Federal Register / Vol. 83, No. 9 / Friday, January 12, 2018 / Rules and Regulations 1529 

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): 

2018–01–11 Airbus: Amendment 39–19152; 

Docket No. FAA–2017–1244; Product 

Identifier 2013–NM–145–AD. 

(a) Effective Date 

This AD becomes effective January 29, 

2018. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus Model A319– 

115 and A319–133 airplanes, certificated in 

any category, all manufacturer serial 

numbers, having received in production 

Airbus modification 33125 (installation of 

Gaseous Oxygen System (GOS) for 

passengers), except those on which Airbus 

modification 153555 and 155860 have been 

embodied in production. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 35, Oxygen. 

(e) Reason 

This AD was prompted by a fire during a 

flight, in the vicinity of the GOS for 

passengers. We are issuing this AD to prevent 

an uncontrolled fire in the vicinity of the 

GOS for passengers, near the cargo area, 

which could result in loss of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Action(s) 

Within 30 days after the effective date of 

this AD, request instructions from the 

Manager, International Section, Transport 

Standards Branch, FAA, to address the 

unsafe condition specified in paragraph (e) of 

this AD; and accomplish the actions at the 

times specified in, and in accordance with, 

those instructions. Guidance can be found in 

Mandatory Continuing Airworthiness 

Information (MCAI) European Aviation 

Safety Agency (EASA) AD 2014–0045, dated 

February 25, 2014; corrected March 4, 2014. 

(h) Alternative Methods of Compliance 

(AMOCs) 

The Manager, International Section, 

Transport Standards Branch, 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 Section, send it to the 

attention of the person identified in 

paragraph (i)(2) of this AD. Information may 

be emailed to: 9-ANM-116-AMOCREQUESTS@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. 

(i) Related Information 

(1) Refer to MCAI EASA AD 2014–0045, 

dated February 25, 2014; corrected March 4, 

2014, for related information. You may 

examine the MCAI on the internet at http:// 

www.regulations.gov by searching for and 

locating Docket No. FAA–2017–1244. 

(2) For more information about this AD, 

contact Sanjay Ralhan, Aerospace Engineer, 

International Section, Transport Standards 

Branch, FAA, 1601 Lind Avenue SW, 

Renton, WA 98057–3356; telephone: 425– 

227–1405; fax: 425–227–1149. 

(j) Material Incorporated by Reference 

None. 

Issued in Renton, Washington, on January 

2, 2018. 

Michael Kaszycki, 

Acting Director, System Oversight Division, 

Aircraft Certification Service. 

[FR Doc. 2018–00343 Filed 1–11–18; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2017–0629; Product 

Identifier 2016–NM–184–AD; Amendment 

39–19149; AD 2018–01–08] 

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 

reports of fatigue cracking in the frame 

outboard chord and in the radius of the 

auxiliary chord at a certain area. This 

AD requires inspections to detect this 

cracking, and corrective action if 

necessary. We are issuing this AD to 

address the unsafe condition on these 

products. 

DATES: This AD is effective February 16, 

2018 . 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of December 26, 2012 (77 FR 69747, 

November 21, 2012). 

ADDRESSES: For service information 

identified in this final rule, contact 

Boeing Commercial Airplanes, 

Attention: Contractual & Data Services 

(C&DS), 2600 Westminster Blvd., MC 

110–SK57, Seal Beach, CA 90740; 

telephone 562–797–1717; internet 

https://www.myboeingfleet.com. You 

may view this service information at the 

FAA, Transport Standards Branch, 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–2017– 

0629. 

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–2017– 

0629; 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 final rule, 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: 

George Garrido, Aerospace Engineer, 

Airframe Section, FAA, Los Angeles 

ACO Branch, 3960 Paramount 

Boulevard, Lakewood, CA 90712–4137; 

phone: 562–627–5232; fax: 562–627– 

5210; email: george.garrido@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 30, 2017 (82 FR 29792). The NPRM 

was prompted by reports of fatigue 

cracking in the frame outboard chord 

and in the radius of the auxiliary chord 

at a certain area. The NPRM proposed 

to require inspections to detect this 

cracking, and corrective action if 

necessary. We are issuing this AD to 

detect and correct fatigue cracking of the 

outboard and auxiliary chords, which 

could result in reduced structural 

integrity of the outboard chord and 

consequent rapid decompression of the 

airplane. 

Comments 

We gave the public the opportunity to 

participate in developing this final rule. 

The following presents the comments 


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1530 Federal Register / Vol. 83, No. 9 / Friday, January 12, 2018 / Rules and Regulations 

received on the NPRM and the FAA’s 

response to each comment. 

Effect of Winglets on Accomplishment 

of the Proposed Actions 

Aviation Partners Boeing stated that 

accomplishing Supplemental Type 

Certificate (STC) ST01219SE does not 

affect the ability to accomplish the 

actions specified in the NPRM. 

We agree with the commenter. We 

have redesignated paragraph (c) of the 

proposed AD as (c)(1) and added 

paragraph (c)(2) to this AD to state that 

installation of STC ST01219SE 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 methods of compliance 

(AMOC) approval request is not 

necessary to comply with the 

requirements of 14 CFR 39.17. 

Request To Remove Certain Language 

in Paragraph (i) of the Proposed AD 

Boeing asked that the language ‘‘and 

repair’’ be removed from paragraph (i) of 

the proposed AD. Boeing stated that the 

language in paragraph (i) refers to a 

section in Part 6 of Boeing Alert Service 

Bulletin 737–53A1166, Revision 2, 

dated May 25, 2006, which is to 

determine if the modification should be 

classified as interim or permanent. 

Boeing noted that the additional 

language ‘‘and repair’’ is not part of that 

section, and suggested it be deleted. 

We agree with the commenter’s 

request for the reason provided. We 

have deleted ‘‘and repair’’ from 

paragraph (i) of this AD. 

Request To Clarify Certain Language 

Swiftair S.A. stated that the language 

describing the requirements in 

paragraph (h) of the proposed AD is 

confusing. Swiftair asked that the 

effectivity and the requirements 

identified in paragraph (h) of the 

proposed AD be clarified in some way 

due to extensive sub-paragraphs. 

Swiftair recommended that the ‘‘and’’ in 

the sentence be emphasized. 

We acknowledge the commenter’s 

concern. However, we cannot 

emphasize or highlight specific text in 

an AD. The affected airplanes in 

paragraph (h) of the AD are those that 

meet all of the criteria specified in the 

sub-paragraphs. We have not changed 

this AD in this regard. 

Swiftair S.A. also stated that the 

language describing the requirements in 

paragraph (j) of the proposed AD is 

confusing. Swiftair added that the preregulatory text in the NPRM refers to 

actions from AD 2012–23–04, 

Amendment 39–17260 (77 FR 69747, 

November 21, 2012) (‘‘AD 2012–23–04’’) 

and the combination of that rulemaking 

and the actions in the proposed AD is 

confusing. Swiftair also stated that 

paragraph (r) of AD 2012–23–04 should 

be explained in the current 

requirements and not in the preregulatory text. 

We agree that some clarification is 

necessary. Concerning the request to 

include the current requirements of AD 

2012–23–04 in this AD, we would have 

had to issue different rulemaking. 

Instead of a stand-alone AD, the 

alternative would have been to 

supersede AD 2012–23–04, which 

would have resulted in a single but 

considerably more complex AD. All 

operators identified in AD 2012–23–04 

would then have to show compliance 

with the new supersedure AD. Our 

experience with similar complex ADs, 

and with operator feedback, is that it is 

preferable to leave the existing AD as is 

and issue a related but stand-alone AD 

such as this one. 

To clarify the criteria in paragraph 

(h)(3) of this AD, we have added Note 

1 to paragraph (h)(3) of this AD to 

reference the optional terminating 

action specified in paragraph (r) of AD 

2012–23–04. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting this 

final rule 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 final rule. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Boeing Alert Service 

Bulletin 737–53A1166, Revision 2, 

dated May 25, 2006. The service 

information describes procedures for 

inspections for cracks of the body 

station (BS) 727 frame outboard chord 

and in the radius of the auxiliary chord, 

and repair or replacement if necessary. 

This 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 160 

airplanes of U.S. registry. We estimate 

the following costs to comply with this 

AD: 

ESTIMATED COSTS

Action Labor cost 

Affected 

airplanes 

of U.S. 

registry 

Cost per 

product 

Cost on 

U.S. operators 

Detailed and High Frequency Eddy Current 

(HFEC) inspections.

6 work-hours × $85 per hour = $510 per 

inspection cycle.

5 $510 $2,550 per inspection cycle. 

One-time follow-on HFEC inspection .......... 9 work-hours × $85 per hour = $765 ......... 5 765 $3,825. 

HFEC inspection ......................................... 9 work-hours × $85 per hour = $765 ......... 150 765 $114,750. 

We estimate the following costs to do 

any necessary repairs that are required 

based on the results of the inspections. 

We have no way of determining the 

number of aircraft that might need these 

repairs: 


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Federal Register / Vol. 83, No. 9 / Friday, January 12, 2018 / Rules and Regulations 1531 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Repair of cracking of the outboard chord frame .......... 514 work-hours × $85 per hour = $43,690 .................. $13,586 $57,276. 

Repair of cracking of the outboard chord .................... 49 work-hours × $85 per hour = $4,165 ...................... 4,255 8,420. 

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. 

This AD is issued in accordance with 

authority delegated by the Executive 

Director, Aircraft Certification Service, 

as authorized by FAA Order 8000.51C. 

In accordance with that order, issuance 

of ADs is normally a function of the 

Compliance and Airworthiness 

Division, but during this transition 

period, the Executive Director has 

delegated the authority to issue ADs 

applicable to transport category 

airplanes to the Director of the System 

Oversight Division. 

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): 

2018–01–08 The Boeing Company: 

Amendment 39–19149; Docket No. 

FAA–2017–0629; Product Identifier 

2016–NM–184–AD. 

(a) Effective Date 

This AD is effective February 16, 2018. 

(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/EBD1CEC7B301293

E86257CB30045557A?OpenDocument

&Highlight=st01219se) 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 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by reports of 

fatigue cracking in the frame outboard chord 

and in the radius of the auxiliary chord at 

body station (BS) 727 and stringer (S) 18A. 

We are issuing this AD to detect and correct 

fatigue cracking of the outboard and auxiliary 

chords, which could result in reduced 

structural integrity of the outboard chord and 

consequent rapid decompression of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Repetitive Inspections and Corrective 

Action 

For airplanes identified in paragraph (h) of 

this AD: Within 4,500 flight cycles or 24 

months after the effective date of this AD, 

whichever occurs first, do internal detailed 

and High Frequency Eddy Current (HFEC) 

inspections to detect cracks in the auxiliary 

chord radius, in accordance with Part 1 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–53A1166, Revision 2, 

dated May 25, 2006. If any crack is found 

during any inspection required by this 

paragraph, before further flight, repair using 

a method approved in accordance with the 

procedures specified in paragraph (l) of this 

AD. Repeat the inspections thereafter at 

intervals not to exceed 15,000 flight cycles. 

Replacement of the outboard chord of the 

frame at BS 727 concurrently with the 

installation of the preventive modification of 

the outboard chord in accordance with Part 

6 of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 737–53A1166, 

Revision 2, dated May 25, 2006, terminates 

the repetitive inspections required by this 

paragraph. 

(h) Airplanes for Actions Specified in 

Paragraph (g) of This AD 

The actions specified in paragraph (g) of 

this AD are required for airplanes that meet 

the criteria of paragraphs (h)(1), (h)(2), (h)(3), 

and (h)(4) of this AD. 

(1) Model 737–100, –200, and –200C series 

airplanes, line numbers 1 through 999 

inclusive. 

(2) Airplanes identified as Groups 1, 2, and 

3 in Boeing Alert Service Bulletin 737– 

53A1166, Revision 2, dated May 25, 2006. 

(3) Airplanes on which a preventive 

modification has been installed in 

accordance with the method specified in 

paragraph (h)(3)(i), (h)(3)(ii), or (h)(3)(iii) of 

this AD. 

Note 1 to paragraph (h)(3) of this AD: The 

modification identified in paragraph (h)(3) of 

this AD is also specified in paragraph (r) of 

AD 2012–23–04, Amendment 39–17260 (77 

FR 69747, November 21, 2012), as optional 

terminating action. 

(i) Part 6 of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–53A1166, Revision 2, dated May 25, 

2006. 


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1532 Federal Register / Vol. 83, No. 9 / Friday, January 12, 2018 / Rules and Regulations 

(ii) Part II of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–53A1166, Revision 1, dated May 25, 

1995. 

(iii) Part II of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–53A1166, dated June 30, 1994. 

(4) Airplanes on which the outboard chord 

has not been replaced in accordance with the 

method specified in paragraph (h)(4)(i), 

(h)(4)(ii), or (h)(4)(iii) of this AD. 

(i) Part 3 of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–53A1166, Revision 2, dated May 25, 

2006. 

(ii) Part I of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–53A1166, Revision 1, dated May 25, 

1995. 

(iii) Part I of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–53A1166, dated June 30, 1994. 

(i) Edge Margin Measurement, Related 

Investigative Actions, and Repair 

For Model 737–100, –200, and –200C 

series airplanes having line numbers 1 

through 999 inclusive, identified as Groups 

1 through 3 in Boeing Alert Service Bulletin 

737–53A1166, Revision 2, dated May 25, 

2006, on which the preventive modification 

has been installed in accordance with Boeing 

Alert Service Bulletin 737–53A1166, dated 

June 30, 1994; or Boeing Alert Service 

Bulletin 737–53A1166, Revision 1, dated 

May 25, 1995: Within 60,000 flight cycles 

after accomplishing the preventive 

modification, determine if the modification is 

classified as interim or permanent by using 

the edge margin measurement classification 

specified in part 6 of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–53A1166, Revision 2, dated May 25, 

2006. In lieu of measuring on the airplane, 

a review of engineering documentation may 

be used to classify the modification if the 

engineering documentation was completed at 

the time of the modification and has the edge 

margins recorded. 

(1) If the modification is classified as 

permanent, no further action is required by 

paragraph (i) of this AD. 

(2) If the modification is classified as 

interim: Within 60,000 flight cycles after 

accomplishment of the interim modification 

of the outboard chord of the frame at BS 727 

at S–18A, but no earlier than 50,000 flight 

cycles after accomplishment of the 

modification, do a one-time follow-on openhole eddy current inspection to detect cracks 

in the modified chord, in accordance with 

part 8 of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 737–53A1166, 

Revision 2, dated May 25, 2006. If any crack 

is found, before further flight, repair in 

accordance with part 3 or part 4, as 

applicable, of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–53A1166, Revision 2, dated May 25, 

2006; except, if the repairs cannot be 

installed using the identified procedures, 

repair before further flight using a method 

approved in accordance with the procedures 

specified in paragraph (l) of this AD. 

(j) Follow-On Inspection for Interim 

Modification and Repair 

For airplanes having line numbers 1 

through 3132 inclusive, on which an interim 

modification of the BS 727 outboard chord as 

defined in part 6 of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–53A1166, Revision 2, dated May 25, 

2006, has been accomplished: Within 60,000 

flight cycles after accomplishment of the 

interim modification of the outboard chord of 

the frame at BS 727 at S–18A, but no earlier 

than 50,000 flight cycles after 

accomplishment of the modification, do a 

one-time follow-on open-hole eddy current 

inspection to detect cracks in the modified 

chord, in accordance with part 8 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–53A1166, Revision 2, 

dated May 25, 2006. If any crack is found 

during the inspection required by this 

paragraph, before further flight, repair in 

accordance with part 3 or part 4, as 

applicable, of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–53A1166, Revision 2, dated May 25, 

2006; except, where the repairs cannot be 

installed using the procedures identified in 

this service bulletin, repair before further 

flight using a method approved in 

accordance with the procedures specified in 

paragraph (l) of this AD. 

(k) Exception to the Service Information 

Access and restoration procedures 

specified in the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–53A1166, Revision 2, dated May 25, 

2006, are not required by this AD. Operators 

may do those actions following their 

approved maintenance procedures. 

(l) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Los Angeles ACO Branch, 

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 

certification office, send it to the attention of 

the person identified in paragraph (m) of this 

AD. Information may be emailed to: 9-ANMLAACO-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, 

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 Branch, 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. 

(m) Related Information 

For more information about this AD, 

contact George Garrido, Aerospace Engineer, 

Airframe Section, FAA, Los Angeles ACO 

Branch, 3960 Paramount Boulevard, 

Lakewood, CA 90712–4137; phone: 562–627– 

5232; fax: 562–627–5210; email: 

george.garrido@faa.gov. 

(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. 

(3) The following service information was 

approved for IBR on December 26, 2012 (77 

FR 69747, November 21, 2012). 

(i) Boeing Alert Service Bulletin 737– 

53A1166, Revision 2, dated May 25, 2006. 

(ii) Reserved. 

(4) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Contractual & Data 

Services (C&DS), 2600 Westminster Blvd., 

MC 110–SK57, Seal Beach, CA 90740; 

telephone 562–797–1717; internet https://

www.myboeingfleet.com. 

(5) You may view this service information 

at the FAA, Transport Standards Branch, 

1601 Lind Avenue SW, Renton, WA. For 

information on the availability of this 

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

(6) 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 

2, 2018. 

Michael Kaszycki, 

Acting Director, System Oversight Division, 

Aircraft Certification Service. 

[FR Doc. 2018–00256 Filed 1–11–18; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2017–1242; Product 

Identifier 2013–NM–043–AD; Amendment 

39–19150; AD 2018–01–09] 

RIN 2120–AA64 

Airworthiness Directives; Fokker 

Services B.V. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 95–25–02, 

which applied to certain Fokker 

Services B.V. Model F28 Mark 0100 


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