803-60 AIRCRAFT MAINTENANCE MANUAL TEMPORARY REVISION TEMPORARY REVISION TR360-AMM-56 ~,,-~ 

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FILING INSTRUCTIONS:

REASON FOR ISSUE: This Temporary Revision incorporates TR360-AMM-34. Remove TR360-AMM-34 and insert this TR before Chapter 

### 5-50-00, page 

### 1. CD-ROM holders ofthe 503-60 Maintenance Manual should retain this Temporary Revision with their CD-ROM,
1.A critical design configuration control limitation 

### (COCel) definition isintroduced. 2.Additional 

### CDCel's have been identified 

### assodated with preservation offuel tank system ignition prevention design features when assessed against the EASAIFAA harmonised criteria. 3. Notes related to application of

### eOCeL's are introduced. 4. All other information inTR360-AMM-34 (section introduced as a consequence ofcompleting the system safety review required by EASA INT/POl!25/12 (and hence SFAR 88)) is re-issued,

NOTE: Record the incorporation ofthis Temporary Revision on the yellow RECORD OF TEMPORARY REVISIONS sheet atthe front ofthe Manual.
The technical content ofthis document isapproved under the authority of DOA No. EASA.21 J.068,

Signed

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EFFECTIVITY: All 

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BOMBARDIER AEROSPACE 8D3-60 AIRCRAFT MAINTENANCE MANUAL TEMPORARY REVISION FUEL SYSTEM CRITICAL DESIGN CONFIGURATION CONTROL LIMITATION 

### 1. General COGel's (Critical DeSign Control Configuration Limitations) are Fuel System Airworthiness Limitations that are a means of identifying certain design configuration features intended to preclude afuel tank ignition source forthe operational life ofthe airplane. COCeL's are mandatory and cannot be changed ordeleted without the approval ofthe European Aviation Safety Agency (EASA), orthe national regulatory authority office that is responsible for the SD3 Type Certificate A critical fuel tank ignition source prevention feature may exist inthe fuel system and its related installation, or insystems that, ifafailure condition were to develop, could interact with the fuel system insuch away that an unsafe condition would develop without this limitation. Strict adherence to configuration, methods, techniques and practices as prescribed below is required to ensure the CDCCl iscomplied with. Any use of parts, methods, techniques or practices not contained inthe applicable CDCCl requires approval bythe European Aviation Safety Agency (EASA), orthe national regulatory authority office that is responsible forthe SD3 Type Certificate. The purpose ofthe COCCl, isto provide instructions to retain acritical ignition source prevention feature during configuration change, that may be caused by modifications, repairs, or maintenance actions.



### A

B ITEM Float switch assemblies

Fuel contents gauging NOTE Field maintenance offloat switches is not permissible. There are internal design features which are critical to fuel tank safety. The unit must be maintained inaccordance with the original equipment manufacturer (OEM) overhaul manual (section 28A1-65), by appropriately approved maintenance organisations. Routing ofany additional electrical power/signal cables is not permitted within six inches ofthe fuel contents gauging system (FCGS) co~axial cables, external tothe fuel tanks {refer to 

### 28·42·02, Fig.201

## I. Itisnot permissible to route any additional electrical power/ signal cables within the fuel tank. Itisnot permissible to clip/attach any additional electrical power/signal cables tothe outside surfaces ofthe fuel tank, or tofuel pipes.

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ITEM C FCGS co-axial cable assemblies

D Fuel tank external bonding leads

E Fuel tank internal bonding leads and cables

2. Notes NOTE Itis important to assure the physical condition ofthe harness cables, which the FCGS co-axial cable assemblies are routed within. When performing maintenance or incorporating design change, all cables must be adequately protected against accidental damage, including swart penetration. Cables must be inspected following completion ofwork, to ensure that no damage has occurred and no swarf material has contaminated the harness (refer to 28-42-02, pb201 and 28-42-03, pb201). Repair of FCGS co-axial cable assemblies [snot permitted; they must be replaced (refer to 20-09-13). Ifdisturbed and/or disassembled, the bonding leads on the fuel vent pipes atthe external forward and afttank interfaces must undergo adetailed visual inspection (DVI), after re-assembly (refer to 20-09-05, pb201). After all internal-to-tank maintenance, itis important to make sure that both fuel vent system bonding leads incelt 2ofthe forward fuel tank have not been disturbed. These bondjng leads must notfoul adjacent pjpes/structure and the security of their attachment must be confirmed Additionally make sure that the sensor cables for the FCGS and the float switches, which go into orthrough the tank have not been disturbed. These cables must not contact adjacent structure and any loose or broken clips must be replaced (refer 

### to20-09-12, pb1).

(1) Any alterations or modifications impacting aCOCCl are considered major design changes and require approval bythe European Aviation Safety Agency (EASA) orbythe responsible local regulatory authority under whose jurisdiction the National Type Certificate isissued_ (2) Incases where the critical jgnition source prevention features of acomponent are designated, any test equipment ortooting utilized to repair oroverhaul the component must be in accordance with the CMM.

EFFECTIVITY: AU 

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