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
Federal Register / Vol. 79, No. 48 / Wednesday, March 12, 2014 / Proposed Rules 13935 

cleaning method CM 3, and clarifies the 

required minimum clearance between 

the disconnect bracket and the adjacent 

station (STA) 1156 bulkhead chord). 

We have revised paragraphs (c) and 

(g), and added new paragraph (h) to this 

SNPRM to refer to Boeing Special 

Attention Service Bulletin 737–33– 

1146, Revision 1, dated July 9, 2013, 

and have redesignated subsequent 

paragraph identifiers accordingly. 

Comments 

We gave the public the opportunity to 

comment on the NPRM (77 FR 54848, 

September 6, 2012). The following 

presents the comments received on the 

NPRM and the FAA’s response to each 

comment. 

Concurrence With the NPRM (77 FR 

54848, September 6, 2012) 

Boeing concurred with the NPRM (77 

FR 54848, September 6, 2012). 

United Airlines (UAL) stated it has no 

objections to the proposed actions in the 

NPRM (77 FR 54848, September 6, 

2012). 

Clarification of Effect of Winglet 

Installation 

Aviation Partners Boeing stated that 

the installation of winglets per STC 

ST00830SE ([http://rgl.faa.gov/

Regulatory_and_Guidance_Library/

rgstc.nsf/0/da95c49000906c7086257be

80044d3d9/$FILE/ST00830SE.pdf]) 

does not affect the accomplishment of 

the manufacturer’s service instructions. 

We have added new paragraph (c)(3) 

to this final rule to state that installation 

of ST00830SE does not affect the ability 

to accomplish the actions required by 

this final rule. Therefore, for airplanes 

on which ST00830SE is installed, a 

‘‘change in product’’ AMOC approval 

request is not necessary to comply with 

the requirements of 14 CFR 39.17. 

Request To Include an Additional 

Action To Remove the Tail Cone and 

Adjust the Costs Accordingly 

American Airlines (AAL) requested 

that we revise the NPRM (77 FR 54848, 

September 6, 2012), to include an 

additional action to remove the tail cone 

and also adjust the cost section for this 

action. AAL explained that due to the 

small size of the tail cone and additional 

equipment installed in this area, 

adequate clearance to install the bracket 

and associated wiring is problematic 

without removal of the tail cone. AAL 

reasoned that removing the tail cone 

could increase the labor requirement by 

up to 50 man-hours. 

We partially agree with AAL’s 

request, since Boeing has revised the 

service information to add an optional 

work instruction step to remove and 

keep the tail cone if necessary. We have 

revised paragraph (g) of this SNPRM to 

refer to Boeing Special Attention 

Service Bulletin 737–33–1146, Revision 

1, dated July 9, 2013. 

We disagree with the request to revise 

the Cost of Compliance section of this 

SNPRM. Removing the tail cone is 

optional and we have no way of 

determining how many operators will 

choose to do that action. The economic 

analysis of this SNPRM is limited only 

to the cost of actions proposed to be 

required and is based on the costs 

provided in Boeing Special Attention 

Service Bulletin 737–33–1146, Revision 

1, dated July 9, 2013. No change has 

been made to this SNPRM in this regard. 

Request for Use of Shield Splice in Lieu 

of Solder Sleeve 

AAL requested that we revise the 

NPRM (77 FR 54848, September 6, 

2012), to allow for use of the shield 

splice contained in splice kit D–150– 

0168 in lieu of solder sleeve 

BACS13CT3C. AAL explained that 

Figure 8, Flag Notes 3 and 9, of Boeing 

Special Attention Service Bulletin 737– 

33–1146, dated November 2, 2011, 

provides instructions to install a solder 

sleeve (BACS13CT3C) and splice kit (D– 

150–0168), respectively. AAL reasoned 

that splice kit D–150–0168 contains all 

of the required parts to properly splice 

the specified BMS 13–48 Type 12 wire, 

and that splice kit D–150–0168 is a 

much cleaner installation, maintains 

continuity of the existing shield, and is 

approved as a standard practice in 

Boeing Standard Wiring Practices 

Manual (SWPM) D6–54446, Section 20– 

30–12. 

We agree to allow for use of the shield 

splice contained in splice kit D–150– 

0168 in lieu of solder sleeve 

BACS13CT3C. Figure 8, Flag Note 3, of 

Boeing Special Attention Service 

Bulletin 737–33–1146, dated November 

2, 2011, specifies to add shielded 

ground wires. Solder sleeve 

BACS13CT3C supplied in the wire kit 

comes with a built-in ground-wire for an 

easier installation. Splice kit D–150– 

0168 does not have a ground wire. 

Therefore, if operators still want to 

supply the ground wires, Boeing SWPM 

20–10–15, referenced in Figure 8, Flag 

Note 3, of Boeing Special Attention 

Service Bulletin 737–33–1146, dated 

November 2, 2011, has the wire type 

information for the ground wires. We 

have added this exception to new 

paragraph (g)(1) of this SNPRM and 

added a note to paragraph (g)(1) of this 

SNPRM to include a reference to the 

SWPM. 

Clarification of Typographical Error in 

the Service Information 

The second sentence of note (c) of 

Figure 3 of the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 737–33–1146, Revision 

1, dated July 9, 2013, contains a 

typographical error and should instead 

read, ‘‘Maintain a minimum of 1.7 

diameter fastener edge margin on the 

disconnect bracket and the stiffener.’’ 

We have included the correct 

information in new paragraph (g)(2) of 

this SNPRM. 

Removal of Concurrent Requirements 

Paragraph (h) of the NPRM (77 FR 

54848, September 6, 2012) proposed to 

require concurrent installation of 

wingtips and tail strobe lights. However, 

the service information identified in 

paragraph (h) of the NPRM is 

conditional service information and is 

not required by this SNPRM. 

FAA’s Determination 

We are proposing this SNPRM 

because we evaluated all the relevant 

information and determined the unsafe 

condition described previously is likely 

to exist or develop in other products of 

these same type designs. Certain 

changes described above expand the 

scope of the NPRM (77 FR 54848, 

September 6, 2012). As a result, we have 

determined that it is necessary to reopen 

the comment period to provide 

additional opportunity for the public to 

comment on this SNPRM. 

Proposed Requirements of This SNPRM 

This SNPRM would require, for 

certain airplanes, installing a new tail 

strobe light housing and a new 

disconnect bracket, and changing the 

wire bundles. This SNPRM would also 

require, for certain other airplanes, an 

inspection to determine if sealant is 

applied, and corrective actions if 

necessary. 

Costs of Compliance 

We estimate that this proposed AD 

affects 1,433 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this proposed AD: 


tkelley on DSK3SPTVN1PROD with PROPOSALS
13936 Federal Register / Vol. 79, No. 48 / Wednesday, March 12, 2014 / Proposed Rules 

ESTIMATED COSTS

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

operators 

Installation for Model 737–300, –400, 

and –500 series airplanes, as identified in Boeing Special Attention 

Service Bulletin 737–33–1149, dated 

April 13, 2012 (396 U.S. registered 

airplanes).

Up to 32 work-hours × $85 

per hour = Up to $2,720.

Up to $14,886 ........... Up to $17,606 ........... Up to $6,971,976. 

Installation for Model 737–600, –700, 

–700C, –800, –900, and –900ER series airplanes, Group 1, as identified 

in Boeing Special Attention Service 

Bulletin 737–33–1146, Revision 1, 

dated July 9, 2013 (465 U.S. registered airplanes).

Up to 21 work-hours × $85 

per hour = Up to $1,785.

Up to 4,422 ............... Up to 6,207 ............... Up to 2,886,255. 

Installation for Model 737–600, –700, 

–700C, –800, –900, and –900ER series airplanes, Group 2, as identified 

in Boeing Special Attention Service 

Bulletin 737–33–1146, Revision 1, 

dated July 9, 2013 (83 U.S. registered airplanes).

Up to 21 work-hours × $85 

per hour = Up to $1,785.

Up to 2,496 ............... Up to 4,281 ............... Up to 355,323. 

Installation for Model 737–600, –700, 

–700C, –800, –900, and –900ER series airplanes, Group 3, as identified 

in Boeing Special Attention Service 

Bulletin 737–33–1146, Revision 1, 

dated July 9, 2013 (25 U.S. registered airplanes).

Up to 20 work-hours × $85 

per hour = Up to $1,700.

Up to 4,478 ............... Up to 6,178 ............... Up to 154,450. 

Installation for Model 737–600, –700, 

–700C, –800, –900, and –900ER series airplanes, Group 4, as identified 

in Boeing Special Attention Service 

Bulletin 737–33–1146, Revision 1, 

dated July 9, 2013 (464 U.S. registered airplanes).

Up to 21 work-hours × $85 

per hour = Up to $1,785.

Up to 4,423 ............... Up to 6,208 ............... Up to 2,880,512. 

Inspection for Model 737–600, –700, 

–700C, –800, –900 and –900ER series airplanes, as identified in Boeing 

Special Attention Service Bulletin 

737–33–1146, Revision 1, dated July 

9, 2013 (up to 1,037 U.S. registered 

airplanes).

Up to 2 work-hours × $85 

per hour = Up to $170.

0 ................................ Up to 170 .................. Up to 176,290. 

We estimate the following cost to 

apply sealant, based on the results of the 

proposed inspection. We have no way of 

determining the number of aircraft that 

might need this sealant application: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Sealant Application ........................... 1 work-hour × $85 per hour = $85 ............................................................. Negligible .... $85 

The parts cost to apply sealant 

between the disconnect bracket and the 

receptacle connector D44582J, and on 

the fasteners is not included in the 

estimate. It is considered ‘‘Parts & 

Materials Supplied by the Operator,’’ 

which is referenced in Boeing Special 

Attention Service Bulletin 737–33– 

1146, Revision 1, dated July 9, 2013. 

According to the manufacturer, all of 

the costs of this proposed AD may be 

covered under warranty, thereby 

reducing the cost impact on affected 

individuals. We do not control warranty 

coverage for affected individuals. As a 

result, we have included all costs in our 

cost estimate. 

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 


tkelley on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 79, No. 48 / Wednesday, March 12, 2014 / Proposed Rules 13937 

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– 

2012–0863; Directorate Identifier 2012– 

NM–108–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 

airplanes, certificated in any category, as 

identified in paragraphs (c)(1) and (c)(2) of 

this AD. 

(1) Model 737–300, –400, and –500 series 

airplanes, as identified in Boeing Special 

Attention Service Bulletin 737–33–1149, 

dated April 13, 2012. 

(2) Model 737–600, –700, –700C, –800, 

–900, and –900ER series airplanes, as 

identified in Boeing Special Attention 

Service Bulletin 737–33–1146, Revision 1, 

dated July 9, 2013. 

(3) Installation of Supplemental Type 

Certificate (STC) ST00830SE [(http://

rgl.faa.gov/RegulatorylandlGuidancel

Library/rgstc.nsf/0/da95c49000906c

7086257be80044d3d9/$FILE/

ST00830SE.pdf)] does not affect the ability to 

accomplish the actions required by this AD. 

Therefore, for airplanes on which STC 

ST00830SE is installed, a ‘‘change in 

product’’ alternative method of compliance 

(AMOC) approval request is not necessary to 

comply with the requirements of 14 CFR 

39.17. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 33, Lights. 

(e) Unsafe Condition 

This AD 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. 

We are issuing this AD 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. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Tail Strobe Light Installation for Model 

737–600, –700, –700C, –800, –900, and 

–900ER Series Airplanes 

For Model 737–600, –700, –700C, –800, 

–900, and –900ER series airplanes on which 

the actions specified in Boeing Special 

Attention Service Bulletin 737–33–1146, 

dated November 2, 2011, have not been done 

before the effective date of this AD: Within 

72 months after the effective date of this AD, 

install a new tail strobe light housing, install 

a new disconnect bracket, and change the 

wire bundles, in accordance with Part 1 of 

the Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 737–33– 

1146, Revision 1, dated July 9, 2013, except 

as required by paragraphs (g)(1) and (g)(2) of 

this AD. 

(1) Where Figure 8, Flag Note 3, of Boeing 

Special Attention Service Bulletin 737–33– 

1146, Revision 1, dated July 9, 2013, refers 

to solder sleeve BACS13CT3C, the shield 

splice contained in splice kit D–150–0168 

may be used in lieu of solder sleeve 

(BACS13CT3C), provided a ground wire is 

used. 

Note 1 to paragraph (g)(1) of this AD: 

Guidance for wire-type information for the 

ground wires may be found in Boeing 

Standard Wiring Practices Manual (SWPM) 

D6–54446, Section 20–10–15. 

(2) Where the second sentence of note (c) 

of Figure 3 of the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 737–33–1146, Revision 1, 

dated July 9, 2013, specifies to ‘‘Maintain a 

minimum of 1.7 Dimensions fastener edge 

margin on the disconnect bracket and the 

stiffener,’’ instead ‘‘Maintain a minimum of 

1.7 diameter fastener edge margin on the 

disconnect bracket and the stiffener.’’ 

(h) Sealant Installation for Model 737–600, 

–700, –700C, –800, –900, and –900ER Series 

Airplanes 

For Model 737–600, –700, –700C, –800, 

–900, and –900ER series airplanes, on which 

the actions specified in Boeing Special 

Attention Service Bulletin 737–33–1146, 

dated November 2, 2011, have been done 

before the effective date of this AD: Within 

72 months after the effective date of this AD, 

do a general visual inspection to ensure there 

is fillet sealant between the disconnect 

bracket and the receptacle connector 

D44582J, and on the fasteners, and do all 

applicable corrective actions, in accordance 

with Part 2 of the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 737–33–1146, Revision 1, 

dated July 9, 2013. Do all applicable 

corrective actions before further flight. 

(i) Tail Strobe Light Installation for Model 

737–300, –400, and –500 Series Airplanes 

For Model 737–300, –400, and –500 series 

airplanes: Within 72 months after the 

effective date of this AD, install a new tail 

strobe light housing, install a new disconnect 

bracket, and change the wire bundles, in 

accordance with the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 737–33–1149, dated April 

13, 2012. 

(j) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle 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 (k) of this AD. Information may be 

emailed to: 9-ANM-Seattle-ACO-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, Seattle 

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. 

(k) Related Information 

(1) For more information about this AD, 

contact Marie Hogestad, Aerospace Engineer, 

Systems and Equipment Branch, FAA, ANM– 


tkelley on DSK3SPTVN1PROD with PROPOSALS
13938 Federal Register / Vol. 79, No. 48 / Wednesday, March 12, 2014 / Proposed Rules 

130S, Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 98057– 

3356; phone: (425) 917–6418; fax: (425) 917– 

6590; email: marie.hogestad@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 98057– 

3356. 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. 2014–05426 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–2014–0142; Directorate 

Identifier 2012–NM–161–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

Airworthiness Directive (AD) 2008–17– 

02, AD 2012–08–03, and AD 2012–15– 

14, for certain Airbus Model A300 B4– 

2C, B4–103, and B4–203 airplanes; 

Model A300 B4–600, B4–600R, and F4– 

600R series airplanes, and Model C4– 

605R Variant F airplanes (collectively 

called A300–600 series airplanes); and 

Model A310 series airplanes. AD 2008– 

17–02, AD 2012–08–03, and AD 2012– 

15–14 currently require repetitive 

inspections of the forward lugs of the aft 

bearing at rib 5 of the main landing gear 

(MLG) on the left-hand (LH) and righthand (RH) wings, and repair if 

necessary; and installation of new 

bushes with increased interference fit in 

the forward lug of the aft bearing at rib 

5 of the MLG on the LH and RH wings. 

Since we issued AD 2008–17–02, AD 

2012–08–03, and AD 2012–15–14, we 

have received two reports of ruptured 

MLG rib 5 forward lugs that had been 

modified (bushes with increased 

interference fit). This proposed AD 

would add airplanes to the 

applicability; and would add, for certain 

airplanes, repetitive inspections of the 

MLG rib 5 aft bearing forward lugs, and 

repair if necessary. We are proposing 

this AD to detect and correct cracking of 

the forward lugs of the aft bearing at rib 

5 of the MLG on the LH and RH wings, 

which could affect the structural 

integrity of the MLG attachment, 

resulting in possible MLG collapse 

during landing or rollout. 

DATES: We must receive comments on 

this proposed AD by April 28, 2014. 

ADDRESSES: You may send comments 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, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed 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 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– 

0142; 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 Operations 

office (telephone (800) 647–5527) is in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

FOR FURTHER INFORMATION CONTACT: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone (425) 227–2125; 

fax (425) 227–1149. 

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–2014–0142; Directorate Identifier 

2012–NM–161–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 based on 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 

On July 31, 2008, we issued AD 2008– 

17–02, Amendment 39–15640 (73 FR 

47032, August 13, 2008), for certain 

Model A310 airplanes. 

On April 5, 2012, we issued AD 2012– 

08–03, Amendment 39–17019 (77 FR 

24367, April 24, 2012), for certain 

Model A300 B4–2C, B4–103, B4–203, 

B4–601, B4–603, B4–620, B4–622, B4– 

605R, B4–622R, F4–605R, F4–622R, C4– 

605R Variant F airplanes; and Model 

A310–203, –204, 221, –222, –304, –322, 

–324, and –325 airplanes. 

On July 23, 2012, we issued AD 2012– 

15–14, Amendment 39–17143 (77 FR 

46937, August 7, 2012), for certain 

Model A300 B4–2C, B4–103, B4–203, 

B4–601, B4–603, B4–620, B4–622, B4– 

605R, B4–622R, F4–605R, and F4–622R, 

and C4–605R Variant F airplanes. 

AD 2008–17–02, Amendment 39– 

15640 (73 FR 47032, August 13, 2008); 

AD 2012–08–03, Amendment 39–17019 

(77 FR 24367, April 24, 2012); and AD 

2012–15–14, Amendment 39–17143 (77 

FR 46937, August 7, 2012); require 

actions intended to address an unsafe 

condition on the products listed above. 

Since we issued AD 2008–17–02, 

Amendment 39–15640 (73 FR 47032, 

August 13, 2008); AD 2012–08–03, 

Amendment 39–17019 (77 FR 24367, 

April 24, 2012); and AD 2012–15–14, 

Amendment 39–17143 (77 FR 46937, 

August 7, 2012); the European Aviation 

Safety Agency (EASA), which is the 

Technical Agent for the Member States 

of the European Community, has issued 

EASA Airworthiness Directive 2012– 

0176, dated September 7, 2012, 

corrected September 20, 2012 (referred 

to after this as the Mandatory 

Continuing Airworthiness Information, 


tkelley on DSK3SPTVN1PROD with PROPOSALS