Federal Register / Vol. 81, No. 65 / Tuesday, April 5, 2016 / Proposed Rules 19509 

the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the EASA; or Airbus’s EASA DOA. If 

approved by the DOA, the approval must 

include the DOA-authorized signature. 

(l) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2013–0167, dated 

July 26, 2013, 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 it in Docket No. 

FAA–2016–5039. 

(2) 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. 

You may view this service information at the 

FAA, Transport Airplane Directorate, 1601 

Lind Avenue SW., Renton, WA. For 

information on the availability of this 

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

Issued in Renton, Washington, on March 

24, 2016. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–07569 Filed 4–4–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–5040; Directorate 

Identifier 2013–NM–192–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

Airbus Model A300 series airplanes; 

and Model A300 B4–600, B4–600R, and 

F4–600R series airplanes, and Model 

A300 C4–605R Variant F airplanes 

(collectively called Model A300–600 

series airplanes). This proposed AD was 

prompted by the determination that 

certain existing inspection thresholds 

and intervals must be reduced. This 

proposed AD would require repetitive 

detailed inspections for corrosion, and 

related investigative and corrective 

actions if necessary. We are proposing 

this AD to detect and correct corrosion 

and cracking on the lower wing root 

joint, which could reduce the structural 

integrity of the airframe. 

DATES: We must receive comments on 

this proposed AD by May 20, 2016. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this NPRM, 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 

Airplane Directorate, 1601 Lind Avenue 

SW., Renton, WA. For information on 

the availability of this material at the 

FAA, call 425–227–1221. 

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– 

5040; 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 proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Operations 

office (telephone 800–647–5527) is in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

FOR FURTHER INFORMATION CONTACT: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone (425) 227–2125; 

fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2016–5040; Directorate Identifier 

2013–NM–192–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD based on those comments. 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2013–0230, dated September 

24, 2013 (referred to after this as the 

Mandatory Continuing Airworthiness 

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

an unsafe condition for certain Airbus 

Model A300 and A300–600 series 

airplanes. The MCAI states: 

Several cases of corrosion on the lower 

wing root joint, located in the wing bottom 

skin inboard and outboard of the external 

lower surface splice, have been reported by 

operators. 

This condition, if not detected and 

corrected, could affect the structural integrity 

of the airframe. 

Prompted by these findings, [Directorate 

General for Civil Aviation] (DGAC) France 

issued AD 1997–006–210 [which 

corresponds to FAA AD 98–21–34, 

Amendment 39–10842 (63 FR 55524, October 

16, 1998)] to require repetitive inspections to 

detect the presence of corrosion and prevent 

crack propagation at the wing bottom skin, 

inboard and outboard of the Rib 1 external 

lower surface splice, between Frame (FR) 40 

and FR47. 

DGAC France * * * issued [an AD] to 

expand the choice of applicable Service 

Bulletins (SB). [The] DGAC France AD * * * 

was issued to allow A300–600 operators to 

use Revision 04 of Airbus SB A300–57–6047, 

converting flight cycles/‘‘Fatigue rating’’ into 

flight cycles (FC)/flight hours (FH). 

Subsequently, Airbus modification 10599 

was developed to improve the corrosion 

behaviour of the area. This improvement 

allowed refining the inspection programme 

of the A300–600 aeroplane. For postmodification 10599 A300–600 aeroplanes, 

the application of the Maintenance Review 

Board Report (MRBR) inspection tasks was 

deemed sufficient for maintaining an 

adequate level of safety on these aeroplanes. 

Consequently, EASA issued AD 2008–0208 

[http://ad.easa.europa.eu/blob/easa_ad_

2008_0208_R2.pdf/AD_2008-0208R2_1] (later 

revised), retaining the requirements of [a] 

DGAC France AD * * *, which was 

superseded, to require the use of Airbus SB 

A300–57–6047 Revision 05 for the 

inspections and to exclude post-modification 


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19510 Federal Register / Vol. 81, No. 65 / Tuesday, April 5, 2016 / Proposed Rules 

10599 A300–600 aeroplanes from the 

Applicability. 

Since EASA AD 2008–0208R1 was issued, 

a fleet survey and updated Fatigue and 

Damage Tolerance analyses have been 

performed in order to substantiate the second 

A300–600 Extended Service Goal (ESG2) 

exercise. The results of these analyses 

determined that the threshold and interval 

must be reduced to allow timely detection of 

these cracks and the accomplishment of an 

applicable corrective action. 

For the reasons described above, this 

[EASA] AD takes over and retains the 

requirements for A300 and A300–600 

aeroplanes from EASA AD 2008–0208R1 

(which has been revised, remaining 

applicable only to A310 aeroplanes) and 

requires accomplishment of the inspections 

within the new thresholds and intervals. 

Required actions include repetitive 

detailed inspections for corrosion of the 

rib 1 external lower surface splice 

between FR40 and FR47, and repetitive 

fatigue inspections for cracking of the 

fasteners and on the surface of the 

forward and aft lower surface panels if 

necessary, and corrective actions 

(including application of new protective 

coating, removal of corrosion, and 

measurement of the reworked depth) if 

necessary. 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– 

5040. 

Related Rulemaking 

AD 98–21–34, Amendment 39–10842 

(63 FR 55524, October 16, 1998) (‘‘AD 

98–21–34’’), applies to all Model A300, 

A300–600, and A310 series airplanes. 

This NPRM proposes to apply to only 

certain Model A300 and A300–600 

series airplanes. The actions in this 

proposed AD are the same as those 

required by AD 98–21–34, but with 

certain revised compliance times. 

Accomplishment of the initial 

inspection specified in this proposed 

AD would terminate the repetitive 

inspection requirements of AD 98–21– 

34 for the affected airplanes. Certain 

modified Model A300–600 series 

airplanes would not be subject to the 

inspection requirements of this AD, and 

would no longer be subject to the 

repetitive inspection requirements of 

AD 98–21–34. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Service Bulletin A300– 

57–0204, Revision 01, dated April 2, 

1999; and Airbus Service Bulletin 

A300–57–6047, Revision 06, dated 

October 17, 2011. This service 

information describes procedures for 

repetitive detailed inspections for 

corrosion of the rib 1 external lower 

surface splice between FR40 and FR47, 

repetitive fatigue inspections for 

cracking of the fasteners and on the 

surface of the forward and aft lower 

surface panels if necessary, and 

corrective actions (including application 

of new protective coating, removal of 

corrosion, and measurement of the 

reworked depth) if necessary. This 

service information is reasonably 

available because the interested parties 

have access to it through their normal 

course of business or by the means 

identified in the ADDRESSES section. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of these same 

type designs. 

Costs of Compliance 

We estimate that this proposed AD 

affects 29 airplanes of U.S. registry. We 

also estimate that it would take about 8 

work-hours per product to comply with 

the basic requirements of this proposed 

AD. The average labor rate is $85 per 

work-hour. Based on these figures, we 

estimate the cost of this proposed AD on 

U.S. operators to be $19,270, or $680 per 

product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 8 work-hours, for a cost of $680 

per product. We have no way of 

determining the number of aircraft that 

might need these actions. 

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. 

Regulatory Findings 

We determined that this proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would 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 this proposed regulation: 

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. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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): 

Airbus: Docket No. FAA–2016–5040; 

Directorate Identifier 2013–NM–192–AD. 

(a) Comments Due Date 

We must receive comments by May 20, 

2016. 

(b) Affected ADs 

This AD affects AD 98–21–34, Amendment 

39–10842 (63 FR 55524, October 16, 1998) 

(‘‘AD 98–21–34’’). 

(c) Applicability 

This AD applies to all Airbus airplanes, 

certificated in any category, identified in 

paragraphs (c)(1) and (c)(2) of this AD. 


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(1) Model A300 B2–1A, B2–1C, B2K–3C, 

B2–203, B4–2C, B4–103, and B4–203 

airplanes. 

(2) Model A300 B4–601, B4–603, B4–620, 

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

622R, and C4–605R Variant F airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Reason 

This AD was prompted by the 

determination that certain existing inspection 

thresholds and intervals must be reduced. 

We are issuing this AD to detect and correct 

corrosion and cracking on the lower wing 

root joint, which could reduce the structural 

integrity of the airframe. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Airplanes Excluded From Requirements 

of This AD and AD 98–21–34 

For airplanes identified in paragraph (c)(2) 

of this AD on which Airbus modification 

10599 has been incorporated: 

(1) No action is required by this AD; and 

(2) As of the effective date of this AD, the 

actions specified in AD 98–21–34 are no 

longer required. 

(h) Inspection and Corrective Actions 

Within 60 months since the airplane’s first 

flight, or within 60 months since 

accomplishment of the last inspection 

specified in Airbus Service Bulletin A300– 

57–0204 or A300–57–6047, whichever occurs 

later: Do a detailed inspection for corrosion 

of the rib 1 external lower surface splice 

between frame (FR)40 and FR47, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A300– 

57–0204, Revision 01, dated April 2, 1999; or 

Airbus Service Bulletin A300–57–6047, 

Revision 06, dated October 17, 2011; as 

applicable. Repeat the inspection thereafter 

at intervals not to exceed 60 months. 

Accomplishment of the initial inspection 

required by this paragraph terminates the 

requirements of AD 98–21–34 for Model 

A300 and A300–600 series airplanes. 

(i) Corrective Actions for Corrosion 

If any corrosion is found during any 

inspection required by paragraph (h) of this 

AD, do the actions specified in paragraph 

(i)(1) and (i)(2) of this AD. 

(1) Before further flight, do all applicable 

corrective actions in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A300–57–0204, Revision 01, 

dated April 2, 1999; or Airbus Service 

Bulletin A300–57–6047, Revision 06, dated 

October 17, 2011; as applicable; except as 

required by paragraph (j)(1) of this AD. 

(2) At the applicable time specified in 

paragraph (i)(2)(i) or (i)(2)(ii) of this AD, 

except as required by paragraph (j)(2) of this 

AD: Do fatigue inspections to detect cracks of 

the fasteners and on the surface of the 

forward and aft lower surface panels, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A300– 

57–0204, Revision 01, dated April 2, 1999; or 

Airbus Service Bulletin A300–57–6047, 

Revision 06, dated October 17, 2011; as 

applicable. Repeat the fatigue inspections 

thereafter at the applicable interval specified 

in paragraph B.(5) of Airbus Service Bulletin 

A300–57–0204, Revision 01, dated April 2, 

1999; or Figure A–FBGAA, Sheet 01, of 

Airbus Service Bulletin A300–57–6047, 

Revision 06, dated October 17, 2011; as 

applicable; except as required by paragraph 

(j)(2) of this AD. If any cracking is found 

during any fatigue inspection required by 

this paragraph: Before further flight, repair 

using a method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or the European 

Aviation Safety Agency (EASA); or Airbus’s 

EASA Design Organization Approval (DOA). 

(i) For Model A300 series airplanes: Do the 

initial inspection at the applicable time 

specified in paragraph B.(5) of Airbus Service 

Bulletin A300–57–0204, Revision 01, dated 

April 2, 1999. 

(ii) For Model A300–600 series airplanes: 

Do the initial inspection at the later of the 

times specified in paragraphs (i)(2)(ii)(A) and 

(i)(2)(ii)(B) of this AD. 

(A) At the applicable time specified in 

Figure A–FBGAA, Sheet 01, of Airbus 

Service Bulletin A300–57–6047, Revision 06, 

dated October 17, 2011. 

(B) Within 500 flight cycles or 1,050 flight 

hours after the effective date of this AD, 

whichever occurs first, without exceeding the 

time specified in paragraph (i)(2)(ii)(A) of 

this AD. 

(j) Exceptions to Service Bulletin 

Specifications 

(1) Where Airbus Service Bulletin A300– 

57–0204, Revision 01, dated April 2, 1999; or 

Airbus Service Bulletin A300–57–6047, 

Revision 06, dated October 17, 2011; 

specifies to contact Airbus for appropriate 

corrective action, this AD requires repair 

before further flight using a method approved 

by the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

EASA; or Airbus’s EASA DOA. 

(2) Where Airbus Service Bulletin A300– 

57–6047, Revision 06, dated October 17, 

2011, specifies to contact Airbus for the 

appropriate threshold or repetitive interval, 

this AD requires that the compliance time be 

determined using a method approved by the 

Manager, International Branch, ANM–116, 

Transport Airplane Directorate, FAA; or 

EASA; or Airbus’s EASA DOA. 

(k) Calculating Average Flight Time (AFT) 

The accumulated flight hours (counted 

from the takeoff up to the landing) divided 

by the number of accumulated flight cycles 

is the AFT per flight cycle. 

(l) Credit for Previous Actions 

This paragraph provides credit for the 

inspections and corrective actions required 

by paragraphs (h) and (i) of this AD, if those 

actions were performed before the effective 

date of this AD using the applicable service 

information specified in paragraphs (l)(1) 

through (l)(3) of this AD. 

(1) Airbus Service Bulletin A300–57–6047, 

Revision 02, dated April 2, 1999, which is 

not incorporated by reference in this AD. 

(2) Airbus Service Bulletin A300–57–6047, 

Revision 03, dated September 28, 1999, 

which is not incorporated by reference in this 

AD. 

(3) Airbus Service Bulletin A300–57–6047, 

Revision 05, dated May 27, 2008, which is 

not incorporated by reference in this AD. 

(m) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, 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 Branch, send it to ATTN: 

Dan Rodina, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone (425) 227–2125; fax (425) 227– 

1149. Information may be emailed to: 9- 

ANM-116-AMOC-REQUESTS@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. The AMOC 

approval letter must specifically reference 

this AD. 

(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 Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the EASA; or Airbus’s EASA DOA. If 

approved by the DOA, the approval must 

include the DOA-authorized signature. 

(n) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2013–0230, dated 

September 24, 2013, 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–2016–5040. 

(2) 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. 

You may view this service information at the 

FAA, Transport Airplane Directorate, 1601 

Lind Avenue SW., Renton, WA. For 

information on the availability of this 

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

Issued in Renton, Washington, on March 

24, 2016. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–07575 Filed 4–4–16; 8:45 am] 

BILLING CODE 4910–13–P 


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