Federal Register / Vol. 80, No. 30 / Friday, February 13, 2015 / Proposed Rules 7989 

(2) For service information identified in 

this AD, contact Airbus SAS, Airworthiness 

Office—EAL, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

5 61 93 36 96; fax +33 5 61 93 45 80; email 

airworthiness.A330-A340@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 January 

30, 2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–02537 Filed 2–12–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0083; Directorate 

Identifier 2014–NM–131–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 A330–200, A330–200 

Freighter, and A330–300 series 

airplanes; and all A340–200 and A340– 

300 series airplanes. This proposed AD 

was prompted by reports that a bracket 

that attaches the cockpit instrument 

panel to the airplane structure, does not 

sustain the fatigue loads of the design 

service goal. This proposed AD would 

require repetitive inspections of that 

bracket for cracking and to determine if 

both lugs are fully broken, an inspection 

for cracking of an adjacent bracket, if 

necessary, and corrective actions if 

necessary. This AD would also provide 

an optional modification, which would 

terminate the repetitive inspections. We 

are proposing this AD to detect and 

correct cracking on a bracket of the 

cockpit instrument panel, which, 

combined with failure of the horizontal 

beam, could lead to collapse of the 

cockpit panel, and reduced 

controllability of the airplane. 

DATES: We must receive comments on 

this proposed AD by March 30, 2015. 

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: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact Airbus SAS, 

Airworthiness Office—EAL, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

96; fax +33 5 61 93 45 80; email 

airworthiness.A330–A340@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–2015– 

0083; 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: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–1138; 

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–2015–0083; Directorate Identifier 

2014–NM–131–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 2014–0127, dated May 15, 

2014 (referred to after this as the 

Mandatory Continuing Airworthiness 

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

an unsafe condition for certain Airbus 

Model A330–200, A330–200 Freighter, 

and A330–300 series airplanes; and all 

A340–200, and A340–300 series 

airplanes. The MCAI states: 

During flight tests, high stress levels have 

been measured on the bracket No 6 which 

attaches the cockpit instrument panel to the 

aeroplane structure, apparently introduced 

through the nose landing gear due to bumps 

on the runway. Airbus determined that the 

bracket does not sustain the fatigue loads 

during the Design Service Goal (DSG). This 

condition, if not detected and corrected, 

combined with failure of the horizontal 

beam, could lead to collapse of the cockpit 

panel, possibly resulting in reduced control 

of the aeroplane. 

To address this potential unsafe condition, 

Airbus developed a program to inspect the 

condition of the affected cockpit instrument 

panel bracket No 6, and designed a stronger 

(reinforced titanium undrilled) bracket. The 

new bracket can be installed in-service 

through Airbus Service Bulletin (SB) A330– 

25–3548 or SB A340–25–4354, as applicable 

to aeroplane type. 

For the reasons described above, this 

[EASA] AD requires repetitive inspections of 

the cockpit instrument panel bracket No 6 

and, depending on findings, the 

accomplishment of applicable corrective 

actions. This [EASA] AD also provides the 

installation of the stronger bracket as 

optional terminating action for the repetitive 

actions required by this [EASA] AD. 

The corrective actions include replacing 

bracket No. 6 and bracket No. 7 with 

serviceable parts, and repair, as 

applicable. 

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–2015– 

0083. 


wreier-aviles on DSK5TPTVN1PROD with PROPOSALS
7990 Federal Register / Vol. 80, No. 30 / Friday, February 13, 2015 / Proposed Rules 

Related Service Information Under 1 

CFR Part 51 

Airbus has issued the following 

service information. 

• Airbus Service Bulletin A330–25– 

3538, Revision 02, dated April 24, 2014, 

which provides procedures for 

inspection of cockpit instrument panel 

bracket 6. 

• Airbus Service Bulletin A330–25– 

3548, dated October 31, 2013, which 

provides procedures for reinforcement 

of cockpit instrument panel bracket 6. 

• Airbus Service Bulletin A340–25– 

4351, Revision 01, dated January 31, 

2014, which provides procedures for 

inspection of cockpit instrument panel 

bracket 6. 

• Airbus Service Bulletin A340–25– 

4354, dated October 31, 2013, which 

provides procedures for reinforcement 

of cockpit instrument panel bracket 6. 

The actions described in this service 

information are intended to correct the 

unsafe condition identified in the 

MCAI. This service information is 

reasonably available; see ADDRESSES for 

ways to access this service information. 

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. 

Explanation of ‘‘RC’’ Procedures and 

Tests in Service Information 

The FAA worked in conjunction with 

industry, under the Airworthiness 

Directives Implementation Aviation 

Rulemaking Committee (AD ARC), to 

enhance the AD system. One 

enhancement was a new process for 

annotating which procedures and tests 

in the service information are required 

for compliance with an AD. 

Differentiating these procedures and 

tests from other tasks in the service 

information is expected to improve an 

owner’s/operator’s understanding of 

crucial AD requirements and help 

provide consistent judgment in AD 

compliance. The actions specified in 

Airbus Service Bulletin A330–25–3538, 

Revision 02, dated April 24, 2014; and 

Airbus Service Bulletin A340–25–4351, 

Revision 01, dated January 31, 2014; 

include procedures and tests that are 

identified as RC (required for 

compliance) because these procedures 

have a direct effect on detecting, 

preventing, resolving, or eliminating an 

identified unsafe condition. 

As specified in a NOTE under the 

Accomplishment Instructions of the 

specified service information, 

procedures and tests identified as RC 

must be done to comply with the 

proposed AD. However, procedures and 

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 alternative method of compliance 

(AMOC), provided the procedures and 

tests identified as RC can be done and 

the airplane can be put back in a 

serviceable condition. Any substitutions 

or changes to procedures or tests 

identified as RC will require approval of 

an AMOC. 

Costs of Compliance 

We estimate that this proposed AD 

affects 76 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 $51,680, or $680 per product. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the follow-on repairs 

specified in this AD. 

In addition, we estimate that any 

necessary follow-on replacements 

would take about 23 work-hours and 

require parts costing $0, for a cost of 

$1,955 per product. We have no way of 

determining the number of aircraft that 

might need these actions. 

We estimate that the optional 

modification would take about 9 work 

hours and require parts costing $1,770, 

for a cost of $2,535. 

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–2015–0083; 

Directorate Identifier 2014–NM–131–AD. 

(a) Comments Due Date 

We must receive comments by March 30, 

2015. 

(b) Affected ADs 

None. 


wreier-aviles on DSK5TPTVN1PROD with PROPOSALS
Federal Register / Vol. 80, No. 30 / Friday, February 13, 2015 / Proposed Rules 7991 

(c) Applicability 

This AD applies to the Airbus airplanes 

identified in paragraphs (c)(1) and (c)(2) of 

this AD, certificated in any category. 

(1) Model A330–201, –202, –203, –223, 

–243, –223F, –243F, –301, –302, –303, –321, 

–322, –323, –341, –342, and –313 airplanes, 

all manufacturer serial numbers except those 

on which Airbus Modification 203287 has 

been embodied in production. 

(2) Model A340–211, –212, –213, –311, 

–312, and –313 airplanes, all manufacturer 

serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 25, Equipment/Furnishings. 

(e) Reason 

This AD was prompted by reports that a 

bracket that attaches the cockpit instrument 

panel to the airplane structure, does not 

sustain the fatigue loads of the design service 

goal. We are issuing this AD to detect and 

correct cracking on a bracket of the cockpit 

instrument panel, which, combined with 

failure of the horizontal beam, could lead to 

collapse of the cockpit panel, and reduced 

controllability of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection of Bracket No. 6 of the Cockpit 

Instrument Panel 

At the latest of the times specified in 

paragraphs (g)(1), (g)(2), and (g)(3) of this AD: 

Do a detailed inspection of bracket No. 6 of 

the cockpit instrument panel for cracking and 

to determine if both bracket lugs are fully 

broken, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A330–25–3538, Revision 02, 

dated April 24, 2014; or Airbus Service 

Bulletin A340–25–4351, Revision 01, dated 

January 31, 2014; as applicable. Repeat the 

inspection thereafter at intervals not to 

exceed 2,600 flight cycles. 

(1) Prior to accumulating 17,200 total flight 

cycles since the airplane’s first flight. 

(2) Prior to bracket No. 6 of the cockpit 

instrument panel accumulating 17,200 total 

flight cycles since installation on an airplane. 

(3) Within 500 flight cycles after the 

effective date of this AD. 

(h) Inspection and Corrective Actions 

(1) If, during any inspection required by 

paragraph (g) of this AD, any cracking of 

bracket No. 6 of the cockpit instrument panel 

is found, but both bracket lugs are not fully 

broken: Within 2,600 flight cycles after that 

inspection, replace bracket No. 6 of the 

cockpit instrument panel with a serviceable 

part, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A330–25–3538, Revision 02, 

dated April 24, 2014; or Airbus Service 

Bulletin A340–25–4351, Revision 01, dated 

January 31, 2014; as applicable. Replacement 

of bracket No. 6 of the cockpit instrument 

panel does not constitute terminating action 

for the repetitive inspections required by 

paragraph (g) of this AD. 

(2) If, during any inspection required by 

paragraph (g) of this AD, any cracking of 

bracket No. 6 of the cockpit instrument panel 

is found and both bracket lugs are fully 

broken: Before further flight, do a detailed 

inspection of bracket No. 7 of the cockpit 

instrument panel for cracking, in accordance 

with the Accomplishment Instructions of 

Airbus Service Bulletin A330–25–3538, 

Revision 02, dated April 24, 2014; or Airbus 

Service Bulletin A340–25–4351, Revision 01, 

dated January 31, 2014; as applicable. 

(i) If, during the inspection required by 

paragraph (h)(2) of this AD, no cracking is 

found in bracket No. 7 of the cockpit 

instrument panel: Before further flight, 

replace bracket No. 6 and bracket No. 7 of the 

cockpit instrument panel with serviceable 

parts, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A330–25–3538, Revision 02, 

dated April 24, 2014; or Airbus Service 

Bulletin A340–25–4351, Revision 01, dated 

January 31, 2014; as applicable. Replacement 

of bracket No. 6 of the cockpit instrument 

panel does not constitute terminating action 

for the repetitive inspections required by 

paragraph (g) of this AD. 

(ii) If, during the inspection required by 

paragraph (h)(2) of this AD, any cracking is 

found in bracket No. 7 of the cockpit 

instrument panel: Although Airbus Service 

Bulletin A330–25–3538, Revision 02, dated 

April 24, 2014; and Airbus Service Bulletin 

A340–25–4351, Revision 01, dated January 

31, 2014; specify to contact Airbus for repair 

instructions, and specify that action as ‘‘RC’’ 

(Required for Compliance), repair the 

cracking before further flight using a repair 

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) Optional Terminating Modification for 

Paragraph (g) of This AD 

Modifying an airplane by replacing bracket 

No. 6 of the cockpit instrument panel with 

a new, reinforced bracket, in accordance with 

the Accomplishment Instructions of Airbus 

Service Bulletin A330–25–3548, dated 

October 31, 2013; or Airbus Service Bulletin 

A340–25–4354, dated October 31, 2013; as 

applicable; terminates the repetitive 

inspections required by paragraph (g) of this 

AD. 

(j) Credit for Previous Actions 

This paragraph provides credit for actions 

required by paragraphs (g) and (h) of this AD, 

if those actions were performed before the 

effective date of this AD using the service 

information identified in paragraph (j)(1), 

(j)(2), or (j)(3) of this AD, which are not 

incorporated by reference in this AD. 

(1) Airbus Service Bulletin A330–25–3538, 

dated September 10, 2013. 

(2) Airbus Service Bulletin A330–25–3538, 

Revision 01, dated April 24, 2014. 

(3) Airbus Service Bulletin A340–25–4351, 

dated September 10, 2014. 

(k) 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: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1138; 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. 

(3) Required for Compliance (RC): Except 

as required by paragraph (h)(2)(ii) of this AD, 

if Airbus Service Bulletin A330–25–3538, 

Revision 02, dated April 24, 2014; or Airbus 

Service Bulletin A340–25–4351, Revision 01, 

dated January 31, 2014; contain procedures 

or tests that are identified as RC, those 

procedures and tests must be done to comply 

with this AD; any procedures and 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 

operators 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 a serviceable condition. Any 

substitutions or changes to procedures or 

tests identified as RC require approval of an 

AMOC. 

(l) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2014–0127, dated 

May 15, 2014, 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– 

2015–0083. 

(2) For service information identified in 

this AD, contact Airbus SAS, Airworthiness 

Office—EAL, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

5 61 93 36 96; fax +33 5 61 93 45 80; email 

airworthiness.A330-A340@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. 


wreier-aviles on DSK5TPTVN1PROD with PROPOSALS
7992 Federal Register / Vol. 80, No. 30 / Friday, February 13, 2015 / Proposed Rules 

Issued in Renton, Washington, on January 

30, 2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–02536 Filed 2–12–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0084; Directorate 

Identifier 2014–NM–181–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 B4–2C, B4–103, and 

B4–203 airplanes; Airbus Model A300 

B4–600 series airplanes; and Airbus 

Model A300 B4–600R series airplanes. 

This proposed AD was prompted by 

reports indicating that, on airplanes that 

received a certain repair following crack 

findings, cracks can re-initiate. This 

proposed AD would require repetitive 

inspections for cracking of the frame 

(FR) 40 forward fittings for airplanes 

previously repaired. We are proposing 

this AD to detect and correct cracking 

on the FR 40 forward fittings, which 

could result in rupture of the forward 

fittings and reduction of in-flight 

structural strength. 

DATES: We must receive comments on 

this proposed AD by March 30, 2015. 

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: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed 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. 

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–2015– 

0084; 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–2015–0084; Directorate Identifier 

2014–NM–181–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 2014–0199, dated September 

05, 2014 (referred to after this as the 

Mandatory Continuing Airworthiness 

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

an unsafe condition for certain Airbus 

Model A300 B4–2C, B4–103, and B4– 

203 airplanes; Airbus Model A300 B4– 

600 series airplanes; and Airbus Model 

A300 B4–600R series airplanes. The 

MCAI states: 

During routine inspection on an A300–600 

aeroplane, a crack was found in the righthand frame (FR) 40 forward fitting between 

stringer (STRG) 32 and STRG 33. The subject 

aeroplane had previously been modified, as 

a crack prevention measure, in accordance 

with Airbus SB A300–57–6053 (mod 10453). 

To ensure the structural integrity of FR 40, 

pending completion of the full root cause 

analysis using a refined Finite Element 

Model (FEM), EASA issued AD 2009–0094 

[dated April 21, 2009, http://

ad.easa.europa.eu/ad/2009–0094], to require, 

a one-time Detailed Visual Inspection (DVI) 

of A300 and A300–600 aeroplanes on which 

Airbus SB A300–53–0297 or SB A300–57– 

6053, as applicable, was embodied as a crack 

prevention measure. 

Thereafter, cracks were found during 

maintenance check in the FR 40 forward 

fitting on two aeroplanes, one A300 with 

Airbus SB A300–53–0297 embodied and one 

A300–600 with Airbus SB A300–57–6053 

embodied. EASA AD 2009–0094 had been 

accomplished on both aeroplanes. 

Consequently, EASA issued AD 2011–0163 

[dated August 30, 2011, http://

ad.easa.europa.eu/ad/2011-0163], 

superseding EASA AD 2009–0094, to require, 

for aeroplanes modified preventively, 

repetitive DVI of the FR 40 forward fitting 

(without nut removal), accomplishment of a 

one-time Eddy Current (EC) inspection or 

liquid penetrant inspection of this area (with 

nut removal) and, depending on findings, the 

accomplishment of associated corrective 

actions. 

A detailed FEM study was recently 

completed which demonstrated that, on 

aeroplanes repaired following crack findings 

in accordance with the instructions of Airbus 

SB A300–53–0297 or SB A300–57–6053 at 

any revision, as applicable, cracks can reinitiate. 

For the reasons described above, this 

[EASA] AD requires repetitive inspections of 

the FR 40 forward fitting for aeroplanes 

repaired in accordance with the instructions 

of Airbus SB A300–53–0297 or SB A300–57– 

6053 following crack findings. 

The corrective actions include a 

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). 

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–2015– 

0084. 


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