# SERVICE BULLETIN

Number: A320

- 5 3

- 00 6

Airbus A318/ A 319/ A 320

Inspection of IFE Radome



### 1. Planning Information



### A. Effectivity

This service bulle tin is applicable to all Airbus A318/ A 319/ A 320 aircraft w ith Radome P/N 5063

- 100

- xx (where XX designates the color option) installed in a ccordance w ith LiveTV STC

ST 00788SE.



### B. Concurrent Requirement

None



### C. Reason

This service bulletin provides the instruction to inspect the effected aircraft with STC ST 00788SE

IFE radome installed for outer ply cracks. If cracks are found, the radome is to b e replaced before further flight

.

This service bulletin is a result of a safety analysis performed by the STC holder and the FAA based on knowledge that the Airbus A320 series aircraft are not certified to a ccount for th e type of damage described below, o r for energy levels related to a comparable bird strike event with the aircraft empennage

. I nspections accomplished in accordance with the LiveTV Service Bulletin

Number A320

- 53

- 003 provided the basis for an analysis of this radome cracking issue. Th is

an alysis determined that radome cracks could pos sibly propagate, allowing larg e pieces to separate from the aircraft and strike the tail. The full core section of the radome weighs 10.5 lbs and there is no data available to substantiate that a section large r than 8 lbs could not separate.

The Airbus A318, A319 and A320 aircraft (TCDS A28NM) are ce rtified to 14CFR Part 25

Amendment L evel 25

- 56 with Airbus electing to comply with 14CFR Part 25.571 to Amendment

L evel 91. The resulting certification Amendment L evel for the aircraft empennage is an 8 lb object at V cruise per 14CFR Part 25.631 for bird strike damage and a 4 lb object at V cruise per
14CFR Part 25.571(e) ( 1 ) for Damage T olerance and F atigue evaluation of structure. Therefore
impact with the 10.5 lb radome could cause an unsafe condition. T he severity of the unsafe condition would depend on the size, trajectory and orientation of the released radome piece(s) at
impact. T he radome shape is primarily an oval, 44 inches wide and 63 inches long and 5.7” high. The greatest damage is expected to be a direct strike to the vertical stabilizer leading edge in an edgewise orientation due to the concentration of the energy in a small area.

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# SERVICE BULLETIN

Radome m anufacturing variation due to a lack of dimensional controls

, as shown in early manufacturing drawing revisions, can result in the introduction of preload stress on the radome. Preload stress combined with flight or ground maintenance / handling stress, such as stepping on the radome fairing assembly, may initiate a crack. The radome drawings were revised on September 13, 2010 to add a control dimension which would eliminate the preload stress and will prevent the possibility of ra d ome cracking. This design change was incorporated at radome serial number 498(F) and higher . “F” designations identify radome units that have flex

- coat paint incorporated to alleviate surface paint crazing conditions. The inclusion of the “F” designation does not change the base serial number. The base serial number will be used from t his point

forward in the SB.



### D. Description

This service b ulletin provides instructions for an external visual ins pection for cracks of the IFE (In Flight Entertainment) radome. If any crack ( s ) is/ are found the radome is to be replaced before further flight

. Following each inspection, the ‘ Reporting Form ’ contained within this Service
Bulletin shall be completed and returned to LiveTV.



### E. Accomplishment Recommendation

1) It is recommended that t he operator accomplish the initial inspection within 3

, 900 Flight

Hou rs (FH) following the release date of this service bulletin . This will ensure initial
inspection per th is SB within 3 900 F light H ours (FH)

. 2) It is recommended that the operator initialize a r epetitive i nspection every 3, 900 FH

thereafter

. 3) The operator is t o report any crack indications to the STC holder

. 4) Currently there is no terminating action.

5) T erminating action ( s ) are currently under evaluation by the FAA and STC holder

. 

### F. Regulatory Approval

This Service Bulletin contains no modification information that revises the approved configuration.



### G. Manpower

The manpower estimates given in this Service Bulletin are based on the direct labor cost to do

the work. These estimates assume that the work will be done by experience d personnel and may
need to be revised upwa rds to suit operator’s circumstances

. The estimated labo r to accomplish

this Service Bulletin is :

Phase or Part Technicians Elapsed Time Labor

- Hours

Inspection 1 1 1

Radome

, replace if required 2 * 8 (Based on RTV

- 108 cure time of 6 hrs.) 4

*If RTV 230A /B is used , elapsed time will be shorter.

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# SERVICE BULLETIN

H. W eight and Balance

None



### I. Electrical Load Data

Not Changed



### J. Software Accomplishment Summary

Not Applicable



### K. References

• STC ST00788SE Airbus A318/ A 319/ A 320 aircraft

• LiveTV IPC LTV

- 6 05

• LiveTV IPC LTV

- 6 15

• LiveTV AMM LTV

- 53 0

• LiveTV AMM LTV

- 535

• Airbus AMM A318/319/320

• LiveTV Radome Installation Drawings for STC ST00788SE :

• LTV933100 SH 202 Rev F (A318 FR )

• LTV933100 SH 102 Rev E (A319 FR )

• LTV933100 SH 4 Rev H (A320)

• 320L2102 R ev IR (A320 FR )

• LiveTV SIL

- 0059

• AC 20

- 17 6

• AAS

- NDT

- 09

- 001 Non

- Destructive Testing Manual for LiveTV Alterations and Repairs

• LiveTV Service Bulletin 320

- 53

- 003

• LiveTV Service Bulletin 320

- 53

- 004



### L. Publications Affected

None



### M. Interchanging and Intermixing Parts

None



### N. Revision History

Revision Reason D ate

00 Initial Release 27 August 201 4

01 Added ‘Revision 01’ notation to Section N and Reporting Form, Pages 3 & 13,

Edited form submittal instruction at top of Page 14. 10 September 2014

A320

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# SERVICE BULLETIN

2. Material Information



### A. Material

– Availability

All parts and mate rials are provided in accordance with contractual agreements.

No additional parts are required.

Material questions should be directed to the location listed below:

STC holder Materials Group Phone: (1) 407

- 240

- 3265

7415 Emerald Dunes Drive
Suite 2000 Fax : (1) 407

- 240

- 8664

Orlando, FL 32822

USA



### B. Industry Support Information

Support information or questions should be directed t o the location(s) listed below:

STC holder Maintenance Technical Support Phone: (1) 407

- 812

- 2538

Fax : (1) 407

- 812

- 2526

E mail: T echSupport@LiveTV.ne t

STC holder Certification Manager

Oscar Hernandez

Manager , Aircraft Certification Email: CertificationEngineering @livetv.net

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# SERVICE BULLETIN

C. Consumables Requirements

The following consumables may be required:

Mfg. Part Number Nomenclature Quant ity Source

Cor

- ban 27 L Compound, Anti

seize A/R Commercially Available

RTV

- 108 or RTV

230 A/B Sealant or Sealant, Rapid Cure A/R Commercially Available



### D. LiveTV Supplied Material

Mfg. Part Number Nomenclature Quantity Source

5063

- 100

- XX (XX refers to c olor option) Radome 1 per A/C
(as required) LiveTV



### E. Operator/Customer Supplied Material

Not applicable



### F. Re

- identified Parts

N on e



### G. Tooling

– Availability

(1) Standard m echanic t ools may be used

. (2) The following special tools are required:



### Mfg. Part
Number Nomenc lature Quantity Source

A/R * Torque Wrench, 65

- 100 inch pounds 1 Commercially A vailable



### A/R Access maint en ance stand
to reach Crown area 1 Commercially Available

* R equired if radome is removed and replaced.

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# SERVICE BULLETIN

3. Accompli s hment Instructions

• For Aircraft th at utilize LiveTV AMM LTV

- 535 accomplish step 3.1

• For Aircraft that utilize LiveTV AMM LTV

- 530 accomplish step 3.2

3.1 Accomplishment Instructions

A. Genera l

WARNING: Make sure that you obey all the warnings and cautions included in the referenced
procedur es.

NOTE: Some steps in the accomplishment instructions are identified as ‘ Required for Compliance ’ (RC ). T he steps identified as ( RC ) must be fully accomplished to comply with this SB . Steps

not identified with (RC ) are recommended and may be deviated from, done as part of other action, or done with acceptable methods different from those indicated in this SB

.

1) Preparation : a) Ensure aircraft is sa fe for maintenance; refer to Air b us A318/A319/A320 AMM “INTRO”

. b) Remove power to the IFE system; refer to LiveT V AMM LTV

- 535 , section 4000. c) Gain acces s the radome in the crown area.

B. Work Instructions

1) (RC) Accomplish a detailed visual i nspect ion (D VI) of r adome assembly in area s detailed in Fig ure 1

.

Radome Visual Inspection Procedures

• Stands, ladders or platfo rms may be required to gain proximity to the area being inspected.

• Inspection area should have clear access to the inspection surface.

• Inspection surface shall be clean, dry and free of oil, grease, sealant, corrosion, chemical

residues , or any coating whi ch could affect the accuracy of the inspection, except for paint,

pr imer, clad and anodize coatings

. Note: Mechanical/chemical cleaning or corrosion removal is not authorized in this procedure and must
have previous approval by the airworthiness authority to whom the operator is responsible.

N ote : Previous cracks noted were in excess of 1 inch in length and could be seen without the need for magnification

, and were visible through the paint layer from a typical distance of 18 inches

.

• This level of inspe ction is made under normally available lighting conditions such as daylight or hangar lighting

, supplemented with a direct source of good lighting at an intensity deemed appropriate by the person performing the inspection

. A flashlight or drop light direc ted at an angle to the surface being inspected as shown in the view below can be used

.

• All visual inspections should be performed as close as possible to the part being inspected and no greater than 18 inches from the surface of the part.

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# SERVICE BULLETIN

NOTE: Figu re 2 provides examples of typical cracks found at forward and aft locations of the radome

exterior.

• If any crack IS found

, proceed to Step 2

.

• If crack IS NOT found , proceed with Step 3

. 2) (RC) If a ny crack is found, remove and r eplace the IFE Radome before further flight per LiveTV

AMM LTV

- 535 , section 4000.

NOTE : Seal the re veal area between Radome and Fairing with : (Refer to Figure 3)

• RTV

- 108 ( requires a 6 hour cure time prior to flight @ 77 d eg. F and 50% relative humidity )

,

• or alternate s ealant RTV

- 23 0A/B ( requires a 2 hour cure time prior to flight @ 77 d eg. F and 50%
relative humidity )

.

3) Restore the aircraft to normal condition

, refer to Airbus A318/ A 319/ A 320 AMM and restore power

to IFE system, refer to LiveTV AMM LTV

- 535 , section 4000.

C. Reporti ng Form

1) (RC) C ompl ete the “Reporting Form” and attach the completed inspection r esults to the STC

holder Technical Support AND Certification group s via e

- mail or fax

, as noted in S ection 2 B

, with subject line heading of : “ Service Bulletin A320

- 53

- 006 and (Aircraft Registration Number) ”

.

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# SERVICE BULLETIN

3.2 Accomplishment Instructions

A. Genera l

WARNING: Make sure that you obey all the warnings and cautions included in the referenced
procedures.

NOTE: Some steps in the accomplishment instructions are identified as ‘ Required for Compliance ’ (RC ). T he steps identified as (RC ) must be fully accomplished to comply with this SB . Steps

not identified with (RC ) are recommended and may be deviated from, done as part of other action, or done with acceptable methods differe nt from those indicated in this SB

.

1) Preparation d) Ensure a ircraft is safe for maintenance; refer to Airbus A318/A319/A320 AMM “INTRO”

. a) Remove power to the IFE system; refer to LiveTV AMM LTV

- 530 , section 4000. b) Gain access the radome in th e crown area.

B. Work Instructions

1) (RC) Accomplish a detailed visual inspection (DVI) of radome assembly in areas detailed in Figure 1

.

Radome Visual Inspection Procedures

• Stands, ladders or platforms may be required to gain proximity to the area being inspected.

• Inspectio n area should have clear access to the inspection surface.

• Inspection surface shall be clean, dry and free of oil, grease, sealant, corrosion, c hemical

residues

, or any coating which could affect the accuracy of the inspection, except for paint,

pr imer, cl ad and anodize coatings

. Note: Mechanical/chemical cleaning or corrosion removal is not authorized in this procedure and must
have previous approval by the airworthiness authority to whom the operator is responsible.

N ote : Previous cracks noted were in excess of 1 inch in length and could be seen without the need for magnification

, and were visible through the paint layer from a typical distance of 18 inches

.

• This level of inspection is made under normally available lighting conditions such as daylight or hangar lighting

, supplemented with a direct source of good lighting at an intensity deemed appropriate by the person performing the inspection

. A flashlight or drop light directed at an angle to the surface being inspected as shown in the view below ca n be used

.

• All visual inspections should be performed as close as possible to the part being inspected and no greater than 18 inches from the surface of the part.

A320

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# SERVICE BULLETIN

NOTE: Figure 2 provides examples of typical cracks found at forward and aft locations of the radome

exterior.

• If any crack IS found, proceed to Step 2

.

• If crack IS NOT found, proceed with Step 3.

2) (RC) If a ny crack is found, remove and replace the IFE Radome before further flight per LiveTV

AMM LTV

- 530 , section 4000.

NOTE : Seal the reveal area between Radome and Fairing with: (Refer to Figure 3)

• RTV

- 108 ( requires a 6 hour cure time prior to flight @ 77 d eg. F and 50% relative humidity )

,

• or alternate s ealant RTV

- 230A/B ( requires a 2 hour cure time prior to flight @ 77 d eg. F and 50%

relat ive humidity)

.

3) Restore the aircraft to normal condition, refer to Airbus A318/A319/A320 AMM and restore power
to IFE sys tem, refer to LiveTV AMM LTV

- 530 , section 4000.

C. Reporting Form

1) (RC) C omplete the “Reporting Form” and attach the completed in spection results to the STC

holder Technical Support AND Certification group s via e

- mail or fax

, as noted in S ection 2B

, with subject line heading of: “ Service Bulletin A320

- 53

- 006 and (Aircraft Registration Number) ”

.

A320

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# SERVICE BULLETIN

B

B (See Figure 3) BRIDGE FITTINGS AREA

TYP.

ABOVE SCREW HOLES
6.00 INCHES

INSPECTION

AREA

TYP. BRIDGE
FITTING
LOCATION 

# FWD

VIEW LOOKING DOWN

Radome External Visual Insp ection Areas

FIGURE 1

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# SERVICE BULLETIN

Figure 2

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# SERVICE BULLETIN

Radome Fairing Reveal

Figure 3

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# SERVICE BULLETIN

S ERVICE 

## B ULLETIN 

## REPORTING FORM

S ERVICE 

## B ULLETIN 

## T ITLE Airbus A318/ A 31 9/ A 320 Inspection of IFE Radome 

## S ERVICE 

## B ULLETIN 

## & R EVISION A320

- 53

- 00 6, Rev 0 1



## P LEASE PROVIDE THE FO LLOWING INFORMATION 

## : S ERVICE OR 

## W ORK 

## O RDER 

## N UMBER



## D ATE OF 

## A CCOMPLISHMENT



## L OCATION OF 

## A CCOMPLISHMENT



## A IRCRAFT 

## R EGISTRATION



## A CCOMPLISHING 

## T ECHNICIAN 

## N AME

AND 

## B ADGE 

## # (PRINT):


## R ADOME 

## S ERIAL 

## N UMBER 

## : N OT REQUIRED IF RADOM E IS NOT

REMOVED



## . A NY 

## R ADOME 

## D EFECTS ARE 

## O BSERVED



## . P ROVIDE DETAILS



## , e.g. location, crack length

, etc

. T OTAL 

## A IRFRAME 

## H OURS 

## : T OTAL 

## A IRFRAME 

## C YCLES 

## : T OTAL 

## R ADOME 

## H OURS 

## : T OTAL 

## R ADOME 

## C YCLES 

## : T OTAL 

## A IRFRAME 

## H OURS SIN CE IN IT IAL 

## STC INSTALLATION 

## : T OTAL AIRFRAME 

## C YCLES SINCE INITI AL 

## STC INSTALLATION 

## :

RECORD ANY ADDITIONAL INFORMATI ON BELOW 

## :

A320

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# SERVICE BULLETIN

E

- MAIL COMPLETED F ORMS TO :

D EPARTMENT N AME E

- mail


### LiveTV Certification

– attn.: Oscar Hernandez CertificationEngineering@livetv.net LiveTV Tech Support TechSupport@livetv.net



### A PPROVALS

FOR APPROVAL SIGNATURES SEE THE SIGNATURE MANIFEST AT THE END OF THIS

DOCUME NT IN THE LIVETV MASTER CONTROL SYSTEM.

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