Federal Register / Vol. 79, No. 73 / Wednesday, April 16, 2014 / Rules and Regulations 21389 

(g) Replacement 

Within 6,000 flight hours or 30 months, 

whichever occurs first, after the effective date 

of this AD: Remove and replace the locking 

plate having part number (P/N) CC670– 

12076–1 with an anti-migration assembly 

having P/N CC670–12370–1, on both the left 

and right number 3 slats, in accordance with 

the Accomplishment Instructions of 

Bombardier Service Bulletin 670BA–27–066, 

dated June 10, 2013. 

(h) Parts Installation Prohibition 

As of the effective date of this AD, no 

person may install any locking plate having 

P/N CC670–12076–1 on any airplane. 

(i) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York Aircraft 

Certification Office (ACO), ANE–170, 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 tour request to your principal 

inspector or local Flight Standards District 

Office, as appropriate. If sending information 

directly to the New York ACO, send it to 

ATTN: Program Manager, Continuing 

Operational Safety, FAA, New York ACO, 

1600 Stewart Avenue, Suite 410, Westbury, 

NY 11590; telephone 516–228–7300; fax 

516–794–5531. 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) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer, use these actions if they are 

FAA-approved. Corrective actions are 

considered FAA-approved if they were 

approved by the State of Design Authority (or 

its delegated agent, or the Design Approval 

Holder with a State of Design Authority’s 

design organization approval, as applicable). 

You are required to ensure the product is 

airworthy before it is returned to service. 

(j) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Airworthiness Directive CF–2013–31, dated 

October 8, 2013, for related information. This 

MCAI may be found in the AD docket on the 

Internet at http://www.regulations.gov/

#!documentDetail;D=FAA-2013-1069-0002. 

(k) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

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

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless this AD specifies otherwise. 

(i) Bombardier Service Bulletin 670BA–27– 

066, dated June 10, 2013. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Bombardier, Inc., 400 CoˆteVertu Road West, Dorval, Que ́bec H4S 1Y9, 

Canada; telephone 514–855–5000; fax 514– 

855–7401; email thd.crj@

aero.bombardier.com; Internet http://

www.bombardier.com. 

(4) 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. 

(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 April 4, 

2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–08452 Filed 4–15–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0865; Directorate 

Identifier 2012–NM–199–AD; Amendment 

39–17819; AD 2014–07–05] 

RIN 2120–AA64 

Airworthiness Directives; Fokker 

Services B.V. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Fokker Services B.V. Model F.28 Mark 

0070 and 0100 airplanes. This AD was 

prompted by an evaluation by the 

design approval holder (DAH) 

indicating that the butt-joints on the 

forward fuselage above the passenger 

door are subject to widespread fatigue 

damage (WFD). This AD requires 

inspecting the forward fuselage buttjoints for cracking, repairing any crack, 

and eventually doing a terminating 

repair. We are issuing this AD to 

prevent fatigue cracking of such buttjoints, which could result in reduced 

structural integrity of the airplane and 

in-flight decompression of the airplane. 

DATES: This AD becomes effective May 

21, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of May 21, 2014. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2013-0865: or in 

person at the 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. 

For service information identified in 

this AD, contact Fokker Services B.V., 

Technical Services Dept., P.O. Box 

1357, 2130 EL Hoofddorp, the 

Netherlands; telephone +31 (0)88–6280– 

350; fax +31 (0)88–6280–111; email 

technicalservices@fokker.com; Internet 

http://www.myfokkerfleet.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. 

FOR FURTHER INFORMATION CONTACT: Tom 

Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, 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 certain Fokker Services B.V. 

Model F.28 Mark 0070 and 0100 

airplanes. The NPRM published in the 

Federal Register on October 23, 2013 

(78 FR 63132). The NPRM was 

prompted by an evaluation by the DAH 

indicating that the butt-joints on the 

forward fuselage above the passenger 

door are subject to WFD. The NPRM 

proposed to require inspecting the 

forward fuselage butt-joints for cracking, 

repairing any crack, and eventually 

doing a terminating repair. We are 

issuing this AD to prevent fatigue 

cracking of such butt-joints, which 

could result in reduced structural 

integrity of the airplane and in-flight 

decompression of the airplane. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2012–0218, 

dated October 19, 2012 (referred to after 

this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for the specified products. The MCAI 

states: 

A report has been received of a crack, 

detected in a butt-joint on the forward 


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21390 Federal Register / Vol. 79, No. 73 / Wednesday, April 16, 2014 / Rules and Regulations 

fuselage of an F28 Mark 0100 aeroplane, 

above the passenger door. Investigation 

results revealed that, depending on the 

configuration of the aeroplane, four butt 

joints in the forward fuselage can be affected, 

at stringers 8, 37, 42 and 67 between fuselage 

stations 3850 and 5305. 

This condition, if not detected and 

corrected, can result in an exponential crack 

growth rate, possibly leading to failure of the 

butt-joint over a certain length and 

consequent in-flight decompression of the 

aeroplane. 

For the reasons described above, this 

[EASA] AD requires a one-time inspection 

[low frequency eddy current] of the forward 

fuselage butt joints for cracks and, depending 

on findings, accomplishment of a temporary 

repair [including a detailed inspection for 

cracks in the butt strap on the inside of the 

applicable joint, and corrective actions if 

necessary] and reporting the findings to 

Fokker Services. In addition, this AD requires 

a permanent repair/modification [and a 

detailed inspection for cracks in the butt 

strap on the inside of the applicable joint, 

and corrective actions if necessary]. 

Corrective actions include removing 

the cracked part of the butt joint and 

installing an insert, and installing of an 

external repair strap. You may examine 

the MCAI in the AD docket on the 

Internet at http://www.regulations.gov/

#!documentDetail;D=FAA-2013-0865- 

0001. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (78 

FR 63132, October 23, 2013) 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 (78 FR 

63132, October 23, 2013) for correcting 

the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (78 FR 63132, 

October 23, 2013). 

Costs of Compliance 

We estimate that this AD affects 4 

airplanes of U.S. registry. 

We also estimate that it will take 

about 127 work-hours per product to 

comply with the basic requirements of 

this AD. The average labor rate is $85 

per work-hour. Based on these figures, 

we estimate the cost of this AD on U.S. 

operators to be $43,180, or $10,795 per 

product. 

In addition, we estimate that any 

necessary follow-on actions will take 

about 30 work-hours, for a cost of 

$2,550 per product. We have no way of 

determining the number of aircraft that 

might need these actions. 

Paperwork Reduction Act 

A federal agency may not conduct or 

sponsor, and a person is not required to 

respond to, nor shall a person be subject 

to penalty for failure to comply with a 

collection of information subject to the 

requirements of the Paperwork 

Reduction Act unless that collection of 

information displays a current valid 

OMB control number. The control 

number for the collection of information 

required by this AD is 2120–0056. The 

paperwork cost associated with this AD 

has been detailed in the Costs of 

Compliance section of this document 

and includes time for reviewing 

instructions, as well as completing and 

reviewing the collection of information. 

Therefore, all reporting associated with 

this AD is mandatory. Comments 

concerning the accuracy of this burden 

and suggestions for reducing the burden 

should be directed to the FAA at 800 

Independence Ave. SW., Washington, 

DC 20591, Attn: Information Collection 

Clearance Officer, AES–200. 

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 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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2013-0865; 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 Operations office (telephone 

(800) 647–5527) is in the ADDRESSES

section. 

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 AD: 

2014–07–05 Fokker Services B.V.: 

Amendment 39–17819. Docket No. 

FAA–2013–0865; Directorate Identifier 

2012–NM–199–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective May 21, 2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Fokker Services B.V. 

Model F.28 Mark 0070 and 0100 airplanes, 

certificated in any category, as identified in 

Fokker Service Bulletin SBF100–53–118, 

Revision 2, dated October 16, 2012. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 


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Federal Register / Vol. 79, No. 73 / Wednesday, April 16, 2014 / Rules and Regulations 21391 

(e) Reason 

This AD was prompted by an evaluation by 

the design approval holder (DAH) indicating 

that the butt-joints on the forward fuselage 

above the passenger door are subject to 

widespread fatigue damage (WFD). We are 

issuing this AD to prevent fatigue cracking of 

such butt-joints, which could result in 

reduced structural integrity of the airplane 

and in-flight decompression of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection 

Before the accumulation of 35,000 total 

flight cycles, or within 8 months after the 

effective date of this AD, whichever occurs 

later: Do a low frequency eddy current 

inspection for cracking of the forward 

fuselage butt-joints, in accordance with the 

Accomplishment Instructions of Fokker 

Service Bulletin SBF100–53–118, Revision 2, 

dated October 16, 2012. 

(h) Repair 

If any cracking is found during the 

inspection specified in paragraph (g) of this 

AD, before further flight, do the actions 

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

AD. 

(1) Accomplish a temporary repair, 

including a detailed inspection for cracks in 

the butt strap on the inside of the applicable 

joint, and all applicable corrective actions, in 

accordance with the Accomplishment 

Instructions of Fokker Service Bulletin 

SBF100–53–118, Revision 2, dated October 

16, 2012. 

(2) Do a terminating repair of the forward 

fuselage butt-joints, including a detailed 

inspection for cracks in the butt strap on the 

inside of the applicable joint, and all 

applicable corrective actions, in accordance 

with the Accomplishment Instructions of 

Fokker Service Bulletin SBF100–53–119, 

Revision 2, dated May 8, 2013. 

Accomplishing the terminating repair 

specified in this paragraph is a method of 

compliance with the terminating repair 

required by paragraph (j) of this AD. 

(i) Reporting 

Submit a report of any crack findings from 

the inspection specified in paragraph (g) of 

this AD to Fokker Services, Hoeksteen 40, 

2132 MS Hoofddorp, P.O. Box 1357, 2130 EL 

Hoofddorp, The Netherlands; by using the 

Reporting Form (figure 14 and figure 15, as 

applicable) of Fokker Service Bulletin 

SBF100–53–118, Revision 2, dated October 

16, 2012; at the applicable time specified in 

paragraph (i)(1) or (i)(2) of this AD. 

(1) If the inspection was done on or after 

the effective date of this AD: Submit the 

report within 30 days after the inspection. 

(2) If the inspection was done before the 

effective date of this AD: Submit the report 

within 30 days after the effective date of this 

AD. 

(j) Terminating Repair 

Before the accumulation 50,000 total flight 

cycles, or within 8 months after the effective 

date of this AD, whichever occurs later: Do 

the terminating repair of the forward fuselage 

butt-joints, including a detailed inspection 

for cracks in the butt strap on the inside of 

the applicable joint, and all applicable 

corrective actions, in accordance with the 

Accomplishment Instructions of Fokker 

Service Bulletin SBF100–53–119, Revision 2, 

dated May 8, 2013. Do all applicable 

corrective actions before further flight. 

(k) Credit for Previous Actions 

(1) This paragraph provides credit for 

applicable actions required by paragraphs (g) 

and (h)(1) of this AD, if those actions were 

performed before the effective date of this AD 

using the service bulletins specified in 

paragraph (k)(1)(i) or (k)(1)(ii) of this AD, 

which are not incorporated by reference in 

this AD. 

(i) Fokker Service Bulletin SBF100–53– 

118, dated April 10, 2012. 

(ii) Fokker Service Bulletin SBF100–53– 

118, Revision 1, dated July 6, 2012. 

(2) This paragraph provides credit for 

actions required by paragraphs (h)(2) and (j) 

of this AD, if those actions were performed 

before the effective date of this AD using the 

service bulletins specified in paragraph 

(k)(2)(i) or (k)(2)(ii) of this AD, which are not 

incorporated by reference in this AD. 

(i) Fokker Service Bulletin SBF100–53– 

119, dated June 20, 2012. 

(ii) Fokker Service Bulletin SBF100–53– 

119, Revision 1, dated October 30, 2012. 

(l) Compliance Time Provisions 

No alternative compliance times may be 

used for the modification required by 

paragraph (j) of this AD, unless extensive 

new data are provided and the compliance 

time is approved as an alternative method of 

compliance (AMOC) in accordance with the 

procedures specified in paragraph (m) of 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, 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: 

Tom Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; telephone (425) 227–1137; 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) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(3) Reporting Requirements: A federal 

agency may not conduct or sponsor, and a 

person is not required to respond to, nor 

shall a person be subject to a penalty for 

failure to comply with a collection of 

information subject to the requirements of 

the Paperwork Reduction Act unless that 

collection of information displays a current 

valid OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0056. Public reporting for 

this collection of information is estimated to 

be approximately 5 minutes per response, 

including the time for reviewing instructions, 

completing and reviewing the collection of 

information. All responses to this collection 

of information are mandatory. Comments 

concerning the accuracy of this burden and 

suggestions for reducing the burden should 

be directed to the FAA at: 800 Independence 

Ave. SW., Washington, DC 20591, Attn: 

Information Collection Clearance Officer, 

AES–200. 

(n) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) European 

Aviation Safety Agency Airworthiness 

Directive 2012–0218, dated October 19, 2012, 

for related information. This MCAI may be 

found in the AD docket on the Internet at 

http://www.regulations.gov/

#!documentDetail;D=FAA-2013-0865-0001. 

(2) Service information identified in this 

AD that is not incorporated by reference may 

be viewed at the addresses specified in 

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

(o) 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) Fokker Service Bulletin SBF100–53– 

118, Revision 2, dated October 16, 2012. 

(ii) Fokker Service Bulletin SBF100–53– 

119, Revision 2, dated May 8, 2013. 

(3) For service information identified in 

this AD, contact Fokker Services B.V., 

Technical Services Dept., P.O. Box 1357, 

2130 EL Hoofddorp, the Netherlands; 

telephone +31 (0)88–6280–350; fax +31 

(0)88–6280–111; email technicalservices@

fokker.com; Internet http://

www.myfokkerfleet.com. 

(4) 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. 

(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. 


pmangrum on DSK3VPTVN1PROD with RULES
21392 Federal Register / Vol. 79, No. 73 / Wednesday, April 16, 2014 / Rules and Regulations 

Issued in Renton, Washington, on March 

28, 2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–07821 Filed 4–15–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0668; Directorate 

Identifier 2013–NM–017–AD; Amendment 

39–17826; AD 2014–08–02] 

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 certain 

Airbus Model A300 B4–600 and A300 

B4–600R series airplanes. This AD was 

prompted by reports of cracks found in 

certain bottom wing skin stringers 

during full-scale fatigue testing and in 

service. This AD requires modifying the 

profile of stringer run-outs of both 

wings, including a high frequency eddy 

current inspection of the fastener holes 

for defects and, if necessary, repairs. We 

are issuing this AD to prevent cracking 

in the bottom wing skin stringers, which 

could result in reduced structural 

integrity of the wings. 

DATES: This AD becomes effective May 

21, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of May 21, 2014. 

ADDRESSES: You may examine the AD 

on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2013-0668; or in 

person at the 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. 

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 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. 

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: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to certain Airbus Model A300 B4– 

600 and A300 B4–600R series airplanes. 

The NPRM published in the Federal 

Register on August 1, 2013 (78 FR 

46536). The NPRM was prompted by 

reports of cracks found in the bottom 

wing skin stringers at rib 14 during fullscale fatigue testing and in service. The 

NPRM proposed to require modifying 

the profile of stringer run-outs at rib 14 

of both wings, including a high 

frequency eddy current inspection of 

the fastener holes for defects and repairs 

if necessary. We are issuing this AD to 

prevent cracking in the bottom wing 

skin stringers, 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 

Community, has issued EASA 

Airworthiness Directive 2013–0008R1, 

dated January 22, 2013 (referred to after 

this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for the specified products. The MCAI 

states: 

During full-scale fatigue testing, cracks 

were detected in the bottom wing skin 

stringers at rib 14. In addition, A300 

aeroplane operators have also reported 

finding cracks in the same area. 

This condition, if not detected and 

corrected, could impair the structural 

integrity of the wings. 

Additional analysis results showed that the 

improved design of the stringer run-out is 

necessary for aeroplanes operating beyond 

the ESG 1 [extended service goal 1: 42,500 

flight cycles]. 

For the reasons described above, this 

[EASA] AD requires the removal of the 

stringer end run-out plate at stringer 19 on 

the bottom wing skin and the re-profiling 

modification of the stringers 10, 11, 12, 17 

and 19. 

* * * * * 

The modification also includes doing a 

high frequency eddy current inspection 

of the fastener holes for defects and, if 

necessary, repairs. You may examine 

the MCAI in the AD docket on the 

Internet at http://www.regulations.gov/

#!documentDetail;D=FAA-2013-0668- 

0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comment 

received on the NPRM (78 FR 46536, 

August 1, 2013) and the FAA’s response 

to the comment. 

Request To Refer to New Service 

Information 

UPS requested that the source of work 

instructions for accomplishing the 

proposed actions be revised to Airbus 

Mandatory Service Bulletin A300–57– 

6046, Revision 02, dated June 21, 2013. 

UPS noted that the NPRM (78 FR 46536, 

August 1, 2013) referenced Airbus 

Mandatory Service Bulletin A300–57– 

6046, Revision 01, dated April 18, 2011, 

as the source of work instructions. 

We agree. We have revised paragraph 

(g) of this final rule to refer to Airbus 

Mandatory Service Bulletin A300–57– 

6046, Revision 02, dated June 21, 2013, 

instead. We have revised paragraph (i) 

of this AD to also identify Airbus 

Mandatory Service Bulletin A300–57– 

6046, Revision 01, dated April 18, 2011, 

as an acceptable source of instructions 

if those actions are accomplished before 

the effective date of this AD. 

Additional Change 

We have revised paragraph (g) of this 

final rule to clarify when the applicable 

repairs are required to be done. 

Conclusion 

We reviewed the relevant data, 

considered the comment received, and 

determined that air safety and the 

public interest require adopting this AD 

with the changes described previously 

and minor editorial changes. We have 

determined that these changes: 

• Are consistent with the intent that 

was proposed in the NPRM (78 FR 

46536, August 1, 2013) for correcting 

the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (78 FR 46536, 

August 1, 2013). 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this AD. 

Costs of Compliance 

We estimate that this AD affects 29 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 


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