
[Federal Register Volume 80, Number 197 (Tuesday, October 13, 2015)]
[Proposed Rules]
[Pages 61327-61330]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-25758]


 ========================================================================
 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. 80, No. 197 / Tuesday, October 13, 2015 / 
Proposed Rules  

[[Page 61327]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-3985; Directorate Identifier 2014-NM-182-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to supersede Airworthiness Directive (AD) 2010-04-
03, for all Airbus Model A310 series airplanes. AD 2010-04-03 currently 
requires accomplishing repetitive detailed visual inspections for 
cracking around the fastener holes in certain wing top skin panels 
between the right side and left side of the front and rear spars, and 
repair if needed. Since we issued AD 2010-04-03, Airbus improved the 
ultrasonic inspection program to allow earlier crack detection and to 
extend the repetitive inspection intervals. We have determined these 
inspections are necessary to address the unsafe condition. This 
proposed AD would continue to require the repetitive detailed 
inspections for cracking around the fastener holes in certain wing top 
skin panels between the front and rear spars, and repair if needed, and 
would require supplemental repetitive ultrasonic inspections for 
cracking around the fastener holes in certain wing top skin panels and 
repair if needed. We are proposing this AD to detect and correct 
cracking around the fastener holes in certain wing top skin panels 
between the right side and left side of the front and rear spars, which 
could result in reduced structural integrity of the airplane.

DATES: We must receive comments on this proposed AD by November 27, 
2015.

ADDRESSES: You may send comments 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-2015-
3985; 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-2015-3985; 
Directorate Identifier 2014-NM-182-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

    On January 28, 2010, we issued AD 2010-04-03, Amendment 39-16196 
(75 FR 6852, February 12, 2010). AD 2010-04-03 requires actions 
intended to address an unsafe condition on all Airbus Model A310 series 
airplanes.
    Since we issued AD 2010-04-03, Amendment 39-16196 (75 FR 6852, 
February 12, 2010), the manufacturer improved the ultrasonic inspection 
program to allow earlier crack detection and to extend the repetitive 
inspection intervals. We have determined these inspections are 
necessary to address the unsafe condition.
    The European Aviation Safety Agency, which is the Technical Agent 
for the Member States of the European Community, has issued EASA 
Airworthiness Directive 2014-0200R1, dated September 19, 2014 (referred 
to after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition on all Airbus Model A310 
series airplanes. The MCAI states:

    Following scheduled maintenance, cracks were found around the 
wing top skin panels fastener holes at Rib 2, between Stringer (STG) 
2 and STG14.
    This condition, if not detected and corrected, could affect the 
structural integrity of the aeroplane. The General Visual Inspection 
required by the existing applicable Airworthiness Limitation Items 
(ALI) tasks may not be adequate to detect these cracks.
    To address this issue, Airbus developed an inspection programme 
based on repetitive detailed inspections (DET) to ensure that any 
visible cracks in the wing top skin panels 1 and 2 along Rib 2 are 
detected in time and repaired appropriately. EASA issued [EASA]

[[Page 61328]]

AD 2008-0211 [http://ad.easa.europa.eu/ad/2008-0211] to require 
implementation of this inspection programme.
    Since that [EASA] AD was issued, Airbus improved the inspection 
programme with an ultrasonic inspection to allow earlier crack 
detection, to subsequently reduce the scope of potential repair 
action, and to extend the intervals of the repetitive inspections.
    For the reasons described above, this [EASA] AD [http://ad.easa.europa.eu/ad/2014-0200R1] retains the requirements of EASA 
AD 2008-0211, which is superseded, and requires supplementary 
repetitive ultrasonic inspections [for cracking] of the wing top 
skin panel 1 and 2 between STG2 and STG10 at Rib 2 [and repair if 
needed].
* * * * *

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-2015-
3985.

Related Service Information Under 1 CFR Part 51

    Airbus has issued the following service information:
     Airbus Service Bulletin A310-57-2096, dated May 6, 2008,
     Airbus Service Bulletin A310-57-2096, Revision 01, dated 
August 5, 2010.
     Airbus Service Bulletin A310-57-2096, Revision 02, dated 
March 5, 2014.

This service information describes procedures for detailed visual and 
ultrasonic inspections for cracking around the fastener holes of the 
wing top skin panels between the right side and left side of the front 
and rear spars at certain locations, and repair if needed. 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 of this NPRM.

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.

Explanation of ``RC'' Procedures and Tests in Service Information

    The FAA worked in conjunction with industry, under the 
Airworthiness Directive Implementation Aviation Rulemaking Committee 
(ARC), to enhance the AD system. One enhancement was a new process for 
annotating which procedures and tests in the service information are 
required for compliance with an AD. Differentiating these procedures 
and tests from other tasks in the service information is expected to 
improve an owner's/operator's understanding of crucial AD requirements 
and help provide consistent judgment in AD compliance. The procedures 
and tests identified as RC (required for compliance) in any service 
information have a direct effect on detecting, preventing, resolving, 
or eliminating an identified unsafe condition.
    As specified in a NOTE under the Accomplishment Instructions of the 
specified service information, procedures and tests that are identified 
as RC in any service information must be done to comply with the 
proposed AD. However, procedures and tests that are not identified as 
RC are recommended. Those procedures and tests that are not identified 
as RC may be deviated from using accepted methods in accordance with 
the operator's maintenance or inspection program without obtaining 
approval of an alternative method of compliance (AMOC), provided the 
procedures and tests identified as RC can be done and the airplane can 
be put back in a serviceable condition. Any substitutions or changes to 
procedures or tests identified as RC will require approval of an AMOC.

Costs of Compliance

    We estimate that this proposed AD affects 13 airplanes of U.S. 
registry.
    We also estimate that it would take about 5 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 $0 per 
product. Based on these figures, we estimate the cost of this proposed 
AD on U.S. operators to be $5,525, or $425 per product.
    We have received no definitive data that would enable us to provide 
cost estimates 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 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 removing Airworthiness Directive (AD) 
2010-04-03, Amendment 39-16196 (75 FR 6852, February 12, 2010), and 
adding the following new AD:

Airbus: Docket No. FAA-2015-3985; Directorate Identifier 2014-NM-
182-AD.

[[Page 61329]]

(a) Comments Due Date

    We must receive comments by November 27, 2015.

(b) Affected ADs

    This AD replaces AD 2010-04-03, Amendment 39-16196 (75 FR 6852, 
February 12, 2010).

(c) Applicability

    This AD applies to all 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 57, Wings.

(e) Reason

    This AD was prompted by cracking around the fastener holes in 
certain wing top skin panels between the right side and left side of 
the front and rear spars. This AD was also prompted by the 
development of an ultrasonic inspection program to allow for earlier 
crack detection and extend the repetitive inspection intervals. We 
are issuing this AD to detect and correct cracking around the 
fastener holes in certain wing top skin panels between the right 
side and left side of the front and rear spars, which could result 
in reduced structural integrity of the airplane.

(f) Compliance

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

(g) Repetitive Inspections

    Except as required by paragraph (i) of this AD: Within the 
initial compliance time and thereafter at repetitive intervals 
specified in paragraphs (h)(1) through (h)(3) of this AD, as 
applicable, accomplish the actions specified in paragraphs (g)(1) 
and (g)(2) concurrently and in sequence, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A310-57-2096, 
Revision 02, dated March 5, 2014, except as provided by paragraph 
(j) of this AD.
    (1) Accomplish a detailed inspection for cracking around 
fastener holes in the wing top skin panels 1 and 2, along rib 2 
between the front and rear spars on both the left-side and right-
side of the fuselage.
    (2) Accomplish an ultrasonic inspection for cracking around 
fastener holes in the wing top skin panels 1 and 2, along rib 2, 
between stringer 2 and stringer 10 on the left-side and right-side 
of the fuselage.

(h) Compliance Times for Airplanes Not Previously Inspected

    (1) For Model A310-203, -204, -221, and -222 airplanes: Do the 
actions required by paragraph (g)(1) and (g)(2) of this AD at the 
later of the times specified in paragraph (h)(1)(i) or (h)(1)(ii) of 
this AD. Repeat the inspections specified in paragraphs (g)(1) and 
(g)(2) of this AD thereafter at intervals not to exceed 2,000 flight 
cycles or 4,100 flight hours, whichever occurs first.
    (i) Prior to the accumulation of 18,700 flight cycles or 37,400 
flight hours since first flight of the airplane, whichever occurs 
first.
    (ii) Within 30 days after the effective date of this AD.
    (2) For Model A310-304, -322, -324, and -325 airplanes having an 
average flight time (AFT) of less than 4 hours: Do the actions 
required by paragraph (g)(1) and (g)(2) of this AD at the later of 
the times specified in paragraph (h)(2)(i) or (h)(2)(ii) of this AD. 
Repeat the inspections specified in paragraphs (g)(1) and (g)(2) of 
this AD thereafter at intervals not to exceed 2,000 flight cycles or 
5,600 flight hours, whichever occurs first.
    (i) Prior to the accumulation of 17,300 flight cycles or 48,400 
flight hours since first flight of the airplane, whichever occurs 
first.
    (ii) Within 30 days after the effective date of this AD.
    (3) For Model A310-304, -322, -324, and -325 airplanes having an 
AFT of equal to or more than 4 hours: Do the actions required by 
paragraph (g)(1) and (g)(2) of this AD at the later of the times 
specified in paragraph (h)(3)(i) or (h)(3)(ii) of this AD. Repeat 
the inspections specified in paragraphs (g)(1) and (g)(2) of this AD 
thereafter at intervals not to exceed 1,500 flight cycles or 7,500 
flight hours, whichever occurs first.
    (i) Prior to the accumulation of 12,800 flight cycles or 64,300 
flight hours since first flight of the airplane, whichever occurs 
first.
    (ii) Within 30 days after the effective date of this AD.

(i) Compliance Times of Airplanes Previously Inspected

    For airplanes previously inspected before the effective date of 
this AD using Airbus Service Bulletin A310-57-2096, dated May 6, 
2008; or Airbus Service Bulletin A310-57-2096, Revision 01, dated 
August 5, 2010: At the applicable compliance times specified in 
paragraphs (i)(1) through (i)(3) of this AD, accomplish the actions 
specified in paragraphs (g)(1) and (g)(2) concurrently and in 
sequence, in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A310-57-2096, Revision 02, dated March 5, 
2014. Repeat the inspections specified in paragraphs (g)(1) and 
(g)(2) of this AD, thereafter at the repetitive intervals specified 
in paragraphs (h)(1) through (h)(3) of this AD, as applicable.
    (1) For Model A310-203, -204, -221, and -222 airplanes: Do the 
actions required by paragraph (g)(1) and (g)(2) of this AD within 
3,500 flight hours or 1,700 flight cycles, whichever occurs first 
since the most recent inspection.
    (2) For Model A310-304, -322, -324, and -325 airplanes having an 
AFT of less than 4 hours: Do the actions required by paragraph 
(g)(1) and (g)(2) of this AD within 4,600 flight hours or 1,600 
flight cycles, whichever occurs first since the most recent 
inspection.
    (3) For Model A310-304, -322, -324, and -325 airplanes having an 
AFT of equal to or more than 4 hours: Do the actions required by 
paragraph (g)(1) and (g)(2) of this AD within 6,100 flight hours or 
1,200 flight cycles, whichever occurs first since the most recent 
inspection.

(j) Compliance Times if No Ultrasonic Equipment Is Available

    If no ultrasonic equipment is available for the initial or 
second inspection required by paragraph (g) or (h) of this AD, 
accomplish the detailed inspection specified in paragraph (g)(1) of 
this AD, within the applicable compliance times specified in 
paragraphs (j)(1) and (j)(2) of this AD. After accomplishing the 
detailed inspection, do the inspections specified in paragraphs 
(g)(1) and (g)(2) of this AD at the applicable compliance times 
specified by paragraphs (i)(1) through (i)(3) of this AD. 
Subsequently, repeat the inspections specified in paragraphs (g)(1) 
and (g)(2) of this AD thereafter at the applicable repetitive 
intervals specified in paragraphs (h)(1) through (h)(3) of this AD.
    (1) For airplanes not previously inspected before the effective 
date of this AD: Do the actions required by paragraph (g)(1) of this 
AD within the initial compliance time specified by paragraphs (h)(1) 
through (h)(3) of this AD, as applicable.
    (2) For airplanes previously inspected before the effective date 
of this AD using the service information identified in paragraph 
(j)(2)(i), (j)(2)(ii), or (j)(2)(iii) of this AD: Do the actions 
required by paragraph (g)(1) of this AD within the applicable 
compliance times specified in paragraphs (i)(1) through (i)(3) of 
this AD.
    (i) Airbus Service Bulletin A310-57-2096, dated May 6, 2008.
    (ii) Airbus Service Bulletin A310-57-2096, Revision 01, dated 
August 5, 2010.
    (iii) Airbus Service Bulletin A310-57-2096, Revision 02, dated 
March 5, 2014.

(k) Repair of Cracking

    If any cracking is found during any inspection required by 
paragraphs (g), (h), (i), or (j) of this AD, before further flight, 
repair the cracking 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).

(l) Terminating Action for Certain Repetitive Inspections

    Accomplishment of a repair using the service information 
identified in paragraph (l)(1), (l)(2), or (l)(3) of this AD, 
constitutes terminating action for the requirements of paragraph (g) 
of this AD, only for the repaired areas of the airplane.
    (1) Airbus Service Bulletin A310-57-2096, dated May 6, 2008.
    (2) Airbus Service Bulletin A310-57-2096, Revision 01, dated 
August 5, 2010.
    (3) Airbus Service Bulletin A310-57-2096, Revision 02, dated 
March 5, 2014.

(m) Definition of Average Flight Time (AFT)

    For the purposes of this AD, the AFT should be established as 
specified in paragraphs (m)(1), (m)(2), and (m)(3) of this AD for 
the determination of the compliance times.
    (1) The inspection threshold is defined as the total flight 
hours accumulated (counted from take-off to touch-down), divided by 
the total number of flight cycles accumulated at the effective date 
of this AD.
    (2) The initial inspection interval is defined as the total 
flight hours accumulated divided by the total number of flight 
cycles accumulated at the time of the initial inspection threshold.

[[Page 61330]]

    (3) The second inspection interval is defined as the total 
flight hours accumulated divided by the total number of flight 
cycles accumulated between the initial and second threshold.

(n) Credit for Previous Actions

    This paragraph provides credit for actions required by paragraph 
(g)(1) of this AD, if those actions were performed before the 
effective date of this AD using Airbus Service Bulletin A310-57-
2096, dated May 6, 2008; or Airbus Service Bulletin A310-57-2096, 
Revision 01, dated August 5, 2010.

(o) 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: As of the effective date of 
this AD, 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.
    (3) Required for Compliance (RC): If any service information 
contains procedures or tests that are identified as RC, those 
procedures and tests must be done to comply with this AD; any 
procedures or tests that are not identified as RC are recommended. 
Those procedures and tests that are not identified as RC may be 
deviated from using accepted methods in accordance with the 
operator's maintenance or inspection program without obtaining 
approval of an AMOC, provided the procedures and tests identified as 
RC can be done and the airplane can be put back in a serviceable 
condition. Any substitutions or changes to procedures or tests 
identified as RC require approval of an AMOC.

(p) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2014-0200R1, dated September 19, 
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-2015-3985.
    (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 September 28, 2015.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-25758 Filed 10-9-15; 8:45 am]
 BILLING CODE 4910-13-P


