Federal Register / Vol. 80, No. 115 / Tuesday, June 16, 2015 / Rules and Regulations 34249 

Issued in Fort Worth, Texas, on June 2, 

2015. 

Lance T. Gant, 

Acting Directorate Manager, Rotorcraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–14415 Filed 6–15–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0618; Directorate 

Identifier 2012–NM–171–AD; Amendment 

39–18178; AD 2015–12–05] 

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) 2008–06– 

18 for all Airbus 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); and Model 

A300 series airplanes. AD 2008–06–18 

required repetitive inspections for any 

cracking of the wing lower skin panel 

and associated internal support 

structure, and if necessary, corrective 

actions such as modifying the lower 

panel inboard of rib 9 aft of the rear spar 

and repairing cracks. This new AD 

continues to require actions required by 

AD 2008–06–18, and reduces certain 

compliance times. This AD was 

prompted by a report that information 

from an analysis and a fleet survey 

shows a need for reduced compliance 

times and intervals. We are issuing this 

AD to detect and correct cracking, 

which could lead to reduced structural 

integrity of the airplane. 

DATES: This AD becomes effective July 

21, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of July 21, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of April 23, 2008 (73 FR 

14670, March 19, 2008). 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2014-0618; 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. It is also 

available on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2014– 

0618. 

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 to supersede AD 2008–06–18, 

Amendment 39–15430 (73 FR 14670, 

March 19, 2008). AD 2008–06–18 

applied to all Airbus 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); and 

Model A300 series airplanes. The NPRM 

published in the Federal Register on 

September 3, 2014 (79 FR 52263). The 

NPRM proposed to continue to require 

repetitive inspections for any cracking 

of the wing lower skin panel and 

associated internal support structure, 

and if necessary, corrective actions such 

as modifying the lower panel inboard of 

rib 9 aft of the rear spar and repairing 

cracks. The NPRM also proposed to 

reduce some compliance times. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2012–0203, dated October 1, 

2012 (referred to after this as the 

Mandatory Continuing Airworthiness 

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

an unsafe condition on all Airbus 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); and Model A300 series 

airplanes. The MCAI states: 

During routine maintenance, cracks were 

found in the wing bottom skin and in the 

associated internal support structure on an 

A300 aeroplane aft of the rear spar and 

inboard of rib 9. Initially, cracks were found 

in the skin only, starting from a fastener close 

to the forward outboard corner of access 

panel 575FB/675FB. Subsequently, cases 

were reported of cracks being found in the 

skin support strap and the stiffener. 

This condition, if not detected and 

corrected, could affect the structural integrity 

of the aeroplane. 

To address this unsafe condition, EASA 

issued AD 2006–0282 [http://

ad.easa.europa.eu/ad/2006-0282] [which 

corresponds with FAA AD 2008–06–18, 

Amendment 39–15430 (73 FR 14670, March 

19, 2008)] to require repetitive inspections of 

the wing lower skin panel and associated 

internal support structure aft of the rear spar 

and inboard of rib 9. 

Since that [EASA] AD was issued, the 

results of a fleet survey and updated Fatigue 

and Damage Tolerance analysis, which were 

performed in order to substantiate the second 

A300 and A300–600 Extended Service Goal 

(ESG2) exercise, revealed that the inspection 

threshold and interval had to be reduced to 

allow timely detection of cracks and the 

accomplishment of an applicable corrective 

action. 

Prompted by these findings, Airbus issued 

Revision 05 of Airbus Service Bulletin (SB) 

A300–57–0177 and Revision 07 of Airbus SB 

A300–57–6029. 

For the reasons described above, this 

[EASA] AD retains the requirements of EASA 

AD 2006–0282, which is superseded, but 

requires the accomplishment of those actions 

within reduced thresholds and intervals. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2014-0618- 

0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comment 

received on the NPRM (79 FR 52263, 

September 3, 2014) and the FAA’s 

response to each comment. 

Request To Revise Method Used To 

Determine Compliance Times 

United Parcel Service (UPS) requested 

that the proposed compliance times be 

revised to be less complex. UPS stated 

that the proposed compliance times 

contain a method known as ‘‘Average 

Flight Time’’ (AFT) which results in a 

variable flight hour limit and adds an 

unnecessary complexity to the threshold 

table and subsequent inspection actions. 

UPS added that use of the AFT method, 

along with a lack of standard procedures 

for implementing the AFT method 

would create uncertainty for operators 


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34250 Federal Register / Vol. 80, No. 115 / Tuesday, June 16, 2015 / Rules and Regulations 

and inspectors trying to determine the 

correct compliance time. UPS stated 

that in review of prior FAA ADs, 

including AD 98–18–02, that the FAA 

does not concur with the AFT 

compliance time methodology as ‘‘. . . 

such adjustments may not address the 

unsafe condition in a timely manner’’ 

and ‘‘. . . they (AFT compliance times) 

do not fit into the AD tracking process 

for operators or for Principle 

Maintenance Inspectors (PMIs) 

attempting to ascertain compliance with 

ADs.’’ UPS compiled a table of fixed 

compliance times that it suggested 

would be simpler to use instead of the 

proposed AFT-based compliance times. 

We disagree with the commenter’s 

request to revise the compliance times 

in this AD. In AD 98–18–02, 

Amendment 39–10718 (63 FR 45689, 

August 27, 1998), and certain other ADs, 

the required actions referred to service 

information that contained inspection 

thresholds and intervals based on 

airplane flight cycles only. Therefore, 

the FAA did not agree with the use of 

the ‘‘average flight time’’ (AFT) method 

to adjust the inspection thresholds and 

intervals, which were based only on 

flight cycles. However, for this AD the 

compliance times in Airbus Service 

Bulletin A300–57–0177, Revision 05, 

dated March 23, 2007, and Airbus 

Service Bulletin A300–57–6029, 

Revision 08, dated April 25, 2013, have 

been determined for a combination of 

flight cycles and flight hours for which 

the AFT methodology is appropriate. 

We acknowledge that a fixed 

compliance time for a fleet could be 

easier for operators to schedule and 

record compliance. Therefore, under the 

provisions of paragraph (j)(1) of this AD, 

we will consider requests for approval 

of an alternative method of compliance 

(AMOC) if a proposal is submitted that 

is supported by technical data that 

includes fatigue and damage tolerance 

analysis We have not changed this AD 

in this regard. 

Conclusion 

We reviewed the available data, 

including the comment received, 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 (79 FR 

52263, September 3, 2014) for correcting 

the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (79 FR 52263, 

September 3, 2014). 

Related Service Information Under 1 

CFR Part 51 

Airbus has issued Service Bulletin 

A300–57–6029, Revision 08, dated April 

25, 2013. The service information 

describes procedures for inspecting the 

wing lower skin panel and associated 

internal support structure aft of the rear 

spar and inboard of rib 9 and applying 

applicable corrective measures. 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 of 

this AD. 

Costs of Compliance 

We estimate that this AD affects 162 

airplanes of U.S. registry. 

The actions that were required by AD 

2008–06–18, Amendment 39–15430 (73 

FR 14670, March 19, 2008), and retained 

in this AD take about 2 work-hours per 

product, at an average labor rate of $85 

per work-hour. Based on these figures, 

the estimated cost of the actions that 

were required by AD 2008–06–18 is 

$170 per product. 

We also estimate that it will take 

about 2 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 $27,540, or $170 per 

product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 12 work-hours and require parts 

costing $10,000, for a cost of $11,020 

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-2014-0618; 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. 


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Federal Register / Vol. 80, No. 115 / Tuesday, June 16, 2015 / Rules and Regulations 34251 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by 

removing Airworthiness Directive (AD) 

2008–06–18, Amendment 39–15430 (73 

FR 14670, March 19, 2008), and adding 

the following new AD: 

2015–12–05 Airbus: Amendment 39–18178. 

Docket No. FAA–2014–0618; Directorate 

Identifier 2012–NM–171–AD. 

(a) Effective Date 

This AD becomes effective July 21, 2015. 

(b) Affected ADs 

This AD replaces AD 2008–06–18, 

Amendment 39–15430 (73 FR 14670, March 

19, 2008). 

(c) Applicability 

This AD applies to the airplanes identified 

in paragraphs (c)(1) through (c)(5) of this AD, 

certificated in any category, all certified 

models, all serial numbers. 

(1) Airbus Model A300 B2–1A, B2–1C, 

B2K–3C, B2–203, B4–2C, B4–103, and B4– 

203 airplanes. 

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

B4–620, and B4–622 airplanes. 

(3) Airbus Model A300 B4–605R and B4– 

622R airplanes. 

(4) Airbus Model A300 F4–605R and F4– 

622R airplanes. 

(5) Airbus Model A300 C4–605R Variant F 

airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Reason 

This AD was prompted by a report that 

information from an analysis and a fleet 

survey shows a need for reduced compliance 

times and intervals. We are issuing this AD 

to detect and correct cracking, which could 

lead to reduced structural integrity of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Actions and Compliance Times, 

with Revised Service Information 

This paragraph restates the requirements of 

paragraph (f) of AD 2008–06–18, Amendment 

39–15430 (73 FR 14670, March 19, 2008), 

with revised service information. Unless 

already done, do the following actions. 

(1) Except as provided by paragraphs 

(g)(1)(i), (g)(1)(ii), (g)(1)(iii), (g)(1)(iv), and (h) 

of this AD: At the threshold specified in 

paragraph 1.E.(2), ‘‘Accomplishment 

Timescale,’’ of Airbus Service Bulletin A300– 

57–0177, Revision 05, dated March 23, 2007 

(for Model A300 series airplanes); Airbus 

Service Bulletin A300–57–6029, Revision 06, 

dated March 23, 2007 (for Model A300–600 

series airplanes); or Airbus Service Bulletin 

A300–57–6029, Revision 08, dated April 25, 

2013 (for Model A300–600 series airplanes); 

as applicable; perform the inspection of the 

wing lower skin panel and associated 

internal support structure aft of the rear spar 

and inboard of rib 9 and apply applicable 

corrective measures in accordance with 

Airbus Service Bulletin A300–57–0177, 

Revision 05, dated March 23, 2007 (for Model 

A300 series airplanes); Airbus Service 

Bulletin A300–57–6029, Revision 06, dated 

March 23, 2007 (for Model A300–600 series 

airplanes); or Airbus Service Bulletin A300– 

57–6029, Revision 08, dated April 25, 2013 

(for Model A300–600 series airplanes); as 

applicable. All applicable corrective 

measures must be done at the applicable 

times specified in paragraph 1.E.(2) and the 

Accomplishment Instructions of Airbus 

Service Bulletin A300–57–0177, Revision 05, 

dated March 23, 2007 (for Model A300 series 

airplanes); Airbus Service Bulletin A300–57– 

6029, Revision 06, dated March 23, 2007 (for 

Model A300–600 series airplanes); or Airbus 

Service Bulletin A300–57–6029, Revision 08, 

dated April 25, 2013 (for Model A300–600 

series airplanes); as applicable. 

Accomplishing the requirements of 

paragraph (h) of this AD terminates the 

requirements of this paragraph for Model 

A300–600 airplanes. 

(i) Where the tables in paragraph 1.E.(2), 

‘‘Accomplishment Timescale,’’ of Airbus 

Service Bulletin A300–57–0177, Revision 05, 

dated March 23, 2007; and Airbus Service 

Bulletin A300–57–6029, Revision 06, dated 

March 23, 2007; specify a grace period for 

doing the actions, this AD requires that the 

actions be done within the specified grace 

period relative to April 23, 2008 (the effective 

date of AD 2008–06–18, Amendment 39– 

15430 (73 FR 14670, March 19, 2008)). 

(ii) Where the tables in paragraph 

1.E.(2)(e), ‘‘Config 04,’’ of Airbus Service 

Bulletin A300–57–0177, Revision 05, dated 

March 23, 2007, specify an inspection 

interval but not an initial threshold, this AD 

requires that the actions be done within the 

specified interval after inspecting in 

accordance with Table 1A or 1B, as 

applicable, for Configuration 01 airplanes 

described in the Airbus Service Bulletin 

A300–57–0177, Revision 05, dated March 23, 

2007, and thereafter at the inspection interval 

specified in the tables in paragraph 1.E.(2)(e), 

‘‘Config 04,’’ of Airbus Service Bulletin 

A300–57–0177, Revision 05, dated March 23, 

2007. 

(iii) Where the tables in paragraph 

1.E.(2)(f), ‘‘Config 05,’’ of Airbus Service 

Bulletin A300–57–6029, Revision 06, dated 

March 23, 2007, specify an inspection 

interval but not an initial threshold, this AD 

requires that the actions be done within the 

specified interval after inspecting in 

accordance with Table 1A, or 1B, as 

applicable, for Configuration 01 airplanes 

described in Airbus Service Bulletin A300– 

57–6029, Revision 06, dated March 23, 2007, 

and thereafter at the inspection interval 

specified in the tables in paragraph 1.E.(2)(f), 

‘‘Config 05,’’ of Airbus Service Bulletin 

A300–57–6029, Revision 06, dated March 23, 

2007. 

(iv) All crack lengths specified in Airbus 

Service Bulletin A300–57–0177, Revision 05, 

dated March 23, 2007; and Airbus Service 

Bulletin A300–57–6029, Revision 06, dated 

March 23, 2007, are considered ‘‘not to 

exceed’’ lengths. 

(2) Repeat the inspection at the intervals 

in, and according to the instructions defined 

in, Airbus Service Bulletin A300–57–0177, 

Revision 05, dated March 23, 2007 (for Model 

A300 series airplanes); Airbus Service 

Bulletin A300–57–6029, Revision 06, dated 

March 23, 2007 (for Model A300–600 series 

airplanes); or Airbus Service Bulletin A300– 

57–6029, Revision 08, dated April 25, 2013 

(for Model A300–600 series airplanes); as 

applicable; except where Airbus Service 

Bulletin A300–57–0177, Revision 05, dated 

March 23, 2007, specifies repetitive 

inspections for cracking if Airbus Service 

Bulletin A300–57–022 has not been 

embodied, this AD requires doing repetitive 

inspections for cracking if Airbus Service 

Bulletin A300–57–0222 (modification 

11178H5410) has not been embodied. 

(3) Report to Airbus the first inspection 

results, whatever they may be, at the 

applicable time specified in paragraph 

(g)(3)(i) or (g)(3)(ii) of this AD. 

(i) If the inspection was done after April 

23, 2008 (the effective date of AD 2008–06– 

18, Amendment 39–15430 (73 FR 14670, 

March 19, 2008)), submit the report within 30 

days after the inspection. 

(ii) If the inspection was accomplished 

prior to April 23, 2008 (the effective date of 

AD 2008–06–18, Amendment 39–15430 (73 

FR 14670, March 19, 2008)), submit the 

report within 30 days after April 23, 2008. 

(h) New Requirement of This AD: New 

Compliance Times for Model A300–600 

Series Airplanes 

For Model A300–600 series airplanes, do 

the actions specified in paragraphs (h)(1) 

through (h)(3) of this AD at the applicable 

times specified in those paragraphs. 

(1) Except as provided by paragraphs 

(h)(1)(i) and (h)(1)(ii) of this AD: Within the 

compliance times specified in Airbus Service 

Bulletin A300–57–6029, Revision 08, dated 

April 25, 2013, perform the inspection of the 

wing lower skin panels and associated 

internal support structures aft of the rear spar 

and inboard of rib 9, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A300–57–6029, Revision 08, 

dated April 25, 2013. Thereafter, repeat these 

inspections at intervals specified in Airbus 

Service Bulletin A300–57–6029, Revision 08, 

dated April 25, 2013. Accomplishment of the 

actions required by this paragraph terminates 


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34252 Federal Register / Vol. 80, No. 115 / Tuesday, June 16, 2015 / Rules and Regulations 

the requirements of paragraph (g) of this AD 

for Model A300–600 airplanes. 

(i) Where the tables in paragraph 1.E.(2), 

‘‘Accomplishment Timescale,’’ of Airbus 

Service Bulletin A300–57–6029, Revision 08, 

dated April 25, 2013, specify a grace period 

for doing the actions for airplanes that have 

exceeded the thresholds, this AD requires, for 

all airplanes, that the actions be done within 

the specified grace period after the effective 

date of this AD or before the specified 

thresholds, whichever occurs later. 

(ii) Where Airbus Service Bulletin A300– 

57–6029, Revision 08, dated April 25, 2013, 

specifies to ‘‘contact Airbus’’ before further 

flight, this AD requires repairing using a 

method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or European 

Aviation Safety Agency (EASA); or Airbus’s 

EASA Design Organization Approval (DOA); 

and accomplishing those actions before 

further flight. If approved by the DOA, the 

approval must include the DOA-authorized 

signature. 

(2) If, during any inspection as required by 

paragraph (h)(1) of this AD, discrepancies are 

detected, before next flight, accomplish the 

applicable corrective actions, in accordance 

with the Accomplishment Instructions of 

Airbus Service Bulletin A300–57–6029, 

Revision 08, dated April 25, 2013. 

(3) Corrective actions, as required by 

paragraph (h)(2) of this AD, do not constitute 

terminating action for the repetitive 

inspection requirements of paragraph (h)(1) 

of this AD. 

(i) Credit for Previous Actions 

(1) This paragraph provides credit for 

actions required by paragraph (g) of this AD, 

if those actions were performed before April 

23, 2008 (the effective date of AD 2008–06– 

18, Amendment 39–15430 (73 FR 14670, 

March 19, 2008)), using the applicable 

service information identified in paragraphs 

(i)(1)(i) through (i)(1)(iv) of this AD, which 

are not incorporated by reference by this AD. 

(i) Airbus Service Bulletin A300–57–0177, 

Revision 03, dated May 29, 2006 (for Model 

A300 series airplanes). 

(ii) Airbus Service Bulletin A300–57–0177, 

Revision 04, dated January 5, 2007 (for Model 

A300 series airplanes). 

(iii) Airbus Service Bulletin A300–57– 

6029, Revision 04, dated May 29, 2006 (for 

Model A300–600 series airplanes). 

(iv) Airbus Service Bulletin A300–57– 

6029, Revision 05, dated October 23, 2006 

(for Model A300–600 series airplanes). 

(2) This paragraph provides credit for 

actions required by paragraph (g) or (h) of 

this AD, if those actions were performed 

before the effective date of this AD, using 

Airbus Service Bulletin A300–57–6029, 

Revision 07, dated June 6, 2011 (for Model 

A300–600 series airplanes), which is not 

incorporated by reference by this AD. 

(j) 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. 

(i) 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. 

(ii) AMOCs approved previously for AD 

2008–06–18, Amendment 39–15430 (73 FR 

14670, March 19, 2008), are approved as 

AMOCs for the corresponding requirements 

of this AD. 

(2) Contacting the Manufacturer: As of the 

effective date of this AD, for any requirement 

in this AD to obtain corrective actions from 

a manufacturer, the action must be 

accomplished using a method approved by 

the Manager, International 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) 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. 

(k) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2012–0203, dated 

October 1, 2012, 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– 

2014–0618. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (l)(5) and (l)(6) of this AD. 

(l) 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. 

(3) The following service information was 

approved for IBR on July 21, 2015. 

(i) Airbus Service Bulletin A300–57–6029, 

Revision 08, dated April 25, 2013. 

(ii) Reserved. 

(4) The following service information was 

approved for IBR on April 23, 2008 (73 FR 

14670, March 19, 2008). 

(i) Airbus Service Bulletin A300–57–0177, 

Revision 05, dated March 23, 2007. 

(ii) Airbus Service Bulletin A300–57–6029, 

Revision 06, dated March 23, 2007. 

(5) 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. 

(6) 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. 

(7) 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 June 3, 

2015. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–14283 Filed 6–15–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0485; Directorate 

Identifier 2014–NM–093–AD; Amendment 

39–18176; AD 2015–12–03] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2007–13– 

05 for all The Boeing Company Model 

777–200, –200LR, –300, and –300ER 

series airplanes. AD 2007–13–05 

required repetitive measurements of the 

freeplay of the right and left elevators, 

rudder, and rudder tab, and related 


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