Document ID: FAA-2015-0926-0001
Agency: faa
Document Type: Proposed Rule
Title: Airworthiness Directives: Airbus Airplanes
Posted Date: 2015-04-24T04:00Z

[Federal Register Volume 80, Number 79 (Friday, April 24, 2015)]
[Proposed Rules]
[Pages 22943-22946]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-09549]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-0926; Directorate Identifier 2014-NM-121-AD]
RIN 2120-AA64

Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to supersede Airworthiness Directive (AD) 97-07-14, 
for certain Airbus Model A320-111, -211, and -231 airplanes. AD 97-07-
14 currently requires modification of an area on the front spar of the 
wing center section by installing shims and new fasteners to reinforce 
pressure floor fittings. Since we issued AD 97-07-14, we have 
determined the need for repetitive inspections on airplanes on which 
the modification of the rib flange on the front spar of the wing center 
section has been done. This proposed AD would continue to require 
modifying the rib flange on the front spar of the wing center section 
by installing shims and new fasteners to reinforce pressure floor 
fittings; and would require repetitive high frequency eddy current 
inspections for cracking of the radius of the rib flanges and vertical 
stiffener at frame 36, a rototest inspection for cracking of the 
fastener holes of the rib flanges, repair if needed, and adding 
additional airplanes to the applicability. We are proposing this AD to 
prevent fatigue cracking on the rib flange area of the front spar of 
the wing center section, which can reduce the structural integrity of 
fuselage frame 36 and the wing center section.

DATES: We must receive comments on this proposed AD by June 8, 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, Airworthiness Office--EIAS, 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-
0926; 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: Sanjay Ralhan, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405; 
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-2015-0926; 
Directorate Identifier 2014-NM-121-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 March 27, 1997, we issued AD 97-07-14, Amendment 39-9988 (62 FR 
16473, April 7, 1997). AD 97-07-14 requires modification of an area on 
the front spar of the wing center section by installing shims and new 
fasteners to reinforce pressure floor fittings on certain Airbus Model 
A320-111, -211 and -231 airplanes.
    Since we issued AD 97-07-14, Amendment 39-9988 (62 FR 16473, April 
7, 1997), we have determined the need for repetitive inspections on 
airplanes on which Airbus Modification 20976 (modification of the rib 
flange on the front spar of the wing center section) was done in 
production, or was done using Airbus Service Bulletin A320-57-1013, 
dated April 12, 1989; or Airbus Service Bulletin A320-57-1013, Revision 
1, dated September 29, 1992.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent

[[Page 22944]]

for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2014-0053, dated March 7, 2014 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition on certain Airbus Model 
A320-211 and -231 airplanes. The MCAI states:

    During full scale fatigue tests on the Airbus A320 test 
specimen, cracks were found in the rib flange on the front spar side 
perpendicular to vertical posts at frame (FR) 36. It was determined 
that similar cracks could develop on certain in-service aeroplanes.
    This condition, if not detected and corrected, could affect the 
wing structural integrity.
    To reduce the risk of crack initiation, two modifications for 
aeroplanes in production and one modification for in-service 
aeroplanes were developed by Airbus: Prior to [manufacturer serial 
number] MSN 0085, the adaptation modification (Mod) 20976 was 
applied in production, consisting in installing shims under the 
fasteners linking the rib flange, the lower corner, the front spar 
and its vertical stiffener; from MSN 0085 onwards, the serial Mod 
20908 was applied in production, consisting in installing reinforced 
lower surface rib flanges at front spar level.
    Airbus issued Service Bulletin (SB) A320-57-1013 for affected 
in-service aeroplanes, and [Directorate General for Civil Aviation] 
DGAC France issued AD 95-098-066 [which corresponds to FAA AD 97-07-
14, Amendment 39-9988, (62 FR 16473, April 7, 1997)] to require 
installation of shims under the fasteners linking the rib flange, 
the lower corner, the front spar and its vertical stiffener.
    Following a recent analysis, Airbus identified the need for 
repetitive [HFEC and rototest] inspections for aeroplanes on which 
Airbus SB A320-57-1013 or production Mod 20976 has been embodied.
    For the reason described above, this [EASA] AD retains the 
requirements of DGAC France AD 95-098-066, which is superseded, and 
requires repetitive [HFEC and rototest] inspections of the center 
wing lower ribs at FR 36 and, depending on findings, accomplishment 
of a repair.
    After EASA issued PAD 14-013, it was discovered that additional 
work [removal of shims and fasteners on the rib flange on the front 
spar side and doing an HFEC inspection for cracking of the radius of 
the rib flanges and a rototest inspection for cracking of the 
fastener holes during each inspection] to be included in Revision 01 
of Airbus SB A320-57-1175, is required to accomplish the 
inspections. This Final [EASA] AD has been amended accordingly.

    Airplanes having MSNs 001, 009, and 015 were not included in the 
applicability of AD 97-07-14, Amendment 39-9988 (62 FR 16473, April 7, 
1997). EASA AD 2014-0053, dated March 7, 2014, expanded the 
applicability to all airplanes having up to MSN 0084. We included 
paragraph (h) of this proposed AD to require the modification for the 
airplanes having MSNs 001, 009, and 015.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-2015-0926.

Related Service Information Under 1 CFR part 51

    Airbus has issued Service Bulletin A320-57-1175, Revision 01, 
including Appendix 01 and Appendix 02, dated May 28, 2014. The service 
information describes procedures for repetitive high frequency eddy 
current inspections for cracking of the radius of the rib flanges and 
vertical stiffener at frame 36, a rototest inspection for cracking of 
the fastener holes of the rib flanges, and repair. The actions 
described in this service information are intended to correct the 
unsafe condition identified in the MCAI. This service information is 
reasonably available; see ADDRESSES for ways to access this service 
information.

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

    The FAA worked in conjunction with industry, under the 
Airworthiness Directives Implementation Aviation Rulemaking Committee 
(AD 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 
actions specified in the service information identified previously 
include procedures and tests that are identified as RC (required for 
compliance) because these procedures 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 identified as RC 
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.

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.

Differences Between the AD and the MCAI or Service Information

    Although Airbus Service Bulletin A320-57-1175, Revision 01, 
including Appendix 01 and Appendix 02, dated May 28, 2014, specifies to 
contact the manufacturer for instructions on how to repair certain 
conditions, this proposed AD would require repairing those conditions 
using a method approved by the Manager, International Branch, ANM-116, 
Transport Airplane Directorate, FAA; or EASA or its delegated agent, or 
Airbus' EASA Design Organization Approval (DOA).

Costs of Compliance

    We estimate that this proposed AD affects 11 airplanes of U.S. 
registry.
    The actions required by AD 97-07-14, Amendment 39-9988 (62 FR 
16473, April 7, 1997), and retained in this proposed AD take about 13 
work-hours per product, at an average labor rate of $85 per work-hour. 
Required parts cost about $576 per product. Based on these figures, the 
estimated cost of the actions that are required by AD 97-07-14 is 
$1,681 per product.
    We also estimate that it would take about 45 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 $1,600 
per product. Based on these figures, we estimate the cost of this 
proposed AD on U.S. operators to be $59,675, or $5,425 per product.

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:

[[Page 22945]]

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) 
97-07-14, Amendment 39-9988 (62 FR 16473, April 7, 1997), and adding 
the following new AD:

Airbus: Docket No. FAA-2015-0926; Directorate Identifier 2014-NM-
121-AD.

(a) Comments Due Date

    We must receive comments by June 8, 2015.

(b) Affected ADs

    This AD replaces AD 97-07-14, Amendment 39-9988 (62 FR 16473, 
April 7, 1997).

(c) Applicability

    This AD applies to Airbus Model A320-211 and -231 airplanes, 
certificated in any category, all manufacturer serial numbers (MSN) 
up to MSN 0084 inclusive.

(d) Subject

    Air Transport Association (ATA) of America Code 57, Wings.

(e) Reason

    This AD was prompted by the determination that repetitive 
inspections are needed on airplanes on which the modification of the 
rib flange on the front spar of the wing center section has been 
done. We are issuing this AD to prevent fatigue cracking on the rib 
flange area of the front spar of the wing center section, which can 
reduce the structural integrity of fuselage frame 36 and the wing 
center section.

(f) Compliance

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

(g) Retained Modification

    This paragraph restates the requirements of paragraph (a) of AD 
97-07-14, Amendment 39-9988 (62 FR 16473, April 7, 1997). For 
airplanes with manufacturer serial number (MSN) 005 through 008 
inclusive, MSN 010 through 014 inclusive, and MSN 016 through 042 
inclusive: Prior to the accumulation of 16,000 total landings, or 
within 3 months after May 12, 1997 (the effective date of AD 97-07-
14), whichever occurs later, modify the rib flange on the front spar 
of the wing center section by installing shims and new fasteners to 
reinforce pressure floor fittings, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A320-57-1013, 
Revision 1, dated September 29, 1992.

(h) Modification for Airplanes With MSNs 001, 009, and 015

    Prior to the accumulation of 16,000 total landings since first 
flight, or within 30 days after the effective date of this AD, 
whichever occurs later, modify the rib flange on the front spar of 
the wing center section by installing shims and new fasteners to 
reinforce pressure floor fittings, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A320-57-1013, 
Revision 1, dated September 29, 1992.

(i) New Requirement of This AD: Repetitive Inspections

    Within the applicable compliance times specified in paragraphs 
(i)(1) and (i)(2) of this AD, do a high frequency eddy current 
(HFEC) inspection for cracking of the radius of the rib flanges and 
vertical stiffener at frame 36 and do a rototest inspection for 
cracking of the fastener holes of the rib flanges and vertical 
stiffener, in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A320-57-1175, Revision 01, including 
Appendix 01, dated May 28, 2014. During each inspection, remove the 
shims and fasteners on the rib flange on the front spar side and do 
an HFEC inspection for cracking of the radius of the rib flanges and 
a rototest inspection for cracking of the fastener holes. If no 
cracking is found, oversize the holes of the rib flange and the 
holes of the shims, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A320-57-1175, Revision 01, 
including Appendix 01, dated May 28, 2014. Repeat the inspections 
thereafter at intervals not to exceed 32,500 flight cycles or 65,000 
flight hours, whichever occurs first.
    (1) For airplanes having Airbus Modification 20976 embodied: At 
the later of the times specified in paragraphs (i)(1)(i) or 
(i)(1)(ii) of this AD.
    (i) Before exceeding 47,800 flight cycles or 95,600 flight 
hours, whichever occurs first, since the airplane's first flight.
    (ii) Within 850 flight cycles or 1,700 flight hours, whichever 
occurs first, after the effective date of this AD.
    (2) For airplanes on which the modification of the front spar of 
the wing center section was accomplished using Airbus Service 
Bulletin A320-57-1013, Revision 1, dated September 29, 1992: At the 
later of the times specified in paragraphs (i)(2)(i) or (i)(2)(ii) 
of this AD.
    (i) Before exceeding 10,700 flight cycles or 21,500 flight 
hours, whichever occurs first, after the modification of the rib 
flange on the front spar of the wing center section was done using 
Airbus Service Bulletin A320-57-1013, Revision 1, dated September 
29, 1992.
    (ii) Within 850 flight cycles or 1,700 flight hours, whichever 
occurs first, after the effective date of this AD.

(j) Repair

    If, during any inspection required by paragraph (i) of this AD, 
any cracking is found, 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).

(k) Credit for Previous Actions

    This paragraph restates the requirements of Note 2 of paragraph 
(g) of AD 97-07-14, Amendment 39-9988 (62 FR 16473, April 7, 1997): 
This paragraph provides credit for the modification of the rib 
flange required by paragraph (g) of this AD, if those actions were 
performed before May 12, 1997 (the effective date of AD 97-07-14) 
using Airbus Service Bulletin A320-57-1013, dated April 12, 1989.

(l) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International

[[Page 22946]]

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: Sanjay 
Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone 425-227-1405; 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 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 (j) of this AD, if the 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 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 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.

(m) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2014-0053, dated March 7, 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-2015-0926.
    (2) For service information identified in this AD, contact 
Airbus, Airworthiness Office--EIAS, 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 April 6, 2015.
John P. Piccola, Jr.,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-09549 Filed 4-23-15; 8:45 am]
 BILLING CODE 4910-13-P