SERVICE BULLETIN

Number: A320-53-006

Airbus A318/A319/A320

Inspection of IFE Radome

1. Planning Information

A. Effectivity

This service bulletin is applicable to all Airbus A318/A319/A320 aircraft with Radome P/N 5063-

100-xx (where XX designates the color option) installed in accordance with LiveTV STC 

ST00788SE.

B. Concurrent Requirement

None

C. Reason

This service bulletin provides the instruction to inspect the effected aircraft with STC ST00788SE

IFE radome installed for outer ply cracks. If cracks are found, the radome is to be 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 account for the type 

of damage described below, or for energy levels related to a comparable bird strike event with the 

aircraft empennage. Inspections accomplished in accordance with the LiveTV Service Bulletin 

Number A320-53-003 provided the basis for an analysis of this radome cracking issue. This

analysis determined that radome cracks could possibly propagate, allowing large 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 larger than 8 lbs could not separate.

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

Amendment Level 25-56 with Airbus electing to comply with 14CFR Part 25.571 to Amendment 

Level 91. The resulting certification Amendment Level for the aircraft empennage is an 8 lb 

object at Vcruise per 14CFR Part 25.631 for bird strike damage and a 4 lb object at Vcruise per 

14CFR Part 25.571(e)(1) for Damage Tolerance and Fatigue evaluation of structure. Therefore 

impact with the 10.5 lb radome could cause an unsafe condition. The severity of the unsafe 

condition would depend on the size, trajectory and orientation of the released radome piece(s) at 

impact. The 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 manufacturing 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 radome 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 this point 

forward in the SB.

D. Description

This service bulletin provides instructions for an external visual inspection 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 the operator accomplish the initial inspection within 3,900 Flight 

Hours (FH) following the release date of this service bulletin. This will ensure initial 

inspection per this SB within 3900 Flight Hours (FH).

2) It is recommended that the operator initialize a repetitive inspection every 3,900 FH 

thereafter.

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

4) Currently there is no terminating action.

5) Terminating 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 experienced personnel and may 

need to be revised upwards to suit operator’s circumstances. The estimated labor 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. Weight and Balance

None

I. Electrical Load Data

Not Changed

J. Software Accomplishment Summary

Not Applicable

K. References

• STC ST00788SE Airbus A318/A319/A320 aircraft

• LiveTV IPC LTV-605

• LiveTV IPC LTV-615

• LiveTV AMM LTV-530

• 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 Rev IR (A320 FR)

• LiveTV SIL-0059

• AC 20-176

• 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 Date

00 Initial Release 27 August 2014

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

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SERVICE BULLETIN

2. Material Information

A. Material – Availability

All parts and materials 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 to the location(s) listed below:

STC holder Maintenance Technical Support Phone: (1) 407-812-2538

Fax: (1) 407-812-2526

Email: TechSupport@LiveTV.net

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 Quantity Source

Cor-ban 27L Compound, Antiseize A/R Commercially Available

RTV-108 or RTV230 A/BSealant or Sealant, 

Rapid Cure A/R Commercially Available

D. LiveTV Supplied Material 

Mfg. Part Number Nomenclature Quantity Source

5063-100-XX

(XX refers to color 

option)

Radome 1 per A/C

(as required)

LiveTV

E. Operator/Customer Supplied Material

Not applicable

F. Re-identified Parts

None

G. Tooling – Availability

(1) Standard mechanic tools may be used.

(2) The following special tools are required:

Mfg. Part 

Number Nomenclature Quantity Source

A/R *Torque Wrench, 65-100 

inch pounds

1 Commercially Available

A/R Access maintenance stand 

to reach Crown area

1 Commercially Available

*Required if radome is removed and replaced.

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SERVICE BULLETIN

3. Accomplishment Instructions

• For Aircraft that 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. General

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). The 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 safe for maintenance; refer to Airbus A318/A319/A320 AMM “INTRO”.

b) Remove power to the IFE system; refer to LiveTV AMM LTV-535, section 4000.

c) Gain access the radome in the 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.

• 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 which could affect the accuracy of the inspection, except for paint, 

primer, 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.

Note: 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 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: 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 any crack is found, remove and replace the IFE Radome before further flight per LiveTV 

AMM LTV-535, 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 deg. F and 50% relative humidity),

• or alternate sealant RTV-230A/B (requires a 2 hour cure time prior to flight @ 77 deg. F and 50% 

relative humidity).

3) Restore the aircraft to normal condition, refer to Airbus A318/A319/A320 AMM and restore power 

to IFE system, refer to LiveTV AMM LTV-535, section 4000.

C. Reporting Form

1) (RC) Complete the “Reporting Form” and attach the completed inspection results to the STC 

holder Technical Support AND Certification groups via e-mail or fax, as noted in Section 2B, 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. General

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). The 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

d) Ensure aircraft 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 the 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.

• 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 which could affect the accuracy of the inspection, except for paint, 

primer, 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.

Note: 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 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: 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 any 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 deg. F and 50% relative humidity),

• or alternate sealant RTV-230A/B (requires a 2 hour cure time prior to flight @ 77 deg. F and 50% 

relative humidity).

3) Restore the aircraft to normal condition, refer to Airbus A318/A319/A320 AMM and restore power 

to IFE system, refer to LiveTV AMM LTV-530, section 4000.

C. Reporting Form

1) (RC) Complete the “Reporting Form” and attach the completed inspection results to the STC 

holder Technical Support AND Certification groups via e-mail or fax, as noted in Section 2B, with 

subject line heading of: “Service Bulletin A320-53-006 and (Aircraft Registration Number)”.

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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 Inspection 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

SERVICE BULLETIN REPORTING FORM

SERVICE BULLETIN TITLE Airbus A318/A319/A320 Inspection of IFE Radome

SERVICE BULLETIN & REVISION A320-53-006, Rev 01

PLEASE PROVIDE THE FOLLOWING INFORMATION:

SERVICE OR WORK ORDER NUMBER

DATE OF ACCOMPLISHMENT

LOCATION OF ACCOMPLISHMENT

AIRCRAFT REGISTRATION

ACCOMPLISHING TECHNICIAN NAME

AND BADGE # (PRINT):

RADOME SERIAL NUMBER :

NOT REQUIRED IF RADOME IS NOT 

REMOVED.

ANY RADOME DEFECTS ARE 

OBSERVED. PROVIDE DETAILS, e.g.

location, crack length, etc.

TOTAL AIRFRAME HOURS: TOTAL AIRFRAME CYCLES:

TOTAL RADOME HOURS: TOTAL RADOME CYCLES:

TOTAL AIRFRAME HOURS SINCE INITIAL 

STC INSTALLATION:

TOTAL AIRFRAME CYCLES SINCE INITIAL 

STC INSTALLATION:

RECORD ANY ADDITIONAL INFORMATION BELOW:

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SERVICE BULLETIN

E-MAIL COMPLETED FORMS TO:

DEPARTMENT NAME E-mail

LiveTV Certification – attn.: Oscar Hernandez CertificationEngineering@livetv.net 

LiveTV Tech Support TechSupport@livetv.net 

APPROVALS

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

DOCUMENT IN THE LIVETV MASTER CONTROL SYSTEM.

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