Airworthiness Directives; Airbus Airplanes, 55358-55362 [2016-19486]
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Federal Register / Vol. 81, No. 161 / Friday, August 19, 2016 / Rules and Regulations
(o) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) Canadian
Airworthiness Directive CF–2014–45, dated
December 23, 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–2015–3986.
(2) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (p)(3), (p)(4), and (p)(5) of this
AD.
jstallworth on DSK7TPTVN1PROD with RULES
(p) 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.
(i) Bombardier ModSum IS4Q2400028,
Revision B, dated December 11, 2012. (This
document has 33 pages; the first page of the
modsum indicates that there are 32 pages.)
(ii) Bombardier ModSum IS4Q2400029,
Revision A, dated July 6, 2012.
(iii) Bombardier ModSum IS4Q5450002,
Revision B, dated June 22, 2012.
(iv) Bombardier ModSum IS4Q5450003,
Revision C, dated November 29, 2012.
(v) Bombardier Service Bulletin 84–32–
112, Revision C, dated April 2, 2015.
(vi) Bombardier Service Bulletin 84–32–
114, Revision B, dated February 3, 2015.
(vii) Bombardier Service Bulletin 84–54–
19, dated April 18, 2013.
(viii) Bombardier Service Bulletin 84–54–
20, Revision C, dated March 5, 2015.
(ix) Bombardier Service Bulletin 84–54–21,
dated May 9, 2013.
(x) Goodrich Service Bulletin 46400–32–
102 R2, Revision 2, dated February 17, 2015.
(3) For Bombardier service information
identified in this AD, contact Bombardier,
Inc., Q-Series Technical Help Desk, 123
Garratt Boulevard, Toronto, Ontario M3K
1Y5, Canada; telephone 416–375–4000; fax
416–375–4539; email
thd.qseries@aero.bombardier.com; Internet
https://www.bombardier.com.
(4) For Goodrich service information
identified in this AD, contact Goodrich
Corporation, Landing Gear, 1400 South
Service Road, West Oakville, ON, Canada
L6L 5Y7; phone: 905–825–1568; email:
jean.breed@goodrich.com; Internet: https://
www.goodrich.com/TechPubs.
(5) 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.
(6) 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.
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Issued in Renton, Washington, on August
4, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2016–19480 Filed 8–18–16; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–4226; Directorate
Identifier 2015–NM–095–AD; Amendment
39–18616; AD 2016–17–03]
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) 2003–25–
07 for certain Airbus Model A319 and
A320 series airplanes, and AD 2005–13–
39 for certain Airbus Model A321 series
airplanes. AD 2003–25–07 required a
revision to the airplane flight manual
(AFM) and replacement of both elevator
aileron computers (ELACs) having L80
standards with new ELACs having L81
standards. AD 2005–13–39 required a
revision to the AFM, replacement of
existing ELACs with ELACs having L83
or L91 standards, as applicable; and a
concurrent action. Since we issued AD
2003–25–07 and AD 2005–13–39, we
have determined that new ELAC
standards must be incorporated. The
ELAC standards have been upgraded to
version L97+, which implements
enhanced angle-of-attack (AOA)
monitoring to better detect AOA
blockage, including multiple AOA
blockages. This AD requires replacing
existing ELACs with new ELACs having
L97+ standards or revising the software
in an existing ELAC to the L97+
standards, as applicable, which
terminates the requirements of AD
2003–25–07 and AD 2005–13–39. This
AD also expands the applicability to
include all Airbus Model A318, A319,
A320, and A321 series airplanes. We are
issuing this AD to prevent inadvertent
activation of the AOA protections.
Inadvertent activation of the AOA
protections could result in a continuous
nose-down pitch rate that could result
in reduced controllability of the
airplane.
DATES: This AD is effective September
23, 2016.
SUMMARY:
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The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of September 23, 2016.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of August 9, 2005 (70 FR 38580, July
5, 2005).
The Director of the Federal Register
approved the incorporation by reference
of a certain other publication listed in
this AD as of January 22, 2004 (68 FR
70431, December 18, 2003).
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–2016–
4226.
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–2016–
4226; 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 2003–25–07,
Amendment 39–13390 (68 FR 70431,
December 18, 2003) (‘‘AD 2003–25–
07’’); and AD 2005–13–39, Amendment
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jstallworth on DSK7TPTVN1PROD with RULES
39–14176 (70 FR 38580, July 5, 2005)
(‘‘AD 2005–13–39’’).
AD 2003–25–07 applied to certain
Airbus Model A319 and A320 series
airplanes, and AD 2005–13–39 applied
to certain Airbus Model A321 series
airplanes. The NPRM published in the
Federal Register on March 17, 2016 (81
FR 14404). The NPRM was prompted by
a determination that new ELAC
standards must be incorporated. The
ELAC standards have been upgraded to
version L97+, which implements
enhanced AOA monitoring to better
detect AOA blockage, including
multiple AOA blockages.
The NPRM proposed to require
replacing existing ELACs with new
ELACs having L97+ standards or
revising the software in an existing
ELAC to the L97+ standards, as
applicable, which would terminate the
requirements of AD 2003–25–07 and AD
2005–13–39. We are issuing this AD to
prevent inadvertent activation of the
AOA protections. Inadvertent activation
of the AOA protections could result in
a continuous nose-down pitch rate that
could result in reduced controllability
of the airplane.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA Airworthiness
Directive 2015–0088R1, including
Appendix 01, dated June 2, 2015
(referred to after this as the Mandatory
Continuing Airworthiness Information,
or ‘‘the MCAI’’), to correct an unsafe
condition for all Airbus Model A318,
A319, A320, and A321 series airplanes.
The MCAI states:
[EASA] AD, and one P/N ELAC was
inadvertently omitted. This [EASA] AD
revises EASA AD 2015–0088 to correct these
errors and to add clarification to paragraph
(7) [of the EASA AD].
The latest elevator aileron computer
(ELAC) standard, L97+, implements
enhanced Angle of Attack (AOA) monitoring
in order to better detect cases of AOA
blockage, including multiple AOA blockage.
Two ELAC L97+ versions are currently
available, Part Number (P/N) 3945129109
with data loading capability, and P/N
3945128215 without the data loading
capability. Three existing [EASA] ADs
requiring installation of earlier ELAC
(software) have been identified and taken
into account for cancellation by this new
[EASA] AD.
For the reasons described above, EASA
issued AD 2015–0088, cancelling DGAC
´ ´
[Direction Generale de l’Aviation Civile]
France AD 95–203–072 (no requirements
retained) [which corresponds to FAA AD 98–
09–18, Amendment 39–10499 (63 FR 23374,
April 29, 1998)], and partially retaining the
requirements of DGAC France AD 2001–508
[which corresponds to FAA AD 2003–25–07],
and [DGAC France] AD F–2004–147 (EASA
approval ref. 2004–8601) [which corresponds
to FAA AD 2005–13–39], which were
superseded, and to require replacement of all
ELAC with ELAC L97+ standard.
Since that [EASA] AD was issued, some
errors were detected in Appendix 1 of the
Airbus has issued Service Bulletin
A320–27–1243, including Appendix 01,
dated March 17, 2015. This service
information describes procedures for
replacing the existing ELACs with new
ELACs having L97+ standards, and
modifying existing ELACs into units
with L97+ standards.
Airbus has also issued Service
Bulletin A320–27–1244, dated March 5,
2015. This service information describes
procedures for modification of an
airplane by replacing any existing ELAC
unit with an ELAC 97+ unit having P/
N 3945128215.
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.
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The required actions include either
replacing existing ELACs with new
ELACs having L97+ standards
uploaded, or revising the software in the
existing ELACs to L97+ standards. This
AD also expands the applicability to
include all Airbus Model A318, A319,
A320, and A321 series airplanes. 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–2016–
4226.
Comments
We gave the public the opportunity to
participate in developing this AD. We
considered the comment received. The
commenter supported the NPRM.
Conclusion
We reviewed the available data,
including the comment received, 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 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
Costs of Compliance
We estimate that this AD affects 940
airplanes of U.S. registry.
The actions required by AD 2003–25–
07 and retained in this AD take about
1 work-hour per product, at an average
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55359
labor rate of $85 per work-hour. Based
on these figures, the estimated cost of
the actions that were required by AD
2003–25–07 is $85 per product.
The actions required by AD 2005–13–
39 and retained in this AD take about
1 work-hour per product, at an average
labor rate of $85 per work-hour. Based
on these figures, the estimated cost of
the actions that were required by AD
2005–13–39 is $85 per product.
We also estimate that it will take
about 3 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 $7,230 per product. Based on
these figures, we estimate the cost of
this AD on U.S. operators to be
$7,035,900, or $7,485 per product.
According to the parts manufacturer,
some of the costs of this AD may be
covered under warranty, thereby
reducing the cost impact on affected
individuals. We do not control warranty
coverage for affected individuals. As a
result, we have included all costs in our
cost estimate.
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;
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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:
(c) Applicability
This AD applies to the airplanes identified
in paragraphs (c)(1) through (c)(4) of this AD,
certificated in any category, all manufacturer
serial numbers.
(1) Airbus Model A318–111, –112, –121,
and –122 airplanes.
(2) Airbus Model A319–111, –112, –113,
–114, –115, –131, –132, and –133 airplanes.
(3) Airbus Model A320–211, –212, –214,
–231, –232, and –233 airplanes.
(4) Airbus Model A321–111, –112, –131,
–211, –212, –213, –231, and –232 airplanes.
(d) Subject
Air Transport Association (ATA) of
America Code 27, Flight Controls.
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
(1) AD 2003–25–07, Amendment 39–13390
(68 FR 70431, December 18, 2003) (‘‘AD
2003–25–07’’).
(2) AD 2005–13–39, Amendment 39–14176
(70 FR 38580, July 5, 2005) (‘‘AD 2005–13–
39’’).
[Amended]
2. The FAA amends § 39.13 by:
a. Removing Airworthiness Directive
(AD) 2003–25–07, Amendment 39–
13390 (68 FR 70431, December 18,
2003); and AD 2005–13–39,
Amendment 39–14176 (70 FR 38580,
July 5, 2005); and
■ b. Adding the following new AD:
■
■
2016–17–03 Airbus: Docket No. FAA–2016–
4226; Directorate Identifier 2015–NM–
095–AD.
(a) Effective Date
This AD is effective September 23, 2016.
(b) Affected ADs
This AD replaces the ADs identified in
paragraphs (b)(1) and (b)(2) of this AD.
(e) Reason
This AD was prompted by a determination
that new elevator aileron computer (ELAC)
standards must be incorporated. The ELAC
standards have been upgraded to version
L97+, which implements enhanced angle-ofattack (AOA) monitoring to better detect
AOA blockage, including multiple AOA
blockages. We are issuing this AD to prevent
inadvertent activation of the AOA
protections. Inadvertent activation of the
AOA protections could result in a continuous
nose-down pitch rate that could result in
reduced controllability of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Retained Replacement of ELAC L80 Units
With L81 Units, With No Changes
For Model A319 and A320 series airplanes,
equipped with ELAC L80 standards having
part numbers listed in Airbus Service
Bulletin A320–27–1135, dated June 29, 2001:
This paragraph restates the requirements of
paragraph (b) of AD 2003–25–07, with no
changes. Within 1 year after January 22, 2004
(the effective date of AD 2003–25–07):
Replace both ELACs having L80 standards
with new ELACs having L81 standards, by
doing all the actions per paragraphs A., B.,
C., and D. of the Accomplishment
Instructions of Airbus Service Bulletin A320–
27–1135, dated June 29, 2001.
(h) Retained Installation of ELAC L83 or L91
Software, With No Changes
For Model A321–111, –112, –131, –211,
and –231 airplanes, except those with Airbus
Modification 34043 installed in production:
This paragraph restates the requirements of
paragraph (g) of AD 2005–13–39, with no
changes. Within 16 months after August 9,
2005 (the effective date of AD 2005–13–39):
Replace existing ELACs with ELACs having
L83 standards, by accomplishing all of the
actions specified in the Accomplishment
Instructions of Airbus Service Bulletin A320–
27–1151, dated March 9, 2004, including
Appendix 01, dated March 9, 2004; or with
ELACs having L91 standards, by
accomplishing all of the actions specified in
the Accomplishment Instructions of Airbus
Service Bulletin A320–27–1152, dated June
4, 2004, including Appendix 01, dated June
4, 2004; as applicable.
(i) New Requirement of This AD: ELAC
Replacement or Modification
At the applicable times specified in table
1 to paragraphs (i) and (m)(3)(ii) of this AD:
Replace each ELAC unit with an ELAC L97+
unit having part number (P/N) 3945129100
and software having P/N 3945129109, or
modify existing ELAC units into ELAC L97+
units having P/N 3945129100 with L97+
operational software P/N 3945129109 loaded,
as applicable, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–27–1243, including
Appendix 01, dated March 17, 2015.
Accomplishing this replacement terminates
the actions required by paragraphs (g) and (h)
of this AD.
TABLE 1 TO PARAGRAPHS (i) AND (m)(3)(ii) OF THIS AD—COMPLIANCE TIMES
Compliance time
(after the effective
date of this AD)
jstallworth on DSK7TPTVN1PROD with RULES
Airbus airplane models
Model A318 series airplanes with UTAS (formerly Goodrich) AOA P/N 0861ED or P/N 0861ED2 installed in all 3 positions
(captain, first officer, and standby).
Model A319 series airplanes with UTAS (formerly Goodrich) AOA P/N 0861ED or P/N 0861ED2 installed in all 3 positions
(captain, first officer, and standby).
Model A320 series airplanes with UTAS (formerly Goodrich) AOA P/N 0861ED or P/N 0861ED2 installed in all 3 positions
(captain, first officer, and standby).
Model A321 series airplanes with UTAS (formerly Goodrich) AOA P/N 0861ED or P/N 0861ED2 installed in all 3 positions
(captain, first officer, and standby).
Model A318, A319, A320, and A321 series airplanes that do not have UTAS (formerly Goodrich) AOA P/N 0861ED or P/N
0861ED2 installed in all 3 positions (captain, first officer, and standby).
(j) Optional Method of Compliance
Modification of an airplane by replacing
any existing ELAC unit with an ELAC 97+
unit having P/N 3945128215, in accordance
with the Accomplishment Instructions of
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Airbus Service Bulletin A320–27–1244,
dated March 5, 2015, is an acceptable method
of compliance for the requirements of
paragraph (i) of this AD, for only that
modified airplane. Accomplishing this
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Within 5 months.
Within 10 months.
Within 10 months.
Within 5 months.
Within 25 months.
modification terminates the actions required
by paragraphs (g) and (h) of this AD for that
modified airplane.
Note 1 to paragraph (j) of this AD: ELAC
unit P/N 3945128215 is not data-loadable,
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but it is fully interchangeable and mixable
with data-loadable ELAC 97+ unit P/N
3945129100 with software P/N 3945129109
loaded.
(k) Airplanes Excluded From Requirements
of Paragraphs (g), (h), and (i), and From the
Actions in Paragraph (j) of This AD
Airplanes on which Airbus Modification
156546 (installation of ELAC L97+ with
software P/N 3945129109) was installed in
production are excluded from the
requirements of paragraphs (g), (h), and (i) of
this AD, and from the actions specified in
paragraph (j) of this AD, provided it can be
determined that no ELAC having a part
number identified in table 2 to paragraphs (k)
and (m) of this AD has been installed on that
airplane since the date of issuance of the
original airworthiness certificate or the date
of issuance of the original export certificate
of airworthiness.
TABLE 2 TO PARAGRAPHS (k) AND (m) OF THIS AD—PROHIBITED ELAC PART NUMBERS
Part No.
Designation
3945122202 ...............................................................................
3945122203 ...............................................................................
3945122303 ...............................................................................
3945122304 ...............................................................................
3945122305 ...............................................................................
3945122306 ...............................................................................
3945122307 ...............................................................................
C12370AA01 ..............................................................................
3945122501 ...............................................................................
3945122502 ...............................................................................
3945122503 ...............................................................................
3945122504 ...............................................................................
3945122505 ...............................................................................
3945123505 ...............................................................................
3945128101 ...............................................................................
3945122506 ...............................................................................
3945123506 ...............................................................................
3945128102 ...............................................................................
3945122507 ...............................................................................
3945123507 ...............................................................................
3945128103 ...............................................................................
3945122608 ...............................................................................
3945123608 ...............................................................................
3945122609 ...............................................................................
3945123609 ...............................................................................
3945128204 ...............................................................................
3945128205 ...............................................................................
3945128206 ...............................................................................
3945129101 ...............................................................................
3945128207 ...............................................................................
3945128208 ...............................................................................
3945128209 ...............................................................................
3945129103 ...............................................................................
3945128210 ...............................................................................
3945129104 ...............................................................................
3945128212 ...............................................................................
3945129106 ...............................................................................
3945129107 ...............................................................................
3945128214 ...............................................................................
3945129108 ...............................................................................
jstallworth on DSK7TPTVN1PROD with RULES
(l) Later-Approved Parts
Installation of an ELAC version (part
number) approved after the effective date of
this AD is an approved method of
compliance with the requirements of
paragraph (i) of this AD, and the actions
specified in paragraph (j) of this AD,
provided the requirements specified in
paragraphs (l)(1) and (l)(2) of this AD are met.
(1) The version (part number) must be
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).
(2) The installation must be done using a
method approved by the Manager,
International Branch, ANM–116, Transport
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ELAC
ELAC
ELAC
ELAC
ELAC
ELAC
ELAC
ELAC
ELAC
ELAC
ELAC
ELAC
ELAC
ELAC
ELAC
ELAC
ELAC
ELAC
ELAC
ELAC
ELAC
ELAC
ELAC
ELAC
ELAC
ELAC
ELAC
ELAC
ELAC
ELAC
ELAC
ELAC
ELAC
ELAC
ELAC
ELAC
ELAC
ELAC
ELAC
ELAC
A320–111 Type Def. .....................................................
L50C ..............................................................................
L50C ..............................................................................
L60 .................................................................................
L61B ..............................................................................
L61F ...............................................................................
L62C ..............................................................................
L68C ..............................................................................
L69 .................................................................................
L69J ...............................................................................
L77 .................................................................................
L78 .................................................................................
A L80 .............................................................................
A’ L80 ............................................................................
B L80 .............................................................................
A L81 .............................................................................
A’ L81 ............................................................................
B L81 .............................................................................
A L82 .............................................................................
A’ L82 ............................................................................
B L82 .............................................................................
A L83 .............................................................................
A’ L83 ............................................................................
A L84 .............................................................................
A’ L84 ............................................................................
B L90L ...........................................................................
B L90N ...........................................................................
B L91 .............................................................................
B L91 data loadable ......................................................
B L92 .............................................................................
B L92L ...........................................................................
B L93 .............................................................................
B L93 data loadable ......................................................
B L94 .............................................................................
B L94 data loadable ......................................................
B L96 .............................................................................
B L96 data loadable ......................................................
B L96 H–A data loadable ..............................................
B L97 .............................................................................
B L97 data loadable ......................................................
Airplane Directorate, FAA; or the EASA; or
Airbus’s EASA DOA.
(m) Parts Installation Limitation
As of the applicable time specified in
paragraph (m)(1) or (m)(2) of this AD, do not
install on any airplane an ELAC unit having
a part number identified in table 2 to
paragraphs (k) and (m) of this AD, except as
specified in paragraph (m)(3) of this AD.
(1) For an airplane that, as of the effective
date of this AD, has any ELAC unit installed
having a part number identified in table 2 to
paragraphs (k) and (m) of this AD: After
modification of that airplane as required by
paragraph (i) of this AD, or as specified in
paragraph (j) of this AD.
(2) For an airplane that, as of the effective
date of this AD, does not have any ELAC unit
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installed having a part number identified in
table 2 to paragraphs (k) and (m) of this AD:
As of the effective date of this AD.
(3) As of the effective date of this AD, a
data-loadable ELAC B unit having a part
number identified in table 2 to paragraphs (k)
and (m) of this AD can be installed on an
airplane provided that L97+ software P/N
3945129109 is uploaded at the applicable
time specified in paragraph (m)(3)(i) or
(m)(3)(ii) of this AD.
(i) For all airplanes except those identified
in paragraph (m)(3)(ii) of this AD: Before
further flight after the ELAC B unit
installation.
(ii) For airplanes that have not been
modified as required by paragraph (i) of this
AD: Within the applicable compliance time
E:\FR\FM\19AUR1.SGM
19AUR1
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Federal Register / Vol. 81, No. 161 / Friday, August 19, 2016 / Rules and Regulations
specified in table 1 to paragraphs (i) and
(m)(3)(ii) of this AD.
jstallworth on DSK7TPTVN1PROD with RULES
(n) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane
Directorate FAA, has the authority to approve
AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19. In
accordance with 14 CFR 39.19, send your
request to your principal inspector or local
Flight Standards District Office, as
appropriate. If sending information directly
to the International Branch send it to ATTN:
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.
(ii) AMOCs approved previously for AD
2003–25–07 are approved as AMOCs for the
corresponding provisions of paragraph (g) of
this AD.
(iii) AMOCs approved previously for AD
2005–13–39 are approved as AMOCs for the
corresponding provisions of paragraph (h) of
this AD.
(2) Contacting the Manufacturer: As of the
effective date of this AD, for any requirement
in this AD to obtain corrective actions from
a manufacturer, the action must be
accomplished using a method approved by
the Manager, International Branch, ANM–
116, Transport Airplane Directorate, FAA; or
the EASA; or Airbus’s EASA DOA. If
approved by the DOA, the approval must
include the DOA-authorized signature.
(3) Required for Compliance (RC): If any
service information contains procedures or
tests that are identified as RC, those
procedures and tests must be done to comply
with this AD; any procedures or tests that are
not identified as RC are recommended. Those
procedures and tests that are not identified
as RC may be deviated from using accepted
methods in accordance with the operator’s
maintenance or inspection program without
obtaining approval of an AMOC, provided
the procedures and tests identified as RC can
be done and the airplane can be put back in
an airworthy condition. Any substitutions or
changes to procedures or tests identified as
RC require approval of an AMOC.
(o) Related Information
Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2015–0088R1,
including Appendix 01, dated June 2, 2015,
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–2016–4226.
(p) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
VerDate Sep<11>2014
14:10 Aug 18, 2016
Jkt 238001
(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 September 23, 2016.
(i) Airbus Service Bulletin A320–27–1243,
including Appendix 01, dated March 17,
2015.
(ii) Airbus Service Bulletin A320–27–1244,
dated March 5, 2015.
(4) The following service information was
approved for IBR on August 9, 2005 (70 FR
38580, July 5, 2005).
(i) Airbus Service Bulletin A320–27–1151,
including Appendix 01, dated March 9, 2004.
(ii) Airbus Service Bulletin A320–27–1152,
including Appendix 01, dated June 4, 2004.
(5) The following service information was
approved for IBR on January 22, 2004 (68 FR
70431, December 18, 2003).
(i) Airbus Service Bulletin A320–27–1135,
dated June 29, 2001.
(ii) Reserved.
(6) 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.
(7) 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.
(8) 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 August
8, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2016–19486 Filed 8–18–16; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–8463; Directorate
Identifier 2014–NM–226–AD; Amendment
39–18612; AD 2016–16–14]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
PO 00000
Frm 00012
Fmt 4700
Sfmt 4700
We are superseding
Airworthiness Directive (AD) 2013–20–
11, for all Airbus Model A318, A319,
A320, and A321 series airplanes. AD
2013–20–11 required modifying the
passenger emergency oxygen container
assembly. This new AD expands the
affected group of oxygen containers to
include those labeled ‘‘DAe Systems.’’
This AD was prompted by a
determination that the unsafe condition
also affects oxygen containers labeled
‘‘DAe Systems.’’ We are issuing this AD
to prevent a high temperature oxygen
generator and mask from falling down
and possibly resulting in an ignition
source in the passenger compartment,
injury to passengers, and reduced
availability of supplemental oxygen.
DATES: This AD is effective September
23, 2016.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of December 2, 2013 (78 FR 64162,
October 28, 2013).
ADDRESSES: 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.airwortheas@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–
8463.
SUMMARY:
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–
8463; 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,
E:\FR\FM\19AUR1.SGM
19AUR1
]]>Agencies
[Federal Register Volume 81, Number 161 (Friday, August 19, 2016)]
[Rules and Regulations]
[Pages 55358-55362]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-19486]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2016-4226; Directorate Identifier 2015-NM-095-AD;
Amendment 39-18616; AD 2016-17-03]
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) 2003-25-07 for
certain Airbus Model A319 and A320 series airplanes, and AD 2005-13-39
for certain Airbus Model A321 series airplanes. AD 2003-25-07 required
a revision to the airplane flight manual (AFM) and replacement of both
elevator aileron computers (ELACs) having L80 standards with new ELACs
having L81 standards. AD 2005-13-39 required a revision to the AFM,
replacement of existing ELACs with ELACs having L83 or L91 standards,
as applicable; and a concurrent action. Since we issued AD 2003-25-07
and AD 2005-13-39, we have determined that new ELAC standards must be
incorporated. The ELAC standards have been upgraded to version L97+,
which implements enhanced angle-of-attack (AOA) monitoring to better
detect AOA blockage, including multiple AOA blockages. This AD requires
replacing existing ELACs with new ELACs having L97+ standards or
revising the software in an existing ELAC to the L97+ standards, as
applicable, which terminates the requirements of AD 2003-25-07 and AD
2005-13-39. This AD also expands the applicability to include all
Airbus Model A318, A319, A320, and A321 series airplanes. We are
issuing this AD to prevent inadvertent activation of the AOA
protections. Inadvertent activation of the AOA protections could result
in a continuous nose-down pitch rate that could result in reduced
controllability of the airplane.
DATES: This AD is effective September 23, 2016.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of September 23,
2016.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of August 9,
2005 (70 FR 38580, July 5, 2005).
The Director of the Federal Register approved the incorporation by
reference of a certain other publication listed in this AD as of
January 22, 2004 (68 FR 70431, December 18, 2003).
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-2016-
4226.
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-2016-
4226; 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 2003-25-07, Amendment 39-13390 (68 FR 70431,
December 18, 2003) (``AD 2003-25-07''); and AD 2005-13-39, Amendment
[[Page 55359]]
39-14176 (70 FR 38580, July 5, 2005) (``AD 2005-13-39'').
AD 2003-25-07 applied to certain Airbus Model A319 and A320 series
airplanes, and AD 2005-13-39 applied to certain Airbus Model A321
series airplanes. The NPRM published in the Federal Register on March
17, 2016 (81 FR 14404). The NPRM was prompted by a determination that
new ELAC standards must be incorporated. The ELAC standards have been
upgraded to version L97+, which implements enhanced AOA monitoring to
better detect AOA blockage, including multiple AOA blockages.
The NPRM proposed to require replacing existing ELACs with new
ELACs having L97+ standards or revising the software in an existing
ELAC to the L97+ standards, as applicable, which would terminate the
requirements of AD 2003-25-07 and AD 2005-13-39. We are issuing this AD
to prevent inadvertent activation of the AOA protections. Inadvertent
activation of the AOA protections could result in a continuous nose-
down pitch rate that could result in reduced controllability of the
airplane.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA
Airworthiness Directive 2015-0088R1, including Appendix 01, dated June
2, 2015 (referred to after this as the Mandatory Continuing
Airworthiness Information, or ``the MCAI''), to correct an unsafe
condition for all Airbus Model A318, A319, A320, and A321 series
airplanes. The MCAI states:
The latest elevator aileron computer (ELAC) standard, L97+,
implements enhanced Angle of Attack (AOA) monitoring in order to
better detect cases of AOA blockage, including multiple AOA
blockage.
Two ELAC L97+ versions are currently available, Part Number (P/
N) 3945129109 with data loading capability, and P/N 3945128215
without the data loading capability. Three existing [EASA] ADs
requiring installation of earlier ELAC (software) have been
identified and taken into account for cancellation by this new
[EASA] AD.
For the reasons described above, EASA issued AD 2015-0088,
cancelling DGAC [Direction G[eacute]n[eacute]rale de l'Aviation
Civile] France AD 95-203-072 (no requirements retained) [which
corresponds to FAA AD 98-09-18, Amendment 39-10499 (63 FR 23374,
April 29, 1998)], and partially retaining the requirements of DGAC
France AD 2001-508 [which corresponds to FAA AD 2003-25-07], and
[DGAC France] AD F-2004-147 (EASA approval ref. 2004-8601) [which
corresponds to FAA AD 2005-13-39], which were superseded, and to
require replacement of all ELAC with ELAC L97+ standard.
Since that [EASA] AD was issued, some errors were detected in
Appendix 1 of the [EASA] AD, and one P/N ELAC was inadvertently
omitted. This [EASA] AD revises EASA AD 2015-0088 to correct these
errors and to add clarification to paragraph (7) [of the EASA AD].
The required actions include either replacing existing ELACs with
new ELACs having L97+ standards uploaded, or revising the software in
the existing ELACs to L97+ standards. This AD also expands the
applicability to include all Airbus Model A318, A319, A320, and A321
series airplanes. 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-2016-4226.
Comments
We gave the public the opportunity to participate in developing
this AD. We considered the comment received. The commenter supported
the NPRM.
Conclusion
We reviewed the available data, including the comment received, 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 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 Service Bulletin A320-27-1243, including Appendix
01, dated March 17, 2015. This service information describes procedures
for replacing the existing ELACs with new ELACs having L97+ standards,
and modifying existing ELACs into units with L97+ standards.
Airbus has also issued Service Bulletin A320-27-1244, dated March
5, 2015. This service information describes procedures for modification
of an airplane by replacing any existing ELAC unit with an ELAC 97+
unit having P/N 3945128215.
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 940 airplanes of U.S. registry.
The actions required by AD 2003-25-07 and retained in this AD take
about 1 work-hour per product, at an average labor rate of $85 per
work-hour. Based on these figures, the estimated cost of the actions
that were required by AD 2003-25-07 is $85 per product.
The actions required by AD 2005-13-39 and retained in this AD take
about 1 work-hour per product, at an average labor rate of $85 per
work-hour. Based on these figures, the estimated cost of the actions
that were required by AD 2005-13-39 is $85 per product.
We also estimate that it will take about 3 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 $7,230 per
product. Based on these figures, we estimate the cost of this AD on
U.S. operators to be $7,035,900, or $7,485 per product.
According to the parts manufacturer, some of the costs of this AD
may be covered under warranty, thereby reducing the cost impact on
affected individuals. We do not control warranty coverage for affected
individuals. As a result, we have included all costs in our cost
estimate.
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;
[[Page 55360]]
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:
0
a. Removing Airworthiness Directive (AD) 2003-25-07, Amendment 39-13390
(68 FR 70431, December 18, 2003); and AD 2005-13-39, Amendment 39-14176
(70 FR 38580, July 5, 2005); and
0
b. Adding the following new AD:
2016-17-03 Airbus: Docket No. FAA-2016-4226; Directorate Identifier
2015-NM-095-AD.
(a) Effective Date
This AD is effective September 23, 2016.
(b) Affected ADs
This AD replaces the ADs identified in paragraphs (b)(1) and
(b)(2) of this AD.
(1) AD 2003-25-07, Amendment 39-13390 (68 FR 70431, December 18,
2003) (``AD 2003-25-07'').
(2) AD 2005-13-39, Amendment 39-14176 (70 FR 38580, July 5,
2005) (``AD 2005-13-39'').
(c) Applicability
This AD applies to the airplanes identified in paragraphs (c)(1)
through (c)(4) of this AD, certificated in any category, all
manufacturer serial numbers.
(1) Airbus Model A318-111, -112, -121, and -122 airplanes.
(2) Airbus Model A319-111, -112, -113, -114, -115, -131, -132,
and -133 airplanes.
(3) Airbus Model A320-211, -212, -214, -231, -232, and -233
airplanes.
(4) Airbus Model A321-111, -112, -131, -211, -212, -213, -231,
and -232 airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 27, Flight
Controls.
(e) Reason
This AD was prompted by a determination that new elevator
aileron computer (ELAC) standards must be incorporated. The ELAC
standards have been upgraded to version L97+, which implements
enhanced angle-of-attack (AOA) monitoring to better detect AOA
blockage, including multiple AOA blockages. We are issuing this AD
to prevent inadvertent activation of the AOA protections.
Inadvertent activation of the AOA protections could result in a
continuous nose-down pitch rate that could result in reduced
controllability of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Replacement of ELAC L80 Units With L81 Units, With No
Changes
For Model A319 and A320 series airplanes, equipped with ELAC L80
standards having part numbers listed in Airbus Service Bulletin
A320-27-1135, dated June 29, 2001: This paragraph restates the
requirements of paragraph (b) of AD 2003-25-07, with no changes.
Within 1 year after January 22, 2004 (the effective date of AD 2003-
25-07): Replace both ELACs having L80 standards with new ELACs
having L81 standards, by doing all the actions per paragraphs A.,
B., C., and D. of the Accomplishment Instructions of Airbus Service
Bulletin A320-27-1135, dated June 29, 2001.
(h) Retained Installation of ELAC L83 or L91 Software, With No Changes
For Model A321-111, -112, -131, -211, and -231 airplanes, except
those with Airbus Modification 34043 installed in production: This
paragraph restates the requirements of paragraph (g) of AD 2005-13-
39, with no changes. Within 16 months after August 9, 2005 (the
effective date of AD 2005-13-39): Replace existing ELACs with ELACs
having L83 standards, by accomplishing all of the actions specified
in the Accomplishment Instructions of Airbus Service Bulletin A320-
27-1151, dated March 9, 2004, including Appendix 01, dated March 9,
2004; or with ELACs having L91 standards, by accomplishing all of
the actions specified in the Accomplishment Instructions of Airbus
Service Bulletin A320-27-1152, dated June 4, 2004, including
Appendix 01, dated June 4, 2004; as applicable.
(i) New Requirement of This AD: ELAC Replacement or Modification
At the applicable times specified in table 1 to paragraphs (i)
and (m)(3)(ii) of this AD: Replace each ELAC unit with an ELAC L97+
unit having part number (P/N) 3945129100 and software having P/N
3945129109, or modify existing ELAC units into ELAC L97+ units
having P/N 3945129100 with L97+ operational software P/N 3945129109
loaded, as applicable, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320-27-1243, including
Appendix 01, dated March 17, 2015. Accomplishing this replacement
terminates the actions required by paragraphs (g) and (h) of this
AD.
Table 1 to Paragraphs (i) and (m)(3)(ii) of This AD--Compliance Times
------------------------------------------------------------------------
Compliance time (after the
Airbus airplane models effective date of this AD)
------------------------------------------------------------------------
Model A318 series airplanes with UTAS Within 5 months.
(formerly Goodrich) AOA P/N 0861ED or
P/N 0861ED2 installed in all 3
positions (captain, first officer,
and standby).
Model A319 series airplanes with UTAS Within 10 months.
(formerly Goodrich) AOA P/N 0861ED or
P/N 0861ED2 installed in all 3
positions (captain, first officer,
and standby).
Model A320 series airplanes with UTAS Within 10 months.
(formerly Goodrich) AOA P/N 0861ED or
P/N 0861ED2 installed in all 3
positions (captain, first officer,
and standby).
Model A321 series airplanes with UTAS Within 5 months.
(formerly Goodrich) AOA P/N 0861ED or
P/N 0861ED2 installed in all 3
positions (captain, first officer,
and standby).
Model A318, A319, A320, and A321 Within 25 months.
series airplanes that do not have
UTAS (formerly Goodrich) AOA P/N
0861ED or P/N 0861ED2 installed in
all 3 positions (captain, first
officer, and standby).
------------------------------------------------------------------------
(j) Optional Method of Compliance
Modification of an airplane by replacing any existing ELAC unit
with an ELAC 97+ unit having P/N 3945128215, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A320-27-1244,
dated March 5, 2015, is an acceptable method of compliance for the
requirements of paragraph (i) of this AD, for only that modified
airplane. Accomplishing this modification terminates the actions
required by paragraphs (g) and (h) of this AD for that modified
airplane.
Note 1 to paragraph (j) of this AD: ELAC unit P/N 3945128215 is
not data-loadable,
[[Page 55361]]
but it is fully interchangeable and mixable with data-loadable ELAC
97+ unit P/N 3945129100 with software P/N 3945129109 loaded.
(k) Airplanes Excluded From Requirements of Paragraphs (g), (h), and
(i), and From the Actions in Paragraph (j) of This AD
Airplanes on which Airbus Modification 156546 (installation of
ELAC L97+ with software P/N 3945129109) was installed in production
are excluded from the requirements of paragraphs (g), (h), and (i)
of this AD, and from the actions specified in paragraph (j) of this
AD, provided it can be determined that no ELAC having a part number
identified in table 2 to paragraphs (k) and (m) of this AD has been
installed on that airplane since the date of issuance of the
original airworthiness certificate or the date of issuance of the
original export certificate of airworthiness.
Table 2 to Paragraphs (k) and (m) of This AD--Prohibited ELAC Part
Numbers
------------------------------------------------------------------------
Part No. Designation FIN
------------------------------------------------------------------------
3945122202.................. ELAC A320-111 Type 2 CE 1/2
Def..
3945122203.................. ELAC L50C........... 2 CE 1/2
3945122303.................. ELAC L50C........... 2 CE 1/2
3945122304.................. ELAC L60............ 2 CE 1/2
3945122305.................. ELAC L61B........... 2 CE 1/2
3945122306.................. ELAC L61F........... 2 CE 1/2
3945122307.................. ELAC L62C........... 2 CE 1/2
C12370AA01.................. ELAC L68C........... 2 CE 1/2
3945122501.................. ELAC L69............ 2 CE 1/2
3945122502.................. ELAC L69J........... 2 CE 1/2
3945122503.................. ELAC L77............ 2 CE 1/2
3945122504.................. ELAC L78............ 2 CE 1/2
3945122505.................. ELAC A L80.......... 2 CE 1/2
3945123505.................. ELAC A' L80......... 2 CE 1/2
3945128101.................. ELAC B L80.......... 2 CE 1/2
3945122506.................. ELAC A L81.......... 2 CE 1/2
3945123506.................. ELAC A' L81......... 2 CE 1/2
3945128102.................. ELAC B L81.......... 2 CE 1/2
3945122507.................. ELAC A L82.......... 2 CE 1/2
3945123507.................. ELAC A' L82......... 2 CE 1/2
3945128103.................. ELAC B L82.......... 2 CE 1/2
3945122608.................. ELAC A L83.......... 2 CE 1/2
3945123608.................. ELAC A' L83......... 2 CE 1/2
3945122609.................. ELAC A L84.......... 2 CE 1/2
3945123609.................. ELAC A' L84......... 2 CE 1/2
3945128204.................. ELAC B L90L......... 2 CE 1/2
3945128205.................. ELAC B L90N......... 2 CE 1/2
3945128206.................. ELAC B L91.......... 2 CE 1/2
3945129101.................. ELAC B L91 data 2 CE 1/2 SW1
loadable.
3945128207.................. ELAC B L92.......... 2 CE 1/2
3945128208.................. ELAC B L92L......... 2 CE 1/2
3945128209.................. ELAC B L93.......... 2 CE 1/2
3945129103.................. ELAC B L93 data 2 CE 1/2 SW1
loadable.
3945128210.................. ELAC B L94.......... 2 CE 1/2
3945129104.................. ELAC B L94 data 2 CE 1/2 SW1
loadable.
3945128212.................. ELAC B L96.......... 2 CE 1/2
3945129106.................. ELAC B L96 data 2 CE 1/2 SW1
loadable.
3945129107.................. ELAC B L96 H-A data 2 CE 1/2 SW1
loadable.
3945128214.................. ELAC B L97.......... 2 CE 1/2
3945129108.................. ELAC B L97 data 2 CE 1/2 SW1
loadable.
------------------------------------------------------------------------
(l) Later-Approved Parts
Installation of an ELAC version (part number) approved after the
effective date of this AD is an approved method of compliance with
the requirements of paragraph (i) of this AD, and the actions
specified in paragraph (j) of this AD, provided the requirements
specified in paragraphs (l)(1) and (l)(2) of this AD are met.
(1) The version (part number) must be 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).
(2) The installation must be done using a method approved by the
Manager, International Branch, ANM-116, Transport Airplane
Directorate, FAA; or the EASA; or Airbus's EASA DOA.
(m) Parts Installation Limitation
As of the applicable time specified in paragraph (m)(1) or
(m)(2) of this AD, do not install on any airplane an ELAC unit
having a part number identified in table 2 to paragraphs (k) and (m)
of this AD, except as specified in paragraph (m)(3) of this AD.
(1) For an airplane that, as of the effective date of this AD,
has any ELAC unit installed having a part number identified in table
2 to paragraphs (k) and (m) of this AD: After modification of that
airplane as required by paragraph (i) of this AD, or as specified in
paragraph (j) of this AD.
(2) For an airplane that, as of the effective date of this AD,
does not have any ELAC unit installed having a part number
identified in table 2 to paragraphs (k) and (m) of this AD: As of
the effective date of this AD.
(3) As of the effective date of this AD, a data-loadable ELAC B
unit having a part number identified in table 2 to paragraphs (k)
and (m) of this AD can be installed on an airplane provided that
L97+ software P/N 3945129109 is uploaded at the applicable time
specified in paragraph (m)(3)(i) or (m)(3)(ii) of this AD.
(i) For all airplanes except those identified in paragraph
(m)(3)(ii) of this AD: Before further flight after the ELAC B unit
installation.
(ii) For airplanes that have not been modified as required by
paragraph (i) of this AD: Within the applicable compliance time
[[Page 55362]]
specified in table 1 to paragraphs (i) and (m)(3)(ii) of this AD.
(n) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, Transport Airplane Directorate FAA,
has the authority to approve AMOCs for this AD, if requested using
the procedures found in 14 CFR 39.19. In accordance with 14 CFR
39.19, send your request to your principal inspector or local Flight
Standards District Office, as appropriate. If sending information
directly to the International Branch send it to ATTN: 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.
(ii) AMOCs approved previously for AD 2003-25-07 are approved as
AMOCs for the corresponding provisions of paragraph (g) of this AD.
(iii) AMOCs approved previously for AD 2005-13-39 are approved
as AMOCs for the corresponding provisions of paragraph (h) of this
AD.
(2) Contacting the Manufacturer: As of the effective date of
this AD, for any requirement in this AD to obtain corrective actions
from a manufacturer, the action must be accomplished using a method
approved by the Manager, International Branch, ANM-116, Transport
Airplane Directorate, FAA; or the EASA; or Airbus's EASA DOA. If
approved by the DOA, the approval must include the DOA-authorized
signature.
(3) Required for Compliance (RC): If any service information
contains procedures or tests that are identified as RC, those
procedures and tests must be done to comply with this AD; any
procedures or tests that are not identified as RC are recommended.
Those procedures and tests that are not identified as RC may be
deviated from using accepted methods in accordance with the
operator's maintenance or inspection program without obtaining
approval of an AMOC, provided the procedures and tests identified as
RC can be done and the airplane can be put back in an airworthy
condition. Any substitutions or changes to procedures or tests
identified as RC require approval of an AMOC.
(o) Related Information
Refer to Mandatory Continuing Airworthiness Information (MCAI)
EASA Airworthiness Directive 2015-0088R1, including Appendix 01,
dated June 2, 2015, 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-2016-4226.
(p) 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
September 23, 2016.
(i) Airbus Service Bulletin A320-27-1243, including Appendix 01,
dated March 17, 2015.
(ii) Airbus Service Bulletin A320-27-1244, dated March 5, 2015.
(4) The following service information was approved for IBR on
August 9, 2005 (70 FR 38580, July 5, 2005).
(i) Airbus Service Bulletin A320-27-1151, including Appendix 01,
dated March 9, 2004.
(ii) Airbus Service Bulletin A320-27-1152, including Appendix
01, dated June 4, 2004.
(5) The following service information was approved for IBR on
January 22, 2004 (68 FR 70431, December 18, 2003).
(i) Airbus Service Bulletin A320-27-1135, dated June 29, 2001.
(ii) Reserved.
(6) 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.
(7) 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.
(8) 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 August 8, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2016-19486 Filed 8-18-16; 8:45 am]
BILLING CODE 4910-13-P
