737424-HDK02 i Issue: 4 Date: 01/04/20

MULTIFUNCTION CONTROL PANEL

REPLACEMENT IN B737

TITULO/TITLE:

MAINTENANCE MANUAL SUPPLEMENT

DOCUMENT NR.: 737424-HDK02

EDIC./ISS. 1 2 3 4

FECHA/DT. 14/01/20 10/02/20 18/03/20 01/04/20

NOMBRE/NAME FIRMA/SIGNAT. FECHA/DT.

PREPARED F. GUERRERO 01/04/20

REVISED

A. SÁNCHEZ 01/04/20

APPROVED (CVE)

A. SÁNCHEZ 01/04/20

737424-HDK02 ii Issue: 4 Date: 01/04/20

S4A S.A. posee los derechos de autor de este documento que se entrega confidencialmente, y que no será utilizado con ningún fin distinto de aquel para el que ha sido entregado, no siendo tampoco reproducido en su totalidad o en parte, copiado o transmitido a ninguna persona sin autorización del propietario o del solicitante del trabajo.

S4A copyrights this document, which is delivered in confidence. This document will not be used for any other different purpose than that to which it is intended. This document can not be reproduced by any means without the written authorization of S4A.

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Mail expenses will be reimbursed

LISTA DE DISTRIBUCIÓN/DISTRIBUTION LIST

NAME COMPANY NR. COPIES

INTERNAL: ARCHIVO S4A 1

AWARE: CALIDAD S4A -

EXTERNAL: LOGIC AIR 1

737424-HDK02 iii Issue: 4 Date: 01/04/20

REGISTRO DE EDICIONES DE PAGINAS/PAGE ISSUE REGISTRATION

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PAGINA/PAGE EDICION/ISSUE

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REGISTRO DE CAMBIOS EN EL DOCUMENTO/DOCUMENT CHANGE REGISTRATION

EDIC./REV. FECHA/DATE RAZON DEL CAMBIO/CHANGE REASON

1

2

3

4

14/01/20

10/02/20

18/03/20

01/04/20

EDICIÓN ORIGINAL/ORIGINAL ISSUE CUSTOMER REQUEST (MAJOR MODIFICATION) EASA COMMENTS (MAJOR MODIFICATION) CUSTOMER REQUEST (MINOR MODIFICATION)

737424-HDK02 1 Issue: 4 Date: 01/04/20

TABLE OF CONTENTS

1. OBJECT............................................................................................................................. 2 2. NORMATIVE COMPLIANCE .............................................................................................. 2 3. APPLICABILITY ................................................................................................................. 2 4. APPROVAL........................................................................................................................ 2 5. INSTALLATION DESCRIPTION.......................................................................................... 2 6. SERVICE CENTER ............................................................................................................ 4 7. MAINTENANCE PROGRAM ............................................................................................... 4 8. MAINTENANCE SCHEDULE AND METHODS. ................................................................... 6

8.1. CONTROL PANEL DISPLAY ...................................................................................6 8.2. ELECTRICAL WIRING ..............................................................................................6

9. SPECIAL PROCEDURES ................................................................................................... 7 9.1. ELECTRICAL WIRING DAMAGES ..........................................................................7

10. ACCEPTABLE CORROSION LEVELS .............................................................................. 8 11. AIRWORTHINESS LIMITATIONS ..................................................................................... 8 12. EWIS INSTRUCTIONS ..................................................................................................... 8 13. INSTALLATION/ REMOVAL INSTRUCTIONS ................................................................... 8

13.1. Removal instructions ...............................................................................................8 13.2. Installation instructions ............................................................................................9

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1. OBJECT

The purpose of this document is to describe the actions to be followed in order to ensure continued airworthiness of Boeing 737 aircraft where S4A Service Bulletin

737424-SB001 has been implemented. The stated service bulletin consists on the multifunction control panel

replacement on board Boeing 737 aircraft.

2. NORMATIVE COMPLIANCE

This document shows compliance with next paragraphs of normative CS 25

Amendment 24: 25.1309 a) b) c) e)

25.1529

3. APPLICABILITY

This document is applicable to Boeing 737 aircraft where S4A Service Bulletin 737424-SB001 has been implemented.

4. APPROVAL

The technical content of this document is approved under the authority of DOA nr. EASA21.J.409

5. INSTALLATION DESCRIPTION

The Boeing 737 aircraft was modified installing a SBAS system as per EASA STC number 10043626. The operator has decided to replace the existing control panels (P/N CMA-5025) with a new single control panel Gable (P/N G7321-122). The rest of

the elements of the SBAS system are the same as before the modification. IMPORTANT NOTE: Neither the activation nor the operation of any

equipment is covered by this modification (equipment and connections are only installed as provisions; activation and operation shall be approved separately).

The new display is attached to the Forward Center Pedestal in the location indicated in next figures by means of standard fasteners.

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Figure 1: Location of the control unit in cockpit

Figure 2: Detail of the location in the cockpit panel

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6. SERVICE CENTER

The service center of the equipments comprising this system is:

Gables Engineering Inc. 247 Greco Avenue, Coral Gables, Florida 33146

Tel: (305) 774-4400

Fax: (305) 774-4465 www.gableseng.com

Corporation Logic Air Inc. 91 Gaston Dumoulin

Blainville (Québec) J7C 6B4

CANADA Tel: 579-637-3077

7. MAINTENANCE PROGRAM

It is clearly distinguished between maintenance actions on the new installed items and on the aircraft structure supporting them.

Another paragraph is included describing actions to be taken and procedures to

be followed in the event the aircraft undergoes any damage due to: lightning strike, ground vehicle impact, defective installation of new items, impacts due to maintenance or operation, etc and landing on salty water.

All equipments not requiring any maintenance task are listed, that is to say, they will only be replaced/repaired when it has been checked that the item is out of order (On Condition), and hence, it does not require a check or maintenance task to ensure its

appropriate operation.

Those systems complying with the previous paragraph and, besides, have a BIT (Built in Test) switch, whereby the system operation can be verified, and, therefore, they do not require any check/maintenance task, will also be listed, along with all the

Systems requiring any maintenance task.

Any equipment/component requiring replacement for another one, due to any failure, will be replaced by other of identical P/N, compatible and qualified by the system

manufacturer. Replacements shall be carried out by authorized and properly qualified maintenance personnel exclusively.

All aircraft structural elements where the new installed items are supported or attached are listed in this document. Any element of the supporting structure is listed with its P/N, according to the aircraft

IPC (Illustrated Parts Catalogue). Acceptable corrosion levels, repairable corrosion levels and rejectable corrosion

levels are also mentioned for supporting structure elements.

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Procedures for detection and removal of corrosion, besides that mentioned in the previous paragraph, will be those set up in the aircraft SRM (structural repair manual).

Distinction will be made between mandatory maintenance tasks, as those

stemming from the airworthiness limitation list. If these maintenance tasks are not achieved, the system or supporting structure would decay and, finally, the aircraft safety (on ground or in flight) will be jeopardized and the recommended maintenance tasks,

that if not achieved, would only affect the new installed items and not the aircraft safety.

Mandatory maintenance tasks make up the minimum maintenance supplement for this aircraft model. It is aircraft operator’s or owner’s responsibility to carry out these

maintenance tasks. These tasks are listed highlighted with an asterisk (*). The rest of maintenance tasks comprise the recommended maintenance supplement of the aircraft when operating with this configuration and they intend to help the operator to

successfully perform its missions. These tasks are also listed in this document and are regarded as operator’s guidelines when the aircraft is endowed with this configuration.

Special procedures are listed to be followed if the aircraft undergoes any of the

following incidents:

- Lightning strike. - Defective installation of modification elements

- Accidental impact during maintenance, operation, etc.

These procedures do not imply regular maintenance tasks, but they assess damage levels and actions to be taken and in what particular moment, if any special

situation, previously mentioned, arises.

This document can be reviewed in order to enhance it. Among others, maintenance interval escalation, previously requested by the aircraft operator, can be

achieved. These requests have to be appropriately justified, following a controlled process by S4A, as modification designer, supervised and approved by S4A.

This maintenance supplement is part of the aircraft maintenance program, with the stated configuration, and must be included in it, in order to have a single maintenance program.

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8. MAINTENANCE SCHEDULE AND METHODS.

8.1. CONTROL PANEL DISPLAY

This component does not require a specific maintenance program, except the periodical cleaning of the display, and it shall be repaired or replaced if damaged for any reason.

These parts do not imply any limitation to life of structural supports. Therefore,

these shall be inspected when damage is detected or suspected in order to verify if

damages occur. Summing up, next maintenance characteristics are applicable for control panel

display: Maintenance type: On condition

Inspection interval: If damage is suspected Inspection method: Visual and perform a functional check

Perform periodical cleaning of the element according to following procedure:

1. Access to the MAIN MCDU page of the Gable display.

2. Select CLEAN. With this option, the unit will provide 30 seconds of ‘dead front’ where there are no line selects or any other functions available.

Clean display glass with isopropyl alcohol swipes or equivalent products.

8.2. ELECTRICAL WIRING

Electrical provisions consist in electrical connections between the new control

panel display and the existing elements of the SBAS system. These elements can be considered “On Condition” items and they do not need any specific maintenance program and will be replaced if damaged for any reason or once thy become

unreadable. Summing up, next maintenance characteristics are applicable for electrical

provisions installed: Maintenance type: On Condition

Inspection interval: On condition Inspection method: Visual*

* Perform visual inspection of each harness of the installation, regarding to general state

and fixing of themselves. In case of finding damaged wiring, follow the procedures indicated in paragraph 9.1. of this document.

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9. SPECIAL PROCEDURES

In case of incident, follow the procedures and actions subsequently indicated:

NOTE: All inspections are visual, at the impact area, in order to assess damage level.

INCIDENT ELEMENT TO

BE INSPECTED ACTION TO BE IMPLEMENTED WHEN TO INSPECT?

Lightning strike

The entire Aircraft structure

and all new elements installed

Inspection according to aircraft maintenance manual

Immediately after the aircraft is on ground and

inside the hangar

Defective installation All new items

installed Remove the defective element and

install it back

After removing the element and before re-

installation

Accidental impacts due to operation or maintenance tasks.

Control Panel

Repair according to procedures established by control panel’s manufacturer. If not applicable

maintenance instructions, for not mentioned damages in the manual or if not applicable because of large damage, replace item with another

one of identical part number.

Immediately after the damage has been

caused and the aircraft is on ground and in a maintenance base or

airport

9.1. ELECTRICAL WIRING DAMAGES

Installation Wiring

DAMAGE SCOPE ACTION TO BE TAKEN

Wire damaged or copper expose

Any Replace harness

Electrical power harness: Insulation with scratches or friction signals, but NO

expose copper

Length: any Depth: < 2 mm

Repair according to procedures of aircraft standard

electrical practices manual

Length: any Depth: > 2 mm

Replace harness

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10. ACCEPTABLE CORROSION LEVELS

ELEMENT ACCEPTABLE CORROSION

REPAIRABLE CORROSION

REPLACEMENT OF ELEMENT

Control Display Unit Not applicable Not applicable Not applicable

11. AIRWORTHINESS LIMITATIONS

No airworthiness limitations applied to this installation.

Life of control display unit is:

Unlimited

This installation does not reduce life of any aircraft element and/or component

affected by this installation.

The Airworthiness Limitations Section is approved and variations must also be

approved.

12. EWIS INSTRUCTIONS

N/A

13. INSTALLATION/ REMOVAL INSTRUCTIONS

13.1. Removal instructions

1. Disconnect all electrical connections between the control panel and SBAS

system and between the control panel and the aircraft.

2. Remove the control panel display (P/N G7321-122) unscrewing the DZUS

fasteners that fix the equipment to the cockpit panel. Retain all the fastener for

their use in re-installation process

3. If required uninstall the grounding studs by unscrew the existing screws and nuts

that fixed the ground connections. Retain the fasteners for their use in re-installation process.

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13.2. Installation instructions

1. If the ground connection where removed during the removal process install them

back in the location where it was installed previous the removal. Ensure the

fasteners used are exactly the same as in the original modification.

2. Attach the control display unit to the instruments panel according by means of

DZUS fasteners. Ensure the fasteners are in the same location as before the removal.

3. Connect all electrical connections between the control panel and SBAS system and between control panel and aircraft electrical system.