This section of the FEDERAL REGISTER

contains regulatory documents having general

applicability and legal effect, most of which

are keyed to and codified in the Code of

Federal Regulations, which is published under

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REGISTER issue of each week.

Rules and Regulations Federal Register

49903 

Vol. 78, No. 159 

Friday, August 16, 2013 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0637; Directorate 

Identifier 2012–NM–006–AD; Amendment 

39–17532; AD 2013–15–16] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 737–600, 

–700, –700C, –800, –900, and –900ER 

series airplanes. This AD was prompted 

by a report of an inboard main landing 

gear (MLG) door assembly departure 

due to premature fatigue cracking in the 

inboard MLG door hinge fittings. This 

AD requires repetitive inspections for 

cracking of the inboard MLG door hinge 

fittings; and replacement or 

modification of cracked fittings. This 

AD also provides an option to remove 

the affected MLG door. We are issuing 

this AD to detect and correct fatigue 

cracking in the inboard MLG door hinge 

fittings, which could result in loss of the 

MLG door assembly from the airplane, 

and the MLG door assembly could 

impact the flight control surfaces and 

result in reduced controllability of the 

airplane. 

DATES: This AD is effective September 

20, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of September 20, 2013. 

ADDRESSES: 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 

review copies of the 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; 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 AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (phone: 800–647–5527) is 

Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Nancy Marsh, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–917–6440; fax: 

425–917–6590; email: 

nancy.marsh@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. The 

NPRM published in the Federal 

Register on June 18, 2012 (77 FR 36222). 

The NPRM proposed to require 

repetitive inspections for cracking of the 

inboard MLG door hinge fittings; and 

modification of cracked fittings, which 

would terminate the repetitive 

inspections. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal (77 FR 36222, 

June 18, 2012) and the FAA’s response 

to each comment. 

Request To Extend Compliance Time 

American Airlines requested that we 

revise the NPRM (77 FR 36222, June 18, 

2012) to extend the compliance time for 

the initial inspections from 10,000 total 

flight cycles to before 18,000 total flight 

cycles. American Airlines stated that the 

FAA has not provided sufficient 

evidence to warrant issuance of 

regulatory action with such a reduced 

compliance time. American Airlines 

calculated that the event described in 

the service information represents only 

0.085 percent of the airplanes under 

U.S. registry, and that the event 

described occurred at 24,000 total flight 

cycles. 

We disagree with the request to 

extend the compliance time. In 

developing an appropriate compliance 

time for this action, we considered the 

safety implications, parts availability, 

and normal maintenance schedules for 

the timely accomplishment of the 

inspections and modifications. There is 

additional data related to the MLG door 

hinge failures that is not included in the 

manufacturer’s service bulletin. Up to 

10 percent of hinges inspected to date 

have been found with cracking. The 

cracking occurred between 11,000 and 

24,000 total flight cycles, and has been 

found on both hinges of the inboard 

MLG door. In consideration of these 

items, we have determined that a 

compliance time of before 10,000 total 

flight cycles will ensure an acceptable 

level of safety and allow the inspections 

and modifications to be done during 

scheduled maintenance intervals for 

most affected operators. We have not 

changed the AD in this regard. 

Request To Allow New Hinges Having 

Part Numbers (P/Ns) 113A8341–1 and 

113A8341–2 

American Airlines requested that we 

revise paragraph (g) of the NPRM (77 FR 

36222, June 18, 2012) to allow 

installation of new hinges having P/Ns 

113A8341–1 and 113A8341–2 as 

replacements for cracked hinges found 

during the inspections. American 

Airlines stated that paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 737–52A1167, dated December 

1, 2011 (referred to in the NPRM as the 

appropriate source of service 

information), implies that an operator 

may install a new set of hinges having 

P/Ns 113A8341–1 and 113A8341–2 and 

restart the inspection threshold and 


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49904 Federal Register / Vol. 78, No. 159 / Friday, August 16, 2013 / Rules and Regulations 

interval; however, the Accomplishment 

Instructions recommend installation of 

new hinges having P/Ns 113A8341–9 

and 113A8341–10 if cracking is found. 

American Airlines stated that 

installation of a new set of hinges 

having P/Ns 113A8341–1 and 

113A8341–2 should be acceptable as 

long as the on-going repetitive 

inspections are accomplished as defined 

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

Boeing Alert Service Bulletin 737– 

52A1167, dated December 1, 2011. 

We agree to allow replacement of 

cracked hinges with new hinges having 

P/Ns 113A8341–1 and 113A8341–2, as 

long as inspections of the replacement 

hinges are accomplished at the time 

specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 737–52A1167, dated December 

1, 2011. We have added new paragraph 

(h)(2) to this AD to clarify that installing 

new MLG door hinge fittings having 

P/N 113A8341–1 and 113A8341–2, is 

acceptable for compliance with the 

modification specified in paragraphs 

(g)(1)(ii) and (g)(2)(i) of this AD. 

Paragraph (h)(2) also specifies that 

installation of the MLG door hinge 

fittings having P/N 113A8341–1 and 

113A8341–2, must be done using a 

method approved in accordance with 

the procedures specified in paragraph (j) 

of this AD. We have revised subsequent 

paragraph identifiers accordingly. This 

difference has been coordinated with 

Boeing. 

Request for Clarification of Follow-On 

Actions 

Boeing requested that we reword 

paragraph (g) of the NPRM (77 FR 

36222, June 18, 2012) to clarify the 

follow-on actions required after the 

inspections. Boeing stated that the 

requirement to continue repetitive 

inspections needs to be clarified since it 

only pertains if the hinges were found 

to be uncracked. 

We agree that clarification is needed. 

The repetitive inspections are not 

required if the modification has been 

accomplished with hinges having P/Ns 

113A8341–9 and 113A8341–10. 

However, the repetitive inspections are 

required if hinges having P/N 

113A8341–1 and 113A8341–2 are 

installed. We have added this 

clarification in paragraphs (g)(1) and 

(g)(2) of this AD. 

Request To Require Modification of 

Only Doors Having Cracked Hinges 

Southwest Airlines (Southwest) 

requested that replacement of the hinges 

be required only on the door where 

cracks were found, rather than replacing 

both doors if cracking is found only on 

one door. Southwest stated it wants the 

option to not modify a door on which 

the hinges are not cracked, even though 

there is hinge cracking on the door on 

the other side of the airplane. Southwest 

added that, for a door that has no 

cracked hinges, the repetitive 

inspections would remain effective, and 

modification would not be required 

prior to further flight. 

We agree that only doors with cracked 

hinges need to be modified, and that the 

repetitive inspections specified in the 

AD remain in effect for the door that has 

not been modified. We have revised 

paragraph (g)(2)(i) of this AD to clarify 

that modification is only required on 

affected doors. 

Request for the Option To Remove 

Inboard MLG Door in Accordance With 

the Configuration Deviation List (CDL) 

Southwest requested that we allow 

the option of removing the inboard MLG 

door from the airplane as specified in 

the CDL. Southwest noted that the CDL 

allows for continued operation without 

the inboard MLG door. 

We agree with adding an option to the 

AD to remove the affected inboard MLG 

door. However, the removal must be 

done in accordance with a method 

approved by the FAA because 

applicable flight effects and restrictions 

must be accounted for. In addition, if a 

door with new hinge fittings is 

reinstalled, the inspection required by 

paragraph (h) of this AD must be done. 

We have added paragraph (g)(2)(ii) of 

this AD accordingly. We have also 

added note 1 to paragraph (g)(2)(ii) of 

this AD to this AD to refer to the CDL 

as guidance. 

Supplemental Type Certificate (STC) 

Winglet Comment 

Aviation Partners Boeing stated that 

the installation of winglets per STC 

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

Regulatory_and_Guidance_Library/

rgstc.nsf/0/408E012E008616A786

2578880060456C?OpenDocument&

Highlight=st00830se) does not affect the 

accomplishment of the manufacturer’s 

service instructions. 

We have added paragraph (c)(1) to 

this AD to state that installation of STC 

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

Regulatory_and_Guidance_Library/

rgstc.nsf/0/408E012E008616A78625788

80060456C?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. For all 

other AMOC requests, the operator must 

request approval of an AMOC in 

accordance with the procedures 

specified in paragraph (j) of this AD. 

New Optional Installation Paragraph 

We have added new paragraph (h)(1) 

to this AD to clarify that installing new 

MLG door hinge fittings having P/N 

113A8341–9 and 113A8341–10, 

terminates the inspection requirements 

of this AD for only the door on which 

new fittings are installed. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting this AD 

with the changes described previously 

and minor editorial changes. We have 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (77 FR 

36222, June 18, 2012) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (77 FR 36222, 

June 18, 2012). 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this AD. 

Costs of Compliance 

We estimate that this AD affects 1,175 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product Cost on U.S. operators 

Inspection ....................... 3 work-hours × $85 per hour = $255 per inspection cycle.$0 $255 per inspection 

cycle.

$299,625 per inspection 

cycle. 


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Federal Register / Vol. 78, No. 159 / Friday, August 16, 2013 / Rules and Regulations 49905 

We estimate the following costs to do 

any necessary modification that would 

be required based on the results of the 

inspection. We have no way of 

determining the number of airplanes 

that might need this modification: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per product 

Modification ................................ 9 work-hours × $85 per hour = $765 .......................................... $6,550 $7,315 

According to the manufacturer, some 

of the costs of this 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 

This AD will not have federalism 

implications under Executive Order 

13132. This AD will 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 that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

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

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. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 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): 

2013–15–16 The Boeing Company: 

Amendment 39–17532; Docket No. 

FAA–2012–0637; Directorate Identifier 

2012–NM–006–AD. 

(a) Effective Date 

This AD is effective September 20, 2013. 

(b) Affected ADs 

None. 

(c) Applicability 

(1) This AD applies to The Boeing 

Company Model 737–600, –700, –700C, 

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

certificated in any category, as identified in 

Boeing Alert Service Bulletin 737–52A1167, 

dated December 1, 2011. 

(2) Installation of Supplemental Type 

Certificate (STC) ST00830SE (http://rgl.faa.

gov/Regulatory_and_Guidance_Library/rgstc.

nsf/0/408E012E008616A7862578880060

456C?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 52, Doors. 

(e) Unsafe Condition 

This AD was prompted by a report of an 

inboard main landing gear (MLG) door 

assembly departure due to premature fatigue 

cracking in the inboard MLG door hinge 

fittings. We are issuing this AD to detect and 

correct fatigue cracking in the inboard MLG 

door hinge fittings, which could result in loss 

of the MLG door assembly from the airplane, 

and the MLG door assembly could impact the 

flight control surfaces and result in reduced 

controllability of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Initial and Repetitive Inspections 

Except as provided by paragraph (i) of this 

AD, at the applicable time specified in 

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

Alert Service Bulletin 737–52A1167, dated 

December 1, 2011, do either a detailed or 

surface high frequency eddy current (HFEC) 

inspection for cracking of the left- and rightside inboard MLG door hinge fittings, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–52A1167, dated December 1, 2011. 

(1) If no cracking is found, at the times 

specified in paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin 737–52A1167, 

dated December 1, 2011, do the actions 

specified in either paragraph (g)(1)(i) or 

(g)(1)(ii) of this AD, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–52A1167, dated 

December 1, 2011. 

(i) Repeat either a detailed or a surface 

HFEC inspection for cracking of the left- and 

right-side inboard MLG door hinge fittings. 

(ii) Modify the hinge fittings on the inboard 

MLG doors by installing P/N 113A8341–9 

and 113A8341–10, in accordance with Part 3 

of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 737–52A1167, 

dated December 1, 2011. Doing the 

modification specified in this paragraph 

terminates the inspection requirements for 

only the door on which new fittings are 

installed. 

(2) If any cracking is found, before further 

flight, do the actions specified in either 

paragraph (g)(2)(i) or (g)(2)(ii) of this AD. 

(i) Modify the hinge fittings on all affected 

inboard MLG doors by installing P/N 

113A8341–9 and 113A8341–10, in 

accordance with Part 3 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–52A1167, dated 

December 1, 2011. Doing the modification 

specified in this paragraph terminates the 

inspection requirements for only the door on 

which new fittings are installed. 

(ii) Remove the affected MLG door, using 

a method approved in accordance with the 

procedures specified in paragraph (j) of this 

AD. For airplanes on which this door is 

reinstalled, before further flight, accomplish 

the actions specified in either paragraph 


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49906 Federal Register / Vol. 78, No. 159 / Friday, August 16, 2013 / Rules and Regulations 

(h)(1) or (h)(2) of this AD on the reinstalled 

door. 

Note 1 to paragraph (g)(2)(ii) of this AD: 

Guidance for removing the door can be found 

in Section 32–10 of Appendix CDL, 

Configuration Deviation List, Model 737– 

100/200/300/400/500/600/700/800/900/900 

ER Series, to the Boeing 737–700 Airplane 

Flight Manual Document D631A001. 

(h) Optional Installation 

(1) Installing new MLG door hinge fittings 

having P/N 113A8341–9 and 113A8341–10, 

terminates the inspection requirements of 

this AD for only the doors on which new 

fittings are installed. 

(2) Installing new MLG door hinge fittings 

having P/N 113A8341–1 and 113A8341–2, is 

acceptable for compliance with the 

modification specified in paragraphs (g)(1)(ii) 

and (g)(2)(i) of this AD, provided the 

inspections (both the initial and the 

repetitive inspections) required by paragraph 

(g) of this AD are done within the applicable 

times specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 737–52A1167, dated December 1, 

2011. Installation of the MLG door hinge 

fittings having P/N 113A8341–1 and 

113A8341–2, as applicable, must be done 

using a method approved in accordance with 

the procedures specified in paragraph (j) of 

this AD. Accomplishing the requirements of 

this paragraph does not terminate the 

inspection requirements of paragraph (g) of 

this AD. 

(i) Exception to the Service Information 

Where Boeing Alert Service Bulletin 737– 

52A1167, dated December 1, 2011, specifies 

a compliance time ‘‘after the original issue 

date of this service bulletin,’’ this AD 

requires compliance within the specified 

compliance time after the effective date of 

this AD. 

(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 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. 

(k) Related Information 

For more information about this AD, 

contact Nancy Marsh, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: 425–917–6440; fax: 425–917–6590; 

email: nancy.marsh@faa.gov. 

(l) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Boeing Alert Service Bulletin 737– 

52A1167, dated December 1, 2011. 

(ii) Reserved. 

(3) 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. 

(4) You may view this service information 

at 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. 

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http:// 

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on July 21, 

2013. 

Stephen P. Boyd, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–18090 Filed 8–15–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0361; Directorate 

Identifier 2013–NM–026–AD; Amendment 

39–17527; AD 2013–15–11] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all The 

Boeing Company Model 727 airplanes. 

This AD was prompted by a report of 

cracking in the left-side chord of the fin 

closure rib on the vertical stabilizer. 

This AD requires repetitive inspections 

of the left and right side chords of the 

fin closure rib for cracking and 

corrosion, and related investigative and 

corrective actions if necessary. We are 

issuing this AD to detect and correct 

cracking and corrosion in the left- and 

right-side chords of the fin closure rib, 

which could lead to widespread 

cracking in the chords that might 

weaken the fin closure rib structure and 

result in loss of airplane control due to 

lack of horizontal stabilizer support. 

DATES: This AD is effective September 

20, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of September 20, 2013. 

ADDRESSES: 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 

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 AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (phone: 800–647–5527) is 

Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Berhane Alazar, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; phone: 425– 

917–6577; fax: 425–917–6590; email: 

berhane.alazar@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. The 

NPRM published in the Federal 


tkelley on DSK3SPTVN1PROD with RULES