Attachment 2 Draft Test Plan

0124-EX-PL-2012 Text Documents

Panasonic Avionics Corporation

2012-03-07ELS_123776

ATTACHMENT 2 DRAFT T-PED Susceptibility Testing Frequency Plan Prepared by Armstrong Aerospace JC241-90282-02 Rev PB (January 3, 2012)

Proprietary Notice DOCUMENT NO.: JC241-9082-02 Test Procedure, Ground EMC Test This document and the information disclosed herein are proprietary data of Armstrong Aerospace, Inc. Neither Transmitting Portable Electronic Devices (T-PEDs) REV.: PB this document nor the information contained within shall Boeing 747-400 Series Aircraft be used, reproduced, or disclosed to others without the DATE: JAN 03, 2012 written authorization of Armstrong Aerospace, Inc. www.armstrongaerospace.com

Ref. : JC241-9082-02 TEST PROCEDURE, GROUND EMC TEST Rev. : PB Transmitting Portable Electronic Devices (T-PEDs) Date : JAN 03, 2012 Boeing 747-400 Series Aircraft Page : 2/20 TABLE OF REVISIONS REVISION DATE REASON FOR REVISION ISSUED BY APPROVED BY PB 01/03/12 Preliminary Release, C C. Porter R. Beech

Ref. : JC241-9082-02 TEST PROCEDURE, GROUND EMC TEST Rev. : PB Transmitting Portable Electronic Devices (T-PEDs) Date : JAN 03, 2012 Boeing 747-400 Series Aircraft Page : 3/20 TABLE OF CONTENTS TABLE OF REVISIONS ................................................................................................ 2 TABLE OF CONTENTS ................................................................................................ 3 1. PURPOSE ............................................................................................................ 4 2. SCOPE ................................................................................................................. 4 3. REFERENCE DOCUMENTS ................................................................................ 4 4. PREREQUISITE ACTIVITIES ............................................................................... 5 5. SCHEDULE / EFFECTIVITY LIST ........................................................................ 6 6. SITE REQUIREMENTS / RESOURCES REQUIRED ........................................... 8 7. AIRCRAFT CONFIGURATION ............................................................................. 9 8. TEST WITNESSING & PERFORMANCE OF TESTS........................................... 9 9. EQUIPMENT UNDER TEST (EUT) .................................................................... 10 10. OPERATION OF TEST AMPLIFIERS................................................................. 10 11. RF PLANNING CHART/CALIBRATION RECORD ............................................. 11 12. FCC EXPOSURE LIMITS ................................................................................... 12 13. BACK-DOOR EVALUATION ............................................................................... 13 14. FRONT-DOOR EVALUATION ............................................................................ 17

Ref. : JC241-9082-02 TEST PROCEDURE, GROUND EMC TEST Rev. : PB Transmitting Portable Electronic Devices (T-PEDs) Date : JAN 03, 2012 Boeing 747-400 Series Aircraft Page : 4/20 1. PURPOSE The purpose of this document is to present a means of compliance with Federal Aviation Regulations 14 CFR 25.1309(a). This Electromagnetic Compatibility (EMC) test procedure is provided to establish that passenger and crew Transmitting Portable Electronic Devices (T-PEDs), as identified herein, do not adversely affect the operation and integrity of aircraft systems installed in Boeing 747-400 series aircraft. 2. SCOPE This test procedure demonstrates that only those specific T-PED technologies, as identified herein, do not adversely affect the operation and integrity of other systems on the aircraft. 3. REFERENCE DOCUMENTS  Armstrong Aerospace document JC241-8092-01, Setup/Calibration Procedure, Ground EMC Test, Transmitting Portable Electronic Devices (T-PEDs)  Armstrong Aerospace drawing JC241-8092-03, Setup/Calibration Diagram, Ground EMC Test, Transmitting Portable Electronic Devices (T-PEDs)  Armstrong Aerospace drawing JC241-9082-04, Test Procedure Diagram, Ground EMC Test, Transmitting Portable Electronic Devices (T-PEDs), Boeing 747-400 Series Aircraft  Armstrong Aerospace document JC241-9082-05, Aircraft Equipment Record, Ground EMC Test, Transmitting Portable Electronic Devices (T-PEDs), Boeing 747-400 Series Aircraft  Armstrong Aerospace document PL44-8092-10, Test Equipment Parts List, Ground EMC Test, Transmitting Portable Electronic Devices (T-PEDs)  RTCA/DO-294C – Guidance on Allowing Transmitting Portable Electronic Devices (T-PEDs) on Aircraft

Ref. : JC241-9082-02 TEST PROCEDURE, GROUND EMC TEST Rev. : PB Transmitting Portable Electronic Devices (T-PEDs) Date : JAN 03, 2012 Boeing 747-400 Series Aircraft Page : 5/20 4. PREREQUISITE ACTIVITIES 4.1 Test Equipment Calibration Calibration of the test equipment must be performed prior to execution of this test procedure as described in JC241-8092-01 and JC241-8092-03. Calibration data will be recorded electronically in Appendix A – RF Frequency Chart/Calibration Record. Columns A-J of Appendix A – RF Frequency Chart/Calibration Record identify the wireless standards, the uplink band of the standard, the test frequency in the uplink band that will be used to assess the aircraft systems for compatibility, the modulation of the test frequency that will be used, the test waveform that will be used, and the maximum effective isotropic radiated power (EIRP) allowed by regulation for the standard in both Watts EIRP (column I) and dBm EIRP (column J). Column K defines the multiple equipment factor (MEF) that will be used to account for multiple device usage within the aircraft. The MEF was determined based on the 747-400 maximum seating of 624 passengers. Expected usage is less than half of all seats with spacing between users estimated at 1 meter. RTCA/DO-294C, Table 6.G-1 for a distance of 1m and 312 sources yields an MEF of 12. An MEF of 12 is used for all wireless standards except for the 802.11 standard which has been determined to have no MEF due to the transmission method that is used, however, DO-294C describes a minimum 10 dB be used to account for additional factors, therefore, an MEF of 10 is used for the 802.11 technologies. Columns L-N provide the target EIRP in dBm, target EIRP in Watts and effective radiated power (ERP) in Watts. Columns P-S provide typical dB gain and loss numbers for the antennas, amplifiers, cables and calculate the input to the amplifier. Column T provides the calculated SigGen setting that should be used during calibration. The calculated SigGen setting is an estimate and may be adjusted during calibration. Column U should be used to record the calibrated SigGen setting that was determined during calibration. Columns W-AC provide the field strength of the signal in V/m, dBuV/m, antenna calibration factors, etc, used during calibration. Columns AE and EF define the exposure limits for both controlled and uncontrolled environments. Section 6 summarizes the exposure limits for test personnel. NOTE: The power levels and test frequencies in Appendix A – RF Frequency Chart/Calibration Record should be coordinated with applicable local regulatory authorities for approval prior to testing. NOTE: Uplink band - From handset device to base station.

Ref. : JC241-9082-02 TEST PROCEDURE, GROUND EMC TEST Rev. : PB Transmitting Portable Electronic Devices (T-PEDs) Date : JAN 03, 2012 Boeing 747-400 Series Aircraft Page : 6/20 4.2 Aircraft Equipment Record Record the airplane system (major component) part numbers and manufacturer information for all airplane systems being evaluated in JC241-9082-05. This establishes the airplane configuration at the time of test, which may be applicable for similarity considerations for follow-on installations on other airplanes. NOTE: If it is determined that there are aircraft systems regarded as “Critical”, “Essential”, and “Non-Essential but Required for Dispatch” that have not been identified in this test plan, these equipment should also be evaluated for interference and results recorded at the end of the applicable section under “Additional Equipment”. 5. SCHEDULE / EFFECTIVITY LIST 5.1 Aircraft Effectivity List This plan is applicable to the following six aircraft: Customer Effectivity Code Registration Number Manufacturing Serial Number 003 VP‐BVR 26637 004 VP‐BKJ 26638 005 VP‐BKL 28468 006 EI‐XLZ 29119 007 VQ‐BHW 28959 008 ZS‐SBS 28959 038 EI‐XLK 29950 039 EI‐XLL 28031 040 EI‐XLM 28028 041 EI‐XLN 28029 042 EI‐XLO 28025 913 N913UN 26359 914 EI‐XLD 26360 916 EI‐XLE 26362 917 EI‐XLG 29899 918 EI‐XLH 27650 919 EI‐XLC 27100 920 EI‐XLI 27648

Ref. : JC241-9082-02 TEST PROCEDURE, GROUND EMC TEST Rev. : PB Transmitting Portable Electronic Devices (T-PEDs) Date : JAN 03, 2012 Boeing 747-400 Series Aircraft Page : 7/20 Customer Effectivity Code Registration Number Manufacturing Serial Number 921 EI‐XLF 27645 922 EI‐XLJ 27646 NOTE: Aircraft not listed in the Aircraft Effectivity List, including future new deliveries, will require an analysis of the aircraft data (AMM, WDM, IPB) in order to determine applicability of this plan to those aircraft. 5.2 Aircraft Configurations Analysis of the data for the aircraft listed in the Aircraft Effectivity List has determined the following configuration differences within the effective aircraft. 747-400 Aircraft Configurations Equipment Effectivity Equipment Differences Location E1‐1 913 B08238‐ LOCATED ONLY ON LISTED EFF. E1‐2 003, 004, 005, 913 M07877‐ LOCATED ONLY ON LISTED EFF. E1‐5 003, 004, 005, 007, 008 B08385‐ LOCATED ONLY ON LISTED EFF. E1‐5 003, 004, 005, 007, 008 B07019‐ LOCATED ONLY ON LISTED EFF. E2‐1 913 M00118‐ LOCATED ONLY ON LISTED EFF. E2‐3 003, 004, 005 B07743‐ LOCATED ONLY ON LISTED EFF. E8 913 M06769‐ LOCATED ONLY ON LISTED EFF. E8 003, 004, 005, 913 M06770‐ LOCATED ONLY ON LISTED EFF. E8 003, 004, 005, 007, 008 M00526‐ LOCATED ONLY ON LISTED EFF. E8 913 B07454‐ LOCATED ONLY ON LISTED EFF. E8 913 B08459‐ LOCATED ONLY ON LISTED EFF. E8 913 B07455‐ LOCATED ONLY ON LISTED EFF. E29 003, 004, 005 B08237‐ LOCATED ONLY ON LISTED EFF. E29 003, 004, 005 B08228‐ LOCATED ONLY ON LISTED EFF. E31 003, 004, 005 M00698‐ LOCATED ONLY ON LISTED EFF. E31 003, 004, 005, 007, 008 B07454‐ LOCATED ONLY ON LISTED EFF. E31 003, 004, 005, 007, 008 B07455‐ LOCATED ONLY ON LISTED EFF. 5.3 Susceptibility Assessment Schedule As detailed within this test plan, testing will be performed at 20 locations (flight deck, 12 electronic equipment bay/rack locations, and seven cabin locations). A common test profile is used at each test location. The estimated average time for completion of each

Ref. : JC241-9082-02 TEST PROCEDURE, GROUND EMC TEST Rev. : PB Transmitting Portable Electronic Devices (T-PEDs) Date : JAN 03, 2012 Boeing 747-400 Series Aircraft Page : 8/20 back-door assessment (assuming no susceptibility is detected and no test equipment failures) is as follows: Given: Equipment configuration and antenna positioning time = 20 min. Length of time required for FAA Representative/Designee to assess aircraft systems = 20 min. Number of antenna polarizations = 2. Therefore: 20 min + (20 min x 2 polarizations) = 60 min The estimated average time for completion of each front-door assessment (assuming no susceptibility is detected and no test equipment failures) is as follows: Given: Equipment configuration and antenna positioning time = 10 min. Length of time required for FAA Representative/Designee to assess aircraft systems = 10 min. Number of antenna polarizations = 2. Therefore: 10 min + (10 min x 2 polarizations) = 30 min. 6. SITE REQUIREMENTS / RESOURCES REQUIRED 6.1 Site Requirements The testing will be accomplished at a suitable facility that can provide the personnel and support equipment as described within this plan.  Since communication and navigation systems are being evaluated, it is preferable for the airplane to be outside of the hanger and 500 or more feet from large metallic structures. (NOTE: Due to potential local license restrictions, testing may be required to be performed inside of a hangar in order to comply with the local restrictions).  Electrical and hydraulic power must be available throughout the test. Airplane power can be from any source (engine, APU, or external) during the test. In addition, APU and main engines will be run for evaluation of engine controls and electrical generation (IDG, GCU).  Minimum of three 115/220VAC 50/60 Hz 20A sources of power are required to operate the test equipment (power requirements will vary depending on the number of amplifier/antenna assemblies used).  The tests described herein may be performed in any order.  Since the RF radiated field can be hazardous to personnel, the admittance of people in the vicinity of the tests should be minimized. Observers and visitors shall only be allowed onboard the aircraft in company of the test personnel. In addition,

Ref. : JC241-9082-02 TEST PROCEDURE, GROUND EMC TEST Rev. : PB Transmitting Portable Electronic Devices (T-PEDs) Date : JAN 03, 2012 Boeing 747-400 Series Aircraft Page : 9/20 a flashing red light will be located close to the aircraft entrance to inform personnel of the transmitting state. 6.2 Resources Required  Test Sets and electrical power for ATC, TCAS, VOR/ILS, Marker Beacon, DME, and SELCAL. Note: Where possible, local off-the-air signals will be used when testing these systems. The test sets will be used only in the absence of valid local signals.  Flashing red light  Personal communication devices (i.e. hand-held radios) for communication between test personnel, FAA Representative/Designee, mechanics including headsets for Service Intercom communication.  Tape measure (16’ or longer)  Test equipment specified in Test Equipment Parts List PL44-8092-10.  Aircraft maintenance personnel with the authority and knowledge to assist in the performing of the aircraft system checks from the cockpit and Cabin Crew Control Stations.  Aircraft maintenance personnel with the knowledge to operate the In-Flight Entertainment Equipment (IFE) including knowledge of crew passwords and login information.  Exterior observers to monitor control surfaces for uncommanded movements (requires enough personnel to monitor flight control surfaces simultaneously such as rudder, elevator, ailerons and spoilers).  Armstrong Aerospace personnel to set up and operate the test equipment, and coordinate the test effort.  Digital camera to document test antenna positions and test equipment setup. 7. AIRCRAFT CONFIGURATION As much as practically possible while allowing for personnel access and test cable routing, doors and hatches should be closed. All systems that can be safely operated on the ground should be switched on and set to valid modes. Select all navigation and communication systems on and receiving valid but minimal signals when test sets are available. Operate the navigation and communications equipment on at least one low, high and mid-band frequency. Record all frequencies used. Check that engine instruments, radio altimeter, stall warning, and flap indications are powered. Tune all radio receivers to the test set frequency or to a distant active channel. Check the magnetic compass is not displaying any erroneous heading at least four times throughout the test. 8. TEST WITNESSING & PERFORMANCE OF TESTS Individuals witnessing the tests (FAA representative or designee) shall verify antenna position placement prior to performance of tests. The test witness shall be positioned such that observation of normal operation of the system/equipment under test is evident.

Ref. : JC241-9082-02 TEST PROCEDURE, GROUND EMC TEST Rev. : PB Transmitting Portable Electronic Devices (T-PEDs) Date : JAN 03, 2012 Boeing 747-400 Series Aircraft Page : 10/20 Testing personnel shall communicate any observations, such as fault displays, to the attention of the test witness. 9. EQUIPMENT UNDER TEST (EUT) These test procedures should not be executed until all logbook discrepancies for any of the targeted aircraft systems have been resolved. All aircraft systems regarded as “Critical”, “Essential”, and “Non-Essential but Required for Dispatch” will be evaluated for interference in the presence of the EMC test signal. Any observed effects should be assessed as failing the test but the interference threshold should be determined to allow for possible post-test evaluation and mitigation. In the “Non-Essential” category, aircraft equipment that is not required for dispatch, but that might have a susceptibility to transmissions at the test frequencies will be tested. Equipment in this category includes primarily the IFE (in-flight entertainment) system head-end, distribution, and display units (if equipped). Any effect on devices in this category will be recorded and reported to the airline for additional action. Devices falling within this category will be clearly labeled “Non-Essential” on the aircraft-specific results report form. 10. OPERATION OF TEST AMPLIFIERS Operator control of the low-band and high-band amplifiers is identical, and simple. The only control on the Amplifier Enclosure is a lighted ON-OFF switch. The amplifiers contain an integral fan within the enclosure that blows across the power supply and the cooling fins of the power amplifier. If the fan does not run when the power cord of the enclosure is plugged in, unplug the power cord and check the fuse in the holder mounted adjacent to the lighted ON-OFF switch. Replace if necessary, after determining cause of failure. Do not operate the power amplifiers if the enclosure fan is inoperative. CAUTION: If any amplifier is operated without cooling airflow, POWER AMPLIFIER FAILURE WILL RESULT. If an amplifier has been running for several minutes or longer, allow at least 2 minutes for the fan to run (to cool the amplifier) after the ON-OFF switch has been turned OFF, before disconnecting the Amplifier Enclosure power cord from the 115/220 VAC source. Avoid plugging in or disconnecting the power cord with the enclosure switch in the ON position. When ready to commence testing, check that RF output of the SigGen is turned OFF, then turn the Amplifier Enclosure switch ON. The switch should light, indicating that power is being supplied to the amplifier. Allow several minutes for the amplifier to reach a normal operating temperature. Remove personnel from the vicinity of all test antenna(s) before turning the SigGen RF output ON again. When the particular test is finished, turn the SigGen RF output OFF. Depending on the wait time before starting the next test, the Amplifier Enclosure ON-OFF switch may be either turned OFF, or left ON. As long as the SigGen RF output is turned OFF, there will be no RF emission from the antenna(s), even with DC power being supplied to the amplifier.

Ref. : JC241-9082-02 TEST PROCEDURE, GROUND EMC TEST Rev. : PB Transmitting Portable Electronic Devices (T-PEDs) Date : JAN 03, 2012 Boeing 747-400 Series Aircraft Page : 11/20 11. RF PLANNING CHART/CALIBRATION RECORD Provides the test frequencies, modulation and power levels to be used during on-aircraft testing. In addition, signal generator amplitude settings required to generate the required power level are determined during the calibration process and recorded there. 11.1 Test Signal Waveforms DO-294C, table 6.F-1 provides an evaluation of wireless technologies and provides two basic signal waveforms for back-door EMI effects testing and limited front-door testing. The first basic signal waveform has been found to be applicable to all TDMA-like standards and the second to all CDMA/FDMA based access schemes. These two basic waveforms will be used for on-aircraft susceptibility testing. 11.1.1 Test Waveform 1 (TDMA and CSMA/FHSS Standards) Test signal 1 is a pulse-modulated signal with a pulse-repetition-frequency (PRF) in the range of 200 Hz and a pulse duration in the range of 625 us as shown in Figure 1 – Test Waveform 1. Figure 1 – Test Waveform 1 11.1.2 Test Waveform 2 (CDMA/FDMA Standards) Test signal 2 is a continuous waveform with no pulse-modulation as shown in Figure 2 – Test Waveform 2. Figure 2 – Test Waveform 2

Ref. : JC241-9082-02 TEST PROCEDURE, GROUND EMC TEST Rev. : PB Transmitting Portable Electronic Devices (T-PEDs) Date : JAN 03, 2012 Boeing 747-400 Series Aircraft Page : 12/20 12. FCC EXPOSURE LIMITS FCC Part 1 (Sec. 1.1310 Radio Frequency Radiation Exposure Limits) offers guidelines for human exposure to electromagnetic fields. Two limits are defined, one for Occupational Exposure and another for the general public (Incidental or Uncontrolled Exposure). Because our test occurs within a controlled environment, we must only comply with the Occupational Exposure limit, and not the more restrictive Incidental Exposure limit. However, we will calculate for both limits to allow personnel the knowledge to limit their exposure as much as possible. Below 1500 MHz, FCC limits vary with the frequency in use. Below 1500 MHz, FCC Exposure Limits Limit Type Exposure Limit Occupational/Controlled f/300 mW/cm2 (f/30 W/m2), where f is frequency, Exposure: averaged over 6 minutes General Public/Uncontrolled f/1500 mW/cm2 (f/150 W/m2), where f is Exposure: frequency, averaged over 30 minutes FCC limits are the same for all frequencies between 1500 and 100,000 MHz. Below 1500 MHz, FCC Exposure Limits Limit Type Exposure Limit Occupational/Controlled 5 mW/cm2 (50 W/m2), averaged over 6 minutes Exposure: General Public/Uncontrolled 1 mW/cm2 (10 W/m2), averaged over 30 Exposure: minutes Note that the allowable values for exposure represent a power density averaged over a certain amount of time. A power density at or below that exposure limit may be tolerated for an indefinite period of time. A power density above that limit must be averaged over the specified time period. For example, an occupational exposure to a power density of 50 W/m2 for an entire work shift is allowable. If the power density is increased to 150 W/m2, for every 2 minutes of exposure to the field, a person must then be completely removed from the field for 4 minutes. The electric field strengths (Ef) to be used are provided in Appendix A. Knowing the power density of our test signal and the distance from the antenna at which it is to be generated, we may use a ratio to calculate the distance from the transmitting antenna to the power density representing the FCC limit (reference column AG). This distance may then be employed as “closest point of approach” to a radiating antenna during conduct of the tests. Caution: Exposure to Radio Frequency Radiation! All personnel must remain at least 16” from any radiating test antenna.

Ref. : JC241-9082-02 TEST PROCEDURE, GROUND EMC TEST Rev. : PB Transmitting Portable Electronic Devices (T-PEDs) Date : JAN 03, 2012 Boeing 747-400 Series Aircraft Page : 13/20 13. BACK-DOOR EVALUATION Back-door evaluation tests are performed to determine if the aircraft electronics are susceptible to interference from passenger T-PEDs through coupling of power or signal wires, or through apertures in the device enclosures. Reference JC241-9082-04 for back- door evaluation test antenna positions. At these positions, the equipment will be exercised and monitored by the FAA Representative/Designee. In addition to all systems and equipment listed in this section, the following cabin components are to be evaluated. At the discretion of the FAA Representative/Designee, the equipment will be exercised and monitored per applicable maintenance instructions. Cabin Components / Equipment System Test Record Cabin Components / Equipment B.21 1. Ensure calibration of test equipment setup has been accomplished in accordance with JC241-8092-01. Accuracy of this calibration will be relied on to generate the desired field strength level of the test signals. 2. Identify and become familiar with the location of the aircraft equipment racks/locations as shown in JC241-9082-04. 3. Locate the test antenna at the first back-door evaluation location (order of testing is at the discretion of the Test Director and FAA Representative/Designee). 4. Set up the test equipment per JC241-8092-03. 5. Allow sufficient cable/wiring lengths to keep personnel separated from the test antennas during the test. 6. Orient the antenna in the horizontal polarization as shown in JC241-9082-03. 7. Record the test antenna location and test equipment setup using a digital camera. 8. Ensure that the SigGen RF outputs are both OFF. 9. Turn the amplifier enclosure switches ON. The power switches should light, indicating power is being supplied to the amplifiers. 10. Remove personnel from the vicinity of the antenna(s). 11. Set up the SigGen(s) (Vector Signal Generators) to transmit at the frequency and modulation for Test Frequency #1 as shown in Appendix A. Set the SigGen(s) amplitude to the specified RF level(s) established during calibration as recorded in column W of Appendix A. This will produce the field strength(s) identified during calibration. NOTE: The SigGens are capable of being remotely controlled and may be pre-programmed during the calibration process to automatically sweep through the required test frequencies at the required power levels. Automated operation is at the discretion of the test personnel and is not described within this document.

Ref. : JC241-9082-02 TEST PROCEDURE, GROUND EMC TEST Rev. : PB Transmitting Portable Electronic Devices (T-PEDs) Date : JAN 03, 2012 Boeing 747-400 Series Aircraft Page : 14/20 12. Turn the SigGen RF output(s) ON. The aircraft equipment is now being exposed to the test signal(s). Exercise the applicable aircraft equipment and verify that no abnormal equipment function occurs. 13. If abnormal function of an EUT does occur, coordinate with the FAA Representative/Designee a series of steps to confirm the effect. First, turn the SigGen RF Output(s) OFF and verify the abnormal function clears. After confirmation of the effect, turn the SigGen RF output(s) back on and reduce the output(s) of the SigGen(s) by .5 dB steps, pausing 10 seconds between steps while exercising the aircraft equipment, and note the level at which the abnormal function does not occur. Evaluate the position of the antenna, the polarization and the distance from the effected unit to determine if local beam strength is at or above desired test signal level. If necessary, reposition the test antenna and repeat the test. 14. Turn the SigGen RF Output(s) OFF. In Appendix B, record the test results as either ‘Pass’ or ‘Fail’ and if there was an ‘Effect’, provide a description of the effect (identify equipment, describe abnormal behavior, etc.). Record the test frequency(s) causing the effect, the transmit identifier (modulation and antenna polarization) and the susceptibility threshold (SigGen RF Output Level(s) at the lowest level observed to cause the effect), even if the local threshold level is ultimately determined to be above the required test signal level. 15. Repeat steps 11 through 14 for the remainder of the test frequencies listed in Appendix A. 16. Rotate the test antenna(s) to the vertical polarization. 17. Repeat steps 11-15 for the vertical antenna polarization. 18. Repeat steps 7-17 for the remaining back-door test antenna locations. 13.1 Antenna Position #1 – Flight Deck Position test antenna(s) 40” from main instrument panel (reference JC241-9082-04 Test Procedure Diagram). Exercise and monitor the following systems. Reference the aircraft maintenance manual (AMM), if necessary, for guidance on operational test procedures. Note: It may not be possible to expose all flight deck instruments with a single antenna position. Re-aim the antenna as required during the procedure. Exercise and monitor the following systems per the airplane maintenance manual operational test procedures: Antenna Position #1, Flight Deck Systems / Equipment System Test Record Flight Deck Systems / Equipment B.1

Ref. : JC241-9082-02 TEST PROCEDURE, GROUND EMC TEST Rev. : PB Transmitting Portable Electronic Devices (T-PEDs) Date : JAN 03, 2012 Boeing 747-400 Series Aircraft Page : 15/20 13.2 Antenna Position #2 – E1 Equipment Rack (Requires Engine Run) Position test antenna(s) a maximum of 40” FWD of rack face (reference JC241-9082-04 Test Procedure Diagram). Exercise and monitor the following systems. Reference the aircraft maintenance manual (AMM), if necessary, for guidance on operational test procedures. Antenna Position #2, E1 Equipment Rack Systems / Equipment System Test Record E1 Equipment Rack Systems / Equipment B.2 13.3 Antenna Position #3 – E2 Equipment Rack (Requires Engine Run) Position test antenna(s) a maximum of 40” FWD of rack face (reference JC241-9082-04 Test Procedure Diagram). Exercise and monitor the following systems. Reference the aircraft maintenance manual (AMM), if necessary, for guidance on operational test procedures. Antenna Position #3, E2 Equipment Rack Systems / Equipment System Test Record E2 Equipment Rack Systems / Equipment B.3 13.4 Antenna Position #4 – E31 Equipment Rack (Requires Engine Run) Position test antenna(s) 40” AFT of rack face (reference JC241-9082-04 Test Procedure Diagram). Exercise and monitor the following systems. Reference the aircraft maintenance manual (AMM), if necessary, for guidance on operational test procedures. Antenna Position #4, E31 Equipment Rack Systems / Equipment System Test Record E31 Equipment Rack Systems / Equipment B.4 13.5 Antenna Position #5 – E30 Equipment Rack Position test antenna(s) 40” AFT of rack face (reference JC241-9082-04 Test Procedure Diagram). Exercise and monitor the following systems. Reference the aircraft maintenance manual (AMM), if necessary, for guidance on operational test procedures. Antenna Position #5, E30 Equipment Rack Systems / Equipment System Test Record E30 Equipment Rack Systems / Equipment B.5

Ref. : JC241-9082-02 TEST PROCEDURE, GROUND EMC TEST Rev. : PB Transmitting Portable Electronic Devices (T-PEDs) Date : JAN 03, 2012 Boeing 747-400 Series Aircraft Page : 16/20 13.6 Antenna Position #6 – E6 and E9 Equipment Rack Position test antenna(s) centered between racks, maximum of 40” from rack faces (reference JC241-9082-04 Test Procedure Diagram). Exercise and monitor the following systems. Reference the aircraft maintenance manual (AMM), if necessary, for guidance on operational test procedures. Antenna Position #6, E6 and E9 Equipment Rack Systems / Equipment System Test Record E6 and E9 Equipment Rack Systems / Equipment B.6 13.7 Antenna Position #7 – E29 Equipment Rack Position test antenna(s) 40” from rack face (reference JC241-9082-04 Test Procedure Diagram). Exercise and monitor the following systems. Reference the aircraft maintenance manual (AMM), if necessary, for guidance on operational test procedures. Antenna Position #7, E29 Equipment Rack Systems / Equipment System Test Record E29 Equipment Rack Systems / Equipment B.7 13.8 Antenna Position #8 – E8 Equipment Rack Position test antenna(s) 40” from rack face (reference JC241-9082-04 Test Procedure Diagram). Exercise and monitor the following systems. Reference the aircraft maintenance manual (AMM), if necessary, for guidance on operational test procedures. Antenna Position #8, E8 Equipment Rack Systems / Equipment System Test Record E8 Equipment Rack Systems / Equipment B.8 13.9 Antenna Position #9 – E42 Equipment Rack Position test antenna(s) 40” from rack face (reference JC241-9082-04 Test Procedure Diagram). Exercise and monitor the following systems. Reference the aircraft maintenance manual (AMM), if necessary, for guidance on operational test procedures. Antenna Position #9, E42 Equipment Rack Systems / Equipment System Test Record E42 Equipment Rack Systems / Equipment B.9 13.10 Antenna Position #10 – E33 Equipment Rack Position test antenna(s) 40” from rack face (reference JC241-9082-04 Test Procedure Diagram). Exercise and monitor the following systems. Reference the aircraft maintenance manual (AMM), if necessary, for guidance on operational test procedures. Antenna Position #10, E33 Equipment Rack Systems / Equipment System Test Record E33 Equipment Rack Systems / Equipment B.10

Ref. : JC241-9082-02 TEST PROCEDURE, GROUND EMC TEST Rev. : PB Transmitting Portable Electronic Devices (T-PEDs) Date : JAN 03, 2012 Boeing 747-400 Series Aircraft Page : 17/20 13.11 Antenna Position #11 – M7603 Card File (Requires Engine Run) Position test antenna(s) 40” from rack face (reference JC241-9082-04 Test Procedure Diagram). Exercise and monitor the following systems. Reference the aircraft maintenance manual (AMM), if necessary, for guidance on operational test procedures. Antenna Position #11, M7603 Card File Systems / Equipment System Test Record M7603 Card File Systems / Equipment B.11 13.12 Antenna Position #12 – M0826 and M7852 Card Files Position test antenna(s) 40” from rack face (reference JC241-9082-04 Test Procedure Diagram). Exercise and monitor the following systems. Reference the aircraft maintenance manual (AMM), if necessary, for guidance on operational test procedures. Antenna Position #12, M0826 and M7852 Card Files Systems / Equipment System Test Record M0826 and M7852 Card Files Systems / Equipment B.12 13.13 Antenna Position #13 – M7952 Card File (MAWEA) Position test antenna(s) 40” from rack face (reference JC241-9082-04 Test Procedure Diagram). Exercise and monitor the following systems. Reference the aircraft maintenance manual (AMM), if necessary, for guidance on operational test procedures. Antenna Position #13, M7952 Card File Systems / Equipment System Test Record M7952 Card File Systems / Equipment B.13 14. FRONT-DOOR EVALUATION The purpose of front-door evaluation is to determine if the onboard receiver systems are susceptible to interference from passenger T-PEDs through coupling of the aircraft antenna system. At these positions, the specific onboard receiver system being evaluated will be exercised and monitored by the designated FAA Representative/Designee. 1. Ensure calibration of test equipment setup has been accomplished in accordance with JC241-8092-01 Setup/Calibration, Ground EMC Test, T-PEDs. Accuracy of this calibration will be relied on to generate the desired field strength level of the test signal. 2. Identify and become familiar with the location of the aircraft antennas as shown in drawing JC241-9082-04. 3. Locate the test antenna at the first front-door evaluation location horizontally polarized. Refer to JC241-8092-01 for guidance on Antenna Aiming (NOTE: Location of the test antennas during front-door evaluation focuses on areas where it is expected to be minimal path loss to each aircraft antenna system. Table 5.B-1 of RTCA/DO-294C provides guidance on test locations where path loss is minimal for the 747-400 aircraft).

Ref. : JC241-9082-02 TEST PROCEDURE, GROUND EMC TEST Rev. : PB Transmitting Portable Electronic Devices (T-PEDs) Date : JAN 03, 2012 Boeing 747-400 Series Aircraft Page : 18/20 4. Allow sufficient cable/ wiring lengths to keep personnel separated from the test antennas during the test. 5. Record the test antenna location and test equipment setup using a digital camera. 6. Set up the SigGen (Vector Signal Generator) to transmit at the frequency and modulation for Test Freq # 1 as shown in Appendix A. Set the SigGen amplitude to the specified RF level established during calibration. This will produce the field strength identified during calibration Turn the SigGen RF Output OFF. 7. Turn the amplifier enclosure switch ON. The power switch should light, indicating power is being supplied to the amplifier. 8. Remove personnel from the vicinity of the antenna. 9. Turn the SigGen RF output ON. The aircraft equipment is now being exposed to the test signal. Exercise the identified aircraft equipment and verify that no abnormal equipment function occurs. 10. If abnormal function of EUT does occur, turn the SigGen RF Output OFF and verify abnormal function clears. After confirmation of effect, reduce the output of the SigGen by .5 dB steps, pausing 10 seconds between steps while exercising the aircraft equipment, and note the level at which the abnormal function does not occur. Evaluate position of antenna and distance from effected unit to determine if local beam strength is at or above desired test signal level. If necessary, reposition the test antenna and repeat test. 11. Turn the SigGen RF Output OFF. Record the test results as either ‘Effect’ or ‘No Effect’. For all effects, describe the symptom or aircraft indicator, and whether or not the test signal was the source of interference. Record the test frequency being transmitted and the SigGen ‘RF Output Level’ at the susceptibility threshold (lowest level observed to cause the effect), even if the local threshold level is ultimately determined to be above our required test signal level. 12. Rotate the test antenna(s) to the vertical polarization. 13. Repeat steps 9-11 for the vertical antenna polarization. 14. Repeat steps 6 through 13 for all of the test frequencies listed in Appendix A. 15. Repeat steps 1 through 14 for the remaining front-door test antenna locations. 14.1 Antenna Position #14 – ~ STA 510 Position test antenna 40” from ~STA 510. Exercise and monitor the following systems. Reference the aircraft maintenance manual (AMM), if necessary, for guidance on operational test procedures. Antenna Position #14, ~STA 510, Receiver Systems System Test Record ~STA 510, Receiver Systems B.14

Ref. : JC241-9082-02 TEST PROCEDURE, GROUND EMC TEST Rev. : PB Transmitting Portable Electronic Devices (T-PEDs) Date : JAN 03, 2012 Boeing 747-400 Series Aircraft Page : 19/20 14.2 Antenna Position #15 – ~ STA 670 Position test antenna 40” from ~STA 670. Exercise and monitor the following systems. Reference the aircraft maintenance manual (AMM), if necessary, for guidance on operational test procedures. Antenna Position #15, ~STA 670, Receiver Systems System Test Record ~STA 670, Receiver Systems B.15 14.3 Antenna Position #16 – ~ STA 840 Position test antenna 40” from ~STA 840. Exercise and monitor the following systems. Reference the aircraft maintenance manual (AMM), if necessary, for guidance on operational test procedures. Antenna Position #16, ~STA 840, Receiver Systems System Test Record ~STA 840, Receiver Systems B.16 14.4 Antenna Position #17 – ~ STA 980 Position test antenna 40” from ~STA 980. Exercise and monitor the following systems. Reference the aircraft maintenance manual (AMM), if necessary, for guidance on operational test procedures. Antenna Position #17, ~STA 980, Receiver Systems System Test Record ~STA 980, Receiver Systems B.17 14.5 Antenna Position #18 – ~ STA 1320 Position test antenna 40” from ~STA 1320. Exercise and monitor the following systems. Reference the aircraft maintenance manual (AMM), if necessary, for guidance on operational test procedures. Antenna Position #18, ~STA 1320, Receiver Systems System Test Record ~STA 1320, Receiver Systems B.18 14.6 Antenna Position #19 – ~ STA 1710 Position test antenna 40” from ~STA 1710. Exercise and monitor the following systems. Reference the aircraft maintenance manual (AMM), if necessary, for guidance on operational test procedures. Antenna Position #19, ~STA 1710, Receiver Systems System Test Record ~STA 1710, Receiver Systems B.19

Ref. : JC241-9082-02 TEST PROCEDURE, GROUND EMC TEST Rev. : PB Transmitting Portable Electronic Devices (T-PEDs) Date : JAN 03, 2012 Boeing 747-400 Series Aircraft Page : 20/20 14.7 Antenna Position #20 – Aft-Most Cabin Position test antenna 40” from most aft location in the cabin. Exercise and monitor the following systems. Reference the aircraft maintenance manual (AMM), if necessary, for guidance on operational test procedures. Antenna Position #21, Aft-Most Cabin, Receiver Systems System Test Record Aft-Most Cabin, Receiver Systems B.20 14.8 CONCLUSION If no anomalous system responses are noted while performing these tests, then the T- PEDs identified within this document will be considered electromagnetically compatible with the Boeing 747-400 aircraft and in compliance with 14 CFR 25.1309(a).

Transmitting Portable Electronic Devices Ref: JC241-9082-02 (T-PEDs) Rev: PB Boeing 747-400 Series Aircraft Date: 01/03/12 Page: A1 Uplink Uplink T‐PED Target EIRP 50' RF Exposure Hazard Frequency Frequency Intentional Target SigGen SpecA Test Modulation T‐PED (dBm, Target Biconical Amplifier LMR‐500 SigGen Minimum Distance From Test Wireless (T‐PED (T‐PED Emission EIRP (W) MEF Target Amplifier Output Indicated Frequency Intentional highest EIRP Antenna Gain Cable Output Antenna (inches) # Standard Transmit) Transmit) Code From (dB ERP (W) Input (Est‐ Signal (MHz) EIRP (dBm) value (W) Gain (dB) Loss (Actual) Start of End of Band DO‐294C added) imated) (dBm) of group) ( ‐ dBm) Band (MHz) (MHz) Table 6.F‐4 Controlled Uncontrolled Pulse CW Enviroment Enviroment 1 CDMA2000 410 420 415 CW N0N 1 30.0 12 42.0 15.8 13.7 0.4 44 ‐2.4 1.0 ‐1.4 ‐6.80 15.4 12 27 2 GSM400 450.4 457.6 454 Pulse P0N 2 33.0 12 45.0 31.7 29.5 0.6 46 ‐1.6 1.1 ‐0.5 ‐4.80 18.4 16 36 3 CDMA2000 450 460 454 CW N0N 1 30.0 12 42.0 15.8 13.7 0.6 46 ‐4.6 1.1 ‐3.5 ‐7.80 15.4 11 25 4 CDMA2000 479 484 482 CW N0N 1 30.0 12 42.0 15.8 13.7 0.1 46 ‐4.1 1.1 ‐3.0 ‐7.80 15.9 11 25 5 CDMA2000 776 794 785 CW N0N 1 30.0 12 42.0 15.8 13.7 0.6 53 ‐11.6 1.5 ‐10.1 ‐8.40 12.2 9 19 CDMA2000 806 849 N0N 1 30.0 12 13.7 0.0 53 ‐11.0 1.5 6 CDMAone CW N0N 1 30.0 12 42.0 15.8 13.7 0.0 53 ‐53.0 1.5 ‐9.5 11.5 824 849 UMTS FDD N0N 0.25 24.0 12 13.7 0.0 53 ‐53.0 1.5 ‐6.50 828 12 27 GSM850 P0N 2 33.0 12 29.5 0.0 53 ‐8.0 1.5 7 IS‐136 824 849 Pulse P0N 0.6 27.8 12 45.0 31.7 29.5 0.0 53 ‐53.0 1.5 ‐6.5 14.5 UMTS TDD P0N 0.25 24.0 12 29.5 0.0 53 ‐53.0 1.5 ‐3.20 8 CDMA2000 870 925 898 CW N0N 1 30.0 12 42.0 15.8 13.7 ‐0.9 53 ‐10.1 1.6 ‐8.5 ‐4.00 11.0 8 18 9 GSM900 876 915 913 Pulse P0N 2 33.0 12 45.0 31.7 29.5 ‐1.1 53 ‐6.9 1.6 ‐5.3 0.00 13.8 11 25 10 MOBILE SAT 1613.8 1626.5 1626 Pulse P0N 1 30.0 12 42.0 15.8 13.7 1.1 53 ‐12.1 2.2 ‐9.9 ‐9.00 4.7 6 14 11 CDMA2000 CW N0N 1 30.0 12 42.0 15.8 13.7 1.1 53 ‐12.1 2.2 ‐9.9 ‐11.00 3.5 6 14 1710 1785 1748 12 DCS1800 Pulse P0N 1 30.0 12 42.0 15.8 13.7 1.1 53 ‐12.1 2.2 ‐9.9 ‐11.00 3.5 6 14 CDMA2000 N0N 1 30.0 12 13.7 1.1 53 ‐12.1 2.3 13 UMTS FDD CW N0N 0.25 24.0 12 42.0 15.8 13.7 1.1 53 ‐54.1 2.3 ‐9.8 2.8 6 14 CDMAone N0N 1 30.0 12 13.7 1.1 53 ‐54.1 2.3 ‐12.00 1850 1910 1884 UMTS TDD P0N 0.25 24.0 12 13.7 1.1 53 ‐12.1 2.3 14 PCS1900 Pulse P0N 1 30.0 12 42.0 15.8 13.7 1.1 53 ‐12.1 2.3 ‐9.8 2.8 6 14 IS‐136 P0N 0.6 27.8 12 13.7 1.1 53 ‐54.1 2.3 ‐12.00 15 UMTS TDD 1900 1920 1910 Pulse P0N 0.25 24.0 12 36.0 4.0 1.8 1.1 53 ‐18.1 2.4 ‐15.7 ‐18.00 ‐3.5 3 7 CDMA2000 N0N 1 30.0 12 13.7 1.1 53 ‐12.1 2.4 16 1920 1980 1949 CW 42.0 15.8 ‐9.7 2.4 6 14 UMTS FDD N0N 0.25 24.0 12 13.7 1.1 53 ‐54.1 2.4 ‐10.50 17 UMTS TDD 2010 2025 2018 Pulse P0N 0.25 24.0 12 36.0 4.0 1.8 1.1 53 ‐18.1 2.4 ‐15.7 ‐17.00 ‐3.9 3 7 18 UMTS/3G/PCN 2110 2170 2140 CW N0N 0.25 24.0 12 36.0 4.0 1.8 1.1 53 ‐18.1 2.5 ‐15.6 ‐12.00 ‐4.8 3 7 19 2412 Pulse P0N 0.5 27.0 10 37.0 5.0 2.9 1.1 53 ‐17.1 2.7 ‐14.4 ‐7.00 ‐4.7 4 8 20 802.11b/g/n 2.4 GHz 2.497 GHz 2437 Pulse P0N 0.5 27.0 10 37.0 5.0 2.9 1.1 53 ‐17.1 2.7 ‐14.4 ‐8.50 ‐5.0 4 8 21 2462 Pulse P0N 0.5 27.0 10 37.0 5.0 2.9 1.1 53 ‐17.1 2.7 ‐14.4 ‐9.50 ‐5.1 4 8 22 FDD LTE (Band TBD) 2500 2685 2595 Pulse CW P0N/N0N 1 30.0 12 42.0 15.8 13.7 1.9 53 ‐12.9 3.3 ‐9.6 ‐4.40 ‐0.6 6 14 23 Wi‐Max 3400 3600 3450 Pulse CW P0N/N0N 1 30.0 12 42.0 15.8 13.7 1.9 53 ‐12.9 3.3 ‐9.6 ‐8.90 ‐4.2 6 14 24 5150 5250 5170 Pulse P0N 0.5 27.0 10 37.0 5.0 2.9 1.7 53 ‐17.7 4.2 ‐13.5 ‐5.20 ‐14.1 4 8 25 5250 5350 5300 Pulse P0N 0.5 27.0 10 37.0 5.0 2.9 1.7 53 ‐17.7 4.2 ‐13.5 ‐13.90 ‐14.8 4 8 802.11a/n 26 5470 5725 5580 Pulse P0N 0.5 27.0 10 37.0 5.0 2.9 1.7 53 ‐17.7 4.4 ‐13.3 ‐13.30 ‐15.3 4 8 27 5725 5825 5825 Pulse P0N 0.5 27.0 10 37.0 5.0 2.9 1.7 53 ‐17.7 4.4 ‐13.3 ‐13.90 ‐16.5 4 8

TEST PROCEDURE GROUND EMC TEST Ref: JC241‐9082‐02 Transmitting Portable Electronic Devices Rev: ‐ (T-PEDs) Date: 2/6/2012 Boeing 747-400 Aircraft Page: B1 Frequency Range / Transmit Identifier Antenna Position Paragraph System Effectivity AMM Reference(s) 400 MHz to 1.0 GHz 1.0 GHz to 2.5 GHz 2.5 GHz to 6.0 GHz Description of Effect Test Frequency(s) Causing Effect Transmit Identifier Susceptibility Threshold H‐PS H‐CW V‐PS V‐CW H‐PS H‐CW V‐PS V‐CW H‐PS H‐CW V‐PS V‐CW BACK DOOR EVALUATION 1 ‐ Flight Deck B.1.1 EEL All 33‐51 Cockpit Lighting All 33‐13, 33‐15 ` Cabin Lighting All 33‐21, 33‐22, 33‐23, 33‐24 B.1.2 Autopilot Mode Control Panel All 22‐12 B.1.3 Display System (PFD, ND, ECIAS) All 31‐61 B.1.4 FMS CDUs All 34‐61 B.1.5 ACP (Audio Control Panels) All 23‐51 B.1.6 Standby Instruments All 34‐24, 34‐13, 34‐22 B.1.7 Clocks All 31‐25 Magnetic Compass All 34‐22 B.1.8 Additional Equipment 2‐E1 Rack B.2.1 A/C Power Generation Gen Cont Unit 1 All 24‐22 Gen Cont Unit 2 All 24‐22 Bus Cont Unit 1 All 24‐22 B.2.2 Flight Control Systems Mod 1L‐FCE Power Supply‐ Left 1 All 27‐09 Flap Control Unit‐ Left All 27‐51 Mod Stab Trim/Rudder Ratio‐ Left All 27‐41 FCE Power Supply Mod‐ Left 2 All 27‐09 Computer Fight Control‐ Left All 22‐11 Module Yaw Damper‐ Upper All 22‐21 B.2.3 Fire Protection and Warning Systems Vib Monitor Engine 1 & 2 All 77‐31 Ground Prox Computer All 34‐46 B.2.4 Navigation Air Data Computer All 34‐12 Receiver ILS‐Left All 34‐31 Air Data Computer‐ Center All 34‐12 Multi Mode Rceiver‐ Center All 34‐31 Static Inverter‐ ILS PRCS Unit All 34‐24 ILS Receiver‐ Right All 34‐31 Intertial Ref Unit‐ Left All 34‐21 Intertial Ref Unit‐ Center All 34‐21 Intertial Ref Unit‐ Right All 34‐21 B.2.5 Communications HF Comm Transceiver‐ Left All 23‐11 HF Comm Transceiver‐ Right All 23‐11 B.2.6 Air Conditioning Cabin Pressure Control Auto A All 21‐31 B.2.7 Special Electronics Digital Interface Unit All 23‐32 Data Management Unit All 31‐03 CMC‐ Right All 31‐61 CMC‐ Left All 45‐45 B.2.8 Landing Gear/Hydraulics Unit‐ Tire Press Mon All 32‐45 Proximity SW Elex Unit Mod All 32‐61 B.2.9 De‐Icing Window Heat Control‐1L All 30‐41 B.2.10 Additional Equipment 3 ‐ E2 Rack B.3.1 A/C Power Generation Aux Gen Cont Unit #2 All 24‐22 Bus Cont Unit All 24‐41 Gen Cont Unit 3 &4 All 24‐22 B.3.2 Flight Control Systems FCE Power Supply Mod‐ Right 1 All 27‐09 Flap Cont Unit‐ Center All 27‐51 Stab/Trim Rudder Ratio‐ Right All 27‐41 Yaw Damper Mod‐ Lower All 22‐21 Flap Cont Unit‐Right All 27‐51 FCE Power Supply Mod‐Right 2 All 27‐09 B.3.3 Fire Protection and Warning Systems Vib Monitor Eng 3 & 4 All 77‐31 B.3.4 Navigation Flight Management Computer All 34‐61 DME Interrogator‐ Right All 34‐55 VOR/Marker Receiver‐ Right All 34‐51 FMC‐ Left All 34‐61 Computer‐ Para Visual Display All 34‐35 VOR/Marker Receiver‐ Left All 34‐51 DME Interrogator‐ Left All 34‐55 Computer Air Data‐ Right All 34‐51 B.3.5 Communications Passenger Address Controller All 23‐30

TEST PROCEDURE GROUND EMC TEST Ref: JC241‐9082‐02 Transmitting Portable Electronic Devices Rev: ‐ (T-PEDs) Date: 2/6/2012 Boeing 747-400 Aircraft Page: B2 Frequency Range / Transmit Identifier Antenna Position Paragraph System Effectivity AMM Reference(s) 400 MHz to 1.0 GHz 1.0 GHz to 2.5 GHz 2.5 GHz to 6.0 GHz Description of Effect Test Frequency(s) Causing Effect Transmit Identifier Susceptibility Threshold H‐PS H‐CW V‐PS V‐CW H‐PS H‐CW V‐PS V‐CW H‐PS H‐CW V‐PS V‐CW Cabin Interphone Controller All 23‐31 Audio Management Unit All 23‐42 ACARS Management Unit All 23‐51 VHF Comm XCVR‐ Right All 23‐12 VHF Comm XCVR‐ Left All 23‐12 VHF Comm XCVR‐ Center All 23‐12 SEL‐CAL Decoder All 23‐21 B.3.6 Air Conditioning Cabin Pressure Control Auto B All 21‐31 Pack Temp Controller‐ A All 21‐63 Pack Temp Controller‐ B All 21‐63 Zone Temp Controller Unit All 21‐63 Air Supply Control and Test Unit All 21‐61 B.3.7 Special Electronics Control Management Unit All 45‐10 Electronic Interface Unit‐ Left All 31‐61 Electronic Interface Unit‐ Right All 31‐61 Electronic Interface Unit‐ Center All 31‐61 B.3.8 Air Traffic Control ATC Transponder‐ Right All 34‐53 ATC Transponder‐ Left All 34‐53 ATC Antenna Switch ‐ Top All 34‐53 ATC Antenna Switch‐ Bottom All 34‐53 B.3.9 Landing Gear/Hydraulics Mod Hydraulic Quantity Interface All 29‐33 B.3.10 De‐Icing Window Heat Controller All 30‐41 B.3.11 Additional Equipment 4 ‐ E31 Rack B.4.1 In‐Flight Entertainment (IFE) Passenger Address Tape Reproducer All 23‐34 Audio Entertainment Multiplexer All 23‐30 Audio Entertainment Tape Deck All 23‐32 B.4.2 Additional Equipment 5 ‐ E30 Rack B.5.1 A/C Power Generation Transformer Rectifier Unit 1 All 24‐32 Transformer Rectifier Unit 2 All 24‐32 Transformer Rectifier Unit 3 All 24‐32 Transformer Rectifier Unit 4 All 24‐32 Static Inverter‐ ILS PRCS Unit All 24‐33 Battery Charger All 24‐31 B.5.2 Navigation Rcvr/Transmitter, Weather Radar 1 All 34‐43 Rcvr/ Transmitter, Weather Radar 2 All 34‐43 Rcvr‐ XMTR, WXR Right All 34‐43 B.5.3 Additional Equipment 6 ‐ E6 / E9 Rack B.6.1 Fire Protection and Warning Systems Brake Temp Mon Unit All 32‐46 B.6.2 Engine Control Fuel Quantity Processor All 28‐21 B.6.3 Navigation Rad Alt XMTR Receiver‐ Right All 34‐33 Rad Alt XMTR Receiver‐ Center All 34‐33 Rad Alt XMTR Receiver‐ Left All 34‐33 ADF Receiver‐ Right All 34‐57 ADF Receiver‐ Left All 34‐57 B.6.4 Landing Gear/Hydraulics Brake System Control Unit All 32‐42 B.6.5 Additional Equipment 7 ‐ E29 Rack B.7.1 In‐Flight Entertainment (IFE) Video System Control Unit All 23‐32 PFIDS Mode Selector/ Cabin Controller Unit All 23‐30 Video Tape Reproducer 1 All 23‐32 Video Tape Reproducer 2 All 23‐32 Video Tape Reproducer 3 All 23‐32 B.7.2 Additional Equipment 8 ‐ E8 Rack B.8.1 A/C Power Generation APU Static Inverter All 24‐33 Controller, APU All 49‐11 B.8.2 Special Electronics Digital Flight Data Recorder All 31‐31

TEST PROCEDURE GROUND EMC TEST Ref: JC241‐9082‐02 Transmitting Portable Electronic Devices Rev: ‐ (T-PEDs) Date: 2/6/2012 Boeing 747-400 Aircraft Page: B3 Frequency Range / Transmit Identifier Antenna Position Paragraph System Effectivity AMM Reference(s) 400 MHz to 1.0 GHz 1.0 GHz to 2.5 GHz 2.5 GHz to 6.0 GHz Description of Effect Test Frequency(s) Causing Effect Transmit Identifier Susceptibility Threshold H‐PS H‐CW V‐PS V‐CW H‐PS H‐CW V‐PS V‐CW H‐PS H‐CW V‐PS V‐CW Cockpit Voice Recorder All 23‐71 SPD Card File All 27‐28 B.8.3 Fuel Control Fuel Quality Indicating System All 28‐21 B.8.4 Additional Equipment 9 ‐ E42 Rack B.9.1 Communications Radio Frequency Unit (RFU) All 23‐25 Satcom Data Unit (SDU) All 23‐25 B.9.2 Additional Equipment 10 ‐ E33 Rack B.10.1 A/C Power Generation Charger APU Battery All 24‐31 Battery‐ APU All 24‐31 DCCS‐ APU Battery All 24‐31 B.10.2 Additional Equipment 11 ‐ M7603 Card File B.11.1 Electrical System Card File All 12 ‐ M0826 / M7852 Card Files B.12.1 Fire Detection Card File All B.12.2 Fuel System Card File All 13 ‐ M7952 Card File B.13.1 MAWEA Card File All FRONT DOOR EVALUATION 14 ‐ Upper Deck, ~STA 510 B.14.1 Air Traffic Control (ATC) ATC (ATC Antenna Bottom) All 34‐53 B.14.2 Navigation TCAS (TCAS Antenna Top and Bottom) All 34‐45 B.14.3 Communications Airborne Telephone All 23‐12 15 ‐ Lower Deck, ~STA 670 B.15.1 Air Traffic Control (ATC) ATC (ATC Antenna Top) All 34‐53 B.15.2 Navigation DME‐L All 34‐55 B.15.3 Communications LGA 005‐006 23‐25 VHF‐L 005‐006 23‐12 VHF‐C 101‐105 23‐12 VHF‐R 005‐006 23‐12 16 ‐ Lower Deck, ~STA 840 B.16.1 Navigation RA TX‐L All 34‐33 RA TX‐R All 34‐33 RA TX‐C All 34‐33 GPS‐L 006, 101‐105 34‐58 GPS‐R 006, 101‐105 34‐58 DME‐R All 34‐55 B.16.2 Communications Airborne Telephone All 23‐19 17 ‐ Lower Deck, ~STA 980 B.17.1 Navigation RA RX‐L All 34‐33 RA RX‐R All 34‐33 RA RX‐C All 34‐33 MB All 34‐32 18 ‐ Lower Deck, ~STA 1320 B.18.1 Navigation ADF‐L All 34‐57 ADF‐R All 34‐57 B.18.2 Communications Airborne Telephone All 23‐19 19 ‐ Lower Deck, ~STA 1710 B.19.1 Communications HGA Top All 23‐25 VHF‐L 101‐105 23‐12 VHF‐C 005‐006 23‐12 VHF‐R 101‐105 23‐12 Airborne Telephone All 23‐19 20 ‐ Lower Deck, Aft‐Most Cabin B.20.1 Navigation VOR All 34‐51 B.20.2 Communications HF All 23‐11 Cabin Components B.21.1 Lavatory Smoke Detectors All B.21.2 AED (Automated External Defibrillator) All B.21.3 DEU (Decoder Encoder Unit) All B.21.4 AIP (Attendant Indication Panel) All B.21.5 Area Call Panel / Interphones All B.21.6 FAP (Flight Attendant Panel) All B.21.7 PSU (Passenger Service Unit) All B.21.8 In‐Seat IFE Equipment All B.21.9 Rotating Navigation Beacon – Exterior Upper Fuselage, FR All LEGEND HP Horizontal Antenna, Pulse Wave HC Horizontal Antenna, Continuous Wave VP Vertical Antenna, Pulse Wave VC Vertical Antenna, Continuous Wave

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Document Created: 2012-03-06 18:17:32
Document Modified: 2012-03-06 18:17:32
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