Honeywell International Inc. 21111 N. 19th Avenue Phoenix, Arizona 85027-2708 U.S.A. CAGE: 58960 Telephone: 800-601-3099 (Toll Free U.S.A./Canada) Telephone: 602-365-3099 (International Direct)
Website: www

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# SERVICE BULLETIN ALERT

NAVIGATION -(1) AIR DATA MODULE, (2) AIR DATA COMPUTER, (3) AIR DATA ATTITUDE HEADING REFERENCE SYSTEM, (4) DIGITAL AIR DATA CO MPUTER - (1) Air Data Computer (ADC), PN 7014700-626, -914, PN 7024900-31304, PN 7030700-71701, -71703, -71704, (2) Air Data Module, PN 4071400-904, PN HG1153CA03, PN HG1153CA04, PN PG1152BC02, (3) Air Data Attitude Heading Reference System (ADAHRS), PN 065-00188-5103, -5502, (4) Digital Air Data Computer (DADC), PN 4040800-915; Inspection of Pressure Error and Remove Equipment if Necessary Legal Notice Export Control

This docu ment contains technical data and is subject to U.S. export regulations. These commodities, technology, or software were exported from the United States in accordance with the export administration regulations. Diversion contrary to U.S. law is prohibited. ECCN: 7E994. Proprietary Information Honeywell - Confidential THIS COPYRIGHTED WORK AND ALL INFORMATION ARE THE PROPERTY OF HONEYWELL INTERNATIONAL INC., CONTAIN TRADE SECRETS AND MAY NOT, IN WHOLE OR IN PART, BE USED, DUPLICATED, OR DISCLOSED FOR ANY PURP OSE WITHOUT PRIOR WRITTEN PERMISSION OF HONEYW ELL INTERNATIONAL INC. ALL RIGHTS RESERVED.

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Honeywell Materials License Agreement The documents and information contained herein (“the Materials”) are the proprietary data of Honeywell International Inc. and Honeywell Intellectual Properties Inc (collectively “Honeywell”). These Materials are provided for the exclusive use of Honeywell Service Centers; Honeywell-authorized repair facilities; operators of Honeywell aerospace products subject to an applicable product support agreement, their wholly owned-subsidiaries or a formally designated third party se rvice provider; and direct recipients of Materials from Honeywell’s Aerospace Technical Publication Distribution. The terms and conditions of this License Agreement govern your use of these Materials, except to the extent that any terms and conditions of another applicable agreement with Honeywell regarding the operation, maintenance, or repair of Honeywell aerospace products conflict with the terms and conditions of this License Agreement, in which case the terms and conditions of the other agreement will govern. However, this License Agreement will govern in the event of a conflict between its terms and conditions and those of a purchase order or acknowledgement. 1. License Grant - If you are a party to an applicable product support agreement, a Honeywell Service Center agreement, or an authorized repair facility agreement, Honeywell hereby grants you a limited, non-exclusive license to use these Materials to operate, maintain, or repair Honeywell aerospace products only in accordance with that agreement. If you are a direct recipient of these Materials from Honeywell’s Aerospace Technical Publication Distribution and are not a party to an agreement related to the operation, maintenance or repair of Honeywell aerospace products, Honeywell hereby grants you a limited, non-exclusive license to use these Materials to maintain or repair the subject Honeywell aerospace products only at the facility to which these Materials have been shipped ("the Licensed Facility"). Transfer of the Materials to another facility owned by you is permitted only if the original Licensed Facility retains no copies of the Materials and you provide prior written notice to Honeywell. 2. Rights In Materials - Honeywell retains all rights in these Materials and in any copies thereof that are not expressly granted to you, including all rights in patents, copyrights, trademarks, and trade secrets. No license to use any Honeywell trademarks or patents is granted under this License Agreement. 3. Confidentiality - You acknowledge that these Materials contain information that is confidential and proprietary to Honeywell. You agree to take all reasonable efforts to maintain the confidentiality of these Materials. 4. Assignment And Transfer - This License Agreement may be assigned to a formally designated service designee or transferred to a subsequent owner or operator of an aircraft containing the subject Honeywell aerospace products. However, the recipient of any s uch assignment or transfer must assume all of your obligations under this License Agreement. No assignment or transfer shall relieve any party of any obligation that such party then has hereunder. 5. Copies of Materials - Unless you have the express written permission of Honeywell, you may not make or permit making of copies of the Materials. Notwithstanding the foregoing, you may make copies of only portions of the Material for your internal use. You agree to return the Materials and any copies thereof to Honeywell upon the request of Honeywell. 6. Term - This License Agreement is effective until terminated as set forth herein. This License Agreement will terminate immediately, without notice from Honeywell, if you fail to comply with any provision of this License Agreement or will terminate simultaneously with the termination or expiration of your applicable product support agreement, authorized repair facility agreement, or your formal designation as a third party service provider. Upon termination of this License Ag reement, you will return these Materials to Honeywell without retaining any copies and will have one of your authorized officers certify that all Materials have been returned with no copies retained. 7. Remedies - Honeywell reserves the right to pursue all available remedies and damages resulting from a breach of this License Agreement. 8. Limitation of Liability - Honeywell does not make any representation regarding the use or sufficiency of the Materials. THERE ARE NO OTHER WARRANTIES, WHETHER WRITTEN OR ORAL, EXPRESS, IMPLIED OR STATUTORY, INCLUDING, BUT NOT LIMITED TO, (i) WARRANTIES ARISI NG FROM COURSE OF

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PERFORMANCE, DEALING, USAGE, OR TRADE, WHICH ARE HEREBY EXPRESSLY DISCLAIMED, OR (ii) WARRANTIES AGAINST INFRINGEMENT OF INTEL LECTUAL PROPERTY RIGHTS OF THIRD PARTIES, EVEN IF HONEYWELL HAS BEEN ADVISED OF ANY SUCH INFRINGEMENT. IN NO EVENT WILL HONEYWELL BE LIABLE FOR ANY INCIDENTAL DAMAGES, CONSEQUENTIAL DAMAGES, SPECIAL DAMAGES, INDIRECT DAMAGES, LOSS OF PROFITS, LOSS OF REVENUES, OR LOSS OF USE, EVEN IF INFORMED OF THE POSSIBILITY OF SUCH DAMAGES. TO THE EXTENT PERMITTED BY APPLICABLE LAW, THESE LIMITATIONS AND EXCLUSIONS WILL APPLY REGARDLESS OF WHETHER LIABILITY ARISES FROM BREACH OF CONTRACT, WARRANTY, TORT (INCLUDING BUT NOT LIMITED TO NEGLIGENCE), BY OPERATION OF LAW, OR OTHERWISE. 9. Controlling Law - This License shall be governed and construed in accordance with the laws of the State of New York without regard to the conflicts of laws provisions thereof. This license sets forth the entire agreement between you and Honeywell and may only be modified by a writing duly executed by the duly authorized representatives of the parties. Safety Advisory WARNING: BE FORE THE MATERIALS CALLED OUT IN THIS PUBLICATION ARE USED, KNOW THE HANDLING, STORAGE AND DISPOSAL PRECAUTIONS RECOMMENDED BY THE MANUFACTURER OR SUPPLIER. FAILURE TO OBEY THE MANUFACTURERS’ OR SUPPLIERS’ RECOMMENDATIONS CAN RESULT IN P ERSONAL INJURY OR DISEASE. This publication describes physical and chemical processes which can make it necessary to use chemicals, solvents, paints, and other commercially available materials. The user of this publication must get the Material Safety Data Sheets (OSHA Form 174 or equivalent) from the manufacturers or suppliers of the materials to be used. The user must know the manufacturer/supplie r data and obey the procedures, recommendations, warnings and cautions set forth for the safe use, handling, storage, and disposal of the materials. Warranty /Liability Advisory WARNING: HONEYWELL ASSUMES NO RESPONSI BILITY FOR ANY HONEYWELL EQUIPMENT WHICH IS N OT MAINTAINED AND/OR REPAIRED IN ACCORDANCE WITH HONEYWELL’S PUBLISHED INSTRUCTIONS AND/OR HONEYWELL’S FAA/SFA R 36 REPAIR AUTHORIZATION. NEITHER DOES HONEYWELL ASSUME RESPONSIBILITY FOR SPECI AL TOOLS AND TEST EQUIPMENT FABRICATED BY COMPAN IES OTHER THAN HONEYWELL. WARNING: INCORRECTLY REPAIRED COMPONENTS CAN AFFECT AIRWORTHINESS OR DECREASE THE LIFE O F THE COMPONENTS. INCORRECTLY FABRICATED SPECIAL TOOLING OR TEST EQUIPMENT CAN RESULT IN DAMAGE TO THE PRODUCT COMPONENTS OR GIVE UNSATISFACTORY RESULTS. 

## Copyright - Notice Copyrig ht 2012 Honeywell International Inc. All rights reserved. Honeywe ll is a registered trademark of Honeywell International Inc. All other marks are owned by their respective companies.

THIS IS T

HE SB FOSI - DATE: 20101101

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Transmittal I nformation ATA Number ADM/ADC/ADAHRS-34-01 (Publication Number D201210000088) Summary This is the INI TIAL release. Revision History This service b ulletin has had no revision(s) as shown in Table 1. Table 1. Revis ion History Revision Number Revision Date 0 6 Nov 2012

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1. P l a n n i n g I nfo rm ati o n A. Effectivity (1) This service bulletin is applicable to the equipment identified below. Refer to Table 2 thru Table 14 for the serial numbers of the equipment. Use the part number of the equipment to find the applicable table. • ADC: – PN 7014700-626 (Table 2) – PN 7014700-914 (Table 3) – PN 7024900-31304 (Table 4) – PN 7030700-71701 (Table 5). – PN 7030700-71703 (Table 6) – PN 7030700-71704 (Table 7). • ADM: – PN 4071400-904 (Table 8) – PN HG1153CA03 (Table 9) – PN HG1153CA04 (Table 10) – PN PG1152BC02 (Table 11). • ADAHRS: – PN 065-00188-5103 (Table 12) – PN 065-00188-5502 (Table 13). • DADC: – PN 4040800-915 (Table 14) Table 2. ADC, PN 7014700-626, Serial Numbers (Embraer 140/145) Serial Number Serial Number Serial Number Serial Number Serial Number 03036850 04097519 05057652 98071938 98122373 Table 3. ADC, PN 7014700-914, Serial Numbers (Cessna Excel) Serial Number 02076454 Table 4. ADC, PN 7024900-31304, Serial Numbers (Cessna XLS) Serial Number 04090901

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Table 5. ADC, PN 7030700-71701, Serial Numbers (Embraer Legacy 600) Serial Number Serial Number Serial Number Serial Number Serial Number 11042731 12012770 12032786 12042792 12042799 11112764 12022775 12032787 12042797 12062805 12012769 12022778 12032789 12042798 12062809 Table 6. ADC, PN 7030700-71703, Serial Numbers (Cessna 560XLS) Serial Number 05060573 Table 7. ADC, PN 7030700-71704, Serial Numbers (Learjet 40/45) Serial Number Serial Number Serial Number Serial Number 03110048 11102761 11112766 12042793 11102760 11102763 11122768 12042794 Table 8. ADM, PN 4071400-904, Serial Numbers (Boeing 777) Serial Number Serial Number Serial Number Serial Number Serial Number Serial Number 35523840 35525377 35526542 35526895 35527348 35529654 35524958 35525451 35526543 35526897 35528065 35532746 35525376 35526308 35526595 35527326 35528640 35532823 Table 9. ADM, PN HG1153CA03, Serial Numbers (Agusta AW139, Dassault F900/F2000) Serial Number Serial Number Serial Number Serial Number Serial Number Serial Number 11104995 11115072 12035321 12045364 12045389 12055441 11115070 12035318 12035329 12045375 12055428 -/-/- Table 10. ADM, PN HG1153CA04, Serial Numbers (Gulfstream G450/550) Serial Number 11115082 Table 11. ADM, PN PG1152BC02, Serial Numbers (Airbus A318/319/320/321/330/340) Serial Number Serial Number Serial Number Serial Number Serial Number Serial Number 1110V633 1112W181 1112W311 1201W448 1201W634 1202W877 1111V887 1112W185 1112W313 1201W459 1201W636 1202W880 1111V956 1112W186 1112W317 1201W463 1201W639 1202W881 1111W021 1112W187 1112W318 1201W470 1201W640 1202W887

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Table 11. ADM, PN PG1152BC02, Serial Numbers (Airbus A318/319/320/321/330/340) (Cont) Serial Number Serial Number Serial Number Serial Number Serial Number Serial Number 1111W022 1112W191 1112W329 1201W474 1201W641 1202W893 1112W040 1112W194 1112W334 1201W475 1201W649 1202W894 1112W044 1112W199 1112W338 1201W483 1201W666 1202W901 1112W062 1112W200 1112W344 1201W486 1201W667 1202W906 1112W072 1112W205 1112W350 1201W489 1201W668 1202W917 1112W079 1112W210 1112W353 1201W506 1201W683 1202W919 1112W082 1112W216 1112W358 1201W511 1201W684 1202W927 1112W083 1112W219 1112W360 1201W517 1201W688 1202W928 1112W086 1112W228 1112W370 1201W518 1201W704 1202W935 1112W087 1112W231 1112W371 1201W530 1201W710 1202W936 1112W089 1112W240 1112W378 1201W534 1201W726 1202W944 1112W097 1112W241 1112W379 1201W536 1201W756 1202W945 1112W098 1112W244 1112W391 1201W546 1201W779 1202W946 1112W103 1112W245 1112W392 1201W557 1201W788 1202W947 111 2W105 111 2W252 111 2W395 120 1W559 120 1W790 1202W950 1112W112 1112W260 1112W399 1201W568 1201W797 1202W953 1112W123 1112W262 1112W400 1201W571 1201W799 1202W994 1112W124 1112W270 1112W401 1201W572 1201W823 1202X008 1112W146 1112W277 1112W410 1201W577 1201W825 1202X064 1112W167 1112W289 1201W425 1201W594 1201W829 1202X067 1112W169 1112W294 1201W432 1201W600 1201W838 -/-/- 1112W176 1112W297 1201W434 1201W622 1201W839 -/-/- 1112W178 1112W299 1201W442 1201W626 1202W843 -/-/- 1112W179 1112W307 1201W443 1201W633 1202W856 -/-/- Table 12. ADAHRS, PN 065-00188-5103, Serial Numbers (Pilatus PC-12/47E, Viking DHC-6-400) Serial Number Serial Number Serial Number Serial Number Serial Number KSG7200-B1187 KSG7200-B1807 KSG7200-B1839 KSG7200-B1874 KSG7200-B1900 KSG7200-B1192 KSG7200-B1810 KSG7200-B1844 KSG7200-B1875 KSG7200-B1901 KSG7200-B1305 KSG7200-B1814 KSG7200-B1849 KSG7200-B1876 KSG7200-B1902 KSG7200-B1337 KSG7200-B1815 KSG7200-B1850 KSG7200-B1879 KSG7200-B1904

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Table 12. ADAHRS, PN 065-00188-5103, Serial Numbers (Pilatus PC-12/47E, Viking DHC-6-400) (Cont) Serial Number Serial Number Serial Number Serial Number Serial Number KSG7200-B1376 KSG7200-B1816 KSG7200-B1851 KSG7200-B1883 KSG7200-B1905 KSG7200-B1379 KSG7200-B1819 KSG7200-B1852 KSG7200-B1884 KSG7200-B1910 KSG7200- B1397 KSG7200- B1822 KSG7200- B1853 KSG7200- B1885 KSG7200- B1912 KSG7200-B1408 KSG7200-B1823 KSG7200-B1854 KSG7200-B1887 KSG7200-B1914 KSG7200-B1653 KSG7200-B1824 KSG7200-B1856 KSG7200-B1889 KSG7200-B1916 KSG7200-B1748 KSG7200-B1826 KSG7200-B1864 KSG7200-B1891 KSG7200-B1921 KSG7200-B1770 KSG7200-B1832 KSG7200-B1865 KSG7200-B1892 KSG7200-B1922 KSG7200-B1800 KSG7200-B1836 KSG7200-B1871 KSG7200-B1894 KSG7200-B1923 KSG7200-B1801 KSG7200-B1837 KSG7200-B1872 KSG7200-B1895 KSG7200-B1929 KSG7200-B1802 KSG7200-B1838 KSG7200-B1873 KSG7200-B1898 KSG7200-B1930 Table 13. ADAHRS, PN 065-00188-5502, Serial Numbers (Bell 429) Serial Number Serial Number Serial Number Serial Number Serial Number KSG7200-B1099 KSG7200-B1806 KSG7200-B1831 KSG7200-B1866 KSG7200-B1903 KSG7200-B1108 KSG7200-B1808 KSG7200-B1840 KSG7200-B1867 KSG7200-B1906 KSG7200-B1194 KSG7200-B1809 KSG7200-B1841 KSG7200-B1868 KSG7200-B1908 KSG7200-B1382 KSG7200-B1811 KSG7200-B1845 KSG7200-B1869 KSG7200-B1909 KSG7200-B1440 KSG7200-B1812 KSG7200-B1846 KSG7200-B1870 KSG7200-B1913 KSG7200-B1452 KSG7200-B1813 KSG7200-B1847 KSG7200-B1878 KSG7200-B1917 KSG7200-B1474 KSG7200-B1818 KSG7200-B1855 KSG7200-B1880 KSG7200-B1924 KSG7200-B1652 KSG7200-B1820 KSG7200-B1858 KSG7200-B1881 KSG7200-B1925 KSG7200-B1660 KSG7200-B1821 KSG7200-B1859 KSG7200-B1882 KSG7200-B1926 KSG7200-B1754 KSG7200-B1825 KSG7200-B1860 KSG7200-B1893 -/-/- KSG7200-B1804 KSG7200-B1827 KSG7200-B1861 KSG7200-B1896 -/-/- KSG7200-B1805 KSG7200-B1830 KSG7200-B1863 KSG7200-B1897 -/-/- Table 14. DADC, PN 4040800-915, Serial Numbers (Boeing 767) Serial Number Serial Number Serial Number 35519835 35525873 35532353 B. Concurrent Requirements (1) No other modification must be done before the test given in this service bulletin.

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C. Reason (1) Problem (a) A potential problem has been found with the pressure sensor(s) used within the equipment listed in Paragraph 1.A.(1) that may impact the accuracy of the pressure sensor measurements over the life of the product. (b) If present, the defect will result in the pressure sensor providing a lower pressure reading than the actual pressure. The magnitude of the error will grow with time and is dependent on the calendar time from the factory calibration and not the operating time. (c) Errors in the pressure sensor measurements may impact other aircraft systems using the pressure measure ments. The primary concern is the impact on the air data system and the associated airspeed and altitude computations. An error in the static pressure measurement will result in a higher indicated altitude than the actual altitude. An error on the static pressure measurement will also result in a higher indicated airspeed than actual airspeed. An error in the pitot pressure sensor will result in a lower indicated airspeed than actual airspeed. (2) Analysis (a) The error in the pressure sensor measurement is a result of a leak within the pressure sensor’s vacuum reference that is compared with the actual applied pressure. (b) The errors in the air data system airspeed computations have the most significant impact at low airspeeds and decrease with increasing airspeed. The altitude computations have the most significant impact at high altitudes (including reduced vertical separation minimum (RVSM) airspace) and increase with altitude. Fundamentally, the airspeed errors decrease with an increase in actual airspeed and the altitude errors grow with an increase in altitude. (3) Purpose (a) The purpose of this service bulletin is to provide operators with specific instructions to permit continued operation of the equipment listed in Paragraph 1.A.(1). These instructions include s pecific pressure error thresholds and associated actions and time frame for subsequent action. These instructions are designed to ensure that equipment in the field that has unacceptable errors is removed from service in the quickest possible manner while minimizing the disruption to operators. (b) Provide a formal list of parts that must be tested to ensure that they are not impacted by the problem specified in Paragraph 1.C.(1).

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(4) Action (a) Operators must perform one of the following actions for the equipment listed in Paragraph 1.A.(1). 1 Perform the tests for the corresponding aircraft type as defined in Paragraph 3 and provide the data back to Honeywell as defined in Paragraph 4.A. These tests have been designed considering that a pressure error greater than 0.7 millibar (mB) presents an unacceptable error for the airspeed and/or altitude computations and requires immediate action. OR 2 Remove the equipment and return it to Honeywell for formal testing and repair (if applicable). OR 3 Perform a complete pitot-static certificati on test every 30 days in accordance with the specific aircraft manufacturer’s maintenance manual. D. Description (1) A summary of the work necessary to do this test is given below. (a) An indicated altitude test is to be performed. (b) A pressure sensor test is to be performed. (c) The pressure error is calculated and used to make a decision about what to do with the equipment. E. Compliance (1) This test is mandatory because it has potential effect on aircraft safety. Do this test as soon as possible. F. Approval (1) This service bulletin includes approved test instructions from the manufacturer. The actions specified by this test are approved by the applicable regulatory agency. (2) The Accomplishment Instructions section of this service bulletin has been approved by the FAA on November 6, 2012. G. Manpower (1) This test can be completed in the approximate time that follows: • 2.0 hour(s) for the labor to do the test of the equipment. H. Weight and Balance (1) None. I. Electrical Load Data (1) Not changed.

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J. Software Accomplishment Summary (1) Not applicable. K. References (1) To find, see, a nd download Honeywell Technical Publications, go to www.myaerospace.com. (2) The applicable Aircraft Maintenance Manual (AMM) can possibly be necessary to complete this test. Refer to the instructions for the specific aircraft type in Paragraph 3. L. Other Publications Affected (1) Not applicable. M. Interchangeability or Intermixability of Parts (1) Not applicab le.

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2. M ate ri a l I nfo rm ati o n A. Material - Price and Availability (1) Speak to Honeywell personnel at the location identified below for the necessary documentatio n, applicable labor prices, and supply times. Honeywell Aerospace Contact Team Telephone: 800-601-3099 (Toll Free U.S.A./Canada) Telephone: 602-365-3099 (International Direct) (2) This test can be done at a Honeywell service center or Honeywell-authorized repair location. There will be no cost to approved customers. B. Industry Support Information (1) The maximum labor hours that will be reimbursed by Honeywell to do this test are given below. Reimbursement will not be more than Honeywell’s applicable reimbursement labor rate or as specified in the agreement or contract. • 2.0 hour(s) for the labor to do the test. (2) Warranty claims should be sent by email to AerospaceWarranty@honeywell.com. C. Material Necessary for Each Component (1) Not applicable. D. Material Necessary for Each Spare (1) Not applicable. E. Reidentified Parts (1) Not applicable. F. Tooling - Price and Availability (1) Only usual aircraft maintenance equipment is necessary to do this service bulletin. An order must not be sent to Honeywell for the necessary equipment as part of this service bulletin.

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3. Acco m p l i s h me nt I n stru ct i o n s A. General Information W

A R N I N G : TO AVOID INJURY TO PERSONNEL, BE AWARE THAT VOLTAGES ARE PRESENT IN THE UNIT AND IN THE TEST EQUIPMENT. VOLTAGES AS LOW AS 28 VOLTS CAN CAUSE SERIOUS INJURY UNDER SOME CONDITIONS. DO NOT BE MISLED BY THE TERM “LOW VOLTAGE.” CA U T I O N : THE EQUIPMENT CONTAINS ELECTROSTATIC DISCHARGE SENSITIVE ITEMS. USE INDUSTRY APPROVED PRECAUTIONS. CA U T I O N : THIS EQUIPMENT CONTAINS MOISTURE-SENSITIVE PARTS. SPECIAL HANDLING IS NECESSARY. (1) Obey the precautions. (2) Obey standard established practices during inspection of the equipment unless specified differently. (3) Do the instructions in the applicable paragraph specified in Table 15. Use the aircraft type to find the correct instructions. If your aircraft type is not identified in Table 15, refer to Paragraph 1.C.(4)(a)2 , Paragraph 1.C.(4)(a)3 , or contact the applicable OEM for FAA approved alternate means of compliance. Table 15. Location of Instructions Aircraft Type Location of Instructions Boeing 777 Paragraph 3.B. Gulfstream G450/550 Paragraph 3.C. Pilatus PC-12/47E Paragraph 3.D. B. Boeing 777 (1) Indicated Altitude Test (a) Obtain barometric pressure reference from airfield (Automatic Terminal Information Service [ATIS]). (b) Obtain aircraft elevation. (c) Set barometric correction in altimeter. (d) Compare indicated altitude to aircraft elevation and ensure indicated altitude is within 75 feet (23 m) of aircraft elevation. If the indicated altitude exceeds 75 feet (23 m) of the aircraft elevation, refer to the applicable OEM AMM procedure for an inaccurate altitude reading. (2) Pressure Sensor Test N OT E : Performed at the maintenance access terminal (MAT) or portable MAT (PMAT) in the flight deck. (a) Ensure the aircraft is stationary and that the pressure sensors are isolated from wind (that is, winds less than 5 knots). Probe covers may be used, but caution should be used (that is, ensure that pitot heat is off). Ensure that power is applied to the ADMs and air data inertial reference unit (ADIRU).

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(b) To record the pressure readings from each pressure sensor (pitot and static), do the following step. Refer to TASK 45-10-00-760-801 in the applicable AMM. 1 On the maintenance access terminal, select ONBOARD MAINTENANCE from the initial MAT or PMAT menu. 2 Select OTHER FUNCTIONS from the CMC system (CMCS) main menu. 3 Select INPUT MONITORING from the other functions menu. 4 Select GENERAL INPUT from the input monitoring main menu. 5 Select CONTINUE. 6 Put the cursor in a direct entry field. 7 Use the MAT or PMAT keyboard to type the signal specifications identified in Table 16 into the direct entry field for each ADM. Table 16. Boeing 777 MAT or PMAT Signal Specifications Signal Source Signal Specification Left pitot ADM L/629/FC L/FE0/0/2-3 Left static ADM L/629/FC L/FE0/1/2-3 Right pitot ADM L/629/FC R/FE0/2/2-3 Right static ADM L/629/FC R/FE0/3/2-3 Center pitot ADM L/629/FC C/FE0/4/2-3 Center static ADM L/629/FC C/FE0/5/2-3
8 Put the cursor in a direct entry field. 9 Select UNITS. 1 0 Select CONTINUE if input/output module (IOM) selection page is displayed. 1 1 Select ENGINEERING. 1 2 Put the cursor in a direct entry field. 1 3 Use the MAT or PMAT keyboard to enter the values from Table 17 for each ENGINEERING UNITS parameter. Table 17. Boeing 777 Engineering Units Parameter Values Parameter Value Lower boundary (LWR BND) -2048 Upper boundary (UPR BND) 2048 Sign bit 31 Most significant bit (MSB) 30

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Table 17. Boeing 777 Engineering Units Parameter Values (Cont) Parameter Value Least significant bit (LSB) 13 Units millibars 1 4 Return to Paragraph 3.B.(2)(b)6 to enter signal specification for another ADM until the last ADM input is complete. (c) To print out the ADM results from the flight deck printer, do the following steps. Refer to TASK 45-10-00-970-801 in the applicable AMM. 1 Select REPORT from the CMCS main menu. 2 Select REPORT PAGE DATA from the report menu. 3 Select SEND adjacent to printer. (d) To determine the action to take for each ADM, do the following steps. 1 Select the pressure sensor reading with the highest pressure reading a nd calculate the difference between the highest pressure reading and each of the other pressure readings: • Pressure error = highest pressure – pressure sensor reading. 2 Compare the pressure error using the thresholds in Table 18. Based on the comparison, take the appropriate action within the time frame designated by Table 18. Table 18. Boeing 777 Pressure Error Action Data Pressure Error (mB) Action Time Frame >0.70 Remove Immediate 0.51 to 0.70 Retest Less than 30 days 0.25 to 0.50 Retest Less than 120 days <0.25 None Not applicable (e) To record the air data inertial reference system (ADIRS) system configuration, do the following steps. Refer to TASK 45-10-00-750-803 in the applicable AMM. 1 From the initial MAT or PMAT menu, select ONBOARD MAINTENANCE. 2 Select LINE MAINTENANCE from the CMCS main menu. 3 Select SYSTEM CONFIGURATION from the line maintenance main menu. 4 Select ATA Chapter 34, ADIRS. 5 Select CONTINUE. (f) Find all six ADMs on the display and read the configuration data (use the scroll bar to see all the data).

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(g) To print out the ADIRS system configuration report from the flight desk printer, do the following. 1 Select REPORT. 2 Select SEND adjacent to printer. (h) Obtain the ADM serial numbers and provide the Data Collection Form in Paragraph 4.A. C. Gulfstream G450/550 (1) Indicated Altitude Test (a) Obtain barometric pressure reference from airfield (ATIS). (b) Obtain aircraft elevation. (c) On the display control panel, ensure that ADM 1 is displayed on pilot’s primary flight display (PFD) and ADM 2 is displayed on copilot’s PFD. (d) Set barometric correction in altimeter. (e) Compare indicated altitude to aircraft e levation and ensure indicated altitude is within 75 feet (23 m) of aircraft elevation. If the indicated altitude exceeds 75 feet (23 m) of the aircraft elevation, refer to the applicable OEM AMM procedure for an inaccurate altitude reading. (f) On display control panel, select pilot’s PFD to display ADM 3. (g) Perform Paragraph 3.C.(1)(d) and Paragraph 3.C.(1)(e) to verify ADM 3 accuracy. (2) Pressure Sensor Test (a) Ensure that the aircraft is stationary and that the pressure sensors are isolated from wind (that is, winds less than 5 knots). Probe covers may be used, but caution should be used (that is, ensure that pitot heat is off). (b) With power applied to the ADMs, record the pressure readings from each pressure sensor (pitot and static). (c) Select central maintenance computer (CMC) on a multifunction display (MFD). (d) Select System Diagnostics. (e) Select 34, Navigation. (f) Select 12, Air Data Application 1. (g) Select Data: ADA parameters (ADA1) (h) Comparison shall be made between the following parameters: • AIR DATA 1: – L STATIC PRESSURE – TOTAL PRESSURE • AIR DATA 2:

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– R STATIC PRESSURE – TOTAL PRESSURE • AIR DATA 3: – AVG STATIC PRESSURE – TOTAL PRESSURE 1 Refer to Figure 1.

Figure 1. (Sheet 1 of 1) Gulfstream G450/550 Pressure Sensor Test (i) Select the pressure sensor reading with the highest pressure reading and calculate the difference between the highest pressure reading and each of the other pressure readings: Pressure error = highest pressure – pressure sensor reading. (j) Compare the pressure error using the thresholds in Table 19. Based on the comparison, take the appropriate action within the time frame designated by Table 19.

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Table 19. Gulfstream G450/550 Pressure Error Action Data Pressure Error (mB) Action Time Frame >0.70 Remove Immediate 0.51 to 0.70 Retest Less than 30 days 0.25 to 0.50 Retest Less than 120 days <0.25 None Not applicable D. Pilatus PC-12/47E (1) Indicated Altitude Test (a) Obtain barometric pressure reference from airfield ATIS. (b) Obtain aircraft elevation. (c) On the display control panel, ensure that ADAHRS Channel A is displayed on pilot’s PFD and ADAHRS Channel B is displayed on copilot’s PFD. (d) Set barometric correction in altimeter. (e) Compare indicated altitude to aircraft e levation and ensure indicated altitude is within 75 feet (23 m) of aircraft elevation. If the indicated altitude exceeds 75 feet (23 m) of the aircraft elevation, refer to the applicable OEM AMM procedure for an inaccurate altitude reading. (2) Pressure Sensor Test (a) Ensure that the aircraft is stationary and that the pressure sensors are isolated from wind (that is, winds less than 5 knots). Probe covers may be used, but caution should be used (that is, ensure that pitot heat is off). Ensure that power is applied to the ADMs and ADIRU. (b) With power applied to the ADAHRS CHANNEL A and CHANNEL B, record the pressure readings from each pressure sensor (total and static). (c) Connect a remote terminal to the aircraft local area network (LAN) and start the CMC/RT program. (d) Select System Diagnostics. (e) Select 34, Navigation. (f) Select Air Data System A. (g) Select Data: AIR PRESSURE PARAMETERS Channel A. (h) Record the STATIC PRESSURE (INHG) and TOTAL PRESSURE (MB). (i) Select TEST COMPLT button on bottom right to return to select a system page. (j) Select Air Data System B. (k) Select Data: AIR PRESSURE PARAMETERS CHANNEL B. (l) Record the STATIC PRESSURE (INHG) and TOTAL PRESSURE (MB) (refer to Figure 2).

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Figure 2. (Sheet 1 of 1) Pilatus PC-12/47E Air Pressure Parameters (m) Convert the static pressure (inHg to mB) using the following conversion factor: • Static Pressure (mB) = Static Pressure (inHg) x 33.863879. (n) Calculate the difference between the average total pressure readings from ADAHRS CHANNEL A and ADAHRS CHANN EL B and the static pressure reading from each ADAHRS Channel: • Pressure error = average total pressure – static pressure sensor reading. (o) Compare the pressure error using the thresholds in Table 20. Based on the comparison, take the appropriate action within the time frame designated by Table 20. Table 20. Pilatus PC-12/47E Pressure Error Action Data Pressure Error (mB) Action Time Frame >0.70 Remove Immediate 0.51 to 0.70 Retest Less than 30 days 0.25 to 0.50 Retest Less than 120 days <0.25 None Not applicable

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4. Ap pe n d ix A. Appendix A, Data Collection Form (1) Collect the data as specified in Table 21 thru Table 24 during the test. Table 21. Operator Contact Information Name Phone Number Email Table 22. Aircraft Information Aircraft Manufacturer’s Serial Number Aircraft Type Date Time (UTC) Location (Airport Identification) Aircraft Elevation (feet) Table 23. Weather Barometer Setting mB/inHg Wind Knots Temperature C/ F Table 24. Test Data Equipment Serial Number 1 Indicated Altitude (feet) for Static Pressure Only Pressure Measurement (mB/inHg)

NOTE: 1. For PC-12/47E, identify Channel A or Channel B. (2) Send the Data Collection Form to one of the locations identified below: Email: AeroTechSupport@honeywell.com Fax: 602-365-1871

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