Federal Register / Vol. 81, No. 23 / Thursday, February 4, 2016 / Rules and Regulations 5893 

Service Bulletin A300–53–6123, Revision 06, 

dated September 28, 2011, except as 

provided by paragraph (m) of this AD. 

(m) New Requirement of This AD: Exception 

to Service Information 

If any crack is found during any inspection 

required by paragraph (j) or (k) of this AD 

and Airbus Service Bulletin A300–53–6123, 

Revision 06, dated September 28, 2011; or 

Airbus Service Bulletin A300–53–0350, 

Revision 03, dated July 26, 2007; specifies to 

contact Airbus: Before further flight, repair 

the crack using a method approved by the 

Manager, International Branch, ANM–116, 

Transport Airplane Directorate, FAA; or the 

EASA; or Airbus’s EASA DOA. 

(n) Credit for Previous Actions 

This paragraph provides credit for actions 

required by paragraphs (j) and (l) of this AD, 

if those actions were performed before the 

effective date of this AD using the applicable 

service information specified in paragraphs 

(n)(1) through (n)(6) of this AD. 

(1) Airbus Service Bulletin A300–53–0350, 

Revision 01, dated December 18, 2001, which 

is not incorporated by reference in this AD. 

(2) Airbus Service Bulletin A300–53–0350, 

Revision 02, excluding Appendix 01, dated 

November 12, 2002, which was incorporated 

by reference in AD 2004–20–14, Amendment 

39–13819 (69 FR 60809, October 13, 2004). 

(3) Airbus Service Bulletin A300–53–6123, 

Revision 01, dated December 18, 2001, which 

is not incorporated by reference in this AD. 

(4) Airbus Service Bulletin A300–53–6123, 

Revision 03, dated August 20, 2004, which is 

not incorporated by reference in this AD. 

(5) Airbus Service Bulletin A300–53–6123, 

Revision 04, dated April 25, 2008, which is 

not incorporated by reference in this AD. 

(6) Airbus Service Bulletin A300–53–6123, 

Revision 05, dated August 1, 2011, which is 

not incorporated by reference in this AD. 

(o) 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: 

Dan Rodina, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–2125; fax 425–227–1149. 

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

AMOC-REQUESTS@faa.gov. 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. 

(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 

the EASA; or Airbus’s EASA DOA. If 

approved by the DOA, the approval must 

include the DOA-authorized signature. 

(p) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) 

Airworthiness Directive 2013–0184R1, dated 

August 22, 2013, for related information. 

This MCAI may be found in the AD docket 

on the Internet at http://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2015–1417. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (q)(5) and (q)(6) of this AD. 

(q) 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. 

(3) The following service information was 

approved for IBR on March 10, 2016. 

(i) Airbus Service Bulletin A300–53–0350, 

Revision 03, dated July 26, 2007. 

(ii) Airbus Service Bulletin A300–53–6123, 

Revision 06, dated September 28, 2011. 

(4) The following service information was 

approved for IBR on November 17, 2004 (69 

FR 60809, October 13, 2004). 

(i) Airbus Service Bulletin A300–53–6123, 

Revision 02, excluding Appendix 01, dated 

November 12, 2002. 

(ii) Reserved. 

(5) For service information identified in 

this AD, contact Airbus SAS, Airworthiness 

Office—EAW, 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. 

(6) 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. 

(7) 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 

December 31, 2015. 

Phil Forde, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–00379 Filed 2–3–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–1983; Directorate 

Identifier 2015–NM–020–AD; Amendment 

39–18388; AD 2016–03–01] 

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 737–100, –200, 

–200C, –300, –400, and –500 series 

airplanes. This AD was prompted by a 

report of a crack of the forward leg of 

the left front spar lower chord and 

cracks on the lower wing skin at three 

fastener holes common to the nacelle 

outboard side load fitting. This AD 

requires repetitive inspections for cracks 

on the front spar lower chord, inspar 

skin, and wing skin, and corrective 

action if necessary. We are issuing this 

AD to detect and correct fatigue 

cracking of the forward leg of the front 

spar lower chord, inspar skin, and wing 

skin common to the nacelle outboard 

side load fitting, which could adversely 

affect the structural integrity of the 

wing. 

DATES: This AD is effective March 10, 

2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of March 10, 2016. 

ADDRESSES: For service information 

identified in this final rule, 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–2015– 

1983. 

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–2015– 


asabaliauskas on DSK5VPTVN1PROD with RULES
5894 Federal Register / Vol. 81, No. 23 / Thursday, February 4, 2016 / Rules and Regulations 

1983; 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: 

Jennifer Tsakoumakis, Aerospace 

Engineer, Airframe Branch, ANM–120L, 

FAA, Los Angeles Aircraft Certification 

Office (ACO), 3960 Paramount 

Boulevard, Lakewood, CA 90712–4137; 

phone: 562–627–5264; fax: 562–627– 

5210; email: jennifer.tsakoumakis@

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 all The Boeing Company Model 

737–100, –200, –200C, –300, –400, and 

–500 series airplanes. The NPRM 

published in the Federal Register on 

June 24, 2015 (80 FR 36258) (‘‘the 

NPRM’’). The NPRM was prompted by 

a report of a crack of the forward leg of 

the left front spar lower chord and 

cracks on the lower wing skin at three 

fastener holes common to the nacelle 

outboard side load fitting. The NPRM 

proposed to require repetitive 

inspections for cracks on the front spar 

lower chord, inspar skin, and wing skin, 

and corrective action if necessary. We 

are issuing this AD to correct the unsafe 

condition on these products. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the NPRM and the FAA’s 

response to each comment. 

Support for the NPRM 

Boeing stated that it concurs with the 

NPRM. 

Effect of Winglets on Accomplishment 

of the NPRM 

Southwest Airlines (SWA) requested 

clarification whether the installation of 

Aviation Partners Boeing (APB) 

Supplemental Type Certificate (STC) 

ST01219SE (http://rgl.faa.gov/

Regulatory_and_Guidance_Library/

rgstc.nsf/0/

ebd1cec7b301293e86257cb30045557a/

$FILE/ST01219SE.pdf) has any affect to 

the ability of accomplishment of the 

action of this proposed AD (80 FR 

36258, June 24, 2015). APB stated that 

the installation of winglets per STC 

ST01219SE does not affect the 

accomplishment of the manufacturer’s 

service instructions. 

We concur with APB’s comment and 

agree to clarify. We have redesignated 

paragraph (c) of the proposed AD (80 FR 

36258, June 24, 2015) as paragraph (c)(1) 

and added new paragraph (c)(2) to this 

AD to state that installation of STC 

ST01219SE (http://rgl.faa.gov/

Regulatory_and_Guidance_Library/

rgstc.nsf/0/

ebd1cec7b301293e86257cb30045557a/

$FILE/ST01219SE.pdf) does not affect 

the ability to accomplish the actions 

required by this AD. Therefore, for 

airplanes on which STC ST01219SE 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. 

Request for Critical Design 

Configuration Control Limitation 

(CDCCL) Instructions 

SWA requested that we add 

instructions to paragraph (i) of the 

proposed AD (80 FR 36258, June 24, 

2015) to specify that important CDCCL 

information must be observed during 

access and close-up while performing 

the actions specified in paragraph (i) of 

the proposed AD. SWA explained that 

Boeing Alert Service Bulletin 737– 

57A1323, dated December 5, 2014, does 

not contain any references to CDCCLs, 

despite the required access to the fuel 

tank, in order to perform either option 

1 or option 2 non-destructive test 

inspection requirements. SWA stated 

that the access and close-up steps 

indicate, as a reference, the maintenance 

planning document (section 4), which 

does not provide a clear path to the 

airplane maintenance manual section 

that addresses CDCCL requirements. 

We agree with the commenter’s 

request. Boeing Alert Service Bulletin 

737–57A1323, dated December 5, 2014, 

does not contain any references to 

CDCCLs that are part of the 

airworthiness limitations (AWLs). All 

applicable AWLs must still be observed 

while performing the actions mandated 

by this AD. We have revised paragraph 

(i) of this AD to state that while 

accomplishing the actions required by 

paragraph (i) of this AD, operators must 

ensure that all applicable CDCCLs are 

complied with. 

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 for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM. 

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 737–57A1323, dated December 

5, 2014. The service information 

describes procedures for repetitive 

inspections for cracks on the left and 

right wing front spar lower chord, 

inspar skin, and wing skin, and 

corrective action. The service 

information is reasonably available 

because the interested parties have 

access to it through their normal course 

of business or by the means identified 

in the ADDRESSES section. 

Costs of Compliance 

We estimate that this AD affects 331 

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 (28 Group 2 airplanes) 7 work-hours × $85 per hour = 

$595 per inspection cycle.

$0 ...................... $595 per inspection cycle.$16,660 per inspection cycle. 

Inspection and fastener installation (302 Group 3 airplanes).Up to 94 work-hours × $85 per 

hour = $7,990 per inspection 

cycle.

0 ........................ Up to $7,990 per 

inspection 

cycle.

Up to $2,412,980 per inspection 

cycle. 


asabaliauskas on DSK5VPTVN1PROD with RULES
Federal Register / Vol. 81, No. 23 / Thursday, February 4, 2016 / Rules and Regulations 5895 

We have received no definitive data 

that will enable us to provide cost 

estimates for the actions specified for 

the Group 1 airplane in this AD. 

We also have received no definitive 

data that will 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 

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): 

2016–03–01 the Boeing Company: 

Amendment 39–18388; Docket No. 

FAA–2015–1983; Directorate Identifier 

2015–NM–020–AD. 

(a) Effective Date 

This AD is effective March 10, 2016. 

(b) Affected ADs 

None. 

(c) Applicability 

(1) This AD applies to all The Boeing 

Company Model 737–100, –200, –200C, 

–300, –400, and –500 series airplanes, 

certificated in any category. 

(2) Installation of Supplemental Type 

Certificate (STC) ST01219SE (http://

rgl.faa.gov/Regulatory_and_Guidance_

Library/rgstc.nsf/0/ebd1cec7b301293e86257

cb30045557a/$FILE/ST01219SE.pdf) does 

not affect the ability to accomplish the 

actions required by this AD. Therefore, for 

airplanes on which STC ST01219SE is 

installed, a ’’change in product’’ alternative 

method of compliance (AMOC) approval 

request is not necessary to comply with the 

requirements of 14 CFR 39.17. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Unsafe Condition 

This AD was prompted by a report of a 

crack in the forward leg of the left front spar 

lower chord and cracks on the lower wing 

skin at three fastener holes common to the 

nacelle outboard side load fitting. We are 

issuing this AD to detect and correct fatigue 

cracking of the forward leg of the front spar 

lower chord, inspar skin, and wing skin 

common to the nacelle outboard side load 

fitting, which could adversely affect the 

structural integrity of the wing. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspections and Corrective Actions for 

Group 1 Airplanes 

For Group 1 airplanes identified in Boeing 

Alert Service Bulletin 737–57A1323, dated 

December 5, 2014: Within 120 days after the 

effective date of this AD, do inspections of 

the left and right wing front spar lower chord 

and inspar skin, and the left and right wing 

nacelle outboard side load fitting fastener 

holes common to the front spar lower chord 

and skin, and do all applicable corrective 

actions, using a method approved in 

accordance with the procedures specified in 

paragraph (k) of this AD. 

(h) Repetitive Detailed Inspections and 

Corrective Actions 

For Group 2 and 3 airplanes identified in 

Boeing Alert Service Bulletin 737–57A1323, 

dated December 5, 2014: Except as provided 

by paragraph (j)(1) of this AD, at the 

applicable time specified in Table 1 of 

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

Alert Service Bulletin 737–57A1323, dated 

December 5, 2014, do a detailed inspection 

for cracks on the left and right wing front 

spar lower chord and inspar skin, and do all 

applicable corrective actions, in accordance 

with the Accomplishment Instructions of 

Boeing Alert Service Bulletin 737–57A1323, 

dated December 5, 2014, except as specified 

in paragraph (j)(2) of this AD. Do all 

applicable corrective actions before further 

flight. Repeat the inspection thereafter at the 

applicable interval specified in Table 1 of 

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

Alert Service Bulletin 737–57A1323, dated 

December 5, 2014, except in areas repaired in 

accordance with the procedures specified in 

paragraph (k) of this AD. 

(i) Repetitive High Frequency Eddy Current 

(HFEC) Inspections and Corrective Actions 

For Group 3 airplanes identified in Boeing 

Alert Service Bulletin 737–57A1323, dated 

December 5, 2014: Except as provided by 

paragraph (j)(1) of this AD, at the applicable 

time specified in Table 2 or Table 3 of 

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

Alert Service Bulletin 737–57A1323, dated 

December 5, 2014, do the actions specified in 

paragraphs (i)(1) or (i)(2) of this AD. Repeat 

the inspection specified in either paragraph 

(i)(1) or (i)(2) of this AD thereafter at the 

applicable interval specified in Table 2 or 

Table 3 of paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin737–57A1323, 

dated December 5, 2014. While 

accomplishing the actions required by this 

paragraph, ensure that all applicable critical 

design configuration control limitations are 

complied with. 

(1) Do an HFEC open hole probe inspection 

for cracks of the left and right wing nacelle 

outboard side load fitting fastener holes 

common to the front spar lower chord and 

skin, and perform all applicable corrective 

actions, in accordance with Part 2, Option 1 

of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 737–57A1323, 

dated December 5, 2014, except as provided 

by paragraph (j)(2) of this AD. Do all 

applicable corrective actions before further 

flight. 

(2) Do an HFEC surface probe inspection 

for cracks in the wing inspar skin, and 

perform all applicable corrective actions, in 

accordance with Part 2, Option 2 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–57A1323, dated 

December 5, 2014, except as provided by 

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

corrective actions before further flight. 

(j) Exceptions to Service Information 

Specifications 

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

Boeing Alert Service Bulletin 737–57A1323, 

dated December 5, 2014, specifies a 

compliance time ‘‘after the original issue date 

of this service bulletin,’’ this AD requires 


asabaliauskas on DSK5VPTVN1PROD with RULES
5896 Federal Register / Vol. 81, No. 23 / Thursday, February 4, 2016 / Rules and Regulations 

compliance within the specified compliance 

time ‘‘after the effective date of this AD.’’ 

(2) Although Boeing Alert Service Bulletin 

737–57A1323, dated December 5, 2014, 

specifies to contact Boeing for repair 

instructions, and specifies that action as 

‘‘RC’’ (Required for Compliance), this AD 

requires repair before further flight 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, Los Angeles 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) of this AD. Information may be 

emailed to: 9-ANM-LAACO-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, 

modification, or alteration required by this 

AD if it is approved by the Boeing 

Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Los Angeles 

ACO, to make those findings. To be 

approved, the repair method, modification 

deviation, or alteration deviation must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(4) Except as required by paragraph (j)(2) 

of this AD: For service information that 

contains steps that are labeled as Required 

for Compliance (RC), the provisions of 

paragraphs (k)(4)(i) and (k)(4)(ii) apply. 

(i) The steps labeled as RC, including 

substeps under an RC step and any figures 

identified in an RC step, must be done to 

comply with the AD. An AMOC is required 

for any deviations to RC steps, including 

substeps and identified figures. 

(ii) Steps not labeled as RC may be 

deviated from using accepted methods in 

accordance with the operator’s maintenance 

or inspection program without obtaining 

approval of an AMOC, provided the RC steps, 

including substeps and identified figures, can 

still be done as specified, and the airplane 

can be put back in an airworthy condition. 

(l) Related Information 

For more information about this AD, 

contact Jennifer Tsakoumakis, Aerospace 

Engineer, Airframe Branch, ANM–120L, 

FAA, Los Angeles ACO, 3960 Paramount 

Boulevard, Lakewood, CA 90712–4137; 

phone: 562–627–5264; fax: 562–627–5210; 

email: jennifer.tsakoumakis@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 737– 

57A1323, dated December 5, 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 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 January 

25, 2016. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–01827 Filed 2–3–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Parts 61 and 183 

[Docket No.: FAA–2010–1127; Amdt. Nos. 

61–135 and 183–15] 

RIN 2120–AJ42 

Student Pilot Application 

Requirements 

Correction 

In rule document 2016–00199 

beginning on page 1292 in the issue of 

Tuesday, January 12, 2016, make the 

following correction: 

1. On pages 1293–1294, table ‘‘B. 

Student Pilot Application 

Requirements: Summary of Current, 

Proposed, and Finalized Provisions’’ is 

corrected as set forth below. 

B. Student Pilot Application 

Requirements: Summary of Current, 

Proposed, and Finalized Provisions 


asabaliauskas on DSK5VPTVN1PROD with RULES