43160 Federal Register / Vol. 82, No. 177 / Thursday, September 14, 2017 / Rules and Regulations 

accordance with the procedures specified in 

paragraph (l)(2) of this AD. 

(i) No Terminating Action for Inspections 

Accomplishing corrective actions on an 

airplane as required by paragraph (g) or (h)(2) 

of this AD does not constitute terminating 

action for the repetitive actions required by 

paragraph (g) of this AD. 

(j) Terminating Action 

Accomplishment of the initial inspection 

required by paragraph (g) of this AD 

constitutes terminating action for the actions 

required by paragraph (h) of AD 2011–10–06. 

(k) Credit for Previous Actions 

This paragraph provides credit for actions 

required by paragraph (g) of this AD, if those 

actions were performed before the effective 

date of this AD using the service information 

specified in Airbus Service Bulletin A310– 

57–2050, Revision 03, dated December 19, 

2014. 

(l) 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 (m)(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 

Airbus’s EASA Design Organization 

Approval (DOA). If approved by the DOA, 

the approval must include the DOAauthorized signature. 

(3) Required for Compliance (RC): Except 

as required by paragraph (h)(2) of this AD: If 

any service information contains procedures 

or tests that are identified as RC, those 

procedures and tests must be done to comply 

with this AD; any procedures or tests that are 

not identified as RC are recommended. Those 

procedures and tests that are not identified 

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 procedures and tests identified as RC can 

be done and the airplane can be put back in 

an airworthy condition. Any substitutions or 

changes to procedures or tests identified as 

RC require approval of an AMOC. 

(m) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2016–0196, dated 

September 30, 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–2017–0560. 

(2) For more information about this AD, 

contact Dan Rodina, Aerospace Engineer, 

International Section, Transport Standards 

Branch, FAA, 1601 Lind Avenue SW., 

Renton, WA 98057–3356; telephone 425– 

227–2125; fax 425–227–1149. 

(3) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (n)(3) and (n)(4) of this AD. 

(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 this AD specifies otherwise. 

(i) Airbus Service Bulletin A310–57–2050, 

Revision 04, dated March 13, 2015. 

(ii) Reserved. 

(3) 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. 

(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 

31, 2017. 

Dionne Palermo, 

Acting Director, System Oversight Division, 

Aircraft Certification Service. 

[FR Doc. 2017–19042 Filed 9–13–17; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–0451; Product 

Identifier 2013–NM–253–AD; Amendment 

39–19026; AD 2017–18–17] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2004–23– 

20, which applied to certain Airbus 

Model A300, A300 B4–600, and A300 

B4–600R series airplanes; and Model 

A300 F4–605R and A300 C4–605R 

Variant F airplanes. AD 2004–23–20 

required, for certain airplanes, repetitive 

inspections for cracking around certain 

attachment holes, installation of new 

fasteners for certain airplanes, and 

follow-on corrective actions if 

necessary. AD 2004–23–20 also required 

modifying certain fuselage frames, 

which terminated certain repetitive 

inspections. This new AD reduces 

certain compliance times, expands the 

applicability, and requires an additional 

repair on certain modified airplanes. 

This AD was prompted by a report 

indicating that the material used to 

manufacture the upper frame feet was 

changed and negatively affected the 

fatigue life of the frame feet. We are 

issuing this AD to address the unsafe 

condition on these products. 

DATES: This AD is effective October 19, 

2017. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of October 19, 2017. 

ADDRESSES: For service information 

identified in this final rule, 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. 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–2016– 

0451. 


rmajette on DSKBCKNHB2PROD with RULES
Federal Register / Vol. 82, No. 177 / Thursday, September 14, 2017 / Rules and Regulations 43161 

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–2016– 

0451; 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 (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: Dan 

Rodina, Aerospace Engineer, 

International Section, Transport 

Standards Branch, 1601 Lind Avenue 

SW., Renton, WA 98057–3356; 

telephone 425–227–2125; fax 425–227– 

1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a supplemental notice of 

proposed rulemaking (SNPRM) to 

amend 14 CFR part 39 to supersede AD 

2004–23–20, Amendment 39–13875 (69 

FR 68779, November 26, 2004) (‘‘AD 

2004–23–20’’). AD 2004–23–20 applied 

to certain Airbus Model A300 B2, A300 

B4, A300 B4–600, and A300 B4–600R 

series airplanes; and Model A300 F4– 

605R and A300 C4–605R Variant F 

airplanes. The SNPRM published in the 

Federal Register on June 15, 2017 (82 

FR 27444) (‘‘the SNPRM’’). We preceded 

the SNPRM with a notice of proposed 

rulemaking (NPRM) that published in 

the Federal Register on February 1, 

2016 (81 FR 5056) (‘‘the NPRM’’). The 

NPRM was prompted by a report 

indicating that the material used to 

manufacture the upper frame feet was 

changed and negatively affected the 

fatigue life of the frame feet. The NPRM 

proposed to reduce the compliance 

times for the initial inspection and the 

inspection intervals. The NPRM also 

proposed to expand the applicability 

and require an additional repair on 

certain airplanes that have been 

modified. The SNPRM proposed to 

reduce the compliance times, require an 

additional modification, and omit the 

requirement for the repetitive 

inspections. We are issuing this AD to 

prevent cracking of the center section of 

the fuselage, which could result in a 

ruptured frame foot and reduced 

structural integrity 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 AD 2016–0249, 

dated December 14, 2016; corrected 

January 10, 2017 (referred to after this 

as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’); to correct an unsafe condition 

for all Airbus Model A300 B4–603, 

A300 B4–620, A300 B4–622, A300 B4– 

605R, A300 B4–622R, A300 F4–605R, 

A300 F4–622R, and A300 C4–605R 

Variant F airplanes. The MCAI states: 

During an inspection in accordance with 

Airworthiness Limitation Item (ALI) 53–15– 

54 on an A300–600 aeroplane, Frames (FR) 

43, FR44, FR45 and FR46 were found cracked 

between stringer (STGR) 24 and STGR30 on 

the aeroplane right hand side. FR45 was also 

found cracked on the aeroplane left hand 

side. 

This condition, if not detected and 

corrected, could reduce the structural 

integrity of the fuselage. 

To address this potential unsafe condition 

and improve the fatigue life of the upper 

frame feet fittings, Airbus issued Service 

Bulletin (SB) A300–53–6125 to provide 

instructions for expansion of the most 

sensitive fastener holes between FR41 and 

FR46. DGAC [Direction Ge ́ne ́rale de 

l’Aviation Civile] France issued AD F–2004– 

002 (EASA approval 2003–2108) [which 

corresponds to FAA AD 2004–23–20] to 

require the structural modification defined in 

SB A300–53–6125 Revision 03 (Airbus 

modification 12168). 

[French] AD F–2004–002 was subsequently 

superseded by EASA AD 2013–0295 to 

amend the inspection programme in this area 

as provided in SB A300–53–6122 (which is 

now obsolete and replaced by ALI task 

531558, published in the [Airworthiness 

Limitation Section] ALS Part 2 Revision 01 

dated 07 August 2015). 

Since EASA AD 2013–0295 was issued, a 

new investigation was conducted in the 

frame of the Widespread Fatigue Damage 

study. Airbus revised the thresholds for the 

accomplishment of the instructions defined 

in SB A300–53–6125 and issued SB A300– 

53–6178 to provide modification instructions 

to improve the fatigue life of upper frame feet 

fittings on aeroplane[s] on which Airbus 

modification (mod) 12168 or Airbus SB 

A300–53–6125 was embodied. 

For the reason described above, this 

[EASA] AD retains some requirements of 

EASA AD 2013–0295, which is superseded, 

and requires modification of the upper frame 

feet fittings from FR41 to FR46 [repetitive 

inspections are not retained]. 

This [EASA] AD is republished to correct 

a typographical error in the compliance time 

* * *. 

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–2016– 

0451. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the SNPRM or 

on the determination of the cost to the 

public. 

Conclusion 

We reviewed the available 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 SNPRM for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the SNPRM. 

Related Service Information Under 1 

CFR Part 51 

Airbus has issued Service Bulletin 

A300–53–6125, Revision 04, dated 

March 17, 2015; and Service Bulletin 

A300–53–6178, dated March 17, 2015. 

The service information describes 

procedures for the modification of 

certain upper frame feet fittings. These 

documents are distinct since they apply 

to airplanes in different configurations. 

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 65 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

The actions that were required by AD 

2004–23–20 and retained in this AD 

take about 90 work-hours per product, 

at an average labor rate of $85 per workhour. Required parts cost about $4,000 

per product. Based on these figures, the 

estimated cost of the actions that were 

required by AD 2004–23–20 is $11,650 

per product. 

We also estimate that it will take up 

to 109 work-hours per product to 

comply with the new basic 

requirements of this AD. The average 

labor rate is $85 per work-hour. 

Required parts will cost up to $6,070 

per product. Based on these figures, we 

estimate the cost of this AD on U.S. 

operators to be up to $996,775, or up to 

$15,335 per product. 

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 


rmajette on DSKBCKNHB2PROD with RULES
43162 Federal Register / Vol. 82, No. 177 / Thursday, September 14, 2017 / Rules and Regulations 

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 

removing Airworthiness Directive (AD) 

2004–23–20, Amendment 39–13875 (69 

FR 68779, November 26, 2004), and 

adding the following new AD: 

2017–18–17 Airbus: Amendment 39–19026; 

Docket No. FAA–2016–0451; Product 

Identifier 2013–NM–253–AD. 

(a) Effective Date 

This AD is effective October 19, 2017. 

(b) Affected ADs 

This AD replaces AD 2004–23–20, 

Amendment 39–13875 (69 FR 68779, 

November 26, 2004) (‘‘AD 2004–23–20’’). 

(c) Applicability 

This AD applies to Airbus Model A300 B4– 

603, A300 B4–620, A300 B4–622, A300 B4– 

605R, A300 B4–622R, A300 F4–605R, A300 

F4–622R, and A300 C4–605R Variant F 

airplanes; certificated in any category; all 

manufacturer serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Reason 

This AD was prompted by a report 

indicating that the material used to 

manufacture the upper frame feet was 

changed and negatively affected the fatigue 

life of the frame feet. We are issuing this AD 

to prevent cracking of the center section of 

the fuselage, which could result in a ruptured 

frame foot and reduced structural integrity of 

the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Modification of the Upper Frame Feet 

Fittings 

(1) Except for airplanes identified in table 

2 to paragraphs (g)(1) and (g)(2) of this AD: 

At the times specified in table 1 to paragraph 

(g)(1) of this AD, depending on the average 

flight time (AFT), as defined in paragraph (i) 

of this AD, modify the upper frame feet 

fittings, including doing all applicable 

related investigative and corrective actions, 

in accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A300– 

53–6125, Revision 04, dated March 17, 2015 

(‘‘SB A300–53–6125, Revision 04’’). Do all 

applicable related investigative and 

corrective actions before further flight. Where 

Airbus SB A300–53–6125, Revision 04, 

specifies to contact Airbus for appropriate 

action, and specifies that action as ‘‘RC’’ 

(Required for Compliance): Before further 

flight, accomplish corrective actions in 

accordance with the procedures specified in 

paragraph (l)(2) of this AD. 

TABLE 1 TO PARAGRAPH (g)(1) OF THIS AD—MODIFICATION SB A300–53–6125, REVISION 04 

Airplane usage Initial compliance time 

(flight cycles or flight hours, whichever occurs first since first flight) 

AFT greater than 1.5 .......................................... Within 10,200 flight cycles or 22,100 flight hours. 

AFT equal to or less than 1.5 ............................. Within 11,000 flight cycles or 16,600 flight hours. 

TABLE 2 TO PARAGRAPHS (g)(1) AND (g)(2) OF THIS AD—MODIFICATION SB A300–53–6178 

Airplane configuration Initial compliance time 

Post-modification 12168 ..................................... Within 27,100 flight cycles or 47,300 flight hours since the airplane’s first flight, whichever occurs first. 

Post-SB A300–53–6125 ..................................... Within 27,100 flight cycles or 47,300 flight hours after embodiment of SB A300–53–6125, 

whichever occurs first. 

(2) For airplanes identified in table 2 to 

paragraphs (g)(1) and (g)(2) of this AD: At the 

applicable compliance time specified in table 

2 to paragraphs (g)(1) and (g)(2) of this AD, 

modify the upper frame feet fittings, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A300– 

53–6178, dated March 17, 2015. Where 

Airbus Service Bulletin A300–53–6178, 

dated March 17, 2015, specifies to contact 

Airbus for appropriate action, and specifies 

that action as ‘‘RC’’: Before further flight, 


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Federal Register / Vol. 82, No. 177 / Thursday, September 14, 2017 / Rules and Regulations 43163 

accomplish corrective actions in accordance 

with the procedures specified in paragraph 

(l)(2) of this AD. 

(h) Additional Post-Modification Actions 

Prior to exceeding 24,100 total flight cycles 

or 42,000 total flight hours, whichever occurs 

first after doing the modification required by 

paragraph (g)(2) of this AD: Contact the 

Manager, International Section, Transport 

Standards Branch, FAA; or the European 

Aviation Safety Agency (EASA); or Airbus’s 

EASA Design Organization Approval (DOA); 

for instructions to do additional actions, and 

do those actions at the compliance times 

stated therein. 

(i) Definition of AFT 

For the purpose of this AD, to establish the 

applicable AFT for the actions required by 

paragraph (g)(1) of this AD, divide the total 

accumulated flight hours counted from takeoff to touch-down by the total accumulated 

flight cycles as of the effective date of this 

AD. 

(j) Credit for Previous Actions 

This paragraph provides credit for the 

modification required by paragraph (g)(1) of 

this AD, if the modification was performed 

before the effective date of this AD using the 

service information specified in paragraph 

(j)(1), (j)(2), (j)(3), or (j)(4) of this AD. 

(1) Airbus Service Bulletin A300–53–6125, 

dated November 8, 2000, which is not 

incorporated by reference in this AD. 

(2) Airbus Service Bulletin A300–53–6125, 

Revision 01, dated June 13, 2003, which was 

incorporated by reference in AD 2004–23–20. 

(3) Airbus Service Bulletin A300–53–6125, 

Revision 02, dated February 25, 2005, which 

is not incorporated by reference in this AD. 

(4) Airbus Service Bulletin A300–53–6125, 

Revision 03, dated September 13, 2011, 

which is not incorporated by reference in this 

AD. 

(k) Exempt Airplanes 

For airplanes on which Airbus 

Modification 12168 has been embodied in 

production: The modification required by 

paragraph (g)(1) of this AD is not required by 

this AD. 

(l) 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 (m)(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: 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 Section, Transport 

Standards Branch, FAA; or EASA; or 

Airbus’s EASA DOA. If approved by the 

DOA, the approval must include the DOAauthorized signature. 

(3) Required for Compliance (RC): Except 

as required by paragraphs (g)(1) and (g)(2) of 

this AD: If any service information contains 

procedures or tests that are identified as RC, 

those procedures and tests must be done to 

comply with this AD; any procedures or tests 

that are not identified as RC are 

recommended. Those procedures and tests 

that are not identified 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 

procedures and tests identified as RC can be 

done and the airplane can be put back in an 

airworthy condition. Any substitutions or 

changes to procedures or tests identified as 

RC require approval of an AMOC. 

(m) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2016–0249, dated 

December 14, 2016; corrected January 10, 

2017; 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– 

2016–0451. 

(2) For more information about this AD, 

contact Dan Rodina, Aerospace Engineer, 

International Section, Transport Standards 

Branch, 1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–2125; fax 

425- 227–1149. 

(3) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (n)(3) and (n)(4) of this AD. 

(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 this AD specifies otherwise. 

(i) Airbus Service Bulletin A300–53–6125, 

Revision 04, dated March 17, 2015. 

(ii) Airbus Service Bulletin A300–53–6178, 

dated March 17, 2015. 

(3) 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. 

(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 

29, 2017. 

Jeffrey E. Duven, 

Director, System Oversight Division, Aircraft 

Certification Service. 

[FR Doc. 2017–19303 Filed 9–13–17; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2017–0524; Product 

Identifier 2016–NM–122–AD; Amendment 

39–19034; AD 2017–19–04] 

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 certain 

Dassault Aviation Model FALCON 

900EX airplanes. This AD was 

prompted by a determination that new 

or more restrictive maintenance 

requirements and/or airworthiness 

limitations are necessary. This AD 

requires revising the maintenance or 

inspection program, as applicable, to 

incorporate new or more restrictive 

maintenance requirements and/or 

airworthiness limitations. We are 

issuing this AD to address the unsafe 

condition on these products. 

DATES: This AD is effective October 19, 

2017. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of October 19, 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 


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