FILING INSTRUCTIONS:

REASON FOR ISSUE: 

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# SD3JSh®wlP~ MAINTENANCE MANUAL TEMPORARY REVISION
TEMPORARY REVISION TRSD3S-AMM-37
This Temporary Revision incorporates TRSD3S-AMM-16. Remove TRSD3S-AMM-16 and insert this TR before Chapter 5-50-00, page 1. Microfiche holders ofthe SD3 Sherpa Aircraft Maintenance Manual should insert thisTemporary Revision atthe front oftheir microfiche folder. 1.Acritical design configuration control limitation 

### (COCel) definition is introduced. 2.Additional COCeL's have been identified associated with preselVation offuel tank system ignition prevention design features when assessed against the EASAIFAA harmonised crfteria. 3. Notes related to application of

### COCeL's are introduced. 4. All other information inTRSD3S-AMM-16 (section introduced as aconsequence of completing the system safety review required by EASA INT/POLl25/12 (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.21J.068.

Signed

. Date

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# 5-20-02 TRSD3S-AMM-37 Page 1 of 3 Jun 19/06

# Sik1@rA~

# 5D31SlhKl!!WPiij] MAINTENANCE MANUAL TEMPORARY REVISION FUEL SYSTEM CRITICAL DESIGN CONFIGURATION CONTROL LIMITATION 

### General
GOCeL's (Critical Design Control Configuration Limitations) are Fuel System Airworthiness Limitations that are ameans of identifying certain design configuration features intended to preclude afuel tank ignition source forthe operational life ofthe airplane. COGeL'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 in such 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 COCCl 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 for the S03 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.

ITEM NOTE A Float switch assemblies Field maintenance ofthe float switches is not permissible. There are internal design features which are critical tofuel tank safety, The unit must be maintained in accordance with the original equipment manufacturer (OEM) overhaul manual (section 28-41-65), byappropriately approved maintenance organisations. B Fuel contents gauging 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. Itis not permissible to route any additional electrical power/ signal cables within the fuel tank. Itis not permissible to clip/attach any additional electrical power/signal cables tothe outside surfaces ofthe fuel tank, or to fuel pipes.



# 5-20-02 TRSD35-AMM-37 Page 2of3 

### Jun 19/06ITEM C FCGS co-axial cable assemblies

o Fuel tank external bonding leads

E Fuel tank internal bonding leads and cables 

# SiFi©(n~5 D3JSIh®wPr'~

MAINTENANCE MANUAL TEMPORARY REVISION 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 swarf penetration. Cables must be inspected following completion ofwork, to ensure that no damage has occurred and no swarf matenal has contaminated the harness (refer to 2842-02, pb201 and 28-42-03, pb201). Repair of FCGS co-axial cable assemblies is not permitted; they must be replaced (refer to 20-09-13, pb201). Ifdisturbed and/or disassembled, the bonding leads on the fuel vent pipes atthe external forward and afttank interfaces must undergo adetailed visual inspection (OVI), after re-assembly (refer to 20-09-05, pb201). After all intemal-to-tank maintenance, itis important to make sure that both fuel vent system bonding leads in cell 2ofthe forward fuel tank have not been disturbed. These bonding leads must not foul adjacent pipes/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, pb201).
2. Notes (1) Any alterations or modifications impacting aCOCCl are considered major design changes and require approval bythe European Aviation Safety Agency (EASA) or bythe responsible local regulatory authority under whose jurisdiction the National Type Certificate is issued. (2) In cases where the critical ignition source prevention features of acomponent are designated, any test equipment ortooling utilized to repair or overhaul the component must be in accordance with the CMM.



# 5-20-02 TRSD3S-AMM-37 Page 3of 3 Jun 

### 19/06