MAINTENANCE

MANUAL

FILING INSTRUCTIONS:

REASON FOR ISSUE:

~

503-60

Sherpa

TEMPORARY REVISION

TEMPORARY REVISION TRSD360S-AMM-36

This Temporary Revision incorporates TRSD360S-AMM-15.

Remove TRSD360S-AMM-15 and insert this TR before Chapter

5-50-00, page 1.

Microfiche holders of the 8D3-60 Sherpa Aircraft Maintenance

Manual should insert this Temporary Revision at the front of their

microfiche folder.

1. A critical design configuration control limitation (COCel)

definition is introduced.

2. Additional GOCel's have been identified associated with

preservation of fuel tank system ignition prevention design

features when assessed against the EASAlFAA harmonised

criteria.

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

4. All other information in TRSD360S-AMM-15 (section introduced

as a consequence of completing the system safety review

required by EASA fNT/POU25/12 (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. EASA21J.068.

Signed .

Date

5-20-02 TRSD360S-AMM-36

Page 1 of 3

Jun 27/06
MAINTENANCE

MANUAL

TEMPORARY REVISION

FUEL SYSTEM CRITICAL DESIGN CONFIGURATION CONTROL LIMITATION

1. General

COCeL's (Critical Design Control Configuration Limitations) are Fuel System Ahworthiness

Limitations that are a means of identifying certain design configuration features intended to

preclude a fuel lank ignition source for the operational life of the airplane. COGeL'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 condiUon 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 GOGGl 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 GOCel, 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 NOTE

A Float switch assemblies Field maintenance of the 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 28-41-65), by appropriately approved maintenance

organisations.

B Fuel contents gauging 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, Figure 201).

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.

5-20-02 TRSD360S-AMM-36

Page 2 of3

Jun 27/06
MAINTENANCE

MANUAL

ITEM

C FCGS co-axial cable

assemblies

o Fuel tank external

bonding leads

E Fuel tank internal

bonding leads and

cables

TEMPORARY REVISION

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 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 28-42-02, 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).

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 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 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- t 2, pb201).

2. Notes

(1) Any alterations or modifications impacting a CDCel 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 TRSD360S·AMM·36

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Jun 27/06