803-60 AIRCRAFT MAINTENANCE MANUAL

TEMPORARY REVISION

TEMPORARY REVISION TR360-AMM-56

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BOMBARDIER

AEROSPACE

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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 of the 503-60 Maintenance Manual should retain

this Temporary Revision with their CD-ROM,

1. A critical design configuration control limitation (COCel)

definition is introduced.

2. Additional CDCel's have been identified assodated with

preservation of fuel 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 in TR360-AMM-34 (section introduced as a

consequence of completing the system safety review required by

EASA INT/POl!25/12 (and hence SFAR 88)) is re-issued,

NOTE: Record the incorporation of this Temporary Revision on the yellow RECORD OF

TEMPORARY REVISIONS sheet at the front of the Manual.

The technical content of this document is approved under the authority of DOA No. EASA.21 J.068,

Signed ...

Date _ .

EFFECTIVITY: All 5-20-02

TR360-AMM-56

Page 1

Nov 11/05
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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 a fuel tank ignition source for the operational life of the airplane. COCeL's are

mandatory and cannot be changed or deleted without the approval of the European Aviation

Safety Agency (EASA), or the national regulatory authority office that is responsible for the SD3

Type Certificate

A critical fuel tank ignition source prevention feature may exist in the fuel system and its related

installation, or in systems that, if a failure condition were to develop, could interact with the fuel

system in such a way 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 is complied with. Any use of parts, methods, techniques or

practices not contained in the applicable CDCCl requires approval by the European Aviation

Safety Agency (EASA), or the national regulatory authority office that is responsible for the SD3

Type Certificate.

The purpose of the COCCl, is to provide instructions to retain a critical 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 of float switches is not permissible. There

are internal design features which are critical to fuel tank

safety. The unit must be maintained in accordance with the

original equipment manufacturer (OEM) overhaul manual

(section 28A1-65), by appropriately approved maintenance

organisations.

Routing of any additional electrical power/signal cables is not

permitted within six inches of the fuel contents gauging system

(FCGS) co~axial cables, external to the fuel tanks {refer to

28·42·02, Fig. 201 I.

It is not permissible to route any additional electrical power/

signal cables within the fuel tank.

It is not permissible to clip/attach any additional electrical

power/signal cables to the outside surfaces of the fuel tank, or

to fuel pipes.

EFFECTIVITY All 5-20-02

TR360·AMM·56

Page 2

Nov 11/05
SD3-60 AIRCRAFT MAINTENANCE MANUAL

TEMPORARY REViSION

BOMBARDIER

AEROSPACE

ITEM

C FCGS co-axial cable

assemblies

D Fuel tank external

bonding leads

E Fuel tank internal

bonding leads and

cables

2. Notes

NOTE

It is important to assure the physical condition of the 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 of work, 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 [s not permitted;

they must be replaced (refer to 20-09-13).

If disturbed and/or disassembled, the bonding leads on the fuel

vent pipes at the external forward and aft tank interfaces must

undergo a detailed visual inspection (DVI), after re-assembly

(refer to 20-09-05, pb201).

After all internal-to-tank maintenance, it is important to make

sure that both fuel vent system bonding leads in celt 2 of the

forward fuel tank have not been disturbed. These bondjng

leads must not foul 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 or through the tank have

not been disturbed. These cables must not contact adjacent

structure and any loose or broken clips must be replaced (refer

to 20-09-12, pb1).

(1) Any alterations or modifications impacting a COCCl are considered major design

changes and require approval by the European Aviation Safety Agency (EASA) or by the

responsible local regulatory authority under whose jurisdiction the National Type

Certificate is issued_

(2) In cases where the critical jgnition source prevention features of a component are

designated, any test equipment or tooting utilized to repair or overhaul the component

must be in accordance with the CMM.

EFFECTIVITY: AU 5-20-02

TR360-AMM-56

Page 3

Nov 11/05