Document ID: FAA-2016-6671-0001
Agency: faa
Document Type: Proposed Rule
Title: Airworthiness Directives: Airbus Airplanes
Posted Date: 2016-05-23T04:00Z

[Federal Register Volume 81, Number 99 (Monday, May 23, 2016)]
[Proposed Rules]
[Pages 32256-32258]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-11681]

 ========================================================================
 Proposed Rules
                                                 Federal Register
 ________________________________________________________________________
 
 This section of the FEDERAL REGISTER contains notices to the public of 
 the proposed issuance of rules and regulations. The purpose of these 
 notices is to give interested persons an opportunity to participate in 
 the rule making prior to the adoption of the final rules.
 
 ========================================================================
 

  Federal Register / Vol. 81, No. 99 / Monday, May 23, 2016 / Proposed 
Rules  

[[Page 32256]]

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-6671; Directorate Identifier 2015-NM-164-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 
certain Airbus Model A300B4-203 and A300B4-2C airplanes. This proposed 
AD was prompted by cracks found on pylon side panels (upper section) at 
rib 8. This proposed AD would require a detailed inspection for crack 
indications of the pylon side panels, a high frequency eddy current 
(HFEC) inspection to confirm any crack indications, modification of the 
pylon side panels, and repetitive inspections and repair if necessary. 
We are proposing this AD to detect and correct cracking of the pylon 
side panels. Such cracking could result in pylon structural failure and 
in-flight loss of an engine.

DATES: We must receive comments on this proposed AD by July 7, 2016.

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: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this NPRM, 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-2016-
6671; 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 
Office (phone: 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 proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2016-6671; 
Directorate Identifier 2015-NM-164-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 because of 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 2015-0201, dated October 7, 2015 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for certain Airbus Model 
A300B4-203 and A300B4-2C airplanes. The MCAI states:

    Cracks were found on pylon side panels (upper section) at rib 8 
on Airbus A300, A310 and A300-600 aeroplanes equipped with General 
Electric engines. Investigation of these findings indicated that 
this problem was likely to also affect aeroplanes of this type 
design with other engine installations.
    This condition, if not detected and corrected, could lead to 
reduced strength of the pylon primary structure, possibly resulting 
in pylon structural failure and in-flight loss of an engine.
    Prompted by these findings, EASA issued AD 2008-0181 [which 
corresponded to FAA AD 2010-06-04, Amendment 39-16228 (75 FR 11428, 
March 11, 2010; corrected May 4, 2010 (75 FR 23572))] to require 
repetitive detailed visual inspections and, depending on aeroplane 
configuration and/or findings, the accomplishment of applicable 
corrective action(s).
    Since that [EASA] AD 2008-0181 was issued, a fleet survey and 
updated Fatigue and Damage Tolerance analyses have been performed in 
order to substantiate the second A300-600 Extended Service Goal 
(ESG2) exercise. The results of these analyses have shown that the 
risk for these aeroplanes is higher than initially determined and 
consequently, the threshold and interval were reduced to allow 
timely detection of these cracks and the accomplishment of 
applicable corrective action(s).
    Consequently, EASA AD 2013-0136 was published to supersede EASA 
AD 2008-0181 and to require the inspections to be accomplished 
within reduced thresholds and intervals. Afterwards, [EASA] AD 2013-
0136 was mistakenly revised [EASA AD 2013-0136R1 corresponds to FAA 
AD 2015-26-06, Amendment 39-18354 (81 FR January 14,2016)] to reduce 
the Applicability, because it was considered at the time that 
aeroplanes on which Airbus mod 03599 was embodied, were not 
concerned by the requirements of EASA AD 2013-0136.
    Since EASA AD 2013-0136R1 was issued, a more thorough analysis 
determined that post-mod 03599 aeroplanes could be affected by this 
unsafe condition after all.
    [During] further deeper review, a list of nineteen A300 
aeroplanes was identified as

[[Page 32257]]

missing in the [EASA] AD 2013-0136R1 applicability, (aeroplanes 
post-mod 03599).
    For the reasons described above this AD retains the requirements 
of EASA AD 2013-0136R1 and mandates these requirements for the 19 
missing A300 aeroplanes MSNs.

    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-2016-
6671.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletin A300-54-0075, Revision 04, dated 
May 26, 2015. The service information describes procedures for an 
inspection for crack indications of the pylons, a HFEC inspection to 
confirm cracking, modification of the pylon side panels, and repairs if 
cracks are found.
    Airbus has also issued Service Bulletin A300-54-0081, dated August 
11, 1993. This service information describes installation of a doubler 
on the left pylon 1 and right pylon 2, on pylon side panels (upper 
section) at Rib 8.
    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.

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 these 
same type designs.

Differences Between Proposed Rule and Service Bulletin

    Unlike the procedures described in Airbus Service Bulletin A300-54-
0075, Revision 04, dated May 26, 2015, this proposed AD would not 
permit further flight if cracks are detected in the pylon or pylon side 
panels. We have determined that because of the safety implications and 
consequences associated with that cracking, any cracked pylon or pylon 
side panel must be repaired or modified before further flight. This 
difference has been coordinated with EASA.

Costs of Compliance

    We estimate that this proposed AD affects 4 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
               Action                         Labor cost             Cost per product     Cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
Inspection of the pylon side panels  30 work-hours x $85 per      $2,550 per inspection   $10,200 per inspection
                                      hour = $2,550 per            cycle.                  cycle.
                                      inspection cycle.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary repairs that 
would be required based on the results of the proposed inspection. We 
have no way of determining the number of airplanes that might need this 
repair.

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
               Action                         Labor cost                Parts cost           Cost per product
----------------------------------------------------------------------------------------------------------------
Crack Repair.......................  56 work-hours x $85 per      $3,910 per repair.....  $8,670 per repair.
                                      hour = $4,760 per repair.
----------------------------------------------------------------------------------------------------------------

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-2016-6671; Directorate Identifier 2015-NM-
164-AD.

[[Page 32258]]

(a) Comments Due Date

    We must receive comments by July 7, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus Model A300B4-203 and A300B4-2C 
airplanes, certificated in any category, manufacturer serial numbers 
210, 212, 218, 220, 227, 234, 235, 236, 239, 247, 255, 256, 259, 
261, 274, 277, 292, 299, and 302.

(d) Subject

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

(e) Reason

    This AD was prompted by cracks found on pylon side panels (upper 
section) at rib 8. We are proposing this AD to detect and correct 
cracking of the pylon side panels. Such cracking could result in 
pylon structural failure and in-flight loss of an engine.

(f) Compliance

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

(g) Detailed Inspection of Pylons and Corrections

    At the applicable time specified in Airbus Service Bulletin 
A300-54-0075, Revision 04, dated May 26, 2015: Do a detailed 
inspection for crack indications of the pylons 1 and 2 side panels 
(upper section) at rib 8, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A300-54-0075, Revision 04, 
dated May 26, 2015.

(h) Crack Confirmation

    If any crack indication is found during the inspection required 
by paragraph (g) of this AD: Before further flight, do a high 
frequency eddy current (HFEC) inspection to confirm the crack, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A300-54-0075, Revision 04, dated May 26, 2015.

(i) Follow-On Actions for No Crack/Indication

    If the inspection required by paragraph (g) of this AD reveals 
no crack indication, or if the HFEC inspection specified by 
paragraph (h) of this AD confirms no crack: Do the actions specified 
in either paragraph (i)(1) or (i)(2) of this AD.
    (1) Repeat the inspection required by paragraph (g) of this AD 
at the applicable time specified in Airbus Service Bulletin A300-54-
0075, Revision 04, dated May 26, 2015.
    (2) At the applicable time specified in Airbus Service Bulletin 
A300-54-0081, dated August 11, 1993: Modify the pylons, in 
accordance with Airbus Service Bulletin 300-54-0081, dated August 
11, 1993. Thereafter, repeat the HFEC inspection specified in 
paragraph (h) of this AD at the applicable interval specified in 
Airbus Service Bulletin A300-54-0075, Revision 04, dated May 26, 
2015, and repair any crack before further flight 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).

(j) Follow-On Actions for Crack Findings

    If any crack is confirmed during the inspection required by 
paragraph (h) of this AD, repair before further flight using a 
method approved by the Manager, International Branch, ANM-116, 
Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA.

(k) Credit for Previous Actions

    This paragraph provides credit for actions required by 
paragraphs (g), (h), (i), and (j) of this AD, if those actions were 
performed before the effective date of this AD using the service 
information specified in paragraphs (k)(1) through (k)(4) of this 
AD.
    (1) Airbus Service Bulletin A300-54-0075, dated August 11, 1993, 
which was incorporated by referenced in AD 2010-06-04, Amendment 39-
16228 (75 FR 11428, March 11, 2010); corrected May 4, 2010 (75 FR 
23572).
    (2) Airbus Service Bulletin A300-54-0075, Revision 01, dated 
November 9, 2007, which is not incorporated by reference in this AD.
    (3) Airbus Service Bulletin A300-54-0075, Revision 02, dated 
June 26, 2008, which is not incorporated by reference in this AD.
    (4) Airbus Service Bulletin A300-54-0075, Revision 03, dated 
March 27, 2013, which is not incorporated by reference in this AD.

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

(m) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2015-0201, dated October 7, 
2015, 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-2016-6671.
    (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 May 11, 2016.
Suzanne Masterson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-11681 Filed 5-20-16; 8:45 am]
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