Federal Register / Vol. 78, No. 232 / Tuesday, December 3, 2013 / Rules and Regulations 72561 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in 

paragraph (l) 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 14 

CFR 25.571, Amendment 45, and the 

approval must specifically refer to this AD. 

(l) Related Information 

(1) For more information about this AD, 

contact Sarah Piccola, Aerospace Engineer, 

Cabin Safety and Environmental Systems 

Branch, ANM–150S, FAA, Seattle Aircraft 

Certification Office, 1601 Lind Avenue SW., 

Renton, WA 98057–3356; phone: 425–917– 

6483; fax: 425–917–6590; email: 

sarah.piccola@faa.gov. 

(2) Service information that is referenced 

in this AD but is not incorporated by 

reference may be obtained at the addresses 

identified in paragraphs (m)(3) and (m)(4) of 

this AD. 

(m) 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 Service Bulletin 737–53–1120, 

Revision 1, dated May 13, 1993. 

(ii) Boeing Service Bulletin 737–53–1244, 

Revision 5, dated July 27, 2011. 

(iii) Boeing Special Attention Service 

Bulletin 737–53–1260, Revision 1, dated May 

23, 2013. 

(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 

November 19, 2013. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–28752 Filed 12–2–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0420; Directorate 

Identifier 2011–NM–241–AD; Amendment 

39–17685; AD 2013–24–11] 

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 certain 

The Boeing Company Model 747–100, 

747–100B, 747–100B SUD, 747–200B, 

747–200C, 747–200F, 747–300, 747– 

400, 747–400D, 747–400F, 747SR, and 

747SP series airplanes. This AD was 

prompted by a report of a disbonded 

doubler and a skin crack in section 41 

of the fuselage, and multiple reports of 

cracked or missing fastener heads. This 

AD requires repetitive inspections for 

cracking of the fuselage skin, discrepant 

fasteners, and for disbonds at the 

doublers; and related investigative and 

corrective actions if necessary. For 

certain airplanes, this AD also requires 

a terminating repair for repair doublers. 

We are issuing this AD to prevent rapid 

decompression and loss of structural 

integrity of the airplane due to such 

disbonding and subsequent cracking of 

the skin panels. 

DATES: This AD is effective January 7, 

2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of January 7, 2014. 

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 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; 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: 

Nathan Weigand, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office 

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

WA 98057–3356; phone: 425–917–6428; 

fax: 425–917–6590; email: 

Nathan.P.Weigand@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to the specified products. The 

NPRM published in the Federal 

Register on May 16, 2013 (78 FR 28767). 

The NPRM proposed to require 

repetitive inspections for cracking of the 

fuselage skin, discrepant fasteners, and 

for disbonds at the doublers; and related 

investigative and corrective actions if 

necessary. For certain airplanes, the 

NPRM also proposed to require a 

terminating repair for repair doublers. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal (78 FR 28767, 

May 16, 2013) and the FAA’s response 

to each comment. 

Request To Add Terminating Action for 

Other AD Actions 

Boeing requested that we include the 

requirements of paragraph (h) of AD 

2006–24–05, Amendment 39–14834 (76 

FR 68434, November 27, 2006), in 

paragraph (k)(3) of the NPRM (78 FR 

28767, May 16, 2013), which specifies 

that accomplishing the required actions 

proposed by the NPRM terminates 

certain requirements of AD 2006–24–05. 

Boeing stated that including the 

requirements of paragraph (h) of AD 

2006–24–05 in paragraph (k) of the 

NPRM would then be consistent with 

paragraph (k)(2) of the NPRM that 


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includes paragraph (l) of AD 2006–24– 

02. 

We do not agree with the commenter’s 

request. Boeing Service Bulletin 747– 

53A2747, Revision 2, dated February 22, 

2012, which is the referenced service 

information in this final rule, is an 

alternative method of compliance 

(AMOC) for the three ADs specified in 

paragraph (k) of this final rule for only 

the corresponding paragraphs of those 

ADs that are listed in paragraphs (k)(1), 

(k)(2), and (k)(3) of this final rule. 

Boeing Service Bulletin 747–53A2747, 

Revision 2, dated February 22, 2012, 

does not list paragraph (h) of AD 2006– 

24–05, Amendment 39–14834 (76 FR 

68434, November 27, 2006), as one of 

the paragraphs for which the service 

information is a method of compliance. 

We have not changed this final rule in 

this regard. 

Request To Revise the Compliance 

Time 

Delta Airlines (DAL) requested that 

we revise the compliance time to make 

it more feasible for an operator to 

accomplish the actions in the NPRM (78 

FR 28767, May 16, 2013). DAL stated 

that certain affected DAL airplanes will 

require inspections within 150 flight 

cycles after the effective date of the final 

rule. DAL also stated that current usage 

of the affected DAL airplanes is 

approximately 500 to 540 flight cycles 

per year and, therefore, the 150-flightcycle compliance time would require 

‘‘special visits to complete.’’ 

We do not agree with the commenter’s 

request to extend the compliance time. 

In developing an appropriate 

compliance time for this final rule, we 

considered the urgency associated with 

the identified unsafe condition and the 

manufacturer’s recommendations. 

Disbonded doublers, skin cracking, and 

cracked or missing fastener heads are a 

significant safety issue, and we have 

determined that the inspection 

compliance times are warranted. The 

commenter provided no technical 

justification for revising the inspection 

thresholds. However, under the 

provisions of paragraph (l) of this final 

rule, we will consider requests for 

approval of an extension of the 

compliance time if sufficient data are 

submitted to substantiate that the 

extension would provide an acceptable 

level of safety. We have not changed 

this final rule in this regard. 

Request To Expand Work-Hour 

Break-Outs 

DAL requested that we break out the 

work-hours identified in paragraph G. 

(Manpower) of Boeing Service Bulletin 

747–53A2747, Revision 2, dated 

February 22, 2012, by zones and 

conditions that will ultimately assist the 

operators in scheduling each unique 

condition. DAL stated that the 

compliance times in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Service 

Bulletin 747–53A2747, Revision 2, 

dated February 22, 2012, are broken out 

by Zone 1 and Zone 2, and can occur 

at different times depending on each 

resulting condition. 

We do not agree with the commenter’s 

request. The stated costs in ADs must 

address all actions mandated by the AD. 

The hours described in paragraph G. 

(Manpower) of Boeing Service Bulletin 

747–53A2747, Revision 2, dated 

February 22, 2012, are an estimate of the 

total hours to perform the actions. This 

final rule includes the work-hours 

specified in Boeing Service Bulletin 

747–53A2747, Revision 2, dated 

February 22, 2012. These actions are not 

intended to be broken out to a task-bytask level. We have not changed this 

final rule in this regard. 

Request To Revise AD 2006–24–02, 

Amendment 39–14831 (71 FR 67445, 

November 22, 2006) 

DAL requested that we support an 

expedited revision to AD 2006–24–02, 

Amendment 39–14831 (71 FR 67445, 

November 22, 2006), prior to issuance of 

this final rule. DAL stated that 

according to a recent customer support 

presentation of Boeing Service Bulletin 

747–53A2747, Revision 2, dated 

February 22, 2012, Boeing is currently 

working on a revision to this service 

bulletin, which may relax some 

compliance times. 

We do not agree with the commenter’s 

request. We have not received Revision 

3 to Boeing Service Bulletin 747– 

53A2747 to review. We have 

determined that this final rule must not 

be delayed for issuance of a new 

revision to Boeing Service Bulletin 747– 

53A2747, Revision 2, dated February 22, 

2012, since we have determined that an 

unsafe condition exists and that 

inspections in this final rule must be 

conducted to ensure continued safety. 

When Revision 3 of Boeing Service 

Bulletin 747–53A2747 is submitted, we 

will review and evaluate it as an 

alternative method of compliance to this 

final rule and determine if additional 

rulemaking is necessary. We have not 

changed this final rule in this regard. 

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 change described previously 

except for minor editorial changes. We 

have determined that these minor 

changes: 

• Are consistent with the intent that 

was proposed in the NPRM (78 FR 

28767, May 16, 2013) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (78 FR 28767, 

May 16, 2013). 

Costs of Compliance 

We estimate that this AD affects 98 

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 

Inspections ................................ 878 work-hours × $85 per hour 

= $74,630 per inspection 

cycle.

$0 $74,630 per inspection cycle ... $7,313,740 per inspection 

cycle. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this AD. 

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 


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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): 

2013–24–11 The Boeing Company: 

Amendment 39–17685; Docket No. 

FAA–2013–0420; Directorate Identifier 

2011–NM–241–AD. 

(a) Effective Date 

This AD is effective January 7, 2014. 

(b) Affected ADs 

This AD affects AD 2006–20–02, 

Amendment 39–14771 (71 FR 56861, 

September 28, 2006); AD 2006–24–02, 

Amendment 39–14831 (71 FR 67445, 

November 22, 2006); and AD 2006–24–05, 

Amendment 39–14834 (71 FR 68434, 

November 27, 2006). 

(c) Applicability 

This AD applies to The Boeing Company 

Model 747–100, 747–100B, 747–100B SUD, 

747–200B, 747–200C, 747–200F, 747–300, 

747–400, 747–400D, 747–400F, 747SR, and 

747SP series airplanes; certificated in any 

category; as identified in Boeing Service 

Bulletin 747–53A2747, Revision 2, dated 

February 22, 2012. 

(d) Subject 

Joint Aircraft System Component (JASC)/

Air Transport Association (ATA) of America 

Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by a disbonded 

doubler and a skin crack in section 41 of the 

fuselage, and multiple reports of cracked or 

missing fastener heads. We are issuing this 

AD to prevent rapid decompression and loss 

of structural integrity of the airplane due to 

such disbonding and subsequent cracking of 

the skin panels. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Repetitive Skin Panel, Fastener, and 

Doubler Inspections 

At the applicable time specified in 

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

Service Bulletin 747–53A2747, Revision 2, 

dated February 22, 2012, except as required 

by paragraphs (i)(1) and (i)(3) of this AD: Do 

the applicable inspections (including 

detailed, high frequency eddy current 

(HFEC), and low frequency eddy current 

(LFEC)) for any cracking of the fuselage skin, 

for discrepant fasteners, and for disbonds at 

the doublers; and do all applicable related 

investigative and corrective actions in 

accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 747– 

53A2747, Revision 2, dated February 22, 

2012, except as provided by paragraph (i)(2) 

of this AD. Repeat the applicable inspections 

thereafter at intervals not to exceed those 

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

Boeing Service Bulletin 747–53A2747, 

Revision 2, dated February 22, 2012. Do all 

applicable related investigative and 

corrective actions at the applicable time 

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

Boeing Service Bulletin 747–53A2747, 

Revision 2, dated February 22, 2012. Options 

provided in Boeing Service Bulletin 747– 

53A2747, Revision 2, dated February 22, 

2011, for accomplishing the disbond 

inspection are acceptable for the 

corresponding requirements of this paragraph 

provided that the inspection is done at the 

applicable times in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Service Bulletin 

747–53A2747, Revision 2, dated February 22, 

2011. 

(1) Replacing a skin panel, in accordance 

with the Accomplishment Instructions of 

Boeing Service Bulletin 747–53A2747, 

Revision 2, dated February 22, 2012, is an 

acceptable alternative to doing the structural 

repair manual (SRM) skin panel repairs and 

the repetitive skin panel inspections 

specified in tables 1, 2, and 3 of paragraph 

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

Bulletin 747–53A2747, Revision 2, dated 

February 22, 2012, for only the skin panel 

that has been replaced. 

(2) Accomplishment of the terminating 

repair identified in tables 4 and 5 of 

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

Service Bulletin 747–53A2747, Revision 2, 

dated February 22, 2012, terminates the 

repetitive inspections identified in tables 4 

and 5 of paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Service Bulletin 747–53A2747, 

Revision 2, dated February 22, 2012, for only 

the area on which the terminating repair has 

been done. 

(h) Terminating Action 

For airplanes identified in tables 4 and 5 

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

Service Bulletin 747–53A2747, Revision 2, 

dated February 22, 2012: At the applicable 

compliance time specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Service Bulletin 

747–53A2747, Revision 2, dated February 22, 

2012, do the terminating action for the repair 

doubler, including doing an open hole HFEC 

inspection for skin cracks at the fastener 

holes common to the inspection area and an 

inspection for disbond of the internal 

doubler; and as applicable, replacing the 

existing external repair doubler with a new 

extended external repair doubler, in 

accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 747– 

53A2747, Revision 2, dated February 22, 

2012, except as provided by paragraph (i)(2) 

of this AD. Accomplishment of the 

terminating action identified in tables 4 and 

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

Service Bulletin 747–53A2747, Revision 2, 

dated February 22, 2012, terminates the 

repetitive inspections identified in tables 4 

and 5 of paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Service Bulletin 747–53A2747, 

Revision 2, dated February 22, 2012, for only 

areas on which the terminating action has 

been done. 

(i) Exceptions to Certain Service Information 

Instructions 

This paragraph specifies exceptions to 

certain instructions in Boeing Service 

Bulletin 747–53A2747, Revision 2, dated 

February 22, 2012. 

(1) Where Boeing Service Bulletin 747– 

53A2747, Revision 2, dated February 22, 

2012, 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. 

(2) Where Boeing Service Bulletin 747– 

53A2747, Revision 2, dated February 22, 

2012, specifies to contact Boeing for special 

repair instructions, this AD requires using a 

method approved in accordance with the 

procedures specified in paragraph (l) of this 

AD. 

(3) The Condition column of paragraph 

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

Bulletin 747–53A2747, Revision 2, dated 

February 22, 2012, refers to certain 


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conditions ‘‘as of the original issue date of 

this service bulletin.’’ This AD, however, 

applies to the airplanes with the specified 

condition as of the effective date of this AD. 

(j) Credit for Previous Actions 

This paragraph provides credit for the 

actions required by paragraphs (g) and (h) of 

this AD, if those actions were performed 

before the effective date of this AD using 

Boeing Service Bulletin 747–53A2747, 

Revision 1, dated October 12, 2011, which is 

not incorporated by reference in this AD. 

(k) Terminating Action for Other ADs 

(1) Accomplishing the requirements of this 

AD terminates the requirements of 

paragraphs (f), (g), and (h) of AD 2006–20– 

02, Amendment 39–14771 (71 FR 56861, 

September 28, 2006). 

(2) Accomplishing the requirements of this 

AD terminates the requirements of 

paragraphs (f), (k), and (l) of AD 2006–24–02, 

Amendment 39–14831 (71 FR 67445, 

November 22, 2006). 

(3) Accomplishing the requirements of this 

AD terminates the requirements of 

paragraphs (f) and (i) of AD 2006–24–05, 

Amendment 39–14834 (71 FR 68434, 

November 27, 2006). 

(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 

paragraph (m)(1) 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. 

(m) Related Information 

(1) For more information about this AD, 

contact Nathan Weigand, Aerospace 

Engineer, Airframe Branch, ANM–120S, 

FAA, Seattle Aircraft Certification Office 

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

98057–3356; phone: 425–917–6428; fax: 425– 

917–6590; email: Nathan.P.Weigand@

faa.gov. 

(2) Service information identified in this 

AD that is not incorporated by reference in 

this AD may be obtained at the addresses 

specified in paragraphs (n)(3) and (n)(4) of 

this AD. 

(n) 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 Service Bulletin 747–53A2747, 

Revision 2, dated February 22, 2012. 

(ii) Reserved. 

(3) For Boeing 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 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. 

(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, WA, on November 15, 

2013. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–28611 Filed 12–2–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1229; Directorate 

Identifier 2012–NM–135–AD; Amendment 

39–17684; AD 2013–24–10] 

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 757 and 

Model 767 airplanes. This AD was 

prompted by a standby power relay 

failure and subsequent illumination of 

the ‘‘STANDBY BUS OFF’’ light, which 

led the flightcrew to set the standby 

power switch to the ‘‘BAT’’ position, 

isolating the battery and standby buses, 

disabling the battery charger, and 

eventually causing the main battery to 

be depleted. This AD requires doing 

wiring changes and installing a new air/ 

ground relay to the battery charger 

system. We are issuing this AD to 

prevent discharge of the main battery, 

which could result in multiple system 

degradation, reduced airplane 

controllability, and runway excursion 

upon landing. 

DATES: This AD is effective January 7, 

2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of January 7, 2014. 

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 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; 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: 

Marie Hogestad, Aerospace Engineer, 

Systems and Equipment Branch, ANM– 

130S, Seattle Aircraft Certification 

Office (ACO), FAA, 1601 Lind Avenue 

SW., Renton, WA 98057–3356; phone: 

425–917–6418; fax: 425–917–6590; 

email: marie.hogestad@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to the specified products. The 

NPRM published in the Federal 

Register on December 20, 2012 (77 FR 

75402). The NPRM proposed to require 

doing wiring changes and installing a 


emcdonald on DSK67QTVN1PROD with RULES