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[Federal Register Volume 81, Number 132 (Monday, July 11, 2016)]
[Proposed Rules]
[Pages 44812-44815]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-16210]

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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: Supplemental notice of proposed rulemaking (NPRM); reopening of 
comment period.

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SUMMARY: We are revising an earlier proposed airworthiness directive 
(AD) to supersede Airworthiness Directive (AD) 2010-04-03, for all 
Airbus Model A310 series airplanes. AD 2010-04-03 currently requires 
accomplishing repetitive detailed inspections for cracking around the 
fastener holes in certain wing top skin panels between the front and 
rear spars on the left- and right-hand sides of the fuselage, and 
repair if necessary. The NPRM proposed to continue to require the 
repetitive detailed inspections, and would also require supplemental 
repetitive ultrasonic inspections for cracking around the fastener 
holes in wing top skin panels 1 and 2 at rib 2, and repair if 
necessary. This action revises the NPRM by expanding the inspection 
area to include rib 3 due to widespread fatigue damage. We are 
proposing this supplemental NPRM (SNPRM) to detect and correct fatigue 
cracking around the fastener holes, which could result in reduced 
structural integrity of the airplane. Since these actions impose an 
additional burden over those proposed in the NPRM, we are reopening the 
comment period to allow the public the chance to comment on these 
proposed changes.

DATES: We must receive comments on this SNPRM by August 25, 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: 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 SNPRM, 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 
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.

[[Page 44813]]

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

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2010-04-03, Amendment 39-16196 (75 FR 6852, 
February 12, 2010) (``AD 2010-04-03''). AD 2010-04-03 applied to all 
Airbus Model A310 series airplanes. The NPRM published in the Federal 
Register on October 13, 2015 (80 FR 61327) (``the NPRM''). The NPRM was 
prompted by development of an ultrasonic inspection program to allow 
for earlier crack detection and extend the repetitive inspection 
intervals. The NPRM proposed to retain the requirements of AD 2010-04-
03, and proposed to require supplemental repetitive ultrasonic 
inspections for cracking around the fastener holes in wing top skin 
panels 1 and 2 at rib 2, and repair if necessary.
    Since we issued the NPRM, a widespread fatigue damage analysis 
determined that the inspection area should be expanded to include 
cracking around the fastener holes in wing top skin panels 1 and 2 
between the front and rear spar at rib 3.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2016-0005, dated January 7, 2016 (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] AD 
2008-0211 [http://ad.easa.europa.eu/ad/2008-0211, which corresponds 
to FAA AD 2010-04-03] to require implementation of this inspection 
programme.
    After 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.
    Consequently, EASA issued and AD 2014-0200 (later revised), 
superseding [EASA] AD 2008-0211, retaining its requirements, and to 
require 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].
    Since EASA AD 2014-0020R1 was issued, a widespread fatigue 
damage analysis concluded that the inspection programme has to be 
extended to include the wing top skin panels at Rib 3 attachments. 
For the reasons described above, this [EASA] AD retains the 
requirements of EASA AD 2014-0200R1, which is superseded, and 
extends the inspection area to include Rib 3.

    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 Service Bulletin A310-57-2096, Revision 03, dated 
June 30, 2015. This service information describes procedures for 
detailed and ultrasonic inspections for cracking around the fastener 
holes of wing top skin panels 1 and 2, at ribs 2 and 3, on the left- 
and right-hand sides of the fuselage. 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.

Comments

    We gave the public the opportunity to participate in developing 
this proposed AD. We considered the comment received. The commenter, 
FedEx, supported the content of the NPRM and is currently complying 
with the requirements.

FAA's Determination and Requirements of This SNPRM

    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.
    Certain changes described above expand the scope of the NPRM. As a 
result, we have determined that it is necessary to reopen the comment 
period to provide additional opportunity for the public to comment on 
this SNPRM.

Costs of Compliance

    We estimate that this SNPRM affects 28 airplanes of U.S. registry.
    We also estimate that it would take about 8 work-hours per product 
to comply with the basic requirements of this proposed AD. The average 
labor rate is $85 per work-hour. Based on these figures, we estimate 
the cost of this proposed AD on U.S. operators to be $19,040, or $680 
per product.
    We estimate that it would take about 15 work-hours per product to 
do any necessary on-condition actions that would be required based on 
the results of the inspections. Required parts would cost about $10,000 
per product. We have no way of determining the number of aircraft that 
might need these actions.

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.

[[Page 44814]]

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.

(a) Comments Due Date

    We must receive comments by August 25, 2016.

(b) Affected ADs

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

(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 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 fatigue cracking around the fastener holes in 
certain wing top skin panels between the front and rear spars on the 
left- and right-hand sides of the fuselage, 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 the 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) of this AD concurrently and in sequence, in accordance 
with the Accomplishment Instructions of Airbus Service Bulletin 
A310-57-2096, Revision 03, dated June 30, 2015, except as provided 
by paragraph (j) of this AD.
    (1) Accomplish a detailed inspection for cracking around the 
fastener holes in the wing top skin panels 1 and 2, along ribs 2 and 
3, between the front and rear spars on the left- and right-hand 
sides of the fuselage.
    (2) Accomplish an ultrasonic inspection for cracking around the 
fastener holes in the wing top skin panels 1 and 2, along ribs 2 and 
3, between stringer (STG) 2 and STG10 on the left- and right-hand 
sides 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 paragraphs (g)(1) and (g)(2) of this AD at the 
later of the times specified in paragraphs (h)(1)(i) and (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 paragraphs (g)(1) and (g)(2) of this AD at the later of 
the times specified in paragraphs (h)(2)(i) and (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 
paragraphs (g)(1) and (g)(2) of this AD at the later of the times 
specified in paragraphs (h)(3)(i) and (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 for 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; Airbus Service Bulletin A310-57-2096, Revision 01, dated 
August 5, 2010; or Airbus Service Bulletin A310-57-2096, Revision 
02, dated March 5, 2014: At the applicable compliance times 
specified in paragraphs (i)(1), (i)(2), and(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 03, 
dated June 30, 2015. Repeat the inspections specified in paragraphs 
(g)(1) and (g)(2) of this AD thereafter at the repetitive intervals 
specified in paragraphs (h)(1), (h)(2), and (h)(3) of this AD, as 
applicable.
    (1) For Model A310-203, -204, -221, and -222 airplanes: Do the 
actions required by paragraphs (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 paragraphs 
(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 
paragraphs (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), (i)(2), and (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), (h)(2), and (h)(3) of this 
AD.
    (1) For airplanes not previously inspected before the effective 
date of this AD using the

[[Page 44815]]

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 initial compliance time specified by 
paragraphs (h)(1), (h)(2), and (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), (i)(2), and (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 
paragraph (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). Accomplishing the repair 
specified in this paragraph terminates the repetitive inspections 
required by paragraph (h), (i), or (j) of this AD, as applicable, 
for the repaired area only.

(l) Definition of Average Flight Time (AFT)

    For the purposes of this AD, the AFT should be established as 
specified in paragraphs (l)(1), (l)(2), and (l)(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.
    (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 inspection 
threshold.

(m) Credit for Previous Actions

    This paragraph provides credit for the actions required by 
paragraph (g)(1) of this AD, if those actions were performed before 
the effective date of this AD using the applicable service 
information identified in paragraph (m)(1), (m)(2), or (m)(3) of 
this AD.
    (1) Airbus Service Bulletin A310-57-2096, dated May 6, 2008, 
which was incorporated by reference in AD 2010-04-03.
    (2) Airbus Service Bulletin A310-57-2096, Revision 01, dated 
August 5, 2010, which is not incorporated by reference in this AD.
    (3) Airbus Service Bulletin A310-57-2096, Revision 02, dated 
March 5, 2014, which is not incorporated by reference in this AD.

(n) 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): Except as required by 
paragraph (k) of this AD, 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 an airworthy condition. Any 
substitutions or changes to procedures or tests identified as RC 
require approval of an AMOC.

(o) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2016-0005, dated January 7, 
2016, 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 July 1, 2016.
Phillip Forde,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-16210 Filed 7-8-16; 8:45 am]
 BILLING CODE 4910-13-P
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