j & c minor change or repair approval sheetin other cases, substantiating tests must be made to...

JC/DOC/334 ISSUE 1.7

MINOR CHANGE or REPAIR APPROVAL SHEET

J & C Engineering Services Ltd

Tel: +44 (0)1763 252900 Fax: +44 (0)8709 223614 Email: [email protected] Web: www.jandceng.co.uk

TITLE

INSTALLATION OF AN EFB BRACKET ON THE EXISTING MAP HOLDER SUPPORT BRACKET

AIRCRAFT MAKE/TYPE SERIAL NUMBER REGISTRATION

BOEING 737-300, -400 SEE SECTION 2.4 OF JC/ER/3927

SEE SECTION 2.4 OF JC/ER/3927

ASSOCIATED TECHNICAL DOCUMENTS

DOCUMENT NUMBER ISSUE DESCRIPTION

JC/ER/3927 9.0 INSTALLATION OF AN EFB BRACKET ON THE EXISTING MAP HOLDER SUPPORT BRACKET

REASON FOR CHANGE OPERATOR’S REQUEST

SPECIALISM MEANS OF COMPLIANCE CVE DATE S01 AIRWORTHINESS 0 1 2 3 4 5 6 7 8 9 WER JENKINS 14-05-18

S02 RELIABILITY 0 1 2 3 4 5 6 7 8 9

S03 AERODYNAMICS 0 1 2 3 4 5 6 7 8 9

S04 AVIONIC SYSTEMS 0 1 2 3 4 5 6 7 8 9

S05 ELECTRICAL SYSTEMS 0 1 2 3 4 5 6 7 8 9

S06 TECH. PUBLICATIONS 0 1 2 3 4 5 6 7 8 9 WER JENKINS 14-05-18

S07 MECH/FLUID SYSTEMS 0 1 2 3 4 5 6 7 8 9

S08 FURNISHINGS 0 1 2 3 4 5 6 7 8 9

S09 STRUCTURES 0 1 2 3 4 5 6 7 8 9 WER JENKINS 14-05-18

S10 INTERIORS 0 1 2 3 4 5 6 7 8 9 WER JENKINS 14-05-18

MEANS OF COMPLIANCE CODES 0 – Definition 4 – Lab Rig Test 8 – Simulator Test 1 – Drawing & Description 5 – Ground Test 9 – Equipment Qualification 2 – Calculation & Analysis 6 – Flight Test 3 – System Safety Analysis 7 – Inspection/Survey

The technical content of this Change or Repair is approved under the authority of J & C Engineering Services Ltd Design Organisation Approval number EASA.21J.037 / AD/1853/05. I hereby declare that this Change or Repair complies with the Airworthiness, Environmental Protection and OSD Requirements applicable to the subject aircraft or equipment and has no unsafe features.

AUTHORISED SIGNATORY

CHANGE/REPAIR NUMBER

WER JENKINS (Head of Design)

Signature Date 14-05-18 JC/MOD/3927 ISSUE 9.0

mailto:[email protected]�

http://www.jandceng.co.uk/�


ENGINEERING REPORT

Report No. Issue

JC/ER/3927 9.0

Sheet 1 of 14


Date:

P

age:

TITLE



BOEING 737-300, -400 SEE SECTION 2.4 SEE SECTION 2.4

DOCUMENTS AFFECTED CONTENTS

MANUAL AFFECTED AMENDMENT

RESPONSIBILITY

YES NO J & C OPERATOR

AFM X AMM X X

CMM/IPC X ELA X AIPC X X MEL X SB X

SRM X W & B X WDM X

OPERATIONAL SUITABILITY DATA (OSD)

MMEL X FCOM X CCOM X

Description 1.0 Certification Basis 2.0 Compliance with Requirements 3.0 Accomplishment Instructions 4.0 Tests 5.0 Manuals 6.0 Weight and Balance 7.0 Electrical Load 8.0 Limitations/Concessions 9.0 Continued Airworthiness 10.0 Documents Required 11.0

COMPILED CHECKED APPROVED

AW MASTERS

WER JENKINS

HEAD OF OFFICE OF AIRWORTHINESS

WER JENKINS DATE: 14-05-18


ENGINEERING REPORT

Report No. Issue

JC/ER/3927 9.0

Sheet 2 of 14


Date:

P

age:

REVISIONS PAGE

ISSUE RAISED ISSUE DETAILS PAGES AFFECTED

1.0

1.1

2.0

3.0

4.0

5.0

6.0

7.0

8.0

9.0

Initial Issue

EO Up-Issued and Compliance Statements Amended.

EO Up-Issued to Change the Method of Installation. JC/WQN/451, JC/WQN/457 and JC/WQN/458 Incorporated.

Aircraft Effectivity MSN: 25105 & 25109 Added.

Aircraft Effectivity MSN: 25168, 24440 & 25184 Added.

Aircraft Effectivity MSN: 25110, 25111 & 27632 Added. Stress Memo Not Affected By This Change.

Aircraft Effectivity MSN: 25147 Added.

AMM and IPC Document Numbers Added. Stress Memo Not Affected By This Change.

Aircraft Effectivity changed MSN: 29201, 29202 and 29203

Added. Stress Memo Not Affected By This Change.

Removal Instructions, AMMS and IPCS Added. Stress Memo Not Affected By This Change.

JC/WQN/756 Incorporated.

Aircraft Effectivity MSN: 25097 and 28886 Added. Stress Memo Not Affected By This Change.

Aircraft Effectivity MSN: 28892, 28893 and 29270 Added,

Compliance Statements Updated and CS26 Statement Added. Stress Memo Not Affected By This Change.

All

All

All

All

All

All

All

All

All

All

THE LATEST REVISION AS DEFINED ABOVE SUPERSEDES ALL PREVIOUS REVISIONS UNLESS STATED OTHERWISE


ENGINEERING REPORT

Report No. Issue

JC/ER/3927 9.0

Sheet 3 of 14


Date:

P

age:

1.0 DESCRIPTION 1.1 This change is for the removal of the existing Map Holders and installation of new EFB

Brackets at the Pilot and Co-Pilot Locations on the existing Map Holder support brackets.

1.2 This change also includes removal instructions.

1.3 This change has been classified minor via the Minor Change Classification Process Sheet IAW 21A.91.

2.0 CERTIFICATION BASIS 2.1 The applicable certification basis of the aircraft type is referenced in TCDS IM.A.120.

However, compliance for this change will be with the latest requirements of CS25 amendment 20 unless stated otherwise.

2.2 The existing noise type certificate, as defined in the TCDS and as detailed in ICAO Annex 16, Volume 1, is not affected by this change.

2.3 The engine emissions, as detailed in ICAO Annex 16 Vol. 2, are not affected by this change. 2.4 Aircraft Effectivity:

Boeing 737-300

Serial Number Registration 23513 OO-TNC 29108 OE-IBZ 29109 OO-TNL

Boeing 737-400 Serial Number Registration

24440 - 25097 - 25105 - 25109 - 25110 - 25111 - 25147 OE-IAB 25168 - 25184 - 27131 OO-TNN 27256 OO-TNP 27632 - 28881 OO-TNO 28886 -


ENGINEERING REPORT

Report No. Issue

JC/ER/3927 9.0

Sheet 4 of 14


Date:

P

age:

Boeing 737-400 Serial Number Registration

28892 - 28893 - 29201 - 29202 - 29203 - 29205 OO-TNQ 29206 OE-IAP 29207 OE-IAQ 29208 OE-IAR 29209 OE-IAS 29210 OE-IAT 29270 -

3.0 CERTIFICATION BASIS

CS25.301 Loads: (a) Strength requirements are specified in terms of limit loads (the maximum loads to be expected in service) and ultimate loads (limit loads multiplied by prescribed factors of safety). Unless otherwise provided, prescribed loads are limit loads. (b) Unless otherwise provided the specified air, ground, and water loads must be placed in equilibrium with inertia forces, considering each item of mass in the aeroplane. These loads must be distributed to conservatively approximate or closely represent actual conditions. Methods used to determine load intensities and distribution must be validated by flight load measurement unless the methods used for determining those loading conditions are shown to be reliable. (c) If deflections under load would significantly change the distribution of external or internal loads, this redistribution must be taken into account. The installation of the EFB Bracket does not alter the provisioned loading on the structure as the map holder support bracket abuse allowable is greater than the weight of the EFB Bracket introduced. The local attachment of the EFB Bracket to the external surface of the map holder support bracket is analysed to ensure structural integrity for flight and emergency landing inertias, as applicable. See Stress Memo as defined in section 11. CS25.303 Factor of Safety: Unless otherwise specified, a factor of safety of 1 ∙5 must be applied to the prescribed limit loads which are considered external loads on the structure. When loading condition is prescribed in terms of ultimate loads, a factor of safety need not be applied unless otherwise specified. The installation of the EFB Bracket does not alter the provisioned loading on the structure as the map holder support bracket abuse allowable is greater than the weight of the EFB Bracket introduced. The local attachment of the EFB Bracket to the external surface of the map holder support bracket is analysed to ensure structural integrity for flight and emergency landing inertias, as applicable. See Stress Memo as defined in section 11. CS25.305 Strength and Deformation: (a) The structure must be able to support limit loads without detrimental permanent deformation. At any load up to limit loads, the deformation may not interfere with safe operation. (b) The structure must be able to support ultimate loads without


ENGINEERING REPORT

Report No. Issue

JC/ER/3927 9.0

Sheet 5 of 14


Date:

P

age:

failure for at least 3 seconds. However, when proof of strength is shown by dynamic tests simulating actual load conditions, the 3-second limit does not apply. Static tests conducted to ultimate load must include the ultimate deflections and ultimate deformation induced by the loading. When analytical methods are used to show compliance with the ultimate load strength requirements, it must be shown that – (1) The effects of deformation are not significant; (2) The deformations involved are fully accounted for in the analysis; or (3) The methods and assumptions used are sufficient to cover the effects of these deformations. (c) Where structural flexibility is such that any rate of load application likely to occur in the operating conditions might produce transient stresses appreciably higher than those corresponding to static loads, the effects of this rate of application must be considered. The installation of the EFB Bracket does not alter the provisioned loading on the structure as the map holder support bracket abuse allowable is greater than the weight of the EFB Bracket introduced. The local attachment of the EFB Bracket to the external surface of the map holder support bracket is analysed to ensure structural integrity for flight and emergency landing inertias, as applicable. See Stress Memo as defined in section 11. CS25.307 Proof of Structures: (a) Compliance with the strength and deformation requirements of this Subpart must be shown for each critical loading condition. Structural analysis may be used only if the structure conforms to that for which experience has shown this method to be reliable. In other cases, substantiating tests must be made to load levels that are sufficient to verify structural behaviour up to loads specified in CS 25.305. The installation of the EFB Bracket does not alter the provisioned loading on the structure as the map holder support bracket abuse allowable is greater than the weight of the EFB Bracket introduced. The local attachment of the EFB Bracket to the external surface of the map holder support bracket is analysed to ensure structural integrity for flight and emergency landing inertias, as applicable. See Stress Memo as defined in section 11. CS25.561 Emergency Landing General: (a) The aeroplane, although it may be damaged in emergency landing conditions on land or water, must be designed as prescribed in this paragraph to protect each occupant under those conditions. (b) The structure must be designed to give each occupant every reasonable chance of escaping serious injury in a minor crash landing when (1) Proper use is made of seats, belts, and all other safety design provisions ; (3) The occupant experiences the following ultimate inertia forces acting separately relative to the surrounding structure: (i) Upward, 3∙0g (ii) Forward, 9∙0g (iii) Sideward, 3∙0g on the airframe and 4∙0g on the seats and their attachments (iv) Downward, 6∙0g (v) Rearward, 1∙5g (d) Seats and items of mass (and their supporting structure) must not deform under any loads up to those specified in subparagraph (b)(3) of this paragraph in any manner that would impede subsequent rapid evacuation of occupants. (c) For equipment, cargo in the passenger compartments and any other large masses, the following apply: (1) These items must be positioned so that if they break loose they will be unlikely to: (i) Cause direct injury to occupants; (ii) Penetrate fuel tanks or lines or cause fire or explosion hazard by damage to adjacent systems; or (iii) Nullify any of the escape facilities provided for use after an emergency landing. (2) When such positioning is not practical (e.g. fuselage mounted engines or auxiliary power units) each such item of mass must be restrained under all loads up to those specified in sub-paragraph (b)(3) of this paragraph. The local attachments for these items should be designed to withstand 1·33 times the specified loads if these items are subject to severe wear and tear through frequent removal (e.g. quick change interior items). (d) Seats and items of mass (and their supporting structure) must not deform under any loads up to those specified in subparagraph (b)(3) of this paragraph in any manner that would impede subsequent rapid evacuation of occupants.


ENGINEERING REPORT

Report No. Issue

JC/ER/3927 9.0

Sheet 6 of 14


Date:

P

age:

The installation of the EFB Bracket does not alter the provisioned loading on the structure as the map holder support bracket abuse allowable is greater than the weight of the EFB Bracket introduced. The local attachment of the EFB Bracket to the external surface of the map holder support bracket is analysed to ensure structural integrity for flight and emergency landing inertias, as applicable. See Stress Memo as defined in section 11. CS25.601 Design and Construction General: The aeroplane may not have design features or details that experience has shown to be hazardous or unreliable. The suitability of each questionable design detail and part must be established by tests. The EFB Bracket introduced by this change has no details that are hazardous or unreliable. See Production Change JC/MOD/3923 as defined in section 11. CS25.603 Materials: The suitability and durability of materials used for parts, the failure of which could adversely affect safety, must – (a) Be established on the basis of experience or tests; (b) Conform to approved specification that ensure their having the strength and other properties assumed in the design data. (c) Take into account the effects of environmental conditions, such as temperature and humidity, expected in service. The EFB Bracket introduced by this change is a standard aerospace part and is manufactured from standard aerospace material as applicable. See Production Change JC/MOD/3923 as defined in section 11.

CS25.605 Fabrication Methods: (a) The methods of fabrication used must produce a consistently sound structure. If a fabrication process (such as gluing, spot welding, or heat treating) requires close control to reach this objective, the process must be performed under an approved process specification. (b) Each new aircraft fabrication method must be substantiated by a test programme.

Not affected by this change. No fabrication methods used require close control and no new

methods of fabrication are introduced. See Production Change JC/MOD/3923 as defined in section 11.

CS25.607 Fasteners: (a) Each removable bolt, screw, nut, pin or other removable fastener must incorporate two separate locking devices if – (1) Its loss could preclude continued flight and landing within the design limitations of the aeroplane using normal pilot skill and strength; or (2) Its loss could result in reduction in pitch, roll or yaw control capability or response below that required by Subpart B of this CS–25. Not affected by this change. No fasteners are used that require additional locking methods. See Production Change JC/MOD/3923 as defined in section 11.

CS25.609 Protection of Structure: Each part of the structure must- (a) be suitably protected against deterioration or loss of strength in service due to any cause, including – (1) Weathering; (2) Corrosion; and (3) Abrasion; and (b) Have provisions for ventilation and drainage where necessary for protection. The EFB Bracket introduced by this change has been suitably protected against deterioration or loss of strength by weathering, corrosion and abrasion. See Production Change JC/MOD/3923 as defined in section 11.

CS25.611 Accessibility Provisions: (a) Means must be provided to allow inspection (including inspection of principal structural elements and control systems), replacement of parts normally requiring replacement, adjustment, and lubrication as necessary for continued airworthiness. The


ENGINEERING REPORT

Report No. Issue

JC/ER/3927 9.0

Sheet 7 of 14


Date:

P

age:

inspection means for each item must be practicable for the inspection interval for the item. Non-destructive inspection aids may be used to inspect structural elements where it is impracticable to provide means for direct visual inspection if it is shown that the inspection is effective and the inspection procedures are specified in the maintenance manual required by CS 25.1529. The EFB Bracket introduced by this change does not affect access, inspection, replacement, adjustment or lubrication of parts. See Production Change JC/MOD/3923 as defined in section 11. CS25.613 Material Strength Properties and Material Design Values: (a) Material strength properties must be based on enough tests of material meeting approved specifications to establish design values on a statistical basis. (b) Material design values must be chosen to minimise the probability of structural failures due to material variability. Except as provided in subparagraphs (e) and (f) of this paragraph, compliance must be shown by selecting material design values which assure material strength with the following probability: (c) The effects of environmental conditions, such as temperature and moisture, on material design values used in an essential component or structure must be considered where these effects are significant within the aeroplane operating envelope. (e) Greater material design values may be used if a “premium selection” of the material is made in which a specimen of each individual item is tested before use to determine that the actual strength properties of that particular item will equal or exceed those used in design. (f) Other material design values may be used if approved by the Agency. Not affected by this change. The EFB Bracket introduced by this change is an approved part and the material strength properties are based on approved specifications. See Production Change JC/MOD/3923 as defined in section 11. CS25.619 Special Factors: The factor of safety prescribed in CS 25.303 must be multiplied by the highest pertinent special factor of safety prescribed in CS 25.621 through CS 25.625 for each part of the structure whose strength is – (a) Uncertain. (b) Likely to deteriorate in service before normal replacement; or (c) Subject to appreciable variability because of uncertainties in manufacturing processes or inspection methods. Where the Agency is not satisfied in a specific case that a special factor is the correct approach to ensuring the necessary integrity of the parts of the structure under service conditions, other appropriate measures must be taken. The installation of the EFB Bracket does not alter the provisioned loading on the structure as the map holder support bracket abuse allowable is greater than the weight of the EFB Bracket introduced. The local attachment of the EFB Bracket to the external surface of the map holder support bracket is analysed to ensure structural integrity for flight and emergency landing inertias, as applicable. See Stress Memo as defined in section 11. CS25.621 Casting Factors: (a) General. For castings used in structural applications, the factors, tests, and inspections specified in subparagraphs (b) through (d) of this paragraph must be applied in addition to those necessary to establish foundry quality control. The inspections must meet accepted specifications. Subparagraphs (c) and (d) of this paragraph apply to any structural castings except castings that are pressure tested as parts of hydraulic or other fluid systems and do not support structural loads. Not affected by this change. No Cast items used in this installation. See Production Change JC/MOD/3923 as defined in section 11. CS25.623 Bearing Factors: (a) Except as provided in subparagraph (b) of this paragraph, each part that has clearance (free fit), and that is subject to pounding or vibration, must have a bearing


ENGINEERING REPORT

Report No. Issue

JC/ER/3927 9.0

Sheet 8 of 14


Date:

P

age:

factor large enough to provide for the effects of normal relative motion. (b) No bearing factor need be used for a part for which any larger special factor is prescribed. Not affected by this change. The EFB Bracket is fixed and does not have a relative motion and no bearing factors are required. See Production Change JC/MOD/3923 as defined in section 11. CS25.625 Fitting Factors: For each fitting (a part or terminal used to join one structural member to another), the following apply: (a) For each fitting whose strength is not proven by limit and ultimate load tests in which actual stress conditions are simulated in the fitting and surrounding structures, a fitting factor of at least 1∙15 must be applied to each part of – (1) The fitting; (2) The means of attachment; and (3) The bearing on the joined members. (b) No fitting factor need be used – (1) For joints made under approved practices and based on comprehensive test data (such as continuous joints in metal plating, welded joints, and scarf joints in wood) ; or (2) With respect to any bearing surface for which a larger special factor is used. (c) For each integral fitting, the part must be treated as a fitting up to the point at which the section properties become typical of the member. (d) For each seat, berth, safety belt, and harness, the fitting factor specified in CS 25.785(f)(3) applies. The installation of the EFB Bracket does not alter the provisioned loading on the structure as the map holder support bracket abuse allowable is greater than the weight of the EFB Bracket introduced. The local attachment of the EFB Bracket to the external surface of the map holder support bracket is analysed to ensure structural integrity for flight and emergency landing inertias, as applicable. No new special factors are required. See Stress Memo as defined in section 11. CS25.771 Pilot compartment: (a) Each pilot compartment and its equipment must allow the minimum flight crew (established under CS 25.1523) to perform their duties without unreasonable concentration or fatigue. (b) The primary controls listed in CS 25.779 (a), excluding cables and control rods, must be located with respect to the propellers so that no member of the minimum flight crew (established under CS 25.1523), or part of the controls, lies in the region between the plane of rotation of any inboard propeller and the surface generated by a line passing through the centre of the propeller hub making an angle of 5º forward or aft of the plane of rotation of the propeller. (c) If provision is made for a second pilot, the aeroplane must be controllable with equal safety from either pilot seat. (d) The pilot compartment must be constructed so that, when flying in rain or snow, it will not leak in a manner that will distract the crew or harm the structure. (e) Vibration and noise characteristics of cockpit equipment may not interfere with safe operation of the aeroplane. This requirement has been considered and has been found not to be applicable for this change. CS25.773 Pilot compartment view: (a) Non-precipitation conditions. For non-precipitation conditions, the following apply: (1) Each pilot compartment must be arranged to give the pilots a sufficiently extensive, clear, and undistorted view, to enable them to safely perform any manoeuvres within the operating limitations of the aeroplane, including taxiing, take-off, approach and landing. (2) Each pilot compartment must be free of glare and reflection that could interfere with the normal duties of the minimum flight crew (established under CS25.1523). This must be shown in day and night flight tests under non-precipitation conditions. Not affected by this change. The installation of the EFB Bracket does not alter the flight crew’s view or abilities to perform their duties as the EFB introduced is located on the existing map holder support bracket where a map holder would be located as defined in the EO. See EO as defined in section 11.


ENGINEERING REPORT

Report No. Issue

JC/ER/3927 9.0

Sheet 9 of 14


Date:

P

age:

CS25.787 Stowage Compartments: (a) Each compartment for the stowage of cargo, baggage, carryon articles and equipment (such as life rafts) and any other stowage compartment must be designed for its placarded maximum weight of contents and for the critical load distribution at the appropriate maximum load factors corresponding to the specified flight and ground load conditions and, where the breaking loose of the contents of such compartments could– (1) Cause direct injury to occupants; (2) Penetrate fuel tanks or lines or cause fire or explosion hazard by damage to adjacent systems; or (3) Nullify any of the escape facilities provided for use after an emergency landing, to the emergency landing conditions of CS 25.561 (b) (3). The EFB Bracket introduced onto the map holder support bracket does not alter the provisioned loading on the structure as the map holder support bracket abuse allowable is greater than the weight of the EFB Bracket introduced. See Stress Memo as defined in section 11. CS25.789 Retention of Items of Mass in the Passenger and Crew Compartments and Galleys: Means must be provided to prevent each item of mass (that is part of the aeroplane type design) in a passenger or crew compartment from becoming a hazard by shifting under the appropriate load factors corresponding to the specified flight and ground load conditions and to the emergency landing conditions of CS25.561(b). The EFB Bracket is attached IAW standard OEM practices. The local attachment has been assessed for structural integrity and the weight of the EFB Bracket is within the abuse allowable of the map holder support bracket. See Stress Memo as defined in section 11. CS25.853 Compartment Interiors: For each compartment occupied by the crew or passengers, the following apply: (a) Materials (including finishes or decorative surfaces applied to the materials) must meet the applicable test criteria prescribed in Part I of Appendix F or other approved equivalent methods, regardless of the passenger capacity of the aeroplane. The EFB Bracket Plate introduced by this change are metallic and does not require a burns test as the material Al-Alloy 2024 or Al-Alloy 5754 chemical composition is less than 10% magnesium as defined in Aluminium Federation Issue 9.2 and aalco material data sheet for Al-Alloy 5754. See Production Change JC/MOD/3923 as defined in section 11. The Foam and the Plastic for the Clamp Plates introduced by this change are considered a small parts and do not require a burns test. See Production Change JC/MOD/3923 as defined in section 11. CS25.1519 Weight, Centre of Gravity and Weight Distribution: The aeroplane weight, centre of gravity, and weight distribution limitations determined under CS 25.23 to CS 25.27 must be established as operating limitations. There is a change to the weight and balance by the introduction of this change. It is the operator’s responsibility to document the change in weight and balance documentation if the weight of the parts, introduced or removed, is greater than 10lbs, as defined in section 7, and to ensure that the weight and balance remain within the prescribed weight and balance envelope of the aircraft. CS25.1529 Instructions for Continued Airworthiness: Instructions for Continued Airworthiness in accordance with Appendix H must be prepared. All required continued airworthiness instructions are specified in this document. A General Visual Inspection for damage to the EFB Bracket is to be carried out at the aircrafts C check. Co-ordination of these matters is the responsibility of the operator. See section 10.


ENGINEERING REPORT

Report No. Issue

JC/ER/3927 9.0

Sheet 10 of 14


Date:

P

age:

CS25.1557 Miscellaneous Markings and Placards: (a) Baggage and cargo compartments and ballast location. Each baggage and cargo compartment, and each ballast location must have a placard stating any limitations on contents, including weight, that are necessary under the loading requirements. However, underseat compartments designed for the storage of carry-on articles weighing not more than 9 kg (20 lb) need not have a loading limitation placard. Powerplant fluid filler openings. The following apply: (1) Fuel filler openings must be marked at or near the filler cover with – (i) The word ‘fuel’; (ii) Reserved. (iii) The permissible fuel designations; and (iv) For pressure fuelling systems, the maximum permissible fuelling supply pressure and the maximum permissible defuelling pressure. (2) Oil filler openings must be marked at or near the filler cover with the word ‘oil’. (3) Augmentation fluid filler openings must be marked at or near the filler cover to identify the required fluid. (c) Emergency exit placards. Each emergency exit placard must meet the requirements of CS 25.811. (d) Doors. Each door that must be used in order to reach any required emergency exit must have a suitable placard stating that the door is to be latched in the open position during take-off and landing. Not affected by this change. The weight EFB Bracket introduced is within the abuse allowable of the map holder support bracket. See Stress Memo as defined in section 11. AMC 20-25 - 6.1.1.1.1 Mounting Device: The mounting device (or other securing mechanism) attaches or allows mounting of the EFB system. The EFB system may include more than one mounting device if it consists of separate items (e.g. one docking station for the EFB host platform and one cradle for the remote display).The mounting device should not be positioned in such a way that it obstructs visual or physical access to aircraft controls and/or displays, flight crew ingress or egress, or external vision. The design of the mounting device should allow the user easy access to any item of the EFB system, even if stowed, and notably to the EFB controls and a clear view of the EFB display while in use. The following design practices should be considered: (a) The mounting device and associated mechanisms should not impede the flight crew in the performance of any task (normal, abnormal, or emergency) associated with operating any aircraft system. (b) When the mounting device is used to secure an EFB display (e.g. portable EFB, installed EFB side display), the mount should be able to be locked in position easily. If necessary, selection of positions should be adjustable enough to accommodate a range of flight crew member preferences. In addition, the range of available movement should accommodate the expected range of users’ physical abilities (i.e. anthropometrics constraints). Locking mechanisms should be of the low-wear types that will minimise slippage after extended periods of normal use. (c) Crashworthiness considerations should be taken into account in the design of this device. This includes the appropriate restraint of any device when in use. (d) When the mounting device is used to secure an EFB display (e.g. portable EFB, installed EFB side display), a provision should be provided to secure or lock the mounting device in a position out of the way of flight crew operations when not in use. When stowed, the device and its securing mechanism should not intrude into the flight crew compartment space to the extent that they cause either visual or physical obstruction of flight controls/displays and/or egress routes. (e) Mechanical interference issues of the mounting device, either on the side panel (side stick controller) or on the control yoke in terms of full and free movement under all operating conditions and non-interference with buckles, etc. For yoke mounted devices, (Supplemental) Type Certificate holder data should be obtained to show that the mass inertia effect on column force has no adverse effect on the aircraft handling qualities. (f) Adequate means should be provided (e.g. hardware or software) to shut down the portable EFB when its controls are not accessible by the pilot strapped in the normal seated position. This objective can be achieved through a dedicated installed resource certified according to 6.1.1.1 (e.g. button accessible from pilot seated position).


ENGINEERING REPORT

Report No. Issue

JC/ER/3927 9.0

Sheet 11 of 14


Date:

P

age:

This installation of the EFB Bracket is in compliance with this AMC. The installation of the EFB Bracket does not alter the flight crew’s abilities to perform their duties. The EFB Bracket provides means of securing the EFB in a position out of the way of flight crew operations as the EFB introduced is located on the existing map holder support bracket where a map holder would be located as defined in the EO. See EO as defined in section 11. CS26.150 Compartment Interiors: Compliance with Part 26.150 is demonstrated by complying with CS 25.853 and Appendix F or equivalent, CS 25.853(e) or equivalent and CS 25.791 or equivalent. See CS25.853. CS25.791 is not applicable to this change.

Operation Suitability Data (OSD): The operation suitability data must be checked, where applicable for EU aircraft delivered after the 17 February 2014, to ensure that there are no changes that affect the OSD. This requirement has been considered and the change/repair has been found not to affect the OSD. See page 1 of this report.

4.0 ACCOMPLISHMENT INSTRUCTIONS 4.1 See Engineering Order as defined in section 11. 5.0 TESTS

TEST REQUIRED RESPONSIBILITY

YES NO J & C OPERATOR

GROUND TEST X

STRUCTURAL TEST X BURNS TEST X

6.0 MANUALS 6.1 See Page 1 for Manuals and Documents affected.


ENGINEERING REPORT

Report No. Issue

JC/ER/3927 9.0

Sheet 12 of 14


Date:

P

age:

7.0 WEIGHT AND BALANCE 7.1 There is a change to the weight and balance. It is the operator’s responsibility to update the

aircraft weight and balance documentation with the change in weight and balance as defined below. (Note: The change in weight and balance documentation is only required if the weight of all of the part(s)/equipment introduced or removed, is greater than 10lbs.)

JC/EO/3927-1 - INSTALLATION OF NEW EFB BRACKET

REMOVED

PART NUMBER/ITEM QTY. PER A/C WEIGHT (lbs) ea. TOTAL

WEIGHT (lbs)

Existing OEM Map Holder 2 0.44 - 0.88

INTRODUCED


WEIGHT (lbs) EFB Bracket

P/N: TNT251JC1642-001 2 0.55 + 1.10

CHANGE

+ 0.22

JC/EO/3927-2 - REINSTALLATION OF OEM MAP HOLDER

REMOVED


WEIGHT (lbs) EFB Bracket

P/N: TNT251JC1642-001 2 0.55 - 1.10

INTRODUCED


WEIGHT (lbs)

Existing OEM Map Holder 2 0.44 + 0.88

CHANGE

- 0.22

8.0 ELECTRICAL LOAD 8.1 There is no change to the electrical load.


ENGINEERING REPORT

Report No. Issue

JC/ER/3927 9.0

Sheet 13 of 14


Date:

P

age:

9.0 LIMITATIONS/CONCESSIONS

9.1 The installer must verify the compatibility of this change/repair taking into account any existing changes/repairs installed on the subject aircraft. Where the potential for conflict exists between changes/repairs the advice of J& C Engineering Services Ltd. must be sought.

10.0 CONTINUED AIRWORTHINESS 10.1 The influence of this change on Airworthiness Directive, Service Bulletin and other applicable

publications will be considered and monitored accordingly.

10.2 A General Visual Inspection for damage to the EFB Bracket is to be carried out at the aircrafts C check. This is the responsibility of the operator.

11.0 DOCUMENTS REQUIRED

11.1 The following J & C Engineering Services Ltd approved document(s) are required: DOCUMENT NUMBER ISSUE/REV TITLE/DESCRIPTION JC/EO/3927-1 9.0 Accomplishment Instructions JC/EO/3927-2 3.0 Removal Instructions JC/AMMS/3927-1 5.0 AMM Supplement JC/IPCS/3927-1 5.0 IPC Supplement

11.2 The following reference document(s) are required: DOCUMENT NUMBER ISSUE/REV TITLE/DESCRIPTION D6-38550 Latest Boeing 737-300, -400 IPC D6-37529 Latest Boeing 737-300, -400 AMM D6-37534 Latest Boeing 737-300, -400 AMM D6-37592 Latest Boeing 737-300, -400 AMM D6-39023 Latest Boeing 737-300, -400 AMM D6-39032 Latest Boeing 737-300, -400 AMM D6-39033 Latest Boeing 737-300, -400 AMM D6-37532 Latest Boeing 737-300, -400 AMM D6-37535 Latest Boeing 737-300, -400 AMM D6-37540 Latest Boeing 737-300, -400 AMM D6-37541 Latest Boeing 737-300, -400 AMM D6-37544 Latest Boeing 737-300, -400 AMM D6-37584 Latest Boeing 737-300, -400 AMM


ENGINEERING REPORT

Report No. Issue

JC/ER/3927 9.0

Sheet 14 of 14


Date:

P

age:

DOCUMENT NUMBER ISSUE/REV TITLE/DESCRIPTION JC/MOD/3923 Latest Production Change for EFB Bracket AMC 20-25 09/02/14 AMC for EFB These document(s) have been reviewed by J & C Engineering Services Ltd and have been found to be appropriate to support this change/repair. 11.3 The following internal document(s) have been used to define applicable Certification Specification

Subpart paragraphs, additional applicable regulations, substantiation and to define the change classification:

DOCUMENT NUMBER ISSUE/REV TITLE/DESCRIPTION JC/CVC/3927 9.0 Compliance Verification Checklist JC/CCP/3927 9.0 Change / Repair Classification Process Sheet JC/SM/3927 3.0 Stress Memo 11.4 The following document(s) have been checked for compliance by the following Compliance

Verification Engineer(s) (CVE) as defined below:

DOCUMENT NUMBER ISSUE/REV CVE SPECIALISM

JC/ER/3927 9.0 WER JENKINS WER JENKINS WER JENKINS

S06 S09 S10

JC/EO/3927-1 9.0 WER JENKINS WER JENKINS

S09 S10

JC/EO/3927-2 3.0 WER JENKINS WER JENKINS

S09 S10

JC/AMMS/3927-1 5.0 WER JENKINS S06

JC/IPCS/3927-1 5.0 WER JENKINS S06

JC/SM/3927 3.0 WER JENKINS S09


ENGINEERING ORDER

Report No. Issue

JC/EO/3927-1 9.0

Sheet 1 of 21


Date:

P

age:

TITLE



BOEING 737-300, -400 SEE SECTION 2.4 OF JC/ER/3927 ISS 9.0

SEE SECTION 2.4 OF JC/ER/3927 ISS 9.0

MATERIAL REQUIREMENT

ITEM/PART NUMBER DESCRIPTION QTY (PER A/C)

TNT251JC1642-001 EFB BRACKET 2

REFERENCE DOCUMENT(S)

DOCUMENT NUMBER ISSUE/REV TITLE/DESCRIPTION TNT251JC1642 B Drawing of EFB Bracket D6-38550 Latest Boeing 737-300, -400 IPC D6-37529 Latest Boeing 737-300, -400 AMM D6-37534 Latest Boeing 737-300, -400 AMM D6-37592 Latest Boeing 737-300, -400 AMM D6-39023 Latest Boeing 737-300, -400 AMM D6-39032 Latest Boeing 737-300, -400 AMM D6-39033 Latest Boeing 737-300, -400 AMM D6-37532 Latest Boeing 737-300, -400 AMM D6-37535 Latest Boeing 737-300, -400 AMM D6-37540 Latest Boeing 737-300, -400 AMM D6-37541 Latest Boeing 737-300, -400 AMM D6-37544 Latest Boeing 737-300, -400 AMM D6-37584 Latest Boeing 737-300, -400 AMM


AW MASTERS

WER JENKINS




ENGINEERING ORDER

Report No. Issue

JC/EO/3927-1 9.0

Sheet 2 of 21


Date:

P

age:

REVISIONS PAGE


1.0

1.1

2.0

3.0

4.0

5.0

6.0

7.0

7.1

8.0

9.0

Initial Issue

Sub-Tasks Added and Reworded

Installation Method Change. JC/WQN/451, JC/WQN/457 and JC/WQN/458 Incorporated.

Aircraft Effectivity MSN: 25105 & 25109 Added.



Aircraft Effectivity MSN: 25147 Added. AMM and IPC Document Numbers Added.

Aircraft Effectivity changed MSN: 29201, 29202, 29203 Added.

29201, 29202, 29203 added to task 25 to 46

Aircraft Effectivity Details Amended On Sheet 1

Aircraft Effectivity MSN: 25097 and 28886 Added.

Aircraft Effectivity MSN: 28892, 28893 and 29270 Added.

All

All

All

All

All

All

All

All

All

All

All


ENGINEERING ORDER

Report No. Issue

JC/EO/3927-1 9.0

Sheet 3 of 21


Date:

P

age:

ACCOMPLISHMENT INSTRUCTIONS:

SIGN / AUTH / DATE TASK: Preparation Prior to Accomplishment of this EO

NOTES DESCRIPTION ACCOMP BY

INSPECT BY

N1 Read entire Engineering Order prior to accomplishment.

N2 Refer to associated Maintenance Manuals for additional information as required.

N3 Unless otherwise stated all work to be accomplished IAW aircraft AMM, SRM, WDM/AWM and SWPM.


ENGINEERING ORDER

Report No. Issue

JC/EO/3927-1 9.0

Sheet 4 of 21


Date:

P

age:


SIGN / AUTH / DATE

TASK: Replacement of Existing EFB bracket on Flight Deck Map Holder P1 Installed by the Previous Revision of This Change. FOR AIRCRAFT MSN: 23513, 29108, 29109, 27131, 27256, 28881, 29205, 29206, 29207, 29208, 29209 and 29210

Sub task DESCRIPTION ACCOMP

BY INSPECT

BY

1 Gain access to cockpit.

2 Locate Flight Deck Map Holder in P1 Pilot position.

3 Gently remove the Foam (P/N: TAS85079301) from the top side of the EFB Bracket. Retain for later reinstallation.

4 Remove the existing EFB Bracket (Installed by the previous revision of this change) by drilling out the securing rivets (Qty. 3) IAW Standard Maintenance Practices. Retain the EFB Bracket for later reinstallation.

5 Remove the existing Map Holder by unscrewing the securing screws (Qty. 3) IAW Standard Maintenance Practices. Tag Map Holder Serviceable / Unserviceable and return to stores. Tag screw (Qty. 1) Serviceable / Unserviceable and return to stores. Retain securing screws (Qty. 2) for later reinstallation.


ENGINEERING ORDER

Report No. Issue

JC/EO/3927-1 9.0

Sheet 5 of 21


Date:

P

age:


SIGN / AUTH / DATE



BY INSPECT

BY

6 Position the EFB Bracket on the removed Map Holder as shown if Figure 1, secure using clamps.

Figure 1 – EFB Bracket to Map Holder Positioning

(Dimensions in Millimetres)

7 Using the removed Map Holder as a template, mark off the position of the 2 securing screw holes, as show in Figure 2.

Figure 2 – Securing Screw Holes to be Marked Off


ENGINEERING ORDER

Report No. Issue

JC/EO/3927-1 9.0

Sheet 6 of 21


Date:

P

age:


SIGN / AUTH / DATE



BY INSPECT

BY

8 Once the 2 securing screw holes have been marked off on the EFB Bracket remove the clamps.

9 Drill the 2 holes marked in the EFB Bracket IAW Standard Maintenance Practices, ensuring they match the hole sizes and locations of the existing holes in the Map Holder Support Bracket. Reference Figure 3.

Figure 3 – Securing Screw Holes Existing on Map Holder Support Bracket


ENGINEERING ORDER

Report No. Issue

JC/EO/3927-1 9.0

Sheet 7 of 21


Date:

P

age:


SIGN / AUTH / DATE



BY INSPECT

BY

10 Using the securing screws retained in Sub-Task 5 secure the EFB Bracket to the Map Holder Support Bracket.

11 Make 2 holes in the Foam (P/N: TAS85079301) retained in Sub-Task 3 to allow for access to the 2 securing screws in the EFB Bracket.

12 Reinstall Foam (P/N: TAS85079301) on the top side of the EFB Bracket to protect the iPad from the screw heads.


ENGINEERING ORDER

Report No. Issue

JC/EO/3927-1 9.0

Sheet 8 of 21


Date:

P

age:


SIGN / AUTH / DATE

TASK: Replacement of Existing EFB bracket on Flight Deck Map Holder P1 Installed by the Previous Revision of This Change.

FOR AIRCRAFT MSN: 23513, 29108, 29109, 27131, 27256, 28881, 29205, 29206, 29207, 29208, 29209 and 29210


BY INSPECT

BY


14 Locate Flight Deck Map Holder in P2 Co-Pilot position.

15 Gently remove the Foam (P/N: TAS85079301) from the top side of the EFB Bracket. Retain for later reinstallation.

16 Remove the existing EFB Bracket (Installed by the previous revision of this change) by drilling out the securing rivets (Qty. 3) IAW Standard Maintenance Practices. Retain the EFB Bracket for later reinstallation.



ENGINEERING ORDER

Report No. Issue

JC/EO/3927-1 9.0

Sheet 9 of 21


Date:

P

age:


SIGN / AUTH / DATE




BY INSPECT

BY







ENGINEERING ORDER

Report No. Issue

JC/EO/3927-1 9.0

Sheet 10 of 21


Date:

P

age:


SIGN / AUTH / DATE




BY INSPECT

BY





ENGINEERING ORDER

Report No. Issue

JC/EO/3927-1 9.0

Sheet 11 of 21


Date:

P

age:


SIGN / AUTH / DATE




BY INSPECT

BY


23 Make 2 holes in the Foam (P/N: TAS85079301) retained in Sub-Task 15 to allow for access to the 2 securing screws in the EFB Bracket.



ENGINEERING ORDER

Report No. Issue

JC/EO/3927-1 9.0

Sheet 12 of 21


Date:

P

age:


SIGN / AUTH / DATE

TASK: Installation of EFB bracket on Flight Deck Map Holder Support Bracket P1. FOR AIRCRAFT MSN: 24440, 25097, 25105, 25109, 25110, 25111,

25147, 25168, 25184, 27632, 28886, 28892, 28893, 29201, 29202, 29203 and 29270


BY INSPECT

BY


26 Locate Flight Deck Map Holder in P1 Pilot position.






ENGINEERING ORDER

Report No. Issue

JC/EO/3927-1 9.0

Sheet 13 of 21


Date:

P

age:


SIGN / AUTH / DATE


25147, 25168, 25184, 27632, 28886, 28892, 28893, 29201, 29202, 29203 and 29270


BY INSPECT

BY





ENGINEERING ORDER

Report No. Issue

JC/EO/3927-1 9.0

Sheet 14 of 21


Date:

P

age:


SIGN / AUTH / DATE


25147, 25168, 25184, 27632, 28886, 28892, 28893, 29201, 29202, 29203 and 29270


BY INSPECT

BY





ENGINEERING ORDER

Report No. Issue

JC/EO/3927-1 9.0

Sheet 15 of 21


Date:

P

age:


SIGN / AUTH / DATE


25147, 25168, 25184, 27632, 28886, 28892, 28893, 29201, 29202, 29203 and 29270


BY INSPECT

BY

33 Make 2 holes in the Foam (P/N: TAS85079301) to allow for access to the 2 securing screws in the EFB Bracket.


35 Install/Position ‘Small Bracket Bumper’ P/N: TAS85079303 and ‘Large Bracket Bumper’ P/N: TAS85079305 with reference to EFB Bracket Drawing TNT251JC1642 ISS B.


ENGINEERING ORDER

Report No. Issue

JC/EO/3927-1 9.0

Sheet 16 of 21


Date:

P

age:


SIGN / AUTH / DATE


25147, 25168, 25184, 27632, 28886, 28892, 28893, 29201, 29202, 29203 and 29270


BY INSPECT

BY


37 Locate Flight Deck Map Holder in P2 Co-Pilot position.






ENGINEERING ORDER

Report No. Issue

JC/EO/3927-1 9.0

Sheet 17 of 21


Date:

P

age:


SIGN / AUTH / DATE


25147, 25168, 25184, 27632, 28886, 28892, 28893, 29201, 29202, 29203 and 29270


BY INSPECT

BY





ENGINEERING ORDER

Report No. Issue

JC/EO/3927-1 9.0

Sheet 18 of 21


Date:

P

age:


SIGN / AUTH / DATE


25147, 25168, 25184, 27632, 28886, 28892, 28893, 29201, 29202, 29203 and 29270


BY INSPECT

BY





ENGINEERING ORDER

Report No. Issue

JC/EO/3927-1 9.0

Sheet 19 of 21


Date:

P

age:


SIGN / AUTH / DATE


25147, 25168, 25184, 27632, 28886, 28892, 28893, 29201, 29202, 29203 and 29270


BY INSPECT

BY

44 Make 2 holes in the Foam (P/N: TAS85079301) to allow for access to the 2 securing screws in the EFB Bracket.


46 Install/Position ‘Small Bracket Bumper’ P/N: TAS85079303 and ‘Large Bracket Bumper’ P/N: TAS85079305 with reference to EFB Bracket Drawing TNT251JC1642 ISS B.


ENGINEERING ORDER

Report No. Issue

JC/EO/3927-1 9.0

Sheet 20 of 21


Date:

P

age:


SIGN / AUTH / DATE TASK: Close-up, Function and Conformity Checks, and Deviations


BY INSPECT

BY

C1 Perform loose articles check IAW Standard Maintenance Practices.

C2 Update the aircraft records to record this change, as defined on the Minor Change or Repair Approval Sheet, has been embodied.

NOTE For deviations to this EO where the Aircraft is not configured electrically and mechanically as defined then a WQN (JC/DOC/346) must be raised and sent to J & C Engineering Services Ltd (www.jandceng.co.uk) to address the deviations.


J & C Engineering Services Ltd QUERY NOTE

Report No. Issue

JC/WQN/

Sheet of

Page 21 of 21 JC/DOC/326 ISSUE 1.4

Date:

P

age:

TITLE REFERENCE

JC/MOD/


REPORTING DETAILS

REPORTED BY: DATE: COMPANY NAME:

TELEPHONE: FAX: WEB: EMAIL:

DESCRIPTION OF QUERY

RESPONSE (TO BE FILLED IN BY J & C ENGINEERING SERVICES LTD)

DOCUMENT(S) TO BE UP-ISSUED / CHANGED: YES NO



DATE:


ENGINEERING ORDER

Report No. Issue

JC/EO/3927-2 3.0

Sheet 1 of 6


Date:

P

age:

TITLE

REMOVAL OF AN EFB BRACKET ON THE EXISTING MAP HOLDER SUPPORT BRACKET


BOEING 737-300, -400 SEE SECTION 2.4 OF JC/ER/3927 ISS 9.0

SEE SECTION 2.4 OF JC/ER/3927 ISS 9.0

MATERIAL REQUIREMENT NONE

REFERENCE DOCUMENT(S)

DOCUMENT NUMBER ISSUE/REV TITLE/DESCRIPTION TNT251JC1642 B Drawing of EFB Bracket D6-38550 Latest Boeing 737-300, -400 IPC D6-37529 Latest Boeing 737-300, -400 AMM D6-37534 Latest Boeing 737-300, -400 AMM D6-37592 Latest Boeing 737-300, -400 AMM D6-39023 Latest Boeing 737-300, -400 AMM D6-39032 Latest Boeing 737-300, -400 AMM D6-39033 Latest Boeing 737-300, -400 AMM D6-37532 Latest Boeing 737-300, -400 AMM D6-37535 Latest Boeing 737-300, -400 AMM D6-37540 Latest Boeing 737-300, -400 AMM D6-37541 Latest Boeing 737-300, -400 AMM D6-37544 Latest Boeing 737-300, -400 AMM D6-37584 Latest Boeing 737-300, -400 AMM


AW MASTERS

WER JENKINS




ENGINEERING ORDER

Report No. Issue

JC/EO/3927-2 3.0

Sheet 2 of 6


Date:

P

age:

REVISIONS PAGE


1.0

2.0

3.0

Initial Issue



All

All

All


ENGINEERING ORDER

Report No. Issue

JC/EO/3927-2 3.0

Sheet 3 of 6


Date:

P

age:


SIGN / AUTH / DATE TASK: Preparation Prior to Accomplishment of this EO

NOTES DESCRIPTION ACCOMP BY

INSPECT BY

N1 Read entire Engineering Order prior to accomplishment.

N2 Refer to associated Maintenance Manuals for additional information as required.

N3 Unless otherwise stated all work to be accomplished IAW aircraft AMM, SRM, WDM/AWM and SWPM.


ENGINEERING ORDER

Report No. Issue

JC/EO/3927-2 3.0

Sheet 4 of 6


Date:

P

age:


SIGN / AUTH / DATE TASK: Removal of Existing EFB Bracket on Flight Deck Map Holder P1 & P2


BY INSPECT

BY


2 Locate Flight Deck Map Holder in P1 Pilot and P2 Co-Pilot position.

3 Gently remove the Foam (P/N: TAS85079301) from the top side of the EFB Bracket. Tag removed foam Serviceable / Unserviceable and return to stores.

4 Remove the existing EFB Bracket by unscrewing the securing screws (Qty. 2) IAW Standard Maintenance Practices. Tag removed EFB bracket Serviceable / Unserviceable and return to stores. Retain securing screws (Qty. 2) for later reinstallation, if required.

5 If required, reinstall the OEM Map Holder (retained from JC/EO/3927-1) using the securing screws (Qty. 3, 2 of which have been retained from sub-task 4 and 1 additional screw (retained from JC/EO/3927-1) will need to be retrieved from stores) IAW Standard Maintenance Practices.


ENGINEERING ORDER

Report No. Issue

JC/EO/3927-2 3.0

Sheet 5 of 6


Date:

P

age:


SIGN / AUTH / DATE TASK: Close-up, Function and Conformity Checks, and Deviations


BY INSPECT

BY

C1 Perform loose articles check IAW Standard Maintenance Practices.

C2 Update the aircraft records to record this change, as defined on the Minor Change or Repair Approval Sheet, has been removed.

NOTE For deviations to this EO where the Aircraft is not configured electrically and mechanically as defined then a WQN (JC/DOC/346) must be raised and sent to J & C Engineering Services Ltd (www.jandceng.co.uk) to address the deviations.


J & C Engineering Services Ltd QUERY NOTE

Report No. Issue

JC/WQN/ 1.0

Sheet of

Page 6 of 6 JC/DOC/326 ISSUE 1.4

Date:

P

age:

TITLE REFERENCE

JC/MOD/


REPORTING DETAILS

REPORTED BY: DATE: COMPANY NAME:

TELEPHONE: FAX: WEB: EMAIL:

DESCRIPTION OF QUERY

RESPONSE (TO BE FILLED IN BY J & C ENGINEERING SERVICES LTD)

DOCUMENT(S) TO BE UP-ISSUED / CHANGED: YES NO



DATE:



TEL: +44 (0)1763 252900 FAX: +44 (0)8709 223614

EMAIL:[email protected] WEB: www.jandceng.co.uk

Report No. JC/AMMS/3927-1

Issue

5.0

Sheet 1 of 11

Date:

P

age:

AIRCRAFT MAINTENANCE MANUAL SUPPLEMENT AIRCRAFT MAKE/TYPE

BOEING 737-300, -400 INTRODUCTION General A list of applicable changes is defined in Associated Changes to this manual. These changes are in addition to the initial design of the aircraft and are therefore detailed within this manual using appropriate and related ATA chapters. Effectivity The information contained within this manual concerns changes to the aircraft as defined in section 1. Associated Publications This Aircraft Manual Maintenance Supplement is to be used in conjunction with the existing Aircraft Maintenance Manual (AMM):

DOCUMENT NUMBER

ISSUE/ REV

DOCUMENT NUMBER

ISSUE/ REV DESCRIPTION

D6-37529 Latest D6-37532 Latest Aircraft Maintenance Manual D6-37534 Latest D6-37535 Latest Aircraft Maintenance Manual D6-37592 Latest D6-37540 Latest Aircraft Maintenance Manual D6-39023 Latest D6-37541 Latest Aircraft Maintenance Manual D6-39032 Latest D6-37544 Latest Aircraft Maintenance Manual D6-39033 Latest D6-37584 Latest Aircraft Maintenance Manual

The technical information contained within this document with reference to associated changes has been approved under the authority of Part 21J Design Organisation Approval No. EASA.21J.037


AW MASTERS

WER JENKINS





TEL: +44 (0)1763 252900 FAX: +44 (0)8709 223614



Issue

5.0

Sheet 2 of 11

Date:

P

age:

REVISION PAGE


1.0

2.0

3.0

4.0

5.0

Initial Issue

Aircraft Effectivity MSN: 24440, 25110, 25111, 25168, 25184 & 27632 Added and AMM References Added.

Aircraft Effectivity MSN: 29201, 29202 and 29203 and AMM References

Added and Associated Changes Updated

Aircraft Effectivity MSN: 25097 and 28886 Added and Associated Changes Updated

Aircraft Effectivity MSN: 28892, 28893 and 29270 Added and Associated

Changes Updated

All

All

All

All

All



TEL: +44 (0)1763 252900 FAX: +44 (0)8709 223614



Issue

5.0

Sheet 3 of 11

Date:

P

age:

TABLE OF CONTENTS

SECTION

AIRCRAFT EFFECTIVITIY 1.0

ASSOCIATED CHANGES 2.0

INSTALLATION 3.0

REMOVAL 4.0

CLEANING 5.0

NOTES 6.0

INSPECTION 7.0

AIRWORTHNESS LIMITATIONS 8.0



TEL: +44 (0)1763 252900 FAX: +44 (0)8709 223614



Issue

5.0

Sheet 4 of 11

Date:

P

age:

1.0 AIRCRAFT EFFECTIVITY

MODEL IDENT. CODE

EFFECT. CODE

BLOCK NUMBER

SERIAL NUMBER

LINE NUMBER REG.

B737-300 - - - 23513 - OO-TNC B737-300 - - - 29108 - OE-IBZ B737-300 - - - 29109 - OO-TNL B737-400 - - - 24440 - - B737-400 - - - 25097 - - B737-400 - - - 25105 - - B737-400 - - - 25109 - - B737-400 - - - 25110 - - B737-400 - - - 25111 - - B737-400 - - - 25168 - - B737-400 - - - 25184 - - B737-400 - - - 27131 - OO-TNN B737-400 - - - 27256 - OO-TNP B737-400 - - - 27632 - - B737-400 - - - 28881 - OO-TNO B737-400 - - - 28886 - - B737-400 - - - 28892 - B737-400 - - - 28893 - B737-400 - - - 29205 - OO-TNQ B737-400 - - - 29206 - OE-IAP B737-400 - - - 29207 - OE-IAQ B737-400 - - - 29208 - OE-IAR B737-400 - - - 29209 - OE-IAS B737-400 - - - 29210 - OE-IAT B737-400 - - - 29201 - - B737-400 - - - 29202 - - B737-400 - - - 29203 - - B737-400 - - - 29270 - -



TEL: +44 (0)1763 252900 FAX: +44 (0)8709 223614



Issue

5.0

Sheet 5 of 11

Date:

P

age:

2.0 ASSOCIATED CHANGES

CHANGE ISSUE/REV TITLE/DESCRIPTION JC/MOD/3923 2.0 Production of EFB Bracket JC/MOD/3927 9.0 Installation of an EFB Bracket on Existing Map Holder



TEL: +44 (0)1763 252900 FAX: +44 (0)8709 223614



Issue

5.0

Sheet 6 of 11

Date:

P

age:

Figure 1.0

EFB Bracket Location

Figure 2.0 EFB Bracket Location

3.0 INSTALLATION



TEL: +44 (0)1763 252900 FAX: +44 (0)8709 223614



Issue

5.0

Sheet 7 of 11

Date:

P

age:

Figure 3.0 Location of EFB Bracket Holes



TEL: +44 (0)1763 252900 FAX: +44 (0)8709 223614



Issue

5.0

Sheet 8 of 11

Date:

P

age:

To assemble the EFB Bracket, carry out the following procedure:

1. Gain access to cockpit.

2. Locate Flight Deck Map Holder L/H and/or R/H.

3. Remove Flight Deck Map holder by unscrewing the securing screws (Qty. 3) IAW Standard Maintenance Practices.

4. Position EFB Bracket P/N: TNT251JC1642-001 on the removed Map Holder as defined on figure

1.0 & 2.0 and secure with clamps.

5. Using the removed Map Holder as a template, mark off the position of the 2 AFT securing screw holes.

6. Once the 2 AFT securing screw holes have been marked off on the EFB Bracket P/N:

TNT251JC1642-001 remove the clamps.

7. Drill the 2 holes marked in the EFB Bracket P/N: TNT251JC1642-001 IAW Standard Maintenance Practices, ensuring they match the hole sizes and locations of the existing holes in the Map Holder Support Bracket.

8. Using 2 of the securing screws retained in Task 3 secure the EFB Bracket P/N: TNT251JC1642-

001 to the Map Holder Support Bracket.

9. Make 2 holes in the Foam (P/N: TAS85079301) to allow for access to the 2 securing screws in the EFB Bracket.

10. Cover the top side of the EFB Bracket with Foam P/N: TAS85079301 to protect the iPad from the

screw heads.

11. Install/Position ‘Small Bracket Bumper’ P/N: TAS85079303 and ‘Large Bracket Bumper’ P/N: TAS85079305 with reference to EFB Bracket Drawing TNT251JC1642 ISS B.



TEL: +44 (0)1763 252900 FAX: +44 (0)8709 223614



Issue

5.0

Sheet 9 of 11

Date:

P

age:

4.0 REMOVAL

To disassemble the EFB Bracket carry out the following procedure:

1. Gain access to cockpit.

2. Locate Flight Deck Map Holder with integral EFB Bracket L/H and/or R/H.

3. Remove EFB Bracket P/N: TNT251JC1642-001 by unscrewing the securing screws (Qty. 2) IAW Standard Maintenance Practices.

4. Reinstall Flight Deck Map Holder IAW Standard Maintenance Practices using OEM securing screws (Qty. 3). If disassembly is required remove the EFB Bracket from the aircraft, and if required return to: ASL AIRLINES BELGIUM (ENGINEERING DEPARTMENT) LIEGE AIRPORT BUILDING 101 B-4460 GRACE-HOLLOGNE BELGIUM



TEL: +44 (0)1763 252900 FAX: +44 (0)8709 223614



Issue

5.0

Sheet 10 of 11

Date:

P

age:

5.0 CLEANING

WARNING: Solvents are toxic and must only be used in well ventilated work areas. Avoid inhaling solvent fumes or allowing solvent to come into contact with the skin. Keep solvents away from all sources of ignition. CAUTION: Cleaning Agents containing chlorinated solvents, benzene, mek or petrol must not be used on plastics or composite parts. CAUTION: Plastic parts are prone to cracking in the presence of some chemicals. Mr. Clean, Fantastik, Top Job and Formula 409 must not be used. Use only approved cleaners.

To clean the EFB BRACKET, carry out the following procedure:

Using the following cleaning products:

• Cloth – Lint Free • Any water based Aircraft Interior Cleaner

1. Cleaning of the metallic items should be carried out in accordance with standard aircraft

practices, and care should be taken not to introduce chemicals or cleaners bearing areas. ABRASIVE PADS OR CLEANERS MUST NOT BE USED.

6.0 INSPECTION

Carry out a general inspection of the entire product using:

• Glass, Magnifying • Light, High Intensity

Reject any items that have the following defects:

• Cracks • Major Surface Damages (abrasions, grooves and scratches exceeding 0.0001” depth on

bearing surfaces and 0.001” depth on non-bearing surfaces) • Damaged Screw Threads • Dents • Distortion • Wear



TEL: +44 (0)1763 252900 FAX: +44 (0)8709 223614



Issue

5.0

Sheet 11 of 11

Date:

P

age:

Carry out a detailed inspection of EFB BRACKET looking for the following:

A visual inspection of the EFB Bracket and map holder is to be carried out every ‘C’ check. 1. Gain access to cockpit 2. Visually inspect the EFB Bracket and map holder for security 3. If damage, loose or corrosion is found, report finding. If necessary replace EFB Bracket.

Should any items be rejected return to: ASL AIRLINES BELGIUM (ENGINEERING DEPARTMENT) LIEGE AIRPORT BUILDING 101 B-4460 GRACE-HOLLOGNE BELGIUM

7.0 SPECIAL TOOLS, FIXTURES, EQUIPMENT & MATERIALS None

8.0 AIRWORTHINESS LIMITATIONS SECTION None The airworthiness limitations section is approved and variations must also be approved.



TEL: +44 (0)1763 252900 FAX: +44 (0)8709 223614


Report No. JC/IPCS/3927-1

Issue

5.0

Sheet 1 of 8

Date:

P

age:

ILLUSTRATED PARTS CATALOGUE SUPPLEMENT AIRCRAFT MAKE/TYPE

BOEING 737-300, -400 INTRODUCTION General A list of applicable changes is defined in Associated Changes to this manual. These changes are in addition to the initial design of the aircraft and are therefore detailed within this manual using appropriate and related ATA chapters. Effectivity The information contained within this manual concerns changes to the aircraft as defined in section 1. Associated Publications This Illustrated Parts Catalogue Supplement is to be read in conjunction with the following existing Illustrated Parts Catalogue (IPC):

DOCUMENT NUMBER ISSUE/REV TITLE/DESCRIPTION D6-38550 Latest Aircraft Illustrated Parts Catalogue

The technical information contained within this document with reference to associated changes has been

approved under the authority of Part 21J Design Organisation Approval No. EASA.21J.037


AW MASTERS

WER JENKINS





TEL: +44 (0)1763 252900 FAX: +44 (0)8709 223614



Issue

5.0

Sheet 2 of 8

Date:

P

age:

REVISION PAGE


1.0

2.0

3.0

4.0

5.0

Initial Issue

Aircraft Effectivity MSN: 24440, 25110, 25111, 25168, 25184 & 27632 Added.


Changes Updated

Aircraft Effectivity MSN: 25097 and 28886 Added and Associated Changes Updated


Changes Updated

All

All

All

All

All



TEL: +44 (0)1763 252900 FAX: +44 (0)8709 223614



Issue

5.0

Sheet 3 of 8

Date:

P

age:

TABLE OF CONTENTS

SECTION

AIRCRAFT EFFECTIVITIY 1.0

ASSOCIATED CHANGES 2.0

ILLUSTRATED PARTS CATALOGUE SUPPLEMENT 3.0



TEL: +44 (0)1763 252900 FAX: +44 (0)8709 223614



Issue

5.0

Sheet 4 of 8

Date:

P

age:

1.0 AIRCRAFT EFFECTIVITY

MODEL IDENT. CODE

EFFECT. CODE

BLOCK NUMBER

SERIAL NUMBER

LINE NUMBER REG.

B737-300 - - - 23513 - OO-TNC B737-300 - - - 29108 - OE-IBZ B737-300 - - - 29109 - OO-TNL B737-400 - - - 24440 - - B737-400 - - - 25097 - - B737-400 - - - 25105 - - B737-400 - - - 25109 - - B737-400 - - - 25110 - - B737-400 - - - 25111 - - B737-400 - - - 25168 - - B737-400 - - - 25184 - - B737-400 - - - 27131 - OO-TNN B737-400 - - - 27256 - OO-TNP B737-400 - - - 27632 - - B737-400 - - - 28881 - OO-TNO B737-400 - - - 28886 - - B737-400 - - - 28892 - B737-400 - - - 28893 - B737-400 - - - 29205 - OO-TNQ B737-400 - - - 29206 - OE-IAP B737-400 - - - 29207 - OE-IAQ B737-400 - - - 29208 - OE-IAR B737-400 - - - 29209 - OE-IAS B737-400 - - - 29210 - OE-IAT B737-400 - - - 29201 - - B737-400 - - - 29202 - - B737-400 - - - 29203 - - B737-400 - - - 29270 - -



TEL: +44 (0)1763 252900 FAX: +44 (0)8709 223614



Issue

5.0

Sheet 5 of 8

Date:

P

age:

2.0 ASSOCIATED CHANGES

CHANGE ISSUE/REV TITLE/DESCRIPTION JC/MOD/3923 2.0 Production of EFB Bracket JC/MOD/3927 9.0 Installation of an EFB Bracket on Existing Map Holder



TEL: +44 (0)1763 252900 FAX: +44 (0)8709 223614



Issue

5.0

Sheet 6 of 8

Date:

P

age:

The purpose of this Illustrated Parts Catalogue (IPC) is to provide means of locating and identifying parts of the EFB Bracket. Using the IPC an illustration is shown of the EFB Bracket each replaceable part will have an item number. These item numbers will then correlate with a table listing the part number, description and number off per assemble. If applicable each item will have an effectivity code detailing which specific assembly the part is applicable to. Throughout the IPC the following abbreviations may be used:

AFT Aft (Rear) A/R As Required ASSY Assembly BKDN Breakdown BRKT Bracket CBR Counter bore CSK Countersunk FWD Forward INST’N Installation L/H Left Hand NHA Next Higher Assembly OPT Optional OUTBD Outboard R/H Right hand UNC Unified Coarse UNF Unified Fine

3.0 ILLUSTRATED PARTS CATALOGUE SUPPLEMENT



TEL: +44 (0)1763 252900 FAX: +44 (0)8709 223614



Issue

5.0

Sheet 7 of 8

Date:

P

age:

Figure 1 EFB BRACKET ASSEMBLY



TEL: +44 (0)1763 252900 FAX: +44 (0)8709 223614



Issue

5.0

Sheet 8 of 8

Date:

P

age:

FIG

ITEM PART NUMBER NOMENCLATURE EFFECT. UNITS PER

ASSY 1

1 2 3 4 5 6 7 8 9

10

-11

-12

-13

14

TNT251JC1642-101 TNT251JC1642-102 TNT251JC1642-103 TAS85079305 TAS85079303 TNT251JC1642-104 TNT251JC1642-105 TNT251JC1642-106 TAS85079301 TAS85079601 MS24693 - - TNT251JC1642-107

EFB BRACKET PLATE BRACKET BUMPER BRACKET BUMPER CLAMP BUMPER R/H CLAM BUMPER L/H CLAMP PLATE R/H CLAM PLATE L/H LINCHPIN & RETENTION KNOB FOAM FOAM OEM CSK SCREW - - LINCHPIN & RETENTION KNOB ASSEMBLY

- 1 1 1 1 1 1 1 2 1

A/R 2 - - 2

* ITEM NOT ILLUSTRATED