPERATE A LAUNCH SITE Authority: 51 U.S.C. 50901-50923. Source: Docket No. FAA-1999-5833, 65 FR 62861, Oct. 19, 2000, unless otherwise noted. Subpart A—General § 420.1 General. (a) Scope. (b) Equivalent level of safety. [Doc. No. FAA-2016-6761, Amdt. No. 420-8, 83 FR 28535, June 20, 2018] § 420.3 Applicability. This part applies to any person seeking a license to operate a launch site or to a person licensed under this part. A person operating a site that only supports amateur rocket activities as defined in 14 CFR 1.1, does not need a license under this part to operate the site. [Doc. No. FAA-2007-27390, 73 FR 73782, Dec. 4, 2008] § 420.5 Definitions. For the purpose of this part. Ballistic coefficient Compatibility Debris dispersion radius max Downrange area E,F,G coordinate system E,N,U coordinate system Effective casualty area (A c ) Energetic liquid Explosive Explosive division Explosive equivalent Explosive hazard facility Flight azimuth Flight corridor Guided suborbital launch vehicle Hazard class Impact dispersion area Impact dispersion factor Impact dispersion radius (R i ) Impact range Impact range factor Instantaneous impact point (IIP) Intraline distance Launch area Launch point Liquid propellant (1) A monopropellant on a launch vehicle or related device; or (2) Incompatible energetic liquids co-located for purposes of serving as propellants on a launch vehicle or a related device where the incompatible energetic liquids are housed in tanks connected by piping for purposes of mixing. Maximum credible event Net explosive weight (NEW) Nominal Overflight dwell time Overflight exclusion zone Populated area Population density Position data Public area Public area distance Public traffic route Public traffic route distance Trajectory Unguided sub-orbital launch vehicle X, Y, Z coordinate system φ 0 λ 0 h 0 0 0 0 0 0 [Doc. No. FAA-1999-5833, 65 FR 62861, Oct. 19, 2000, as amended by Amdt. 420-3, 72 FR 17019, Apr. 6, 2007; Amdt. 420-6, 77 FR 55113, Sept. 7, 2012; Doc. No. FAA-2019-0229, Amdt. 420-9, 85 FR 79716, Dec. 10, 2020] §§ 420.6-420.14 [Reserved] Subpart B—Criteria and Information Requirements for Obtaining a License § 420.15 Information requirements. (a) General Launch site operator. (2) Launch site. (i) A list of downrange equipment; (ii) A description of the layout of the launch site, including launch points; (iii) The types of launch vehicles to be supported at each launch point; (iv) The range of launch azimuths planned from each launch point; and (v) The scheduled operational date. (3) Foreign ownership. (i) For a sole proprietorship or partnership, all foreign owners or partners; (ii) For a corporation, any foreign ownership interest of 10 percent or more; and (iii) For a joint venture, association, or other entity, any foreign entities participating in the entity. (b) Environmental. (1) Environmental impact statement or environmental assessment. (i) Prepare an Environmental Assessment with FAA oversight; (ii) Assume financial responsibility for preparation of an Environmental Impact Statement by an FAA-selected and -managed consultant contractor; or (iii) Submit information to support a written re-evaluation of a previously submitted Environmental Assessment or Environmental Impact Statement when requested by the FAA. (2) Categorical exclusion. (3) Environmental information. (c) Launch site location. (2) An applicant who is proposing to locate a launch site at an existing launch point at a federal launch range is not required to comply with paragraph (c)(1) of this section if a launch vehicle of the same type and class as proposed for the launch point has been safely launched from the launch point. (d) Explosive site plan. (2) If an applicant plans to operate a launch site located on a federal launch range, and if the applicant is required by the federal launch range to comply with the federal launch range's explosive safety requirements, the applicant shall submit the explosive site plan submitted to the federal launch range. (e) Launch site operations. [Docket No. FAA-1999-5833, 65 FR 62861, Oct. 19, 2000, as amended by Doc. No. FAA-2019-0229, Amdt. 420-9, 85 FR 79716, Dec. 10, 2020] § 420.17 Bases for issuance of a license. (a) The FAA will issue a license under this part when the FAA determines that: (1) The application provides the information required by § 420.15; (2) The FAA has completed an analysis of the environmental impacts associated with the proposed operation of the launch site, in accordance with NEPA, 40 CFR parts 1500-1508, and FAA Order 1050.1D; (3) The launch site location meets the requirements of §§ 420.19, 420.21, 420.23, 420.25, 420.27, and 420.29; (4) The applicant has completed the agreements required by § 420.31; (5) The application demonstrates that the applicant shall satisfy the requirements of §§ 420.53, 420.55, 420.57, 420.59, 420.61 and 420.71; (6) The explosive site plan meets the criteria of §§ 420.63, 420.65, 420.67 and 420.69; and (7) Issuing a license would not jeopardize foreign policy or national security interests of the United States. (b) The FAA advises an applicant, in writing, of any issue arising during an application review that would lead to denial. The applicant may respond in writing, submit additional information, or amend its license application. § 420.19 Launch site location review—general. (a) To gain approval for a launch site location, an applicant shall demonstrate that for each launch point proposed for the launch site, at least one type of expendable or reusable launch vehicle can be flown from the launch point safely. For purposes of the launch site location review: (1) A safe launch must possess a risk level estimated, in accordance with the requirements of this part, not to exceed an expected number of 1 × 10 −4 c (2) Types of launch vehicles include orbital expendable launch vehicles, guided sub-orbital expendable launch vehicles, unguided sub-orbital expendable launch vehicles, and reusable launch vehicles. Orbital expendable launch vehicles are further classified by weight class, based on the weight of payload the launch vehicle can place in a 100-nm orbit, as defined in table 1. (b) If an applicant proposes to have more than one type of launch vehicle flown from a launch point, the applicant shall demonstrate that each type of expendable or reusable launch vehicle planned to be flown from the launch point can be flown from the launch point safely. (c) If an applicant proposes to have more than one weight class of orbital expendable launch vehicles flown from a launch point, the applicant shall demonstrate that the heaviest weight class planned to be flown from the launch point can be flown from the launch point safely. Table 1 of § 420.19—Orbital Expendable Launch Vehicle Classes by Payload Weight (lbs) 100 nm orbit Weight class Small Medium Medium large Large 28 degrees inclination * ≤4400 >4400 to ≤11100 >11100 to ≤18500 >18500 90 degrees inclination ≤3300 >3300 to ≤8400 >8400 to ≤15000 >15000 * 28 degrees inclination orbit from a launch point at 28 degrees latitude. [Docket No. FAA-1999-5833, 65 FR 62861, Oct. 19, 2000, as amended by Docket No. FAA-2014-0418, Amdt. No. 420-7, 81 FR 47026, July 20, 2016] § 420.21 Launch site location review—launch site boundary. (a) The distance from any proposed launch point to the closest launch site boundary must be at least as great as the debris dispersion radius of the largest launch vehicle type and weight class proposed for the launch point. (b) For a launch site supporting any expendable launch vehicle, an applicant shall use the largest distance provided by table 2 for the type and weight class of any launch vehicle proposed for the launch point. (c) For a launch site supporting any reusable launch vehicle, an applicant shall determine the debris dispersion radius that represents the maximum distance from a launch point that debris travels given a worst-case launch vehicle failure in the launch area. An applicant must clearly and convincingly demonstrate the validity of its proposed debris dispersion radius. Table 2 of § 420.21—Minimum Distance From Launch Point to Launch Site Boundary (feet) Orbital expendable launch vehicle class Type of suborbital launch vehicle Small Medium Medium large Large Guided Unguided 7300 9300 10600 13000 8000 1600 § 420.23 Launch site location review—flight corridor. (a) Guided orbital expendable launch vehicle. (1) Encompasses an area that the applicant estimates, in accordance with the requirements of this part, to contain debris with a ballistic coefficient of ≥3 pounds per square foot, from any non-nominal flight of a guided orbital expendable launch vehicle from the launch point to a point 5000 nm downrange, or where the IIP leaves the surface of the Earth, whichever is shorter; (2) Includes an overflight exclusion zone where the public risk criteria of 1 × 10 −4 (3) Uses one of the methodologies provided in appendix A or B of this part. (b) Guided sub-orbital expendable launch vehicle. (1) Encompasses an area that the applicant estimates, in accordance with the requirements of this part, to contain debris with a ballistic coefficient of ≥3 pounds per square foot, from any non-nominal flight of a guided sub-orbital expendable launch vehicle from the launch point to impact with the earth's surface; (2) Includes an impact dispersion area for the launch vehicle's last stage; (3) Includes an overflight exclusion zone where the public risk criteria of 1 × 10 −4 (4) Uses one of the methodologies provided in appendix A or B to this part. (c) Unguided sub-orbital expendable launch vehicle. (i) Impact dispersion areas that the applicant estimates, in accordance with the requirements of this part, to contain the impact of launch vehicle stages from nominal flight of an unguided sub-orbital expendable launch vehicle from the launch point to impact with the earth's surface; and (ii) An overflight exclusion zone where the public risk criteria of 1 × 10 −4 (2) An applicant shall base its analysis on an unguided suborbital launch vehicle whose final launch vehicle stage apogee represents the intended use of the launch point. (d) Reusable launch vehicle. [Docket No. FAA-1999-5833, 65 FR 62861, Oct. 19, 2000, as amended by Docket No. FAA-2014-0418, Amdt. No. 420-7, 81 FR 47026, July 20, 2016; Doc. No. FAA-2016-6761, Amdt. No. 420-8, 83 FR 28535, June 20, 2018] § 420.25 Launch site location review—risk analysis. (a) If a flight corridor or impact dispersion area defined by § 420.23 contains a populated area, the applicant shall estimate the casualty expectation associated with the flight corridor or impact dispersion area. An applicant shall use the methodology provided in appendix C to this part for guided orbital or suborbital expendable launch vehicles and appendix D for unguided suborbital launch vehicles. (b) For licensed launches, the FAA will not approve the location of the proposed launch point if the estimated expected casualty exceeds 1 × 10 −4 [Doc. No. FAA-1999-5833, 65 FR 62861, Oct. 19, 2000, as amended by Amdt. 420-3, 72 FR 17019, Apr. 6, 2007; Docket No. FAA-2014-0418, Amdt. No. 420-7, 81 FR 47027, July 20, 2016; Doc. No. FAA-2016-6761, Amdt. No. 420-8, 83 FR 28535, June 20, 2018] § 420.27 Launch site location review—information requirements. An applicant shall provide the following launch site location review information in its application: (a) A map or maps showing the location of each launch point proposed, and the flight azimuth, IIP, flight corridor, and each impact range and impact dispersion area for each launch point; (b) Each launch vehicle type and any launch vehicle class proposed for each launch point; (c) Trajectory data; (d) Wind data, including each month and any percent wind data used in the analysis; (e) Any launch vehicle apogee used in the analysis; (f) Each populated area located within a flight corridor or impact dispersion area; (g) The estimated casualty expectancy calculated for each populated area within a flight corridor or impact dispersion area; (h) The effective casualty areas used in the analysis; (i) The estimated casualty expectancy for each flight corridor or set of impact dispersion areas; and (j) If populated areas are located within an overflight exclusion zone, a demonstration that there are times when the public is not present or that the applicant has an agreement in place to evacuate the public from the overflight exclusion zone during a launch. § 420.29 Launch site location review for unproven launch vehicles. An applicant for a license to operate a launch site for an unproven launch vehicle shall provide a clear and convincing demonstration that its proposed launch site location provides an equivalent level of safety to that required by this part. § 420.30 Launch site location review for permitted launch vehicles. If an applicant plans to use its proposed launch site solely for launches conducted under an experimental permit, the FAA will approve a launch site location if the FAA has approved an operating area under part 437 for launches from that site. [Doc. No. FAA-2006-24197, 72 FR 17019, Apr. 6, 2007] § 420.31 Agreements. (a) Except as provided by paragraph (c) of this section, an applicant shall complete an agreement with the local U.S. Coast Guard district to establish procedures for the issuance of a Notice to Mariners prior to a launch and other such measures as the Coast Guard deems necessary to protect public health and safety. (b) Except as provided by paragraph (c) of this section, an applicant shall complete an agreement with the FAA Air Traffic Control (ATC) office having jurisdiction over the airspace through which launches will take place, to establish procedures for the issuance of a Notice to Airmen prior to a launch and for closing of air routes during the launch window and other such measures as the FAA ATC office deems necessary to protect public health and safety. (c) An applicant that plans to operate a launch site located on a federal launch range does not have to comply with section 420.31 if the applicant is using existing federal launch range agreements with the U.S. Coast Guard and the FAA ATC office having jurisdiction over the airspace through which launches will take place. §§ 420.32-420.40 [Reserved] Subpart C—License Terms and Conditions § 420.41 License to operate a launch site—general. (a) A license to operate a launch site authorizes a licensee to operate a launch site in accordance with the representations contained in the licensee's application, with terms and conditions contained in any license order accompanying the license, and subject to the licensee's compliance with 51 U.S.C. Subtitle V, chapter 509 and this chapter. (b) A license to operate a launch site authorizes a licensee to offer its launch site to a launch operator for each launch point for the type and any weight class of launch vehicle identified in the license application and upon which the licensing determination is based. (c) Issuance of a license to operate a launch site does not relieve a licensee of its obligation to comply with any other laws or regulations; nor does it confer any proprietary, property, or exclusive right in the use of airspace or outer space. [Doc. No. FAA-1999-5833, 65 FR 62861, Oct. 19, 2000, as amended by Amdt. 420-5, 77 FR 20533, Apr. 5, 2012] § 420.43 Duration. A license to operate a launch site remains in effect for five years from the date of issuance unless surrendered, suspended, or revoked before the expiration of the term and is renewable upon application by the licensee. § 420.45 Transfer of a license to operate a launch site. (a) Only the FAA may transfer a license to operate a launch site. (b) The FAA will transfer a license to an applicant who has submitted an application in accordance with 14 CFR part 413, satisfied the requirements of § 420.15, and obtained each approval required by § 420.17 for a license. (c) The FAA may incorporate by reference any findings made part of the record that supported a prior related licensing determination. § 420.47 License modification. (a) Upon application or upon its own initiative, the FAA may modify a license to operate a launch site at any time by issuing a license order that adds, removes, or modifies a license term or condition to ensure compliance with the Act and the requirements of this chapter. (b) After a license to operate a launch site has been issued, a licensee shall apply to the FAA for modification of its license if: (1) The licensee proposes to operate the launch site in a manner that is not authorized by the license; or (2) The licensee proposes to operate the launch site in a manner that would make any representation contained in the license application that is material to public health and safety or safety of property no longer accurate and complete. (c) An application to modify a license shall be prepared and submitted in accordance with part 413 of this chapter. The licensee shall indicate any part of its license or license application that would be changed or affected by a proposed modification. (d) The FAA approves a modification request that satisfies the requirements of this part. (e) Upon approval of a license modification, the FAA issues either a written approval to the licensee or a license order modifying the license if a stated term or condition of the license is changed, added, or deleted. A written approval has the full force and effect of a license order and is part of the licensing record. § 420.49 Compliance monitoring. A licensee shall allow access by and cooperate with federal officers or employees or other individuals authorized by the FAA to observe any activities of the licensee, its customers, its contractors, or subcontractors, associated with licensed operation of the licensee's launch site. Subpart D—Responsibilities of a Licensee § 420.51 Responsibilities—general. A licensee must operate its launch site in accordance with the representations in its application. [Docket No. FAA-2019-0229, Amdt. 420-9, 85 FR 79716, Dec. 10, 2020] § 420.53 Control of public access. (a) A licensee shall prevent unauthorized access to the launch site, and unauthorized, unescorted access to explosive hazard facilities or other hazard areas not otherwise controlled by a launch operator, through the use of security personnel, surveillance systems, physical barriers, or other means approved as part of the licensing process. (b) A licensee shall notify anyone entering the launch site of safety rules and emergency and evacuation procedures prior to that person's entry unless that person has received a briefing on those rules and procedures within the previous year. (c) A licensee shall employ warning signals or alarms to notify any persons at the launch site of any emergency. § 420.55 Scheduling of launch site operations. (a) A licensee shall develop and implement procedures to schedule operations to ensure that each operation carried out by a customer at the launch site does not create the potential for a mishap that could result in harm to the public because of the proximity of the operations, in time or place, to operations of any other customer. A customer includes any launch operator, and any contractor, subcontractor or customer of the launch site operator's customer at the launch site. (b) A licensee shall provide its launch site scheduling requirements to each customer before the customer begins operations at the launch site. § 420.57 Notifications. (a) A licensee shall notify each launch operator and any other customer of any limitations on the use of the launch site. A licensee shall also communicate limitations on the use of facilities provided to customers by the launch site operator. (b) A licensee shall maintain its agreement, made in accordance with § 420.31(a), with the local U.S. Coast Guard district. (c) A licensee shall maintain its agreement, made in accordance with § 420.31(b), with the FAA ATC office having jurisdiction over the airspace through which launches will take place. (d) At least 2 days prior to flight of a launch vehicle, unless the Administrator agrees to a different time frame in accordance with § 404.15, the licensee must notify local officials and all owners of land adjacent to the launch site of the flight schedule. [Docket No. FAA-1999-5833, 65 FR 62861, Oct. 19, 2000, as amended by Doc. No. FAA-2019-0229, Amdt. 420-9, 85 FR 79716, Dec. 10, 2020] § 420.59 Mishap plan. (a) General. (b) Launch mishaps. (c) Other agency procedures. [Doc. No. FAA-2019-0229, Amdt. 420-9, 85 FR 79716, Dec. 10, 2020] § 420.61 Records. (a) A licensee shall maintain all records, data, and other material needed to verify that its operations are conducted in accordance with representations contained in the licensee's application. A licensee shall retain records for three years. (b) For any event that meets any of paragraph (1), (5), or (8) of the definition of “mishap” in § 401.7 of this chapter, a licensee must preserve all records related to the event. Records must be retained until completion of any Federal investigation and the FAA advises the licensee that the records need not be retained. (c) A licensee shall make available to federal officials for inspection and copying all records required to be maintained under the regulations. [Docket No. FAA-1999-5833, 65 FR 62861, Oct. 19, 2000, as amended by Doc. No. FAA-2019-0229, Amdt. 420-9, 85 FR 79717, Dec. 10, 2020] § 420.63 Explosive siting. (a) Except as otherwise provided by paragraph (b) of this section, a licensee must ensure the configuration of the launch site follows its explosive site plan, and the licensee's explosive site plan complies with the requirements of §§ 420.65 through 420.70. The explosive site plan must include: (1) A scaled map that shows the location of all explosive hazard facilities at the launch site and that shows actual and minimal allowable distances between each explosive hazard facility and all other explosive hazard facilities, each public traffic route, and each public area, including the launch site boundary; (2) A list of the maximum quantity of energetic liquids, solid propellants and other explosives to be located at each explosive hazard facility, including explosive class and division; (3) A description of each activity to be conducted at each explosive hazard facility; and (4) An explosive site map using a scale sufficient to show whether distances and structural relationships satisfy the requirements of this part. (b) A licensee operating a launch site located on a federal launch range does not have to comply with the requirements in §§ 420.65 through 420.70 if the licensee complies with the federal launch range's explosive safety requirements. (c) For explosive siting issues not addressed by the requirements of §§ 420.65 through 420.70, a launch site operator must clearly and convincingly demonstrate a level of safety equivalent to that otherwise required by this part. (d) A launch site operator may separate an explosive hazard facility from another explosive hazard facility, public area, or public traffic route by a distance different from one required by this part only if the launch site operator clearly and convincingly demonstrates a level of safety equivalent to that required by this part. [Doc. No. FAA-2011-0105, 77 FR 55113, Sept. 7, 2012] § 420.65 Separation distance requirements for handling division 1.1 and 1.3 explosives. (a) Quantity. (1) A launch site operator must determine the maximum total quantity of division 1.1 and 1.3 explosives by class and division, in accordance with 49 CFR part 173, Subpart C, to be located in each explosive hazard facility where division 1.1 and 1.3 explosives will be handled. (2) When division 1.1 and 1.3 explosives are located in the same explosive hazard facility, the total quantity of explosive must be treated as division 1.1 for determining separation distances; or, a launch site operator may add the net explosive weight of the division 1.3 items to the net explosive weight of division 1.1 items to determine the total quantity of explosives. (b) Separation of division 1.1 and 1.3 explosives and determination of distances. (1) For division 1.1 explosives, the launch site operator must use tables E-1, E-2, and E-3 of appendix E of this part to determine the distance to each public area and public traffic route, and to determine each intraline distance. (2) For division 1.3 explosives, the launch site operator must use table E-4 of appendix E of this part to determine the distance to each public area and public traffic route, and to determine each intraline distance. (c) Separation distance by weight and table. (1) Employ no less than the public area distance, calculated under paragraph (b) of this section, to separate an explosive hazard facility from each public area, including the launch site boundary. (2) Employ no less than an intraline distance to separate an explosive hazard facility from all other explosive hazard facilities used by a single customer. For explosive hazard facilities used by different customers a launch site operator must use the greater public area distance to separate the facilities from each other. (3) Separate each public area containing any member of the public in the open by a distance equal to −1133.9 + [389 *ln(NEW)], where the NEW is greater than 450 pounds and less than 501,500 pounds. (d) NEW Quantities that Fall between Table Entries. (e) Calculating Maximum Permissible NEW Given a Distance. A launch site operator must, when determining [Doc. No. FAA-2011-0105, 77 FR 55114, Sept. 7, 2012] § 420.66 Separation distance requirements for storage of hydrogen peroxide, hydrazine, and liquid hydrogen and any incompatible energetic liquids stored within an intraline distance. (a) Separation of energetic liquids and determination of distances. (1) Hydrogen peroxide in concentrations of greater than 91 percent; (2) Hydrazine; (3) Liquid hydrogen; or (4) Any energetic liquid that is: (i) Incompatible with any of the energetic liquids of paragraph (a)(1) through (3) of this section; and (ii) Stored within an intraline distance of any of them. (b) Quantity. (1) The quantity of energetic liquid in a tank, drum, cylinder, or other container is the net weight in pounds of the energetic liquid in the container. The determination of quantity must include any energetic liquid in associated piping to any point where positive means exist for: (i) Interrupting the flow through the pipe, or (ii) Interrupting a reaction in the pipe in the event of a mishap. (2) A launch site operator must convert the quantity of each energetic liquid from gallons to pounds using the conversion factors provided in table E-6 of appendix E of this part and the following equation: Pounds of energetic liquid = gallons × density of energetic liquid (pounds per gallon). (3) Where two or more containers of compatible energetic liquids are stored in the same explosive hazard facility, the total quantity of energetic liquids is the total quantity of energetic liquids in all containers, unless: (i) The containers are each separated from each other by the distance required by paragraph (c) of this section; or (ii) The containers are subdivided by intervening barriers that prevent mixing, such as diking. (4) Where two or more containers of incompatible energetic liquids are stored within an intraline distance of each other, paragraph (d) of this section applies. (c) Determination of separation distances for compatible energetic liquids. (1) To determine each intraline, public area, and public traffic route distance, a launch site operator must use the following tables in appendix E of this part: (i) Table E-7 for hydrogen peroxide in concentrations of greater than 91 percent; and (ii) Table E-8 for hydrazine and liquid hydrogen. (2) For liquid hydrogen and hydrazine, a launch site operator must use the “intraline distance to compatible energetic liquids” for the energetic liquid that requires the greater distance under table E-8 of appendix E of this part as the minimum separation distance between compatible energetic liquids. (d) Determination of separation distances for incompatible energetic liquids. (1) If intervening barriers prevent mixing, a launch site operator must separate the incompatible energetic liquids by no less than the intraline distance that tables E-7 and E-8 of appendix E of this part apply to compatible energetic liquids using the quantity or energetic liquid requiring the greater separation distance. (2) A launch site operator must use the formulas provided in table E-5 of appendix E of this part, to determine the explosive equivalent in pounds of the combined incompatible energetic liquids. A launch site operator must then use the explosive equivalent in pounds requiring the greatest separation distance to determine the minimum separation distance between each explosive hazard facility and all other explosive hazard facilities and each public area and public traffic route as required by tables E-1, E-2 and E-3 of appendix E of this part. [Doc. No. FAA-2011-0105, 77 FR 55114, Sept. 7, 2012] § 420.67 Separation distance requirements for handling incompatible energetic liquids that are co-located. (a) Separation of energetic liquids and determination of distances. (b) Quantity. (1) The quantity of energetic liquid in a launch or reentry vehicle tank is the net weight in pounds of the energetic liquid. The determination of quantity must include any energetic liquid in associated piping to any point where positive means exist for: (i) Interrupting the flow through the pipe; or (ii) Interrupting a reaction in the pipe in the event of a mishap. (2) A launch site operator must convert each energetic liquid's quantity from gallons to pounds using the conversion factors provided by table E-6 of appendix E of this part and the following equation: Pounds of energetic liquid = gallons × density of energetic liquid (pounds per gallon). (c) Determination of separation distances for incompatible energetic liquids. (1) A launch site operator must use the formulas provided in table E-5 of appendix E of this part, to determine the explosive equivalent in pounds of the combined incompatible energetic liquids; and (2) A launch site operator must then use the explosive equivalent in pounds to determine the minimum separation distance between each explosive hazard facility and all other explosive hazard facilities and each public area and public traffic route as required by tables E-1, E-2 and E-3 of appendix E of this part. Where two explosive hazard facilities contain different quantities, the launch site operator must use the quantity of liquid propellant requiring the greatest separation distance to determine the minimum separation distance between the two explosive hazard facilities. (d) Separation distance by weight and table. (1) For an explosive equivalent weight from one pound through and including 450 pounds, determine the distance to any public area and public traffic route following table E-1 of appendix E of this part; (2) For explosive equivalent weight greater than 450 pounds, determine the distance to any public area and public traffic route following table E-2 of appendix E of this part; (3) Separate each public area containing any member of the public in the open by a distance equal to −1133.9 + [389 *ln(NEW)], where the NEW is greater than 450 pounds and less than 501,500 pounds; (4) Separate each explosive hazard facility from all other explosive hazard facilities of a single customer using the intraline distance provided by table E-3 of appendix E of this part; and (5) For explosive hazard facilities used by different customers, use the greater public area distance to separate the facilities from each other. [Doc. No. FAA-2011-0105, 77 FR 55115, Sept. 7, 2012] § 420.69 Separation distance requirements for co-location of division 1.1 and 1.3 explosives with liquid propellants. (a) Separation of energetic liquids and explosives and determination of distances. (b) Liquid propellants and division 1.1 explosives located together. (1) Determine the explosive equivalent weight of the liquid propellants by following § 420.67(c); (2) Add the explosive equivalent weight of the liquid propellants and the net explosive weight of division 1.1 explosives to determine the combined net explosive weight; (3) Use the combined net explosive weight to determine the distance to each public area, public traffic route, and each other explosive hazard facility by following tables E-1, E-2, and E-3 of appendix E of this part; and (4) Separate each public area containing any member of the public in the open by a distance equal to −1133.9 + [389 *ln(NEW)], where the net explosive weight is greater than 450 pounds and less than 501,500 pounds. (c) Liquid propellants and division 1.3 explosives located together. (1) Method 1. (ii) Add to the explosive equivalent weight of the liquid propellants, the net explosive weight of each division 1.3 explosive, treating division 1.3 explosives as division 1.1 explosives; (iii) Use the combined net explosive weight to determine the minimum separation distance to each public area, public traffic route, and each other explosive hazard facility by following tables E-1, E-2, and E-3 of appendix E of this part; and (iv) Separate each public area containing any member of the public in the open by a distance equal to −1133.9 + [389 *ln(NEW)], where the net explosive weight is greater than 450 pounds and less than 501,500 pounds. (2) Method 2. (ii) Add to the explosive equivalent weight of the liquid propellants, the net explosive weight of each division 1.3 explosive to determine the combined net explosive weight; (iii) Use the combined net explosive weight to determine the minimum separation distance to each public area, public traffic route, and each other explosive hazard facility by following tables E-1, E-2, and E-3 of appendix E of this part; and (iv) Separate each public area containing any member of the public in the open by a distance equal to −1133.9 + [389 *ln(NEW)], where the net explosive weight is greater than 450 pounds and less than 501,500 pounds. (d) Liquid propellants and division 1.1 and 1.3 explosives located together. (1) Determine the explosive equivalent weight of the liquid propellants by following § 420.67(c); (2) Determine the total explosive quantity of each division 1.1 and 1.3 explosive by following § 420.65(a)(2); (3) Add the explosive equivalent weight of the liquid propellants to the total explosive quantity of division 1.1 and 1.3 explosives together to determine the combined net explosive weight; (4) Use the combined net explosive weight to determine the distance to each public area, public traffic route, and each other explosive hazard facility by following tables E-1, E-2, and E-3 of appendix E of this part; and (5) Separate each public area containing any member of the public in the open by a distance equal to −1133.9 + [389 *ln(NEW)], where the net explosive weight is greater than 450 pounds and less than 501,500 pounds (e) Use of maximum credible event analysis. [Doc. No. FAA-2011-0105, 77 FR 55115, Sept. 7, 2012] § 420.70 Separation distance measurement requirements. (a) This section applies to all measurements of distances performed under §§ 420.63 through 420.69. (b) A launch site operator must measure each separation distance along straight lines. For large intervening topographical features such as hills, the launch site operator must measure over or around the feature, whichever is the shorter. (c) A launch site operator must measure each minimum separation distance from the closest hazard source, such as a container, building, segment, or positive cut-off point in piping, in an explosive hazard facility. When measuring, a launch site operator must: (1) For a public traffic route distance, measure from the nearest side of the public traffic route to the closest point of the hazard source; and (2) For an intraline distance, measure from the nearest point of one hazard source to the nearest point of the next hazard source. The minimum separation distance must be the distance for the quantity of energetic liquids or net explosive weight that requires the greater distance. [Doc. No. FAA-2011-0105, 77 FR 55116, Sept. 7, 2012] § 420.71 Lightning protection. (a) Lightning protection. (1) Elements of a lighting protection system. (i) Air terminal. (ii) Down conductor. (iii) Earth electrode system. (2) Bonding and surge protection. (i) Bonding. (ii) Surge protection. (3) Circumstances where no lightning protection system is required. (4) Testing and inspection. (b) Electrical power lines. (1) Electric power lines shall be no closer to an explosive hazard facility than the length of the lines between the poles or towers that support the lines unless an effective means is provided to ensure that energized lines cannot, on breaking, come in contact with the explosive hazard facility. (2) Towers or poles supporting electrical distribution lines that carry between 15 and 69 KV, and unmanned electrical substations shall be no closer to an explosive hazard facility than the public area distance for that explosive hazard facility. (3) Towers or poles supporting electrical transmission lines that carry 69 KV or more, shall be no closer to an explosive hazard facility than the public area distance for that explosive hazard facility. Appendix A to Part 420—Method for Defining a Flight Corridor (a) Introduction (1) This appendix provides a method for constructing a flight corridor from a launch point for a guided suborbital launch vehicle or any one of the four classes of guided orbital launch vehicles from table 1, § 420.19, without the use of local meteorological data or a launch vehicle trajectory. (2) A flight corridor includes an overflight exclusion zone in a launch area and, for a guided suborbital launch vehicle, an impact dispersion area in a downrange area. A flight corridor for a guided suborbital launch vehicle ends with the impact dispersion area, and, for the four classes of guided orbital launch vehicles, 5000 nautical miles (nm) from the launch point. (b) Data requirements (1) Maps. An applicant shall use any map for the launch site region with a scale not less than 1:250,000 inches per inch in the launch area and 1:20,000,000 inches per inch in the downrange area. As described in paragraph (b)(2), an applicant shall use a mechanical method, a semi-automated method, or a fully-automated method to plot a flight corridor on maps. A source for paper maps acceptable to the FAA is the U.S. Dept. of Commerce, National Oceanic and Atmospheric Administration, National Ocean Service. (i) Projections for mechanical plotting method. An applicant shall use a conic projection. The FAA will accept a “Lambert-Conformal” conic projection. A polar aspect of a plane-azimuthal projection may also be used for far northern launch sites. (ii) Projections for semi-automated plotting method. An applicant shall use cylindrical, conic, or plane projections for semi-automated plotting. The FAA will accept “Mercator” and “Oblique Mercator” cylindrical projections. The FAA will accept “Lambert-Conformal” and “Albers Equal-Area” conic projections. The FAA will accept “Lambert Azimuthal Equal-Area” and “Azimuthal Equidistant” plane projections. (iii) Projections for fully-automated plotting method. The FAA will accept map projections used by geographical information system software scaleable pursuant to the requirements of paragraph (b)(1). (2) Plotting Methods. (i) Mechanical method. An applicant may use mechanical drafting equipment such as pencil, straight edge, ruler, protractor, and compass to plot the location of a flight corridor on a map. The FAA will accept straight lines for distances less than or equal to 7.5 times the map scale on map scales greater than or equal to 1:1,000,000 inches per inch (in/in); or straight lines representing 100 nm or less on map scales less than 1:1,000,000 in/in. (ii) Semi-automated method. An applicant may employ the range and bearing techniques in paragraph (b)(3) to create latitude and longitude points on a map. The FAA will accept straight lines for distances less than or equal to 7.5 times the map scale on map scales greater than or equal to 1:1,000,000 inches per inch (in/in); or straight lines representing 100 nm or less on map scales less than 1:1,000,000 in/in. (iii) Fully-automated method. An applicant may use geographical information system software with global mapping data scaleable in accordance with paragraph (b)(1). (3) Range and bearing computations on an ellipsoidal Earth model. (i) To create latitude and longitude pairs on an ellipsoidal Earth model, an applicant shall use the following equations to calculate geodetic latitude (+N) and longitude (+E) given the launch point geodetic latitude (+N), longitude (+E), range (nm), and bearing (degrees, positive clockwise from North). (A) Input. An applicant shall use the following input in making range and bearing computations. Angle units must be in radians. (B) Computations. An applicant shall use the following equations to determine the latitude (φ 2 2 12 where: a = WGS-84 semi-major axis (3443.91846652 nmi) b = WGS-84 semi-minor axis (3432.37165994 nmi) (ii) To create latitude and longitude pairs on an ellipsoidal Earth model, an applicant shall use the following equations to calculate the distance (S) of the geodesic between two points (P 1 2 12 1 21 2 1 2 (A) Input. An applicant shall use the following input. Units must be in radians. (B) Computations. An applicant shall use the following equations to determine the distance (S), the forward azimuth (α 12 1 12 2 where: a = WGS-84 semi-major axis (3443.91846652 nmi) b = WGS-84 semi-minor axis (3432.37165994 nmi) (c) Creation of a Flight Corridor (1) To define a flight corridor, an applicant shall: (i) Select a guided suborbital or orbital launch vehicle, and, for an orbital launch vehicle, select from table 1 of § 420.19 a launch vehicle weight class that best represents the launch vehicle the applicant plans to support at its launch point; (ii) Select a debris dispersion radius (D max (iii) Select a launch point geodetic latitude and longitude; and (iv) Select a flight azimuth. (2) An applicant shall define and map an overflight exclusion zone using the following method: (i) Select a debris dispersion radius (D max OEZ (ii) An overflight exclusion zone is described by the intersection of the following boundaries, which are depicted in figure A-1: (A) An applicant shall define an uprange boundary with a half-circle arc of radius D max max (B) An applicant shall define the downrange boundary with a half-circle arc of radius D max max OEZ (C) Crossrange boundaries of an overflight exclusion zone are defined by two lines segments. Each is parallel to the flight azimuth with one to the left side and one to the right side of the flight azimuth line. Each line connects an uprange half-circle arc endpoint to a downrange half-circle arc endpoint as shown in figure A-1. (iii) An applicant shall identify the overflight exclusion zone on a map that meets the requirements of paragraph (b). (3) An applicant shall define and map a flight corridor using the following method: (i) In accordance with paragraph (b), an applicant shall draw a flight corridor on one or more maps with the D max (ii) An applicant shall define the flight corridor using the following boundary definitions: (A) An applicant shall draw an uprange boundary, which is defined by an arc-line GB (figure A-2), directly uprange from and centered on the intended launch point with radius D max (B) An applicant shall draw line CF perpendicular to and centered on the flight azimuth line, and positioned 10 nm downrange from the launch point. The applicant shall use the length of line CF provided in table A-3 corresponding to the guided suborbital launch vehicle or orbital launch vehicle class selected in paragraph (c)(1)(i). (C) An applicant shall draw line DE perpendicular to and centered on the flight azimuth line, and positioned 100 nm downrange from the launch point. The applicant shall use the length of line DE provided in table A-3 corresponding to the guided suborbital launch vehicle or orbital launch vehicle class selected in paragraph (c)(1)(i). (D) Except for a guided suborbital launch vehicle, an applicant shall draw a downrange boundary, which is defined by line HI and is drawn perpendicular to and centered on the flight azimuth line, and positioned 5,000 nm downrange from the launch point. The applicant shall use the length of line HI provided in table A-3 corresponding to the orbital launch vehicle class selected in paragraph (c)(1)(i). (E) An applicant shall draw crossrange boundaries, which are defined by three lines on the left side and three lines on the right side of the flight azimuth. An applicant shall construct the left flight corridor boundary according to the following, and as depicted in figure A-3 : (1) The first line (line BC in figure A-3) is tangent to the uprange boundary arc, and ends at endpoint C of line CF, as depicted in figure A-3; (2) The second line (line CD in figure A-3) begins at endpoint C of line BC and ends at endpoint D of line DH, as depicted in figure A-3; (3) For all orbital launch vehicles, the third line (line DH in figure A-3) begins at endpoint D of line CD and ends at endpoint H of line HI, as depicted in figure A-3; and (4) For a guided suborbital launch vehicle, the line DH begins at endpoint D of line CD and ends at a point tangent to the impact dispersion area drawn in accordance with paragraph (c)(4) and as depicted in figure A-4. (F) An applicant shall repeat the procedure in paragraph (c)(3)(ii)(E) for the right side boundary. (iii) An applicant shall identify the flight corridor on a map that meets the requirements of paragraph (b). (4) For a guided suborbital launch vehicle, an applicant shall define a final stage impact dispersion area as part of the flight corridor and show the impact dispersion area on a map, as depicted in figure A-4, in accordance with the following: (i) An applicant shall select an apogee altitude (H ap (ii) An applicant shall define the impact dispersion area by using an impact range factor [IP(H ap ap (A) An applicant shall calculate the impact range (D) for the final launch vehicle stage. An applicant shall set D equal to the maximum apogee altitude (H ap where: IP(H ap ap (B) An applicant shall calculate the impact dispersion radius (R) for the final launch vehicle stage. An applicant shall set R equal to the maximum apogee altitude (H ap where: DISP(H ap (iii) An applicant shall draw the impact dispersion area on a map with its center on the predicted impact point. An applicant shall then draw line DH in accordance with paragraph (c)(3)(ii)(E)(4). (d) Evaluate the Flight Corridor (1) An applicant shall evaluate the flight corridor for the presence of any populated areas. If an applicant determines that no populated area is located within the flight corridor, then no additional steps are necessary. (2) If a populated area is located in an overflight exclusion zone, an applicant may modify its proposal or demonstrate that there are times when no people are present or that the applicant has an agreement in place to evacuate the public from the overflight exclusion zone during a launch. (3) If a populated area is located within the flight corridor, an applicant may modify its proposal and create another flight corridor pursuant to appendix A, use appendix B to narrow the flight corridor, or complete a risk analysis in accordance with appendix C. Table A-1—Debris Dispersion Radius (D max Orbital launch vehicles Suborbital launch vehicles Small Medium Medium large Large Guided 87,600 111,600 127,200 156,000 96,000 Table A-2—Overflight Exclusion Zone Downrange Distance (D oez Orbital launch vehicles Suborbital launch vehicles Small Medium Medium large Large Guided 240,500 253,000 310,300 937,700 232,100 Appendix B to Part 420—Method for Defining a Flight Corridor (a) Introduction (1) This appendix provides a method to construct a flight corridor from a launch point for a guided suborbital launch vehicle or any one of the four weight classes of guided orbital launch vehicles from table 1, § 420.19, using local meteorological data and a launch vehicle trajectory. (2) A flight corridor is constructed in two sections—one section comprising a launch area and one section comprising a downrange area. The launch area of a flight corridor reflects the extent of launch vehicle debris impacts in the event of a launch vehicle failure and applying local meteorological conditions. The downrange area reflects the extent of launch vehicle debris impacts in the event of a launch vehicle failure and applying vehicle imparted velocity, malfunctions turns, and vehicle guidance and performance dispersions. (3) A flight corridor includes an overflight exclusion zone in the launch area and, for a guided suborbital launch vehicle, an impact dispersion area in the downrange area. A flight corridor for a guided suborbital launch vehicle ends with an impact dispersion area and, for the four classes of guided orbital launch vehicles, 5,000 nautical miles (nm) from the launch point, or where the IIP leaves the surface of the Earth, whichever is shorter. (b) Data Requirements (1) Launch area data requirements. An applicant shall satisfy the following data requirements to perform the launch area analysis of this appendix. The data requirements are identified in table B-1 along with sources where data acceptable to the FAA may be obtained. (i) An applicant must select meteorological data that meet the specifications in table B-1 for the proposed launch site. Table B-1—Launch Area Data Requirements Data category Data item Data source Meteorological Data Local statistical wind data as a function of altitude up to 50,000 feet. Required data include: altitude (ft), atmospheric density (slugs/ft 3 These data may be obtained from: Nominal Trajectory Data State vector data as function of time after liftoff in topocentric launch point centered X,Y,Z,X,Y,Z coordinates with the X-axis aligned with the flight azimuth. Trajectory time intervals shall not be greater than one second. XYZ units are in feet and X,Y,Z units are in ft/sec Actual launch vehicle trajectory data; or trajectory generation software that meets the requirements of paragraph (b)(1)(ii). Debris Data A fixed ballistic coefficient equal to 3 lbs/ft 2 N/A. Geographical Data Launch point geodetic latitude on a WGS-84 ellipsoidal Earth model Geographical surveys or Global Positioning System. Launch point longitude on an ellipsoidal Earth model Maps using scales of not less than 1:250,000 inches per inch within 100 nm of a launch point and 1:20,000,000 inches per inch for distances greater than 100 nm from a launch point Map types with scale and projection information are listed in the Defense Mapping Agency, Public Sale, Aeronautical Charts and Publications Catalog. The catalog and maps may be ordered through the U.S. Dept. of Commerce, National Oceanic and Atmospheric Administration, National Ocean Service. (ii) For a guided orbital launch vehicle, an applicant shall obtain or create a launch vehicle nominal trajectory. An applicant may use trajectory data from a launch vehicle manufacturer or generate a trajectory using trajectory simulation software. Trajectory time intervals shall be no greater than one second. If an applicant uses a trajectory computed with commercially available software, the software must calculate the trajectory using the following parameters, or clearly and convincingly demonstrated equivalents: (A) Launch location: ( 1 ( 2 (B) Ellipsoidal Earth: ( 1 ( 2 ( 3 ( 4 (C) Vehicle characteristics: ( 1 ( 2 ( 3 SP ( 4 (D) Launch events: ( 1 ( 2 (E) Atmosphere: ( 1 ( 2 ( 3 ( 4 (F) Winds: (1) Wind direction as a function of altitude; and (2) Wind magnitude as a function of altitude. (I) Aerodynamics: drag coefficient as a function of mach number for each stage of flight showing subsonic, transonic and supersonic mach regions for each stage. (iii) An applicant shall use a ballistic coefficient (β) of 3 lbs/ft 2 (iv) An applicant shall satisfy the map and plotting requirements for a launch area of appendix A, paragraph (b). (2) Downrange area data requirements. An applicant shall satisfy the following data requirements to perform the downrange area analysis of this appendix. (i) The launch vehicle weight class and method of generating a trajectory used in the launch area shall be used by an applicant in the downrange area as well. Trajectory time intervals must not be greater than one second. (ii) An applicant shall satisfy the map and plotting data requirements for a downrange area of appendix A, paragraph (b). (c) Construction of a Launch Area of a Flight Corridor (1) An applicant shall construct a launch area of a flight corridor using the processes and equations of this paragraph for each trajectory position. An applicant shall repeat these processes at time points on the launch vehicle trajectory for time intervals of no greater than one second. When choosing wind data, an applicant shall use a time period of between one and 12 months. (2) A launch area analysis must include all trajectory positions whose Z-values are less than or equal to 50,000 ft. (3) Each trajectory time is denoted by the subscript “i”. Height intervals for a given atmospheric pressure level are denoted by the subscript “j'. (4) Using data from the GGUAS CD-ROM, an applicant shall estimate the mean atmospheric density, maximum wind speed, height interval fall times and height interval debris dispersions for 15 mean geometric height intervals. (i) The height intervals in the GGUAS source data vary as a function of the following 15 atmospheric pressure levels expressed in millibars: surface, 1000, 850, 700, 500, 400, 300, 250, 200, 150, 100, 70, 50, 30, 10. The actual geometric height associated with each pressure level varies depending on the time of year. An applicant shall estimate the mean geometric height over the period of months selected in subparagraph (1) of this paragraph for each of the 15 pressure levels as shown in equation B1. where: H j m m k = number of wind months of interest (ii) The atmospheric densities in the source data also vary as a function of the 15 atmospheric pressure levels. The actual atmospheric density associated with each pressure level varies depending on the time of year. An applicant shall estimate the mean atmospheric density over the period of months selected in accordance with subparagraph (1) of this paragraph for each of the 15 pressure levels as shown in equation B2. where: ρ j _ ρ m n m k = number of wind months of interest (iii) An applicant shall estimate the algebraic maximum wind speed at a given pressure level as follows and shall repeat the process for each pressure level. (A) For each month, an applicant shall calculate the monthly mean wind speed (W az (B) An applicant shall select the maximum monthly mean wind speed from the 360 azimuths; (C) An applicant shall repeat subparagraphs (c)(4)(iii)(A) and (B) for each month of interest; and (D) An applicant shall select the maximum mean wind speed from the range of months. The absolute value of this wind is designated W max (iv) An applicant shall calculate wind speed using the means for winds from the West (u) and winds from the North (v). An applicant shall use equation B3 to resolve the winds to a specific azimuth bearing. where: az = wind azimuth u = West zonal wind component v = North zonal wind component W az (v) An applicant shall estimate the interval fall time over a height interval assuming the initial descent velocity is equal to the terminal velocity (V T where: ΔH Tj β = ballistic coefficient _ ρx = mean atmospheric density for the corresponding mean geometric heights V Tj (vi) An applicant shall estimate the interval debris dispersion (D j max (5) Once the Dj are estimated for each height interval, an applicant shall determine the total debris dispersion (D i i where: n = number of height intervals below jth height interval (6) Once all the D i (i) On a map meeting the requirements of appendix A, paragraph (b), an applicant shall plot the X i i (ii) An applicant shall draw a circle of radius D i i (iii) An applicant shall repeat the instructions in subparagraphs (c)(6)(i)-(ii) for each D i (iv) The launch area of a flight corridor is the enveloping line that encloses the outer boundary of the D i i (7) An applicant shall define an overflight exclusion zone in the launch area in accordance with the requirements of appendix A, subparagraph (c)(2). (8) An applicant shall draw the launch area flight corridor and overflight exclusion zone on a map or maps that meet the requirements of table B-1. (d) Construction of a Downrange Area of a Flight Corridor (1) The downrange area analysis estimates the debris dispersion for the downrange time points on a launch vehicle trajectory. An applicant shall perform the downrange area analysis using the processes and equations of this paragraph. (2) The downrange area analysis shall include trajectory positions at a height (the Z i (3) An applicant shall compute the downrange area of a flight corridor boundary in four steps, from each trajectory time increment: determine a reduction ratio factor; calculate the launch vehicle position after simulating a malfunction turn; rotate the state vector after the malfunction turn in the range of three degrees to one degree as a function of X i (i) Compute the downrange Distance to the final IIP position for a nominal trajectory as follows: (A) Using equations B30 through B69, determine the IIP coordinates (φ max max (B) Using the range and bearing equations of appendix A, paragraph (b)(3), determine the distance (S max lp lp max max (C) The distance for S max max (ii) Compute the reduction ratio factor (F n (A) Using equations B30 through B69, determine the IIP coordinates (φ i i (B) Using the range and bearing equations of appendix A, paragraph (b)(3), determine the distance (S i lp lp i i (C) The reduction ratio factor is: (iii) An applicant shall compute the launch vehicle position and velocity components after a simulated malfunction turn for each X i (A) Turn duration (Δt) = 4 sec. (B) Turn angle (θ) The turn angle equations perform a turn in the launch vehicle's yaw plane, as depicted in figure B-2. (C) Launch vehicle velocity magnitude at the beginning of the turn (V b e (D) Average velocity magnitude over the turn duration (V (E) Velocity vector path angle (γ i (F) Launch vehicle position components at the end of turn duration where: g 1 2 (G) Launch vehicle velocity components at the end of turn duration (iv) An applicant shall rotate the trajectory state vector at the end of the turn duration to the right and left to define the right-lateral flight corridor boundary and the left-lateral flight corridor boundary, respectively. An applicant shall perform the trajectory rotation in conjunction with a trajectory transformation from the X 90 90 90 90 90 90 (A) An applicant must calculate the flight angle (α) (B) An applicant shall transform X 90 90 90 (C) An applicant shall transform to X 90 90 90 (D) An applicant shall transform the launch point coordinates (φ 0 0 0 0 0 0 (E) An applicant shall transform E,N,U to E 90 90 90 (F) An applicant shall transform to E (v) The IIP computation implements an iterative solution to the impact point problem. An applicant shall solve equations B46 through B69, with the appropriate substitutions, up to a maximum of five times. Each repetition of the equations provides a more accurate prediction of the IIP. An applicant shall use the required IIP computations of paragraphs (d)(3)(v)(A)-(W) below. An applicant shall use this IIP computation for both the left-and right-lateral offsets. The IIP computations will result in latitude and longitude pairs for the left-lateral flight corridor boundary and the right-lateral flight corridor boundary. An applicant shall use the lines connecting the latitude and longitude pairs to describe the entire downrange area boundary of the flight corridor up to 5000 nm or a final stage impact dispersion area. (A) An applicant shall approximate the radial distance (r k,l k,l (B) An applicant shall compute the radial distance (r) from the geocenter to the launch vehicle position. If r <r k,l (C) An applicant shall compute the inertial velocity components. where: ω = 4.178074 × 10 −3 (D) An applicant shall compute the magnitude of the inertial velocity vector. (E) An applicant shall compute the eccentricity of the trajectory ellipse multiplied by the cosine of the eccentric anomaly at epoch ε c where: K = 1.407644 × 10 16 3 2 (F) An applicant shall compute the semi-major axis of the trajectory ellipse (a t If a t t (G) An applicant shall compute the eccentricity of the trajectory ellipse multiplied by the sine of the eccentric anomaly at epoch ε s (H) An applicant shall compute the eccentricity of the trajectory ellipse squared ε 2 If a t E (I) An applicant shall compute the eccentricity of the trajectory ellipse multiplied by the cosine of the eccentric anomaly at impact (ε c k (J) An applicant shall compute the eccentricity of the trajectory ellipse multiplied by the sine of the eccentric anomaly at impact (ε s k If ε s k (K) An applicant shall compute the cosine of the difference between the eccentric anomaly at impact and the eccentric anomaly at epoch (Δε c k (L) An applicant shall compute the sine of the difference between the eccentric anomaly at impact and the eccentric anomaly at epoch (Δε s k (M) An applicant shall compute the f-series expansion of Kepler's equations. (N) An applicant shall compute the g-series expansion of Kepler's equations. (O) An applicant shall compute the E,F,G coordinates at impact (E i i i (P) An applicant shall approximate the distance from the geocenter to the launch vehicle position at impact (r k,2 where: a E e 2 (Q) An applicant shall let r k + 1,1 k,2 k + 1,1 k,1 5,1 5,2 (R) An applicant shall compute the difference between the eccentric anomaly at impact and the eccentric anomaly at epoch (Δε). (S) An applicant shall compute the time of flight from epoch to impact (t). (T) An applicant shall compute the geocentric latitude at impact (φ'). Where: + 90° >φ′ i (U) An applicant shall compute the geodetic latitude at impact (φ). Where: + 90°>φ i (V) An applicant shall compute the East longitude at impact (λ). (W) If the range from the launch point to the impact point is equal to or greater than 5000 nm, an applicant shall terminate IIP computations. (4) For a guided suborbital launch vehicle, an applicant shall define a final stage impact dispersion area as part of the flight corridor and show the area on a map using the following procedure: (i) For equation B70 below, an applicant shall use an apogee altitude (H ap (ii) An applicant shall define the final stage impact dispersion area by using a dispersion factor [DISP(H ap ap where: DISP(H ap (5) An applicant shall combine the launch area and downrange area flight corridor and any final stage impact dispersion area for a guided suborbital launch vehicle. (i) On the same map with the launch area flight corridor, an applicant shall plot the latitude and longitude positions of the left and right sides of the downrange area of the flight corridor calculated in accordance with subparagraph (d)(3). (ii) An applicant shall connect the latitude and longitude positions of the left side of the downrange area of the flight corridor sequentially starting with the last IIP calculated on the left side and ending with the first IIP calculated on the left side. An applicant shall repeat this procedure for the right side. (iii) An applicant shall connect the left sides of the launch area and downrange portions of the flight corridor. An applicant shall repeat this procedure for the right side. (iv) An applicant shall plot the overflight exclusion zone defined in subparagraph (c)(7). (v) An applicant shall draw any impact dispersion area on the downrange map with the center of the impact dispersion area on the launch vehicle final stage impact point obtained from the applicant's launch vehicle trajectory analysis done in accordance with subparagraph (b)(1)(ii). (e) Evaluate the Launch Site (1) An applicant shall evaluate the flight corridor for the presence of populated areas. If no populated area is located within the flight corridor, then no additional steps are necessary. (2) If a populated area is located in an overflight exclusion zone, an applicant may modify its proposal or demonstrate that there are times when no people are present or that the applicant has an agreement in place to evacuate the public from the overflight exclusion zone during a launch. (3) If a populated area is located within the flight corridor, an applicant may modify its proposal or complete an overflight risk analysis in accordance with appendix C. Appendix C to Part 420—Risk Analysis (a) Introduction (1) This appendix provides a method for an applicant to estimate the expected casualty (E c (2) An applicant shall perform a risk analysis when a populated area is located within a flight corridor defined by either appendix A or appendix B. If the estimated expected casualty exceeds 1 × 10 −4 −4 (b) Data Requirements (1) An applicant shall obtain the data specified by subparagraphs (b)(2) and (3) and summarized in table C-1. Table C-1 provides sources where an applicant may obtain data acceptable to the FAA. An applicant must also employ the flight corridor information from appendix A or B, including flight azimuth and, for an appendix B flight corridor, trajectory information. (2) Population data. Total population (N) and the total landmass area within a populated area (A) are required. Population data up to and including 100 nm from the launch point are required at the U.S. census block group level. Population data downrange from 100 nm are required at no greater than 1° × 1° latitude/longitude grid coordinates. (3) Launch vehicle data. Launch vehicle data consist of the launch vehicle failure probability (P f c d f d Table C-1—Overflight Analysis Data Requirements Data category Data item Data source Population Data Total population within a populated area (N) Within 100 nm of the launch point: U.S. census data at the census block-group level. Downrange from 100 nm beyond the launch point, world population data are available from: Total landmass area within the populated area (A) Carbon Dioxide Information Analysis Center (CDIAC) Oak Ridge National Laboratory Launch Vehicle Data Failure probability—P f N/A. Effective casualty area (A c See table C-3. Overflight dwell time Determined by range from the launch point or trajectory used by applicant. Nominal trajectory data (for an appendix B flight corridor only) See appendix B, table B-1. (c) Estimating Corridor Casualty Expectation (1) A corridor casualty expectation [E C (2) An applicant shall identify and locate each populated area in the proposed flight corridor. (3) An applicant shall determine the probability of impact in each populated area using the procedures in subparagraphs (5) or (6) of this paragraph. Figures C-1 and C-2 illustrate an area considered for probability of impact (P i C (4) The P i i (5) Probability of impact (P i i (i) For the launch and downrange areas, but not for a final stage impact dispersion area for a guided suborbital launch vehicle, an applicant shall compute P i where: x 1 2 y 1 2 σ y exp = exponential function (e x P f R C = 643 seconds (constant) Table C-2—IIP Range Rate vs. IIP Range IIP range IIP range rate 0-75 0.75 76-300 1.73 301-900 4.25 901-1700 8.85 1701-2600 19.75 2601-3500 42.45 3501-4500 84.85 4501-5250 154.95 (ii) For each populated area within a final stage impact dispersion area, an applicant shall compute P i (A) An applicant shall estimate the probability of final stage impact in the x and y sectors of each populated area within the final stage impact dispersion area using equations C2 and C3: where: X 1 2 σ x exp = exponential function (e x where: y 1 2 σ y exp = exponential function (e x (B) If a populated area intersects the impact dispersion area boundary so that the x 2 2 2 2 2 1 2 1 2 y (C) An applicant shall calculate the probability of impact for each populated area using equation C4 below: where: P s f (6) Probability of impact computations for a populated area in an appendix B flight corridor. An applicant shall compute P i (i) For the launch and downrange areas, but not for a final stage impact dispersion area for a guided suborbital launch vehicle, an applicant shall compute P i where: y 1 2 σ y exp = exponential function (e x P f t = flight time from lift-off to orbital insertion (seconds) t d (ii) For each populated area within a final stage impact dispersion area, an applicant shall compute P i (A) An applicant shall estimate the probability of final stage impact in the x and y sectors of each populated area within the final stage impact dispersion area using equations C6 and C7: where: x 1 2 σ x exp = exponential function (e x where: y 1 2 σ y exp = exponential function (e x (B) If a populated area intersects the impact dispersion area boundary so that the x 2 2 2 2 2 1 2 1 2 y (C) An applicant shall calculate the probability of impact for each populated area using equation C8 below: where: P s f (7) Using the P i ck where: A c A k N k k Table C-3—Effective Casualty Area (Miles 2 Orbital launch vehicles Suborbital launch Instantaneous impact point range (nautical miles) Small Medium Medium large Large Guided 0-49 3.14 × 10 −2 1.28 × 10 −1 4.71 × 10 −2 8.59 × 10 −2 4.3 × 10 −1 50-1749 2.47 × 10 −2 2.98 × 10 −2 9.82 × 10 −3 2.45 × 10 −2 1.3 × 10 −1 1750-5000 3.01 × 10 −4 5.52 × 10 −3 7.82 × 10 −3 1.14 × 10 −2 3.59 × 10 −6 (8) An applicant shall estimate the total corridor risk using the following summation of risk: (9) Alternative casualty expectancy (E C C C (i) Assume that P x y (ii) Combine populated areas into one or more larger populated areas, and use a population density for the combined area or areas equal to the most densely populated area. (iii) For any given populated area, assume P y (iv) For any given P x y (v) For a given populated area, divide the populated area into smaller rectangles, determine P i i (vi) For a given populated area, use the ratio of the populated area to the area of the P i (d) Evaluation of Results (1) If the estimated expected casualty does not exceed 1 × 10 −4 (2) If the estimated expected casualty exceeds 1 × 10 −4 [Doc. No. FAA-1999-5833, 65 FR 62861, Oct. 19, 2000, as amended by Amdt. 420-2, 71 FR 51972, Aug. 31, 2006; Docket No. FAA-2014-0418, Amdt. No. 420-7, 81 FR 47027, July 20, 2016] Appendix D to Part 420—Impact Dispersion Areas and Casualty Expectancy Estimate for an Unguided Suborbital Launch Vehicle (a) Introduction (1) This appendix provides a method for determining the acceptability of the location of a launch point from which an unguided suborbital launch vehicle would be launched. The appendix describes how to define an overflight exclusion zone and impact dispersion areas, and how to evaluate whether the public risk presented by the launch of an unguided suborbital launch vehicle remains at acceptable levels. (2) An applicant shall base its analysis on an unguided suborbital launch vehicle whose final launch vehicle stage apogee represents the intended use of the launch point. (3) An applicant shall use the apogee of each stage of an existing unguided suborbital launch vehicle with a final launch vehicle stage apogee equal to the one proposed, and calculate each impact range and dispersion area using the equations provided. (4) This appendix also provides a method for performing an impact risk analysis that estimates the expected casualty (E c (5) If the estimated E c −4 c −4 (b) Data Requirements (1) An applicant shall employ the apogee of each stage of an existing unguided suborbital launch vehicle whose final stage apogee represents the maximum altitude to be reached by unguided suborbital launch vehicles launched from the launch point. The apogee shall be obtained from one or more actual flights of an unguided suborbital launch vehicle launched at an 84 degree elevation. (2) An applicant shall satisfy the map and plotting data requirements of appendix A, paragraph (b). (3) Population data. An applicant shall use total population (N) and the total landmass area within a populated area (A) for all populated areas within an impact dispersion area. Population data up to and including 100 nm from the launch point are required at the U.S. census block group level. Population data downrange from 100 nm are required at no greater than 1° × 1° latitude/longitude grid coordinates. (c) Overflight Exclusion Zone and Impact Dispersion Areas (1) An applicant shall choose a flight azimuth from a launch point. (2) An applicant shall define an overflight exclusion zone as a circle with a radius of 1600 feet centered on the launch point. (3) An applicant shall define an impact dispersion area for each stage of the suborbital launch vehicle chosen in accordance with subparagraph (b)(1) in accordance with the following: (i) An applicant shall calculate the impact range for the final launch vehicle stage (D n n n n where: IP(H n IP(H n (ii) An applicant shall calculate the impact range for each intermediate stage (D i i i n (iii) An applicant shall calculate the impact dispersion radius for the final launch vehicle stage (R n n n n where: DISP(H n DISP(Hn) = 0.7 for an apogee of 100 km or greater. (iv) An applicant shall calculate the impact dispersion radius for each intermediate stage (R i i i n (4) An applicant shall display an overflight exclusion zone, each intermediate and final stage impact point (D i n (d) Evaluate the Overflight Exclusion Zone and Impact Dispersion Areas (1) An applicant shall evaluate the overflight exclusion zone and each impact dispersion area for the presence of any populated areas. If an applicant determines that no populated area is located within the overflight exclusion zone or any impact dispersion area, then no additional steps are necessary. (2) If a populated area is located in an overflight exclusion zone, an applicant may modify its proposal or demonstrate that there are times when no people are present or that the applicant has an agreement in place to evacuate the public from the overflight exclusion zone during a launch. (3) If a populated area is located within any impact dispersion area, an applicant may modify its proposal and define a new overflight exclusion zone and new impact dispersion areas, or perform an impact risk analysis in accordance with paragraph (e). (e) Impact Risk Analysis (1) An applicant shall estimate the expected average number of casualties, E C (i) An applicant shall calculate the E c c (ii) An applicant shall estimate the probability of impacting inside the X and Y sectors of each populated area within each impact dispersion area using equations D3 and D4: where: x 1 2 σ x exp = exponential function (e x where: y 1 2 σ y exp = exponential function (e x (iii) If a populated area intersects the impact dispersion area boundary so that the x 2 2 2 2 2 (iv) If a populated area intersects the flight azimuth, an applicant shall solve equation D4 by obtaining the solution in two parts. An applicant shall determine, first, the probability between y 1 2 1 2 y (v) An applicant shall calculate the probability of impact (P i where: P s (vi) An applicant shall calculate the casualty expectancy for each populated area. E c k where: k A c A k N k k Table D-1—Effective Casualty Area (A c Impact range (nm) Effective casualty area 2 0-4 9 × 10 −3 5-49 9 × 10 −3 50-1,749 1.1 × 10 −5 1,750-4,999 3.6 × 10 −6 5,000-more 3.6 × 10 −6 (vii) An applicant shall estimate the total risk using the following summation of risk: (viii) Alternative casualty expectancy (E c c c (A) Assume that P x y (B) Combine populated areas into one or more larger populated areas, and use a population density for the combined area or areas equal to the most densely populated area. (C) For any given populated area, assume P x (D) For any given populated area, assume P y (E) For a given populated area, divide the populated area into smaller rectangles, determine P i i (F) For a given populated area, use the ratio of the populated area to the area of the P i (2) If the estimated expected casualty does not exceed 1 × 10 −4 (3) If the estimated expected casualty exceeds 1 × 10 −4 [Docket No. FAA-1999-5833, 65 FR 62861, Oct. 19, 2000, as amended by Docket No. FAA-2014-0418, Amdt. No. 420-7, 81 FR 47027, July 20, 2016] Appendix E to Part 420—Tables for Explosive Site Plan Table E-1—Division 1.1 Distances to a Public Area or Public Traffic Route for NEW ≤450 lbs NEW Distance to public area 1 2 Distance to public traffic route distance 2 ≤0.5 236 142 0.7 263 158 1 291 175 2 346 208 3 378 227 5 419 251 7 445 267 10 474 284 15 506 304 20 529 317 30 561 337 31 563 338 50 601 361 70 628 377 100 658 395 150 815 489 200 927 556 300 1085 651 450 1243 746 1 NEW ≤0.5 lbs: d = 236 0.5 lbs <NEW <100 lbs: d = 291.3 + [79.2 *ln(NEW)] 100 lbs ≤NEW ≤450 lbs: d = −1133.9 + [389 *ln(NEW)] NEW is in lbs; d is in ft; ln is natural logarithm. To calculate maximum NEW given distance d (noting that d can never be less than 236 ft): 0 ≤d <236 ft: Not allowed (d cannot be less than 236 ft) 236 ft ≤d <658 ft: NEW = exp [(d/79.2)-3.678] 658 ft ≤d <1250 ft: NEW = exp [(d/389) + 2.914] NEW is in lbs; d is in ft; exp[x] is e x 2 Table E-2—Division 1.1 Distance to Public Area and Public Traffic Route for NEW >450 lbs NEW (lbs) Distance to public area 1 Distance to public traffic route 450 lbs<NEW ≤30,000 lbs 1,250 750. 30,000 lbs<NEW ≤100,000 lbs 40*NEW 1/3 0.60*(Distance to Public Area). 100,000 lbs<NEW ≤250,000 lbs 2.42*NEW 0.577 0.60*(Distance to Public Area). 250,000 lbs<NEW 50*NEW 1/3 0.60*(Distance to Public Area). 1 1, 243 ft<d ≤1,857 ft: NEW = d 3 1, 857 ft<d ≤3,150 ft: NEW = 0.2162 * d 1.7331 3,150 ft<d: NEW = d 3 NEW is in lbs; d is in ft. Table E-3—Division 1.1 Intraline Distances 1 2 3 NEW Intraline 50 66 70 74 100 84 150 96 200 105 300 120 500 143 700 160 1,000 180 1,500 206 2,000 227 3,000 260 5,000 308 7,000 344 10,000 388 15,000 444 20,000 489 30,000 559 50,000 663 70,000 742 100,000 835 150,000 956 200,000 1,053 300,000 1,205 500,000 3 1,429 700,000 1,598 1,000,000 1,800 1,500,000 2,060 2,000,000 2,268 3,000,000 2,596 5,000,000 3,078 1 d = 18*NEW 1/3 NEW is in pounds; d is in feet 2 NEW = d 3 NEW is in pounds; d is in feet. 3 Table E-4—Division 1.3 Separation Distances NEW (lbs) Distance to public area or public traffic route (ft) 1 Intraline 2 ≤1000 75 50 1,500 82 56 2,000 89 61 3,000 101 68 5,000 117 80 7,000 130 88 10,000 145 98 15,000 164 112 20,000 180 122 30,000 204 138 50,000 240 163 70,000 268 181 100,000 300 204 150,000 346 234 200,000 385 260 300,000 454 303 500,000 569 372 700,000 668 428 1,000,000 800 500 1,500,000 936 577 2,000,000 1,008 630 1 NEW ≤1,000lbs d= 75 ft 1,000 lbs<NEW ≤96,000 lbs d = exp[2.47 + 0.2368*(ln(NEW)) + 0.00384*(ln(NEW)) 2 96,000 lbs<NEW ≤1,000,000 lbs d = exp[7.2297−0.5984*(ln(NEW)) + 0.04046*(ln(NEW)) 2 NEW >1,000,000 lbs d = 8*NEW 1/3 NEW is in pounds; d is in feet; exp[x] is e x To calculate NEW from distance d to a public area or traffic route (noting that d cannot be less than 75 ft): 0 ≤d <75 ft: Not allowed (d cannot be less than 75 ft) for NEW ≤1000 lbs 75 ft ≤d≤296 ft NEW = exp[−30.833 + (307.465 + 260.417*(ln(d))) 1/2 296 ft<d≤800 ft NEW = exp[7.395 + (−124.002 + 24.716*(ln(d))) 1/2 800 ft<d NEW = d 3 NEW is in lbs; d is in ft; exp[x] is e x 2 NEW ≤1,000 lbs d = 50 ft 1,000 lbs<NEW ≤84,000 lbs d = exp[2.0325 + 0.2488*(ln(NEW)) + 0.00313* (ln(NEW)) 2 84,000 lbs<NEW ≤1,000,000 lbs d= exp[4.338 − 2 1,000,000 lbs<NEW d = 5*NEW 1/3 NEW is in pounds; d is in feet; exp[x] is e x To calculate NEW from an intraline distance d: 0 ≤d <50 ft: Not allowed (d cannot be less than 50 ft) for NEW ≤1000 lbs 50 ft ≤d≤192 ft NEW = exp[−39.744 + (930.257 + 319.49*(ln(d))) 1/2 192 ft<d≤500 ft NEW = exp[3.834 + (−181.58 + 45.249*(ln(d))) 1/2 500 ft≤d NEW = d 3 NEW is in pounds; d is in feet; exp[x] is e x Table E-5—Energetic Liquid Explosive Equivalents 1 2 3 Energetic liquids TNT Equivalence TNT Equivalence Static Test Stands Launch Pads. LO 2 2 See Note 3 See Note 3. LO 2 2 2 Sum of (see Note 3 for LO 2 2 2 Sum of (see Note 3 for LO 2 2 2 LO 2 10% 20% up to 500,000 lbs IRFNA/UDMH 10% 10%. N 2 4 2 4 5% 10%. 1 2 Alcohols or other hydrocarbon for RP-1 H 2 2 2 2 2 MMH for N 2 4 3 2 2 (a) TNT equivalency of 8*W 2/3 2 2 (b) 14 percent of the LO 2 2 Table E-6—Factors To Use When Converting Energetic Liquid Densities Item Density Temperature Ethyl alcohol 6.6 68 Hydrazine 8.4 68 Hydrogen peroxide (90 percent) 11.6 68 Liquid hydrogen 0.59 −423 Liquid oxygen 9.5 −297 Red fuming nitric acid (IRFNA) 12.9 77 RP-1 6.8 68 UDMH 6.6 68 UDMH/Hydrazine 7.5 68 Table E-7—Separation Distance Criteria for Storage of Hydrogen Peroxide in Concentrations of More than 91 Percent 1 2 Quantity Intraline distance or distance to public area or distance to public traffic route 10,000 510 15,000 592 20,000 651 30,000 746 50,000 884 70,000 989 100,000 1114 150,000 1275 200,000 1404 300,000 1607 500,000 1905 1 2 W >10,000 lbs Distance = 24 * W 1/3 Where Distance is in ft and W is in lbs. To calculate weight of hydrogen peroxide from a distance d: d >75 ft W = exp[−134.286 + 71.998*(ln(d)) −12.363*(ln(d)) 2 3 Table E-8—Separation Distance Criteria for Storage of Liquid Hydrogen and Bulk Quantities of Hydrazine Pounds of energetic liquid Pounds of energetic liquid Public area and intraline distance to incompatible energetic liquids Intraline distance to compatible energetic liquids Pounds of energetic liquid Pounds of energetic liquid Public area and intraline distance to incompatible energetic liquids Intraline distance to compatible energetic liquids Over Not Over Distance in feet Distance in feet Over Not Over Distance in feet Distance in feet 60,000 70,000 1,200 130 100 200 600 35 70,000 80,000 1,200 130 200 300 600 40 80,000 90,000 1,200 135 300 400 600 45 90,000 100,000 1,200 135 400 500 600 50 100,000 125,000 1,800 140 500 600 600 50 125,000 150,000 1,800 145 600 700 600 55 150,000 175,000 1,800 150 700 800 600 55 175,000 200,000 1,800 155 800 900 600 60 200,000 250,000 1,800 160 900 1,000 600 60 250,000 300,000 1,800 165 1,000 2,000 600 65 300,000 350,000 1,800 170 2,000 3,000 600 70 350,000 400,000 1,800 175 3,000 4,000 600 75 400,000 450,000 1,800 180 4,000 5,000 600 80 450,000 500,000 1,800 180 5,000 6,000 600 80 500,000 600,000 1,800 185 6,000 7,000 600 85 600,000 700,000 1,800 190 7,000 8,000 600 85 700,000 800,000 1,800 195 8,000 9,000 600 90 800,000 900,000 1,800 200 9,000 10,000 600 90 900,000 1,000,000 1,800 205 10,000 15,000 1,200 95 1,000,000 2,000,000 1,800 235 15,000 20,000 1,200 100 2,000,000 3,000,000 1,800 255 20,000 25,000 1,200 105 3,000,000 4,000,000 1,800 265 25,000 30,000 1,200 110 4,000,000 5,000,000 1,800 275 30,000 35,000 1,200 110 5,000,000 6,000,000 1,800 285 35,000 40,000 1,200 115 6,000,000 7,000,000 1,800 295 40,000 45,000 1,200 120 7,000,000 8,000,000 1,800 300 45,000 50,000 1,200 120 8,000,000 9,000,000 1,800 305 50,000 60,000 1,200 125 9,000,000 10,000,000 1,800 310 [Doc. No. FAA-2011-0105, 77 FR 55116, Sept. 7, 2012]

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