8516 Federal Register / Vol. 80, No. 32 / Wednesday, February 18, 2015 / Rules and Regulations 

test to check for bonding between the re-fuel 

adaptor of the gravity fill and the top skin 

panels on the left-hand and right-hand wings, 

in accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

57–1152, Revision 01, dated December 19, 

2013. 

(1) If the resistance value is 10 milliohms 

or less at the left-hand and right-hand wing, 

no further action is required by this 

paragraph. 

(2) If the resistance value is greater than 10 

milliohms at the left-hand or right-hand 

wing, before further flight, do a general visual 

inspection for corrosion of the component 

interface and adjacent area, in accordance 

with the Accomplishment Instructions of 

Airbus Service Bulletin A320–57–1152, 

Revision 01, dated December 19, 2013. If any 

corrosion is found during the inspection, 

before further flight, repair the gravity fill 

fuel adaptor, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–57–1152, Revision 01, 

dated December 19, 2013; except where 

Airbus Service Bulletin A320–57–1152, 

Revision 01, dated December 19, 2013, 

specifies to contact Airbus, before further 

flight, repair using a method approved by the 

Manager, International Branch, ANM–116, 

Transport Airplane Directorate, FAA; or the 

European Aviation Safety Agency (EASA); or 

Airbus’s EASA Design Organization 

Approval (DOA). If approved by the DOA, 

the approval must include the DOAauthorized signature. 

(h) Credit for Previous Actions 

This paragraph provides credit for the 

actions specified in paragraph (g) of this AD, 

if those actions were performed before the 

effective date of this AD using Airbus Service 

Bulletin A320–57–1152, dated June 14, 2010, 

which was incorporated by reference in AD 

2012–09–07, Amendment 39–17042 (77 FR 

28238, May 14, 2012). 

(i) New Requirement of This AD: 

Maintenance Check/Electrical Bonding Test 

and Corrective Action if Necessary 

For airplanes other than those identified in 

paragraph (g) of this AD: Within 24 months 

after the effective date of this AD, determine 

whether a corrosion repair has been done on 

an overwing refueling aperture, whereby a 

primer coating has been applied on the 

mating surface of the aperture flange. A 

review of the airplane maintenance records is 

acceptable to make this determination, 

provided that whether a primer coat was 

applied can be conclusively determined from 

that review. 

(1) If it is determined that a primer coating 

was applied on the mating surface of the 

aperture flange; or if a determination cannot 

be made, or the outcome is inconclusive: 

Within 24 months after the effective date of 

this AD do the electrical bonding test 

specified in paragraph (g) of this AD, and 

before further flight, do all applicable actions 

specified in paragraph (g)(2) of this AD. 

(2) If it is determined that a corrosion 

repair has not been done, and a primer 

coating has not been applied on the mating 

surface of the aperture flange since first entry 

into service, no further action is required by 

this paragraph. 

(j) Corrosion Repair Provision 

As of the effective date of this AD, any 

corrosion repair done on an overwing 

refueling aperture on any airplane must 

comply with the repair requirements of 

paragraph (g)(2) of this AD. 

(k) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to ATTN: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1405; fax 425–227–1149. 

Information may be emailed to: 9-ANM-116- 

AMOC-REQUESTS@faa.gov. 

(i) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/

certificate holding district office. The AMOC 

approval letter must specifically reference 

this AD. 

(ii) AMOCs approved previously for AD 

2012–09–07, Amendment 39–17042 (77 FR 

28238, May 14, 2012), are approved as 

AMOCs for the corresponding provisions of 

this AD. 

(2) Contacting the Manufacturer: As of the 

effective date of this AD, for any requirement 

in this AD to obtain corrective actions from 

a manufacturer, the action must be 

accomplished using a method approved by 

the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

EASA; or Airbus’s EASA DOA. If approved 

by the DOA, the approval must include the 

DOA-authorized signature. 

(l) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2013–0277R1, dated 

December 4, 2013, for related information. 

This MCAI may be found in the AD docket 

on the Internet at 

http://www.regulations.gov/#!document

Detail;D=FAA-2014-0484-0002. 

(2) Service information identified in this 

AD that is not incorporated by reference in 

this AD is available at the addresses specified 

in paragraphs (m)(4) and (m)(5) 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 this AD specifies otherwise. 

(i) Airbus Service Bulletin A320–57–1152, 

Revision 01, dated December 19, 2013. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Airbus, Airworthiness 

Office—EIAS, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

telephone +33 5 61 93 36 96; fax +33 5 61 

93 44 51; email account.airworth-eas@

airbus.com; Internet http://www.airbus.com. 

(4) You may view this service information 

at the FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, WA. For 

information on the availability of this 

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

(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 February 

4, 2015. 

Dionne Palermo, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–02697 Filed 2–17–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0522; Directorate 

Identifier 2014–NM–087–AD; Amendment 

39–18100; AD 2015–03–04] 

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 reports of fuselage skin 

cracks at the lower forward corner of the 

main entry door (MED) 1 cutout. This 

AD requires repetitive inspections of the 

fuselage skin of the MED 1 cutout for 

cracking, and repair if necessary; and 

also provides an optional terminating 

modification, including post-repair or 

post-modification fuselage skin 

inspections for cracking, and corrective 

actions if necessary. We are issuing this 

AD to detect and correct skin cracking, 

which can become large and could 

adversely affect the structural integrity 

of the airplane. 

DATES: This AD is effective March 25, 

2015. 

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Federal Register / Vol. 80, No. 32 / Wednesday, February 18, 2015 / Rules and Regulations 8517 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of March 25, 2015. 

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. It is also available 

on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2014– 

0522. 

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– 

0522; 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 

Docket 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, Seattle 

Aircraft Certification Office (ACO), 

FAA, 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 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. The NPRM published in the 

Federal Register on August 5, 2014 (79 

FR 45385). The NPRM was prompted by 

reports of fuselage skin cracks at the 

lower forward corner of the MED 1 

cutout. The NPRM proposed to require 

repetitive inspections of the fuselage 

skin of the MED 1 cutout for cracking, 

and repair if necessary. The NPRM also 

provided optional terminating 

modification, including post-repair or 

post-modification inspections for 

cracking of the fuselage skin, and 

corrective actions if necessary. We are 

issuing this AD to detect and correct 

skin cracking, which can become large 

and could adversely affect the structural 

integrity of the airplane. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the NPRM (79 FR 45385, 

August 5, 2014) and the FAA’s response 

to each comment. 

Support for the NPRM (79 FR 45385, 

August 5, 2014) 

UPS stated that it agrees with the 

intent of the NPRM (79 FR 45385, 

August 5, 2014). 

Request To Withdraw the NPRM (79 FR 

45385, August 5, 2014) 

Mr. Jerry Adams requested that we 

withdraw the NPRM (79 FR 45385, 

August 5, 2014). Mr. Adams stated that 

the manufacturer’s analysis and 

subsequent action referred to in Boeing 

Alert Service Bulletin 747–53A2863, 

dated March 11, 2014, should be 

sufficient. Mr. Adams stated that the 

cost of compliance does not include the 

increased cost of airframes that the 

customer must pay for, and that will 

subsequently be passed along to the 

traveling consumer. Mr. Adams asserted 

that this AD action would be 

counterproductive to business and the 

cost of transportation to the general 

public. 

We agree with the comment that the 

actions described in Boeing Alert 

Service Bulletin 747–53A2863, dated 

March 11, 2014, are sufficient to correct 

the identified unsafe condition. 

However, we do not agree with the 

commenter’s request to withdraw the 

NPRM (79 FR 45385, August 5, 2014). 

We have identified an unsafe condition 

that is likely to exist or develop in other 

products. Therefore, we must issue an 

airworthiness directive to correct the 

identified unsafe condition, as required 

by section 39.5 of the Federal Aviation 

Regulations (14 CFR 39.5). We 

accomplish this by mandating specified 

actions described in Boeing Alert 

Service Bulletin 747–53A2863, dated 

March 11, 2014, by AD action. We have 

not changed this AD in this regard. 

We also note that although the 

commenter stated that the cost of 

airframes was not included in the 

NPRM (79 FR 45385, August 5, 2014), 

this AD does not require replacing 

airframes. The costs of accomplishing 

the actions required by this AD, as 

specified in Boeing Alert Service 

Bulletin 747–53A2863, dated March 11, 

2014 (inspection, repair if necessary, 

and optional modification), are included 

in the Costs of Compliance section of 

this AD. 

Request To Revise the Description of 

the Location Where Cracking Was 

Identified 

Boeing requested that we revise the 

SUMMARY and Discussion sections of 

the preamble, and paragraphs (e), (g), 

and (i) in the proposed AD (79 FR 

45385, August 5, 2014) to clarify that 

the cracking occurs in the fuselage skin, 

which would match the title of Boeing 

Alert Service Bulletin 747–53A2863, 

dated March 11, 2014. 

We agree with the commenter’s 

request because this change will help 

clarify the cracking location. We have 

revised this AD accordingly. 

Request To Revise Service Information 

and Cost Estimate 

UPS requested that we revise the 

service information used in this AD. 

UPS stated that the power panels and 

other equipment outboard of the main 

equipment center (MEC) must be 

removed in order to access the repair or 

modification area specified in the 

NPRM (79 FR 45385, August 5, 2014). 

UPS stated that these removals are 

currently not included in the 

Accomplishment Instructions of Boeing 

Alert Service Bulletin 747–53A2863, 

dated March 11, 2014, and will require 

significantly greater manpower than 

specified in the NPRM. 

We disagree with the commenter’s 

request. We have determined it is not 

appropriate to delay this AD to 

incorporate revised service information 

that might be published sometime in the 

future. Note 10, in the Accomplishment 

Instructions of Boeing Alert Service 

Bulletin 747–53A2863, dated March 11, 

2014, states: 

If it is necessary to remove more parts for 

access, you can remove those parts. If you 

can get access without removing identified 

parts, it is not necessary to remove all of the 

identified parts. Jacking and shoring 

limitations must be observed. 

Therefore, operators are already 

permitted to alter the way they gain 

access to the required areas for 

inspections/repairs/modifications 

specified in this AD. We have received 

no definitive data that would enable us 

to provide cost estimates for the MEC 

removal. We have not changed this AD 

in this regard. 

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8518 Federal Register / Vol. 80, No. 32 / Wednesday, February 18, 2015 / Rules and Regulations 

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 (79 FR 

45385, August 5, 2014) for correcting 

the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (79 FR 45385, 

August 5, 2014). 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this AD. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Boeing Alert Service 

Bulletin 747–53A2863, dated March 11, 

2014. The service information describes 

procedures for inspection, repair, and 

modification at the lower forward 

corner of the fuselage main entry door 

1. This service information is reasonably 

available; see ADDRESSES for ways to 

access this service information. 

Costs of Compliance 

We estimate that this AD affects 165 

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 (per door) ............... 11 work-hours × $85 per hour 

= $935 per inspection cycle.

$0 $935 per inspection cycle ....... $154,275 per inspection cycle. 

Optional modification (per 

door).

Up to 66 work-hours × $85 

per hour = $5,610.

0 Up to $5,610 ........................... Up to $925,650. 

Post-repair or -modification inspection (per door).11 work-hours × $85 per hour 

= $935 per inspection cycle.

0 $935 per inspection cycle ....... $154,275 per inspection cycle. 

We estimate the following costs to do 

any necessary repair 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 repair: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per product 

Repair (per door) .............................. 66 work-hours × $85 per hour = 

$5,610.

$7,380 or $9,360 .............................. $12,990 or $14,970. 

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): 

2015–03–04 The Boeing Company: 

Amendment 39–18100 ; Docket No. 

FAA–2014–0522; Directorate Identifier 

2014–NM–087–AD. 

(a) Effective Date 

This AD is effective March 25, 2015. 

(b) Affected ADs 

None. 

(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 Alert 

Service Bulletin 747–53A2863, dated March 

11, 2014. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

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Federal Register / Vol. 80, No. 32 / Wednesday, February 18, 2015 / Rules and Regulations 8519 

(e) Unsafe Condition 

This AD was prompted by reports of 

fuselage skin cracks at the lower forward 

corner of the main entry door (MED) 1 

cutout. We are issuing this AD to detect and 

correct skin cracking, which can become 

large and could adversely affect the structural 

integrity of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Repetitive Inspections and Corrective 

Actions 

Except as specified in paragraph (j)(1) of 

this AD, at the applicable time specified in 

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

Alert Service Bulletin 747–53A2863, dated 

March 11, 2014: Do a detailed inspection and 

a surface high frequency eddy current 

inspection for cracking of the fuselage skin at 

the applicable MED 1 cutout, and do all 

applicable corrective actions, in accordance 

with the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–53A2863, 

dated March 11, 2014. Do all applicable 

corrective actions before further flight. 

Repeat the inspections of the applicable MED 

1 cutout thereafter at the applicable intervals 

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

Boeing Alert Service Bulletin 747–53A2863, 

dated March 11, 2014. Accomplishing the 

corrective actions required by this paragraph 

terminates the repetitive inspection 

requirements of this paragraph. 

(h) Optional Terminating Action 

For airplanes on which no crack is found 

during the initial inspections required by 

paragraph (g) of this AD: Installing the 

preventive modification in accordance with 

the Accomplishment Instructions of Boeing 

Alert Service Bulletin 747–53A2863, dated 

March 11, 2014, terminates the repetitive 

inspections required by paragraph (g) of this 

AD. 

(i) Post-Repair or Post-Modification 

Repetitive Inspections and Corrective 

Actions 

For airplanes on which the corrective 

actions required by paragraph (g) of this AD 

have been done, or airplanes that have 

installed the preventive modification 

specified in paragraph (h) of this AD: At the 

applicable time specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2863, dated March 11, 

2014, do a detailed inspection for cracking of 

the fuselage skin at the applicable MED 1 

cutout, and do all applicable corrective 

actions, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2863, dated March 

11, 2014, except as specified in paragraph 

(j)(2) of this AD. Do all applicable corrective 

actions before further flight. Repeat the 

inspection of the fuselage skin at the 

applicable MED 1 cutout thereafter at the 

intervals specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2863, dated March 11, 

2014. 

(j) Exceptions to Service Information 

(1) Where paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin 747–53A2863, 

dated March 11, 2014, 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) If any cracking is found during any 

inspection required by this AD, and Boeing 

Alert Service Bulletin 747–53A2863, dated 

March 11, 2014, specifies to contact Boeing 

for appropriate action: Before further flight, 

repair the cracking using a method approved 

in accordance with the procedures specified 

in paragraph (k) of this AD. 

(k) 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 (l)(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. 

(l) Related Information 

For more information about this AD, 

contact Nathan Weigand, Aerospace 

Engineer, Airframe Branch, ANM–120S, 

Seattle Aircraft Certification Office (ACO), 

FAA, 1601 Lind Avenue SW., Renton, WA 

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

917–6590; email: 

Nathan.P.Weigand@faa.gov. 

(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 Alert Service Bulletin 747– 

53A2863, dated March 11, 2014. 

(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 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. 

(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 February 

2, 2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–02689 Filed 2–17–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF COMMERCE 

Bureau of Industry and Security 

15 CFR Parts 730 and 744 

[Docket No. 150123073–5073–01] 

RIN 0694–AG48 

Updated Statements of Legal Authority 

for the Export Administration 

Regulations To Include Presidential 

Notice of January 21, 2015 

AGENCY: Bureau of Industry and 

Security, Commerce. 

ACTION: Final rule. 

SUMMARY: This rule updates the Code of 

Federal Regulations (CFR) legal 

authority paragraphs in the Export 

Administration Regulations (EAR) to 

cite a Presidential notice that extended 

an emergency declared pursuant to the 

International Emergency Economic 

Powers Act. This is a procedural rule 

that only updates authority paragraphs 

of the EAR. It does not alter any right, 

obligation or prohibition that applies to 

any person under the EAR. 

DATES: The rule is effective February 18, 

2015. 

FOR FURTHER INFORMATION CONTACT: 

William Arvin, Regulatory Policy 

Division, Bureau of Industry and 

Security, Email william.arvin@

bis.doc.gov, Telephone: (202) 482–2440. 

SUPPLEMENTARY INFORMATION: 

Background 

The authority for parts 730 and 744 of 

the EAR (15 CFR parts 730 and 744) 

rests, in part, on Executive Order 12947 

of January 23, 1995—Prohibiting 

Transactions With Respect to Terrorists 

Who Threaten To Disrupt the Middle 

East Peace Process (60 FR 5079, 3 CFR, 

1995 Comp., p. 356) and on annual 

notices by the President continuing the 

emergency declared in that order. This 

rule updates the authority paragraphs in 

15 CFR parts 730 and 744 to cite the 

Notice of January 21, 2015, 80 FR 3461 

(January 22, 2015), which is the most 

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