Attachment 20140324161710.pdf

20140324161710.pdf

DECISION submitted by IB-FCC

Grant

1997-03-10

This document pretains to SES-MOD-19950221-01399 for Modification on a Satellite Earth Station filing.

IBFS_SESMOD1995022101399_1039967

CAL CORPORRATION an Electromagnetic Sciences Company 71050 Morrison Drive, Ottawa, Ontario Canada K2R B8K7 [(613)820—8280 Telex: O53—3937 Fax: (613)820—6474 DATE: February 27, 1997 FILE: 0881 /Cert. Subject: Request for Special Temporary Authority to operate up to 5 Aeronautical Mobile Satellite Service Terminals Dear Mr. Tycz, Pursuant to Section 25.119 of the Commission‘s Rules, CAL Corporation ("CAL") hereby requests Special Temporary Authority ("STA") to operate up to 5, two—channel aeronautical terminals satellite terminals pursuant to the attached technical exhibit. The terminals will operate on space segment provided by AMSC Subsidiary Corporation. CAL requests that the STA become effective March 10, 1997 and remain in effect until September 7. 1997 or until a grant of CAL‘s type acceptance application , whichever is earlier. Grant of this request will serve the public interest in the continued development of MSS in the United States. s ‘ ical mobile term s. Reort and Order, 7 FCC Red 5895 (1992) CAL also has notxfied the FAAof 1ts intention to make application for type acceptance, including all the required technical data, and will provide the FAA a copy of the final type acceptance application submitted to the FCC. The purpose of the authority requested herein is to allow CAL to conduct end—to—end tests of the two—channel terminals, using the AMSC communications ground segment, control systems and satellite. The tests also permit CAL to comply with FAA type acceptance requirements for specific aircraft models. CAL seeks to conduct tests covering system stability and quality, as well as feature and service functionality to provide mobile satellite services. All participants in these tests will be notified that the terminals have not yet been type accepted and are returnable to CAL if type acceptance is denied. Participants will pay AMSC for appli — trials are to be conducted in the US and in Canada. Granted "04— ss &4 —94"7 date:2l/0l441_= Exe— 9 11l27 Satellite and Radiocommunications Division, International Bureau, authorized by: Federal Communications Commission, 2000 M. Street, N.W., Room 800, Washington, D.C. 20554 signature /3 7 * U.S.A. Attn: Mr. Thomas S. Tycz // /77 RL C (Chief of Division)

These tests represent an important step in the continued development of aeronautical mobile services. Currently, general aviation and corporate aircraft have been unable to receive two—channel, high—quality voice, data and fax service at reasonable rates. The authority requested herein will allow CAL to ensure that the terminals are technically sound‘ and meet all operational requirements prior to the full commencement of services to the public. Therefore, CAL respectfully requests temporary authority to operate up to 5 two—channel aeronautical satellite terminals, consistent with the parameters set forth herein. CAL requests that this STA be granted effective March 10, and last for six months, or until grant of the underlying type acceptance application, whichever is earlier. CAL certifies that no party to this application is subject to a denial of Federal benefits pursuant to Section 5301 of the Anti—Drug Abuse Act of 1988, 21 USC § 835(a). Respectfully submitted, Alxewlx} »Ketlsé VP, Commiat es j}é’f@wfl | CAL Corporation Copy: Frank Peace, JR 1 CAL notes that the transceiver portion of the terminal is constructed by Westinghouse Electric Corporation and previously has been licensed by the FCC. Additionally a single— channel system, of similar basic design, has been type accepted under FCC ID: K6KQC100.

( FEDERAL COMMUNICATIONS COMMISSION Approved by OMB 3060—0589 FCC REMITANCE ADVICE rmpires zosor page Nno. _1 or (RESERVED) SPECIAL USE FCC USE ONLY \ / (Read instructions carefully BEFORE proceeding.) (1) FCC ACCOUNT NUMBER Did you have a number prior to this? Enter it. (2) TOTAL AMOUNT PAID (dollars and cents) 9 [ °[ 8 [ 9 [ + [3 [# [ 9| 9 [ 7 [ [ [ [ [ [ [ J [ [ s 130.00 e (3) PAYOR NAME (If paying by credit card, enter name exactly as it appears on your card) Cal Corporation (4) STREET ADDRESS LINE NO. 1 1050 Morrison Drive (5) STREET ADDRESS LINE NO. 2 (6) CITY (7) STATE (8) ZIP CODE Ottawa, Ontarto Canada K2H 8K7 (9) DAYTIME TELEPHONE NUMBER (Include area code) {10) COUNTRY CODE (if not U.S.A.) Pm mEonNrommATion (11A) NAME OF APPLICANT, LICENSEE, REGULATEE, OR DEBTOR FCC USE ONLY Cal Corporation (12A) FCC CALL SIGN/OTHER ID (13A) ZIP CODE (14A) PAYMENT TYPE CODE (15A) QUANTITY (16A) FEE DUE FOR E@%TYPE CODE K2H SK7 c |e x 1 $ {30.00 (17A) FCC CODE 1 (18A) FCC CODE 2 (19A) ADDRESS LINE NO. 1 (20A) ADDRESS LINE NO. 2) (21A) CITY/STATE OR COUNTRY CODE 1050 Morrison Drive | Ottawa, Ontario Canada ITEM #2 INFORMATION (11B) NAME OF APPLICANT, LICENSEE, REGULATEE, OR DEBTOR FCC USE ONLY (12B) FCC CALL SIGN/OTHER ID (13B) ZIP CODE (14B) PAYMENT TYPE CODE |(15B) QUANTITY |(16B) FEE DUE FOR PAYMENT TYPE CODE IN BLOCK 14 $ (17B) FCC CODE 1 (18B) FCC CODE 2 (19B) ADDRESS LINE NO. 1 (20B) ADDRESS LINE NO. 2 (21B) CITY/STATE OR COUNTRY CODE Ee cr=ort cano payuent iwrorvaro i (22) MASTERCARD/VISA ACCOUNT NUMBER: [7] Mastercard EXPIRATION DATE: D Visa Month Year AUTHORIZED SIGNATURE DATE (23) Ihereby authorize the FCC to charge my VISA or Mastercard is for the service(s)/authorization(s) herein describe. See public burden estimate on reverse. FCC FORM 159 April 1994

vOUCHER NO INVOICE DATE INVOICE NC INVOICE AMOUNT DISCOUNT AMOUNT NET AMOUNT 02/27/97 022797 130.00 130.00 0007252 CAL CORPORATION TOTAL } 130. 00 1050 MORRISON DRIVE. OTTAWA ONTARIO K2H 8K7 TELEPHONE. (6131 820—8280 cHequeno 7252 *"* CAL CORPORATION 0007252 t nL an Electromagnetic Sciences Company cHeque no. 7252 1050 MORRISON DRIVE, OTTAWA, ONTARIO K2H 8K7 w THE TORONTO—DOMINION BANK COMMERCIAL BANKING CENTRE 32866—004 245 STAFFORD ROAD WEST DATE AMOUNT NEPEAN. ONTARIO K2H 9E8 27—FEB—~97 U.S.$ 130.00 **ONE HUNDRED AND THIRTY 00/100 DOLLARS** CALCORPORAT!ON 2t PAY TO F.C.C. THE RpER or 2000 M. STREET, N.W. 4/—'@/ °8°5" roOM 800 ,/ WASHINTON DC 2 ©000 7 2529 n3 ¢866&w—O0Lnr 324586730024 31°

Technical Exhibit in support of application for Special Temporary Authority (STA) DESCRIPTION OF EQUIPMENT: Purpose of Equipment The equipment is intended to provide dual channel voice, FAX and data services in the Aeronautical Mobile Satellite Service. Specifically, it supports the following data rates and services: o 4800 bps digitized voice using the DVSI IMBE vocoder. e 2400 bps Group 3 FAX. e 4800, 2400 and 1200 bps circuit switched data. These services are made available to the maximum extent practicable during all phases of aircraft operation, both on the ground and in the air. Equipment Configuration The equipment will be provided in one of two possible configurations at the customers discretion, single channel or dual channel. The single channel installation has been the subject of a previous Type Acceptance application and received certification under the FCC ID: K6KQC100. The Grant of Equipment Authorization is filed with the FCC under File number 31010/EQU 17.9, dated March 6, 1996. The dual channel configuration is identical to the single channel except that two transceiver subsystems are coupled to the same antenna through a 34B hybrid coupler. The dual channel configuration is shown in figure 1. The major active elements are as follows: 1. The Antenna Unit 2. The Transceiver Subsystem 3. The High Power Amplifier (HPA) 4. The Two Channel Coupler Unit 5. The Handset(s) A brief description of each element follows. Antenna Unit The Antenna Unit is designed for fuselage top mounting. It includes a mechanically steered radiating element and motor drive, and is covered by an aerodynamically contoured radome. The Antenna Unit and its radome also house: the diplexer and LNA combination, a compass to provide steering information, and an active GPS antenna element.

Transceiver Subsystem Each Transceiver Subsystem (TS) includes the Transceiver Unit (TU), the High Power Amplifier (HPA), the beam steering unit (BSU), a GPS receiver and a power converter to suit the aircraft supply. The TU performs all the functions defined for this unit in its land mobile configuration plus providing Doppler correction through the use of software specially developed for aeronautical applications. The GPS receiver provides position and velocity information both for Doppler correction and for use by the BSU in steering the antenna. The two Transceiver Subsystems in the two—channel configuration are functionally identical to that used in the single channel configuration and are completely interchangeable. The special configuration required for them to operate as designated units #1 and #2 in this two—channel configuration results from signaling from the micro—processor in the two—channel combiner to the unit installed in the #2 position. High Power Amplifier The HPA is required to amplify the transmit signal given out by the TU to the level required to meet the specified EIRP requirements. It is co—located with the Transceiver. Two Channel Coupler Unit The Two Channel Combiner Unit provides the RF interface between the two transceivers and the single Antenna. It also provides information, to the transceiver in the # 2 position, on the status of the transceiver in the # 1 position. This allows the #2 Transceiver to disable itself and bypass the hybrid combiner in the #1 transmitted path, when traveling in areas of the coverage where only single channel operation is available. Number of Handsets Each of the two transceiver units is to be supplied with a single handset. Provision will also be made for the installation of multiple handsets, all connected to both TS‘s so that any one of them can be used to communicate through either channel. Handsets In addition to their primary communication function, one of the handsets will have keys and a display, and is to be used as the control panel for the equipment. February 12, 1997 Page 2

Antenna Unit Active GPS Antenna with filter Two—Channel Y ~——=~ Combiner uP Receive Rx Signal ’Xqu ~—_, |Filter CiNo & Sat. long. wEC AEU Doppler olfset Transceiver ka Tx Subsystem ~x2 Filter #2 Transceiver Handsets Transceiver Subsystem 1 2B8V 28|V 1 Figure 1: CALQUESTTY CQ200 Two—Channel System Configuration February 12, 1997 Page 3

Installation Issues The equipment is designed for simple, straightforward installation to minimize the cost of this activity. To this end, the following guidelines are followed: o Minimize the size and weight of the antenna. o Minimize the size and weight of the interior equipment. e Installation will be possible without removal of the antenna from the radome. o The GPS antenna will be incorporated within the main antenna assembly to avoid having to install a separate unit. Range of Aircraft Sizes Provision is made for installing the antenna on fuselages in any one of five size ranges. These ranges encompass most of the commonly used private commuter aircraft in service. Cabling Details The system is designed to maximize the length, and minimize the diameter, of the cabling interconnecting the various subsystems. Power Distribution Power is processed in the Transceiver Subsystem and then distributed to the other subsystems to avoid the need for more than one supply from the aircraft. Connector Circular avionics style bayonet connectors are used wherever possible. Mounting The handset(s) will normally be cradle mounted on a cabin wall or other vertical surface. MANUEACTURERS IDENTIFICATION: The product will be identified as a: CALQUEST*Y Satellite Phone, model CQ200. February 12, 1997 Page 4

ANTENNA CHARACTERISTICS: The gain of the antenna is measured at the input to the antenna element (ie., not at the input to the Antenna Unit). The beam peak gain varies with the antenna pointing orientation, but lies within the following ranges: Receive band 8.3 dBi to 12.3 dBi Transmit band 9.4 dBi to 12.3 dBi The relative transmit antenna gain pattern envelope (i.e., spatial discrimination) for the AES antenna is strongly dependent on the mechanical pointing direction of the antenna relative to the fixed ground plane. Although the requirements for off—axis antenna discrimination nominally apply only to the "horizontal" (e.g., equatorial) plane of the antenna gain characteristic, the complex geometry of a mechanically steered antenna mounted on a maneuvering aircraft significantly broadens this requirement when the gain is referenced to the antenna‘s horizontal and vertical. In order to satisfy all potential geometrys of satellite pointing direction, aircraft orientation and consequent antenna orientation for satellite pointing, the antenna gain envelope contours were analyzed to determine the highest off axis antenna gain at any angle relative to its horizontal / vertical reference planes. These worst case off—axis spatial discrimination gain results were then compared with the maximum allowable off—axis relative gain illustrated in Figure 3 below: Antenna Off—Axis Discrimination The receive and transmit gains of the antenna at 45° and 75° away from the nominal Maximum Antenna Gain direction of the desired satellite Relative to Pea (i.e. not necessarily the direction of either the peak of the transmit or receive antenna gain patterns) shall be a minimum of 4.8 dB and 8 dB, respectively, below the beam * * * - peak value and shall remain 40 50 60 70 80 below the linearly interpolated Angle off Nominal Pointing (degrees) mask shown in Figure 3. Figure 3: Antenna Off—Axis Discrimination February 12, 1997 Page 5

The following plot, Figure 4, illustrates the results of the analysis measured with an antenna elevation angle of 45° where the off axis gain, when measured at the various azimuth pointing angles shown as parameters, was the maximum recorded. In the worst case this indicates there is still a 5° margin in the off—axis discrimination performance. Tx Spatial Discrimination @ 45° Elevation E:g_r "A m 0/45 B 4 & 6045 *é ®o 120/45 -I.g 5 & mim——a—|m _2 © 160745 o . N m 180/45 a 6 \ Eo 200/45 J W & 240/45 8 , [\ &A —300/45 g J \ B Spec. 3 m 20 30 40 50 60 70 80 Angle off boresight (deg) Figure 4: Plot of analyzed maximum off—axis antenna gain when measured with an elevation of 45° to the ground plane. RATED OUTPUT POWER: During periods when a single carrier is activated, and within the constraints of the Signal Timing Limits, the EIRP lies within the range +12.0 dBW to +18.3 dBW. During periods when both carriers are activated, and within the constraints of the Signal Timing Limits, the EIRP lies within the range +9.9 dBW to +15 dBW. The maximum level is not exceeded even when the antenna peak transmit gain is not in the direction of the desired satellite. February 12, 1997 Page 6

EMISSION TYPE AND CHARACTERISTICS: The designation of the station‘s emissions is 6KO0G7ZW when operating in the dual channel configuration. Description of Modulation (each channel): all Single Carrier per Channel (SCPC), FES—C: Outbound communications and Quadrature Phase Shift voice activated with in—band signaling channel from Keyed (QPSK) at 3375 periodic signaling bursts. an LES to a MET. Symbols per second, GC—S: Outbound signaling channels Bi Phase Shift Keying periodic reference bursts. from the NCC to the METs. (BPSK) at 3375 Symbols per second continuous MT— Inbound signaling channels from Bi Phase Shift Keying periodic signaling bursts. ST/SR: the MET to the NCC. (BPSK) at 3375 Symbols per second continuous MET—C: Inbound communications and in— Quadrature Phase Shift voice activated with band signaling channel from the| Keyed (QPSK) at 3375 periodic signaling bursts. MET to an LES. Symbols per second, INTERMODULATION PRODUCTS: When radiating two un—modulated carriers, each 3 dB below the maximum radiated power, no intermodulation product is greater than —24 dB with respect to the mean power of either carrier. FREQUENCIES OF OPERATION: The functional transmit and receive frequency ranges are not less than the following: Receive frequency range: 1525 to 1559 MHz Transmit frequency range: 1626.5 to 1660.5 MHz (see Note 1) Note 1: Transmit range quoted is equipment design range. System operator restricts operations to authorized frequencies. Note 2: channel spacing is 6.0 kHz @ 0.5 kHz increments. February 12, 1997 Page 7

OUT OF BAND EMISSIONS: The EIRP of any radiated harmonic in any spatial direction is less than —37dBW for any frequency up to 20 GHz. The composite spurious and noise output EIRP (excluding harmonics) radiated by the AES does not exceed the following values outside the transmit band: Frequency (MHz) Spurious Emission Limits < 1525 —135 dBe/4 kHz 1525 — 1559 Meet G/T with transmitter on 1559 — 1565 —135 dBce/4 kHz 1565 — 1585 —155 dBe/1 MHz * 1585 — 1610 —57 to —53 dBW/1 MHz linearly interpolated 1610 — 1622 —70 to —39 dBW /30 kHz linearly interpolated 1622 — 1626.5 —39 dBW /30 kHz 1626.5 — 1660.5 —60 dBce/4kHz 1660 — 1735 —60 dBce/4kHz 1735 — 12000 —105 dBce/4kHz 12000 — 18000 —70 dBe/4 kHz * With respect to the maximum two—channel EIRP of 15 dBW. It is recognized, and so noted in the installation / operators handbook, that this system may not be operated at the same time, and on the same aircraft, as the GLONASS navigation system. CRITERIA FOR PRIORITY AND PREEMPTIVE ACCESS: The CALQUEST!Y Aircraft Earth Station incorporates a transceiver which is similar to the Westinghouse equipment used in the AMSC Mobile Telephone System(MTS), for which AMSC has previously received operational authority from the ECC and which has been found, by the FCC, to meet its requirements for Priority and Real Time Preemptive Access. February 12, 1997 Page 8

TECHNICAL CERTIFICATION I hereby certify that I an the technically qualified person responsible for the engineering information in the foregoing Request for Special Temporary Authority, and I an familiar with part 25 of the Commission‘s Rules, that I have reviewed the engineering information submitted in the foregoing request, and that it is complete and accurate to the best of my knowledge. By: %7:/// Mr. Gary Hebb, Director of Engineering Date: b{%vy ///'A7 February 12, 1997 Page 9


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