# Kidde Aerospace Service Bulletin CFD-26-3: Revision 1 - Rights: © KIDDE TECHNOLOGIES, INC. Filed by the FAA in regulations.gov docket FAA-2022-1491; AD 2023-09-01 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. - Document: [Kidde Aerospace Service Bulletin CFD-26-3](https://openairdocs.org/service-documents/kidde/cfd26-3.md) - Title as filed: SB CFD-26-3_Initial - Pages: 33 - PDF: https://openairdocs.org/files/sha256/ea/79/ea79f0367497832ac69a65ed84ca86ab1a2ce4ab06165d78eb99f404d946dbe4 - Page: https://openairdocs.org/service-documents/kidde/cfd26-3/file/ea79f0367497 ## Text Some pages are OCR from a scan. OCR can misread letters and numbers. Each page's text from the PDF; open the PDF at a page with #page=N. ### Page 1 KIDDE AEROSPACE & DEFENSE SERVICE BULLETIN FIRE PROTECTION – AIRBUS CONTINUOUS FIRE DETECTOR (CFD) – AIRBUS SENSING ELEMENT - FIELD TESTING OF CFD FOR PROPER OPERATION January 13/22 CFD-26-3 523-0832622 Transmittal Sheet Summary This service bulletin provides a bench test procedure for Continuous Fire Detector (CFD) sensing elements to verify proper operation. Failed units will be replaced by Kidde Aerospace and Defense. NOTE: This Service Bulletin is classified under Chapter 26 due to the initial classification of the CFD product line. Airbus classifies the Overheat Detection System (OHDS) as Sensing Elements under Chapter 36. CFD's and OHDS Sensing Elements reference the same product. Service Bulletin Revision History REVISION DATE OF RELEASE Initial Release (IR) January 13, 2022 Subject to the EAR, ECCN 9E991 . The data in this document were developed only to maintain systems and/or parts manufactured by or for Collins Aerospace or approved by Collins Aerospace. The data may not be applicable to any other systems and/or parts, regardless of their apparent similarity to systems and/or parts manufactured by or for Collins Aerospace or approved by Collins Aerospace. Do not rely in any way on data in this document to maintain or otherwise support systems and/or parts that wer e not manufactured by or for Collins Aerospace or approved by Collins Aerospace without evidence that the Federal Aviation Administration or other regulatory agency has determined that the data in this document is valid for such use. Collins Aerospace assumes no liability whatsoever, whether contractual, warranty, tort or otherwise, for unauthorized alteration or alterations not performed in accordance with Collins Aerospace approved procedures. ### Page 2 KIDDE AEROSPACE & DEFENSE SERVICE BULLETIN FIRE PROTECTION – AIRBUS CONTINUOUS FIRE DETECTOR (CFD) – AIRBUS SENSING ELEMENT - FIELD TESTING OF CFD FOR PROPER OPERATION January 13/22 CFD-26-3 523-0832622 U.S. Export Classification: EAR 9E991 Page 1 of 30 1. PLANNING INFORMATION A. Effectivity This Service Bulletin (SB) is applicable for CFD (sensing elements) Units. PART NUMBER APPLICABLE TO DATE CODE PART NUMBER APPLICABLE TO DATE CODE PART NUMBER APPLICABLE TO DATE CODE 04-195006-001 Before A2105 04-90014-9186A Before A2105 04-90014-9268A Before A2105 04-195007-001 Before A2105 04-90014-9187A Before A2105 04-90014-9269A Before A2105 04-90014-9088A Before A2105 04-90014-9190A Before A2105 04-90014-9271A Before A2105 04-90014-9098A Before A2105 04-90014-9195A Before A2105 04-90014-9272A Before A2105 04-90014-9099A Before A2105 04-90014-9196A Before A2105 04-90014-9274A Before A2105 04-90014-9102A Before A2105 04-90014-9197A Before A2105 04-90014-9275A Before A2105 04-90014-9113A Before A2105 04-90014-9198A Before A2105 04-90014-9277A Before A2105 04-90014-9115A Before A2105 04-90014-9200A Before A2105 04-90014-9280A Before A2105 04-90014-9117A Before A2105 04-90014-9202A Before A2105 04-90014-9281A Before A2105 04-90014-9119A Before A2105 04-90014-9203A Before A2105 04-90014-9283A Before A2105 04-90014-9120A Before A2105 04-90014-9204A Before A2105 04-90014-9284A Before A2105 04-90014-9121A Before A2105 04-90014-9208A Before A2105 04-90014-9286A Before A2105 04-90014-9122A Before A2105 04-90014-9209A Before A2105 04-90014-9287A Before A2105 04-90014-9126A Before A2105 04-90014-9211A Before A2105 04-90014-9288A Before A2105 04-90014-9130A Before A2105 04-90014-9212A Before A2105 04-90014-9289A Before A2105 04-90014-9134A Before A2105 04-90014-9213A Before A2105 04-90014-9295A Before A2105 04-90014-9136A Before A2105 04-90014-9215A Before A2105 04-90014-9305A Before A2105 04-90014-9137A Before A2105 04-90014-9216A Before A2105 04-90014-9310A Before A2105 04-90014-9140A Before A2105 04-90014-9217A Before A2105 04-90014-9312A Before A2105 04-90014-9142A Before A2105 04-90014-9218A Before A2105 04-90014-9314A Before A2105 04-90014-9143A Before A2105 04-90014-9228A Before A2105 04-90014-9318A Before A2105 04-90014-9145A Before A2105 04-90014-9234A Before A2105 04-90014-9320A Before A2105 04-90014-9147A Before A2105 04-90014-9236A Before A2105 04-90014-9321A Before A2105 04-90014-9148A Before A2105 04-90014-9237A Before A2105 04-90014-9323A Before A2105 04-90014-9149A Before A2105 04-90014-9238A Before A2105 04-90014-9324A Before A2105 04-90014-9150A Before A2105 04-90014-9239A Before A2105 04-90014-9325A Before A2105 04-90014-9151A Before A2105 04-90014-9240A Before A2105 04-90014-9328A Before A2105 04-90014-9152A Before A2105 04-90014-9241A Before A2105 04-90014-9332A Before A2105 04-90014-9155A Before A2105 04-90014-9242A Before A2105 04-90014-9339A Before A2105 04-90014-9158A Before A2105 04-90014-9243A Before A2105 04-90014-9348A Before A2105 04-90014-9165A Before A2105 04-90014-9244A Before A2105 04-90014-9351A Before A2105 04-90014-9166A Before A2105 04-90014-9245A Before A2105 04-90014-9361A Before A2105 04-90014-9167A Before A2105 04-90014-9246A Before A2105 04-90014-9363A Before A2105 04-90014-9168A Before A2105 04-90014-9248A Before A2105 04-90016-901 Before A2105 04-90014-9169A Before A2105 04-90014-9251A Before A2105 04-90016-902 Before A2105 04-90014-9170A Before A2105 04-90014-9252A Before A2105 1002008-051C Before A2105 04-90014-9171A Before A2105 04-90014-9253A Before A2105 1004008-046D Before A2105 04-90014-9172A Before A2105 04-90014-9254A Before A2105 1005008-046D Before A2105 04-90014-9173A Before A2105 04-90014-9256A Before A2105 1070001-217A00 Before A2105 04-90014-9175A Before A2105 04-90014-9257A Before A2105 1070001-221A00 Before A2105 04-90014-9176A Before A2105 04-90014-9258A Before A2105 1072001-041A00 Before A2105 04-90014-9180A Before A2105 04-90014-9259A Before A2105 1072001-041M00 Before A2105 04-90014-9181A Before A2105 04-90014-9263A Before A2105 1072001-044A00 Before A2105 04-90014-9183A Before A2105 04-90014-9264A Before A2105 1072001-044M00 Before A2105 04-90014-9184A Before A2105 04-90014-9267A Before A2105 1072001-046M00 Before A2105 ### Page 3 KIDDE AEROSPACE & DEFENSE SERVICE BULLETIN FIRE PROTECTION – AIRBUS CONTINUOUS FIRE DETECTOR (CFD) – AIRBUS SENSING ELEMENT - FIELD TESTING OF CFD FOR PROPER OPERATION January 13/22 CFD-26-3 523-0832622 U.S. Export Classification: EAR 9E991 Page 2 of 30 PART NUMBER APPLICABLE TO DATE CODE PART NUMBER APPLICABLE TO DATE CODE PART NUMBER APPLICABLE TO DATE CODE 1072001-055A00 Before A2105 1072001-173A00 Before A2105 1072001-245A51 Before A2105 1072001-059A00 Before A2105 1072001-173A51 Before A2105 1072001-247A00 Before A2105 1072001-072A00 Before A2105 1072001-185A00 Before A2105 1072001-247A51 Before A2105 1072001-075A51 Before A2105 1072001-186A00 Before A2105 1072001-248A00 Before A2105 1072001-078A00 Before A2105 1072001-186A51 Before A2105 1072001-248A51 Before A2105 1072001-080A00 Before A2105 1072001-188A00 Before A2105 1072001-250A95 Before A2105 1072001-080A51 Before A2105 1072001-191A00 Before A2105 1072001-251A00 Before A2105 1072001-086A00 Before A2105 1072001-197A00 Before A2105 1072001-251A51 Before A2105 1072001-086A51 Before A2105 1072001-197A51 Before A2105 1072001-255A00 Before A2105 1072001-087A00 Before A2105 1072001-200A00 Before A2105 1072001-255A51 Before A2105 1072001-087A51 Before A2105 1072001-200A51 Before A2105 1072001-256A00 Before A2105 1072001-090A00 Before A2105 1072001-201A00 Before A2105 1072001-256A51 Before A2105 1072001-090A51 Before A2105 1072001-205A00 Before A2105 1072001-260A95 Before A2105 1072001-091A00 Before A2105 1072001-205A51 Before A2105 1072001-262A00 Before A2105 1072001-091A51 Before A2105 1072001-206A00 Before A2105 1072001-262A51 Before A2105 1072001-097A51 Before A2105 1072001-206A51 Before A2105 1072001-263A95 Before A2105 1072001-105A51 Before A2105 1072001-209A00 Before A2105 1072001-270A00 Before A2105 1072001-121A00 Before A2105 1072001-209A51 Before A2105 1072001-270A51 Before A2105 1072001-121A51 Before A2105 1072001-210A00 Before A2105 1072001-277A95 Before A2105 1072001-126A95 Before A2105 1072001-210A51 Before A2105 1072001-285A00 Before A2105 1072001-129A00 Before A2105 1072001-212A00 Before A2105 1072001-286A95 Before A2105 1072001-129A51 Before A2105 1072001-212A51 Before A2105 1072001-287A95 Before A2105 1072001-131A00 Before A2105 1072001-213A00 Before A2105 1072001-291A00 Before A2105 1072001-131A51 Before A2105 1072001-213A51 Before A2105 1072001-297A00 Before A2105 1072001-134A00 Before A2105 1072001-215A00 Before A2105 1072001-297A51 Before A2105 1072001-134A51 Before A2105 1072001-215A51 Before A2105 1072001-317A95 Before A2105 1072001-136A95 Before A2105 1072001-217A51 Before A2105 1072001-319A00 Before A2105 1072001-137A00 Before A2105 1072001-218A00 Before A2105 1072001-319A51 Before A2105 1072001-140A00 Before A2105 1072001-218A51 Before A2105 1072001-323A00 Before A2105 1072001-140A51 Before A2105 1072001-219A00 Before A2105 1072001-323A51 Before A2105 1072001-142A00 Before A2105 1072001-219A51 Before A2105 1072001-328A00 Before A2105 1072001-149C00 Before A2105 1072001-221A00 Before A2105 1072001-328A51 Before A2105 1072001-149C01 Before A2105 1072001-221A51 Before A2105 1072001-A049-51 Before A2105 1072001-149C51 Before A2105 1072001-222A00 Before A2105 1072001-A051-51 Before A2105 1072001-151A95 Before A2105 1072001-222A51 Before A2105 1072001-A075-51 Before A2105 1072001-152A00 Before A2105 1072001-223A00 Before A2105 1072001-A098-51 Before A2105 1072001-152A51 Before A2105 1072001-223A51 Before A2105 1072001-A100-51 Before A2105 1072001-152C51 Before A2105 1072001-229A00 Before A2105 1072001-A115-51 Before A2105 1072001-156C01 Before A2105 1072001-229A51 Before A2105 1072001-A120-51 Before A2105 1072001-158A95 Before A2105 1072001-230A00 Before A2105 1072001-A123-51 Before A2105 1072001-159A00 Before A2105 1072001-234A00 Before A2105 1072001-A126-51 Before A2105 1072001-161C00 Before A2105 1072001-234A51 Before A2105 1072001-A136-51 Before A2105 1072001-161C01 Before A2105 1072001-238A00 Before A2105 1072001-A139-51 Before A2105 1072001-161C51 Before A2105 1072001-238A51 Before A2105 1072001-A141-51 Before A2105 1072001-162A00 Before A2105 1072001-240A00 Before A2105 1072001-A151-51 Before A2105 1072001-162A51 Before A2105 1072001-240A51 Before A2105 1072001-A154-51 Before A2105 1072001-163A00 Before A2105 1072001-242A95 Before A2105 1072001-A158-51 Before A2105 1072001-163A51 Before A2105 1072001-243A00 Before A2105 1072001-A162-51 Before A2105 1072001-166A00 Before A2105 1072001-243A51 Before A2105 1072001-A168-51 Before A2105 1072001-166A51 Before A2105 1072001-244A95 Before A2105 1072001-A170-51 Before A2105 1072001-168A95 Before A2105 1072001-245A00 Before A2105 1072001-A171-51 Before A2105 ### Page 4 KIDDE AEROSPACE & DEFENSE SERVICE BULLETIN FIRE PROTECTION – AIRBUS CONTINUOUS FIRE DETECTOR (CFD) – AIRBUS SENSING ELEMENT - FIELD TESTING OF CFD FOR PROPER OPERATION January 13/22 CFD-26-3 523-0832622 U.S. Export Classification: EAR 9E991 Page 3 of 30 PART NUMBER APPLICABLE TO DATE CODE PART NUMBER APPLICABLE TO DATE CODE PART NUMBER APPLICABLE TO DATE CODE 1072001-A179-51 Before A2105 35546-2-255 Before A2105 35596-2-310 Before A2105 1072001-A182-51 Before A2105 35546-2-310 Before A2105 35597-2-255 Before A2105 1072001-A183-51 Before A2105 35548-2-255 Before A2105 35597-3-255 Before A2105 1072001-A189-51 Before A2105 35549-2-255 Before A2105 35598-2-255 Before A2105 1072001-A192-51 Before A2105 35551-2-255 Before A2105 35599-2-255 Before A2105 1072001-A195-51 Before A2105 35552-2-255 Before A2105 35599-2-310 Before A2105 1072001-A199-51 Before A2105 35553-2-255 Before A2105 35599-2-310 Before A2105 1072001-A203-51 Before A2105 35554-2-255 Before A2105 35599-3-255 Before A2105 1072001-A215-51 Before A2105 35554-4-255 Before A2105 35600-2-255 Before A2105 1072001-A223-51 Before A2105 35556-2-255 Before A2105 35601-2-255 Before A2105 1072001-A225-51 Before A2105 35557-2-255 Before A2105 35601-2-310 Before A2105 1072001-A233-51 Before A2105 35558-2-255 Before A2105 35602-2-255 Before A2105 1072001-A234-51 Before A2105 35558-2-310 Before A2105 35603-2-255 Before A2105 1072001-A236-51 Before A2105 35560-2-255 Before A2105 35604-2-255 Before A2105 1072001-A237-51 Before A2105 35561-2-255 Before A2105 35605-2-255 Before A2105 1072001-A238-51 Before A2105 35562-2-255 Before A2105 35606-2-255 Before A2105 1072001-A240-51 Before A2105 35563-2-255 Before A2105 35607-2-255 Before A2105 1072001-A241-51 Before A2105 35566-2-255 Before A2105 35609-2-255 Before A2105 1072001-A242-51 Before A2105 35566-2-310 Before A2105 35610-2-255 Before A2105 1072001-A247-51 Before A2105 35567-2-255 Before A2105 35611-2-255 Before A2105 1072001-A250-51 Before A2105 35567-3-255 Before A2105 35611-3-255 Before A2105 1072001-A258-51 Before A2105 35568-2-255 Before A2105 35612-2-255 Before A2105 1072001-A259-51 Before A2105 35568-4-255 Before A2105 35614-2-255 Before A2105 1072001-A260-51 Before A2105 35569-2-255 Before A2105 35615-2-255 Before A2105 1072001-A263-51 Before A2105 35571-2-255 Before A2105 35616-2-255 Before A2105 1072001-A270-51 Before A2105 35572-2-255 Before A2105 35617-2-255 Before A2105 1072001-A286-51 Before A2105 35573-2-255 Before A2105 35618-2-255 Before A2105 1072001-A287-51 Before A2105 35574-2-255 Before A2105 35619-2-255 Before A2105 1072001-A306-51 Before A2105 35575-2-255 Before A2105 35620-2-255 Before A2105 1072001-A308-51 Before A2105 35576-2-255 Before A2105 35621-2-255 Before A2105 1072001-A317-51 Before A2105 35577-2-255 Before A2105 35622-2-255 Before A2105 1072001-A326-51 Before A2105 35579-2-255 Before A2105 35622-4-310 Before A2105 1072001-A342-51 Before A2105 35580-2-255 Before A2105 35623-2-255 Before A2105 1072001-C149-51 Before A2105 35581-2-255 Before A2105 35624-2-255 Before A2105 1072001-C152-51 Before A2105 35582-2-255 Before A2105 35624-2-310 Before A2105 1094006-046 Before A2105 35583-2-255 Before A2105 35625-2-255 Before A2105 1095006-046 Before A2105 35584-2-255 Before A2105 35626-2-255 Before A2105 35518-48-400 Before A2105 35584-3-255 Before A2105 35627-2-255 Before A2105 35522-2-255 Before A2105 35586-2-255 Before A2105 35628-2-255 Before A2105 35523-2-255 Before A2105 35587-2-255 Before A2105 35629-2-255 Before A2105 35524-2-255 Before A2105 35588-2-255 Before A2105 35630-2-255 Before A2105 35525-2-255 Before A2105 35589-2-255 Before A2105 35631-2-255 Before A2105 35526-2-255 Before A2105 35590-2-255 Before A2105 35632-2-255 Before A2105 35527-2-255 Before A2105 35591-2-255 Before A2105 35633-2-255 Before A2105 35528-2-255 Before A2105 35592-2-310 Before A2105 35634-2-255 Before A2105 35532-2-255 Before A2105 35593-2-255 Before A2105 35636-2-255 Before A2105 35532-2-310 Before A2105 35593-3-255 Before A2105 35636-2-310 Before A2105 35535-2-255 Before A2105 35594-2-255 Before A2105 35637-2-310 Before A2105 35535-2-310 Before A2105 35594-2-310 Before A2105 35637-3-255 Before A2105 35537-2-255 Before A2105 35595-2-255 Before A2105 35638-2-255 Before A2105 35545-2-310 Before A2105 35596-2-255 Before A2105 35639-2-255 Before A2105 ### Page 5 KIDDE AEROSPACE & DEFENSE SERVICE BULLETIN FIRE PROTECTION – AIRBUS CONTINUOUS FIRE DETECTOR (CFD) – AIRBUS SENSING ELEMENT - FIELD TESTING OF CFD FOR PROPER OPERATION January 13/22 CFD-26-3 523-0832622 U.S. Export Classification: EAR 9E991 Page 4 of 30 PART NUMBER APPLICABLE TO DATE CODE PART NUMBER APPLICABLE TO DATE CODE PART NUMBER APPLICABLE TO DATE CODE 35640-2-255 Before A2105 35661-2-310 Before A2105 35774-200-255 Before A2105 35641-3-255 Before A2105 35663-2-255 Before A2105 35777-200-255 Before A2105 35642-2-255 Before A2105 35665-2-255 Before A2105 35778-200-255 Before A2105 35643-2-255 Before A2105 35666-3-310 Before A2105 35780-200-255 Before A2105 35647-2-255 Before A2105 35667-2-255 Before A2105 35781-200-255 Before A2105 35650-2-255 Before A2105 35668-2-255 Before A2105 35784-200-255 Before A2105 35654-2-255 Before A2105 35668-2-310 Before A2105 35795-200-255 Before A2105 35655-2-255 Before A2105 35670-2-255 Before A2105 35796-200-255 Before A2105 35658-2-255 Before A2105 35673-2-255 Before A2105 35798-200-255 Before A2105 35658-2-310 Before A2105 35677-2-255 Before A2105 35808-200-255 Before A2105 35659-3-310 Before A2105 35680-2-255 Before A2105 35812-200-255 Before A2105 35660-2-310 Before A2105 35687-2-255 Before A2105 NOTE: Numeric Date Code: AYYWW (YY 2-digit year, WW 2-digit Week) Example A2105 (Date of Manufacture 5 th week of 2021). B. Concurrent Requirement Not applicable. C. Reason (1) Description of Existing Condition (a) CFD sensing elements produced between November 24, 2004 and January 31, 2021 may not properly detect thermal bleed leak events. This specific failure mode is not detectable by Overheat Detection System. (2) Extent Condition Encountered (a) Any CFD sensing elements Part Numbers listed in Section 1.A. may be affected. (3) Expected Benefits of Modification (a) Verification that CFD sensing elements will operate per specification. (4) Safety Intent of Corrective Action (a) Identify inoperable units by testing for functionality. (b) Remove inoperable units from the field. ### Page 6 KIDDE AEROSPACE & DEFENSE SERVICE BULLETIN FIRE PROTECTION – AIRBUS CONTINUOUS FIRE DETECTOR (CFD) – AIRBUS SENSING ELEMENT - FIELD TESTING OF CFD FOR PROPER OPERATION January 13/22 CFD-26-3 523-0832622 U.S. Export Classification: EAR 9E991 Page 5 of 30 (5) Regulatory Action (a) To be determined by the governing civil aviation authority. D. Description Shop test CFD sensing elements for proper operation. Failed units will be replaced Free Of Charge (FOC) by Kidde Aerospace and Defense. E. Compliance Optional - Service Bulletin for convenience or option. Desirable - Service Bulletin to introduce improvements. X Recommended - Service Bulletin recommended to be accomplished to prevent significant operational disruptions. Mandatory - Service Bulletin must be accomplished. NOTE: Service Bulletin compliance is Highly Recommended per ATA-2200 definition. F. Approval (1) The approved design of the CFD sensing element part numbers listed in Section 1.A is in compliance with the requirements of TSO-C11e. This SB allows you to determine if the suspect parts conform to the approved design (2) The inspection procedures described in the SB are reviewed and technically accepted by Airbus to apply to the Airbus fleet affected. This SB does not contain any change information that revises the equipment definition covered by Airbus approved modifications. NOTE: This statement is only valid for PN certified by Airbus, refer to paragraph Effectivity. G. Manpower The total estimated time to accomplish the work in this service bulletin is 0.5 man hours per unit. TASK ESTIMATED HOURS Preparation 0.2 Installation 0.0 Testing 0.3 Total 0.5 ### Page 7 KIDDE AEROSPACE & DEFENSE SERVICE BULLETIN FIRE PROTECTION – AIRBUS CONTINUOUS FIRE DETECTOR (CFD) – AIRBUS SENSING ELEMENT - FIELD TESTING OF CFD FOR PROPER OPERATION January 13/22 CFD-26-3 523-0832622 U.S. Export Classification: EAR 9E991 Page 6 of 30 H. Weight and Balance No change. I. Electrical Load Data No change. J. Software Accomplishment Summary None. K. References (1) Abbreviated Component Main tenance Manual (ACMM) fo r 1070001- XXXXXX, 36-22-16 (2) ACMM for 1072001- XXXXXXX, 36-22-17 (3) ACMM for 1094006- XXXXXX, 1095006- XXX, 04-90014-XXXX, and 04-90016-XXX, 36- 22-05 (4) ACMM for 35518-48- XXX and 35XXX-X-XXX, 26-14-12 L. Other Publications Affected None. M. Interchangeab ility or Intermixability of Parts N/A 2. MATERIAL INFORMATION A. Material - Price and Availability Tooling Kit part number 173948 available. NOTE: Tooling Kit 173948 contains items from tables in Section 2.E. NOTE: Order if test equipment is not available. ### Page 8 KIDDE AEROSPACE & DEFENSE SERVICE BULLETIN FIRE PROTECTION – AIRBUS CONTINUOUS FIRE DETECTOR (CFD) – AIRBUS SENSING ELEMENT - FIELD TESTING OF CFD FOR PROPER OPERATION January 13/22 CFD-26-3 523-0832622 U.S. Export Classification: EAR 9E991 Page 7 of 30 NOTE: The current charge for Collins to perform this service bulletin is $794.60 United States Dollars (USD) and may be subject to future price adjustments. Pricing is only valid through December 31, 2022. B. Industry Support Information (1) The modification materials in this service bulletin may be obtained from: Not Applicable (2) The tooling kit in this service bulletin may be obtained from: Rockwell Collins Rental Exchange 400 Collins Road NE Cedar Rapids, IA 52498-0001 TELEPHONE: 1.800.713.5467 Email: Collinsdispatchprograms@rockwellcollins.com Include the following: Email Subject: CFD NOE Kit Provide FOC PO Power Requirements: 110V or 220V NOTE: Please review the commercially available test equipment required in Section 2.E.(2). Order if test equipment is not available. (3) Warranty For units in and out of warranty, Collins Aerospace will reimburse the cost of this service bulletin or perform this service bulletin at no charge for the materials and labor. NOTE: Warranty claims will be accepted through December 31, 2028. (4) Instructions for Warranty Claims can be found at: https://portal.rockwellcollins.com/web/support-self-service/warranty ### Page 9 KIDDE AEROSPACE & DEFENSE SERVICE BULLETIN FIRE PROTECTION – AIRBUS CONTINUOUS FIRE DETECTOR (CFD) – AIRBUS SENSING ELEMENT - FIELD TESTING OF CFD FOR PROPER OPERATION January 13/22 CFD-26-3 523-0832622 U.S. Export Classification: EAR 9E991 Page 8 of 30 (5) Operators can also forward claims for labor reimbursement to the e-mail: kiddewarranty@collins.com C. List of Components (1) Materials Purchased None. (2) Materials Supplied by Customer PART NUMBER KEY WO RD DESCRIPTION QUANTITY SPECIAL I N S TRUCTION/ DISPOSITION Commercially Available* Marking Material Customer Preference As Required (AR) Locally Sourced * Part is at the customers discretion based on local availability D. Subcomponents to be re-identified CFD sensing element part numbers listed in Section 1.A E. Tooling (1) Materials Purchased for Testing Procedure PART NUMBER KEY WO RD DESCRIPTION QUANTITY SPECIAL I N S TRUCTION/ DISPOSITION Kit 173948 Contains the items below as well as items in the Table from Section 2.E.(2) 1146006-0254-00 Connecting Cable 100in, Gold, Pin Connector 2 N/A 1148006-0254-00 Connecting Cable 100in, Gold, Socket Connector 2 N/A 476232 Shell and Insert Assy Gold 20 Contact Socket -Capable receiving 0.06 inch (1.52 mm) diameter contact pin 349457 Contact Pin Gold 20 Gold Plated 0.06 inch (1.52 mm) diameter ### Page 10 KIDDE AEROSPACE & DEFENSE SERVICE BULLETIN FIRE PROTECTION – AIRBUS CONTINUOUS FIRE DETECTOR (CFD) – AIRBUS SENSING ELEMENT - FIELD TESTING OF CFD FOR PROPER OPERATION January 13/22 CFD-26-3 523-0832622 U.S. Export Classification: EAR 9E991 Page 9 of 30 F. Materials Supplied by Customer for Testing Procedure PART NUMBER KEY WO RD DESCRIPTION QUANTITY RANGE TOLERANCE BK 879B or Equivalent LCR Meter Electronic Test Equipment 1 1 kHz test frequency 0.6-1.0 Vrms test level 0 VDC 0-40 k Ω Z impedance 32-104°F (0- 40 °C) operate temp ±5% Not applicable ±0.02 VDC ±5% Not applicable Steinel HG2320E or Equivalent Heat Gun Heating Gun 1 32-662°F (0-350 °C) (at nozzle) ±10 °F (±5 °C) Steinel 07051 or Equivalent Heat Gun Shield Heat Shield 1 N/A N/A HH501BJK or Fluke 289 or Equivalent Digital Multimeter (DMM) or Digital Temperature Meter (DTM) Measures Temperature 1 Type K input 32- 1100°F (0-594°C) 32-104°F (0-40 °C ) operate temp ±4°F (±2.2°C) or 0.75% (whichever is greater) Not applicable KMQSS-062U-12 or Equivalent Thermal Couple Measures Temperature 1 Type K input 32-1100°F (0 -594°C) or greater ±4°F (±2.2°C) or 0.75% (whichever is greater) 4TM11 or Equivalent Stopwatch Stopwatch Time 1 2 minutes (min) 1 second resolution (±5 secs over range) G. Special Tools None. 3. ACCOMPLISHMENT INSTRUCTIONS NOTE: Some steps in the accomplishment instructions are identified as Required for Compliance (RC). If this service bulletin is mandated by an airworthiness directive (AD), the steps identified as RC must be done to comply with the AD. Steps not identified with RC are recommended and may be deviated from; done as a part of other actions; or done with accepted methods different from those given in SB if the RC steps can be done and the airplane returned to a serviceable condition. ### Page 11 KIDDE AEROSPACE & DEFENSE SERVICE BULLETIN FIRE PROTECTION – AIRBUS CONTINUOUS FIRE DETECTOR (CFD) – AIRBUS SENSING ELEMENT - FIELD TESTING OF CFD FOR PROPER OPERATION January 13/22 CFD-26-3 523-0832622 U.S. Export Classification: EAR 9E991 Page 10 of 30 A. General (1) RC - Test Environment Testing may be performed at a room temperature between 55°F (12.8°C) and 85°F (29.4°C), and relative humidity not exceeding 90%. Test area must be free from flammable vapors. Work surface used for bench top testing must be made from non-flammable and non-conductive materials. WARNING: Hot air tool can produce up to 1300°F (795°C) of flameless heat at the nozzle. Do not direct airstream at clothing, hair, or other body parts. If the hot air is set above 392°F (200°C), ensure the surroundings are free of fuel vapors and other ignition sources. WARNING: Do not use near flammable liquids or in an explosive environment (fumes, gases, or dust). Remove materials or debris that may become ignited from work area. WARNING: Always hold tool by plastic enclosure. The metal nozzle requires approximately 20 minutes to cool to where it can be touched. Do not touch nozzle or accessory tips until cool. WARNING: Do not store tool until nozzle has cooled to room temperature. Place tool in a clear area away from combustible materials while cooling. WARNING: Use shield materials around the heated area to prevent damage or fire. CAUTION: Do not cut off airflow by placing nozzle too close to work piece. Keep intake vents clean and clear of obstructions. WARNING: Do not leave tool unattended while running or cooling down. Otherwise risk of fire. CAUTION: Place tool on a level surface when tool is not handheld. Place cord in a position that won’t cause tipping. ### Page 12 (OCR) KIDDE AEROSPACE & DEFENSE SERVICE BULLETIN FIRE PROTECTION - AIRBUS CONTINUOUS FIRE DETECTOR (CFD) - AIRBUS SENSING ELEMENT - FIELD TESTING OF CFD FOR PROPER OPERATION NOTE: Keep a fully charged fire extinguisher nearby. (2) RC - Sensing Elements Heating Procedure The following figures show how to use the heat gun. A heat protection shield must be used and attached to the end of the heat gun outlet. A heat protection shield (Steinel P/N 07051) is normally supplied in the referenced kit. If not available, the following dimensions can be followed to produce an acceptable heat protection shield. The heat protection shield shall be 1.410.2 inch (~3.56 cm 10.5 cm) in width and rolled in a half circle with a radius of approximately 0.75 inches (1.91 cm) for optimum testing. The end of the half circle shall be 1.25-1.5 inches (~3.18 to 3.81 cm) away from the heat gun outlet as shown in Figure 1 and Figure 2. ELEMENT SEN SING HEAT GUN OUTLET HEAT PROTECTION SHIELD AIRFLOW -1.00 to 1.25 INCH- RADIUS APPROX (2.54 TO 3.18 cm) 0.75 INCH (1.91 cm) - 1.25 to 1.5 INCH (3.18 TO 3.81 cm) Figure 1: Heat Protection Shield Side View OFF-AXIS THERMOCOUPLE LOCATION TC TIP PLACED 0.33 INCH (0.85 cm) FROM CENTERUNE HEAT GUN OUTLET 1.2 TO 1.6 INCH _ HEAT PROTECTION AIRFLOW (3.06 TO 4.06 cm) SENSING ELEMENT TC TIP ON CENTERLINE OF HEAT FLANGE CENTER THERMOCOUPLE LOCATION •1.00 to 1.25 INCH (2.54 TO 3.18 cm) Figure 2: Heat gun with heat protection shield top down view January 13/22 CFD-26-3 523-0832622 U.S. Export Classification: EAR 9E991 Page 11 of 30 ### Page 13 KIDDE AEROSPACE & DEFENSE SERVICE BULLETIN FIRE PROTECTION – AIRBUS CONTINUOUS FIRE DETECTOR(CFD)– AIRBUS SENSING ELEMENT - FIELD TESTING OF CFD FOR PROPER OPERATION January 13/22 CFD-26-3 523-0832622 U.S. Export Classification: EAR 9E991 Page 12 of 30 If a curved heat protection shield is not available place a flat heat protection shield (i.e. aluminum plate) behind the sensing element being heated and hold the heat gun 1.00 to 1.25 inch (2.54 to 3.18 cm) from the sensing element as shown in Figure 3. Figure 3: Heat gun using heat protection shield side view B. RC - Preparation (1) Heat Gun Temperature Verification at sensing element position: NOTE: To ensure that the Heat Gun Temperature is consistent during all testing, this verification procedure must be performed prior to testing the first sensing element of each alarm set point and repeated after every four hours of testing or when the sensing element set point changes or when the ambient conditions in the test location change but not less than once per shift. (a) Install the heat protection shield on the heat gun as shown in Figure 1. (b) Connect the thermocouple to the Digital Mu ltimeter (DMM) or Digital Temperature Meter (DTM) and set the DMM or DTM to measure temperature. (c) Turn on the heat gun and set airflow rate to maximum on the heat gun if the setting is available. ### Page 14 KIDDE AEROSPACE & DEFENSE SERVICE BULLETIN FIRE PROTECTION – AIRBUS CONTINUOUS FIRE DETECTOR (CFD) – AIRBUS SENSING ELEMENT - FIELD TESTING OF CFD FOR PROPER OPERATION January 13/22 CFD-26-3 523-0832622 U.S. Export Classification: EAR 9E991 Page 13 of 30 (d) Place the thermocouple at the center of the heat protection shield, not touching the shield, at the approximate location the sensing element will be placed as shown in Figure 1 and Figure 2. (e) Set the heat gun temperature so that the thermocouple reads the Thermocouple Test Temperature value specified in Table 1 for the correct Salt Type Letter. NOTE: It is recommended that the Heat Gun setting temperature be initially set high enough such to achieve a Thermocouple Test Temperature that uses approximately ½ the allowable temperature tolerance defined in Table 1. NOTE: For Heat Guns with a digital display, the Heat Gun display temperature will typically be higher than the temperature at the thermocouple. NOTE: During Heat Gun Temperature Settings calibration to achieve the Thermocouple Test Temperature, the thermocouple temperature will slightly vary up and down according to the thermal regulation of the Heat Gun. The temperature values recorded should be the average of the observed results. (f) Verify and record that the center thermocouple temperature value is within the Thermocouple Test Temperature value tolerance specified in Table 1. (g) Move and place the thermocouple approximately 0.33 inch (0.85 cm) from the centerline of the heat protection shield left or right at the approximate location the sensing element will be placed as shown in Figure 1 and Figure 2. NOTE: If measuring the 2 nd location right of centerline, route thermocouple from the right. If measuring the 2 nd location left of centerline, route thermocouple from the left. NOTE: The Heat Gun 2 nd or off-axis location may be below the lower limit in the Table 1 as the temperature may reduce near the edges left or right of center test position. ### Page 15 KIDDE AEROSPACE & DEFENSE SERVICE BULLETIN FIRE PROTECTION – AIRBUS CONTINUOUS FIRE DETECTOR (CFD) – AIRBUS SENSING ELEMENT - FIELD TESTING OF CFD FOR PROPER OPERATION January 13/22 CFD-26-3 523-0832622 U.S. Export Classification: EAR 9E991 Page 14 of 30 (h) Record the second or off-axis thermocouple value. (i) Calculate the two (2) point average temperature of the center point and second or off- axis thermocouple readings. EXAMPLE Salt Type Letter Step 6 Center Thermocouple Temperature (T center) Step 2nd Thermocouple Temperature (T 2 nd ) 2 pt Average Thermocouple Test Temperature A 290 °F / 143 °C 260 °F / 127 °C 275 °F / 135 °C FORMULA: 2pt Average Thermocouple Test Temperature = (T center + T 2 nd)/2 = (290 °F + 260 °F)/2 = 275 °F (j) If the above 2 Point (pt) average Thermocouple Test Temperature value is not within the tolerance allowed in Table 1 using a Center and Left off axis position or Center and Right off axis position, attempt steps 4) through 9) trying the opposite side of the tested Center and Left or Right off axis position until the 2 Point (pt) average Thermocouple Test Temperature value is within the tolerance limits. This will mitigate some heat gun variability. If the testing is not successful, replace the heat gun with one with a more uniform output. NOTE: It is recommended this value be near or approximately at the mid-point of the temperature range defined by the tolerance in Table 1. (k) Record the two (2) point average Thermocouple Test Temperature verification temperature under the pre-test remarks Data Sheet in Table 2 (Refer Appendix A) for reference only. (2) For Center Wire Resistance (CWR) Measurements ### Page 16 KIDDE AEROSPACE & DEFENSE SERVICE BULLETIN FIRE PROTECTION – AIRBUS CONTINUOUS FIRE DETECTOR (CFD) – AIRBUS SENSING ELEMENT - FIELD TESTING OF CFD FOR PROPER OPERATION January 13/22 CFD-26-3 523-0832622 U.S. Export Classification: EAR 9E991 Page 15 of 30 NOTE: CWR Measurements must be taken with an LCR meter and not a DMM. There a re Sensing Elem ent DC offset volta ge restrictions tha t a re required to be m a intained as well as electrical connection constraints to prevent Sensing Element polarization damage risk. o The LCR meter shall be configured as follows: ƒ Measurement mode: Resistance (R) ƒ Range: 100 Ω or 200 Ω as applicable o The LCR meter shall be capable of meeting the following requirements: ƒ Frequency: 1 kHz ƒ Bias: 0.6-1.0 Vrms, 0 Vdc offset NOTE: These settings must be set at the meter if configurable or it must be confirmed that the meter is capable of these settings if not configurable. (3) For Salt Core Impedance (SCI) Measurements o The LCR meter shall be configured as follows: ƒ Measurement mode: Impedance (Z) ƒ Heated range: 10 Ω or 10000 Ω as applicable ƒ Room Tem perature Impedance range: 10000 Ω or 10MΩ as applicable o The LCR meter shall be capable of meeting the following requirements: ƒ Frequency: 1 kHz ƒ Bias: 0.6-1.0 Vrms, 0 Vdc offset CAUTION: When you do the test, do not use a meter that applies dc voltage. Do not use insulation resistance "megger" testers or dielectric voltage "hypot" testers. These will damage the sensing element. NOTE: These settings must be set at the meter, if configurable or it must be confirmed that the meter is capable of these settings if not configurable. ### Page 17 KIDDE AEROSPACE & DEFENSE SERVICE BULLETIN FIRE PROTECTION – AIRBUS CONTINUOUS FIRE DETECTOR(CFD)– AIRBUS SENSING ELEMENT - FIELD TESTING OF CFD FOR PROPER OPERATION January 13/22 CFD-26-3 523-0832622 U.S. Export Classification: EAR 9E991 Page 16 of 30 C. RC – Procedure - Bench Top Thermal Test (1) Test locations (a) Refer to Figure 4 below for test locations and test sections: Figure 4. Test Locations for Compartment Overheat (b) For sensing elements longer than 30 inch (76.2 cm) it shall be tested in three (3) locations. Testing shall NOT be performed within 1 inch (2.54 cm) of the connectors: 1) The 1 st location shall be from 2-14 inches (5-35 cm) from the beginning of the sensing element and as close to the end as limits allow. Each location will consist of 3 test points with a 3-4 inch (7.62 to 10.16 cm) center to center spacing between each test point. If the “Heated Impedance” Z value is below the Zeq(limit) for test point 1, test point 2, or test point 3, no additional test points within this test location are required and can be entered directly on the data sheet as the final Zeq(Calc). If the “Heated Impedance” Z value is at or above the Zeq(limit) for all 3 test points, the Zeq(limit) will have to be calculated. 2) The 2 nd location shall be a location between 33% and 67% of the length of the sensing element AND at least 10 inches (25 cm) from the 1 st and 3rd test locations for sensing elements longer than 60 inches (152.4 cm). Each location will consist of 3 test points with a 3-4 inch (7.62 to 10.16 cm) center to center spacing between each test point. If the “Heated Impedance” Z value is below the Zeq(limit) for test point 1, test point 2, or test point 3, no additional test points within this test location are required and can be entered directly on the data sheet as the final Zeq(Calc). If the “Heated Impedance” Z value is at or above the Zeq(limit) for all 3 test points, the Zeq(limit) will have to be calculated. ### Page 18 KIDDE AEROSPACE & DEFENSE SERVICE BULLETIN FIRE PROTECTION – AIRBUS CONTINUOUS FIRE DETECTOR (CFD) – AIRBUS SENSING ELEMENT - FIELD TESTING OF CFD FOR PROPER OPERATION January 13/22 CFD-26-3 523-0832622 U.S. Export Classification: EAR 9E991 Page 17 of 30 3) The 3 rd location shall be from 2-14 inches (5-35 cm) from the opposite end of the sensing element and as close to the end as limits allow. Each location will consist of 3 test points with a 3-4 inch (7.62 to 10.16 cm) center to center spacing between each test point. If the “Heated Impedance” Z value is below the Zeq(limit) for test point 1, test point 2, or test point 3, no additional test points within this test location are required and can be entered directly on the data sheet as the final Zeq(Calc). If the “Heated Impedance” Z value is at or above the Zeq(limit) for all 3 test points, the Zeq(limit) will have to be calculated. (c) If the sensing element is between 14 - 30 inches (35 - 76.2 cm) long it shall be tested in two (2) locations. Testing shall NOT be performed within 1 inch (2.54 cm) of the connectors: 1) The 1 st location shall be from 2-14 inches (5-35 cm) from the beginning of the sensing element and as close to the end as limits allow. Each location will consist of 3 test points with a 3-4 inch (7.62 to 10.16 cm) center to center spacing between each test point. If the “Heated Impedance” Z value is below the Zeq(limit) for test point 1, test point 2, or test point 3, no additional test points within this test location are required and can be entered directly on the data sheet as the final Zeq(Calc). If the “Heated Impedance” Z value is at or above the Zeq(limit) for all 3 test points, the Zeq(limit) will have to be calculated. 2) The 2 nd location shall be from 2-14 inches (5-35 cm) from the end of the sensing element and as close to the end as limits allow. Each location will consist of 3 test points with a 3-4 inch (7.62 to 10.16 cm) center to center spacing between each test point. If the “Heated Impedance” Z value is below the Zeq(limit) for test point 1, test point 2, or test point 3, no additional test points within this test location are required and can be entered directly on the data sheet as the final Zeq(Calc). If the “Heated Impedance” Z value is at or above the Zeq(limit) for all 3 test points, the Zeq(limit) will have to be calculated. (d) Preformed and non-preformed sensing elements less than 14 inches (35 cm) shall be tested in one (1) location and at (1) test point furthermost distance from the connectors. Testing shall NOT be performed within 1 inch (2.54 cm) of the connectors. Avoid aiming the heat gun at any grommets used to attach the sensing element if installed ### Page 19 KIDDE AEROSPACE & DEFENSE SERVICE BULLETIN FIRE PROTECTION – AIRBUS CONTINUOUS FIRE DETECTOR (CFD) – AIRBUS SENSING ELEMENT - FIELD TESTING OF CFD FOR PROPER OPERATION January 13/22 CFD-26-3 523-0832622 U.S. Export Classification: EAR 9E991 Page 18 of 30 on a bracket. In some instances, the heat gun flange must be removed in order to effectively execute the testing of the preformed sensing elements. The preformed sensing elements shall be tested to the thermocouple test temperature identified in Table 1 plus 65°F (36°C). 1) The 1 st and only (middle) location shall be in the middle area farthest from the beginning and end of the sensing element that has a width of approximately 1.5 to 2.0 inches (3.81 to 5.08 cm). (2) Test article preparations (a) Remove the sensing element from packing material ensuring that the packing material is stored in a location where it will be shielded from the output of the heat gun. (b) Uncoil the non-preformed sensing element to ensure access to the necessary start, middle, and end locations required for testing. Minimize bending to ensure easier re- coiling and return to packaging. Ensure sensing elements are left straight and not bent for a minimum of 1 inch (2.54 cm) from rear hex nuts of the sensing element connectors. CAUTION: Do not uncoil/straighten preformed sensing elements. They cannot be easily re-formed without a precision fixture. (c) Mark the test locations using a permanent ink marker. Refer to Section 3.C.(1) Test Locations for instructions on test locations. NOTE: Permanent Marker will not affect sensing element operation. It is not necessary to remove the markings after testing is complete. (d) Select test cable (P/N 1146006-0254-00) {Pin Style} or (1148006-0254-00) {Socket Style}, or test contact pin (P/N 349457), or [test contact pin (P/N 349457) and shell & insert assembly (P/N 476232)], which best mate with the sensing element under test. For sensing elements which are terminated with Lugs, the test lead can be clipped to the lug for the center wire connection and the sensing element sheath for the common connection. ### Page 20 KIDDE AEROSPACE & DEFENSE SERVICE BULLETIN FIRE PROTECTION – AIRBUS CONTINUOUS FIRE DETECTOR (CFD) – AIRBUS SENSING ELEMENT - FIELD TESTING OF CFD FOR PROPER OPERATION January 13/22 CFD-26-3 523-0832622 U.S. Export Classification: EAR 9E991 Page 19 of 30 CAUTION: Use a connection cable or install a test pin in the socket connector to prevent damage to the sensing element connectors. (e) Turn on the LCR meter. If the meter is configurable, set the LCR meter to a test frequency of 1 kHz, DC bias to 0 VDC, signal amplitude to approximately 0.8 ±0.2 Vrms, and measurement mode of “Z”. If t he meter is not configurable, using the meter specification sheet, ensure theses parameters are met on the LCR meter. (f) Connect the LCR meter for the appropriate measurement type as described below: For CWR measurements: 1) Connect the center wire of the connecting cable (P/N 1146006-0254-00) {Pin Style} or (1148006-0254-00) {Socket Style}, or test contact pin (P/N 349457), or [test contact pin (P/N 349457) and shell & insert assembly (P/N 476232)], which best mate with the sensing element under test on one end of the sensing element to one terminal on the LCR meter. 2) Connect the center wire of the connecting cable (P/N 1146006-0254-00) {Pin Style} or (1148006-0254-00) {Socket Style}, or test contact pin (P/N 349457), or [test contact pin (P/N 349457) and shell & insert assembly (P/N 476232)], which best mate with the sensing element under test on the other end of the sensing element to the other terminal on the LCR meter. NOTE: It is expected that the connecting cable impedance is less than 0.25 Ohms. It may be necessary to subtract the connecting cable impedance if the tolerances in Section 2.E.(2) Table are not met. For SCI measurements: 1) Connect the center wire of the connecting cable (P/N 1146006-0254-00) {Pin Style} or (1148006-0254-00) {Socket Style}, or test contact pin (P/N 349457), or [test contact pin (P/N 349457) and shell & insert assembly (P/N 476232)], which best mate with the sensing element under test to the plus or positive terminal on the LCR meter ### Page 21 KIDDE AEROSPACE & DEFENSE SERVICE BULLETIN FIRE PROTECTION – AIRBUS CONTINUOUS FIRE DETECTOR (CFD) – AIRBUS SENSING ELEMENT - FIELD TESTING OF CFD FOR PROPER OPERATION January 13/22 CFD-26-3 523-0832622 U.S. Export Classification: EAR 9E991 Page 20 of 30 2) Connect the negative terminal on the LCR meter to the shield of the connecting cable (P/N 1146006-0254-00) {Pin Style} or (1148006-0254-00) {Socket Style} or the sensing element tube near one connector (away from the area or end being heated). CAUTION: When connecting the cable to the sensing element, support the cable back shell with one hand and the sensing element end with the other, then twist the nut until tight. Do not twist the sensing element or the mating test cable if used. NOTE: If using a test cable, ensure that when the mating cable is connected from pin and/or socket connectors, that the mating cable is held so that it does not rotate while threading and connecting to the sensing element connector. An incremental threading and engagement pushing while holding the connector is required to ensure the mating cable is not twisting and damaging the core cables or mating pin contacts or shell and insert assemblies. Same for disconnecting except in reverse. (3) Test Set Up (a) For CWR measurements: 1) Turn on the LCR meter. 2) Refer to the LCR meter operating manual to set the required measurement test conditions. Typical example would be to set the measurement parameter by selecting or entering on the applicable meter buttons (example “L/C/R/Z”); settin g the measurement frequency by selecting or entering on the applicable meter buttons (example “FREQ”); setting the measurement AC amplitude by selecting or entering on the applicable meter buttons (example “AC”); and setting the measurement DC bias to 0 by selecting or entering on the applicable meter buttons (example “DC”); 3) Set the LCR meter to Measurement parameter mode of “R”. 4) Set the LCR meter measurement frequency to 1 kHz if configurable. If the meter is not configurable, using the meter specification sheet, ensure these parameters are met on the LCR meter. ### Page 22 KIDDE AEROSPACE & DEFENSE SERVICE BULLETIN FIRE PROTECTION – AIRBUS CONTINUOUS FIRE DETECTOR (CFD) – AIRBUS SENSING ELEMENT - FIELD TESTING OF CFD FOR PROPER OPERATION January 13/22 CFD-26-3 523-0832622 U.S. Export Classification: EAR 9E991 Page 21 of 30 5) Set the LCR meter measurement AC amplitude to approximately 0.8 +/- 0.2 Vrms and DC bias or offset to 0 Vdc. If the meter is not configurable, using the meter specification sheet, ensure the LCR meter parameters in Section 2.E.(2) Table are met. 6) Set the measurement range as applicable (1 00Ω or 200Ω) if applicable. 7) Connect the LCR meter to the sensing element start and the sensing element end. NOTE: It is expected that the connecting cable impedance is less than 0.25 Ohms. It may be necessary to subtract the connecting cable impedance if the tolerances in Section 2.E.(2) Table are not met. (b) For SCI measurements: 1) If the meter is configurable, set the LCR meter to a test frequency of 1 kHz, ensure or set DC bias to 0Vdc, AC signal amplitude to approximately 0.8 +/- 0.2 Vrms, and measurement mode of “Z”. If the meter is not configurable, using the meter specification sheet, ensure these parameters are met on the LCR meter. 2) Ensure the LCR meter is connected to the sensing element start/end and the sensing element ground (sensing element tube). CAUTION: When you do the test, do not use a meter that applies dc voltage. Do not use insulation resistance "megger" testers or dielectric voltage "hypot" testers. These will damage the sensing element. (4) Test Procedure (a) Enter the top section information (P/N, S/N, date, temperature, Pre Test Remarks, etc.) and record the results on the applicable Data Sheet in Table 2 (Refer Appendix A). ### Page 23 KIDDE AEROSPACE & DEFENSE SERVICE BULLETIN FIRE PROTECTION – AIRBUS CONTINUOUS FIRE DETECTOR (CFD) – AIRBUS SENSING ELEMENT - FIELD TESTING OF CFD FOR PROPER OPERATION January 13/22 CFD-26-3 523-0832622 U.S. Export Classification: EAR 9E991 Page 22 of 30 Table 1: Heat Gun Temperature Settings Salt Type Letter Salt Temp Thermocouple Test Temperature* Family PN Zeq ohms A 255 °F / 124 °C 275 ( -0,+30) °F / 135 (- 0,+17) °C 1070001 148 1072001 148 04-90014 148 ALL OTHERS 127 C 310 °F / 154 °C 332 ( -0,+30) °F / 167 (- 0,+17) °C 1072001 81 ALL OTHERS 68 D 400 °F / 204 °C 427 -0,+30) °F / 219 (-0,+17) °C ALL 97 M 180 °F / 82 °C 196 -0,+30) °F / 91 (-0,+17) °C ALL 128 R 356 °F / 180 °C 381 (-0,+30) °F / 194 (-0,+17) °C ALL 81 * For preformed sensing elements 14” (35 cm) or less, the Thermocouple Test Temperature will be the value stated in Table 1 plus 65 °F (36 °C) Note: The Salt Type is designated by the P/N in one of two ways: The letter in the P/N (i.e. 04-90014-9238A is Salt Type “A”) The end dash number (i.e. 35535-2-310 is Salt Type “C”) P/N’s 04 -90016-901, 04-90016-902, 1094006-046, & 1095006-046 are Salt Type “R” WARNING: If the hot air is set above 392 °F (200 °C), ensure the surroundings are free of fuel vapors and other ignition sources. (b) Measure the Center Wire Resistance and log the value in the Data Sheet Table 2 (Refer Appendix A). (c) Turn on the heat gun and set and verify the temperature at the interval frequency per Section 3.B. using the thermocouple temperature values specified in Table 1. Allow the heat gun to preheat for a minimum of 30 seconds (0.5 minutes) and must reach proper stable test temperature. Ensure that the exhaust of the heat gun is directed in a safe direction. Refer to individual P/N top level drawings to determine salt type . (d) Measure and record the “Room Temperature Impedance” using the LCR meter and SCI Measurement criteria. The value must be ≥ 10 k Ω and < 3M Ω. Log the value on the Data Sheet Table 2 (Refer Appendix A). Refer to Section 3.C.(5).(b). Post Test for values that are out of tolerance. ### Page 24 KIDDE AEROSPACE & DEFENSE SERVICE BULLETIN FIRE PROTECTION – AIRBUS CONTINUOUS FIRE DETECTOR (CFD) – AIRBUS SENSING ELEMENT - FIELD TESTING OF CFD FOR PROPER OPERATION January 13/22 CFD-26-3 523-0832622 U.S. Export Classification: EAR 9E991 Page 23 of 30 NOTE: If the “Room Temperature Impedance” is ≥ 3M Ω check LCR meter lead continuity by shorting leads together and then verify LCR meter to sensing element lead connections and retest if necessary. (e) Heat the 1 st test point in the first test location for a minimum of 60 seconds (1 minute) and no more than 120 seconds (2 minutes). Refer to Section 3.B.(4).(a) Test Locations for instructions on test locations. NOTE: If the “Heated Impedance” is below the Zeq(limit) for five (5) or more seconds prior to 60 seconds, the full 60 seconds wait time is NOT required (can proceed to next test location). NOTE: For optimum test execution it is best to measure the CWR value first, then calculate the Zeq(limit). Perform the individual heated test points and assess if they are below the Zeq(limit). If not, continue heating additional local test points up to three (3) total before advancing to the next test location of the sensing element. Individual Z re adings are not required to be ≤ Zeq(limit). Individual Z readings must be >0.4 Ω and < 3 M Ω (the upper room temperature impedance limit). Repeat the same testing method until all three (3) test locations of the sensing element are tested. Then go back and perform the Zeq(Calc) math calculations to assess pass/fail. (f) Measure and record the “Heated Impedance” using the LCR meter and SCI Measurement criteria. Repeat Steps e) to g) for a total of three (3) times within this test location area (3 readings) with a 3 to 4 inch (7.62 to 10.16 cm) spacing. NOTE: If the “Heated Impedance” Z value is below the Zeq(limit) for test point 1, test point 2, or test point 3, no additional test points within this test location are required and can be entered directly on the data sheet as the final Zeq(Calc). (g) Record each value on the Data Sheet and then use the values to calculate the Zeq(calc) value using the formula below: ### Page 25 KIDDE AEROSPACE & DEFENSE SERVICE BULLETIN FIRE PROTECTION – AIRBUS CONTINUOUS FIRE DETECTOR (CFD) – AIRBUS SENSING ELEMENT - FIELD TESTING OF CFD FOR PROPER OPERATION January 13/22 CFD-26-3 523-0832622 U.S. Export Classification: EAR 9E991 Page 24 of 30 Zeq(Calc) = 1 / {(1/Z 1 + 1/Z2 + 1/Z3)} The Zeq(calc) value must be less than the Zeq(limit) value. Zeq(limit) = Zeq(snsr) from Table 1 for the salt type sensing element + ½ * CWR measured value in ohms and greater than 0.4 Ω. EXAMPLE: Target Limit = 127 Ω CWR = 4 Ω Zeq(Calc) < 127 + 4/2 Zeq(Calc) < 129 Z 1 = 170 Ω Z 2 = 400 Ω Z 3 = 1200 Ω Zeq(Calc) = 1 / {(1/170 + 1/400 + 1/1200)} Zeq(Calc) = 108 Ω Unit Passes NOTE: The calculation is derived to account for differences between this test procedure and the Acceptance Test Procedure (ATP). (h) Log the Zeq(limit) and Zeq(calc) value on the Data Sheet Table 2 (Refer Appendix A). NOTE: The Zeq(Calc) value may be calculated once all 3 test points within a test location are complete. It is not required to calculate Zeq(Calc) before moving on from a single test location. (i) Remove the heat gun from sensing element and let it cool for three (3) minutes or until the “Room Temperature Impedance” is above the limit (see next step). Wipe the sensing element with a damp cloth to restore it to room temperature. 1) If the sensing element does not result in a Zeq value less than the limit with the heat gun applied, then check the connections and repeat Steps c) thru g) and if necessary change the test connection to the sensing element to the end nearest the test location. 2) If the sensing element does not result in a Zeq value less than the limit with the heat gun applied upon retest, then refer to Section 3.C.(5).(b) Post Test for values that are out of tolerance. ### Page 26 KIDDE AEROSPACE & DEFENSE SERVICE BULLETIN FIRE PROTECTION – AIRBUS CONTINUOUS FIRE DETECTOR (CFD) – AIRBUS SENSING ELEMENT - FIELD TESTING OF CFD FOR PROPER OPERATION January 13/22 CFD-26-3 523-0832622 U.S. Export Classification: EAR 9E991 Page 25 of 30 NOTE: If the “Room Temperature Impedance” increases abov e the limit for five (5) or more seconds prior to three (3) minutes with the damp cloth removed, the full three (3) minutes wait time is NOT required (can proceed to next test location). (j) Measure and record the “Room Temperature Impedance” using the LCR me ter and SCI Measurement criteria. The value must be between 10 kΩ and 3MΩ. Log the value on the Data Data Sheet Table 2 (Refer Appendix A). Refer to Section 3.C.(5).(b) Post Test for values that are out of tolerance. (k) Heat the 1 st test point in the second test location for a minimum of 60 seconds (1 minute) and no more than 120 seconds (2 minutes). Refer to Section 3.B.(4).(a) Test Locations for instructions on test locations. NOTE: If the “Heated Impedance” is below the Zeq (limit) for five (5) or more seconds prior to 60 seconds, the full 60 seconds wait time is NOT required (can proceed to next test location). NOTE: For optimum test execution it is best to measure the CWR value first, then calculate the Zeq(limit). Perform the individual heated test points and assess if they are below the Zeq(limit). If not, continue heating additional local test points up to three (3) total before advancing to the next test location of the sensing element. Individual Z readings are not required to be ≤ Zeq(limit). Individual Z readings must be >0.4 Ω and < 3 M Ω (the upper room temperature impedance limit). Repeat the same testing method until all three (3) test locations of the sensing element are tested. Then go back and perform the Zeq(Calc) math calculations to assess pass/fail. (l) Measure and record the “Heated Impedance” using the LCR meter and SCI Measurement criteria. Repeat Steps k) thru m) for a total of three (3) times within this test location area (3 readings) with a 3 to 4 inch (7.62 to 10.16 cm) spacing. ### Page 27 KIDDE AEROSPACE & DEFENSE SERVICE BULLETIN FIRE PROTECTION – AIRBUS CONTINUOUS FIRE DETECTOR (CFD) – AIRBUS SENSING ELEMENT - FIELD TESTING OF CFD FOR PROPER OPERATION January 13/22 CFD-26-3 523-0832622 U.S. Export Classification: EAR 9E991 Page 26 of 30 NOTE: If the “Heated Impedance” Z value is below the Zeq(limit) for test point 1, test point 2, or test point 3, no additional test points within this test location are required and can be entered directly on the data sheet as the final Zeq(Calc). (m) Record each value on the data sheet and then use the values to calculate the Zeq(calc) value using the formula below: Zeq(Calc) = 1 / {(1/Z 1 + 1/Z2 + 1/Z3)} The Zeq(calc) value must be less than the Zeq(limit) value. Zeq(limit) = Zeq(snsr) from Table 2 for the salt type sensing element + ½ * CWR measured value in ohms and greater than 0.4 Ω. (n) Log the Zeq(limit) and Zeq(calc) value on the Data Sheet Table 2 (Refer Appendix A). NOTE: The Zeq(Calc) limit may be calculated once all three (3) test points on a sensing element are complete. It is not required to calculate Zeq(Calc) before moving on from a test location. (o) Remove the heat gun from sensing element and let it cool for at least 3 minutes. A damp cloth can be used to restore sensing element to room temperature. 1) If the sensing element does not result in a Zeq value less than the limit with the heat gun applied, then check the connections and repeat steps j) through m) and if necessary change the test connection to the sensing element to the end nearest the test location. 2) If the sensing element does not result in a Zeq value less than the limit with the heat gun applied upon retest, then refer to Section 3.C.(5).(b) Post Test for values that are out of tolerance. NOTE: If the “Room Temperature Impedance” increases above the limit for five (5) or more seconds prior to three (3) minutes with the damp cloth removed, the full three (3) minutes wait time is NOT required (can proceed to next test location). ### Page 28 KIDDE AEROSPACE & DEFENSE SERVICE BULLETIN FIRE PROTECTION – AIRBUS CONTINUOUS FIRE DETECTOR (CFD) – AIRBUS SENSING ELEMENT - FIELD TESTING OF CFD FOR PROPER OPERATION January 13/22 CFD-26-3 523-0832622 U.S. Export Classification: EAR 9E991 Page 27 of 30 (p) Measure and record the “Room Temperature Impedance” using the LCR meter and SCI Measurement criteria. The value must be ≥ 10 k Ω and < 3 MΩ. Log the value on the Data Sheet Table 2 (Refer Appendix A). Refer to Section 3.C.(5).(b) Post Test for values that are out of tolerance. (q) Heat the 1 st test point in the third test location for a minimum of 60 seconds (1 minute) and no more than 120 seconds (2 minutes). Refer to Section 3.B.(4).(a) Test Locations for instructions on test locations. NOTE: If the “Heated Impedance” is below the Zeq limit for 5 or more seconds prior to 60 seconds, the full 60 seconds wait time is NOT required (can proceed to next test location). NOTE: For optimum test execution it is best to measure the CWR value first, then calculate the Zeq(limit). Perform the individual heated test points and assess if they are below the Zeq(limit). If not, continue heating additional local test points up to three (3) total before advancing to the next test location of the sensing element. Individual Z readings are not required to be ≤ Zeq(limit). Individual Z readings must be >0.4 Ω and < 3 M Ω (the upper room temperature impedance limit). Repeat the same testing method until all three (3) test locations of the sensing element are tested. Then go back and perform the Zeq(Calc) math calculations to assess pass/fail. (r) Measure and record the “Heated Impedance” using the LCR meter and SCI Measurement criteria. Repeat Steps q) thru s) for a total of three (3) times within this test location area (3 readings) with a 3 to 4 (7.62 to 10.16 cm) inch spacing. NOTE: If the “Heated Impedance” Z value is below the Zeq(limit) for test point 1, test point 2, or test point 3, no additional test points within this test location are required and can be entered directly on the data sheet as the final Zeq(Calc). (s) Record each value on the data sheet and then use the values to calculate the Zeq(calc) value using the formula below: ### Page 29 KIDDE AEROSPACE & DEFENSE SERVICE BULLETIN FIRE PROTECTION – AIRBUS CONTINUOUS FIRE DETECTOR (CFD) – AIRBUS SENSING ELEMENT - FIELD TESTING OF CFD FOR PROPER OPERATION January 13/22 CFD-26-3 523-0832622 U.S. Export Classification: EAR 9E991 Page 28 of 30 Zeq = 1 / {(1/Z 1 + 1/Z2 + 1/Z3)} The Zeq(calc) value must be less than the Zeq(limit) value. Zeq(limit) = Zeq(snsr) from Table 1 for the salt type sensing element + ½ * CWR measured value in Ohms and greater than 0.4 Ω. (t) Log the Zeq(limit) and Zeq(calc) value on the Data Sheet Table 2 (Refer Appendix A). NOTE: The Zeq(Calc) limit may be calculated once all 3 test points on a sensing element are complete. It is not required to calculate Zeq(Calc) before moving on from a test location . (u) Remove the heat gun from sensing element and let it cool for at least 3 minutes. A damp cloth can be used to restore sensing element to room temperature. 1) If the sensing element does not result in a Zeq value less than the limit with the heat gun applied, then check the connections and repeat Steps p) thru s) and if necessary change the test connection to the sensing element to the end nearest the test location. 2) If the sensing element does not result in a Zeq value less than the limit with the heat gun applied upon retest, refer to Section 3.C.(5).(b) Post Test for values that are out of tolerance. (v) Measure and record the “Room Temperature Impedance” after testing the third sensing element test location using the LCR meter and SCI Measurement criteria. The value must be ≥ 10 kΩ and < 3 MΩ. Log the value on the Data Sheet Table 2 (Refer Appendix A). Refer to Section 3.C.(5).(b) Post Test for values that are out of tolerance. (w) Run the heat gun on fan only mode for at least five (5) minutes to cool, then turn off the heat gun. (x) Ensure all data is logged on the Data Sheet Table 2 (Refer Appendix A). (5) Post test (a) Verify that all sensing element impedance (Z and Zeq(Calc)) measurements are within the applicable value limits listed in the attached Data Sheet Table 2 (Refer Appendix ### Page 30 KIDDE AEROSPACE & DEFENSE SERVICE BULLETIN FIRE PROTECTION – AIRBUS CONTINUOUS FIRE DETECTOR (CFD) – AIRBUS SENSING ELEMENT - FIELD TESTING OF CFD FOR PROPER OPERATION January 13/22 CFD-26-3 523-0832622 U.S. Export Classification: EAR 9E991 Page 29 of 30 A). Verify that all test result entries are completed, passing results for each sensing element test location or sensing elements tested, and sensing element impedance (Z and Zeq(Calc)) measurements are within applicable value limits. (b) Any unit that does not meet all requirements of Section 3.C. Test Procedure, does not meet the requirements of Federal Aviation Administration (FAA) Technical Standard Order (TSO)-C11e, is not airworthy and cannot be installed on an aircraft. Mark the “Reject” box at the bottom of Table 2 (Refer Appendix A). (c) Ensure that the sensing element has returned to ambient temperature. (d) Remove LCR meter test leads. Inspect the connector both ends of the CFD sensing element for damage. Replace the sensing element connector caps if applicable. (e) Continue to Step 3.D. Identification Procedure. D. RC - Re-identification of Equipment (1) If the element fails any of the tests, continue to Section 3.D.(4). (2) For conforming material, mark one face of the connector hex nut. (3) Carefully recoil the sensing element to the same original coil diameter (approximately 7.5 inch), taking minimum bend radius into consideration (no kinks permitted), free from bends within 1 inch (2.54 cm) of hex nut of sensing element connectors, and replace it in the original packaging material. NOTE: Minimum Bend radius is 1 inch (2.54 cm). (4) Apply a dot to the exterior packaging and insert a copy of the Test Datasheet in the packaging. NOTE: The identification procedure must be accomplished in order for the service bulletin to be complete. If unit fails testing, send unit to address below with Record of Accomplishment form f illed out. Any unit that fails any portion of the test must not be installed/re-installed on an aircraft. ### Page 31 KIDDE AEROSPACE & DEFENSE SERVICE BULLETIN FIRE PROTECTION – AIRBUS CONTINUOUS FIRE DETECTOR (CFD) – AIRBUS SENSING ELEMENT - FIELD TESTING OF CFD FOR PROPER OPERATION January 13/22 CFD-26-3 523-0832622 U.S. Export Classification: EAR 9E991 Page 30 of 30 Collins Aerospace Attn: CFD NOE Return 4200 Airport Dr. Wilson, NC 27896 TELEPHONE: 1.888.265.5467 INTERNATIONAL: 1.319.295.5467 FAX NO: 1.319.295.4941 Email: kiddeCFDreturns@collins.com (5) Record of Accomplishment (a) Record the test results on the form in Appendix A. NOTE: At the discretion of the OEM/customer, send the Record of Accomplishment to: Email: AvionicsSupport@collins.com E. Test Refer to Section 3.C. RC – Procedure - Bench Top Thermal Test F. Close-Up Not Applicable ### Page 32 KIDDE AEROSPACE & DEFENSE SERVICE BULLETIN FIRE PROTECTION – AIRBUS CONTINUOUS FIRE DETECTOR (CFD) – AIRBUS SENSING ELEMENT - FIELD TESTING OF CFD FOR PROPER OPERATION January 13/22 CFD-26-3 523-0832622 U.S. Export Classification: EAR 9E991 Appendix A APPENDIX A ### Page 33 KIDDE AEROSPACE & DEFENSE SERVICE BULLETIN FIRE PROTECTION – AIRBUS CONTINUOUS FIRE DETECTOR (CFD) – AIRBUS SENSING ELEMENT - FIELD TESTING OF CFD FOR PROPER OPERATION January 13/22 CFD-26-3 523-0832622 U.S. Export Classification: EAR 9E991 Appendix A Test Datasheet - Bench Top Thermal Test P/N: Date: ____________ S/N – Date Code: Pre Test Remarks: ____________________________________________________ Test Site Ambient Conditions: Temperature: °F (°C) Pre-test sensing element CWR (30 Ω max) Location (PN, MID, SN) Description Target Z or Zeq(limit) (Ω) Measured Z (Ω) Calculated Zeq(Calc) (Ω) PASS/FAIL (Circle One) Pre-Location 1 Room Temperature Impedance (Z) ≥ 10 k Ω & < 3 M Ω N/A Pass Fail Location 1 ( ) Heated Impedance(Z) / Zeq(Calc) (Zeq(limit) = Zeq(Snsr) from Table 1 + ½*CWRmeas > 0.4 Ω & ≤ Zeq(Snsr) + ½ CWR meas Ω ≤ _______ *Z1= Pass Fail *Z2= *Z3= Pre-Location 2 Room Temperature Impedance (Z) ≥ 10 k Ω & < 3 M Ω N/A Pass Fail Location 2 ( ) Heated Impedance(Z) / Zeq(Calc) (Zeq(limit) = Zeq(Snsr) from Table 1 + ½*CWRmeas > 0.4 Ω & ≤ Zeq(Snsr) + ½ CWR meas Ω ≤ _______ *Z1= Pass Fail *Z2= *Z3= Pre-Location 3 Room Temperature Impedance (Z) ≥ 10 k Ω & < 3 M Ω N/A Pass Fail Location 3 ( ) Heated Impedance(Z) / Zeq(Calc) (Zeq(limit) = Zeq(Snsr) from Table 1 + ½*CWRmeas > 0.4 Ω & ≤ Zeq(Snsr) + ½ CWR meas Ω ≤ _______ *Z1= Pass Fail *Z2= *Z3= Post Test Room Temperature Impedance (Z) ≥ 10 k Ω & < 3 M Ω N/A Pass Fail Sensing Element Performance: Accept [ ] Reject [ ] Test Technicia n: Date: Test Witness: Date: *Individual Z readings are not required to be ≤ Zeq(limit). Individual Z readings must be >0.4 Ω and < 3 M Ω (the upper room temperature impedance limit). Table 2: Test Datasheet - Bench Top Thermal Test --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain, except the copies of manufacturers’ service documents, which belong to their rights holders.