Federal Register / Vol. 79, No. 48 / Wednesday, March 12, 2014 / Proposed Rules 13931 

(2) Model A340–211, –212, –213, –311, 

–312, and –313 airplanes, all manufacturer 

serial numbers, on which Airbus 

Modification 48825D42865 has been 

embodied in production; except for airplanes 

on which Airbus Modification 55606 or 

40161 has been embodied. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 92. 

(e) Reason 

This AD was prompted by a report of 

contact between certain electrical harnesses 

and the hatrack rod that could cause chafing 

between the harnesses and surrounding 

structure. We are issuing this AD to prevent 

chafing and possible short circuit of two 

oxygen chemical generator containers in 

different wiring routes, which could result in 

malfunction of the electrical opening of all 

the containers connected to these routes. 

Such conditions, during a sudden 

depressurization event, could result in lack 

of oxygen and consequent injuries to airplane 

occupants. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Modification 

Within 24 months after the effective date 

of this AD: Modify the routing of electrical 

harnesses 1523VB on the left-hand side and 

1524VB on the right-hand side, at the level 

of the door 3 area between frames 53.6 and 

53.8, and between stringers 14 and 15, in 

accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A330–92–3098 or A340–92–4084, 

both dated January 11, 2013, as applicable. 

(h) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to ATTN: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone (425) 227–1138; fax (425) 227– 

1149. Information may be emailed to: 9- 

ANM-116-AMOC-REQUESTS@faa.gov. 

Before using any approved AMOC, notify 

your appropriate principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office/

certificate holding district office. The AMOC 

approval letter must specifically reference 

this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer, use these actions if they are 

FAA-approved. Corrective actions are 

considered FAA-approved if they were 

approved by the State of Design Authority (or 

its delegated agent, or by the DAH with a 

State of Design Authority’s design 

organization approval). For a repair method 

to be approved, the repair approval must 

specifically refer to this AD. You are required 

to ensure the product is airworthy before it 

is returned to service. 

(i) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) European 

Aviation Safety Agency (EASA) 

Airworthiness Directive 2013–0196, dated 

August 28, 2013, for related information. 

This MCAI may be found in the AD docket 

on the Internet at http://www.regulations.gov 

by searching for and locating it in Docket No. 

FAA–2014–0140. 

(2) For service information identified in 

this AD, contact Airbus, SAS Airworthiness 

Office—EAL, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

5 61 93 36 96; fax +33 5 61 93 45 80; email 

airworthiness.A330-A340@airbus.com; 

Internet http://www.airbus.com. You may 

view this service information at the FAA, 

Transport Airplane Directorate, 1601 Lind 

Avenue SW., Renton, WA. For information 

on the availability of this material at the 

FAA, call 425–227–1221. 

Issued in Renton, Washington, on February 

28, 2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–05424 Filed 3–11–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0141; Directorate 

Identifier 2013–NM–024–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 727–100 

series airplanes. This proposed AD is 

intended to complete certain mandated 

programs intended to support the 

airplane reaching its limit of validity 

(LOV) of the engineering data that 

support the established structural 

maintenance program. For certain 

airplanes, this proposed AD would 

require repetitive inspections for 

cracking in stringers or frames until 

modification, and repair if necessary. 

We are proposing this AD to detect and 

correct cracking in stringers or frames 

originating at or near stringer-to-frame 

attachment fastener holes, which could 

result in reduced structural integrity of 

the airplane, and decompression of the 

cabin. 

DATES: We must receive comments on 

this proposed AD by April 28, 2014. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, WA 98124–2207; 

telephone 206–544–5000, extension 1; 

fax 206–766–5680; Internet https://

www.myboeingfleet.com. You may view 

this referenced service information at 

the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., 

Renton, WA. For information on the 

availability of this material at the FAA, 

call 425–227–1221. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2014– 

0141; or in person at the Docket 

Management Facility between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Office 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Chandra Ramdoss, Aerospace Engineer, 

Airframe Branch, ANM–120L, FAA, Los 

Angeles Aircraft Certification Office 

(ACO), 3960 Paramount Boulevard, 

Lakewood, CA 90712–4137; phone: 

(562) 627–5239; fax: (562) 627–5210; 

email: chandraduth.ramdoss@faa.gov. 

SUPPLEMENTARY INFORMATION: 


tkelley on DSK3SPTVN1PROD with PROPOSALS
13932 Federal Register / Vol. 79, No. 48 / Wednesday, March 12, 2014 / Proposed Rules 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposal. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2014–0141; Directorate Identifier 2013– 

NM–024–AD’’ at the beginning of your 

comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD because of those 

comments. 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

As described in FAA Advisory 

Circular 120–104 (http://www.faa.gov/

documentLibrary/media/Advisory_

Circular/120-104.pdf), several programs 

have been developed to support 

initiatives that will ensure the 

continued airworthiness of aging 

airplane structure. The last element of 

those initiatives is the requirement to 

establish a limit of validity (LOV) of the 

engineering data that support the 

structural maintenance program under 

14 CFR 26.21. This proposed AD is the 

result of an assessment of the previously 

established programs by Boeing during 

the process of establishing the LOV for 

The Boeing Company Model 727 

airplanes. The actions specified in this 

proposed AD are necessary to complete 

certain programs to ensure the 

continued airworthiness of aging 

airplane structure and to support an 

airplane reaching its LOV. 

Fatigue tests conducted by the 

manufacturer show that repeated 

pressurization cycles result in fatigue 

cracks at some of the stringer-to-frame 

connections along the crown of the 

fuselage. Undetected cracking at the 

stringer-to-frame connections along the 

crown of the fuselage, and the lack of 

stringer-to-body frame tie clips in the 

crown area of the fuselage, could result 

in damage to wire bundles and control 

cables for the flight control system, 

reduced structural integrity of the 

airplane, and decompression of the 

cabin. 

Related Rulemaking 

On January 16, 1990, we issued AD 

90–06–09, Amendment 39–6488 (55 FR 

8370, March 7, 1990), which applied to 

certain Boeing Model 727 series 

airplanes. AD 90–06–09 required 

structural modifications specified in 

Section 3 of Boeing Document D6– 

54860, ‘‘Aging Airplane Service Bulletin 

Structural Modification and Inspection 

Program—Model 727,’’ Revision C, 

dated December 11, 1989. AD 90–06–09 

was prompted by a report by the Model 

727 Structures Working Group. The 

actions required by AD 90–06–09 were 

intended to prevent structural failure of 

the airplane. One of the requirements of 

AD 90–06–09 was to do the 

modification in accordance with Boeing 

Service Bulletin 727–53–0041, Revision 

4 dated July 27, 1973, prior to the 

accumulation of 60,000 flights or 4 years 

whichever occurs later. 

On March 23, 1994, we issued AD 94– 

07–08, Amendment 39–8866 (59 FR 

14545, March 29, 1994), which applied 

to certain Boeing Model 727 series 

airplanes. AD 94–07–08 required 

structural inspections specified in 

section 4 and appendices A.4 and B.4 of 

Boeing Document Number D6–54860, 

‘‘Aging Airplane Service Bulletin 

Structural Modification and Inspection 

Program—Model 727,’’ Revision G, 

dated March 5, 1993, and corrective 

actions if necessary. The corrective 

actions included doing small repairs 

and modifications. AD 94–07–08 was 

prompted by reports of incidents 

involving fatigue cracking and 

corrosion. The actions required by AD 

94–07–08 included only postmodification visual inspections per 

Boeing Service Bulletin 727–53–0041, 

Revision 5, dated January 25, 1990. 

This proposed rule requires repetitive 

inspections on those airplanes that have 

not yet accomplished the modification 

that is required by AD 90–06–09. 

Relevant Service Information 

We reviewed Boeing Service Bulletin 

727–53–0041, Revision 6, dated 

September 5, 1991. For information on 

the procedures and compliance times, 

see this service information at http://

www.regulations.gov by searching for 

Docket No. FAA–2014–0141. 

FAA’s Determination 

We are proposing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. 

Proposed AD Requirements 

This proposed AD would require 

accomplishing the actions specified in 

the service information described 

previously. 

Costs of Compliance 

We estimate that this proposed AD 

affects 2 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this proposed AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per product Cost on U.S. 

operators 

Inspection and repetitive inspections.60 work-hours × $85 per hour 

= $5,100 per inspection 

cycle.

$0 $5,100 per inspection ............ $10,200 per inspection. 

We estimate the following costs to do 

any necessary modifications that would 

be required based on the results of the 

proposed inspection. We have no way of 

determining the number of aircraft that 

might need these modifications: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per product 

Modification .......................... 600 work-hours × $85 per hour = $51,000 per inspection cycle.Up to $11,481 .................... Up to $62,481 per modification. 


tkelley on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 79, No. 48 / Wednesday, March 12, 2014 / Proposed Rules 13933 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. Subtitle VII: 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701: 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would not have a 

substantial direct effect on the States, on 

the relationship between the national 

Government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify this proposed regulation: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Is not a ‘‘significant rule’’ under 

the DOT Regulatory Policies and 

Procedures (44 FR 11034, February 26, 

1979), 

(3) Will not affect intrastate aviation 

in Alaska, and 

(4) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

The Boeing Company: Docket No. FAA– 

2014–0141; Directorate Identifier 2013– 

NM–024–AD. 

(a) Comments Due Date 

We must receive comments by April 28, 

2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

Model 727–100 series airplanes, certificated 

in any category, as identified in Boeing 

Service Bulletin 727–53–0041, Revision 6, 

dated September 5, 1991, unless previously 

modified in accordance with the service 

information specified in paragraphs (c)(1), 

(c)(2) or (c)(3) of this AD. 

(1) Boeing Service Bulletin 727–53–0041, 

Revision 4, dated July 27, 1973. 

(2) Boeing Service Bulletin 727–53–0041, 

Revision 5, dated January 25, 1990. 

(3) Boeing Service Bulletin 727–53–0041, 

Revision 6, dated September 5, 1991. 

Note 1 to paragraph (c) of this AD: Boeing 

Service Bulletin 727–53–0041, Revision 4, 

dated July 27, 1973 is specified in Boeing 

Document D6–54860 ‘‘Aging Airplane 

Service Bulletin Structural Modification 

Program—Model 727,’’ Revision C, dated 

December 11, 1989 as mandated by AD 90– 

06–09, Amendment 39–6488 (55 FR 8370, 

March 7, 1990). 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Unsafe Condition 

This AD is intended to complete certain 

mandated programs intended to support the 

airplane reaching its limit of validity (LOV) 

of the engineering data that support the 

established structural maintenance program. 

We are issuing this AD to detect and correct 

cracking in stringers or frames originating at 

or near stringer-to-frame attachment fastener 

holes, which could result in reduced 

structural integrity of the airplane, and 

decompression of the cabin. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspections 

Before the accumulation of 16,000 total 

flight cycles, or within 3,000 flight cycles 

after the effective date of this AD, whichever 

occurs later, do a high frequency eddy 

current inspection and a general visual 

inspection for cracking in stringers and 

frames originating at or near stringer-to-frame 

attachment fastener holes, in accordance 

with the Accomplishment Instructions of 

Boeing Service Bulletin 727–53–0041, 

Revision 6, dated September 5, 1991. Repeat 

the inspections thereafter at intervals not to 

exceed 6,000 flight cycles until the 

modification specified by paragraph (h) of 

this AD is accomplished. If any crack is 

found during any inspection required by 

paragraph (g) of this AD: Before further flight, 

repair or modify the affected stringer-toframe attachment locations, in accordance 

with Part V, ‘‘Repair Data’’ of the 

Accomplishment Instructions of Boeing 

Service Bulletin 727–53–0041, Revision 6, 

dated September 5, 1991. 

(h) Modification 

Modifying the affected stringer-to-frame 

attachment locations, in accordance with Part 

IV, ‘‘Preventive Modification Data,’’ of the 

Accomplishment Instructions of Boeing 

Service Bulletin 727–53–0041, Revision 6, 

dated September 5, 1991, terminates the 

repetitive inspections required by paragraph 

(g) of this AD. 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Los Angeles Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in 

paragraph (j)(1) of this AD. Information may 

be emailed to: 9-ANM-LAACO-AMOCREQUESTS@faa.gov. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/

certificate holding district office. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Los Angeles 

Aircraft Certification Office (ACO) to make 

those findings. For a repair method to be 

approved, the repair must meet the 

certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(j) Related Information 

(1) For more information about this AD, 

contact Chandra Ramdoss, Aerospace 

Engineer, Airframe Branch, ANM–120L, 

FAA, Los Angeles Aircraft Certification 

Office (ACO), 3960 Paramount Boulevard, 

Lakewood, CA 90712–4137; phone: (562) 

627–5239; fax: (562) 627–5210; email: 

chandraduth.ramdoss@faa.gov. 

(2) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, WA 98124–2207; telephone 206– 

544–5000, extension 1; fax 206–766–5680; 

Internet https://www.myboeingfleet.com. You 

may view this referenced service information 

at the FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, WA. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 


tkelley on DSK3SPTVN1PROD with PROPOSALS
13934 Federal Register / Vol. 79, No. 48 / Wednesday, March 12, 2014 / Proposed Rules 

Issued in Renton, Washington, on March 5, 

2014. 

Suzanne Masterson, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–05428 Filed 3–11–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0863; Directorate 

Identifier 2012–NM–108–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Supplemental notice of 

proposed rulemaking (NPRM); 

reopening of comment period. 

SUMMARY: We are revising an earlier 

proposed airworthiness directive (AD) 

for certain The Boeing Company Model 

737–300, –400, –500, –600, –700, 

–700C, –800, –900, and –900ER series 

airplanes. The NPRM proposed to 

require installing a new tail strobe light 

housing and a new disconnect bracket, 

and changing the wire bundles. The 

NPRM was prompted by a review of the 

tail strobe light installation, which 

revealed that the tail strobe light is not 

electrically bonded to primary structure 

of the airplane. This action revises the 

NPRM by adding, for certain airplanes, 

an inspection to determine if sealant is 

applied and corrective actions if 

necessary. We are proposing this 

supplemental NPRM (SNPRM) to 

prevent, in case of a direct lightning 

strike to the tail strobe light, damage to 

the operation of other critical airplane 

systems due to electromagnetic coupling 

and large transient voltages, and damage 

to the control mechanisms or surfaces 

due to a fire, which could result in loss 

of control of the airplane. Since these 

actions impose an additional burden 

over that proposed in the NPRM, we are 

reopening the comment period to allow 

the public the chance to comment on 

these proposed changes. 

DATES: We must receive comments on 

this SNPRM by April 28, 2014. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590, between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. 

For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, WA 98124–2207; telephone 

206–544–5000, extension 1; fax 206– 

766–5680; Internet https://

www.myboeingfleet.com. You may view 

this referenced service information at 

the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., 

Renton, WA 98057–3356. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2012– 

0863; or in person at the Docket 

Management Facility between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Office 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Marie Hogestad, Aerospace Engineer, 

Systems and Equipment Branch, FAA, 

ANM–130S, Seattle Aircraft 

Certification Office, 1601 Lind Avenue 

SW., Renton, Washington 98057–3356; 

phone: (425) 917–6418; fax: (425) 917– 

6590; email: marie.hogestad@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2012–0863; Directorate Identifier 

2012–NM–108–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD because of those 

comments. 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

We issued an NPRM to amend 14 CFR 

part 39 by adding an AD that would 

apply to certain The Boeing Company 

Model 737–300, –400, –500, –600, –700, 

–700C, –800, –900, and –900ER series 

airplanes. The NPRM published in the 

Federal Register on September 6, 2012 

(77 FR 54848). The NPRM proposed to 

require installing a new tail strobe light 

housing and a new disconnect bracket, 

and changing the wire bundles. 

Actions Since Previous NPRM (77 FR 

54848, September 6, 2012) Was Issued 

Since we issued the NPRM (77 FR 

54848, September 6, 2012), we have 

reviewed Boeing Special Attention 

Service Bulletin 737–33–1146, Revision 

1, dated July 9, 2013. We referred to 

Boeing Special Attention Service 

Bulletin 737–33–1146, dated November 

2, 2011, as the appropriate source of 

service information for accomplishing 

certain actions specified in the NPRM. 

Boeing Special Attention Service 

Bulletin 737–33–1146, Revision 1, dated 

July 9, 2013, adds procedures for 

airplanes on which the actions specified 

in Boeing Special Attention Service 

Bulletin 737–33–1146, dated November 

2, 2011, have been done, for a general 

visual inspection to ensure there is fillet 

sealant between the disconnect bracket 

and the receptacle connector D44582J, 

and on the fasteners, and corrective 

actions if necessary. The corrective 

actions include applying sealant. Boeing 

Special Attention Service Bulletin 737– 

33–1146, Revision 1, dated July 9, 2013, 

also does the following: 

• Incorporates the data given in 

Boeing Service Bulletin Information 

Notice 737–33–1146 IN 01, dated 

November 11, 2011, which changes 

Group 1, Configuration 1, to Group 1, 

and changes Group 1, Configuration 2, 

to Group 4. 

• Improves the tail strobe light 

installation work instructions (adds an 

alternate work instruction to remove 

electrical power, adds an optional work 

instruction to improve access, adds the 

process specification for the installation 

of a blind insert, adds a new work 

instruction step, and figure, to do the 

drilling tasks before parts are cleaned 

for bonding, removes the undefined 


tkelley on DSK3SPTVN1PROD with PROPOSALS