Document ID: FAA-2014-0230-0006
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Airbus Airplanes
Posted Date: 2015-01-29T05:00Z

[Federal Register Volume 80, Number 19 (Thursday, January 29, 2015)]
[Rules and Regulations]
[Pages 4769-4772]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2015-00997]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0230; Directorate Identifier 2013-NM-242-AD; 
Amendment 39-18070; AD 2015-02-03]
RIN 2120-AA64

Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
Airbus Model A300 B4-601, B4-603, B4-605R, F4-605R, and C4-605R Variant 
F airplanes. This AD was prompted by reports of cracking found in the 
pylon box, which was due to the stresses resulting from the pressure 
applied by the thrust reverser cowl bumpers. This AD requires 
repetitive high frequency eddy current (HFEC) inspections for cracking; 
and replacement of all fittings if necessary, which terminates the 
repetitive HFEC inspections for the modified side only. We are issuing 
this AD to detect and correct cracks of the pylon rib 5, which could 
result in reduced structural integrity of the airplane.

DATES: This AD becomes effective March 5, 2015.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of March 5, 
2015.

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2014-0230; 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, Washington 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 
B4-601, B4-603, B4-605R, F4-605R, and C4-605R Variant F airplanes. The 
NPRM published in the Federal Register on April 14, 2014 (79 FR 20837).
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2013-0286R1, dated June 6, 2014 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for certain Airbus Model 
A300 B4-601, B4-603, B4-605R, F4-605R, and C4-605R Variant F airplanes. 
The MCAI states:

    Cracks were found on the lower side of rib 5 in the pylon box on 
A300 aeroplanes powered with General Electric engines.
    Investigations revealed that these cracks were due to the 
stresses resulting from the pressure applied by the thrust reverser 
cowl bumpers.
    This condition, if not detected and corrected, could affect the 
structural integrity of the aeroplane.
    Airbus developed an inspection programme to detect the cracks 
and associated actions to correct them.
    For the reasons described above, EASA issued AD 2013-0286 
[http://ad.easa.europa.eu/blob/easa_ad_2013_0286_R1.pdf/AD_2013-0286R1_2] to require repetitive [HFEC] inspections of the pylon rib 
5 on the left hand side (LH) and right hand (RH) side and, when 
cracks are detected, replacement of the affected structural part(s). 
[Replacement of all fittings terminates the repetitive HFEC 
inspections.]
    Since that [EASA] AD was issued, it was found that the [EASA] AD 
has inadvertently been made applicable to all A300-600 Models, which 
is incorrect. This [EASA] AD has been revised to reduce the 
Applicability to only the affected Models.

    You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2014-0230-0004.

Revision to Applicability

    Since the NPRM (79 FR 20837, April 14, 2014), was issued, we have 
determined that paragraph (c), ``Applicability,'' of this AD should not 
include Airbus Model A300 B4-620, B4-622, B4-622R, and F4-622R 
airplanes. We have removed these airplanes from paragraph (c) of this 
AD, and have revised the SUMMARY section and Costs of Compliance 
section of this final rule accordingly.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the NPRM (79 
FR 20837, April 14, 2014) and the FAA's response to each comment.

Request for Credit for Modification

    FedEx requested that we revise paragraph (i) of the NPRM (79 FR 
20837, April 14, 2014) to indicate that prior incorporation of the 
modification specified in Airbus Service Bulletin A300-54-6031, dated 
May 30, 1996, provides credit as a terminating action for the 
repetitive HFEC inspections specified in the NPRM.
    We find that clarification is necessary. Paragraph (h) of this AD 
already specifies that accomplishment of the

[[Page 4770]]

referenced modification is terminating action for the repetitive HFEC 
inspections required by paragraph (g)(1) of this AD for the modified 
side only. We have made no change to this AD in this regard.

Request for Clarification

    UPS requested that we revise paragraphs (g)(2) and (h) of the NPRM 
(79 FR 20837, April 14, 2014) to clarify that replacement of fittings 
is to be done on the affected pylon or on the modified side only. UPS 
reasoned that one interpretation of the phrase ``all the fittings'' 
would be to replace the fittings in the left and right pylons, even 
though cracking was found in only one of the pylons.
    We agree to clarify. We have revised paragraphs (g)(2) and (h) of 
this AD to include the clarifications requested by the commenter.

``Contacting the Manufacturer'' Paragraph in This AD

    Since late 2006, we have included a standard paragraph titled 
``Airworthy Product'' in all MCAI ADs in which the FAA develops an AD 
based on a foreign authority's AD.
    We have become aware that some operators have misunderstood or 
misinterpreted the Airworthy Product paragraph to allow the owner/
operator to use messages provided by the manufacturer as approval of 
deviations during the accomplishment of an AD-mandated action. The 
Airworthy Product paragraph does not approve messages or other 
information provided by the manufacturer for deviations to the 
requirements of the AD-mandated actions. The Airworthy Product 
paragraph only addresses the requirement to contact the manufacturer 
for corrective actions for the identified unsafe condition and does not 
cover deviations from other AD requirements. However, deviations to AD-
required actions are addressed in 14 CFR 39.17, and anyone may request 
the approval for an alternative method of compliance to the AD-required 
actions using the procedures found in 14 CFR 39.19.
    To address this misunderstanding and misinterpretation of the 
Airworthy Product paragraph, we have changed the paragraph and retitled 
it ``Contacting the Manufacturer.'' This paragraph now clarifies that 
for any requirement in this AD to obtain corrective actions from a 
manufacturer, the actions must be accomplished using a method approved 
by the FAA, the EASA, or Airbus's EASA Design Organization Approval 
(DOA).
    The Contacting the Manufacturer paragraph also clarifies that, if 
approved by the DOA, the approval must include the DOA-authorized 
signature. The DOA signature indicates that the data and information 
contained in the document are EASA-approved, which is also FAA-
approved. Messages and other information provided by the manufacturer 
that do not contain the DOA-authorized signature approval are not EASA-
approved, unless EASA directly approves the manufacturer's message or 
other information.
    This clarification does not remove flexibility previously afforded 
by the Airworthy Product paragraph. Consistent with long-standing FAA 
policy, such flexibility was never intended for required actions. This 
is also consistent with the recommendation of the Airworthiness 
Directive Implementation Aviation Rulemaking Committee to increase 
flexibility in complying with ADs by identifying those actions in 
manufacturers' service instructions that are ``Required for 
Compliance'' with ADs. We continue to work with manufacturers to 
implement this recommendation. But once we determine that an action is 
required, any deviation from the requirement must be approved as an 
alternative method of compliance.
    We also have decided not to include a generic reference to either 
the ``delegated agent'' or ``design approval holder (DAH) with State of 
Design Authority design organization approval,'' but instead we have 
provided the specific delegation approval granted by the State of 
Design Authority for the DAH.

Conclusion

    We reviewed the relevant data, considered the comments 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 minor changes:
     Are consistent with the intent that was proposed in the 
NPRM (79 FR 20837, April 14, 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 20837, April 14, 2014).
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this AD.

Related Service Information

    We reviewed Airbus Service Bulletin A300-54-6031, dated May 30, 
1996; and Airbus Service Bulletin A300-54-6034, Revision 02, dated 
August 26, 2013. The service information describes procedures for 
repetitive HFEC inspections for cracking of the lower side of rib 5 in 
the LH and RH pylon box and replacing certain fittings. You can find 
this information at http://www.regulations.gov by searching for and 
locating Docket No. FAA-2014-0230.

Costs of Compliance

    We estimate that this AD affects 54 airplanes of U.S. registry.
    We also estimate that it will take about 9 work-hours per product 
to comply with the basic requirements of this AD. The average labor 
rate is $85 per work-hour. Required parts will cost $0 per product. 
Based on these figures, we estimate the cost of this AD on U.S. 
operators to be $41,310, or $765 per product.
    In addition, we estimate that any necessary follow-on actions will 
take about 32 work-hours and require parts costing $2,450, for a cost 
of $5,170 per product. We have no way of determining the number of 
aircraft that might need this action.

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;

[[Page 4771]]

    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-2014-0230; 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

0
1. The authority citation for part 39 continues to read as follows:

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

Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

2015-02-03 Airbus: Amendment 39-18070. Docket No. FAA-2014-0230; 
Directorate Identifier 2013-NM-242-AD.

(a) Effective Date

    This AD becomes effective March 5, 2015.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus Model A300 B4-601, B4-603, B4-605R, 
F4-605R, and C4-605R Variant F airplanes, certificated in any 
category, all manufacturer serial numbers, except those on which 
Airbus Modification 11110 has been embodied in production, or that 
have been modified in service as specified in Airbus Service 
Bulletin A300-54-6031, dated May 30, 1996.

(d) Subject

    Air Transport Association (ATA) of America Code 54, Nacelles/
Pylons.

(e) Reason

    This AD was prompted by reports of cracking found in the pylon 
box, which was due to the stresses resulting from the pressure 
applied by the thrust reverser cowl bumpers. We are issuing this AD 
to detect and correct cracks of the pylon rib 5, which could result 
in reduced structural integrity of the airplane.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Inspection and Replacement

    (1) Before the accumulation of 15,000 total flight hours since 
the airplane's first flight, or within 6,000 flight hours after the 
effective date of this AD, whichever occurs later: Do a high 
frequency eddy current (HFEC) inspection for cracking on the lower 
area of rib 5 on the left-hand and right-hand side pylons, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A300-54-6034, Revision 02, dated August 26, 2013. Repeat 
the inspection thereafter at intervals not to exceed 15,000 flight 
hours.
    (2) If any crack is found during any inspection required by 
paragraph (g)(1) of this AD, before further flight, replace all the 
fittings--on the affected pylon only--with new standard fittings, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A300-54-6031, dated May 30, 1996.

(h) Terminating Action

    Replacement of all fittings as required by paragraph (g)(2) of 
this AD; or modification of pylons in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A300-54-6031, 
dated May 30, 1996; terminates the repetitive HFEC inspections 
required by paragraph (g)(1) of this AD for the modified side only.

(i) Credit for Previous Actions

    This paragraph provides credit for the inspections required by 
paragraph (g)(1) of this AD, if those actions were performed before 
the effective date of this AD using Airbus Service Bulletin A300-54-
6034, Revision 01, dated September 14, 1999, which is not 
incorporated by reference in 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, Washington 
98057-3356; telephone 425-227-2125; fax 425-227-1149. Information 
may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any 
approved AMOC, notify your appropriate principal inspector, or 
lacking a principal inspector, the manager of the local flight 
standards district office/certificate holding district office. The 
AMOC approval letter must specifically reference this AD.
    (2) Contacting the Manufacturer: For any requirement in this AD 
to obtain corrective actions from a manufacturer, the action must be 
accomplished using a method approved by the Manager, International 
Branch, ANM-116, Transport Airplane Directorate, FAA; or the 
European Aviation Safety Agency (EASA); or Airbus's EASA Design 
Organization Approval (DOA). If approved by the DOA, the approval 
must include the DOA-authorized signature.

(k) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2013-0286R1, dated June 6, 2014, 
for related information. This MCAI may be found in the AD docket on 
the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-
2014-0230-0004.
    (2) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (l)(3) and (l)(4) 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.
    (i) Airbus Service Bulletin A300-54-6031, dated May 30, 1996.
    (ii) Airbus Service Bulletin A300-54-6034, Revision 02, dated 
August 26, 2013.
    (3) For service information identified in this AD, contact 
Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; 
fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com; 
Internet http://www.airbus.com.
    (4) You may view this service information at the FAA, Transport 
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/ibr-locations.html.

[[Page 4772]]

    Issued in Renton, Washington, on January 12, 2015.
John P. Piccola, Jr.,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-00997 Filed 1-28-15; 8:45 am]
BILLING CODE 4910-13-P