Federal Register / Vol. 82, No. 222 / Monday, November 20, 2017 / Rules and Regulations 55037 

all applicable actions specified in paragraph 

(h)(1) or (h)(2) of this AD, in accordance with 

the Accomplishment Instructions of Dassault 

Service Bulletin F900EX–464, dated June 20, 

2016. After the applicable actions specified 

in paragraph (h)(1) or (h)(2) of this AD have 

been completed, the AFM revision required 

by paragraph (g) of this AD may be removed 

from the AFM for that airplane. 

(1) If during the inspection required by the 

introductory text to paragraph (h) of this AD 

it is determined that a diaphragm is present: 

Before further flight, replace the wing anti-ice 

system ducting. 

(2) If during the inspection required by the 

introductory text to paragraph (h) of this AD 

it is determined that a diaphragm is not 

present: Before further flight, do a check of 

the anti-ice pipe part number and re-identify 

the wing anti-ice system ducting. 

(i) New Actions: Inspection, Part 

Replacement, Part Re-identification 

For Model FALCON 2000EX airplanes: 

Within 9 months after the effective date of 

this AD, do a detailed inspection of the wing 

anti-ice system ducting (anti-ice pipe) for the 

presence of a diaphragm, and do all 

applicable actions specified in paragraph 

(i)(1) or (i)(2) of this AD, in accordance with 

the Accomplishment Instructions of Dassault 

Service Bulletin F2000EX–393, dated June 

20, 2016. After the applicable actions 

specified in paragraph (i)(1) or (i)(2) of this 

AD have been completed, the AFM revision 

required by paragraph (g) of this AD may be 

removed from the AFM for that airplane. 

(1) If during the inspection required by the 

introductory text to paragraph (i) of this AD 

it is determined that a diaphragm is not 

present: Before further flight, replace the 

wing anti-ice system ducting. 

(2) If during the inspection required by the 

introductory text to paragraph (i) of this AD 

it is determined that a diaphragm is present: 

Before further flight, do a check of the antiice pipe part number and re-identify the wing 

anti-ice system ducting. 

(j) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) 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 (k)(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. 

(2) Contacting the Manufacturer: 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 Section, 

Transport Standards Branch, FAA; or the 

European Aviation Safety Agency (EASA); or 

Dassault Aviation’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(k) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Emergency AD 2016–0130–E, dated July 5, 

2016, 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– 

2017–1023. 

(2) For more information about this AD, 

contact Tom Rodriguez, Aerospace Engineer, 

International Section, Transport Standards 

Branch, FAA, 1601 Lind Avenue SW., 

Renton, WA 98057–3356; telephone 425– 

227–1137; fax 425–227–1149. 

(l) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

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

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless this AD specifies otherwise. 

(3) The following service information was 

approved for IBR on October 27, 2017 (82 FR 

44305, September 22, 2017). 

(i) Dassault Aviation Service Bulletin 

F900EX–464, dated June 20, 2016. 

(ii) Dassault Aviation Service Bulletin 

F2000EX–393, dated June 20, 2016. 

(4) For service information identified in 

this AD, contact Dassault Falcon Jet 

Corporation, Teterboro Airport, P.O. Box 

2000, South Hackensack, NJ 07606; 

telephone 201–440–6700; Internet http://

www.dassaultfalcon.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 

November 7, 2017. 

Dionne Palermo, 

Acting Director, System Oversight Division, 

Aircraft Certification Service. 

[FR Doc. 2017–24810 Filed 11–17–17; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2017–0773; Product 

Identifier 2017–NM–067–AD; Amendment 

39–19101; AD 2017–23–07] 

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 cracks found in the lower 

chord of the left wing rear spar. This AD 

requires repetitive inspections for 

cracking of the lower chord of the rear 

spar and lower aft skin and applicable 

on-condition actions. We are issuing 

this AD to address the unsafe condition 

on these products. 

DATES: This AD is effective December 

26, 2017. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of December 26, 2017. 

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 90740–5600; 

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– 

0773. 

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– 

0773; 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. 


sradovich on DSK3GMQ082PROD with RULES
55038 Federal Register / Vol. 82, No. 222 / Monday, November 20, 2017 / Rules and Regulations 

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: 

Payman Soltani, Aerospace Engineer, 

Airframe Section, FAA, Los Angeles 

ACO Branch, 3960 Paramount 

Boulevard, Lakewood, CA 90712–4137; 

phone: 562–627–5313; fax: 562–627– 

5210; email: payman.soltani@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 

August 15, 2017 (82 FR 38641). The 

NPRM was prompted by reports of 

cracks found in the lower chord of the 

left wing rear spar. The NPRM proposed 

to require repetitive low frequency eddy 

current (LFEC) inspections for cracking 

of the lower chord of the rear spar and 

detailed inspections for cracking of the 

lower aft skin at wing buttock line 

(WBL) 157 and applicable on-condition 

actions. 

We are issuing this AD to detect and 

correct cracking of the lower chord of 

the rear spar and the lower aft skin at 

WBL 157. 

Comments 

We gave the public the opportunity to 

participate in developing this final rule. 

We have considered the comments 

received. 

Support for the NPRM 

The Boeing Company supported the 

NPRM. 

Effect of Winglets on Accomplishment 

of the Proposed Actions 

Aviation Partners Boeing stated that 

accomplishing the Supplemental Type 

Certificate (STC) ST01219SE does not 

affect the actions specified in the 

NPRM. 

We concur with the commenter. We 

have redesignated paragraph (c) of the 

proposed AD as paragraph (c)(1) of this 

AD 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 method of 

compliance (AMOC) approval request is 

not necessary to comply with the 

requirements of 14 CFR 39.17. 

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 change 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 737–57A1333, dated May 12, 

2017. This service information describes 

procedures for repetitive LFEC 

inspections for cracking of the lower 

chord of the rear spar and detailed 

inspections for cracking of the lower aft 

skin at WBL 157, applicable oncondition actions (e.g., repair), and 

instructions for airplanes that have an 

existing repair in the inspection area. 

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 190 

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 

LFEC and detailed inspections.10 work-hours × $85 per hour = $850 per inspection cycle.$0 $850 per inspection 

cycle.

Up to $161,500 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. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the instructions for 

airplanes that have an existing repair in 

the inspection area 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. 

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), 


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Federal Register / Vol. 82, No. 222 / Monday, November 20, 2017 / Rules and Regulations 55039 

(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): 

2017–23–07 The Boeing Company: 

Amendment 39–19101; Docket No. 

FAA–2017–0773; Product Identifier 

2017–NM–067–AD. 

(a) Effective Date 

This AD is effective December 26, 2017. 

(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/

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. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Unsafe Condition 

This AD was prompted by the report of a 

crack indication in the horizontal flange of 

the lower chord of the left wing rear spar at 

wing buttock line (WBL) 157 and multiple 

reports of similar crack findings on other 

airplanes. We are issuing this AD to detect 

and correct cracking of the lower chord of the 

rear spar and the lower aft skin at WBL 157. 

Undetected cracks could lead to the inability 

of the lower chord of the rear spar, a 

principal structural element, to sustain limit 

load, which could adversely affect the 

structural integrity of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

(1) For Group 2 airplanes identified in 

Boeing Alert Service Bulletin 737–57A1333, 

dated May 12, 2017: Except as required by 

paragraph (h) of this AD, at the applicable 

times specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 737–57A1333, dated May 12, 2017, 

do all applicable actions identified as ‘‘RC’’ 

(required for compliance) in, and in 

accordance with, the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–57A1333, dated May 12, 2017. 

(2) For Group 1 airplanes identified in 

Boeing Alert Service Bulletin 737–57A1333, 

dated May 12, 2017: Within 120 days after 

the effective date of this AD, inspect the 

airplane and do all applicable corrective 

actions using a method approved in 

accordance with the procedures specified in 

paragraph (i) of this AD. 

(h) Exceptions to Service Information 

Specifications 

(1) Where Boeing Alert Service Bulletin 

737–57A1333, dated May 12, 2017, uses the 

phrase ‘‘after the original issue date of this 

service bulletin,’’ for purposes of determining 

compliance with the requirements of this AD, 

the phrase ‘‘after the effective date of this 

AD’’ must be used. 

(2) Where Boeing Alert Service Bulletin 

737–57A1333, dated May 12, 2017, specifies 

contacting Boeing, and specifies that action 

as RC: This AD requires using a method 

approved in accordance with the procedures 

specified in paragraph (i) of this AD. 

(i) 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 (j) 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. 

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

of this AD: For service information that 

contains steps that are labeled as RC, the 

provisions of paragraphs (i)(4)(i) and (i)(4)(ii) 

of this AD 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. If a step or substep is 

labeled ‘‘RC Exempt,’’ then the RC 

requirement is removed from that step or 

substep. 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. 

(j) Related Information 

For more information about this AD, 

contact Payman Soltani, Aerospace Engineer, 

Airframe Section, FAA, Los Angeles ACO 

Branch, 3960 Paramount Boulevard, 

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

5313; fax: 562–627–5210; email: 

payman.soltani@faa.gov. 

(k) 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– 

57A1333, dated May 12, 2017. 

(ii) Reserved. 

(3) 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 90740–5600; 

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

www.myboeingfleet.com. 

(4) 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. 

(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 6, 2017. 

Dionne Palermo, 

Acting Director, System Oversight Division, 

Aircraft Certification Service. 

[FR Doc. 2017–24732 Filed 11–17–17; 8:45 am] 

BILLING CODE 4910–13–P 


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