80 FR 19009 - Airworthiness Directives; Airbus Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 80, Issue 68 (April 9, 2015)

Page Range		19009-19013
FR Document		2015-07799
We are adopting a new airworthiness directive (AD) for certain Airbus Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, F4- 605R, F4-622R, and C4-605R Variant F airplanes; and Model A310-203, - 204, -221, -222, -304, -322, -324, and -325 airplanes. This AD was prompted by a report of inner skin disbonding damage on a rudder. This AD requires repetitive ultrasonic inspections for disbonding of certain rudders; an elasticity of laminate checker inspection; a woodpecker or tap test inspection; venting the core, if necessary; and repairing, if necessary. We are issuing this AD to detect and correct rudder disbonding, which could affect the structural integrity of the rudder.
Federal Register, Volume 80 Issue 68 (Thursday, April 9, 2015)
[Federal Register Volume 80, Number 68 (Thursday, April 9, 2015)]
[Rules and Regulations]
[Pages 19009-19013]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2015-07799]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0123; Directorate Identifier 2013-NM-040-AD; 
Amendment 39-18134; AD 2015-07-06]
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, B4-620, B4-622, B4-605R, B4-622R, F4-
605R, F4-622R, and C4-605R Variant F airplanes; and Model A310-203, -
204, -221, -222, -304, -322, -324, and -325 airplanes. This AD was 
prompted by a report of inner skin disbonding damage on a rudder. This 
AD requires repetitive ultrasonic inspections for disbonding of certain 
rudders; an elasticity of laminate

[[Page 19010]]

checker inspection; a woodpecker or tap test inspection; venting the 
core, if necessary; and repairing, if necessary. We are issuing this AD 
to detect and correct rudder disbonding, which could affect the 
structural integrity of the rudder.

DATES: This AD becomes effective May 14, 2015.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of May 14, 
2015.

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2014-0123; 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-2014-0123.

FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-2125; 
fax 425-227-1149.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to certain Airbus Model A300 
B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, F4-605R, F4-622R, and 
C4-605R Variant F airplanes; and Model A310-203, -204, -221, -222, -
304, -322, -324, and -325 airplanes. The NPRM published in the Federal 
Register on February 28, 2014 (79 FR 11355).
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2013-0039, dated February 26, 2013 (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, B4-620, B4-622, B4-605R, B4-622R, F4-605R, F4-
622R, and C4-605R Variant F airplanes; and Model A310-203, -204, -221, 
-222, -304, -322, -324, and -325 airplanes. The MCAI states:

    One A310 operator found substantial inner skin disbonding damage 
on a rudder that was previously inspected in accordance with the 
instructions of Airbus Service Bulletin (SB) A310-55-2044. The 
results of the subsequent investigation revealed that the most 
probable cause of this damage was a blunt impact with no visible 
damage from outside during the rudder handling. Damage like this 
might grow with pressure variation during ground-air-ground cycles, 
and tests performed with other rudders showed a rapid propagation of 
damage during artificial pressure cycling.
    This condition, if not detected and corrected, could affect the 
structural integrity of the rudder.
    To address this potential unsafe condition, Airbus issued Alert 
Operators Transmission (AOT) A55W002-12 [dated December 13, 2012], 
pending Aircraft Maintenance Manual (AMM) 27-21-21 PB401 revision to 
update rudder handling procedures.
    For the reasons described above, this [EASA] AD requires 
ultrasonic test (UT) inspections of the affected rudders to detect 
signs of disbonding and, depending on findings, accomplishment of 
applicable corrective action(s).

    Required actions also include an elasticity of laminate checker 
inspection to detect external and internal disbonding, and a woodpecker 
or tap test inspection to detect external disbonding. You may examine 
the MCAI in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2014-0123-0002.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the NPRM (79 
FR 11355, February 28, 2014) and the FAA's response to each comment.

Requests To Exclude Certain Airplanes From AD Requirements

    Airbus requested that we revise paragraph (g) of the NPRM (79 FR 
11355, February 28, 2014) to mirror the language in Airbus Alert 
Operators Transmission (AOT) A55W002-12, dated December 13, 2012, which 
takes into account whether or not the rudder has been removed and/or 
installed since the last inspection. Airbus stated that the removal/
installation process is linked to the risk of the unseen damage 
occurring to the rudder. Airbus suggested revised language for a 
requirement to determine if the rudder has been removed or installed 
since the last inspection.
    In addition, FedEx requested that we revise paragraph (c) or (g) of 
the NPRM (79 FR 11355, February 28, 2014) to state that, if the 
installed rudder has been inspected (and not removed) per AD 2008-11-
05, Amendment 39-15527 (73 FR 29423, May 21, 2008), since its 
installation, no further inspection will be required since the unsafe 
condition would be alleviated.
    UPS, FedEx, and Airbus requested that we revise the NPRM (79 FR 
11355, February 28, 2014) to eliminate unnecessary AD tracking 
requirements. UPS noted that the identified risk only exists in cases 
where the rudder has been changed since inspection under AD 2008-11-05, 
Amendment 39-15527 (73 FR 29423, May 21, 2008). UPS further stated that 
the NPRM does not refer to AD 2008-11-05, even though the repetitive 
ultrasonic inspections to detect disbonding in the NPRM are identical 
to the requirements of paragraph (f)(2) of AD 2008-11-05. Also, UPS 
stated that the airplane maintenance manual (AMM) has been updated as 
of June 1, 2013, to include the same ultrasonic inspection specified in 
both AD 2008-11-05 and the NPRM. UPS suggested revised wording for the 
NPRM.
    We concur with the requests to limit the airplanes subject to the 
requirements of paragraph (g) of this AD. This AD does relate to AD 
2008-11-05 (73 FR 29423, dated May 21, 2008), in that the ultrasonic 
inspections are required in both ADs. This AD requires the ultrasonic 
inspections for only certain airplanes. Therefore, we have added a new 
paragraph (h)(2) in this AD. Paragraph (h)(2) of this AD specifies 
that, for airplanes on which it can be conclusively determined that the 
most recent inspection specified in Airbus Service Bulletin A310-55-
2044 or Airbus Service Bulletin A300-55-6043 was done on the airplane; 
or the rudder was not removed for any reason since doing the most 
recent inspection specified in Airbus Service Bulletin A310-55-2044 or 
Airbus Service Bulletin A300-55-6043; no further action is necessary, 
except as specified in paragraphs (j) and (k) of this AD.
    We have also re-designated paragraphs (h), (h)(1), and (h)(2) of 
the NPRM as paragraphs (h)(1), (h)(1)(i), and (h)(1)(ii) of this AD, 
respectively.

Request To Remove Requirement To Refer to This AD in Repair Approvals

    UPS requested that we revise the NPRM (79 FR 11355, February 28, 
2014)

[[Page 19011]]

to remove the requirement to include the AD reference in repair 
approvals. UPS noted its concerns that the NPRM will increase requests 
for approval of alternative methods of compliance (AMOCs) and result in 
delays to other services and actions addressed by the FAA on a daily 
basis.
    We concur with the commenter's request to remove from this AD the 
requirement that repair approvals must specifically refer to 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. The MCAI or referenced service 
information in an FAA AD often directs the owner/operator to contact 
the manufacturer for corrective actions, such as a repair. Briefly, the 
Airworthy Product paragraph allowed owners/operators to use corrective 
actions provided by the manufacturer if those actions were FAA-
approved. In addition, the paragraph stated that any actions approved 
by the State of Design Authority (or its delegated agent) are 
considered to be FAA-approved.
    In the NPRM (79 FR 11355, February 28, 2014), we proposed to 
prevent the use of repairs that were not specifically developed to 
correct the unsafe condition, by requiring that the repair approval 
provided by the State of Design Authority or its delegated agent 
specifically refer to this FAA AD. This change was intended to clarify 
the method of compliance and to provide operators with better 
visibility of repairs that are specifically developed and approved to 
correct the unsafe condition. In addition, we proposed to change the 
phrase ``its delegated agent'' to include ``the Design Approval Holder 
(DAH) with a State of Design Authority's design organization approval 
(DOA)'' to refer to a DAH authorized to approve required repairs for 
the AD.
    In its comments to the NPRM (79 FR 11355, February 28, 2014), UPS 
stated the following: ``The proposed wording, being specific to 
repairs, eliminates the interpretation that Airbus messages or other 
approved EASA documents are acceptable for approving minor deviations 
(corrective actions) needed during accomplishment of a[n AD] mandated 
Airbus service bulletin.''
    This comment has made the FAA 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 that 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, EASA, or Airbus's EASA 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 afforded previously 
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 AD 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.
    Other commenters to another NPRM having Directorate Identifier 
2012-NM-101-AD (78 FR 78285, December 26, 2013) pointed out that in 
many cases the foreign manufacturer's service bulletin and the foreign 
authority's MCAI may have been issued some time before the FAA AD. 
Therefore, the DOA may have provided U.S. operators with an approved 
repair, developed with full awareness of the unsafe condition, before 
the FAA AD is issued. Under these circumstances, to comply with the FAA 
AD, the operator would be required to go back to the manufacturer's DOA 
and obtain a new approval document, adding time and expense to the 
compliance process with no safety benefit.
    Based on these comments, we removed the requirement from this AD 
that the DAH-provided repair specifically refer to this AD. Before 
adopting such a requirement in the future, the FAA will coordinate with 
affected DAHs and verify they are prepared to implement means to ensure 
that their repair approvals consider the unsafe condition addressed in 
an AD. Any such requirements will be adopted through the normal AD 
rulemaking process, including notice-and-comment procedures, when 
appropriate.
    We have also decided not to include a generic reference to either 
the ``delegated agent'' or the ``DAH with State of Design Authority 
design organization approval,'' but instead we will provide the 
specific delegation approval granted by the State of Design Authority 
for the DAH.

Compliance Time Clarification

    In paragraph (g) of this AD, for airplanes on which the part number 
or serial number cannot be determined, we have revised the compliance 
time of ``before further flight'' to ``within 3 months after the 
effective date of this AD.'' This clarification corresponds to the 
compliance time in the MCAI. We have determined that extending the 
compliance time will provide an acceptable level of safety.

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 11355, February 28, 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 11355, February 28, 2014).
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this AD.

[[Page 19012]]

Related Service Information Under 1 CFR Part 51

    Airbus has issued AOT A55W002-12, dated December 13, 2012, 
including Inspection Flowchart. The service information describes, 
among other actions, procedures for an ultrasonic inspection along the 
Z-profile of the rudder side panel. This service information is 
reasonably available; see ADDRESSES for ways to access this service 
information.

Costs of Compliance

    We estimate that this AD affects 89 airplanes of U.S. registry. We 
also estimate that it would take about 10 work-hours per product to 
comply with the basic requirements of this AD. The average labor rate 
is $85 per work-hour. Required parts would cost about $0 per product. 
Based on these figures, we estimate the cost of this AD on U.S. 
operators to be $75,650, or $850 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

    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-2014-0123; 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):

2015-07-06 Airbus: Amendment 39-18134. Docket No. FAA-2014-0123; 
Directorate Identifier 2013-NM-040-AD.

(a) Effective Date

    This AD becomes effective May 14, 2015.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to the airplanes identified in paragraphs (c)(1) 
and (c)(2) of this AD, except airplanes on which modification 08827 
has been embodied in production.
    (1) Airbus Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, 
B4-622R, F4-605R, F4-622R, and C4-605R Variant F airplanes, 
certificated in any category, all manufacturer serial numbers.
    (2) Airbus Model A310-203, -204, -221, -222, -304, -322, -324, 
and -325 airplanes, certificated in any category, all manufacturer 
serial numbers.

(d) Subject

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

(e) Reason

    This AD was prompted by a report of inner skin disbonding damage 
on a rudder. We are issuing this AD to detect and correct rudder 
disbonding, which could affect the structural integrity of the 
rudder.

(f) Compliance

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

(g) Identification of Part Number

    Within 3 months after the effective date of this AD, identify 
the rudder assembly part number (P/N) and serial number (S/N), in 
accordance with Airbus Alert Operators Transmission (AOT) A55W002-
12, dated December 13, 2012, including Inspection Flowchart. If the 
part number or serial number cannot be determined, within 3 months 
after the effective date of this AD, identify the part number and 
serial number, in accordance with a method approved by either 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).

(h) Inspections

    (1) Except as provided by paragraph (h)(2) of this AD, if a 
rudder assembly part number starting with A55471500 is found during 
the inspection required by paragraph (g) of this AD, before further 
flight, do an ultrasonic (UT) inspection for damage (e.g., 
disbonding and liquid ingress) of the rudder side panel along the Z-
profile and in the booster area, in accordance with Airbus AOT 
A55W002-12, dated December 13, 2012, including Inspection Flowchart. 
If any damage is found, before further flight, do the inspections to 
confirm disbonding damage, as specified in paragraphs (h)(1)(i) and 
(h)(1)(ii) of this AD, in accordance with Airbus AOT A55W002-12, 
dated December 13, 2012.
    (i) Do an elasticity of laminate checker inspection to detect 
external and internal disbonding of the rudder side panel along the 
Z-profile and in the booster area.
    (ii) Do a woodpecker or tap test inspection to detect external 
disbonding of the rudder side panel along the Z-profile and in the 
booster area.
    (2) For airplanes on which it can be conclusively determined 
that the most recent inspection specified in Airbus Service Bulletin 
A310-55-2044 or Airbus Service Bulletin A300-55-6043 was done on the 
airplane; or the rudder was not removed for any reason since doing 
the most recent inspection specified in Airbus Service Bulletin 
A310-55-2044 or Airbus Service Bulletin A300-55-6043: No further 
action is required by this AD, except as specified in paragraphs (j) 
and (k) of this AD.

[[Page 19013]]

(i) Repair

    (1) If any disbonding is confirmed during any inspection 
required by paragraphs (h)(1)(i) and (h)(1)(ii) of this AD, before 
further flight, repair as specified in paragraphs (i)(1)(i) and 
(i)(1)(ii) of this AD, as applicable.
    (i) If disbonding is less than or equal to 50 millimeters (mm) 
in width and less than or equal to 150 mm in length, before further 
flight, vent the core, using a method approved by either the 
Manager, International Branch, ANM-116, Transport Airplane 
Directorate, FAA; or EASA; or Airbus's EASA DOA. Within 100 flight 
cycles after the UT inspection specified in paragraph (h) of this AD 
is done, repair using a method approved by the Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA; 
or EASA; or Airbus's EASA DOA.
    (ii) If disbonding is greater than 50 mm in width or greater 
than 150 mm in length, before further flight, repair using a method 
approved by the Manager, International Branch, ANM-116, Transport 
Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA.
    (2) If liquid ingress is confirmed during any inspection 
required by paragraphs (h)(1)(i) and (h)(1)(ii) of this AD, before 
further flight, repair using a method approved by the Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA; 
or EASA; or Airbus's EASA DOA.

(j) Inspection after Re-Installation

    If any rudder has been inspected as specified in Airbus Service 
Bulletin A300-55-6043, Revision 01, dated December 3, 2007; or A310-
55-2044, Revision 01, dated December 3, 2007; as applicable; and has 
been removed and re-installed on any airplane after this inspection, 
that rudder must be re-inspected as required by paragraph (g) of 
this AD; and all applicable actions required by paragraphs (h) and 
(i) of this AD must be done.

(k) Parts Installation Limitation

    As of the effective date of this AD, no person may install, on 
any airplane, a rudder assembly having a part number starting with 
A55471500, unless it has been inspected as required by paragraph (h) 
of this AD, and all applicable actions required by paragraph (i) of 
this AD have been done.

(l) 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. 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 EASA; or 
Airbus's EASA DOA. If approved by the DOA, the approval must include 
the DOA-authorized signature.

(m) Related Information

    Refer to Mandatory Continuing Airworthiness Information (MCAI) 
EASA Airworthiness Directive 2013-0039, dated February 26, 2013, for 
related information. This MCAI may be found in the AD docket on the 
Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2014-
0123-0002.

(n) 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 Alert Operators Transmission (AOT) A55W002-12, dated 
December 13, 2012, including Inspection Flowchart. The inspection 
flowchart attached to this AOT is referred to in the AOT as 
``Appendix 1''; however, the flowchart page does not identify itself 
as an appendix. While the inspection flowchart page does specify the 
AOT document number, it does not specify a revision level or an 
issue date.
    (ii) Reserved.
    (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 March 27, 2015.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-07799 Filed 4-8-15; 08:45 am]
 BILLING CODE 4910-13-P
Federal Register / Vol. 80, No. 68 / Thursday, April 9, 2015 / Rules and Regulations 19009

and forest land to voluntarily make that 7 CFR Part 622 PART 1455—VOLUNTARY PUBLIC
land available for access by the public ACCESS AND HABITAT INCENTIVE
for wildlife-dependent recreation, Watershed projects, Watershed PROGRAM
including hunting and fishing under protection, and Flood prevention.
programs administered by State and 7 CFR Part 624 ■ 3. The authority citation for part 1455
Tribal governments. VPA–HIP is not an continues to read as follows:
entitlement program and no grant will Disaster assistance, Floodplain Authority: 15 U.S.C. 714b and 714c; 16
be made unless the application is easement, Flooding, Imminent threat, U.S.C. 3839.
acceptable to CCC. The program was Natural disaster, and Watershed
impairment. ■ 4. Section 1455.2 is amended in
originally delegated to the paragraph (b) by adding a definition for
Administrator of FSA to administer on 7 CFR Part 625 ‘‘legal entity’’ and revising the
behalf of CCC. The program is now definition of ‘‘privately-held land’’ to
delegated to the Chief of NRCS, and Administrative practice and
read as follows:
NRCS incorporated the necessary procedure, Agriculture, and Soil
administrative changes in the interim conservation. § 1455.2 Definitions.
rule. NRCS announced its Availability 7 CFR Part 652 * * * * *
of Program Funding on May 1, 2014, to Legal entity means any entity created
implement VPA–HIP in fiscal year 2014. NRCS, Soil conservation, and under Federal or State law, excluding:
During its first round of grant proposals, Technical assistance. (a) a local, State or Federal government
NRCS received requests for funding 7 CFR Part 662 or political subdivision or agency of
from Indian Tribes which required such government; and (b) a Tribal
confirmation regarding whether Tribal Administrative practice and government.
lands would be considered private lands procedure, Agriculture, and Soil Privately-held land means farm,
for the purposes of VPA–HIP. This final conservation. ranch, or forest land that is owned or
rule clarifies that governmental and operated by a person or legal entity.
7 CFR Part 1455
Tribal lands are considered private * * * * *
lands for the purposes of VPA–HIP Agriculture, Animals, Environmental Signed this 1st day of April, 2015 in
when such lands are part of a private protection, Fishing, Forests and forest Washington, DC.
operation of a private individual or legal products, Grant programs, Hunting, Jason A. Weller,
entity. Indians, Indians-land, Natural Vice President, Commodity Credit
resources, Recreation and recreation Corporation, Chief, Natural Resources
Discussion of EWPP (7 CFR part 624): areas, Rural areas, State and local Conservation Service.
NRCS purchases floodplain easements governments, and Wildlife. [FR Doc. 2015–08008 Filed 4–8–15; 8:45 am]
to restore, protect, maintain, and
enhance the functions of the floodplain; 7 CFR Part 1465 BILLING CODE 3410–16–P

conserve natural values including fish
Conservation contract, Conservation
and wildlife habitat, water quality, flood plan, Conservation practices, and Soil
water retention, ground water recharge, DEPARTMENT OF TRANSPORTATION
and water conservation.
and open space; reduce long-term
Accordingly, the interim rule Federal Aviation Administration
Federal disaster assistance; and
safeguard lives and property from amending 7 CFR parts 610, 622, 625,
652, 662, 1455, and 1465 which was 14 CFR Part 39
floods, drought, and the products of
erosion. Section 382 of the Federal published at 79 FR 44635 on August 1, [Docket No. FAA–2014–0123; Directorate
Agriculture Improvement and Reform 2014, is adopted as a final rule with the Identifier 2013–NM–040–AD; Amendment
Act of 1996 amended EWPP, 16 U.S.C. following changes: 39–18134; AD 2015–07–06]
2203, to authorize the purchase of PART 624—EMERGENCY RIN 2120–AA64
floodplain easements (FPE) as an WATERSHED PROTECTION
emergency measure on lands that Airworthiness Directives; Airbus
qualify for EWPP assistance. EWPP Airplanes
■ 1. The authority citation for part 624
FPEs are administered under 7 CFR part continues to read as follows: AGENCY: Federal Aviation
624.
Authority: Sec. 216, Pub. L. 81–516, 33 Administration (FAA), Department of
Prior to the 2014 Act, the EWPP–FPE U.S.C. 701b–1; Sec. 403, Pub. L. 95–334, as Transportation (DOT).
statute did not address modification or amended, 16 U.S.C. 2203; 5 U.S.C. 301. ACTION: Final rule.
termination of FPEs; therefore the
regulations at 7 CFR part 624 specified ■ 2. Amend § 624.10 by revising SUMMARY: We are adopting a new
that FPEs could not be modified or paragraph (c) to read as follows: airworthiness directive (AD) for certain
terminated. Section 2206 of the 2014 § 624.10 Floodplain easements. Airbus Model A300 B4–601, B4–603,
Act provided such authority, and NRCS B4–620, B4–622, B4–605R, B4–622R,
* * * * *
is removing this prohibition from EWPP F4–605R, F4–622R, and C4–605R
regulations. (c) The Chief of NRCS may modify or Variant F airplanes; and Model A310–
terminate an easement if, pursuant to 16
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203, –204, –221, –222, –304, –322, –324,
List of Subjects U.S.C. 2203(b), the Chief determines the and –325 airplanes. This AD was
7 CFR Part 610 modification or termination is in the prompted by a report of inner skin
public interest and will address a disbonding damage on a rudder. This
Soil conservation, State Technical compelling public need for which there AD requires repetitive ultrasonic
Committees, Technical assistance, and is no practicable alternative. inspections for disbonding of certain
Water resources. * * * * * rudders; an elasticity of laminate

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checker inspection; a woodpecker or tap 2013 (referred to after this as the suggested revised language for a
test inspection; venting the core, if Mandatory Continuing Airworthiness requirement to determine if the rudder
necessary; and repairing, if necessary. Information, or ‘‘the MCAI’’), to correct has been removed or installed since the
We are issuing this AD to detect and an unsafe condition for certain Airbus last inspection.
correct rudder disbonding, which could Model A300 B4–601, B4–603, B4–620, In addition, FedEx requested that we
affect the structural integrity of the B4–622, B4–605R, B4–622R, F4–605R, revise paragraph (c) or (g) of the NPRM
rudder. F4–622R, and C4–605R Variant F (79 FR 11355, February 28, 2014) to
DATES: This AD becomes effective May airplanes; and Model A310–203, –204, state that, if the installed rudder has
14, 2015. –221, –222, –304, –322, –324, and –325 been inspected (and not removed) per
The Director of the Federal Register airplanes. The MCAI states: AD 2008–11–05, Amendment 39–15527
approved the incorporation by reference (73 FR 29423, May 21, 2008), since its
One A310 operator found substantial inner
of a certain publication listed in this AD skin disbonding damage on a rudder that was installation, no further inspection will
as of May 14, 2015. previously inspected in accordance with the be required since the unsafe condition
instructions of Airbus Service Bulletin (SB) would be alleviated.
ADDRESSES: You may examine the AD
A310–55–2044. The results of the subsequent UPS, FedEx, and Airbus requested
docket on the Internet at http:// investigation revealed that the most probable that we revise the NPRM (79 FR 11355,
www.regulations.gov/ cause of this damage was a blunt impact with February 28, 2014) to eliminate
#!docketDetail;D=FAA-2014-0123; or in no visible damage from outside during the unnecessary AD tracking requirements.
person at the Docket Management rudder handling. Damage like this might UPS noted that the identified risk only
Facility, U.S. Department of grow with pressure variation during ground-
exists in cases where the rudder has
Transportation, Docket Operations, air-ground cycles, and tests performed with
other rudders showed a rapid propagation of been changed since inspection under
M–30, West Building Ground Floor,
damage during artificial pressure cycling. AD 2008–11–05, Amendment 39–15527
Room W12–140, 1200 New Jersey
This condition, if not detected and (73 FR 29423, May 21, 2008). UPS
Avenue SE., Washington, DC.
corrected, could affect the structural integrity further stated that the NPRM does not
For service information identified in
of the rudder. refer to AD 2008–11–05, even though
this AD, contact Airbus SAS, To address this potential unsafe condition, the repetitive ultrasonic inspections to
Airworthiness Office—EAW, 1 Rond Airbus issued Alert Operators Transmission detect disbonding in the NPRM are
Point Maurice Bellonte, 31707 Blagnac (AOT) A55W002–12 [dated December 13, identical to the requirements of
Cedex, France; telephone +33 5 61 93 36 2012], pending Aircraft Maintenance Manual
paragraph (f)(2) of AD 2008–11–05.
96; fax +33 5 61 93 44 51; email (AMM) 27–21–21 PB401 revision to update
rudder handling procedures. Also, UPS stated that the airplane
account.airworth-eas@airbus.com;
For the reasons described above, this maintenance manual (AMM) has been
Internet http://www.airbus.com. You
[EASA] AD requires ultrasonic test (UT) updated as of June 1, 2013, to include
may view this referenced service
inspections of the affected rudders to detect the same ultrasonic inspection specified
information at the FAA, Transport signs of disbonding and, depending on in both AD 2008–11–05 and the NPRM.
Airplane Directorate, 1601 Lind Avenue findings, accomplishment of applicable UPS suggested revised wording for the
SW., Renton, WA. For information on corrective action(s). NPRM.
the availability of this material at the We concur with the requests to limit
Required actions also include an
FAA, call 425–227–1221. It is also the airplanes subject to the requirements
elasticity of laminate checker inspection
available on the Internet at http:// of paragraph (g) of this AD. This AD
to detect external and internal
www.regulations.gov by searching for does relate to AD 2008–11–05 (73 FR
disbonding, and a woodpecker or tap
and locating Docket No. FAA–2014– 29423, dated May 21, 2008), in that the
test inspection to detect external
0123. ultrasonic inspections are required in
disbonding. You may examine the
FOR FURTHER INFORMATION CONTACT: Dan MCAI in the AD docket on the Internet both ADs. This AD requires the
Rodina, Aerospace Engineer, at http://www.regulations.gov/ ultrasonic inspections for only certain
International Branch, ANM–116, #!documentDetail;D=FAA-2014-0123- airplanes. Therefore, we have added a
Transport Airplane Directorate, FAA, 0002. new paragraph (h)(2) in this AD.
1601 Lind Avenue SW., Renton, WA Paragraph (h)(2) of this AD specifies
98057–3356; telephone 425–227–2125; Comments that, for airplanes on which it can be
fax 425–227–1149. We gave the public the opportunity to conclusively determined that the most
SUPPLEMENTARY INFORMATION: participate in developing this AD. The recent inspection specified in Airbus
following presents the comments Service Bulletin A310–55–2044 or
Discussion received on the NPRM (79 FR 11355, Airbus Service Bulletin A300–55–6043
We issued a notice of proposed February 28, 2014) and the FAA’s was done on the airplane; or the rudder
rulemaking (NPRM) to amend 14 CFR response to each comment. was not removed for any reason since
part 39 by adding an AD that would doing the most recent inspection
apply to certain Airbus Model A300 B4– Requests To Exclude Certain Airplanes
From AD Requirements specified in Airbus Service Bulletin
601, B4–603, B4–620, B4–622, B4–605R, A310–55–2044 or Airbus Service
B4–622R, F4–605R, F4–622R, and C4– Airbus requested that we revise Bulletin A300–55–6043; no further
605R Variant F airplanes; and Model paragraph (g) of the NPRM (79 FR action is necessary, except as specified
A310–203, –204, –221, –222, –304, 11355, February 28, 2014) to mirror the in paragraphs (j) and (k) of this AD.
–322, –324, and –325 airplanes. The language in Airbus Alert Operators We have also re-designated
NPRM published in the Federal Transmission (AOT) A55W002–12, paragraphs (h), (h)(1), and (h)(2) of the
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Register on February 28, 2014 (79 FR dated December 13, 2012, which takes NPRM as paragraphs (h)(1), (h)(1)(i), and
11355). into account whether or not the rudder (h)(1)(ii) of this AD, respectively.
The European Aviation Safety Agency has been removed and/or installed since
(EASA), which is the Technical Agent the last inspection. Airbus stated that Request To Remove Requirement To
for the Member States of the European the removal/installation process is Refer to This AD in Repair Approvals
Union, has issued EASA Airworthiness linked to the risk of the unseen damage UPS requested that we revise the
Directive 2013–0039, dated February 26, occurring to the rudder. Airbus NPRM (79 FR 11355, February 28, 2014)

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to remove the requirement to include paragraph does not approve messages or provided U.S. operators with an
the AD reference in repair approvals. other information provided by the approved repair, developed with full
UPS noted its concerns that the NPRM manufacturer for deviations to the awareness of the unsafe condition,
will increase requests for approval of requirements of the AD-mandated before the FAA AD is issued. Under
alternative methods of compliance actions. The Airworthy Product these circumstances, to comply with the
(AMOCs) and result in delays to other paragraph only addresses the FAA AD, the operator would be
services and actions addressed by the requirement to contact the manufacturer required to go back to the
FAA on a daily basis. for corrective actions for the identified manufacturer’s DOA and obtain a new
We concur with the commenter’s unsafe condition and does not cover approval document, adding time and
request to remove from this AD the deviations from other AD requirements. expense to the compliance process with
requirement that repair approvals must However, deviations to AD-required no safety benefit.
specifically refer to this AD. Since late actions are addressed in 14 CFR 39.17, Based on these comments, we
2006, we have included a standard and anyone may request the approval removed the requirement from this AD
paragraph titled ‘‘Airworthy Product’’ in for an alternative method of compliance that the DAH-provided repair
all MCAI ADs in which the FAA to the AD-required actions using the specifically refer to this AD. Before
develops an AD based on a foreign procedures found in 14 CFR 39.19. adopting such a requirement in the
authority’s AD. The MCAI or referenced To address this misunderstanding and future, the FAA will coordinate with
service information in an FAA AD often misinterpretation of the Airworthy affected DAHs and verify they are
directs the owner/operator to contact Product paragraph, we have changed prepared to implement means to ensure
the manufacturer for corrective actions, that paragraph and retitled it
that their repair approvals consider the
such as a repair. Briefly, the Airworthy ‘‘Contacting the Manufacturer.’’ This
unsafe condition addressed in an AD.
Product paragraph allowed owners/ paragraph now clarifies that for any
Any such requirements will be adopted
operators to use corrective actions requirement in this AD to obtain
through the normal AD rulemaking
provided by the manufacturer if those corrective actions from a manufacturer,
process, including notice-and-comment
actions were FAA-approved. In the actions must be accomplished using
procedures, when appropriate.
addition, the paragraph stated that any a method approved by the FAA, EASA,
actions approved by the State of Design or Airbus’s EASA DOA. We have also decided not to include
Authority (or its delegated agent) are The Contacting the Manufacturer a generic reference to either the
considered to be FAA-approved. paragraph also clarifies that, if approved ‘‘delegated agent’’ or the ‘‘DAH with
In the NPRM (79 FR 11355, February by the DOA, the approval must include State of Design Authority design
28, 2014), we proposed to prevent the the DOA-authorized signature. The DOA organization approval,’’ but instead we
use of repairs that were not specifically signature indicates that the data and will provide the specific delegation
developed to correct the unsafe information contained in the document approval granted by the State of Design
condition, by requiring that the repair are EASA-approved, which is also FAA- Authority for the DAH.
approval provided by the State of approved. Messages and other Compliance Time Clarification
Design Authority or its delegated agent information provided by the
specifically refer to this FAA AD. This manufacturer that do not contain the In paragraph (g) of this AD, for
change was intended to clarify the DOA-authorized signature approval are airplanes on which the part number or
method of compliance and to provide not EASA-approved, unless EASA serial number cannot be determined, we
operators with better visibility of repairs directly approves the manufacturer’s have revised the compliance time of
that are specifically developed and message or other information. ‘‘before further flight’’ to ‘‘within 3
approved to correct the unsafe This clarification does not remove months after the effective date of this
condition. In addition, we proposed to flexibility afforded previously by the AD.’’ This clarification corresponds to
change the phrase ‘‘its delegated agent’’ Airworthy Product paragraph. the compliance time in the MCAI. We
to include ‘‘the Design Approval Holder Consistent with long-standing FAA have determined that extending the
(DAH) with a State of Design policy, such flexibility was never compliance time will provide an
Authority’s design organization intended for required actions. This is acceptable level of safety.
approval (DOA)’’ to refer to a DAH also consistent with the
authorized to approve required repairs recommendation of the AD Conclusion
for the AD. Implementation Aviation Rulemaking We reviewed the relevant data,
In its comments to the NPRM (79 FR Committee to increase flexibility in considered the comments received, and
11355, February 28, 2014), UPS stated complying with ADs by identifying determined that air safety and the
the following: ‘‘The proposed wording, those actions in manufacturers’ service public interest require adopting this AD
being specific to repairs, eliminates the instructions that are ‘‘Required for with the changes described previously
interpretation that Airbus messages or Compliance’’ with ADs. We continue to and minor editorial changes. We have
other approved EASA documents are work with manufacturers to implement determined that these minor changes:
acceptable for approving minor this recommendation. But once we
• Are consistent with the intent that
deviations (corrective actions) needed determine that an action is required, any
was proposed in the NPRM (79 FR
during accomplishment of a[n AD] deviation from the requirement must be
11355, February 28, 2014) for correcting
mandated Airbus service bulletin.’’ approved as an alternative method of
This comment has made the FAA the unsafe condition; and
compliance.
aware that some operators have Other commenters to another NPRM • Do not add any additional burden
upon the public than was already
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misunderstood or misinterpreted the having Directorate Identifier 2012–NM–
Airworthy Product paragraph to allow 101–AD (78 FR 78285, December 26, proposed in the NPRM (79 FR 11355,
the owner/operator to use messages 2013) pointed out that in many cases the February 28, 2014).
provided by the manufacturer as foreign manufacturer’s service bulletin We also determined that these
approval of deviations during the and the foreign authority’s MCAI may changes will not increase the economic
accomplishment of an AD-mandated have been issued some time before the burden on any operator or increase the
action. The Airworthy Product FAA AD. Therefore, the DOA may have scope of this AD.

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(i) Repair Avenue SW., Renton, WA 98057–3356; Issued in Renton, Washington, on March
(1) If any disbonding is confirmed during telephone 425–227–2125; fax 425–227–1149. 27, 2015.
any inspection required by paragraphs Information may be emailed to: 9-ANM-116- Michael Kaszycki,
(h)(1)(i) and (h)(1)(ii) of this AD, before AMOC-REQUESTS@faa.gov. Before using Acting Manager, Transport Airplane
further flight, repair as specified in any approved AMOC, notify your appropriate Directorate, Aircraft Certification Service.
paragraphs (i)(1)(i) and (i)(1)(ii) of this AD, as principal inspector, or lacking a principal [FR Doc. 2015–07799 Filed 4–8–15; 08:45 am]
applicable. inspector, the manager of the local flight BILLING CODE 4910–13–P
(i) If disbonding is less than or equal to 50 standards district office/certificate holding
millimeters (mm) in width and less than or
district office. The AMOC approval letter
equal to 150 mm in length, before further
flight, vent the core, using a method must specifically reference this AD. DEPARTMENT OF TRANSPORTATION
approved by either the Manager, (2) Contacting the Manufacturer: For any
International Branch, ANM–116, Transport requirement in this AD to obtain corrective Federal Aviation Administration
Airplane Directorate, FAA; or EASA; or actions from a manufacturer, the action must
Airbus’s EASA DOA. Within 100 flight cycles be accomplished using a method approved 14 CFR Part 39
after the UT inspection specified in by the Manager, International Branch, ANM–
paragraph (h) of this AD is done, repair using 116, Transport Airplane Directorate, FAA; or [Docket No. FAA–2014–0627; Directorate
a method approved by the Manager, Identifier 2013–NM–217–AD; Amendment
EASA; or Airbus’s EASA DOA. If approved
International Branch, ANM–116, Transport 39–18126; AD 2015–06–08]
by the DOA, the approval must include the
Airplane Directorate, FAA; or EASA; or RIN 2120–AA64
DOA-authorized signature.
Airbus’s EASA DOA.
(ii) If disbonding is greater than 50 mm in (m) Related Information Airworthiness Directives; Lockheed
width or greater than 150 mm in length,
before further flight, repair using a method Refer to Mandatory Continuing Martin Corporation/Lockheed Martin
approved by the Manager, International Airworthiness Information (MCAI) EASA Aeronautics Company Airplanes
Branch, ANM–116, Transport Airplane Airworthiness Directive 2013–0039, dated
February 26, 2013, for related information. AGENCY: Federal Aviation
Directorate, FAA; or EASA; or Airbus’s EASA
DOA. This MCAI may be found in the AD docket Administration (FAA), DOT.
(2) If liquid ingress is confirmed during on the Internet at http:// ACTION: Final rule.
any inspection required by paragraphs www.regulations.gov/
(h)(1)(i) and (h)(1)(ii) of this AD, before #!documentDetail;D=FAA-2014-0123-0002. SUMMARY: We are superseding
further flight, repair using a method Airworthiness Directive (AD) 2011–09–
approved by the Manager, International (n) Material Incorporated by Reference 03 for all Lockheed Martin Corporation/
Branch, ANM–116, Transport Airplane (1) The Director of the Federal Register Lockheed Martin Aeronautics Company
Directorate, FAA; or EASA; or Airbus’s EASA approved the incorporation by reference Model 382, 382B, 382E, 382F, and 382G
DOA. (IBR) of the service information listed in this airplanes. AD 2011–09–03 required
(j) Inspection after Re-Installation paragraph under 5 U.S.C. 552(a) and 1 CFR repetitive eddy current inspections to
If any rudder has been inspected as part 51. detect cracks in the center wing upper
specified in Airbus Service Bulletin A300– (2) You must use this service information and lower rainbow fittings, and
55–6043, Revision 01, dated December 3, as applicable to do the actions required by corrective actions if necessary; and
2007; or A310–55–2044, Revision 01, dated this AD, unless this AD specifies otherwise. repetitive replacement of rainbow
December 3, 2007; as applicable; and has (i) Airbus Alert Operators Transmission fittings, which would extend the
been removed and re-installed on any (AOT) A55W002–12, dated December 13, repetitive interval for the next
airplane after this inspection, that rudder 2012, including Inspection Flowchart. The inspection. This new AD requires
must be re-inspected as required by inspection flowchart attached to this AOT is reduced intervals for inspections of the
paragraph (g) of this AD; and all applicable referred to in the AOT as ‘‘Appendix 1’’;
actions required by paragraphs (h) and (i) of upper rainbow fittings. This AD was
however, the flowchart page does not prompted by analysis of in-service
this AD must be done.
identify itself as an appendix. While the cracking, which has shown that a
(k) Parts Installation Limitation inspection flowchart page does specify the reduction in the inspection intervals is
As of the effective date of this AD, no AOT document number, it does not specify necessary for the upper rainbow fittings.
person may install, on any airplane, a rudder a revision level or an issue date. We are issuing this AD to detect and
assembly having a part number starting with (ii) Reserved. correct fatigue cracking of the upper and
A55471500, unless it has been inspected as (3) For service information identified in lower rainbow fittings on the center
required by paragraph (h) of this AD, and all this AD, contact Airbus SAS, Airworthiness
applicable actions required by paragraph (i) wings, which could grow large and lead
Office—EAW, 1 Rond Point Maurice to the failure of the fitting and a
of this AD have been done. Bellonte, 31707 Blagnac Cedex, France; catastrophic failure of the center wing.
(l) Other FAA AD Provisions telephone +33 5 61 93 36 96; fax +33 5 61
DATES: This AD is effective May 14,
The following provisions also apply to this 93 44 51; email account.airworth-eas@
airbus.com; Internet http://www.airbus.com.
2015.
AD:
(4) You may view this service information The Director of the Federal Register
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International at the FAA, Transport Airplane Directorate, approved the incorporation by reference
Branch, ANM–116, Transport Airplane 1601 Lind Avenue SW., Renton, WA. For of a certain publication listed in this AD
Directorate, FAA, has the authority to information on the availability of this as of May 14, 2015.
approve AMOCs for this AD, if requested material at the FAA, call 425–227–1221. The Director of the Federal Register
using the procedures found in 14 CFR 39.19. (5) You may view this service information approved the incorporation by reference
In accordance with 14 CFR 39.19, send your of a certain other publication listed in
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that is incorporated by reference at the
request to your principal inspector or local this AD as of May 26, 2011 (76 FR
National Archives and Records
Flight Standards District Office, as 22311, April 21, 2011).
appropriate. If sending information directly Administration (NARA). For information on
to the International Branch, send it to ATTN: the availability of this material at NARA, call ADDRESSES: For service information
Dan Rodina, Aerospace Engineer, 202–741–6030, or go to: http:// identified in this AD, contact Lockheed
International Branch, ANM–116, Transport www.archives.gov/federal-register/cfr/ibr- Martin Corporation/Lockheed Martin
Airplane Directorate, FAA, 1601 Lind locations.html. Aeronautics Company, Airworthiness

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Document Created: 2015-12-18 11:23:23
Document Modified: 2015-12-18 11:23:23
Category		Regulatory Information
Collection		Federal Register
sudoc Class		AE 2.7: GS 4.107: AE 2.106:
Publisher		Office of the Federal Register, National Archives and Records Administration
Section		Rules and Regulations
Action		Final rule.
Dates		This AD becomes effective May 14, 2015.
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.
FR Citation		80 FR 19009
RIN Number		2120-AA64
CFR Associated		Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety
80 FR 19009 - Airworthiness Directives; Airbus Airplanes

DEPARTMENT OF TRANSPORTATIONFederal Aviation Administration

Federal Register Volume 80, Issue 68 (April 9, 2015)

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
