Airworthiness Directives; Airbus Airplanes, 26677-26680 [2016-08956]
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Federal Register / Vol. 81, No. 86 / Wednesday, May 4, 2016 / Rules and Regulations
docket on the Internet at https://
www.regulations.gov/
#!documentDetail;D=FAA-2015-7490-0001.
(i) 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 the AD specifies otherwise.
(i) Turbomeca S.A. Service Bulletin No.
283 72 0811, Version A, dated August 25,
2015.
(ii) Reserved.
(3) For Turbomeca S.A. service information
identified in this AD, contact Turbomeca
S.A., 40220 Tarnos, France; phone: 33 (0)5 59
74 40 00; fax: 33 (0)5 59 74 45 15.
(4) You may view this service information
at FAA, Engine & Propeller Directorate, 1200
District Avenue, Burlington, MA. For
information on the availability of this
material at the FAA, call 781–238–7125.
(5) You may view this service information
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: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Burlington, Massachusetts, on
April 21, 2016.
Colleen M. D’Alessandro,
Manager, Engine & Propeller Directorate,
Aircraft Certification Service.
[FR Doc. 2016–10279 Filed 5–3–16; 8:45 am]
BILLING CODE 4910–13–P
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
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
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,
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SUMMARY:
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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 https://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 https://
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 https://
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,
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26677
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
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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 https://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.
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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
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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 workhour. 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,
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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
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 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.
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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.
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(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.
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(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 Generale 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
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26679
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-116AMOC-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
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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.
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(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
https://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
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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 https://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: https://
www.archives.gov/federal-register/cfr/ibrlocations.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
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–3990; Directorate
Identifier 2014–NM–255–AD; Amendment
39–18478; AD 2016–08–02]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
Airbus Model A320–214, –232, and
–233 airplanes; and Airbus Model
A321–211 and –231 airplanes. This AD
was prompted by reports of incorrect
installation of jiffy joint connectors on
cables connected to certain passenger
service units (PSUs), which could cause
the passenger oxygen container to
malfunction if the connector becomes
disengaged during flight due to
vibration. This AD requires
identification of the affected PSUs, and
depending on findings, doing applicable
related investigative and corrective
actions. We are issuing this AD to
prevent failure of the door of the
passenger oxygen container to open in
the event of airplane decompression,
resulting in lack of oxygen supply and
consequent injury to occupants.
DATES: This AD becomes effective June
8, 2016.
SUMMARY:
PO 00000
Frm 00014
Fmt 4700
Sfmt 4700
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of June 8, 2016.
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov/
#!docketDetail;D=FAA-2015-3990; 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 Airbus 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 https://www.airbus.com.
For Airbus Operations GmbH service
information identified in this final rule,
contact Airbus Operations GmbH, Cabin
Electronics, Lueneburger Schanze 30,
21614 Buxtehude, Germany; telephone
+49 40 7437 46 32; telefax +49 40 7437
16 80; email ruediger.jansen@
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 https://
www.regulations.gov by searching for
and locating Docket No. FAA–2015–
3990.
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 by adding an AD that would
apply to certain Airbus Model A320–
214, –232, and –233 airplanes; and
Airbus Model A321–211 and –231
airplanes. The NPRM published in the
Federal Register on October 19, 2015
(80 FR 63134) (‘‘the NPRM’’).
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA Airworthiness
Directive 2014–0256, dated November
26, 2014 (referred to after this as the
Mandatory Continuing Airworthiness
Information, or ‘‘the MCAI’’), to correct
an unsafe condition for certain Airbus
E:\FR\FM\04MYR1.SGM
04MYR1
]]>Agencies
[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]
-----------------------------------------------------------------------
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.
-----------------------------------------------------------------------
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
https://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 https://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 https://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 https://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 https://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 https://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: https://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
