43158 Federal Register / Vol. 82, No. 177 / Thursday, September 14, 2017 / Rules and Regulations 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2017–0560; Product 

Identifier 2016–NM–172–AD; Amendment 

39–19028; AD 2017–18–19] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Airbus Model A310–203, –204, –221, 

–222, –304, –322, –324, and –325 

airplanes. This AD was prompted by 

reports of cracking in the drainage holes 

on the lower skin panel in the center 

wing box between frames (FR) 42 and 

FR46. This AD requires repetitive 

rotating probe inspections for cracking 

of the trellis boom drainage holes, the 

holes in the stringers bottom, and the 

holes of the inner pump, and corrective 

actions if necessary. 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 

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.airwortheas@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–2017– 

0560. 

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– 

0560; 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: 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. 

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 Airbus Model A310–203, 

–204, –221, –222, –304, –322, –324, and 

–325 airplanes. The NPRM published in 

the Federal Register on June 20, 2017 

(82 FR 28030) (‘‘the NPRM’’). The 

NPRM was prompted by reports of 

cracking in the drainage holes on the 

lower skin panel in the center wing box 

between frames FR42 and FR46. The 

NPRM proposed to require repetitive 

rotating probe inspections for cracking 

of the trellis boom drainage holes, the 

holes in the stringers bottom, and the 

holes of the inner pump, and corrective 

actions if necessary. We are issuing this 

AD to detect and correct cracking of 

trellis boom drainage holes, the holes in 

the stringers bottom, and the holes of 

the inner pump, which could result in 

reduced structural integrity of the 

wings. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2016–0196, dated September 

30, 2016 (referred to after this as the 

Mandatory Continuing Airworthiness 

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

an unsafe condition for all Airbus 

Model A310–203, –204, –221, –222, 

–304, –322, –324, and –325 airplanes. 

The MCAI states: 

DGAC [Direction Ge ́ne ́rale de l’Aviation 

Civile] France issued AD F–1992–106–132R7 

to require certain inspections and 

modifications which addressed JAR/FAR 

[Joint Aviation Requirements/Federal 

Aviation Regulations] 25–571 requirements, 

related to damage-tolerance and fatigue 

evaluation of structure. Following the 

Extended Design Service Goal activities as 

part of the Structure Task Group for the 

Airbus A310 program, EASA published AD 

2007–0053, which replaced DGAC France AD 

F–1992–106–132R7. 

After EASA issued AD 2007–0053R1, the 

thresholds and the intervals of Airbus 

Service Bulletins (SB) A310–57–2050 and 

A310–57–2064 were updated, prompting 

EASA to issue AD 2009–0057 [which 

corresponds to FAA AD 2011–10–06, 

Amendment 39–16687 (76 FR 27227, May 11, 

2011)] and [EASA] AD 2007–0053 was 

revised (R2) accordingly. EASA AD 2009– 

0057 also required the accomplishment of the 

actions specified in Airbus SB A310–57– 

2048 at Revision 01. 

After EASA issued AD 2009–0057, in the 

frame of the Widespread Fatigue Damage 

campaign, new analysis has indicated the 

need for additional work included in 

Revision 03 of Airbus SB A310–57–2050. 

For the reason described above, this new 

[EASA] AD retains the requirements of EASA 

AD 2009–0057, which is superseded, and 

requires inspection and corrective actions as 

specified in Airbus SB A310–57–2050 

Revision 04. 

Required actions include a repetitive 

rotating probe inspection for cracking of 

certain holes in the stringers bottom, 

inner pumps, and the trellis boom; and 

corrective actions, i.e., repair of holes 

where cracks are discovered. 

The compliance times vary depending 

on airplane configuration. The earliest 

initial inspection compliance time is 

11,400 total flight cycles or 57,300 total 

flight hours, whichever occurs first. The 

latest initial compliance time is 38,700 

total flight cycles or 77,500 total flight 

hours, whichever occurs first. The 

shortest repetitive interval is 6,200 flight 

cycles or 31,200 flight hours, whichever 

occurs first. 

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– 

0560. 

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. 

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 

Airbus has issued Service Bulletin 

A310–57–2050, Revision 04, dated 


rmajette on DSKBCKNHB2PROD with RULES
Federal Register / Vol. 82, No. 177 / Thursday, September 14, 2017 / Rules and Regulations 43159 

March 13, 2015. This service 

information describes procedures for 

repetitive rotating probe inspections for 

cracking of the trellis boom drainage 

holes, the holes in the stringers bottom, 

and the holes of the inner pump, and 

corrective actions. 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 8 

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 ........................................................ 84 work-hours × $85 per hour = $7,140 ........ $5,890 $13,030 $104,240 

We have received no definitive data 

that would 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): 

2017–18–19 Airbus: Amendment 39–19028; 

Docket No. FAA–2017–0560; Product 

Identifier 2016–NM–172–AD. 

(a) Effective Date 

This AD is effective October 19, 2017. 

(b) Affected ADs 

This AD affects AD 2011–10–06, 

Amendment 39–16687 (76 FR 27227, May 11, 

2011) (‘‘AD 2011–10–06’’). 

(c) Applicability 

This AD applies to Airbus Model A310– 

203, –204, –221, –222, –304, –322, –324, and 

–325 airplanes, certificated in any category, 

all serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Reason 

This AD was prompted by reports of 

cracking in the drainage holes on the lower 

skin panel in the center wing box between 

frames (FR) 42 and FR46. We are issuing this 

AD to detect and correct cracking of trellis 

boom drainage holes, the holes in the 

stringers bottom, and the holes of the inner 

pump, which could result in reduced 

structural integrity of the wings. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Rotating Probe Inspections and 

Corrective Actions 

Except as provided by paragraph (h)(1) of 

this AD, before exceeding the applicable 

threshold or grace period, whichever occurs 

later, as defined in paragraph 1.E., 

‘‘Compliance,’’ of Airbus Service Bulletin 

A310–57–2050, Revision 04, dated March 13, 

2015, accomplish the rotating probe 

inspection for cracking of the trellis boom 

drainage holes, the holes in the stringers 

bottom, and the holes of the inner pump, as 

applicable, and do all applicable corrective 

actions, as specified in, and in accordance 

with the Accomplishment Instructions of 

Airbus Service Bulletin A310–57–2050, 

Revision 04, dated March 13, 2015, except as 

required by paragraph (h)(2) of this AD. Do 

all applicable corrective actions before 

further flight. Repeat the inspection 

thereafter at intervals not to exceed those 

defined in paragraph 1.E., ‘‘Compliance,’’ of 

Airbus Service Bulletin A310–57–2050, 

Revision 04, dated March 13, 2015. 

(h) Exceptions to Service Information 

(1) Where Airbus Service Bulletin A310– 

57–2050, Revision 04, dated March 13, 2015, 

specifies a grace period ‘‘after receipt of the 

Service Bulletin without exceeding previous 

Service Bulletin revision values,’’ this AD 

requires compliance within the specified 

grace period after the effective date of this 

AD. 

(2) Where Airbus Service Bulletin A310– 

57–2050, Revision 04, dated March 13, 2015, 

specifies to contact Airbus for appropriate 

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

(Required for Compliance): Before further 

flight, accomplish corrective actions in 


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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. 


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