FILING INSTRUCTIONS:

REASON FOR ISSUE:

Maintenance

Manual

TEMPORARY REVISION

TEMPORARY REVISION TR330-AMM-36

Insert this TR before Ghapter 5-20-02, page 1.

Microfiche holders of the 503-30 Aircraft Maintenance Manual

should insert this Temporary Revision at the front of their microfiche

folder.

1. A critical design configuration control limitation (GOGCl)

definition is introduced.

2. Additional COGCl's have been identified associated with

preservation of fuel tank system ignition prevention design

features when assessed against the EASNF AA harmonised

cmeria.

3. Notes related to application of GOGGl's are introduced.

4. All other information is introduced as a consequence of

completing the system safety review required by

EASA INT/POU25/12 (and hence SFAR 88).

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 OOA No. EASA.21 J.068.

Signed .

Date .

5-20-02 TR330-AMM-36

Page 1 of3

Jun 06/06
SHORTSEiC

Maintenance CQJoC?Jrij1

Manual ~ e?J~

TEMPORARY REVISION

FUEL SYSTEM CRITICAL DESIGN CONFIGURATION CONTROL LIMITATION

1. General

COCel'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. GOGeL'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 COCCl is complied with. Any use of parts, methods, techniques or

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

Safety Agency (EASA), or the national regulatory authority office that is responsible for the S03

Type Certificate.

The purpose of the GOGGl, 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.

ITEM

A Float switch assemblies

8 Fuel contents gauging

C FCGS ca.-axial cable

assemblies

NOTE

Field maintenance of fioat switches is not permissible. There are

internal design features which are critical to fuel tank safety. The

units must be maintained in accordance with the original equipment

manufacturer (OEM) overhaul manual (section 28--41-65), 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, extemal to the fuel tanks. Refer to

28A-42-02 or 288-42-02, Figure 201 (respective Pre or Post Mod

6738 aircraft).

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.

11is important to assure the physical condition of the hamess 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 of work, to ensure

that no damage has occurred and no swarf material has

contaminated the harness. Refer to 28A-42-02 or 288-42-02, pb201

and 28A-42-03 or 288-42-03, pb201 (respective Pre or Post Mod

6738 aircraft).

Repair of FCGS co-axial cable assemblies is not permitted: they must

be replaced (refer to 20-09-13, pb201).

5-20-02 TR330-AMM-36

Page 2 of 3

Jun 06/06
SHIOI~TS50

~@[Q] Maintenance

Manual

TEMPORARY REVISION

D

E

ITEM

Fuel tank external bonding

leads

Fuel tank internal bonding

leads and cables

NOTE

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 cell 2 of the forward fuei

tank have not been disturbed. These bonding leads musl 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 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, pb201),

2. Notes

(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 ignition source prevention features of a component are

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

must be in accordance with the CMM.

5-20-02 TR330-AMM-36

Page30f3

Jun 0r6