# Bombardier Temporary Revision ALI-0193: No revision named - Rights: © Bombardier Inc. Filed by the FAA in regulations.gov docket FAA-2019-0726; AD 2020-04-20 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. - Document: [Bombardier Temporary Revision ALI-0193](https://openairdocs.org/service-documents/bombardier/tr-ali0193.md) - Title as filed: D84MRM-TR-ALI-0193 - Pages: 12 - PDF: https://openairdocs.org/files/sha256/d3/e8/d3e8a3ab92fca1496983fd5c63e8b7b4830cb67bbdcfdc138c130dbe0b1ab225 - Page: https://openairdocs.org/service-documents/bombardier/tr-ali0193/file/d3e8a3ab92fc ## Text Each page's text from the PDF; open the PDF at a page with #page=N. ### Page 1 TEMPORARY REVISION ALI−0193 REF#: 84ALI_199_R 5−00 CRITICAL DESIGN CONFIGURATION CONTROL LIMITATIONS The contents of this Temporary Revision have been approved by the Chief, Engineering (or designate), National Aircraft Cerification Branch, Transport Canada Civil Aviation Date 24 APR 2018 Signed Philippe Ngassam FILING INSTRUCTIONS: This Temporary Revision (TR) replaces the TR ALI−0182. In the Maintenance Requirements Manual Part 2, remove the TR ALI−0182 from Section 5−00, CRITICAL DESIGN CONFIGURATION CONTROL LIMITATIONS and insert this new Temporary Revision in front of page 1. Record the incorporation of this Temporary Revision on the RECORD OF TEMPORARY REVISIONS sheet at the front of the Manual. Keep this Temporary Revision until the normal revision service puts this information into the Maintenance Requirements Manual. DESCRIPTION: This Temporary Revision (TR) replaces the entire Section 5−00 CRITICAL DESIGN CONFIGURATION CONTROL LIMITATIONS of the MRM part 2, by revising the CDCCL Description item "Fuel tank plumbing lines, self bonding couplings, conductive fittings and metal to metal interface electrical bonding of fuel tank components" in the table as follows: Adds the Fuel tank plumbing lines high resistance isolators applicable to Modsum 4−113969 or Modsum 4−113970. Revised Manual Reference (added Fuel System Limitation Detailed Inspection of the Fuel Tank Plumbing Lines Isolator Assemblies), (revised the functional check description to match the MRM task description). Replaced TR ALI−0182 was issued previously to Section 5−00 CRITICAL DESIGN CONFIGURATION CONTROL LIMITATIONS, to revise the Applicability of the CDCCL Description item for "fuel vent lines Teflon protective sleeve inside the fuel tank" in the table. Applicability (was (Post Modsum 4−113299) or (Post Modsum 4−121195) or (Post Modsum 4−110139) or (Post Modsum 4−113977) or (Post Modsum 4−113978) or (Post Modsum 4−124440), (is now applicable to all). E AIRWORTHINESS LIMITATIONS PSM 1−84−7 − Maintenance Requirements Manual − Part 2 EFFECTIVITY: DHC−8−400 Series 5−00 TR ALI−0193 Page 1 of 12 Apr 24/2018 TEMPORARY REVISION TEMPORARY REVISION ### Page 2 Replaced TR ALI−0180 was issued previously to Section 5−00 CRITICAL DESIGN CONFIGURATION CONTROL LIMITATIONS, to revise the Applicability of the CDCCL Description item for "fuel vent lines Teflon protective sleeve inside the fuel tank" in the table. Applicability (was (Post Modsum 4−113299) or (Post Modsum 4−121195) or (Post Modsum 4−110139)), (is now (Post Modsum 4−113299) or (Post Modsum 4−121195) or (Post Modsum 4−110139) or (Post Modsum 4−113977) or (Post Modsum 4−113978) or (Post Modsum 4−124440)). INTRODUCTION 1. GENERAL This section lists the Critical Design Configuration Control Limitations (CDCCL) that are mandated by the Special Federal Aviat ion Regulation (SFAR) 88. A CDCCL is a limitation requirement to preserve a critical ignition source prevention feature of the fuel system design that is necessary to prevent the occurrence of an unsafe condition identified by the SFAR 88 review. The purpose of the CDCCL is to provide instruct ions to retain the critical ignition source prevention feature during configuration change that may be caused by alterations, repairs or maintenance actions. 2. RULES APPLICABLE TO CRITICAL DESIGN CONFIGURATION CONTROL LIMITATIONS A. The critical ignition source prevention features of the parts or components identified in this list as CDCCLs must be maintai ned in a configuration identical to an approved type design for the aircraft. B. Any repairs or overhauls to the critical ignition source prevention features of the parts or components that are identified i n this list must be in accordance with the design approval holders maintenance manual or with other acceptance repair or overhaul specifications and parts approved by Transport Canada Civil Aviation (TCCA) specifically for that part. C. Any alterations to the critical ignition source prevention features of the parts or components identified in this list are co nsidered major alterations and require approval by TCCA. D. In cases where the critical ignition source prevention features of a component are designated, any test equipment or tooling used to repair or overhaul the component must be in accordance with the Component Maintenance Manual (CMM) or otherwise comply with (1) CAR 571.02 (1) and (2) be substituted and documented as equivalent. E AIRWORTHINESS LIMITATIONS PSM 1−84−7 − Maintenance Requirements Manual − Part 2 EFFECTIVITY: DHC−8−400 Series 5−00 TR ALI−0193 Page 2 of 12 Apr 24/2018 TEMPORARY REVISION TEMPORARY REVISION ### Page 3 3. PAGE FORMAT DESCRIPTION The Critical Design Configuration Control Limitations are presented in the following format: CRITICAL DESIGN CONFIGURATION CONTROL LIMITATIONS CDCCL DESCRIPTION DESIGN FEATURE TO BEMAINTAINED MANUAL REFERENCE APPLICABILITY A B C D A. CDCCL Description − Brief description of the critical ignition−source prevention item(s). B. Design Feature to be Maintained − Brief description of the design feature or technical condition that must be maintained duri ng configuration change (i.e. alterations, repairs or maintenance actions). C. Manual Reference − Area in various publications where maintenance instructions (such as manuals, placards, task cards and sta ndard practices) for critical items can be found. D. Applicability − All is for all aircraft. A Modsum and/or Service Bulletin may be listed to identify the CDCCL as it applies t o the aircraft configuration. E AIRWORTHINESS LIMITATIONS PSM 1−84−7 − Maintenance Requirements Manual − Part 2 EFFECTIVITY: DHC−8−400 Series 5−00 TR ALI−0193 Page 3 of 12 Apr 24/2018 TEMPORARY REVISION TEMPORARY REVISION ### Page 4 4. CDCCL TABLES CRITICAL DESIGN CONFIGURATION CONTROL LIMITATIONS CDCCL DESCRIPTION DESIGN FEATURE TO BEMAINTAINED MANUAL REFERENCE APPLICABILITY Fuel quantity gauging metal overall shield between the fuselage disconnect and the fuel tank penetration. To provide lightning protection, metal overall shield to be free of damage and corrosion. Metal overall shield to be electrically bonded to the aircraft structure at both extremities of the cable harness. PSM 1−84−2 Maintenance Manual, Part 2 Chapter 28 Fuel System Limitation − Detailed Inspection of the Metal Overall Shield on the Fuel Quantity Gauging System Fuel System Limitation − Functional Check of the Fuel Quantity Metal Overall Shield for Electrical Bonding PSM 1−84−4 Illustrated Parts Catalogue, Chapter 24, Section 00 Harness, Electrical − Wing PSM 1−84−2W Wiring Diagram Manual, Chapter 28, Section 40 Fuel Indicating System All E AIRWORTHINESS LIMITATIONS PSM 1−84−7 − Maintenance Requirements Manual − Part 2 EFFECTIVITY: DHC−8−400 Series 5−00 TR ALI−0193 Page 4 of 12 Apr 24/2018 TEMPORARY REVISION TEMPORARY REVISION ### Page 5 CRITICAL DESIGN CONFIGURATION CONTROL LIMITATIONS CDCCL DESCRIPTION DESIGN FEATURE TO BEMAINTAINED MANUAL REFERENCE APPLICABILITY Fuel tank plumbing lines, self bonding couplings, conductive fittings and metal to metal interface electrical bonding of fuel tank components. To provide electrostatic and lightning protection, fuel tank plumbing lines and components must be electrically bonded with conductive fittings and metal to metal conductive finishes. PSM 1−84−2 Maintenance Manual, Part 2 Chapter 28, Section 12 Vents, Section 21 Engine Fuel Feed, Section 23 Fuel Transfer, Section 24 Refuel/Defuel, Section 40 Indication Fuel System Limitation − Detailed Inspection of the Self Bonding Couplings Inside the Fuel Tank Fuel System Limitation − Detailed Inspection of the Fuel Tank Plumbing Lines Isolator Assemblies Fuel System Limitation − Functional Check of the Fuel Tank Components and Plumbing Lines for Electrical Bonding PSM 1−84−4 Illustrated Parts Catalogue, Chapter 28, Section 11 Fuel System, Section 12 Fuel Vents, Section 21 Engine Fuel Feed, Section 23 Fuel Transfer, Section 24 Refuel/Defuel, Section 40 Indicating For non−APU lines, couplings and fittings: Modsum 4−126330 or Modsum 4−126330 and Modsum 4−126537 or Modsum 4−126336 Fuel tank plumbing lines high resistance isolators. Modsum 4−113969 or Modsum 4−113970 E AIRWORTHINESS LIMITATIONS PSM 1−84−7 − Maintenance Requirements Manual − Part 2 EFFECTIVITY: DHC−8−400 Series 5−00 TR ALI−0193 Page 5 of 12 Apr 24/2018 TEMPORARY REVISION TEMPORARY REVISION ### Page 6 CRITICAL DESIGN CONFIGURATION CONTROL LIMITATIONS CDCCL DESCRIPTION DESIGN FEATURE TO BEMAINTAINED MANUAL REFERENCE APPLICABILITY APU fuel tank plumbing lines, self bonding couplings, conductive fittings and metal to metal interface electrical bonding of fuel tank components. To provide electrostatic and lightning protection, fuel tank plumbing lines and components must be electrically bonded with conductive fittings and metal to metal conductive finishes. PSM 1−84−2 Maintenance Manual, Part 2 Section 22 APU Fuel Feed Fuel System Limitation − Detailed Inspection of the Self Bonding Couplings Inside the Fuel Tank Fuel System Limitation − Functional Check of the Self Bonding Couplings, Conductive Fittings and Fuel Tank Components for Electrical Bonding PSM 1−84−4 Illustrated Parts Catalogue, Section 22 APU Fuel System For APU lines, couplings and fittings: Modsum 4−901425 or Modsum 4−901423 Sealant around fuel tank access panel anchor nuts (Sta. YW42.000 to YW191.200). To provide lightning protection, sealant covering base of anchor nuts and attachment rivets to be intact. PSM 1−84−2 Maintenance Manual, Part 2 Chapter 51, Section 23 Sealant Fuel System Limitation − Detailed Inspection of the Sealant Around the Anchor Nuts at Access Panels, Sta. YW42.000 to YW191.200 PSM 1−84−3 Structural Repair Manual Chapter 57, Section 25 Main Fuel Tanks All E AIRWORTHINESS LIMITATIONS PSM 1−84−7 − Maintenance Requirements Manual − Part 2 EFFECTIVITY: DHC−8−400 Series 5−00 TR ALI−0193 Page 6 of 12 Apr 24/2018 TEMPORARY REVISION TEMPORARY REVISION ### Page 7 CRITICAL DESIGN CONFIGURATION CONTROL LIMITATIONS CDCCL DESCRIPTION DESIGN FEATURE TO BEMAINTAINED MANUAL REFERENCE APPLICABILITY Fuel tank access panel to wing skin mating surfaces and access panel gasket (Sta. YW191.200 to YW425.019). To provide lightning protection, specified interfaces of the wing skin and fuel access cover to be finished with chemical conversion coating for electrical bonding (no other finishes permitted), and an insulating gasket installed on the access panel. PSM 1−84−3 Structural Repair Manual Chapter 57, Section 25 Main Fuel Tanks Fuel System Limitation − Detailed Inspection of the Access Panel to Wing Skin Mating Surfaces and Access Panel Gasket, Sta. YW191.200 to YW425.019 All Fuel low level float switch wire harness inside the fuel tank. To prevent fretting and to maintain wire integrity, specified segments of the fuel low level float switch wire harness to be contained within the protective sleeve and wire harness supports. PSM 1−84−2 Maintenance Manual, Part 2, Chapter 28, Section 40 Switch, Float Fuel System Limitation − Detailed Inspection of the Low Level Float Switch Harness Inside the Fuel Tank Modsum 4−126370 or Modsum 4−126336 E AIRWORTHINESS LIMITATIONS PSM 1−84−7 − Maintenance Requirements Manual − Part 2 EFFECTIVITY: DHC−8−400 Series 5−00 TR ALI−0193 Page 7 of 12 Apr 24/2018 TEMPORARY REVISION TEMPORARY REVISION ### Page 8 CRITICAL DESIGN CONFIGURATION CONTROL LIMITATIONS CDCCL DESCRIPTION DESIGN FEATURE TO BEMAINTAINED MANUAL REFERENCE APPLICABILITY Fuel tank water drain valve metal to metal interface and dome nut. To provide lightning protection, specified interfaces of the drain valve and the wing skin to be finished with chemical conversion coating for electrical bonding (no other finishes permitted), and the drain valve to be installed with an internal non−metallic dome nut. PSM 1−84−2 Maintenance Manual, Part 2, Chapter 28, Section 11 Fuel Tanks Fuel System Limitation − Detailed Inspection of the Dome Nut on the Fuel Tank Water Drain Valve Fuel System Limitation − Functional Check of the Fuel Tank Water Drain Valve For Electrical Bonding PSM 1−84−4 Illustrated Parts Catalogue, Chapter 28, Section 11 Fuel System All Fuel vent lines Teflon protective sleeve inside the fuel tank. To maintain electrical isolation of the aircraft vent line from aircraft structure, the fuel vent line Teflon protective sleeves to be intact and free of damage. PSM 1−84−2 Maintenance Manual, Part 2, Chapter 28, Section 12 Vents Fuel System Limitation − Detailed Inspection of the Teflon Sleeve on the Fuel Tank Vent Line PSM 1−84−4 Illustrated Parts Catalogue, Chapter 28, Section 12 Fuel Vents All E AIRWORTHINESS LIMITATIONS PSM 1−84−7 − Maintenance Requirements Manual − Part 2 EFFECTIVITY: DHC−8−400 Series 5−00 TR ALI−0193 Page 8 of 12 Apr 24/2018 TEMPORARY REVISION TEMPORARY REVISION ### Page 9 CRITICAL DESIGN CONFIGURATION CONTROL LIMITATIONS CDCCL DESCRIPTION DESIGN FEATURE TO BEMAINTAINED MANUAL REFERENCE APPLICABILITY Fuel quantity wire harness in the center fuselage and the high level sensor wire harness in the center fuselage and along the rear spar. To prevent ignition source, both the fuel quantity wiring harness and the high level sensor wire harness to be contained within protective sleeving and segregated from other aircraft wiring. PSM 1−84−2 Maintenance Manual, Part 2, Chapter 05 EWIS − Detailed Inspection of the W12 and W13 Harnesses Under the Cabin Floor, Between the Side wall and the Fuel Quantity Computer, Sta. X371.15 EWIS − Detailed Inspection of the W12 and W13 Harnesses on the Passenger Cabin Sidewall, Sta. X361.00 EWIS − Detailed Inspection of the W12 and W13 Harnesses at the Cabin Roof, Sta. X361.00 PSM 1−84−2W Wiring Diagram Manual, Chapter 28, Section 40 Fuel Indicating System Modsum 4−126366 or Modsum 4−126333 High level sensor wire harness inside the fuel tank. To prevent fretting and to maintain wire integrity, specified segments of the high level sensor wire harness to be contained within protective sleeving and wire harness supports. PSM 1−84−2 Maintenance Manual, Part 2, Chapter 28, Section 24 Sensor, High Level Fuel System Limitation − Detailed Inspection of the High Level Sensor Harness Inside the Fuel Tank Modsum 4−126370 or Modsum 4−126336 E AIRWORTHINESS LIMITATIONS PSM 1−84−7 − Maintenance Requirements Manual − Part 2 EFFECTIVITY: DHC−8−400 Series 5−00 TR ALI−0193 Page 9 of 12 Apr 24/2018 TEMPORARY REVISION TEMPORARY REVISION ### Page 10 CRITICAL DESIGN CONFIGURATION CONTROL LIMITATIONS CDCCL DESCRIPTION DESIGN FEATURE TO BEMAINTAINED MANUAL REFERENCE APPLICABILITY Fuel quantity gauging wire harness inside the fuel tank. To prevent fretting and to maintain wire integrity, specified segments of the fuel quantity gauging wire harness to be contained within protective sleeving and wire harness supports. PSM 1−84−2 Maintenance Manual, Part 2, Chapter 28, Section 40 Indicating Fuel System Limitation − Detailed Inspection of the Fuel Probe Harness Inside the Fuel Tank Modsum 4−126370 or Modsum 4−126336 Fuel tank vent line bracket fillet sealant and dome sealed attachment hard ware, Sta. YW42.000 To provide electrical bonding of vent line to support bracket, sealant covering bracket hardware to be intact. PSM 1−84−2 Maintenance Manual, Part 2, Chapter 28 Fuel System Limitation − Detailed Inspection of the Sealant on the Vent Line Support Bracket and Attachment Hardware, Sta. YW42.000 Modsum 4−126330 or Modsum 4−122242 Wide cut fuel CGSB 3.22 or ASTM−D1655 Jet B or MIL−DTL−5624 JP−4. Only post Modsum 4−113538 (PWC SB 35189) aircraft may use wide cut type fuel. Dispatch with wide cut type fuel is prohibited with an outside air temperature (OAT) or static air temperature (SAT) warmer than −20°C. PSM 1−84−1A Airplane Flight Manual, Section 2.5.2 Fuel Modsum 4−113538 (PWC SB 35189) E AIRWORTHINESS LIMITATIONS PSM 1−84−7 − Maintenance Requirements Manual − Part 2 EFFECTIVITY: DHC−8−400 Series 5−00 TR ALI−0193 Page 10 of 12 Apr 24/2018 TEMPORARY REVISION TEMPORARY REVISION ### Page 11 CRITICAL DESIGN CONFIGURATION CONTROL LIMITATIONS CDCCL DESCRIPTION DESIGN FEATURE TO BEMAINTAINED MANUAL REFERENCE APPLICABILITY Fuel tank lines Teflon protective sleeve inside the fuel tank and isolation of lines from aircraft. To maintain electrical isolation of the aircraft fuel lines from aircraft structure, the fuel line Teflon protective sleeves to be intact and free of damage and ensure minimum fuel line separation from aircraft structure and other fuel lines. PSM 1−84−2 Maintenance Manual, Part 2, Chapter 28 Fuel System Limitation − Detailed Inspection of the Teflon Sleeve on the Fuel Tank Lines and Clearances Between Fuel Lines and Structure PSM 1−84−4 Illustrated Parts Catalogue, Chapter 28 Modsum 4−113643 and Modsum 4−113754 or Modsum 4−113643 and Modsum 4−113745 and Modsum 113754 or Modsum 4−113762 E AIRWORTHINESS LIMITATIONS PSM 1−84−7 − Maintenance Requirements Manual − Part 2 EFFECTIVITY: DHC−8−400 Series 5−00 TR ALI−0193 Page 11 of 12 Apr 24/2018 TEMPORARY REVISION TEMPORARY REVISION ### Page 12 E AIRWORTHINESS LIMITATIONS THIS PAGE INTENTIONALLY LEFT BLANK PSM 1−84−7 − Maintenance Requirements Manual − Part 2 EFFECTIVITY: DHC−8−400 Series 5−00 TR ALI−0193 Page 12 of 12 Apr 24/2018 TEMPORARY REVISION TEMPORARY REVISION --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. 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