
[Federal Register Volume 80, Number 178 (Tuesday, September 15, 2015)]
[Rules and Regulations]
[Pages 55229-55232]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-22924]


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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; 
Amendment 39-18263; AD 2015-18-05]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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SUMMARY: We are superseding Airworthiness Directive (AD) 97-07-14, for 
certain Airbus Model A320-111, -211, and -231 airplanes. AD 97-07-14 
required modification of an area on the front spar of the wing center 
section by installing shims and new fasteners to reinforce pressure 
floor fittings. This new AD continues 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 requires 
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. This AD was prompted by 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. 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.

DATES: This AD becomes effective October 20, 2015.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of October 20, 
2015.
    The Director of the Federal Register approved the incorporation by 
reference

[[Page 55230]]

of a certain other publication listed in this AD as of May 12, 1997 (62 
FR 16473, April 7, 1997).

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2015-0926; or in person at the 
Docket Management Facility, U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC.
    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 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. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
0926.

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:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 97-07-14, Amendment 39-9988 (62 FR 16473, April 
7, 1997). AD 97-07-14 applied to certain Airbus Model A320-111, -211, 
and -231 airplanes. The NPRM published in the Federal Register on April 
24, 2015 (80 FR 22943).
    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 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 [F-19]95-098-066 [dated May 24, 1995, which 
corresponds to FAA AD 97-07-14, Amendment 39-9988 (62 FR 16473, 
April 7, 1997), http://ad.easa.europa.eu/ad/F-1995-098-066] 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 [F-19]95-098-066, [dated May 24, 
1995, which corresponds to FAA AD 97-07-14, Amendment 39-9988 (62 FR 
16473, April 7, 1997), http://ad.easa.europa.eu/ad/F-1995-098-066], 
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 manufacturer serial numbers up to 
MSN 0084 inclusive. We included paragraph (h) of this 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/#!documentDetail;D=FAA-2015-0926-0002.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM (80 FR 22943, April 24, 
2015) or on the determination of the cost to the public.

Conclusion

    We reviewed the available data and determined that air safety and 
the public interest require adopting this AD as proposed except for 
minor editorial changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM (80 FR 22943, April 24, 2015) for correcting the unsafe condition; 
and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (80 FR 22943, April 24, 2015).

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletin A320-57-1175, Revision 01, 
including Appendix 01, 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. 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 AD.

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

[[Page 55231]]

provide consistent judgment in AD compliance. The procedures and tests 
identified as Required for Compliance (RC) 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 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 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 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 were required by AD 97-07-14 is 
$1,681 per product.
    We also estimate that it will take about 45 work-hours per product 
to comply with the new basic requirements of this AD. The average labor 
rate is $85 per work-hour. Required parts will cost about $1,600 per 
product. Based on these figures, we estimate the cost of this 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: 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 AD will not have federalism implications 
under Executive Order 13132. This AD will 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 that this AD:
    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.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=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 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.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 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:

2015-18-05 Airbus: Amendment 39-18263. Docket No. FAA-2015-0926; 
Directorate Identifier 2014-NM-121-AD.

(a) Effective Date

    This AD becomes effective October 20, 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 numbers (MSN) 005 through 008 
inclusive, MSNs 010 through 014 inclusive, and MSNs 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) New Requirement of This AD: 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

[[Page 55232]]

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, 
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, 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) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (n)(5) and (n)(6) of this AD.

(n) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless this AD specifies otherwise.
    (3) The following service information was approved for IBR on 
October 20, 2015.
    (i) Airbus Service Bulletin A320-57-1175, Revision 01, including 
Appendix 01, dated May 28, 2014.
    (ii) Reserved.
    (4) The following service information was approved for IBR on 
May 12, 1997 (62 FR 16473, April 7, 1997).
    (i) Airbus Service Bulletin A320-57-1013, Revision 1, dated 
September 29, 1992.

    Note 1 to paragraph (n)(4)(i): Airbus Service Bulletin A320-57-
1013, Revision 1, dated September 29, 1992, contains the following 
list of effective pages: Pages 1 through 3 show revision level 1, 
dated September 29, 1992; pages 4 through 11 are from the original 
issue, dated April 12, 1989.

    (ii) Reserved.
    (5) 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.
    (6) 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.
    (7) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on September 2, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-22924 Filed 9-14-15; 8:45 am]
BILLING CODE 4910-13-P


