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[Federal Register Volume 81, Number 13 (Thursday, January 21, 2016)]
[Rules and Regulations]
[Pages 3301-3304]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-00376]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-1045; Directorate Identifier 2014-NM-031-AD; 
Amendment 39-18372; AD 2016-01-13]
RIN 2120-AA64

Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for all 
Airbus Model A310 and 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). This AD was 
prompted by a report of skin disbonding and damage found on the 
composite side panel of the rudder, located between the rudder core and 
skin of a previously repaired area. This AD requires an inspection for 
disbonding or damage of certain rudders, and related investigative 
actions and corrective actions if necessary. We are issuing this AD to 
detect and correct disbonding and damage of the rudder, which could 
result in reduced structural integrity of the rudder and consequent 
reduced controllability of the airplane.

DATES: This AD is effective February 25, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of February 25, 
2016.

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2014-1045; 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 final rule, 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-
1045.

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 all Airbus Model A310 and 
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) series airplanes. The NPRM published in the 
Federal Register on January 23, 2015 (80 FR 3525).
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2014-0026, dated January 28, 2014 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for all Airbus Model A310 
and 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). The MCAI states:

    A case of skin disbonding was reported on a composite side of a 
rudder installed on an A310 aeroplane.
    The investigation results revealed that this disbonding started 
from a skin panel area previously repaired in-service in accordance 
with the Structural Repair Manual (SRM).
    The initial damage has been identified as a disbonding between 
the core and the repaired area. This damage may not be visually 
detectable and likely propagates during normal operation due to the 
variation of pressure during ground-air-ground cycles.
    This condition, if not detected and corrected, could affect the 
structural integrity of the rudder, possibly resulting in reduced 
control of the aeroplane.
    For the reasons described above, this [EASA] AD requires a one-
time thermography inspection of each repaired rudder or rudder whose 
maintenance records are incomplete and, depending on findings, 
accomplishment of applicable corrective and follow-up actions.

Related investigative actions include doing a pulse thermography 
inspection for disbonding or damage of the left- and right-hand rudder 
side shells; a core ventilation through the inner skin, an elasticity 
laminate checker or ultrasonic inspection around the identified repairs 
in the booster area, and around identified fluid ingress; and a Tap 
test inspection of the glass fiber reinforced plastic area to identify 
skin-to-core disbonding and on identified repairs. Corrective actions 
include repairing or replacing any disbonded or damaged rudder.
    Depending on configuration and inspection results, the repetitive 
inspection intervals are 750 or 1,000 flight cycles, or 500 flight 
hours or 4 months, whichever occurs later.
    You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2014-1045-0002.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the NPRM (80 
FR 3525, January 23, 2015) and the FAA's response to each comment.

No Justification for Issuing NPRM (80 FR 3525, January 23, 2015)

    FedEx stated that Airbus has not provided any data or analysis 
showing the de-validated SRM procedures in the proposed AD (80 FR 3525, 
January 23, 2015) as inadequate. FedEx noted that one finding on a 
Model A310 airplane with skin disbonding and damage found on the 
composite side panel of the

[[Page 3302]]

rudder caused the de-validation of all Model A300 and A310 airplanes 
with rudder side shell repairs, and mandatory inspections of all 
rudders repaired using the structural repair manual (SRM). FedEx added 
that a heavy burden is being placed on operators with very little 
justification from the manufacturer. FedEx stated that Airbus has not 
provided new validated SRM procedures, yet FedEx is being required to 
inspect all rudders without having any available, developed repairs; 
instead repairs would need to be done 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). FedEx does not agree with the de-
validation of the SRM procedures and mandating inspections of the 
entire fleet of airplanes, based on one finding.
    We infer that the commenter is asking for justification to support 
issuing this final rule. We acknowledge the commenter's concerns. 
However, the safety risk of undetected rudder skin disbonding that may 
not be detectable visually and could propagate during normal operation 
due to the variation of aerodynamic pressure during ground-air-ground 
cycles is sufficient to require the proposed actions. We also 
acknowledge that Airbus does not have new SRM procedures available, 
partially due to the unknown size and location of previously 
accomplished SRM repairs and the type of skin disbonding that may be 
identified that will result in each repair needing to be evaluated 
individually. Therefore, we have determined that inspections are 
necessary if an applicable SRM repair has been done, or if maintenance 
records are not available or are incomplete. The service information 
provides procedures for the detailed inspections; therefore, using a 
method approved by the FAA, EASA, or Airbus's EASA DOA is necessary 
only for repairs. We have determined it is necessary to proceed with 
issuing this final rule as proposed.

Request To Allow Using Future Revisions of the SRM for Rudder Repairs

    FedEx asked that paragraph (i) of the proposed AD (80 FR 3525, 
January 23, 2015) be revised to allow a composite side shell panel 
repair on any rudder using future revisions of the SRM procedure 
identified in Figure A-GBBAA (Sheet 01 and 02) or Figure A-GBCAA (Sheet 
02) of Airbus Service Bulletin A310-55-2051; or Figure A-GBBAA (Sheet 
01, 02, or 03) or Figure A-GBCAA (Sheet 02 or 04) of Airbus Service 
Bulletin A300-55-6050. FedEx stated that when Airbus revalidates the 
SRM procedures, FedEx won't be able to use those procedures for the 
repair because it is not allowed per paragraph (i) of the proposed AD.
    We do not agree with the request. Although we understand the FedEx 
concerns, allowing the use of later revisions of service documents in 
an AD is not allowed by the Office of the Federal Register's 
regulations. However, after the manufacturer validates a later revision 
of the SRM procedures that provides an acceptable level of safety we 
can evaluate the later revision of the SRM as an alternative method of 
compliance, in accordance with the procedures specified in paragraph 
(m)(1) of this AD. Paragraph (i) of this AD only prohibits the use of 
specific SRM procedures identified in that paragraph. We have not 
changed this AD in this regard.

Conclusion

    We reviewed the relevant data, considered the comments 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 (80 FR 3525, January 23, 2015) for correcting the unsafe 
condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (80 FR 3525, January 23, 2015).

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletins A300-55-2051 and A310-55-6050, 
both Revision 01, both dated August 20, 2014. The service information 
describes procedures for inspecting the left- and right-hand rudder 
side shells for disbonding or damage, and related investigative actions 
and corrective actions if necessary. The actions described in this 
service information are intended to correct the unsafe condition 
identified in the MCAI. 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.

Costs of Compliance

    We estimate that this AD affects 199 airplanes of U.S. registry.
    We also estimate that it will take about 4 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 about $0 per 
product. Based on these figures, we estimate the cost of this AD on 
U.S. operators to be $67,660, or $340 per product.
    We have received no definitive data that would enable us to provide 
a cost estimate for the on-condition actions specified in this AD.

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

    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 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-2014-1045; or in person at the 
Docket Management Facility between 9 a.m. and 5 p.m., Monday through 
Friday, except Federal

[[Page 3303]]

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):

2016-01-13 Airbus: Amendment 39-18372; Docket No. FAA-2014-1045; 
Directorate Identifier 2014-NM-031-AD.

(a) Effective Date

    This AD is effective February 25, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all Airbus Model A310-203, -204, -221, -222, 
-304, -322, -324, and -325 airplanes; Model A300 B4-601, B4-603, B4-
620, and B4-622 airplanes; Model A300 B4-605R and B4-622R airplanes; 
and Model A300 F4-605R, F4-622R, and A300 C4-605R Variant F 
airplanes; certificated in any category.

(d) Subject

    Air Transport Association (ATA) of America Code 55, Stabilizers.

(e) Reason

    This AD was prompted by a report of skin disbonding and damage 
found on the composite side panel of the rudder, located between the 
rudder core and skin of a previously repaired area. We are issuing 
this AD to detect and correct disbonding and damage of the rudder, 
which could result in reduced structural integrity of the rudder, 
and consequent reduced controllability of the airplane.

(f) Compliance

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

(g) Rudder Assembly Identification

    Within 4 months after the effective date of this AD: Check the 
applicable rudder maintenance records to determine if any composite 
side shell panel repair has been done since first installation of 
the rudder, and do the applicable actions specified in paragraph 
(g)(1) or (g)(2) of this AD at the time specified in paragraph 1.E., 
``Compliance,'' of Airbus Service Bulletin A300-55-6050, or A310-55-
2051, both Revision 01, both dated August 20, 2014; as applicable, 
except as provided by paragraph (j)(3) of this AD.
    (1) If a repair is identified based on the maintenance records: 
Perform a rudder thermography inspection of the repaired area only 
for disbonding or damage, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A300-55-6050, or A310-55-
2051, both Revision 01, both dated August 20, 2014; as applicable.
    (2) If the rudder maintenance records are unavailable or 
incomplete: Perform a rudder thermography inspection of the complete 
side shell panels to identify and mark the repair locations for 
disbonding or damage, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A300-55-6050, or A310-55-
2051, both Revision 01, both dated August 20, 2014; as applicable.

(h) Related Investigative Actions/Repair or Replace

    If any disbonding or damage is found during any inspection 
required by paragraph (g)(1) or (g)(2) of this AD: Do the actions 
required by paragraphs (h)(1) and (h)(2) of this AD, as applicable.
    (1) At the time specified in paragraph 1.E., ``Compliance,'' of 
Airbus Service Bulletin A300-55-6050, or A310-55-2051, both Revision 
01, both dated August 20, 2014; as applicable, except as required by 
paragraph (j)(1) of this AD; do the applicable related investigative 
actions identified in Tables 3, 4A, 4B, 4C, 4D, and 5 of paragraph 
1.E., ``Compliance,'' of Airbus Service Bulletin A300-55-6050, or 
A310-55-2051, both Revision 01, both dated August 20, 2014; as 
applicable, to determine the type and extent of the disbonding or 
damage, in accordance with the Accomplishment Instructions of Airbus 
Service Bulletin A300-55-6050, or A310-55-2051, both Revision 01, 
both dated August 20, 2014; as applicable. Repeat the applicable 
inspection at the time specified in paragraph 1.E., ``Compliance'' 
of Airbus Service Bulletin A300-55-6050, or A310-55-2051, both 
Revision 01, both dated August 20, 2014; as applicable.
    (2) Before further flight: Repair any disbonding or damage found 
during any inspection required by paragraph (h)(1) of this AD, or 
replace any affected rudder, as applicable, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A300-55-6050, 
or A310-55-2051, both Revision 01, both dated August 20, 2014; as 
applicable, except as required by paragraph (j)(4) of this AD.

(i) Repair Using Structural Repair Manual (SRM) Procedure Not Allowed

    As of the effective date of this AD, do not accomplish a 
composite side shell panel repair on any rudder using an SRM 
procedure identified in Figure A-GBBAA (Sheet 01 and 02) or Figure 
A-GBCAA (Sheet 02) of Airbus Service Bulletin A310-55-2051; or 
Figure A-GBBAA (Sheet 01, 02, or 03) or Figure A-GBCAA (Sheet 02 or 
04) of Airbus Service Bulletin A300-55-6050; as applicable.

(j) Exceptions to Service Information

    (1) Where Airbus Service Bulletins A300-55-6050; and A310-55-
2051; both Revision 01, both dated August 20, 2014; specify a 
compliance time ``from original service bulletin issue date,'' this 
AD requires compliance within the specified compliance time after 
the effective date of this AD.
    (2) Where Airbus Service Bulletins A300-55-6050; and A310-55-
2051 both Revision 01, both dated August 20, 2014; specify to 
contact Airbus for appropriate action: Before further flight, repair 
using a method approved by the Manager, International Branch, ANM-
116, Transport Airplane Directorate, FAA; or the European Aviation 
Safety Agency (EASA); or Airbus's EASA Design Organization Approval 
(DOA).
    (3) Airplanes on which a rudder is installed having a serial 
number that is not in the range HF-1005 through HF-1323, inclusive; 
HF-1325, HF-1327, HF-1329, HF-1331, HF-1332, HF-1340, TS-1324, TS-
1326, TS-1328, TS-1330, TS-1333 through TS-1339, inclusive; TS-1341 
through TS-1420, inclusive; or TS-2001 through TS-2197, inclusive; 
are not affected by the requirements of paragraphs (g) and (h) of 
this AD, provided that no repairs have been done in accordance with 
the applicable SRM specified in paragraph (i) of this AD on the 
composite side shell panel of that rudder since installation.
    (4) The compliance time for the initial detailed inspection of 
the restored area for loose or lost tape identified in Tables 3 and 
4 of paragraph 1.E., ``Compliance,'' of Airbus Service Bulletins 
A300-55-6050 and A310-55-2051, both Revision 01, both dated August 
20, 2014; specifies ``within 500 FH or 4 months after closing 
holes.'' This AD requires this action within 500 flight hours or 4 
months, whichever occurs later, after the holes are closed.

(k) 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 Airbus Service Bulletin 
A300-55-6050, or A310-55-2051, both dated September 11, 2012; as 
applicable; which are not incorporated by reference in this AD.

(l) Parts Installation Limitations

    As of the effective date of this AD, no person may install any 
affected rudder on any airplane, unless the actions required by 
paragraphs (g) and (h) of this AD have been accomplished.

(m) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
has the authority to approve AMOCs for this AD, if requested

[[Page 3304]]

using the procedures found in 14 CFR 39.19. In accordance with 14 
CFR 39.19, send your request to your principal inspector or local 
Flight Standards District Office, as appropriate. If sending 
information directly to the International Branch, send it to ATTN: 
Dan Rodina, Aerospace Engineer, International Branch, ANM-116, 
Transport Airplane Directorate, FAA 1601 Lind Avenue SW., Renton, WA 
98057-3356; telephone 425-227-2125; fax 425-227-1149. Information 
may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any 
approved AMOC, notify your appropriate principal inspector, or 
lacking a principal inspector, the manager of the local flight 
standards district office/certificate holding district office.
    (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 EASA; or 
Airbus's EASA DOA. If approved by the DOA, the approval must include 
the DOA-authorized signature.

(n) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2014-0026, dated January 28, 
2014, for related information. This MCAI may be found in the AD 
docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2014-1045-0002.
    (2) Service information identified in this AD that is not 
incorporated by reference is available 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 the AD specifies otherwise.
    (i) Airbus Service Bulletin A300-55-6050, Revision 01, dated 
August 20, 2014.
    (ii) Airbus Service Bulletin A310-55-2051, Revision 01, dated 
August 20, 2014.
    (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.

    Issued in Renton, Washington, on December 31, 2015.
Phil Forde,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-00376 Filed 1-20-16; 8:45 am]
 BILLING CODE 4910-13-P
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