SERVICE BULLETIN

B737-53-0011

 29 Mar, 2013 Rev.00

© LiveTV All rights reserved. Page 1 of 13

Number: B737-53-0011

B737-600/700/800/900/900ER 

Inspection of IFE Radome 

1. Planning Information 

A. Effectivity 

1.) Effectivity (Group 1) 

This service bulletin is applicable to all Boeing 737 aircraft with Radome P/N 5063-100-xx 

installed in accordance with STC ST00284BO (B737-700/800/900/900ER). 

2.) Effectivity (Group 2) 

This service bulletin is applicable to all Boeing 737 aircraft with Radome P/N 5063-101-xx 

installed in accordance with STC ST02887AT (B737-600/700/800). 

B. Concurrent Requirement 

 None 

C. Reason 

This service bulletin gives the instructions to inspect Boeing 737 with STC ST00284BO or 

ST02887AT aircraft radomes installed for outer ply cracks. If cracks are found the radome is to 

be replaced before further flights. Manufacturing variation due to lack of dimensional controls can 

result in the introduction of preload stress on the radome. Preload stress combined with flight or 

handling stress such as stepping on the radome fairing assembly, may initiate a crack. The 

radome manufacturing drawings were revised on September 13, 2010 to add a control dimension 

which was incorporated at radome serial number 498(F) and up. “F” designations identify 

radome units that have a 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. 

This service bulletin is a result of a safety analysis performed by STC holder and the FAA based 

on knowledge that the Boeing 737NG (737-600, -700, -800 and -900) aircraft is not certified to 

account for this type of damage (or energy levels related to a comparable bird strike event) CFR 

25.631 and findings of inspections accomplished in accordance with the LiveTV Service Bulletin 

Number B737-53-007. The analysis determined that radome cracks could possibly propagate, 

allowing larger 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 Boeing 737NG (737-600, -700, -800 and -900) aircraft (TCDS A16WE) are certified to CFR 

Part 25 Amdt. 25-77 with risk for pieces having weight / energy exceeding the requirements of 

CFR 25.571e(1) for 4 pound bird strikes unless the structure was significantly modified. Boeing 

document D010A001 does not show the empennage to be modified; therefore these aircraft are 

not certified to sustain the damage from an impact with an 8 lb. bird. The Boeing 737-600, -700, -

800 and -900 are certified to CFR 25.571 Amendt. 25-77 and does include discrete source 

evaluation from impact with a 4-pound bird at Vc (velocity at cruise) at sea level to 8,000 feet. 

Therefore impact with the 10.5 lb radome could cause an unsafe condition. However the severity 

of the unsafe condition will depend on the size of the released piece, the trajectory and 

orientation of the radome pieces at impact. The radome shape is primarily an oval 44 inches wide 

and 63 inches long and 5.7 inches 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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B737-53-0011

 29 Mar, 2013 Rev.00

© LiveTV All rights reserved. Page 2 of 13

Analysis has set the prescribed repeated inspection intervals for identification and replacement of 

a cracked radome which may coincide with the ICA 100 day radome fairing bulb seal inspections. 

D. Description 

This service bulletin provides instructions for an external visual inspection for cracks of the IFE (In 

Flight Entertainment) radome. If cracks are found the radome is to be replaced before further 

flight. 

E. Accomplishment Recommendation 

1) The Federal Administration (FAA) will possibly release an Airworthiness Directive related to 

this service bulletin. If released the Airworthiness Directive will make the compliance task 

and times given in the service bulletin mandatory. 

2) It is recommended that the operator accomplish the initial inspection within 1250 Flight Hours 

(FH) from 120 days following the release date of this service bulletin. This will ensure initial 

inspection per the SB within 1250 Flight Hours (FH) from the end of the 120 days. 

3) It is recommended that the operator initialize a repetitive inspection every 1250 FH thereafter. 

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

5) Currently there is no terminating action. 

6) Terminating action is currently under evaluation by the FAA and STC holder. 

F. Regulatory Approval 

The FAA proposes to mandate inspections by regulatory action and issue an Airworthiness 

Directive. 

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. 
SERVICE BULLETIN

B737-53-0011

 29 Mar, 2013 Rev.00

© LiveTV All rights reserved. Page 3 of 13

H. Weight and Balance 

None 

I. Electrical Load Data 

Not Changed 

J. Software Accomplishment Summary 

Not Applicable 

K. References 

• STC ST00284BO (B737-700/800/900/ER) 

• LiveTV IPC LTV-625 

• LiveTV AMM LTV-580 

• LiveTV Radome Installation Drawing 73SN2100 (B737-700/800/900/ER) for STC 

ST00284BO 

• Boeing AMM 737-600/700/800/900 

• STC ST02887AT (B737-600/700/800) 

• LiveTV IPC LTV-610 

• LiveTV AMM LTV-565 

• LiveTV Radome Installation Drawings for STC ST02887AT: 

• 67422017 Rev C (B737-600) 

• 67432017 Rev K (B737-700) 

• 67442017 Rev D (B737-800) 

• LiveTV SIL-0059 

• AC 20-176 

• AAS-NDT-09-001 Non-Destructive Testing Manual for LiveTV Alterations and Repairs 

L. Publications Affected 

None 

M. Interchanging and Intermixing Parts 

None 

N. Revision History 

Revision Reason Date 

00 Initial Release 29 March 2013 

 

 
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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 Phone: (1) 407-240-3265 

2544 E. Landstreet Rd. Fax : (1) 407-240-8664 

Orlando, FL 32824 

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 

Jane Anne Webb 

Director, Aircraft Certification

Email: janeanne.webb@livetv.net 

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 

RTV-230 A/B 

Sealant or 

Sealant, Rapid 

Cure 

A/R Commercially Available 
SERVICE BULLETIN

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© LiveTV All rights reserved. Page 5 of 13

D. LiveTV Supplied Material 

Mfg. Part Number Nomenclature Quantity Source 

5063-100-V3 

(Group 1) Radome 1 per A/C 

(as required) 

LiveTV 

5063-101-V2 

(Group 2) 

E. Operator/Customer Supplied Material 

Mfg. Part Number Nomenclature Quantity Source 

None 

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 

*Torque Wrench, 65-100 

inch pounds 

1 Commercially Available 

Access maintenance 

stand to reach Crown 

area 

1 Commercially Available 

*May be required. 
SERVICE BULLETIN

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© LiveTV All rights reserved. Page 6 of 13

3. Accomplishment Instructions 

3.1 (Group 1) 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). If this service bulletin is mandated by an airworthiness directive (AD), the steps 

identified as RC must be done to comply with the AD. 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 in SB, if the RC step can be done and the airplane 

put back in a serviceable condition. 

1) Preparation: 

a) Ensure aircraft is safe for maintenance, refer to with Boeing 737-700/800/900 AMM. 

b) Remove power to the IFE system, refer to LiveTV AMM LTV-580, section 4000. 

c) Gain access the radome in the crown area. 

B. Work Instructions 

 

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

and refer to Figure 4 for visual inspection steps. (RC) 

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) If any crack is found, remove and replace the IFE Radome before further flight per LiveTV AMM 

LTV-580, section 4000. (RC)

NOTE: Seal the reveal area between Radome and Fairing with RTV-108 which 

 requires 6 hour cure time prior to flight or alternate Sealant RTV-230A/B 

 which requires 2 hour cure time prior to flight. Refer to figure 3. 

3) Restore the aircraft to normal condition, refer to Boeing 737- 700/800/900 AMM and restore 

power to IFE system, refer to LiveTV AMM LTV-580, section 4000. 

C. Reporting Form 

1) If cracks are found, complete the “Reporting Form” and attach the completed inspection results to 

STC holder Certification Jane Anne Webb via email to janeanne.webb@livetv.net with subject 

line heading of: (Service Bulletin Number) and (Aircraft Registration Number). 
SERVICE BULLETIN

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 29 Mar, 2013 Rev.00

© LiveTV All rights reserved. Page 7 of 13

3.2 (Group 2) 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). If this service bulletin is mandated by an airworthiness directive (AD), the steps 

identified as RC must be done to comply with the AD. 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 in SB, if the RC step can be done and the airplane 

put back in a serviceable condition. 

1) Preparation 

a) Ensure aircraft is safe for maintenance, refer to Boeing 737-600/700/800 AMM. 

b) Remove power to the IFE system, refer to LiveTV AMM LTV-565, section 4000. 

c) Gain access the radome in the crown area. 

B. Work Instructions 

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

and refer to Figure 4 for visual inspection steps. (RC) 

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) If any crack is found, remove and replace the IFE Radome before further flight per LiveTV AMM 

LTV-565, section 4000. (RC)

NOTE: Seal the reveal area between Radome and Fairing with RTV-108 which 

 requires 6 hour cure time prior to flight or alternate Sealant RTV-230A/B 

 which requires 2 hour cure time prior to flight. Refer to figure 3. 

3) Restore the aircraft to normal condition, refer to Boeing 737-600/700/800 AMM and restore power 

to the IFE system, refer to LiveTV AMM LTV-565, section 4000. 

C. Reporting Form 

1) If cracks are found, complete the “Reporting Form” and attach the completed inspection results to 

STC holder Certification Jane Anne Webb via email to janeanne.webb@livetv.net with subject 

line heading of: (Service Bulletin Number) and (Aircraft Registration Number). 

. 
SERVICE BULLETIN

B737-53-0011

 29 Mar, 2013 Rev.00

© LiveTV All rights reserved. Page 8 of 13

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 

(Radome 5063-100 is shown as example, 

5063-101 has more than one lightning diverter strip)
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Figure 2 
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Radome Fairing Reveal 

Figure 3 
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Radome Visual Inspection Procedures 

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

2) Inspection area should have clear access to the inspection surface.

3) 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” in length, could be seen without the need of 

magnification and were visible through the paint layer from a typical distance of 18”. 

4) 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 such as a flashlight or drop light directed at 

an angle to the surface being inspected as shown in below view. 

5) 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. 

Radome Visual Inspection Procedures 

Figure 4 
SERVICE BULLETIN

B737-53-0011

 29 Mar, 2013 Rev.00

© LiveTV All rights reserved. Page 12 of 13

SB REPORTING FORM 

SERVICE BULLETIN & REVISION B737-53-0011 Rev 00 

SERVICE BULLETIN TITLE B737-600/700/800/900/ER Inspection of 

IFE Radome

PLEASE PROVIDE THE FOLLOWING INFORMATION: 

SERVICE OR WORK ORDER NUMBER

DATE OF ACCOMPLISHMENT

LOCATION OF ACCOMPLISHMENT

AIRCRAFT REGISTRATION

ACCOMPLISHING TECHNICIAN NAME

RADOME SERIAL NUMBER : 

REQUIRED IF RADOME IS REMOVED

IF ANY RADOME DEFECTS ARE 

OBSERVED. PROVIDE DETAILS, e.g.

location, crack length etc. 

RECORD ANY ADDITIONAL INFORMATION BELOW:

IF CRACKS ARE FOUND E-MAIL COMPLETED FORMS TO: 

DEPARTMENT NAME Certification – Jane Anne Webb

E-MAIL janeanne.webb@livetv.net 
SERVICE BULLETIN

B737-53-0011

 29 Mar, 2013 Rev.00

© LiveTV All rights reserved. Page 13 of 13

APPROVALS 

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

DOCUMENT IN THE MASTER CONTROL SYSTEM.