14734 Federal Register / Vol. 78, No. 45 / Thursday, March 7, 2013 / Proposed Rules 

5680; Internet https:// 

www.myboeingfleet.com. You may also 

review copies of the referenced service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221. 

Issued in Renton, Washington, on February 

25, 2013. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–05189 Filed 3–6–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0268; Directorate 

Identifier 2011–NM–129–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 

737–600, –700, –700C, –800, –900 and 

–900ER series airplanes. That NPRM 

proposed to require inspecting for a 

serial number that starts with the letters 

‘‘SAIC’’ on the left- and right-side 

horizontal stabilizer identification plate; 

a detailed inspection for correct bolt 

protrusion and chamfer of the 

termination fitting bolts of the 

horizontal stabilizer rear spar, if 

necessary; inspecting to determine if 

certain bolts are installed, if necessary; 

and doing related investigative and 

corrective actions if necessary. That 

NPRM was prompted by reports of 

incorrectly installed bolts common to 

the rear spar termination fitting on the 

horizontal stabilizer. This action revises 

that NPRM by adding airplanes to the 

applicability. We are proposing this 

supplemental NPRM to prevent loss of 

structural integrity of the horizontal 

stabilizer attachment and 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 supplemental NPRM by April 22, 

2013. 

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 proposed AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, Washington 98124– 

2207; telephone 206–544–5000, 

extension 1; fax 206–766–5680; Internet 

https://www.myboeingfleet.com. You 

may review copies of the referenced 

service information at the FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue SW., Renton, Washington. 

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; 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: 

Nancy Marsh, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office 

(ACO), 1601 Lind Avenue SW., Renton, 

Washington 98057–3356; phone: 425– 

917–6440; fax: 425–917–6590; email: 

nancy.marsh@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–2012–0268; Directorate Identifier 

2011–NM–129–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 to include an AD that would 

apply to certain The Boeing Company 

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

–900 series airplanes. That NPRM 

published in the Federal Register on 

March 20, 2012 (77 FR 16188). That 

NPRM proposed to require inspecting 

for a serial number that starts with the 

letters ‘‘SAIC’’ on the left- and right-side 

horizontal stabilizer identification plate; 

a detailed inspection for correct bolt 

protrusion and chamfer of the 

termination fitting bolts of the 

horizontal stabilizer rear spar, if 

necessary; inspecting to determine if 

certain bolts are installed, if necessary; 

and doing related investigative and 

corrective actions if necessary. 

Actions Since Previous NPRM (77 FR 

16188, March 20, 2012) Was Issued 

Since we issued the previous NPRM 

(77 FR 16188, March 20, 2012), we have 

determined that horizontal stabilizers 

are frequently rotated on the fleet and 

could be installed on any Model 737– 

600, –700, –700C, –800, and –900 

airplane, including airplanes outside the 

applicability of the NPRM. Therefore, 

we have determined that the identified 

unsafe condition may exist on all Model 

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

–900ER series airplanes. 

Comments 

We gave the public the opportunity to 

comment on the previous NPRM (77 FR 

16188, March 20, 2012). The following 

presents the comments received on the 

NPRM and the FAA’s response to each 

comment. 

Support for the Previous NPRM (77 FR 

16188, March 20, 2012) 

United Airlines stated it supports the 

previous NPRM (77 FR 16188, March 

20, 2012). 


emcdonald on DSK67QTVN1PROD with PROPOSALS
Federal Register / Vol. 78, No. 45 / Thursday, March 7, 2013 / Proposed Rules 14735 

Request To Revise Applicability 

Southwest Airlines (Southwest) 

requested that we revise the 

applicability of the previous NPRM (77 

FR 16188, March 20, 2012). Southwest 

suggested revising the applicability of 

the NPRM to identify serial numbers of 

the affected horizontal stabilizers, or to 

open the applicability of the NPRM to 

all airplanes, since the applicability 

listed in the previous NPRM and the 

effectivity of the service information do 

not account for horizontal stabilizers 

interchanged between airplanes. 

We agree with the commenter’s 

request for the reasons described in 

‘‘Actions Since Previous NPRM (77 FR 

16188, March 20, 2012) was Issued.’’ We 

have revised paragraph (c) of this 

supplemental NPRM to include all The 

Boeing Company Model 737–600, –700, 

–700C, –800, –900, and –900ER series 

airplanes, because the horizontal 

stabilizers can be rotated among 

airplanes. This change has been 

coordinated with Boeing. 

We also have added new paragraph 

(k) to this supplemental NPRM (and reidentified subsequent paragraphs) to 

prohibit installation of a horizontal 

stabilizer on any airplane included in 

the applicability of this AD unless the 

horizontal stabilizer has been inspected 

and applicable corrective actions have 

been done and no incorrect bolt 

protrusion and no incorrect chamfer of 

the termination fitting fasteners have 

been found. 

Request To Improve Inspection 

Procedures 

Southwest and TUIfly 

Fluggesellschaft mbH requested we 

revise the previous NPRM (77 FR 16188, 

March 20, 2012) to permit operators to 

demonstrate compliance for inspecting 

the horizontal stabilizer to determine 

the serial number by means of a review 

of the manufacturer’s delivery 

documentation for the accomplishment 

of Boeing Service Bulletin 737–55–1090, 

dated March 30, 2011. TUIfly 

Fluggesellschaft said that the delivery 

paperwork received with the airplane 

includes the serial number of the 

stabilizers installed on the airplane at 

the time of delivery. 

We agree that the manufacturer’s 

delivery documentation identifies the 

serial number of the horizontal 

stabilizer assembly installed on the 

airplane at the time of delivery. 

However, as discussed in the previous 

comment, horizontal stabilizers are 

rotable parts, so in addition to the 

delivery records, the airplane 

maintenance records must also be used 

to positively identify the current 

stabilizer installed on the airplane. We 

have added wording to paragraph (g) of 

this supplemental NPRM to state that a 

review of manufacturer delivery and 

operator maintenance records is 

acceptable if that review conclusively 

determines the serial number of the 

horizontal stabilizer. 

STC Winglet Comment 

Aviation Partners Boeing stated that 

the installation of winglets per 

Supplemental Type Certificate (STC) 

ST00830SE does not affect 

accomplishment of the proposed 

requirements. 

We have added paragraph (c)(2) to 

this supplemental NPRM to state that 

installation of STC ST00830SE (http://

rgl.faa.gov/Regulatory_and_Guidance_

Library/rgstc.nsf/0/408E012E

008616A7862578880060456C?Open

Document&Highlight=st00830se) does 

not affect the ability to accomplish the 

actions proposed by this supplemental 

NPRM. 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 Section 39.17 of the 

Federal Aviation Regulations (14 CFR 

39.17). For all other AMOC requests, the 

operator must request approval of an 

AMOC in accordance with the 

procedures specified in paragraph (l) of 

this supplemental NPRM. 

Request To Revise Applicability To 

Include Bolt Type BACB30XL 

American Airlines (American) 

requested that the inspections and 

corrective actions specified in Boeing 

Service Bulletin 737–55–1090, dated 

March 30, 2011, be used to address the 

inspections and corrective actions for 

the alternative bolt type part number (P/ 

N) BACB30XL that may be installed at 

the same locations as bolt type P/N 

BACB30US14K() or BACB30US16K(). 

American indicated the existing service 

information does not provide corrective 

actions for the alternative bolt type P/N 

BACB30XL that may be installed in the 

locations requiring bolt inspection. 

We disagree with the request because 

Boeing Service Bulletin 737–55–1090, 

dated March 30, 2011, provides specific 

inspection criteria and measurements 

that are applicable only to the bolt type 

P/N BACB30US. Those criteria cannot 

be directly applied to the alternative 

bolt types. The manufacturer plans to 

revise that service bulletin to include 

corrective actions for the alternative bolt 

type P/N BACB30XL. We will review 

the service bulletin and may approve 

the revised service instructions as an 

AMOC to the AD, when the revised 

service bulletin is available. We have 

not changed the supplemental NPRM in 

this regard. 

Request To Allow Alternative Service 

Information 

Oman Air (Oman) requested that 

credit for prior accomplishment of 

Boeing Service Letters 737–SL–55–027, 

dated April 12, 2007, and 737–SL–55– 

028, dated April 26, 2007, be given as 

an alternative to the accomplishment of 

the inspections and corrective actions 

specified in Boeing Service Bulletin 

737–55–1090, dated March 30, 2011, 

which are required by paragraphs (g), 

(h), and (k) of the previous NPRM (77 

FR 16188, March 20, 2012). 

We disagree. Boeing Service Letter 

737–SL–55–027, dated April 12, 2007, 

and Boeing Service Letter 737–SL–55– 

028, dated April 26, 2007, were 

published prior to the identification of 

the safety issues created by the missing 

washers. Although these service letters 

provide instructions for the replacement 

of any missing washers, they do not 

address the potential durability issues 

created by the unclamped joint that are 

addressed by the repetitive inspections 

of the structure, as specified in Boeing 

Service Bulletin 737–55–1090, dated 

March 30, 2011. The commenter did not 

provide any data to substantiate the 

durability of the corrective actions 

specified in those service letters. This 

proposal could be considered if data 

were provided to substantiate the 

request, using the procedures defined in 

paragraph (l) of this supplemental 

NPRM for requesting approval of an 

AMOC. We have not changed the 

supplemental NPRM in this regard. 

Revision to Service Bulletin 

The Boeing Company (Boeing) stated 

it will revise Boeing Service Bulletin 

737–55–1090, dated March 30, 2011, to 

instruct operators to inspect for bolt 

types other than BACB30US, to provide 

repair methods for bolt configurations 

other than BACB30US, and to revise 

Figure 1 of that service bulletin to 

correctly identify the serial number 

location in lieu of the part number 

location. 

Boeing did not request a specific 

change to the previous NPRM (77 FR 

16188, March 20, 2012). We already 

specified the correct location of the 

serial number in paragraph (j) of the 

previous NPRM. We also already 

specified that an inspection for bolt 

types other than part number 

BACB30US14K() or BACB30US16K() is 

required for paragraph (g) of the 

previous NPRM. 


emcdonald on DSK67QTVN1PROD with PROPOSALS
14736 Federal Register / Vol. 78, No. 45 / Thursday, March 7, 2013 / Proposed Rules 

FAA’s Determination 

We are proposing this supplemental 

NPRM 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 original 

NPRM (77 FR 16188, March 20, 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 supplemental NPRM. 

Proposed Requirements of the 

Supplemental NPRM 

This supplemental NPRM would 

require inspecting for a serial number 

that starts with the letters ‘‘SAIC’’ on the 

left- and right-side horizontal stabilizer 

identification plate; a detailed 

inspection for correct bolt protrusion 

and chamfer of the termination fitting 

bolts of the horizontal stabilizer rear 

spar, if necessary; inspecting to 

determine if certain bolts are installed, 

if necessary; and doing related 

investigative and corrective actions if 

necessary. 

Costs of Compliance 

We estimate that this proposed AD 

affects 1,147 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 ................................................ 1 work-hour × $85 per hour = $85 per inspection 

cycle.

$0 $85 $97,495 

Replacement of bolts .............................. 17 work-hours × $85 per hour = $1,445 ................ 1,530 2,975 3,412,325 

We have received no definitive data 

that would enable us to provide a cost 

estimate for the on-condition actions 

(contacting Boeing and repairing cracks 

or damage) specified in this 

supplemental NPRM. 

According to the manufacturer, some 

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 

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– 

2012–0268; Directorate Identifier 2011– 

NM–129–AD. 

(a) Comments Due Date 

We must receive comments by April 22, 

2013. 

(b) Affected ADs 

None. 

(c) Applicability 

(1) This AD applies to all The Boeing 

Company Model 737–600, –700, –700C, 

–800, –900, and –900ER series airplanes, 

certificated in any category. 

(2) Installation of Supplemental Type 

Certificate (STC) ST00830SE (http://

rgl.faa.gov/Regulatory_and_Guidance_

Library/rgstc.nsf/0/ 

408E012E008616A7862578880060456C?

OpenDocument&Highlight=st00830se) 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 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 55: Stabilizer. 

(e) Unsafe Condition 

This AD was prompted by reports of 

incorrectly installed bolts common to the rear 

spar termination fitting of the horizontal 

stabilizer. We are issuing this AD to prevent 

loss of structural integrity of the horizontal 

stabilizer attachment and loss of control of 

the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspecting the Horizontal Stabilizer and 

Corrective Actions 

Except as provided by paragraph (i) of this 

AD, at the applicable times specified in 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Service Bulletin 737–55–1090, dated March 


emcdonald on DSK67QTVN1PROD with PROPOSALS
Federal Register / Vol. 78, No. 45 / Thursday, March 7, 2013 / Proposed Rules 14737 

30, 2011: Do an inspection for a serial 

number that starts with the letters ‘‘SAIC’’ on 

the identification plates of the left- and rightside horizontal stabilizers, in accordance 

with the Accomplishment Instructions of 

Boeing Service Bulletin 737–55–1090, dated 

March 30, 2011. A review of manufacturer 

delivery and operator maintenance records is 

acceptable to make the determination 

specified in this paragraph if the serial 

number can be conclusively identified from 

that review. 

(1) If a serial number starting with the 

letters ‘‘SAIC’’ is found on a horizontal 

stabilizer identification plate: Except as 

provided by paragraph (i) of this AD, at the 

applicable times specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Service Bulletin 

737–55–1090, dated March 30, 2011, do a 

detailed inspection for correct bolt protrusion 

and correct chamfer of the termination fitting 

bolts of the horizontal stabilizer rear spar, in 

accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 737– 

55–1090, dated March 30, 2011. Concurrently 

with the detailed inspection, inspect to 

determine if bolts other than part number (P/ 

N) BACB30US14K() or BACB30US16K(), as 

applicable, are installed. Before further flight, 

do all applicable related investigative and 

corrective actions, in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin 737–55–1090, dated March 

30, 2011. 

(2) If no SAIC serial number is found, no 

further action is required by this AD. 

(h) High Frequency Eddy Current (HFEC) 

and Ultrasonic Inspections of Termination 

Fitting and Repair 

For any location where a new bolt having 

a P/N BACB30US14K() is installed due to 

damage found during any inspection 

required by paragraph (g) of this AD: Except 

as provided by paragraph (i) of this AD, at 

the times specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Service Bulletin 

737–55–1090, dated March 30, 2011, do 

HFEC and ultrasonic inspections for cracking 

of the forward and aft sides of the 

termination fitting, in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin 737–55–1090, dated March 

30, 2011. If any crack is found in any 

termination fitting: Before further flight, 

repair in accordance with the procedures 

specified in paragraph (l) of this AD. Repeat 

the HFEC and ultrasonic inspections 

thereafter at intervals not to exceed 3,500 

flight cycles. 

(i) Exception to Compliance Time 

Where Boeing Service Bulletin 737–55– 

1090, dated March 30, 2011, specifies a 

compliance time ‘‘after the original issue date 

on the service bulletin,’’ this AD requires 

compliance within the specified compliance 

time after the effective date of this AD. 

(j) Exceptions to Service Bulletin 

(1) Where Figure 1 of Boeing Service 

Bulletin 737–55–1090, dated March 30, 2011, 

points to the location of a part number rather 

than the serial number, this AD requires an 

inspection for an identification plate with a 

serial number that starts with the letters 

‘‘SAIC.’’ 

(2) If, during any inspection required by 

paragraphs (g) and (h) of this AD, any bolt 

other than P/N BACB30US14K() or 

BACB30US16K(), as applicable, is found: 

Before further flight, repair using a method 

approved in accordance with the procedures 

specified in paragraph (l) of this AD. 

(k) Parts Installation Limitation 

As of the effective date of this AD, no 

person may install a horizontal stabilizer on 

any airplane included in the applicability of 

this AD unless it has been inspected and any 

applicable corrective actions done using the 

procedures specified in paragraph (g) of this 

AD. 

(l) 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 the 

Related Information section of this AD. 

Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@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. 

(m) Related Information 

(1) For more information about this AD, 

contact Nancy Marsh, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office (ACO), 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; phone: 425–917–6440; fax: 425–917– 

6590; email: nancy.marsh@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, Washington 98124–2207; telephone 

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

5680; Internet https:// 

www.myboeingfleet.com. You may review 

copies of the referenced service information 

at the FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, Washington. 

For information on the availability of this 

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

Issued in Renton, Washington, on February 

26, 2013. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–05328 Filed 3–6–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF HOMELAND 

SECURITY 

Federal Emergency Management 

Agency 

44 CFR Part 67 

[Docket ID FEMA–2013–0002; Internal 

Agency Docket No. FEMA–B–1187] 

Proposed Flood Elevation 

Determinations for Sussex County, 

Delaware, and Incorporated Areas 

AGENCY: Federal Emergency 

Management Agency, DHS. 

ACTION: Proposed rule; withdrawal. 

SUMMARY: The Federal Emergency 

Management Agency (FEMA) is 

withdrawing its proposed rule 

concerning proposed flood elevation 

determinations for Sussex County, 

Delaware, and Incorporated Areas. 

DATES: The proposed rule published 

April 6, 2011 (76 FR 19006) is 

withdrawn as of March 7, 2013. 

ADDRESSES: You may submit comments, 

identified by Docket No. FEMA–B– 

1187, to Luis Rodriguez, Chief, 

Engineering Management Branch, 

Federal Insurance and Mitigation 

Administration, Federal Emergency 

Management Agency, 500 C Street SW., 

Washington, DC 20472, (202) 646–4064, 

or (email) 

Luis.Rodriguez3@fema.dhs.gov. 

FOR FURTHER INFORMATION CONTACT: Luis 

Rodriguez, Chief, Engineering 

Management Branch, Federal Insurance 

and Mitigation Administration, Federal 

Emergency Management Agency, 500 C 

Street SW., Washington, DC 20472, 

(202) 646–4064, or (email) 

Luis.Rodriguez3@fema.dhs.gov. 

SUPPLEMENTARY INFORMATION: On April 

6, 2011, FEMA published a proposed 

rulemaking at 76 FR 19006, proposing 

flood elevation determinations along 

one or more flooding sources in Sussex 

County, Delaware. Because FEMA has 

or will be issuing a Revised Preliminary 

Flood Insurance Rate Map, and if 

necessary a Flood Insurance Study 

report, featuring updated flood hazard 

information, the proposed rulemaking is 

being withdrawn. A Notice of Proposed 

Flood Hazard Determinations will be 

published in the Federal Register and in 


emcdonald on DSK67QTVN1PROD with PROPOSALS