Document ID: FAA-2015-5811-0004
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Airbus Airplanes
Posted Date: 2016-05-04T04:00Z

[Federal Register Volume 81, Number 86 (Wednesday, May 4, 2016)]
[Rules and Regulations]
[Pages 26677-26680]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-08956]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-5811; Directorate Identifier 2014-NM-158-AD; 
Amendment 39-18489; AD 2016-08-13]
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) 2004-19-11 for 
certain Airbus Model A320 series airplanes. AD 2004-19-11 required 
modification of the inner rear spar web of the wing, cold expansion of 
the attachment holes of the forward pintle fitting and the actuating 
cylinder anchorage of the main landing gear (MLG), repetitive 
ultrasonic inspections for cracking of the rear spar of the wing, and 
corrective action if necessary. AD 2004-19-11 also provided optional 
terminating action for the repetitive inspections. This new AD retains 
the requirements of AD 2004-19-11, and requires the previously optional 
terminating action. This AD was prompted by a determination that the 
previously optional terminating action is necessary to address the 
unsafe condition. We are issuing this AD to prevent fatigue cracking of 
the inner rear spar, which may lead to reduced structural integrity of 
the wing and the MLG.

DATES: This AD becomes effective June 8, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of June 8, 
2016.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of November 5, 
2004 (69 FR 58828, October 1, 2004).
    The Director of the Federal Register approved the incorporation by 
reference of certain other publications listed in this AD as of June 
30, 2000 (65 FR 34069, May 26, 2000).
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of February 14, 
1994 (59 FR 1903, January 13, 1994).
    The Director of the Federal Register approved the incorporation by 
reference of a certain other publication listed in this AD as of June 
11, 1993 (58 FR 27923, May 12, 1993).

ADDRESSES: For service information identified in this final rule, 
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-
5811.

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-
5811; 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 address for the Docket Office (telephone 800-
647-5527) is 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 20590.

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 2004-19-11, Amendment 39-13805 (69 FR 58828, 
October 1, 2004) (``AD 2004-19-11''). AD 2004-19-11 applied to certain 
Airbus Model 320 series airplanes. The NPRM published in the Federal 
Register on November 27, 2015 (80 FR 74058) (``the NPRM''). The NPRM 
was prompted by a determination that the previously optional 
terminating action is necessary to address the unsafe condition. The 
NPRM proposed to retain the requirements of AD 2004-19-11, and requires 
the previously optional terminating action. We are issuing this AD to 
prevent fatigue cracking of the inner rear spar, which may lead to 
reduced structural integrity of the wing and the MLG.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2014-0169, dated July 17, 2014, corrected July 
22, 2014 (referred to after this as the Mandatory Continuing 
Airworthiness Information, or ``the MCAI''), to correct an unsafe 
condition on certain Airbus Model 320 series airplanes. The MCAI 
states:

    During centre fuselage certification full scale fatigue test, 
cracks were found on the inner rear spar at holes position 52 on the 
right hand wing due to fatigue aspects.
    This condition, if not detected and corrected, could affect the 
structural integrity of the aeroplane.
    To prevent such cracks, Airbus developed modifications, which 
were introduced in production and in service through several Airbus 
Service Bulletins (SB).
    DGAC France issued * * * [an earlier AD], which was subsequently 
superseded by [DGAC] AD 2001-249 [which corresponds with FAA AD 
2004-19-11, Amendment 39-13805 (69 FR 58828, October 1, 2004)], to 
require modification of the rear spar on some

[[Page 26678]]

aeroplanes, post-modification repetitive inspections and, depending 
on findings, accomplishment of a repair. DGAC France AD 2001-249 
also specified that modification in accordance with Airbus SB A320-
57-1089 (in-service equivalent to Airbus mod 24591) constituted 
(optional) terminating action for the repetitive inspections.
    Since that [DGAC] AD [2001-249] was issued, in the framework of 
the A320 Extended Service Goal (ESG), it has been determined that 
Airbus mod 24591 is necessary to allow aeroplanes to operate up to 
the new ESG limit.
    For the reasons described above, this [EASA] AD retains the 
requirements of DGAC France AD 2001-249, which is superseded, and 
requires modification of all pre-mod 24591 aeroplanes.

    The modification includes modifying all specified fastener holes in 
the inner rear spar of the wing. 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-2015-5811.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We considered the comment received. United Airlines provided 
its support for the content of the NPRM.

Explanation of Changes Made to This AD

    We have added a new paragraph (l)(1) to this AD to provide credit 
for actions required by paragraph (h) of this AD, if those actions were 
performed before the effective date of this AD using Airbus Service 
Bulletin A320-57-1060, Revision 1, dated April 26, 1993. We have 
redesignated paragraphs (l)(1) and (l)(2) of the proposed AD as 
paragraphs (l)(2) and (l)(3) of this AD.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
this AD with the changes described previously and minor editorial 
changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM for correcting the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Airbus Service Bulletin A320-57-1089, Revision 
03, dated February 9, 2001. This service information describes 
procedures for modification of the airplane by accomplishing cold re-
expansion of the holes in the inner rear spar for the attachment of 
gear rib 5, forward pintle fitting, and actuating cylinder anchorage; 
and the installation of interference fit fasteners in the rear spar and 
gear rib 5. 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.

Costs of Compliance

    We estimate that this AD affects 84 airplanes of U.S. registry.
    The actions required by AD 2004-19-11, and retained in this AD take 
about 684 work-hours per product, at an average labor rate of $85 per 
work-hour. Required parts cost about $13,644 per product. Based on 
these figures, the estimated cost of the actions that were required by 
AD 2004-19-11 is $71,784 per product.
    We also estimate that it takes about 980 work-hours per product to 
comply with the basic requirements of this AD. The average labor rate 
is $85 per work-hour. Required parts will cost about $32,727 per 
product. Based on these figures, we estimate the cost of this AD on 
U.S. operators to be $9,746,268, or $116,027 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 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.

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) 
2004-19-11, Amendment 39-13805 (69 FR 58828, October 1, 2004), and 
adding the following new AD:

2016-08-13 Airbus: Amendment 39-18489. Docket No. FAA-2015-5811; 
Directorate Identifier 2014-NM-158-AD.

(a) Effective Date

    This AD becomes effective June 8, 2016.

(b) Affected ADs

    This AD replaces AD 2004-19-11, Amendment 39-13805 (69 FR 58828, 
October 1, 2004) (``AD 2004-19-11'').

(c) Applicability

    This AD applies to Airbus Model A320-211, -212, -214, -231, -
232, and -233 airplanes, certificated in any category, all 
manufacturer serial numbers, except those on which Airbus 
modification (mod) 24591 has been embodied in production.

(d) Subject

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

(e) Reason

    This AD was prompted by reports of fatigue cracking of the inner 
rear spar of the wing and also by a determination that the 
modification of the inner rear spar is necessary to address the 
unsafe condition.

[[Page 26679]]

We are issuing this AD to prevent fatigue cracking of the inner rear 
spar, which may lead to reduced structural integrity of the wing and 
the main landing gear (MLG).

(f) Compliance

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

(g) Retained Modification of Inner Rear Spar Web of the Wing, With 
Change to Acceptable Service Information

    This paragraph restates the requirements of paragraph (a) of AD 
2004-19-11, with a change to acceptable service information. For 
airplanes having manufacturer's serial numbers (MSNs) 003 through 
008 inclusive, and 010 through 021 inclusive, except airplanes 
modified as specified in Airbus Service Bulletin A320-57-1089, dated 
December 22, 1996; Revision 01, dated April 17, 1997; Revision 02, 
dated November 6, 1998; or Revision 03, dated February 9, 2001: 
Prior to the accumulation of 12,000 total flight cycles, or within 
500 flight cycles after June 11, 1993 (the effective date of AD 93-
08-15, Amendment 39-8563 (58 FR 27923, May 12, 1993)), whichever 
occurs later, modify the inner rear spar web of the wing in 
accordance with Airbus Service Bulletin A320-57-1004, Revision 1, 
dated September 24, 1992; or Revision 2, dated June 14, 1993. As of 
the effective date of this AD, only Airbus Service Bulletin A320-57-
1004, Revision 2, dated June 14, 1993, may be used for the actions 
required by this paragraph.

(h) Retained Cold Expansion of Holes at Forward Pintle Fitting and 
Actuating Cylinder Anchorage of the Main Landing Gear, With Change to 
Acceptable Service Information

    This paragraph restates the requirements of paragraph (b) of AD 
2004-19-11, with a change to acceptable service information. For 
airplanes having MSNs 002 through 051 inclusive, except airplanes 
modified as specified in Airbus Service Bulletin A320-57-1089, dated 
December 22, 1996; Revision 01, dated April 17, 1997; Revision 02, 
dated November 6, 1998; or Revision 03, dated February 9, 2001: 
Prior to the accumulation of 12,000 total flight cycles, or within 
2,000 flight cycles after February 14, 1994 (the effective date of 
AD 93-25-13, Amendment 39-8777 (59 FR 1903, January 13, 1994)), 
whichever occurs later, accomplish the requirements of paragraphs 
(h)(1) and (h)(2) of this AD in accordance with Airbus Service 
Bulletin A320-57-1060, dated December 8, 1992; Revision 1, dated 
April 26, 1993; or Revision 2, dated December 16, 1994. As of the 
effective date of this AD, only Airbus Service Bulletin A320-57-
1060, Revision 2, dated December 16, 1994, may be used for the 
actions required by this paragraph.
    (1) Perform a cold expansion of all the attachment holes for the 
forward pintle fitting of the main landing gear (MLG), except for 
the holes that are for taper-lok bolts.
    (2) Perform a cold expansion of the holes at the actuating 
cylinder anchorage of the MLG.

(i) Retained Repetitive Ultrasonic Inspections for Cracking of the Rear 
Spar of the Wing, With No Changes

    This paragraph restates the requirements of paragraphs (c), (d), 
and (e) of AD 2004-19-11, with no changes. Except for airplanes 
modified as specified in Airbus Service Bulletin A320-57-1089, dated 
December 22, 1996; Revision 01, dated April 17, 1997; Revision 02, 
dated November 6, 1998; or Revision 03, dated February 9, 2001: Do 
the actions specified in paragraphs (i)(1) and (i)(2) of this AD.
    (1) Do an ultrasonic inspection for cracking of the rear spar of 
the wing, in accordance with Airbus Service Bulletin A320-57-1088, 
Revision 04, dated August 6, 2001. Inspect at the applicable time 
specified in paragraph 1.E. of Airbus Service Bulletin A320-57-1088, 
Revision 04, dated August 6, 2001, except as required by paragraphs 
(i)(1)(i) and (i)(1)(ii) of this AD.
    (i) For any airplane that has not been inspected but has 
exceeded the applicable specified compliance time in paragraph 1.E. 
of Airbus Service Bulletin A320-57-1088, Revision 04, dated August 
6, 2001, as of November 5, 2004 (the effective date of AD 2004-19-
11): Inspect within 18 months after November 5, 2004.
    (ii) For any airplane that has been inspected before November 5, 
2004 (the effective date of AD 2004-19-11): Repeat the inspection 
within 3,600 flight cycles after the most recent inspection.
    (2) Repeat the inspection required by paragraph (i)(1) of this 
AD at intervals not to exceed 3,600 flight cycles or 6,700 flight 
hours, whichever occurs first, until the requirements of paragraph 
(k) of this AD have been done.

(j) Retained Corrective Action for Inspections Required by Paragraphs 
(i)(1) and (i)(2) of This AD, With Specific Delegation Approval 
Language

    This paragraph restates the requirements of paragraph (f) of AD 
2004-19-11, with specific delegation approval language. If any crack 
is found during any inspection required by paragraph (i)(1) or 
(i)(2) of this AD: Before further flight, repair in accordance with 
a method approved by either the Manager, International Branch, ANM-
116, FAA, Transport Airplane Directorate; or the Direction 
G[eacute]n[eacute]rale de l'Aviation Civile (or its delegated 
agent); or the European Aviation Safety Agency (EASA); or Airbus's 
EASA Design Organization Approval (DOA). Accomplishment of a repair 
as required by this paragraph does not constitute terminating action 
for the repetitive inspections required by paragraph (i)(2) of this 
AD.

(k) New Requirement of This AD: Modification of the Inner Rear Spar

    Before exceeding 48,000 flight cycles or 96,000 flight hours, 
whichever occurs first since first flight of the airplane: Modify 
all specified fastener holes in the inner rear spar of the wing, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A320-57-1089, Revision 03, dated February 9, 2001; except, 
where Airbus Service Bulletin A320-57-1089, Revision 03, dated 
February 9, 2001, specifies to contact Airbus for certain 
conditions, before further flight, repair using a method approved by 
the Manager, International Branch, ANM-116, Transport Airplane 
Directorate, FAA; or EASA; or Airbus's EASA DOA. Modification of all 
specified fastener holes in the rear spar of the wing terminates the 
initial and repetitive inspections required by paragraphs (i)(1) and 
(i)(2) of this AD. If the modification is done both before the 
airplane accumulates 12,000 total flight cycles and before the 
effective date of this AD, the modification also terminates the 
actions required by paragraphs (g) and (h) of this AD.

(l) Credit for Previous Actions

    (1) This paragraph provides credit for actions required by 
paragraph (h) of this AD, if those actions were performed before the 
effective date of this AD using Airbus Service Bulletin A320-57-
1060, Revision 1, dated April 26, 1993. This service information is 
not incorporated by reference in this AD.
    (2) This paragraph provides credit for actions required by 
paragraph (i) of this AD, if those actions were performed before the 
effective date of this AD using Airbus Service Bulletin A320-57-
1088, Revision 02, dated July 29, 1999; or Revision 03, dated 
February 9, 2001. This service information is not incorporated by 
reference in this AD.
    (3) This paragraph provides credit for actions required by 
paragraph (k) of this AD, if those actions were performed before the 
effective date of this AD using Airbus Service Bulletin A320-57-
1089, Revision 02, dated November 6, 1998. This service information 
is not incorporated by reference in this AD.

(m) 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.
    (i) 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.
    (ii) AMOCs approved previously in accordance with AD 2004-19-11 
are approved as AMOCs for the corresponding provisions of paragraphs 
(g) through (j) of this AD.
    (2) Contacting the Manufacturer: As of the effective date of 
this AD, for any requirement

[[Page 26680]]

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.

(n) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2014-0169, dated July 17, 2014, 
corrected July 22, 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-2015-5811.
    (2) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (o)(8) and (o)(9) of this AD.

(o) 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 
June 8, 2016.
    (i) Airbus Service Bulletin A320-57-1089, Revision 03, dated 
February 9, 2001.
    (ii) Reserved.
    (4) The following service information was approved for IBR on 
November 5, 2004 (69 FR 58828, October 1, 2004).
    (i) Airbus Service Bulletin A320-57-1088, Revision 04, dated 
August 6, 2001.
    (ii) Reserved.
    (5) The following service information was approved for IBR on 
June 30, 2000 (65 FR 34069, May 26, 2000).
    (i) Airbus Service Bulletin A320-57-1004, Revision 2, dated June 
14, 1993. This service bulletin contains the following list of 
effective pages: Pages 1, 4, 12, 14, 17 through 20, 22, 23, 28, 29, 
Revision 2, dated June 14, 1993; page 15, Revision 1, dated 
September 24, 1992; and pages 2, 3, 5 through 11, 13, 16, 21, 24 
through 27, 30, Original Issue, dated July 9, 1991.
    (ii) Airbus Service Bulletin A320-57-1060, Revision 2, dated 
December 16, 1994.
    (6) The following service information was approved for IBR on 
February 14, 1994 (59 FR 1903, January 13, 1994).
    (i) Airbus Service Bulletin A320-57-1060, dated December 8, 
1992.
    (ii) Reserved.
    (7) The following service information was approved for IBR on 
June 11, 1993 (58 FR 27923, May 12, 1993).
    (i) Airbus Service Bulletin A320-57-1004, Revision 1, dated 
September 24, 1992. This service bulletin contains the following 
list of effective pages: Pages 1, 4, 12, 14 through 15, 17 through 
18, 20, Revision 1, dated September 24, 1992; and pages 2 through 3, 
5 through 11, 13, 16, 19, 21 through 30, Original Issue, dated July 
9, 1991.
    (ii) Reserved.
    (8) 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.
    (9) 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.
    (10) 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 April 8, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-08956 Filed 5-3-16; 8:45 am]
 BILLING CODE 4910-13-P