Fixed ELT installation - ASL Airlines Belgium · 2018. 4. 13. · Manufacture ELT and Control Panel...

2018 – ATL, 11-12 ASHLEY HEATH IND EST, RINGWOOD RD, THREE LEGGED CROSS, WIMBORNE, DORSET, BH21 6UZ, UK.

AS520 ISSUE 6

MODIFICATION SUMMARY

CONTINUATION SHEET

MODIFICATION No.

MOD-12281-00001 Sheet 2. Issue 3

1 Revision History

Issue Date Raised Issue Details Sheet(s) Affected

1 31/08/2012 Initial issue. All

2 01/07/2013 Para 4 – Aircraft MSNs 25181, 25184 & 25261 added to effectivity

Para 14 – New Occurrence Report template added.

6

13

3 31/01/2018 Address changed in footer.

Section 4: Aircraft MSN’s 24440, 24446, 26961, 24433 Applicable Mod issue was 1; MSN’s 25181, 25184, 25261 Applicable Mod issue was 2. Registration column deleted from table.

Para 5.2 Battery P/N was 9386023, and added text: “Not user replaceable”.

Section 10.3 Aircraft Maintenance Manual rewritten for clarity.

Section 10.4 Maintenance Schedule added in table format and MRBR references added.

Section 10.5 Maintenance Instructions completely rewritten for improved clarity, and subsequent paragraphs re-numbered.

Section 14 Design Occurrence Report Form updated.

Section 15 Design Query Form added.

All

6

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9-10

10

10-12

13-14

13,16

2018 - ATL, 11-12 ASHLEY HEATH IND EST, RINGWOOD RD, THREE LEGGED CROSS, WIMBORNE, DORSET, BH21 6UZ, UK. AS520 ISSUE 6


CONTINUATION SHEET

MODIFICATION No.


2 Contents

1 Revision History ............................................................................................................... 2 2 Contents ............................................................................................................................ 3 3 Documents Affected......................................................................................................... 4 3.1 Aircraft Flight Manual.......................................................................................................... 4 3.2 Aircraft Maintenance Manual .............................................................................................. 4 3.3 Illustrated Parts Catalogue ................................................................................................. 4 3.4 Wiring Diagram Manual ...................................................................................................... 4 3.5 Maintenance Schedule ....................................................................................................... 4 3.6 Minimum Equipment List .................................................................................................... 5 3.7 Flight Operation Manual ..................................................................................................... 5 3.8 Overhaul Manual ................................................................................................................ 5 3.9 Repair Manual .................................................................................................................... 5 3.10 Crew Manual ...................................................................................................................... 5 4 Aircraft Effectivity............................................................................................................. 6 5 Modification Details.......................................................................................................... 6 5.1 Introduction ......................................................................................................................... 6 5.2 Major Parts Required Per Aircraft ...................................................................................... 6 5.3 Major Parts Removed Per Aircraft ...................................................................................... 6 5.4 Documents and Drawings .................................................................................................. 6 5.5 Instructions ......................................................................................................................... 7 6 Checks ............................................................................................................................... 8 6.1 Ground Checks ................................................................................................................... 8 6.2 Flight Checks ...................................................................................................................... 8 7 Weight and Balance ......................................................................................................... 9 7.1 Equipment Removed .......................................................................................................... 9 7.2 Equipment Added ............................................................................................................... 9 8 Electrical Load Analysis .................................................................................................. 9 9 Limitations/Concession ................................................................................................... 9 10 Continued Airworthiness ................................................................................................. 9 10.1 Introduction ......................................................................................................................... 9 10.2 Overview ............................................................................................................................. 9 10.3 Aircraft Maintenance Manual .............................................................................................. 9 10.4 Maintenance Schedule ..................................................................................................... 10 10.5 Maintenance Instructions ................................................................................................. 10 10.6 Troubleshooting information ............................................................................................. 12 10.7 Airworthiness Limitations / Concessions .......................................................................... 12 11 Conditions Affecting this Approval .............................................................................. 13 12 Authorisation for Release to Service ........................................................................... 13 13 Post Modification Action ............................................................................................... 13 14 Design Occurrence Reports .......................................................................................... 13 15 Design Queries ............................................................................................................... 13 Appendix A Design Occurrence Report Template. ............................................................ 14 Appendix B Design Query Note Template. ......................................................................... 16


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MODIFICATION No.


3 Documents Affected

Document Document number / Action

Aircraft Flight Manual See paragraph 3.1 No

Aircraft Maintenance Manual See paragraph 3.2 Yes

Illustrated Parts Catalogue See paragraph 3.3 Yes

Wiring Diagram Manual See paragraph 3.4 Yes

Maintenance Schedule See paragraph 3.5, 10.4 Yes

Minimum Equipment List See paragraph 3.6 Yes

Flight Operation Manual See paragraph 3.7 Yes

Overhaul Manual See paragraph 3.8 No

Repair Manual See paragraph 3.9 No

Crew Manual See paragraph 3.10 Yes

Weight & Balance Schedule See paragraph 7 Yes

Electrical Load Analysis See paragraph 8 No

Aircraft Modification Record See paragraph 13.1 Yes

3.1 Aircraft Flight Manual

3.1.1 The Aircraft Flight Manual is not affected by this modification action.

3.2 Aircraft Maintenance Manual

3.2.1 Information that is required for the update of the AMM is contained in paragraph 10 of this document and is provided to the operator to enable the compilation of a supplement to the existing AMM. Supplements produced for the AMM must be provided to ATL for verification and approval prior to issue into the manual. Pending the availability of the supplementary data, this document may be placed into the AMM as an appendix until the manual is updated.

3.3 Illustrated Parts Catalogue

3.3.1 Information that is required for the update of the IPC is contained in paragraph 5.2, to allow the operator to compile a supplement to this manual. Any supplementary information produced must be supplied to ATL for verification and approval. Alternatively, this document may be placed into the IPC as an appendix until the document is updated.

3.4 Wiring Diagram Manual

3.4.1 Wiring diagrams called up by this modification action to be inserted in Aircraft Wiring diagram Manual.

3.5 Maintenance Schedule

3.5.1 Information that is required for the update of the Maintenance Schedule is contained in paragraph 10. A revision to the existing Maintenance Schedule shall be produced by the operator. Alternatively this document may be placed into the Maintenance Schedule as an appendix until the document is updated.



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MODIFICATION No.


3.6 Minimum Equipment List

3.6.1 The following is to be incorporated in the aircraft MEL, Section 23 at revision XX

Boeing 737 Revision No XX Page

Date dd/mm/yy YY

(1) System and Sequence Numbers (2) Rectification Interval

Item (3) Number installed

(4) Number required for dispatch

(5) Remarks or exceptions

23 Communication

ZZ Emergency Locator Transmitter (ELT)

A D

1 -

0 -

May be inoperative provided repairs are made within 6 further flights or 25 flying hours, whichever occurs first. Any in excess of those required may be inoperative.

Note Revision No XX, Date dd/mm/yy, Page YY and ZZ item to be completed on revision to MEL.

3.7 Flight Operation Manual

3.7.1 The Operation Manual is to be amended to include: “crew to check that ELT is installed prior to flight” and information concerning the location and operation of the ELT Remote Switch.

3.8 Overhaul Manual

3.8.1 The Overhaul Manual is not affected by this modification action.

3.9 Repair Manual

3.9.1 The Repair Manual is not affected by this modification action.

3.10 Crew Manual

3.10.1 The Crew Manual is to be amended to show the location of ELT unit as installed by this modification and to include the ELT operation instructions extracted from CEIS TM Model A06 /A06V1 Users Guide P/N 93D6014 at latest revision.

3.11 It is the operator’s responsibility to ensure that aircraft manuals affected by this modification are amended as appropriate.

3.12 All approved manual amendments/changes made as a result of data contained in this modification must be verified by ATL.


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MODIFICATION No.


4 Aircraft Effectivity

Model S/No Line No / Eff Applicable Mod

Issue

737-476 24440 2324 / PW541 3

737-476 24446 2569 / PW547 3

737-4L7 26961 2517 / PW557 3

737-476 24433 2396 / PW544 3

737-4Y0 25181 2203 / PW049 3

737-4Y0 25184 2227 / PW050 3

737-4Y0 25261 2258 / PM552 3

5 Modification Details

5.1 Introduction

5.1.1 This modification is introduced to authorise the installation of a CEIS TM ELTA06 unit in the ceiling of the vestibule area (L1 door) on the subject Boeing 737-400 series aircraft.

5.1.2 There is a Remote Control Panel installed in the flight deck on overhead panel P5 (Aft) to allow the crew monitoring of the system and manual activation of the ELT. Electrical power is supplied from ELT internal battery.

5.1.3 If a crash occurs the ELT detects the occurrence automatically using an associated acceleration sensor and transmits on international distress frequencies. It transmits a unique pre-programmed digital message on 406.025 MHz. designed to transmit a digital distress signal to satellites that are part of the COSPAS/SARSAT system. These satellites transmit the captured signal to the reception stations on the ground.

5.1.4 The CEIS TM ELTA06 also transmits a 121.5 MHz and 243 MHz signal to facilitate the final approach in an emergency (homing).

5.1.5 The technical content of this document is approved under the authority of DOA N° EASA.21J.016.

5.2 Major Parts Required Per Aircraft

Part No. Description Qty Remarks/manufacturer

9260065 ELT 1 CEIS TM ELT A06

89E0003 Bracket 1

93N6035 Remote controller 1

93G6023 Battery Ref 3 year life. Not user replaceable.

5.3 Major Parts Removed Per Aircraft

5.3.1 There are no parts removed as a result of this modification action.

5.4 Documents and Drawings

5.4.1 Refer to Master Document List MDL-12281-00001 for documents and drawings required.



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MODIFICATION No.


5.5 Instructions

Caution:

This transmitter is authorised for use only during situations of grave and imminent danger.

The beacon owner must have it registered. Contact CEIS TM or approved agent to obtain the information relative to this registration.

The beacon must be programmed with the relevant identification, authorised by the local airworthiness authority.

Once the beacon has been programmed, it is assigned to an aircraft (name and identification). If this beacon is used on another aircraft it will have to be reprogrammed (new name and identification).

Before installing or using this equipment the validity of the information on the beacon label must be checked.

Task Task description MECH INSP

5.5.1 Isolate aircraft electrical power and ensure the aircraft is electrically grounded.

5.5.2 Manufacture ELT and Control Panel mounting plates and angles in accordance with drawing ATL12281-001.

5.5.3 Expose location of ELT by removing ceiling panels in the ceiling of the vestibule area (L1 door) to gain access to the fuselage roof structure, in accordance with the Aircraft Maintenance Manual (AMM).

5.5.4

Referring to ATL12281-001 install the ELT mounting bracket.

The brackets major axis must be parallel with the aircraft flight axis as indicated by the bracket's label.

The major axis and the forward/aft directions must imperatively be respected to ensure correct acceleration sensor (G. switch) operation.

5.5.5 Note an angle of up to ± 8° from the aircraft flight axis may be allowed.

An angle of up to ± 3° from the aircraft horizontal axis may be allowed.

5.5.6 Install the beacon on the bracket assembly so that the connectors are pointing toward the front of the aircraft.

5.5.5 Obtain access to the aircraft flight deck.

5.5.6 The following paragraphs are to be performed with reference to CEIS TM Users Handbook Model A06/A06V1 ELT, 93D6014.

5.5.7 Install Control Panel in P5 Overhead Panel (Aft) in accordance with installation drawing ATL12281-001.

5.5.8 Install and terminate wiring in accordance with wiring diagram ATL12281-801.


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MODIFICATION No.


Task Task description MECH INSP

5.5.9

To be operational the beacon must be in AUTO position once it has been installed in its bracket.

As soon as the beacon is in AUTO it can be automatically activated by the internal G-switch.

5.5.10 Re-install ceiling panels removed at Para 5.5.3 above, in accordance with the AMM.

5.5.11 Perform a foreign object inspection in the modification working areas and check for integrity of disturbed units’, wires and panels.

5.5.12 Prepare the aircraft to perform operational checks on the ELT system in accordance with paragraph 6.

6 Checks

6.1 Ground Checks

6.1.1 Note: CAA Airworthiness Information Leaflet AIL/0193 gives guidance on testing ELT’s.

6.1.2 Bonding tests to be carried out between the newly installed components and aircraft structure (maximum value of 0.01 Ohms) and figures recorded.

6.1.3 NOTE: The following tests must be carried out in the first five minutes after the hour UTC (Universal Coordinated Time). Prior to testing, notify any nearby control tower of intention

6.1.4 On completion of installation, at each battery change and every time the system is disturbed the built-in self-test shall be performed in accordance with the CEIS TM Users Handbook Model A06/A06V1 ELT, 93D6014. It’s the operator’s responsibility to ensure that the ELT unit is coded in accordance with ICAO Annex 10.

6.1.5 Prior to flight ensure that ELT unit is present and is within expiry/testing dates.

6.1.6 Prepare the aircraft for return to service.

6.2 Flight Checks

6.2.1 There are no flight checks as a result of this modification action.



CONTINUATION SHEET

MODIFICATION No.


7 Weight and Balance

7.1 Equipment Removed

7.1.1 There is no equipment removed as a result of this modification action.

7.2 Equipment Added

Description Weight (lb)

Station (in)

Moment (lb.in)

Remarks

ELT Mounting Tray 2.866 310 888.46 1.3kg

ELT Transmitter assembly 2.866 310 888.46 1.3kg

Remote Controller 0.62 270 167.4 280g

Totals 6.352 306.1 1944.32

7.3 It is the responsibility of the operator to ensure that the Aircraft Weight and Balance Schedule is updated to include the changes introduced by this modification.

8 Electrical Load Analysis

8.1 There is no change to the aircraft electrical load analysis, since the ELT is battery powered; therefore the capacity of the aircraft generating system and standby battery is not exceeded.

9 Limitations/Concession

9.1 None applied for.

10 Continued Airworthiness

10.1 Introduction

10.1.1 The influence of the modification on Airworthiness Directive, Service Bulletin eligibility and other data must be considered and the publications monitored accordingly. The maintenance schedule for the aircraft should include reference to this material in addition to the original design. Coordination is the responsibility of the operator.

10.2 Overview

10.2.1 This section establishes compliance with CS 25.1529, and CS 25 Appendix H (Instructions for Continued Airworthiness) for the introduction of a fixed ELT on Boeing 737-400 aircraft. The maintenance instructions set out in this section are to be incorporated by the operator into the respective aircraft maintenance manuals, and scheduled maintenance programs.

10.3 Aircraft Maintenance Manual

10.3.1 Use the following paragraphs to amend the AMM. Refer also to the Users Handbook Model A06/A06V1 ELT, 93D6014 Rev B or later.

10.3.2 System Description

The CEIS TM ELT A06 unit is fitted in the ceiling of the vestibule area (L1 door) and the Remote Control Panel installed in the flight deck on overhead panel P5 (Aft) to allow the crew monitoring of the system and manual activation of the ELT. The remote control unit in the


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MODIFICATION No.

MOD-12281-00001 Sheet 10. Issue 3

cockpit consists of a RESET/TEST pushbutton, an ELT ON indicator light, and a two-position ON/ARMED switch with safety cover (flip guard), which forces the switch in to the ARMED position. This switch must always remain in this position, except in the case of manual distress triggering.

There is no external antenna. Electrical power is supplied from ELT internal battery.

If a crash occurs the ELT detects the occurrence automatically using an associated acceleration sensor and transmits on international distress frequencies. It transmits a unique pre-programmed digital message on 406.025 MHz. designed to transmit a digital distress signal to satellites that are part of the COSPAS/SARSAT system. These satellites transmit the captured signal to the reception stations on the ground.

The CEIS TM ELTA06 also transmits a 121.5 MHz and 243 MHz signal to facilitate the final approach in an emergency (homing).

The beacon is integrated in the aircraft and is connected to the remote control unit. This remote control unit enables beacon operation to be forced to ON, to be tested (TEST) or shutdown (RESET) in the event of an untimely triggering of the acceleration sensor from the aircraft cockpit.

10.3.3 Also include below sections 10.5 Maintenance instructions and 10.6 Troubleshooting in the AMM.

10.4 Maintenance Schedule

10.4.1 The following Maintenance Schedule Items are applicable to the ELT system and must be included in the Operator’s Aircraft Maintenance Programme.

Item Task Interval Task Description

23-001-01 (D6-82981-MRBR)

OPC 1 Month Operationally check the emergency locator transmitter (automatic/fixed type)

Reference: Self Check Procedure 10.5.2

23-003-01 (D6-82981-MRBR)

DIS See Note Discard the emergency locator transmitter battery (automatic/fixed type).

Reference: ELT Battery Pack restoration 10.5.3 Note: The battery pack expires 3 years from the

date (month) it is shipped from CElS TM

New Task 23-ATL-01 VCK 12 Months Visual inspection of Fixed ELT System Installation Reference: 10.5.1

10.5 Maintenance Instructions

10.5.1 Inspect the following components of the ELT system:

a) ELT unit and mount - ensure proper installation and secure mounting.

b) Wiring and conduits - ensure proper routing, secure mounting, and no obvious defects exist.

c) Bonding and shielding - ensure proper installation and good condition.

d) Unit Antenna - ensure good condition, secure mounting, and proper operation

10.5.2 Beacon Self-test by means of the Remote Control Unit in the cockpit.

10.5.2.1 Place the beacon’s AUTO/OFF/ON toggle switch in the AUTO position.

10.5.2.2 The Remote Control ARMED/ON switch must be in the ARMED position.



CONTINUATION SHEET

MODIFICATION No.

MOD-12281-00001 Sheet 11. Issue 3

10.5.2.3 Press the RESET/TEST pushbutton for approximately 2 seconds then check that the ELT ON indicator light comes ON, after one short blink more than 10 s.

10.5.2.4 Release the RESET/TEST pushbutton.

10.5.3 ELT Battery Pack Restoration (i.e. remove/replace and send removed ELT to an approved workshop facility) of ELT for battery replacement in the following instances:

a) After use in an emergency.

b) After an inadvertent activation of unknown duration.

c) When the total of all known transmissions exceeds one hour.

d) On or before the battery replacement (expiration) date.

10.5.3.1 Procedure:

Remove the emergency locator transmitter, as per 10.5.4.

Send the transmitter to an approved maintenance shop for restoration (battery replacement), as per 10.5.5.

Install the transmitter, as per 10.5.6.

Do an operational check of the transmitter, as per 10.5.7.

10.5.4 Removal of ELT

10.5.4.1 Gain access to the portable emergency locator transmitter

CAUTION: THE BEACON MUST BE COMPLETELY SHUT DOWN BEFORE ANY MAINTENANCE OPERATIONS ARE CARRIED OUT.

NOTE: The ELT is located in the ceiling of the vestibule area (L1 door)

10.5.4.2 Loosen the cotter pin from the latch of the strap.

10.5.4.3 Raise the latch.

10.5.4.4 Loosen the strap from the latch.

10.5.4.5 Move and hold the transmitter against the direction of flight.

10.5.4.6 Pull, sideways, the transmitter away from the bracket.

10.5.5 Send the transmitter to an approved maintenance shop for restoration (battery replacement).

10.5.6 Installation of ELT

NOTE: MAKE SURE THE REPLACEMENT ELT IS PROGRAMMED FOR THE AIRCRAFT AND REGISTERED WITH THE LOCAL AVIATION AUTHORITY.

10.5.6.1 Install the transmitter on the bracket.

NOTE: The transmitter must be installed on the aircraft according the label on the bracket which indicates the axis.

10.5.6.2 Attach the strap to the latch.

10.5.6.3 Close the latch.


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MODIFICATION No.

MOD-12281-00001 Sheet 12. Issue 3

10.5.6.4 Install the cotter pin.

10.5.7 Do an operational check of the transmitter

10.5.7.1 Ask the ATC operator for clearance to make an ELT transmission on the emergency frequencies.

10.5.7.2 On the transmitter place the AUTO/OFF/ON toggle switch to the ON position.

10.5.7.3 On the transmitter, the TX indicator light comes on. The transmitter buzzer sounds, after a short blink for more than 10 seconds.

10.5.7.4 Set the AUTO/OFF/ON toggle switch to the AUTO position.

10.5.7.5 Ask the ATC operator if the transmission is stopped and the transmission was clear.

10.5.7.6 Remove all tools, materials, and equipment from the work area. Make sure the area is clean.

10.6 Troubleshooting information

10.6.1 Troubleshooting information may be found in CEIS TM installation manual, CEIS TM Users Handbook Model A06/A06V1 ELT, 93D6014 Rev B or later.

10.6.2 In the event of an untimely beacon activation, shutdown the beacon and inform the SAR immediately.

10.6.3 The beacon is shut down by pressing the RESET/TEST pushbutton on the remote control unit, or by switching the beacon's AUTO/OFF/ON toggle switch to OFF (pull and slide to OFF).

10.6.4 Note stopping distress signal transmission by means of the remote control unit does not switch the beacon OFF. It is restored in AUTO mode (ARMED).

10.6.5 CAUTION: The beacon must be completely shut down before any maintenance operations are performed.

10.6.6 The beacon must be completely shut down before it is removed from its bracket and it's AUTO/OFF/ON toggle switch in OFF position.

10.6.7 It is the operator’s responsibility to ensure that the ELT is tested in accordance with the recommendations listed above.

10.6.8 It is the operator’s responsibility to ensure that their approved maintenance programme is amended to include this testing.

10.7 Airworthiness Limitations / Concessions

10.7.1 This section sets forth each mandatory replacement time, structural and inspection interval, and related structural inspection procedure approved under CS 25.571, and any mandatory inspection or replacement time of EWIS components as defined in CS 25.1701, where applicable.

10.7.2 The ELT unit and installation aircraft details must be registered with the appropriate registration agency authority prior to installation and whenever there is any change of ownership. Each 406 MHz ELT contains a unique identification code that is transmitted to the satellite. The unique identification permits accessing a database. This helps the “Rescue Coordination Centre” (RCC) determine whether an emergency actually has occurred.



CONTINUATION SHEET

MODIFICATION No.

MOD-12281-00001 Sheet 13. Issue 3

10.7.3 The local national Civil Aviation Authority in the applicable country must be contacted to obtain the correct registration form. The following details are to be recorded on the registration form.

Owners name

Address

Telephone number

Aircraft type

Aircraft Registration Number

10.7.4 Note: When ordering an ELT system or main assembly, it is necessary to inform CEIS TM of the country of registry and the programming format required, so that the ELT can be programmed accordingly.

10.7.5 The ELT Unit Battery Pack must be replaced once every 3 years.

10.7.6 If the ELT is used on another aircraft it must be reprogrammed with new name and identification.

11 Conditions Affecting this Approval

11.1 The compatibility of this modification with other previously approved modifications installed on the particular aircraft must be verified by the installer. Where the potential for interactions between modifications exists, the advice of the Design Organisation, the National Authority or EASA shall be sought.

12 Authorisation for Release to Service

12.1 In addition to the actions required by the procedures for release to service following maintenance or modification, prior to signing the Certificate of Release to Service, all actions and ground test procedures specified by the modification instructions (see paragraphs 5 & 6) must be completed satisfactorily.

13 Post Modification Action

13.1 Record the accomplishment of this modification in the Aircraft Modification Record.

14 Design Occurrence Reports Any failure, malfunction, defect or other occurrence related to this change, which has resulted in or may result in an unsafe or hazardous condition must be communicated to the ATL design organisation. A confirmation of receipt shall be requested. Notification shall be provided to ATL using the template shown at Appendix A as soon as possible after the condition has been identified. Initial notification may be made by phone, e-mail or similar means if the completed template document is unable to be sent immediately.

15 Design Queries Any queries related to this change must be communicated to the ATL design organisation. Notification shall be provided to ATL using the template shown at Appendix B as soon as possible after the Query has been identified.


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MODIFICATION No.

MOD-12281-00001 Sheet 14. Issue 3

Appendix A Design Occurrence Report Template.



CONTINUATION SHEET

MODIFICATION No.

MOD-12281-00001 Sheet 15. Issue 3


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MODIFICATION No.

MOD-12281-00001 Sheet 16. Issue 3

Appendix B Design Query Note Template.

Fixed ELT installation - ASL Airlines Belgium · 2018. 4. 13. · Manufacture ELT and Control Panel...

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