Attachment Appendix

This document pretains to SES-AMD-20130109-00028 for Amended Filing on a Satellite Earth Station filing.

IBFS_SESAMD2013010900028_980786

ATTACHMENT 1 TECHNICAL APPENDIX

ORBITAL DEBRIS INFORMATION MATRIX Satellite Name Orbital Debris Notes Information Provided? GE-23 No U.S. Licensed Superbird C2 Yes Asiasat 5 Yes Yamal 201 Yes Eutelsat 10A (W2A) Yes Anik F1 Yes Estrela do Sul 2 (T- No Added to Permitted List on April 4, 14R) 2011 Intelsat 14 (IS-14) No U.S. Licensed Telstar 11N No U.S. Licensed Apstar 6 Yes Apstar 7 Yes

SKY Perfect JSAT Corporation 1—14—14, Akasaka, Minato—ku Tokyo 107—0052, Japan SKY Perfect JSAT TEL +81—3—5571—7800 Corporation SUPERBIRD—C2 Satellite End of Life Disposal and Debris Mitigation Plan This statement is prepared by SKY Perfect JSAT Corporation (JSAT") for the purpose of demonstrating the end oflife disposal and debris mitigation policies associated with the SUPERBIRD—C2 telecommunications satellite. Introduction: The SUPERBIRD—C2 satellite operated by JSAT was manufactured and supplied by Mitsubishi Electric Corporation and based on DS2000 bus platform. It was launched on August 15, 2008 with the designed life to be 15 years after In—Orbit Acceptance Review of the satellite. SUPERBIRD—C2 is S—axis stabilized and uses bipropellant chemical propulsion for attitude and on—station control. The satellite is located at orbital slots 144° E.L. The TTC operation of SUPERBIRD—C2 satellite is performed by JSAT Satellite Control Center on basis 7x24 through the ground station located in Yokohama, Japan. For station keeping, the satellite is maintained within a box of size of +0.05 degree. Disposal plan and debris mitigation measures: As a licensed operator in Japan, JSAT will strictly comply with the requirements as stipulated by the guidelines issued by IADC and United Nations and adhere to prevailing international best practices and standards to reduce space debris. According to the said Guidelines, any expired satellite, which has to be de—orbited to the outer space, shall be disposed to an orbit with a delta‘ perigee (Ja) higher than geo—synchronous orbit of no less than : 235Km + (1000 + CR + A/m) Where CR is the solar pressure radiation coefficient of the spacecraft, and A/m is the Area to mass ratio, is square meters per kilogram, of the spacecraft. JSAT will take into account this requirement for any de—orbit operation of this satellite and will reserve sufficient propellant in order to conform to the regulation set forth in Guidelines and comply with the following: Zla requirement Propellant needed SUPERBIRD—C2 300Km 10.2kg When JSAT applied for the Space station Carrier License from Japanese Ministry of +372 +

SKY Perfect JSAT Corporation 1—14—14, Akasaka, Minato—ku Tokyo 107—0052, Japan SKY Perfect JSAT TEL +81—3—5571—7800 Corporation Internal Affairs and Communications (MIC) for SUPERBIRD—C2, JSAT incorporated a disposal plan as well as debris mitigation measures. The license for SUPERBIRD—C2 was subsequently issued by MIC to JSAT for the launch and operation of the satellite. The SUPERBIRD—C2 satellite is based on Mitsubishi DS2000 platform, which is widely known to be a mature and reliable satellite platform. In the design phase, the satellite manufacturer, Mitsubishi Electric Corporation in Japan has already considered this potential issue and design the satellite in such a way that industrial practices and standards are observed. There is no probable failure mode that would lead to accidental break—up and cause space debris. We therefore believe that the design of the satellite and the disposal measures in place are in line with IADC‘s Space Debris Mitigation Guidelines. As the satellite is de—orbited, in accordance with to orbital raising operations, JSAT will configure the satellite with residual energy into a passive state. JSAT will implement procedures to minimize the on—board energy in whatever form of electrical, chemical, kinetic etc., which is considered as a potential source of generating harmful debris. These measures include shutting down the power generating subsystems and all power consumed components. Further, momentum wheels will be maintained at the lowest kinetic energy level. Pyrotechnic components would have been exhausted or completely disabled during operations in the initial stage of life. As such, we consider the risk of de—commissioning of the satellite will be kept minimal and conformed to the standard of the industry. Annexes 1. IADC Space Debris Mitigation Plan, by InterAgency Space Debris Coordination Committee, September 2007 2. Space Debris Mitigation Guidelines of the Committee on the Peaceful Uses of Outer Space by United Nations Office for Outer Space Affairs, 2010 ~ End — SKY Perfect JSAT Corporatign Shigetaka Shinozlka General Manager Satellite Operation Division December 28, 2012 * 202 >

AsiaSat 5 Satellite End of Life Disposal and Debris Mitigation Plan This statement is prepared by Asia Satellite Telecommunications Company Limited ("AsiaSat") for the purpose of assisting its customers who may be subject to the approval authority by such entities as the ITU, FCC USA or OFCA HK with regard to meeting the requirements in relation to the end of life disposal and debris mitigation of a telecommunication satellite. Introduction: The AsiaSat 5 satellite is manufactured and supplied by Space Systems/Loral in the United States and is based on the LS-1300 series satellite platform. The AsiaSat 5 satellite was launched on August 12,2009 with a nominal propellant lifetime to meet the satellite's designed life of 15 years after the handover of the satellite from Space Systems/Loral. AsiaSat 5 is a 3-axis stabilized satellite that uses bi-propellant chemical propulsion for station- keeping and attitude controls. The satellite is located at the nominal orbital location of 100.5E and station kept within a box of +0.05 deg . The TTC operation of the satellite is performed by AsiaSat on a basis of 7x24 through the ground st¿tion located in Hong Kong. Disposal plan and debris mitigation measures: As a licensed satellite operator in Hong Kong, AsiaSat complies to the requirements as stipulated by the "Guidelines for De-commissioning of Satellite" (the "Guidelines") issued by OFCA (Hong Kong Offrce of CommunicationsAuthority) and adhere to prevailing intemational best practices and standards to reduce space debris. According to the said Guidelines, any expired satellite, which has to be de-orbited to outer space, shall be disposed to an orbit with a delta-perigee (Âa) higher than geo-synchronous orbit of no less than: 235tçn+ (1000'CR'A/m) where CR is the solar pressure radiation coefficient of the spacecraft, and A/m is the Area to mass ratio, in square meters per kilogram, of the spacecraft. AsiaSat will take into account this requirement for any de-orbit operation of the AsiaSat 5 satellite and will reserve suffrcient propellant in order to conform to the regulations set forth in the Guidelines: Aa requirement Propellant needed AsiaSat 5 28Okm 7.3ks A¡la Satelllte Telecommunlcatlon¡ Holdlngs Llmlted (lncorporated ln Bemuda wtth llmlted llablllty) 19/F, Sunning Plaza, 10 Hvsan Avenue, Causeway Bav, Hong Kong Telephone: +852 25000888 Facsimile: +852 2576 41 1 1 Website: http/Åruw.asiasat,com

The respective disposal plan as well as debris mitigation measures constitute part of AsiaSat's submissions to OFCA for the applicátion of the Outer Space Ordinance License and Space Søtion Camier License. The AsiaSat 5 satellite is based on the Space Systems/Loral Series LS-1300 series satellite platform, which is widely known to be a mature product and one of the most reliable satellite platforms. In the design phase, the satellite manufacturer, Space Systems/Loral already considered this potential issue and designed the satellite in such away that industrial practices and standards are considered. There is no probable failure mode leading to accidental break-ups and causing space debris. The satellite manufacturer has established a dedicated SPACE DEBRIS MITIGATION PLAN. We therefore believe that the design of the satellite as well as disposal measures are in line with the regulations set forth in either IADC's Space Debris Mitigation Guidelines or Guidelines for De-commissioning of Satellite: issued by HK OFCA, 3l July2007. In addition to the orbit raising operation when de-orbiting AsiaSat 5, AsiaSat will configure the satellite with residual energy in a passive state. AsiaSat will implement procedures to minimize the on-board energy in whatever form of electrical, chemical, kinetic etc, which is considered as a potential source of generating harmful debris. These measures include shutting down the power generation subsystem and all active units. Further, momentum wheels will be maintained at the lowest kinetic energy level. The propellant and pressurized tanks will be eventually depleted and vented. Pyrotechnic components will have been used or disabled during operations in the initial stage of life. As such, AsiaSat considers the risk from de-commissioning of the satellite will be kept to a minimum and will conform to the standard of the industry Annexes: Guidelines for De-commissioning of Satellite: issued by HK OFCA, 3l July 2007; IADC Space Debris Mitigation Guidelines Revision 1: issued by IADC, Sep 2007; As¡a Satell¡te Telecom m unications Com pany Lim ited VP Engineering and Operations Telephone: +852 2500 0888 Faæimile: +852 2576 4l I I Websitq http//wtyw.asiasat.com

GAZKOM OPEN JOINT STOCK COMPANY APPROVED BY First Deputy General Director (signature) Verkhoturov V. 1 on 24.03.2005 Yamal_KA extraterrestral complex with Yamal—200 KA Methods of reduction of GSO pollution 10AOGK.0000—0 PM—3 Director othe Department ofSpace Projects (signature) 0. 8. Grafodatskiy 210305 Director of. the Design Department Signature and (signature) v. L. Kravchenko date 21.03.05 Signature and dat Inv. 4 2008

conTeNts INTRODUCTION............. ane uies ta 9 it uy s REFERENCE DOCUMENTATION.... GENERAL INFORMATION ON KA YAMAL—200. Exploitation of KA YAMAL—200. DEORBITING OF KA YAMAL—200... NOTIFICATIONS.... Inv.# podl. Signature and date Vzam. inv. # Inv. # doubL Siznature and date Ref.# Porv. rimen. tem. Page Document #. Signature Date10AOGK.0000—0PM—3 Design Sharapoy (signature) 12.03.05 Prov Kravchenko (signature) 18.03.05 N. contr Approved. Kravchenko (signature) 18.03.05 Extrate vrestral complex Yamal—KA with KA Yamal—200 Methods of reduction of GSO pollution Lin Page 2 Toialp ages 6

INTRODUCTION "This document was drawn up in order t secure fulfllment of the branch standard of the Federal Space Agency of the Russian Federation (OST 134—1023—2000); t is a common method of reduction of GSO pollution. This plan is used by Gazkom Open Joint Stock Company as one of the basic documents on reduction of space pollution in relation to KA Yamal—200. 1.. REFERENCE DOCUMENTATION The following documentation is not a formal part ofthis document; it is meant only for a more precise understanding ofthe contents: 1.. Branch standard ofthe Federal Space Ageney ofthe Russian Federation OST 134—1023— 2000 "General Requirements on Reduction of the Man—caused NESE pollution". 2. Spacecraft Yamal—200 KA—I Explanatory note. Part 12. Ballistics materials 300GK.0000A201—0 PZL1 part 12. 3. Instruction on preparation of the inital data for flght: contol. Part 1. 300GK.0000A201—0 1B62 part 1. 4. Committee on the Peaceful Uses of Outer Space. Scientiic and Technical Subcommittee Forteth session. Vienna, 17—28 February 2003 Item 10 ofthe provisional agenda. Space debris. 5.. IADS Space Debris Mitigation Guidelines. IADS—02—01. 15 Okt. 2002. 2.. GENERAL INFORMATION ON KA YAMAL—200. KA Yamal—200 was produced in compliance with the Russian standards and specifications, and has a connected useful load produced by Gazkom Open Joint Stock Company. The spacceraft is equipped with orientation engines and plasma correction engines running on xenon. KA Yamal— 200 was launched in the ear 2003, and the period of active existence will expire notearlier than in 203. Inv. # podl. Signature and date Vzam.inv.#. Inv. #doubl.. Signature and date tem. Page Docum.# Sign Date 10a0GE.0000—0 P3 Page 3

3. EXPLOTTATION OF KA YAMAL—200 All materials used in KA Yamal—200 pursuant to GOST R50109—92 have minimal coefficients of outgassing and loss ofmass. Exploitation of KA Yamal—200 at GSO, transfer of the SC to a different operating point at GSO (if necessary), deorbiting of SC [spacecraft] from GSO after regular exploiation should be carried out under permanent control of the ballistic group ofthe TH of the LBCC in order to secure flight safety and exclude collision with other SCs atthe orbit. On—board equipment of KA Yamal—200 includes equipment operating under pressure:. NHAB, xenon SSB.. There is no possibility of destruction of this equipment, and this is assured by a significant safety margin and confirmed by numerous ground tests and flight qualification, over 20 missions. in the course of exploitation of the SC on the GSO and deorbiting of the SC any separations of structural components and devices from KA Yamal—200 are excluded. KA Yamal—200 are functioning on the geostationary orbit in the orbital positions longitude 90 East and 49 East, pursuant to the application filed to the ITU and in compliance with all TTU legal regulations; therefore, possiblity of collision with other SCs through the fault of Gazkom Open Joint Stock Company is excluded. KA Yamal—200 is being operated in continuous mode. Correction ofthe orbitis cartied out by a standard method in compliance with the plan for orbit correction. Construction of on—board systems and principles of operation of KA Yamal—200 are arranged in such a way that no single failure or a single erroncous instruction lead to an unsanctioned ignition ofthe engines. 4.. DEORBITING OF SC YAMAL—200 Gazkom Open Joint Stock Company has planned the following operations on deorbiting ofthe SC upon expiry ofthe period ofactive existence: 1.. Calcultion of the working medium reserve necessary for deorbiting of the SC from GSO upon completion ofexploittion. 2. Telemeric control over working medium reserve of CEL (xenon) throughout the whole period of exploitation (requirement established by paragraph 4. 1743 of TZ for KA Yamal—200). 3. Deorbiting of the SC from GSO upon completion ofexploitation with respective working medium reserves of CEI (requirement established by paragraph 4. 174.3 of TZ for KA Yamal—200).. Perigee of the orbit of SC taken to the deorbiting area should be not less than 200 km over the radius of geostationary orbit (OST 134—1023—2000). Considering this data, raise of altiude during deorbiting from GSO equal to 200 km is approved for KA Yamal—200 (300GK.0000A201—0 P311 part 12). Inv. # podl. Signature and date Vzam.inv.#. Inv. # doubl.. Signature and date Iam. Page Docum.# Sign. Date 10AOGK.0000—0 PM—3 Paged

As part of measures aimed at passivation ofthe SC upon its withdrawal it is provided that all power sources will switched oft, and thus transformation ofhe energy of the on—board power sources into destructive one is excluded. Such measures comprise: Transfer of the correction and orientation engines to the state ofinoperabilty (shutdown of power sources). We would like to note that insignificant remnants of the engine installation‘s working medium (neutral xenon gas) are explosion—safe. Final discharge of the accumulator batteries upon instruction from the LBCC after deorbitingfrom GSO; Shutdown ofthe on—board equipment. During deorbiting of the SC from GSO work of OOW radio line will be planned basing on exclusion ofradio frequeney interferences for other SCs. s. NOTIFICATIONS. Gazkom Open Joint Stock Company undertakes to provide copies of the documents related to this matter as required by (PKA, IADS) with all respective notifcations, as provided by the law or regulations for spacecrafts of Gazkom Open Joint Stock Company, including, but not limited to matters of putting into operation, orbial position, moving to another point, alteration of the orbit incline, moving to another orbit. Inv.# podl. Signature and date Vzam. inv. #. Tnv, #doubl.. Signature and date lem. Page Docum. # Sign. Date 10AOGK.0000—0 PM—3 Page S

Appendic A §8B — xenon storage and supply black; GSO — gcostationary orbit SC—spacerat; ITU — International Telecommunications Union; NHAB — nickel hydrogen accumulator battery; LBCC — land based control center CEI —combined engine intallaion; NESE — near—Farth space environment OOW — order operation wire; TH — tricking headquarters. Inv. # podl. Signature and date Veam.inv. #. Inv. # doubl.. Signature and date em. Page Docum. # Sign Date 10AOGK.0000—0 PM—3 Pase 6

OTKPbITOE AKUMOHEPHOE OBLLIECTBO «FA3KOM» YTBEPKRAIO pobih samectutens panmoro aupertopa ‘Bepxorypos B.M. T >_ 2 2005 rona Kocmmuecknn xomnnexc «Aman—KA» c KA «Aman—200» MeronuKa coxpautenna sarpnanenna TCO 10A0FK.0000—0 NM~ 3 ocms Pyrosoputent anperuumn kocumflecknx npoerron 0.C.Fpaconatekun imX ayir."|_ T es er Havanitink Te unc npoektHo—konctpyrtopcroro ornena / ——~~~B.M. Kpagsenko theaes Toames w uate TeNi m 2005

ConEPXAHAE Tieps rpaen BBEREHME.... hesnmonr o a a o m 4 a & & b uow ccbinouHan A0MEHTAUA osluve cBenEHMA 0 KA «AMAN—200» Oronnyarauna KA «RMAN—200» YBOR C OPEMTeI KA «RMAT—200» YBEFIOMNEHMR....................... Copm Toamce n m & 3 & & 3 4 a 5 1or0ric0000—0 ns FRed Zher| e zon Hog7 Zm [ Popa._|Wapunce 2A Arocmmecant rounnexe «fman—ka» |_Ztm_|_ther Theros 3 [frox |Gens eAF Tart c KA «Fman—200» T: 6 # leronua corpauenusarprsuenum ;| [ rco 2|_ ym [Gaane crale

seensHne Hactonuwi aoryment cosnas a oGecnesenne asinonnerimorpacnesoro cranaapra berepansworo rocumiecroro arentcrsa P® (OCT 134—1023—2000) n npeacrasnser co6on o6uy wmeroamy corpaiemin sarprsnemir FCO. Aarmaii nnaw. wenonssyercs OAO «Faskow» kak orum us ocnosononaraiousx aorymextos no corpauemo sarprshemnn recuecroro npoctpancrea a ornowenmn KA «Aman—200». 1 CCbInOUHAR R0IOMEHTALIIA Creayouian Roiymentauna sensercn we dopwanswoil yaetso atoro aoiymenta i npeawaswavena ana Gonee yervoro nowmanus conepranun 1. Orpacnesof crangapt @eaepansmoro xoommectoro areircrea P OCT 134—1023—2000 «Obume tpeGosanur no orpanimenmo Texvoremnoro sacopeiun OKT». 2. Kecmecnt annapar «Rwan—200» KA—1 Nonomntensman sannore Yacte 12. Matepnansino Ganmwerice. 300FK.0000A201—0 N311 4.12. 3. Mnerpyiais no norrorome nexommaix mamibix na ynpaanemnn o nonere Yaene1. 300FK.0000A201—0 1962 u.1. 4. Committee on the Peaceful Uses of Outer Space. Scientific and Technical Subcommitee Fortieth session. Vienna, 17—28 February 2003 Item 10 of the provisional agenda. Space debris. 5. 1ADS Space Debris Miigation Guidelines. IADS ~02—01. 15 OKt. 2002. Tomc um 2 OME CBEREHMA 0 KA «AMAN—200» KA «$wan—200» worotomnen 8 cooreercrani c poccwlowmm. craxtaptaun i creuidmaumim, w nmeer cansiyio noneshyio narpyary wsrorornesmyi0 OAO «Fastow». imX n Koommecenh annapar vmeer menrarenn. opwertauin w nnaswermie msuraren roppertnn paSoraroume a rcesone KA «Fiwan—200» sanyuen a 2003r., cpor akmmanoro cyuccreosanna sarassnsaeten o pavee 2018r. Tawn Townic x ns 10AOFK.0000—0 NM—3 fise| Trer| Seamow noww:_| m )

3. SKCNIVATAUIAA KA «AMAN—200» Bce marepnansi veronssyeuise. wa KA «Awan—200> s coorsercromn c TOCT P50109—92 niewor unsumansssie xoopdwurermsi macconorepn n raxouun. rennyatain KA «Fwan—200» wa FCO, nepeson KA a nosyio paGouyo towy xa FCO (rom. meoGrormmoet?), yeor KA c TCO noene orowaimr. wramon. arcnnyarauim nposoguten non noctommnsim rortponew i ynpaenermiew Gannwcriecion rpyrinss UV HKY KA «Alwan», uo o6ecnesnsaer Gesonacnocte nonera n wornioaer sosworeocte cronosesu c apyrimw KA wa opGute B coctas Goproson annaparypmi KA «Fman—200» axomut o6opyrosaine, waxonnuieeca nog masnermiew: HBAG, EXM. kcenona.. Boawowoote. paspyueiia yrazaimoro o6opyaoeanina oreyterayer, vto o6ecnesiisaeton anasurensisim sanacamn nposnostn w nogreepxreno. mnorowcnesmsiim. wasemmbimi. wonsirakimin i. néton keannonkaunen, Gonee 20 miconn B npouece arennyaraum KA wa FCO n a npouecce ysona c FCO wormovens: noGue oreneina anewertoe ronorpycuum w arperaton or KA «Fuan—200» KA «Fman—200». dymumonmpyiot. wa reccraumonapron. opSure a. opnransmax noanyiax 90° a 2.n 49° a.2., a coorsercrain c nogano# sanson a MC3 n a cooreercram co scemn. npascesinw nopman MC3, Tarim oGpazom scswownocts cronicseric Apyrimin KA no se OAO «Faskou» nornouena. KA «Awan—200» ynpaansercn 8. wenpepsishom pexsime. Koppertim. opGim nporonuten crangaptisio6pasom a cooreercran c nnawou roppertum opGral. Mloerpoetine Gopromuix curem i. npumuimsi ynpaeneiim KA «Fiman—200 Tome wars oprasnsosans raim o6pasom, vtoBe!rrarooannousin onas unounSouo segarman exmushan komarna e npeopnnn x necanetnomposaktrony sknovermo aonrarenen. 4. YBoR C OPEHTb KA «AMA7—200» imX in OAO «Fasrou» sannammporans: cneayioume onepaunn no yearyKA c opGimsi nocne sarepmeniin CAC: 1. PacuBr meoBxorimoro sanaca paGosero tena anr ysora KA c TCO nocne sasepwenna arcnnyaraum. e 2. Tenewerpieciu rortpons sanacon paGosero tena ORY («cenon) a Teverve scero cpora axcnnyaraum (rpeSoranne n4.17.4.3 T3 wa KA «Fwan—200>). i 3. Yeon KA e TCO nocne oroimahina axennyaraum c cooraercrayiousmm sanacain paGouero tena OfV (tpeGosaime n4.174.3 T na KA «Fman—200»). Nepuren opSitm KA aweneimoro s o6nacté: yeona monwen. npessiware pariye Toames x are reocranonapron opSurei ne menee vew wa 200 rm (OCT 134—1023—2000). C ywerom aroro ana KA «Ran—200» npmmmaetc norndw asicomsi npw yearec FCO pasisi 200« (300FK.0000A201—0 N311 «.12). Tier 10AOFK.0000—0 MM—3 fie| Ahr Neanouw_| Bs fls

4. Kax waet meponpmrtit no naccueauan KA nocne sereona vo axcnnyarauin nperycuwarpneaetcn, uro ace. wctowmar anepmin: Gyayt: seimouenss, Taiom o6pasom newnovaeten soomosocts tpanobopmaiim. aneprim Goprosb netounmos ntaima a paspywaioupio. Veasanssie meponpuntur snouaor + nepesoq s mepaGorocnocoGnce coctonime menrarenei ropperuin n opnentaum (sstmoveie nerowmeor nutaius). HeoGxoqnmo ormemim, uro nesrawurensime octan« pabouero tena. qewratenssof yeranomir (weitrpansmsii ras xcenos) nennioron eapsimoSesonacisiin; + oromarensimif pasprn anymynrtopmex Gatapeit no romanre c HKY noone yeara c TCO; + oneniouerie Goproson annaparypst Bo speus yeore KA c TCO paGora parwonimm CKY Gyzer nnamposamsen wexorn ns exniouehina sosmonerocm novenerina nowex a vacrorax apyrux KA. 5 yeenomneHna OAO «Taskom» Geper wa ce6n o6rsatensrea nperoctagnats ronmm Rorymerton omecsuumen x aasony sonpocy rax tpeSyer (PKA, IADS) co scemm coorsercrayiouimim yeenouneiusim, kax tpeSyercn no sarony un hopmam anr annaparos OAO «Fasiom», srnosan, no ne orpaninmean sonpocs! asora a arcnnyataumo, opSiransiyio noamumo, repeeon e apyryi0 Tosy, wawexerie naxnonenus opim, nepexon ha apyryio opGiny. Touncswam TmJigts Trac mX Torme wume imX mm Trer 10AOFK.0000—0 AM—3 fie| ther Reaogu: ow Jn

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Eutelsat W2A/Eutelsat Issue/Rev No.: Issue 1, Rev. 0 10A Space Debris Date: 20 December 2012 Mitigation Plan Page 1 of 7 Eutelsat W2A/Eutelsat 10A Space Debris Mitigation Plan (prepared for the Federal Communications Commission) ISSUE/REVISION: Issue 1, Rev. 0 ISSUE DATE: 20 December 2012 Prepared by: Position Signature Date D. Zamora Head of Flight 20/12/2012 Dynamics Approved by: Position Signature Date L.R. Pattinson Director of Satellite 20/12/2012 Operations RESTRICTED TO EUTELSAT AND THE FEDERAL COMMUNICATIONS COMMISSION

Eutelsat W2A/Eutelsat Issue/Rev No.: Issue 1, Rev. 0 10A Space Debris Date: 20 December 2012 Mitigation Plan Page 2 of 7 CHANGE RECORD Date Issue/rev Pages affected Description 20/12/2012 1/0 All First issue. RESTRICTED TO EUTELSAT AND THE FEDERAL COMMUNICATIONS COMMISSION

Eutelsat W2A/Eutelsat Issue/Rev No.: Issue 1, Rev. 0 10A Space Debris Date: 20 December 2012 Mitigation Plan Page 3 of 7 TABLE OF CONTENTS 1. INTRODUCTION ......................................................................................................................................... 4 2. RELATED DOCUMENTS............................................................................................................................. 4 2.1. APPLICABLE DOCUMENTS .................................................................................................................... 4 2.2. REFERENCE DOCUMENTS ..................................................................................................................... 4 3. EUTELSAT W2A/10A OPERATIONS ....................................................................................................... 4 4. EUTELSAT W2A/10A END OF LIFE DISPOSAL...................................................................................... 5 5. NOTIFICATIONS ......................................................................................................................................... 7 RESTRICTED TO EUTELSAT AND THE FEDERAL COMMUNICATIONS COMMISSION

Eutelsat W2A/Eutelsat Issue/Rev No.: Issue 1, Rev. 0 10A Space Debris Date: 20 December 2012 Mitigation Plan Page 4 of 7 1. Introduction This document describes the space debris mitigation plan that Eutelsat shall apply to the Eutelsat W2A/10A space station. Eutelsat W2A/10A is based on the Thales Alenia Space Spacebus 4000 bus and it was manufactured according to European standards and specifications. The satellite is 3‐ axis stabilised and uses bi‐propellant chemical propulsion for attitude and on‐station control. Eutelsat W2A/10A was launched in 2009 and the end of its operational life is not expected to be before early 2023. 2. Related documents 2.1. Applicable Documents 1. EUTELSAT Space Debris Mitigation Plan. Issue 1.3. EUT_CTL‐SAT_QMS_PLN_00021, 26 July 2010. 2. FCC. Orbital Debris Mitigation Standard Practices. FCC 04‐130. June 21, 2004. 2.2. Reference Documents 1. European Code of Conduct for Space Debris Mitigation. Issue 1.0. 28 June 2004. 2. IADC Space Debris Mitigation Guidelines. IADC‐02‐01. Revision 1. September 2007. 3. Space Product Assurance. Safety. ECSS‐Q‐40A. 19 April 1996. 4. Orbital Debris Mitigation Standard Practices. FCC 04‐130. 21 June 2004. 5. NASA Safety Standard. Guidelines and Assessment Procedures for limiting Orbital Debris. NSS 1740.14. Aug 1995. 6. ITU Environment Protection of the Geostationary Orbit. S.1003. 1993. 7. UNCOPUOS. Technical Report on Space Debris. 1999. 3. Eutelsat W2A/10A operations - Eutelsat operates in order to control and limit the amount of debris released in a planned manner during normal operations, and assesses and limits 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. - Eutelsat has assessed the amount of debris released in a planned manner and no intentional debris will be released during normal operations of the Eutelsat W2A/10A spacecraft. A safe operational configuration of the satellite system is ensured thanks to the hardware design and operational procedures RESTRICTED TO EUTELSAT AND THE FEDERAL COMMUNICATIONS COMMISSION

Eutelsat W2A/Eutelsat Issue/Rev No.: Issue 1, Rev. 0 10A Space Debris Date: 20 December 2012 Mitigation Plan Page 5 of 7 - Eutelsat minimizes the probability of the satellite becoming a source of debris by collisions with large debris or other operational satellites. Eutelsat assessed for Eutelsat W2A/10A whether there were any known satellite located at the requested orbital location or might overlap. - Eutelsat W2A/10A is controlled within its ITU allocated orbit control window (10.0°E +/‐ 0.1°) by standard routine periodic orbit correction manoeuvres. In case of anticipated violation of the window, correction manoeuvres would be implemented to avoid such violation. - Eutelsat has assessed the probability of accidental explosions during and after completion of mission operations. Thanks to design safety margins and enough safety barriers, the probability of occurrence of accidental explosion of the Eutelsat W2A/10A satellite is negligible. - Satellite design is such that high levels of thruster activity and orbit perturbation do not result when foreseeable on‐board events occur 4. Eutelsat W2A/10A End of life disposal The post‐mission disposal activities have been planned as follows: 1. The orbit of the satellite will be raised by 300 km in order to ensure that the spacecraft will not re‐enter into the GEO protected region (GEO height +/‐ 200 km) in the long term. A mass of 16.7 kg of propellant have been allocated and reserved with a confidence level of 99% to carry‐out the post‐mission disposal manoeuvres. The FCC will be informed of any significant change to the above quantity of propellant. The minimum perigee height to avoid re‐entering into the GEO protected region can be computed using the IADC formula applied to this satellite: ΔH (km) = 235 + 1000.(A/m)eff = 278 km where the final term is the effective area/mass ratio of the satellite. Therefore, the planned 300 km above GEO height is sufficient to satisfy the 278 km requirement. During the satellite lifetime, Eutelsat determine the remaining propellant tanks. 2. As part of the end of life activities Eutelsat W2A/10A energy sources will be rendered inactive, such that debris generation will not result from the conversion of energy sources on board the spacecraft into energy that fragments the satellite. For Eutelsat W2A/10A , this involves the following: RESTRICTED TO EUTELSAT AND THE FEDERAL COMMUNICATIONS COMMISSION

Eutelsat W2A/Eutelsat Issue/Rev No.: Issue 1, Rev. 0 10A Space Debris Date: 20 December 2012 Mitigation Plan Page 6 of 7 ‐ depleting the chemical propulsion system, and where possible leaving open fuel lines and valves. The following table shows the characteristics of the pressurant tank, propellant tanks and propellant lines at end of life (EOL). It shall be noted that during the passivation the four propellant tanks will be depressurised as much as possible. Total Material Predicted mass Element Volume contained at of material at (l) EOL EOL (kg) MON-1 12.1 MON-1 Propellant tank 1391 He 2.8 MMH 3.8 MMH propellant tank 1391 He 3.0 MON-1 lines 0.65 MON-1 1.0 MMH lines 0.65 MMH 0.6 Pressurant tank 1 90 He 0.9 Pressurant tank 2 90 He 0.9 It shall be noted that the Lithium‐Ion batteries mounted on this satellite can not be depressurised. Nevertheless, they have been designed with a security coefficient greater than 3 and the batteries are “leak before burst” designed. The heatpipes, which use ammonia as working fluid, can not be depressurised either. They have been designed with a security coefficient greater than 4, the risk of break‐up is considered negligible. - leaving all batteries in a state of permanent discharge by isolation of the battery charge circuits and leaving certain loads connected to the batteries. 3. The satellite tracking, TM and TC usage are planned so as to avoid electrical interference to other satellites and coordinated with any potential affected satellite networks. 4. During the orbit raising manoeuvres the tracking, TM and TC frequencies will be limited to those where the satellite is authorized to operate. The design of the Eutelsat 10A spacecraft, fully consistent with end of life (“EOL”) passivation requirements as existed at the time of construction, does not allow passive venting once the spacecraft has been switched‐off. Therefore, none of the elements that RESTRICTED TO EUTELSAT AND THE FEDERAL COMMUNICATIONS COMMISSION

Eutelsat W2A/Eutelsat Issue/Rev No.: Issue 1, Rev. 0 10A Space Debris Date: 20 December 2012 Mitigation Plan Page 7 of 7 appear on the previous Table can be vented over time once the spacecraft has been switched‐off. Nevertheless, as part of the passivation of the spacecraft during the EOL operations, Eutelsat always makes best‐efforts to vent the propellant remaining in the propellant tanks and lines as much as possible. The figures in the last column of the Table can be considered as worst‐case post‐passivation remaining mass, after final shut‐down of the satellite. In any case, the pressurant tank is isolated just after the completion of the launch and early orbit phase (“LEOP”) operations and it cannot be passivated as part of the EOL operations. 5. Notifications EUTELSAT undertakes to provide the relevant bodies as required (UNCOPUOS, FCC, ITU, French ANFR, etc) with all appropriate notifications as required by law or regulations for Eutelsat satellites including but not limited to those concerning initial entry of service, location, relocations, inclined orbit operations and re‐orbiting operations. RESTRICTED TO EUTELSAT AND THE FEDERAL COMMUNICATIONS COMMISSION

Anik F1 Satellite End of Life Disposal and Debris Mitigation Plan This statement is prepared by Telesat Canada ("Telesat") for the purpose of assisting its customer in meeting the requirements in relation to the end of life disposal and debris mitigation of a telecommunication satellite. This information addresses requirements contained in §25.114(d)(14)(i)-(iv) of the Commission's rules. Debris Release Assessment. ANIK F1 was launched on November 21, 2000, and began commercial operations in February 2001. Boeing performed the orbit raising and deployments of the spacecraft using their then-current best practices in accordance with their normal operations and procedures for a 702 spacecraft.. Spacecraft Hardware Design: The Anik F1 spacecraft is a reliable Boeing 702 spacecraft which is designed to withstand the harsh space environment. This bus has demonstrated years of safe operational performance. Accidental Explosion Assessment. Telesat has reviewed failure modes for all equipment to assess the possibility of an accidental explosion onboard the spacecraft. In order to ensure that the spacecraft does not explode on orbit Telesat will continue to operate the satellite in accordance with Boeing’s recommended procedures. All batteries and fuel tanks are monitored for pressure or temperature variations. Alarms in the SCC (Satellite Control Center) inform controllers of any variations. Additionally, long term trending analysis will be performed to monitor for any unexpected trends. Operationally, batteries are operated utilizing the manufacturer’s automatic recharging scheme. Doing so ensures that charging terminates normally without building up additional heat and pressure. As this process occurs wholly within the spacecraft, it also affords protection from command link failures (on the ground). In order to protect the propulsion system, fuel tanks are operated in a blow down mode. At the completion of orbit raising, the pressurant was isolated from the fuel system. This will cause the pressure in the tanks to decrease over the life of the spacecraft. This will also protect from a pressure valve failure that could cause the fuel tanks to become over- pressurized. In order to ensure that the spacecraft has no explosive risk after it has been successfully de-orbited, all stored energy onboard the spacecraft will be removed. Upon successful de-orbit of the spacecraft, all propulsion lines and latch valves will be vented and left open. All battery chargers will be turned off and batteries will be left in a permanent discharge state. These steps will ensure that no buildup of energy can occur resulting in an explosion in the years after the spacecraft is de-orbited. Assessment Regarding Collision with Larger Debris and Other Space Stations. Telesat has also assessed and limited the probability of the space station becoming a source of debris by collisions with large debris or other operational space stations. Anik F1 operates in a collocated orbit with Anik F1R and (soon) Anik G1. Telesat will utilize industry standard, time proven techniques in the maneuvering of these collocated spacecraft. These are the same techniques that Telesat has and continues to use for its other collocated spacecraft.

In order to minimize the possibility of a large body impact collision, Telesat has assessed the proximity of other known Space Stations. In addition to working with all known neighbors, Telesat also utilizes three sources to identify collision risk. The first is alerts from the JSpOC for any approaching bodies. The second is the Space Data Center which utilizes our ephemeris as well as the ephemeris for all known bodies and provides us reports for potential collisions. The final is MIT/LL who utilizes its own radar and optical hardware to precisely provide data to Telesat for any close approach with debris. Telesat continually monitors launch details to verify that no new spacecraft will take residence in the vicinity of the F1 spacecraft. In the event that some other spacecraft does locate within the vicinity of the F1 spacecraft, Telesat will work to coordinate orbits and station keeping strategies with the other spacecraft operators as it has done in the past with multiple other operators. Post-Mission Disposal Plans. Anik F1, a Boeing built 702 bus, will be removed from its geostationary orbit at 107.3° W.L. at a perigee altitude no less than ~300 km above the standard geostationary orbit of 35786 km. This altitude was arrived at by using the FCC- recommended equation in §25.283 of the Commission’s rules pertaining to end-of-life satellite disposal. Minimum Deorbit Altitude= 235 km + (1000•CR•A/m) (Eq.1) CR = solar pressure radiation coefficient of the spacecraft = 1.21 A/m = area to mass ratio, in square meters per kilogram, of the spacecraft = 0.0487 Result: . (Eq.1) Minimum Deorbit Altitude = 36,021 km + (1000 1.27•.0378) = 294 km The propellant needed to achieve the minimum deorbit altitude is based on the delta-V required and specified by the spacecraft manufacturer. Based on IADC calculation, an estimated end-of-life mass of 2700 kg, and the delta-V required, approximately 2 kg of propellant will be reserved to ensure minimum de-orbit altitude is obtained. It should be noted that F1 utilizes Xips thrusters (instead of normal Bi Prop). This means that Xenon is the basic fuel type (not Oxidizer (N204) and Fuel (MMH)). Xenon is much more efficient (which is why so little fuel is needed). In addition to Xenon, there is also Oxidizer (N204) and Fuel (MMH) on board that was used during the orbit raising. In the event something happens to the Xenon system, it will be possible to de-orbit the spacecraft using the normal Fuel and Oxidizer. Any remaining propellant will be consumed by further raising the orbit until combustion is no longer possible. The remaining species of Xenon propellant, Oxidizer (N204) or Fuel (MMH), will be vented, placing the propulsion system on the spacecraft in “safe” mode. Propellant tracking is accomplished using a bookkeeping method. Using this method, the ground control station tracks the number of jet seconds utilized for station keeping, momentum control and other attitude control events. From jet seconds, amount of fuel used is determined. This process has been calibrated using data collected from thruster tests conducted on the ground and has been found to be accurate to within a few months of life on the spacecraft.

Apstar 6 and Apstar 7 Satellites End of Life Disposal and Debris Mitigation Plan This statement is prepared by APT Satellite Company Limited (“APT”) for the purpose of assisting its customers who may be subject to the approval authority by such entities as the ITU, FCC USA or OFCA HK with regard to meeting the requirements in relation to the end of life disposal and debris mitigation of a telecommunications satellite. Introduction: Apstar 6 and Apstar 7 satellites of APT are manufactured and supplied by Thales Alenia Space France and are based on Space Bus 4000C2 series platform. They were launched on April 12, 2005 and March 31, 2012 respectively with nominal propellant life times to be 15.97 years and 19.67 years respectively after In Orbit Acceptance Review of the satellites. Both satellites are 3-axis stabilized and use bi-propellant chemical propulsion for attitude and on-station control. The satellites are located at orbital slots 134° E.L. and 76.5° E.L., respectively. The TTC operation of both satellites is performed by APT Satellite SCC Department on basis of 7×24 through the ground station located in Tai Po, New Territory, Hong Kong. For station keeping, both satellites are maintained within a box in size of ±0.05 deg. Disposal plan and debris mitigation measures: As a licensed satellite operator in Hong Kong, APT will strictly comply with the requirements as stipulated by the "Guidelines for De-commissioning of Satellite" (the “Guidelines”) issued by OFCA (Hong Kong Office of Communications Authority) and adhere to prevailing international best practices and standards to reduce space debris. According to the said Guidelines, any expired satellite, which has to be de-orbited to the outer space, shall be disposed to an orbit with a delta-perigee (Δa) higher than geo-synchronous orbit of no less than: 235 km + (1000·CR·A/m) 1

where CR is the solar pressure radiation coefficient of the spacecraft, and A/m is the Area to mass ratio, in square meters per kilogram, of the spacecraft. APT will take into account this requirement for any de-orbit operation of these satellites and will reserve sufficient propellant in order to conform to the regulation set forth in Guidelines. Δa requirement Propellant needed Apstar 6 290 km 8.26 kg Apstar 7 297 km 10.94 kg When APT applied for the Outer Space Ordinance License and Spacestation Carrier Licence from OFCA for Apstar 6 and Apstar 7, APT incorporated the respective disposal plan as well as debris mitigation measures in APT’s submissions to OFCA. The licences for Apstar 6 and Apstar 7 were subsequently issued by OFCA to APT for the launches of these satellites. Both Apstar 6 and Apstar 7 satellites are based on Space Bus 4000C2 platform, which is widely known to be a mature product and one of the most reliable satellite platforms. In the design phase, the satellite manufacturer, Thales Alenia Space France has already considered this potential issue and designed both satellites in such a way that industrial practices and standards are observed. There is no probable failure mode leading to accidental break-ups and cause space debris. Satellite manufacturer has established the dedicated SPACE DEBRIS MITIGATION PLAN. We therefore believe that both the design of these satellite and the disposal measures in place are in line with the regulations set forth in either IADC’s Space Debris Mitigation Guidelines or FCC-04-130. As each satellite is de-orbited, in addition to orbital raising operations, APT will configure the satellite with residual energy into a passive state. APT will implement procedures to minimize the on-board energy in whatever form of electrical, chemical, kinetic etc, which is considered as a potential source of generating harmful debris. These measures include shutting down the power generating subsystem and all power consumed components. Further, momentum wheels will be maintained at the lowest kinetic energy level. The propellant and pressurized tanks will be eventually depleted and vented. Pyrotechnic components in fact would have been executed or completely disabled during operations in the initial stage of life. As such, we consider the risk of de-commissioning of the satellites will be kept minimal and conformed to the standard of the industry. 2

Annexes: Guidelines for De-commissioning of Satellite: issued by HK OFCA, 31 July 2007; IADC Space Debris Mitigation Guidelines Revision 1: issued by IADC, Sep 2007; -End- APT Satellite Company Limited _________________________ Chen Xun Vice President 3


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Document Modified: 2013-01-09 17:12:08
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