Federal Register / Vol. 82, No. 168 / Thursday, August 31, 2017 / Rules and Regulations 41323 

Initial Certificate Effective Date: May 

31, 2000. 

Amendment Number 1 Effective Date: 

July 15, 2002. 

Amendment Number 2 Effective Date: 

June 7, 2005. 

Amendment Number 3 Effective Date: 

May 29, 2007. 

Amendment Number 4 Effective Date: 

January 8, 2008. 

Amendment Number 5 Effective Date: 

July 14, 2008. 

Amendment Number 6 Effective Date: 

August 17, 2009. 

Amendment Number 7 Effective Date: 

December 28, 2009. 

Amendment Number 8 Effective Date: 

May 2, 2012, as corrected on November 

16, 2012 (ADAMS Accession No. 

ML12213A170); superseded by 

Amendment Number 8, Revision 1, 

Effective Date: February 16, 2016. 

Amendment Number 8, Revision 1, 

Effective Date: February 16, 2016. 

Amendment Number 9 Effective Date: 

March 11, 2014, superseded by 

Amendment Number 9, Revision 1, on 

March 21, 2016. 

Amendment Number 9, Revision 1, 

Effective Date: March 21, 2016, as 

corrected (ADAMS Accession No. 

ML17236A451). 

Amendment Number 10 Effective 

Date: May 31, 2016, as corrected 

(ADAMS Accession No. ML17236A452). 

Safety Analysis Report (SAR) 

Submitted by: Holtec International. 

SAR Title: Final Safety Analysis 

Report for the HI–STORM 100 Cask 

System. 

Docket Number: 72–1014. 

Certificate Expiration Date: May 31, 

2020. 

Model Number: HI–STORM 100. 

* * * * * 

Dated at Rockville, Maryland, this 25th day 

of August 2017. 

For the Nuclear Regulatory Commission. 

Pamela J. Shepherd-Vladimir, 

Acting Chief, Rules, Announcements, and 

Directives Branch, Division of Administrative 

Services, Office of Administration. 

[FR Doc. 2017–18456 Filed 8–30–17; 8:45 am] 

BILLING CODE 7590–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2017–0475; Product 

Identifier 2016–NM–142–AD; Amendment 

39–19017; AD 2017–18–08] 

RIN 2120–AA64 

Airworthiness Directives; Dassault 

Aviation Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Dassault Aviation Model FALCON 2000 

and FALCON 2000EX airplanes. This 

AD was prompted by reports of ice 

accretion on the airplane wing due to 

the failure of certain anti-ice piccolo 

tubes in the wing outboard slats. This 

AD requires repetitive inspections of 

each anti-ice piccolo tube and corrective 

action if necessary. We are issuing this 

AD to address the unsafe condition on 

these products. 

DATES: This AD is effective October 5, 

2017. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of October 5, 2017. 

ADDRESSES: For service information 

identified in this final rule, contact 

Dassault Falcon Jet Corporation, 

Teterboro Airport, P.O. Box 2000, South 

Hackensack, NJ 07606; telephone 201– 

440–6700; Internet http://

www.dassaultfalcon.com. You may 

view this referenced 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–2017–0475. 

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– 

0475; 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 street address for 

the Docket Office (telephone 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: 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. 

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 Dassault Aviation Model 

FALCON 2000 and FALCON 2000EX 

airplanes. The NPRM published in the 

Federal Register on May 22, 2017 (82 

FR 23163) (‘‘the NPRM’’). The NPRM 

was prompted by reports of ice 

accretion on the airplane wing due to 

the failure of certain anti-ice piccolo 

tubes in the wing outboard slats. The 

NPRM proposed to require repetitive 

inspections of each anti-ice piccolo tube 

and corrective action if necessary. We 

are issuing this AD to detect and correct 

manufacturing defects in the anti-ice 

piccolo tubes in the wing outboard slats. 

This condition could lead to undetected 

significant ice accretion on a wing, 

resulting in loss of control of the 

airplane. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2016–0149, dated July 25, 

2016 (referred to after this as the 

Mandatory Continuing Airworthiness 

Information, or ‘‘the MCAI’’), to correct 

an unsafe condition for all Dassault 

Aviation Model FALCON 2000 and 

FALCON 2000EX airplanes. The MCAI 

states: 

Occurrences were reported of ice accretion 

on the wing, due to failure of the affected 

anti-ice piccolo tubes Part Number (P/N) 

FGFB725102. Investigation results indicated 

that some wing piccolo tubes P/N 

FGFB725102 could have manufacturing 

defects in their welded parts, which may 

have caused the rupture of the tubes, due to 

fatigue. 

This condition, if not detected and 

corrected, could lead to undetected 

significant ice accretion on the wing, 

possibly resulting in loss of control of the 

aeroplane. 

To address this potential unsafe condition, 

[Dassault Aviation] DA issued Service 

Bulletin (SB) F2000–431 Revision 1 and SB 

F2000EX–391 Revision 1 (hereafter referred 

to collectively as ‘the applicable SB’ in this 

[EASA] AD) to provide instructions for 

endoscopic inspection of the tubes. 


nlaroche on DSKBBV9HB2PROD with RULES
41324 Federal Register / Vol. 82, No. 168 / Thursday, August 31, 2017 / Rules and Regulations 

For the reasons described above, this 

[EASA] AD requires repetitive inspections of 

each wing outboard slat piccolo tube [for 

discrepancies, i.e., manufacturing defects, 

cracking, and loss of material in the welded 

parts] and, depending on findings, 

replacement of the piccolo tube(s) [and the 

outboard slat] with a [new or] serviceable 

part. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2017– 

0475. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM or 

on the determination of the cost to the 

public. 

Change to NPRM 

We have added paragraph (j) to this 

AD to explain that although Dassault 

Service Bulletin F2000–431, Revision 1, 

dated June 6, 2016; and Service Bulletin 

F2000EX–391, Revision 1, dated June 6, 

2016; specify to submit a report of crack 

findings to Dassault, this AD does not 

require a report. We have redesignated 

subsequent paragraphs accordingly. 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting this AD 

as proposed except for 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. 

Related Service Information Under 1 

CFR Part 51 

Dassault Aviation has issued Service 

Bulletin F2000–431, Revision 1, dated 

June 6, 2016; and Service Bulletin 

F2000EX–391, Revision 1, dated June 6, 

2016. The service information describes 

procedures for endoscopic inspections 

of the anti-ice piccolo tube on each wing 

outboard slat, and replacement or reidentification of affected anti-ice piccolo 

tubes and outboard slats. These 

documents are distinct since they apply 

to different airplane models. 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 348 

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 ............................... 6 work-hours × $85 per hour 

= $510 per inspection cycle.

$0 $510 per inspection cycle ...... $177,480 per inspection 

cycle. 

We 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. 

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 

We determined that 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 the 

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): 

2017–18–08 Dassault Aviation: 

Amendment 39–19017; Docket No. 

FAA–2017–0475; Product Identifier 

2016–NM–142–AD. 

(a) Effective Date 

This AD is effective October 5, 2017. 

(b) Affected ADs 

None. 


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Federal Register / Vol. 82, No. 168 / Thursday, August 31, 2017 / Rules and Regulations 41325 

(c) Applicability 

This AD applies to Dassault Aviation 

Model FALCON 2000 and FALCON 2000EX 

airplanes, certificated in any category, all 

serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 30, Ice and Rain Protection. 

(e) Reason 

This AD was prompted by reports of ice 

accretion on the airplane wing due to the 

failure of certain anti-ice piccolo tubes in the 

wing outboard slats. We are issuing this AD 

to detect and correct manufacturing defects 

in the anti-ice piccolo tubes in the wing 

outboard slats. This condition could lead to 

undetected significant ice accretion on a 

wing, resulting in loss of control of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Affected Anti-ice Piccolo Tubes 

(1) For the purpose of this AD, an affected 

anti-ice piccolo tube meets at least one of the 

conditions specified in paragraphs (g)(1)(i) 

and (g)(1)(ii) of this AD. 

(i) Has part number (P/N) FGFB725102 

(left-hand side (LH)) or P/N FGFB726102 

(right-hand side (RH)). 

(ii) Is installed on a wing outboard slat 

having a part number identified in table 1 to 

paragraph (g)(1)(ii) of this AD. 

TABLE 1 TO PARAGRAPH (g)(1)(ii) OF THIS AD—AFFECTED OUTBOARD SLATS PART NUMBERS

LH RH 

FGFB134 .................................................................................................................................... FGFB144. 

FGFB134A1 to FGFB134A9 inclusive ........................................................................................ FGFB144A1 to FGFB144A9 inclusive. 

FGFB134B1 ................................................................................................................................ FGFB144B1. 

FFGFB134C1 to FGFB134C4 inclusive ..................................................................................... FGFB144C1 to FGFB144C4 inclusive. 

From FGFB134D1 to FGFB134D4 inclusive .............................................................................. FGFB144D1 to FGFB144D4 inclusive. 

FGFB135 and FGFB135M ......................................................................................................... FGFB145 and FGFB145M. 

FGFB135A1 to FGFB135A4 inclusive ........................................................................................ FGFB145A1 to FGFB145A4 inclusive. 

From FGFB135A1M to FGFB135A4M inclusive ........................................................................ FGFB145A1M to FGFB145A4M inclusive. 

From FGFB135B1 to FGFB135B3 inclusive .............................................................................. FGFB145B1 to FGFB145B3 inclusive. 

FGFB135B1M to FGFB135B3M inclusive .................................................................................. FGFB145B1M to FGFB145B3M inclusive. 

F2MB135 .................................................................................................................................... F2MB145. 

F2MB135A1 ................................................................................................................................ F2MB145A1. 

F2MB135L1 to F2MB135L5 inclusive ........................................................................................ F2MB145L1 to F2MB145L5 inclusive. 

(2) If the outboard slat part number is 

identified in table 2 to paragraph (g)(2) of this 

AD, the anti-ice piccolo tube is not affected 

because the outboard slat has already been 

retrofitted with a new stiffened anti-ice 

piccolo tube, and no action is required by 

this AD for that piccolo tube. 

TABLE 2 TO PARAGRAPH (g)(2) OF THIS AD—SERVICEABLE OUTBOARD SLATS PART NUMBERS

LH RH 

FGFB134P .................................................................................................................................. FGFB144P. 

FGFB134A1P through FGFB134A9P inclusive .......................................................................... FGFB144A1P through FGFB144A9P inclusive. 

FGFB134B1P .............................................................................................................................. FGFB144B1P. 

FFGFB134C1P to FGFB134C4P inclusive ................................................................................ FGFB144C1P to FGFB144C4P inclusive. 

From FGFB134D1P to FGFB134D4P inclusive ......................................................................... FGFB144D1P to FGFB144D4P inclusive. 

FGFB135P and FGFB135MP ..................................................................................................... FGFB145P and FGFB145MP. 

FGFB135A1P to FGFB135A4P inclusive ................................................................................... FGFB145A1P to FGFB145A4P inclusive. 

From FGFB135A1MP to FGFB135A4MP inclusive ................................................................... FGFB145A1MP to FGFB145A4MP inclusive. 

From FGFB135B1P to FGFB135B3P inclusive ......................................................................... FGFB145B1P to FGFB145B3P inclusive. 

FGFB135B1MP to FGFB135B3MP inclusive ............................................................................. FGFB145B1MP to FGFB145B3MP inclusive. 

F2MB135P .................................................................................................................................. F2MB145P. 

F2MB135A1P .............................................................................................................................. F2MB145A1P. 

F2MB135L1P to F2MB135L5P inclusive .................................................................................... F2MB145L1P to F2MB145L5P inclusive. 

F2MB135L6 to F2MB135L7 inclusive ........................................................................................ F2MB145L6 to F2MB145L7 inclusive. 

(h) Inspections 

If an anti-ice piccolo tube has been 

determined to be affected, as specified in 

paragraph (g) of this AD: At the applicable 

time specified in table 3 to paragraph (h) of 

this AD, do an endoscopic inspection for 

discrepancies, i.e., manufacturing defects, 

cracking, and loss of material in the welded 

parts of each affected anti-ice piccolo tube, in 

accordance with the Accomplishment 

Instructions of Dassault Service Bulletin 

F2000–431, Revision 1, dated June 6, 2016; 

or Service Bulletin F2000EX–391, Revision 1, 

dated June 6, 2016; as applicable. Repeat the 

endoscopic inspection thereafter at intervals 

not to exceed those specified in table 3 to 

paragraph (h) of this AD, until the 

modification specified in paragraph (k) of 

this AD is done. 

TABLE 3 TO PARAGRAPH (h) OF THIS AD—COMPLIANCE TIMES FOR INSPECTIONS

Airplane model Initial inspection Repetitive inspection 

intervals 

FALCON 2000 airplanes .................... Prior to exceeding 2,000 flight cycles since the airplane’s first flight, or 

within 1,000 flight cycles after the effective date of this AD, whichever 

occurs later.

2,000 flight cycles. 


nlaroche on DSKBBV9HB2PROD with RULES
41326 Federal Register / Vol. 82, No. 168 / Thursday, August 31, 2017 / Rules and Regulations 

TABLE 3 TO PARAGRAPH (h) OF THIS AD—COMPLIANCE TIMES FOR INSPECTIONS—Continued 

Airplane model Initial inspection Repetitive inspection 

intervals 

FALCON 2000EX airplanes ............... Prior to exceeding 1,000 flight cycles since the airplane’s first flight, or 

within 500 flight cycles after the effective date of this AD, whichever occurs later.

1,000 flight cycles. 

(i) Corrective Action 

If any discrepancy is found during any 

inspection required by paragraph (h) of this 

AD: Before further flight, replace the affected 

anti-ice piccolo tube with a new or 

serviceable part, and replace or re-identify 

the affected wing outboard slat as applicable, 

in accordance with the Accomplishment 

Instructions of Dassault Service Bulletin 

F2000–431, Revision 1, dated June 6, 2016; 

or Service Bulletin F2000EX–391, Revision 1, 

dated June 6, 2016; as applicable. 

(j) Reporting Provisions 

Although Dassault Service Bulletin F2000– 

431, Revision 1, dated June 6, 2016; and 

Service Bulletin F2000EX–391, Revision 1, 

dated June 6, 2016; specify to submit a report 

of crack findings to Dassault, this AD does 

not require a report. 

(k) Optional Terminating Action 

Modification of an airplane by installing a 

new or serviceable anti-ice piccolo tube, and 

replacing or re-identifying the affected wing 

outboard slat, terminates the repetitive 

inspections required by paragraph (h) of this 

AD, if done in accordance with the 

Accomplishment Instructions of Dassault 

Service Bulletin F2000–431, Revision 1, 

dated June 6, 2016; or Service Bulletin 

F2000EX–391, Revision 1, dated June 6, 

2016; as applicable. 

(l) Parts Installation Prohibition 

As of the time specified in paragraph (l)(1) 

or (l)(2) of this AD, as applicable, no person 

may install on any airplane an affected antiice piccolo tube or an affected outboard slat. 

(1) For an airplane that, on the effective 

date of this AD, has an affected anti-ice 

piccolo tube or an affected outboard slat 

installed: After modification of that airplane 

as required by paragraph (i) of this AD. 

(2) For an airplane that, on the effective 

date of this AD, does not have an affected 

anti-ice piccolo tube or an affected outboard 

slat installed: As of the effective date of this 

AD. 

(m) Later-Approved Parts 

Installation on an airplane of an anti-ice 

piccolo tube having a part number approved 

after the effective date of this AD is 

acceptable for compliance with the 

requirements of paragraph (i) or paragraph (k) 

of this AD, as applicable, provided the 

conditions in paragraphs (m)(1) and (m)(2) of 

this AD are met. 

(1) The anti-ice piccolo tube part number 

must be 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). 

(2) The installation of the anti-ice piccolo 

tube must be accomplished in accordance 

with a method approved by the Manager, 

International Section, Transport Standards 

Branch, FAA; or the EASA; or Dassault 

Aviation’s EASA DOA. 

(n) 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 (o)(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 

EASA; or Dassault Aviation’s EASA DOA. If 

approved by the DOA, the approval must 

include the DOA-authorized signature. 

(o) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA AD 

2016–0149, dated July 25, 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–2017–0475. 

(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. 

(p) 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) Dassault Service Bulletin F2000–431, 

Revision 1, dated June 6, 2016. 

(ii) Dassault Service Bulletin F2000EX– 

391, Revision 1, dated June 6, 2016. 

(3) 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. 

(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 August 

21, 2017. 

Dionne Palermo, 

Acting Director, System Oversight Division, 

Aircraft Certification Service. 

[FR Doc. 2017–18391 Filed 8–30–17; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2017–0247; Product 

Identifier 2016–NM–180–AD; Amendment 

39–19015; AD 2017–18–06] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2012–05– 

03, which applied 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. AD 2012–05–03 

required modifying the fluid drain path 

in the leading edge area of the wing. 

This AD requires additional work to seal 

those drainage holes in the wing access 

panels. This AD was prompted by a 

design review following a ground fire 


nlaroche on DSKBBV9HB2PROD with RULES