Intelsat 27 to 304 5

SUPPLEMENT submitted by Intelsat License LLC

Supplement to Intelsat 27 Application S2827

2012-02-23

This document pretains to SAT-AMD-20111111-00215 for Amended Filing on a Satellite Space Stations filing.

IBFS_SATAMD2011111100215_940248

February 23, 2012 Ms. Marlene H. Dortch Secretary Federal Communications Commission 445 12th Street, S.W. Washington, DC 20554 Re: Supplement to Application for Authority to Launch and Operate Intelsat 27 Call Sign S2827; File No. SAT-LOA-20110610-00105 Dear Ms. Dortch: In response to a question from the FCC staff, Intelsat License LLC (“Intelsat”) hereby corrects an error in its above referenced application for the Intelsat 27 satellite. Specifically, on page 22 of the Engineering Statement, the minimum perigee disposal altitude under the IADC formula for Intelsat 27 should be 285 kilometers above GEO, rather than the 235 kilometers inadvertently stated in the application. The additional data requested by the staff is set forth below: Geostationary Orbit (above the equator): 35786 km Force equation: F= P (CpxS) where P= 4.53.10-6 Nm-2 is the assumed solar flux (reference: Spacecraft Attitude Determination Control by James Wertz, 1978) and (CpxS) is the effective area Solar Radiation Force (provided by the spacecraft manufacturer/vendor) ~ 365x10-6 Newton Estimated Area: P/F = (365x10-6 N) / (4.53x10-6 N/m2) = 80.6 m2 Dry mass of spacecraft: 2821 kg Solar Pressure Coefficient (CR) = 1.1 Estimated A/M = Area / mass = 80.6 m2 / 2821 kg = 0.03 m2/kg A/M adjustment factor = 1.5 (based on the observed Cr for Intelsat’s satellite fleet) Effective A/M ~ 0.045 m2/kg IADC formula: 36,021 km + (1000·CR·A/m) = [36,021 km] + [(1000)(1.1)(0.045 m2/kg)] = 36071 km De-orbit altitude above geostationary orbit: 36071 km – 35786 km = 285 km

Ms. Marlene H. Dortch February 23, 2012 Page 2 ,De-orpit De—orbit Altitude Above GEO (kim) SCIID Efj:;l::[ve FCC Proposal Intelsat Current (mfizll‘(g) (Section 25.282) Reserve 1S27 0.045 285 300 For the Commission‘s convenience, a corrected page 22 of the Intelsat 27 Engineering Statement is attached. CA4c120, Sincerely, Susa;n H. Crandall Assistant General Counsel Intelsat Corporation Co: Bob Nelson Stephen Duall Jay Whaley Attachment

Attachment taking into account the expected mass of the satellit: at the end of life and the required delta—velocity to achieve the desired orbit. The fuel gauging uncertainty has been taken into account in these calculations. In calculating the disposal orbit, Intelsat has used simplifying assumptions as permitted under the Commission‘s Orbital Debris Report and Order. For reference, the effective area to mass ratio (Cr*A/M) of the Intelsat 27 spacecraft is 0.045 m*/kg, resulting in a minimum perigee disposal altitude under the IADC formula of at most 285 kilometers above the geostationary arc, which is lower than the 300 kilometer above geostationary disposal altitude specified by Intelsat in this filing. Accordingly, the Intelsat 27 planned disposal orbit complies with the FCC‘s rules. 13) ITU Filing Intelsat currently has no filing with the ITU for a satellite network within mobile satellite service ("MSS") that specifies operation on the frequency bands of 292.835 — 317.33 MHz and 243.520 — 268.160 MHz. Intelsat will submit to the Commission the API for a new MSS satellite network that utilizes these frequency bands at the nominal orbital location of 55.5° W.L. Page 22 of 80


Document Created: 2012-02-23 14:33:44
Document Modified: 2012-02-23 14:33:44
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