
[Federal Register Volume 80, Number 15 (Friday, January 23, 2015)]
[Proposed Rules]
[Pages 3525-3527]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2015-00946]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-1045; Directorate Identifier 2014-NM-031-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: We propose to adopt a new airworthiness directive (AD) for 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. 
This proposed 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 proposed AD 
would require an inspection for disbonding or damage of certain 
rudders, and related investigative actions and corrective actions if 
necessary. We are proposing 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: We must receive comments on this proposed AD by March 9, 2015.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact 
Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice Bellonte, 
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 
93 44 51; email account.airworth-eas@airbus.com; Internet http://www.airbus.com. You may view this referenced service information at the 
FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. 
For information on the availability of this material at the FAA, call 
425-227-1221.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2014-
1045; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this proposed AD, the regulatory evaluation, any comments 
received, and other information. The street address for the Docket 
Operations office (telephone 800-647-5527) is in the ADDRESSES section. 
Comments will be available in the AD docket shortly after receipt.

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

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2014-1045; 
Directorate Identifier 2014-NM-031-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD based on those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2014-0026, dated January 28, 2014 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for the specified 
products. 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.

[[Page 3526]]

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 by searching for and locating Docket No. FAA-2014-
1045.

Related Service Information

    Airbus has issued Service Bulletins A300-55-6050; and A310-55-2051; 
both Revision 01, 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.

FAA's Determination and Requirements of This Proposed AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI and service 
information referenced above. We are proposing this AD because we 
evaluated all pertinent information and determined an unsafe condition 
exists and is likely to exist or develop on other products of the same 
type design.

Difference Between This Proposed AD and the MCAI or Service Information

    Airbus Service Bulletins A300-55-6050; and A310-55-2051; both 
Revision 01, dated August 20, 2014; do not provide corrective action 
for certain conditions. This proposed AD would require repairing the 
damage 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).

Costs of Compliance

    We estimate that this proposed AD affects 199 airplanes of U.S. 
registry.
    We also estimate that it would take about 4 work-hours per product 
to comply with the basic requirements of this proposed 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 proposed 
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 proposed 
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 proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify this proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979);
    3. Will not affect intrastate aviation in Alaska; and
    4. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

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):

Airbus: Docket No. FAA-2014-1045; Directorate Identifier 2014-NM-
031-AD.

(a) Comments Due Date

    We must receive comments by March 9, 2015.

(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; A300 B4-605R and B4-622R airplanes; and 
A300 F4-605R and 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, 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, dated August 20, 2014; as applicable.
    (2) If the rudder maintenance records are unavailable or 
incomplete: Perform a rudder

[[Page 3527]]

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, 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, dated August 20, 2014; as applicable, except as required by 
paragraph (j)(2) 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, 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, 
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, 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 Airbus Service Bulletin A300-55-6050; or 
A310-55-2051; both Revision 01, dated August 20, 2014; as 
applicable, except as required by paragraph (j)(4) of this AD.

(i) Repair Using 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 dated September 11, 2012; 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 dated September 11, 2012; 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 on the composite 
side shell panel of that rudder since installation in accordance 
with the applicable structural repair manual (SRM).
    (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, 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 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 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 by searching for and locating 
Docket No. FAA-2014-1045.
    (2) 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 service 
information at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue SW., Renton, WA. For information on the availability of this 
material at the FAA, call 425-227-1221.

    Issued in Renton, Washington, on January 13, 2015.
John P. Piccola,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-00946 Filed 1-22-15; 8:45 am]
BILLING CODE 4910-13-P


