Airworthiness Directives; Airbus Airplanes, 10721-10725 [2017-02662]
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10721
Proposed Rules
Federal Register
Vol. 82, No. 30
Wednesday, February 15, 2017
This section of the FEDERAL REGISTER
contains notices to the public of the proposed
issuance of rules and regulations. The
purpose of these notices is to give interested
persons an opportunity to participate in the
rule making prior to the adoption of the final
rules.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–9573; Directorate
Identifier 2016–NM–149–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to supersede
Airworthiness Directive (AD) 2015–23–
13, for all Airbus Model A318, A319,
A320, and A321 series airplanes. AD
2015–23–13 currently requires
modification of the pin programming of
the flight warning computer (FWC) to
activate the stop rudder input warning
(SRIW) logic; and an inspection to
determine the part numbers of the FWC
and the flight augmentation computer
(FAC), and replacement of the FWC and
FAC if necessary. Since we issued AD
2015–23–13, we have determined that,
for certain airplanes, additional
modification instructions must be
accomplished to allow installation of
the minimum FWC and FAC
configuration compatible with SRIW
activation. This proposed AD would, for
certain airplanes, also require
accomplishment of additional
modification instructions to install the
minimum FWC and FAC configuration
compatible with SRIW activation. We
are proposing this AD to address the
unsafe condition on these products.
DATES: We must receive comments on
this proposed AD by April 3, 2017.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
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SUMMARY:
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• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC, between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this NPRM, 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.
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–
9573; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Operations
office (telephone 800–647–5527) is in
the ADDRESSES section. Comments will
be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT:
Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA
98057–3356; telephone 425–227–1405;
fax 425–227–1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2016–9573; Directorate Identifier
2016–NM–149–AD’’ at the beginning of
your comments. We specifically invite
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comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD based on those comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
On November 9, 2015, we issued AD
2015–23–13, Amendment 39–18330 (80
FR 73099, November 24, 2015) (‘‘AD
2015–23–13’’), for all Airbus Model
A318, A319, A320, and A321 series
airplanes. AD 2015–23–13 was
prompted by a determination that, in
specific flight conditions, the allowable
load limits on the vertical tail plane
could be reached and possibly
exceeded. Exceeding allowable load
limits could result in detachment of the
vertical tail plane. AD 2015–23–13
requires modification of the pin
programming of the FWC to activate the
SRIW logic; an inspection to determine
the part numbers of the FWC and the
FAC, and replacement of the FWC and
FAC if necessary. We issued AD 2015–
23–13 to prevent detachment of the
vertical tail plane and consequent loss
of control of the airplane.
Since we issued AD 2015–23–13, we
have determined that, for certain
airplanes, additional modification
instructions must be accomplished to
allow installation of the minimum FWC
and FAC configuration compatible with
SRIW activation.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA Airworthiness
Directive 2016–0132, dated July 5, 2016;
corrected July 20, 2016 (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:
During design reviews that were conducted
following safety recommendations related to
in-service incidents and one accident on
another aircraft type, it has been determined
that, in specific flight conditions, the
allowable load limits on the vertical tail
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plane could be reached and possibly
exceeded.
This condition, if not corrected, could lead
to in-flight detachment of the vertical tail
plane, possibly resulting in loss of control of
the aeroplane.
To address this unsafe condition, Airbus
developed modifications within the flight
augmentation computer (FAC) to reduce the
vertical tail plane stress and to activate a
conditional aural warning within the flight
warning computer (FWC) to further protect
against pilot induced rudder doublets.
Consequently, EASA issued AD 2014–0217
(later revised) [which corresponds to FAA
AD 2015–23–13] to require installation and
activation of the stop rudder input warning
(SRIW) logic. In addition, that [EASA] AD
required upgrades of the FAC and FWC, to
introduce the SRIW logic and SRIW aural
capability, respectively. After modification,
the [EASA] AD prohibited (re)installation of
certain Part Number (P/N) FWC and FAC.
Since EASA AD 2014–0217R1 was issued,
Airbus made available additional
modification instructions that, for certain
aeroplanes, must be accomplished to allow
installation of the minimum FWC and FAC
configuration compatible with SRIW
activation.
For the reasons described above, this
[EASA] AD retains the requirements of EASA
AD 2014–0217R1, which is superseded, and
includes reference to modification
instructions, which must be accomplished on
certain aeroplanes.
This [EASA] AD is republished to remove
a typographical error in Appendix 1 [of the
EASA AD].
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–
9573.
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Related Service Information Under 1
CFR Part 51
Airbus has issued Service Bulletin
A320–22–1480, Revision 03, dated
October 13, 2015. This service
information describes procedures for
modifying the pin programming to
activate the SRIW logic.
Airbus has also issued the following
service information. The service
information describes procedures for
replacing FWCs and FACs. These
documents are distinct since they apply
to different airplane configurations and
software packages.
• Airbus Service Bulletin A320–22–
1375, dated January 15, 2014.
• Airbus Service Bulletin A320–22–
1427, Revision 05, including Appendix
01, dated November 24, 2014.
• Airbus Service Bulletin A320–22–
1447, Revision 03, dated April 21, 2015.
• Airbus Service Bulletin A320–22–
1454, dated February 12, 2014.
• Airbus Service Bulletin A320–22–
1461, Revision 07, including Appendix
01, dated March 23, 2015.
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• Airbus Service Bulletin A320–22–
1502, dated November 14, 2014.
• Airbus Service Bulletin A320–22–
1539, Revision 01, dated February 24,
2016.
• Airbus Service Bulletin A320–22–
1553, dated March 21, 2016.
• Airbus Service Bulletin A320–22–
1554, dated April 19, 2016.
• Airbus Service Bulletin A320–31–
1414, Revision 03, dated September 15,
2014.
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.
FAA’s Determination and Requirements
of This Proposed AD
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
bilateral agreement with the State of
Design Authority, we have been notified
of the unsafe condition described in the
MCAI and service information
referenced above. We are proposing this
AD because we evaluated all pertinent
information and determined an unsafe
condition exists and is likely to exist or
develop on other products of these same
type designs.
Costs of Compliance
We estimate that this proposed AD
affects 1,032 airplanes of U.S. registry.
The actions required by AD 2015–23–
13, and retained in this proposed AD
take about 3 work-hours per product, at
an average labor rate of $85 per workhour. Based on these figures, the
estimated cost of the actions that are
required by AD 2015–23–13 is $255 per
product.
We also estimate that it would take
about 3 work-hours per product to
comply with the basic requirements of
this proposed AD. The average labor
rate is $85 per work-hour. Based on
these figures, we estimate the cost of
this proposed AD on U.S. operators to
be $263,160, or $255 per product.
In addition, we estimate that any
necessary follow-on actions will take
about 6 work-hours (3 work-hours for an
FWC and 3 work-hours for an FAC), and
require parts costing $88,000 (FAC), for
a cost of $88,510 per product. We have
no way of determining the number of
aircraft that might need these actions.
Aviation Programs,’’ describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in ‘‘Subtitle VII,
Part A, Subpart III, Section 44701:
General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
We determined that this proposed AD
would not have federalism implications
under Executive Order 13132. This
proposed AD would not have a
substantial direct effect on the States, on
the relationship between the national
Government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify this proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in
Alaska; and
4. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
Authority for This Rulemaking
§ 39.13
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:
■
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[Amended]
2. The FAA amends § 39.13 by
removing Airworthiness Directive (AD)
2015–23–13, Amendment 39–18330 (80
FR 73099, November 24, 2015), and
adding the following new AD:
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Airbus: Docket No. FAA–2016–9573;
Directorate Identifier 2016–NM–149–AD.
(a) Comments Due Date
We must receive comments by April 3,
2017.
(b) Affected ADs
This AD replaces AD 2015–23–13,
Amendment 39–18330 (80 FR 73099,
November 24, 2015) (‘‘AD 2015–23–13’’).
(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 22, Auto Flight; 31,
Instruments.
(e) Reason
This AD was prompted by a determination
that, in specific flight conditions, the
allowable load limits on the vertical tail
plane could be reached and possibly
exceeded. Exceeding allowable load limits
could result in detachment of the vertical tail
plane. We are issuing this AD to prevent
detachment of the vertical tail plane and
consequent loss of control of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
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(g) Retained Pin Programming Modification,
With New Service Information
This paragraph restates the requirements of
paragraph (g) of AD 2015–23–13, with new
service information. Within 48 months after
December 29, 2015 (the effective date of AD
2015–23–13), modify the pin programming to
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activate the stop rudder input warning
(SRIW) logic, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–22–1480, Revision 02,
dated March 30, 2015; or Airbus Service
Bulletin A320–22–1480, Revision 03, dated
October 13, 2015. As of the effective date of
this AD, use only Airbus Service Bulletin
A320–22–1480, Revision 03, dated October
13, 2015.
(h) Retained Inspection To Determine Part
Numbers (P/Ns), Flight Warning Computer
(FWC) and Flight Augmentation Computer
(FAC) Replacement, With New Replacement
Part Numbers
This paragraph restates the requirements of
paragraph (h) of AD 2015–23–13, with new
replacement part numbers. Prior to or
concurrently with the actions required by
paragraph (g) of this AD: Inspect the part
numbers of the FWC and the FAC installed
on the airplane. If any FWC or FAC having
a part number identified in paragraph (h)(1)
or (h)(2) of this AD, as applicable, is installed
on an airplane, prior to or concurrently with
the actions required by paragraph (g) of this
AD, replace all affected FWCs and FACs with
a unit having a part number identified in
figure 1 to paragraph (h)(3) of this AD, in
accordance with the Accomplishment
Instructions of the applicable Airbus service
information specified in paragraph (i) of this
AD. As of the effective date of this AD, use
only figure 1 to paragraph (h)(3) of this AD
to identify the replacement part numbers.
(1) Paragraphs (h)(1)(i) through (h)(1)(xvii)
of this AD identify FWCs having part
numbers that are non-compatible with the
SRIW activation required by paragraph (g) of
this AD.
(i) 350E017238484 (H1–D1).
(ii) 350E053020303 (H2–E3).
(iii) 350E016187171 (C5).
(iv) 350E053020404 (H2–E4).
(v) 350E017248685 (H1–D2).
(vi) 350E053020606 (H2–F2).
(vii) 350E017251414 (H1–E1).
(viii) 350E053020707 (H2–F3).
(ix) 350E017271616 (H1–E2).
(x) 350E053021010 (H2–F3P).
(xi) 350E018291818 (H1–E3CJ).
(xii) 350E053020808 (H2–F4).
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(xiii) 350E018301919 (H1–E3P).
(xiv) 350E053020909 (H2–F5).
(xv) 350E018312020 (H1–E3Q).
(xvi) 350E053021111 (H2–F6).
(xvii) 350E053020202 (H2–E2).
(2) Paragraphs (h)(2)(i) through
(h)(2)(xxxiv) of this AD identify FACs having
part numbers that are non-compatible with
the SRIW activation required by paragraph
(g) of this AD.
(i) B397AAM0202.
(ii) B397BAM0101.
(iii) B397BAM0512.
(iv) B397AAM0301.
(v) B397BAM0202.
(vi) B397BAM0513.
(vii) B397AAM0302.
(viii) B397BAM0203.
(ix) B397BAM0514.
(x) B397AAM0303.
(xi) B397BAM0305.
(xii) B397BAM0515.
(xiii) B397AAM0404.
(xiv) B397BAM0406.
(xv) B397BAM0616.
(xvi) B397AAM0405.
(xvii) B397BAM0407.
(xviii) B397BAM0617.
(xix) B397AAM0506.
(xx) B397BAM0507.
(xxi) B397BAM0618.
(xxii) B397AAM0507.
(xxiii) B397BAM0508.
(xxiv) B397BAM0619.
(xxv) B397AAM0508.
(xxvi) B397BAM0509.
(xxvii) B397BAM0620.
(xxviii) B397AAM0509.
(xxix) B397BAM0510.
(xxx) B397CAM0101.
(xxxi) B397AAM0510.
(xxxii) B397BAM0511.
(xxxiii) B397CAM0102.
(xxxiv) Soft P/N G2856AAA01 installed on
hard P/N C13206AA00.
(3) As of the effective date of this AD,
figure 1 to paragraph (h)(3) of this AD
identifies the FACs and FWCs having the
part numbers that are compatible with SRIW
activation required by paragraph (g) of this
AD.
BILLING CODE 4910–13–P
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BILLING CODE 4910–13–C
(i) Retained Service Information for Actions
Required by Paragraph (h) of This AD, With
New Service Information
This paragraph restates the requirements of
paragraph (i) of AD 2015–23–13, with new
service information. Do the actions required
by paragraph (h) of this AD in accordance
with the Accomplishment Instructions of the
applicable Airbus service information
specified in paragraphs (i)(1) through (i)(10)
of this AD.
(1) Airbus Service Bulletin A320–22–1375,
dated January 15, 2014 (FAC 621 hard B).
(2) Airbus Service Bulletin A320–22–1427,
Revision 05, including Appendix 01, dated
November 24, 2014 (FAC 622 hard B).
(3) Airbus Service Bulletin A320–22–1447,
Revision 03, dated April 21, 2015 (FAC
CAA02 hard C).
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(4) Airbus Service Bulletin A320–22–1454,
dated February 12, 2014 (FAC CAA02).
(5) Airbus Service Bulletin A320–22–1461,
Revision 07, including Appendix 01, dated
March 23, 2015 (FAC 623 hard B).
(6) Airbus Service Bulletin A320–22–1502,
dated November 14, 2014 (FAC CAA02).
(7) Airbus Service Bulletin A320–22–1539,
Revision 01, dated February 24, 2016 (FAC
CAA03).
(8) Airbus Service Bulletin A320–22–1553,
dated March 21, 2016 (FAC B624).
(9) Airbus Service Bulletin A320–22–1554,
dated April 19, 2016 (FAC CAA03).
(10) Airbus Service Bulletin A320–31–
1414, Revision 03, dated September 15, 2014
(FWC H–F7).
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(j) Retained Exclusion From Actions
Required by Paragraphs (g) and (h) of This
AD, With No Changes
This paragraph restates the requirements of
paragraph (j) of AD 2015–23–13, with no
changes. An airplane on which Airbus
Modification 154473 has been embodied in
production is excluded from the
requirements of paragraphs (g) and (h) of this
AD, provided that within 30 days after
December 29, 2015 (the effective date of AD
2015–23–13), an inspection of the part
numbers of the FWC and the FAC installed
on the airplane is done to determine that no
FWC having a part number listed in
paragraph (h)(1) of this AD, and no FAC
having a part number listed in paragraph
(h)(2) of this AD, has been installed on that
airplane since date of manufacture. A review
of airplane maintenance records is acceptable
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in lieu of this inspection if the part numbers
of the FWC and FAC can be conclusively
determined from that review. If any FWC or
FAC having a part number identified in
paragraph (h)(1) or (h)(2) of this AD, as
applicable, is installed on a post Airbus
Modification 154473 airplane: Within 30
days after December 29, 2015, do the
replacement required by paragraph (h) of this
AD.
(k) Retained Parts Installation Prohibitions,
With New Requirements
This paragraph restates the parts
installation prohibitions specified in
paragraph (k) of AD 2015–23–13, with new
requirements.
(1) After modification of an airplane as
required by paragraphs (g), (h), or (j) of this
AD: Do not install on that airplane any FWC
having a part number listed in paragraph
(h)(1) of this AD or any FAC having a part
number listed in paragraph (h)(2) of this AD.
(2) For an airplane that does not have a
FWC having a part number listed in
paragraph (h)(1) of this AD and does not have
a FAC having a part number listed in
paragraph (h)(2) of this AD: As of the
effective date of this AD, do not install a
FWC having a part number listed in
paragraph (h)(1) of this AD or a FAC having
a part number listed in paragraph (h)(2) of
this AD.
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(l) Retained Later Approved Parts, With a
Different Effective Date
This paragraph restates the requirements of
paragraph (l) of AD 2015–23–13, with a
different effective date. Installation of a
version (part number) of the FWC or FAC
approved after March 5, 2015 (the effective
date of European Aviation Safety Agency
(EASA) AD 2014–0217R1), is an approved
method of compliance with the requirements
of paragraph (h) or (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 EASA; or Airbus’s EASA
Design Organization Approval (DOA).
(2) The installation 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.
(m) Credit for Previous Actions
(1) This paragraph restates the credit
provided by paragraph (m)(1) of AD 2015–
23–13. This paragraph provides credit for
actions required by paragraph (g) of this AD,
if those actions were performed before
December 29, 2015 (the effective date of AD
2015–23–13) using the service information
specified in paragraphs (m)(1)(i) or (m)(1)(ii)
of this AD.
(i) Airbus Service Bulletin A320–22–1480,
dated July 9, 2014.
(ii) Airbus Service Bulletin A320–22–1480,
Revision 01, dated February 6, 2015.
(2) This paragraph provides credit for
actions required by paragraph (g) of this AD,
if those actions were performed before the
effective date of this AD using Airbus Service
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Bulletin A320–22–1480, Revision 02, dated
March 30, 2015.
(3) This paragraph restates the credit
provided by paragraph (m)(2) of AD 2015–
23–13. This paragraph provides credit for
actions required by paragraph (i) of this AD,
if those actions were performed before
December 29, 2015 (the effective date of AD
2015–23–13) using the applicable Airbus
service information identified in paragraphs
(m)(3)(i) through (m)(3)(xviii) of this AD.
(i) Airbus Service Bulletin A320–22–1427,
dated January 25, 2013.
(ii) Airbus Service Bulletin A320–22–1427,
Revision 01, dated July 30, 2013.
(iii) Airbus Service Bulletin A320–22–
1427, Revision 02, dated October 14, 2013.
(iv) Airbus Service Bulletin A320–22–
1427, Revision 03, dated November 8, 2013.
(v) Airbus Service Bulletin A320–22–1427,
Revision 04, dated February 11, 2014.
(vi) Airbus Service Bulletin A320–22–
1447, dated October 18, 2013.
(vii) Airbus Service Bulletin A320–22–
1447, Revision 01, dated September 18, 2014.
(viii) Airbus Service Bulletin A320–22–
1447, Revision 02, dated December 2, 2014.
(ix) Airbus Service Bulletin A320–22–
1461, dated October 31, 2013.
(x) Airbus Service Bulletin A320–22–1461,
Revision 01, dated February 25, 2014.
(xi) Airbus Service Bulletin A320–22–
1461, Revision 02, dated April 30, 2014.
(xii) Airbus Service Bulletin A320–22–
1461, Revision 03, dated July 17, 2014.
(xiii) Airbus Service Bulletin A320–22–
1461, Revision 04, dated September 15, 2014.
(xiv) Airbus Service Bulletin A320–22–
1461, Revision 05, dated November 13, 2014.
(xv) Airbus Service Bulletin A320–22–
1461, Revision 06, dated January 21, 2015.
(xvi) Airbus Service Bulletin A320–31–
1414, dated December 19, 2012.
(xvii) Airbus Service Bulletin A320–31–
1414, Revision 01, dated March 21, 2013.
(xviii) Airbus Service Bulletin A320–31–
1414, Revision 02, dated July 30, 2013.
(4) 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 A320–22–1539, dated December 28,
2015.
(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,
PO 00000
Frm 00005
Fmt 4702
Sfmt 9990
10725
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
(ii) AMOCs approved previously for 2015–
23–13, are approved as AMOCs for the
corresponding provisions 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
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2016–0132, dated
July 5, 2016; corrected July 20, 2016; 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–2016–9573.
(2) For service information identified in
this AD, contact Airbus, Airworthiness
Office—EIAS, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France;
telephone +33 5 61 93 36 96; fax +33 5 61
93 44 51; email account.airworth-eas@
airbus.com; Internet https://www.airbus.com.
You may view this service information at the
FAA, Transport Airplane Directorate, 1601
Lind Avenue SW., Renton, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
Issued in Renton, Washington, on January
27, 2017.
Dionne Palermo,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2017–02662 Filed 2–14–17; 8:45 am]
BILLING CODE 4910–13–P
E:\FR\FM\15FEP1.SGM
15FEP1
Agencies
[Federal Register Volume 82, Number 30 (Wednesday, February 15, 2017)]
[Proposed Rules]
[Pages 10721-10725]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-02662]
========================================================================
Proposed Rules
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.
========================================================================
Federal Register / Vol. 82, No. 30 / Wednesday, February 15, 2017 /
Proposed Rules
[[Page 10721]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2016-9573; Directorate Identifier 2016-NM-149-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to supersede Airworthiness Directive (AD) 2015-23-
13, for all Airbus Model A318, A319, A320, and A321 series airplanes.
AD 2015-23-13 currently requires modification of the pin programming of
the flight warning computer (FWC) to activate the stop rudder input
warning (SRIW) logic; and an inspection to determine the part numbers
of the FWC and the flight augmentation computer (FAC), and replacement
of the FWC and FAC if necessary. Since we issued AD 2015-23-13, we have
determined that, for certain airplanes, additional modification
instructions must be accomplished to allow installation of the minimum
FWC and FAC configuration compatible with SRIW activation. This
proposed AD would, for certain airplanes, also require accomplishment
of additional modification instructions to install the minimum FWC and
FAC configuration compatible with SRIW activation. We are proposing
this AD to address the unsafe condition on these products.
DATES: We must receive comments on this proposed AD by April 3, 2017.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
For service information identified in this NPRM, 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.
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-
9573; or in person at the Docket Management Facility between 9 a.m. and
5 p.m., Monday through Friday, except Federal holidays. The AD docket
contains this proposed AD, the regulatory evaluation, any comments
received, and other information. The street address for the Docket
Operations office (telephone 800-647-5527) is in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405;
fax 425-227-1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2016-9573;
Directorate Identifier 2016-NM-149-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD based on those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
On November 9, 2015, we issued AD 2015-23-13, Amendment 39-18330
(80 FR 73099, November 24, 2015) (``AD 2015-23-13''), for all Airbus
Model A318, A319, A320, and A321 series airplanes. AD 2015-23-13 was
prompted by a determination that, in specific flight conditions, the
allowable load limits on the vertical tail plane could be reached and
possibly exceeded. Exceeding allowable load limits could result in
detachment of the vertical tail plane. AD 2015-23-13 requires
modification of the pin programming of the FWC to activate the SRIW
logic; an inspection to determine the part numbers of the FWC and the
FAC, and replacement of the FWC and FAC if necessary. We issued AD
2015-23-13 to prevent detachment of the vertical tail plane and
consequent loss of control of the airplane.
Since we issued AD 2015-23-13, we have determined that, for certain
airplanes, additional modification instructions must be accomplished to
allow installation of the minimum FWC and FAC configuration compatible
with SRIW activation.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA
Airworthiness Directive 2016-0132, dated July 5, 2016; corrected July
20, 2016 (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:
During design reviews that were conducted following safety
recommendations related to in-service incidents and one accident on
another aircraft type, it has been determined that, in specific
flight conditions, the allowable load limits on the vertical tail
[[Page 10722]]
plane could be reached and possibly exceeded.
This condition, if not corrected, could lead to in-flight
detachment of the vertical tail plane, possibly resulting in loss of
control of the aeroplane.
To address this unsafe condition, Airbus developed modifications
within the flight augmentation computer (FAC) to reduce the vertical
tail plane stress and to activate a conditional aural warning within
the flight warning computer (FWC) to further protect against pilot
induced rudder doublets.
Consequently, EASA issued AD 2014-0217 (later revised) [which
corresponds to FAA AD 2015-23-13] to require installation and
activation of the stop rudder input warning (SRIW) logic. In
addition, that [EASA] AD required upgrades of the FAC and FWC, to
introduce the SRIW logic and SRIW aural capability, respectively.
After modification, the [EASA] AD prohibited (re)installation of
certain Part Number (P/N) FWC and FAC.
Since EASA AD 2014-0217R1 was issued, Airbus made available
additional modification instructions that, for certain aeroplanes,
must be accomplished to allow installation of the minimum FWC and
FAC configuration compatible with SRIW activation.
For the reasons described above, this [EASA] AD retains the
requirements of EASA AD 2014-0217R1, which is superseded, and
includes reference to modification instructions, which must be
accomplished on certain aeroplanes.
This [EASA] AD is republished to remove a typographical error in
Appendix 1 [of the EASA AD].
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-
9573.
Related Service Information Under 1 CFR Part 51
Airbus has issued Service Bulletin A320-22-1480, Revision 03, dated
October 13, 2015. This service information describes procedures for
modifying the pin programming to activate the SRIW logic.
Airbus has also issued the following service information. The
service information describes procedures for replacing FWCs and FACs.
These documents are distinct since they apply to different airplane
configurations and software packages.
Airbus Service Bulletin A320-22-1375, dated January 15,
2014.
Airbus Service Bulletin A320-22-1427, Revision 05,
including Appendix 01, dated November 24, 2014.
Airbus Service Bulletin A320-22-1447, Revision 03, dated
April 21, 2015.
Airbus Service Bulletin A320-22-1454, dated February 12,
2014.
Airbus Service Bulletin A320-22-1461, Revision 07,
including Appendix 01, dated March 23, 2015.
Airbus Service Bulletin A320-22-1502, dated November 14,
2014.
Airbus Service Bulletin A320-22-1539, Revision 01, dated
February 24, 2016.
Airbus Service Bulletin A320-22-1553, dated March 21,
2016.
Airbus Service Bulletin A320-22-1554, dated April 19,
2016.
Airbus Service Bulletin A320-31-1414, Revision 03, dated
September 15, 2014.
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.
FAA's Determination and Requirements of This Proposed AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all pertinent information and determined an unsafe condition
exists and is likely to exist or develop on other products of these
same type designs.
Costs of Compliance
We estimate that this proposed AD affects 1,032 airplanes of U.S.
registry.
The actions required by AD 2015-23-13, and retained in this
proposed AD take about 3 work-hours per product, at an average labor
rate of $85 per work-hour. Based on these figures, the estimated cost
of the actions that are required by AD 2015-23-13 is $255 per product.
We also estimate that it would take about 3 work-hours per product
to comply with the basic requirements of this proposed AD. The average
labor rate is $85 per work-hour. Based on these figures, we estimate
the cost of this proposed AD on U.S. operators to be $263,160, or $255
per product.
In addition, we estimate that any necessary follow-on actions will
take about 6 work-hours (3 work-hours for an FWC and 3 work-hours for
an FAC), and require parts costing $88,000 (FAC), for a cost of $88,510
per product. We have no way of determining the number of aircraft that
might need these actions.
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 proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify this proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in Alaska; and
4. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD)
2015-23-13, Amendment 39-18330 (80 FR 73099, November 24, 2015), and
adding the following new AD:
[[Page 10723]]
Airbus: Docket No. FAA-2016-9573; Directorate Identifier 2016-NM-
149-AD.
(a) Comments Due Date
We must receive comments by April 3, 2017.
(b) Affected ADs
This AD replaces AD 2015-23-13, Amendment 39-18330 (80 FR 73099,
November 24, 2015) (``AD 2015-23-13'').
(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 22, Auto Flight;
31, Instruments.
(e) Reason
This AD was prompted by a determination that, in specific flight
conditions, the allowable load limits on the vertical tail plane
could be reached and possibly exceeded. Exceeding allowable load
limits could result in detachment of the vertical tail plane. We are
issuing this AD to prevent detachment of the vertical tail plane and
consequent loss of control of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Pin Programming Modification, With New Service Information
This paragraph restates the requirements of paragraph (g) of AD
2015-23-13, with new service information. Within 48 months after
December 29, 2015 (the effective date of AD 2015-23-13), modify the
pin programming to activate the stop rudder input warning (SRIW)
logic, in accordance with the Accomplishment Instructions of Airbus
Service Bulletin A320-22-1480, Revision 02, dated March 30, 2015; or
Airbus Service Bulletin A320-22-1480, Revision 03, dated October 13,
2015. As of the effective date of this AD, use only Airbus Service
Bulletin A320-22-1480, Revision 03, dated October 13, 2015.
(h) Retained Inspection To Determine Part Numbers (P/Ns), Flight
Warning Computer (FWC) and Flight Augmentation Computer (FAC)
Replacement, With New Replacement Part Numbers
This paragraph restates the requirements of paragraph (h) of AD
2015-23-13, with new replacement part numbers. Prior to or
concurrently with the actions required by paragraph (g) of this AD:
Inspect the part numbers of the FWC and the FAC installed on the
airplane. If any FWC or FAC having a part number identified in
paragraph (h)(1) or (h)(2) of this AD, as applicable, is installed
on an airplane, prior to or concurrently with the actions required
by paragraph (g) of this AD, replace all affected FWCs and FACs with
a unit having a part number identified in figure 1 to paragraph
(h)(3) of this AD, in accordance with the Accomplishment
Instructions of the applicable Airbus service information specified
in paragraph (i) of this AD. As of the effective date of this AD,
use only figure 1 to paragraph (h)(3) of this AD to identify the
replacement part numbers.
(1) Paragraphs (h)(1)(i) through (h)(1)(xvii) of this AD
identify FWCs having part numbers that are non-compatible with the
SRIW activation required by paragraph (g) of this AD.
(i) 350E017238484 (H1-D1).
(ii) 350E053020303 (H2-E3).
(iii) 350E016187171 (C5).
(iv) 350E053020404 (H2-E4).
(v) 350E017248685 (H1-D2).
(vi) 350E053020606 (H2-F2).
(vii) 350E017251414 (H1-E1).
(viii) 350E053020707 (H2-F3).
(ix) 350E017271616 (H1-E2).
(x) 350E053021010 (H2-F3P).
(xi) 350E018291818 (H1-E3CJ).
(xii) 350E053020808 (H2-F4).
(xiii) 350E018301919 (H1-E3P).
(xiv) 350E053020909 (H2-F5).
(xv) 350E018312020 (H1-E3Q).
(xvi) 350E053021111 (H2-F6).
(xvii) 350E053020202 (H2-E2).
(2) Paragraphs (h)(2)(i) through (h)(2)(xxxiv) of this AD
identify FACs having part numbers that are non-compatible with the
SRIW activation required by paragraph (g) of this AD.
(i) B397AAM0202.
(ii) B397BAM0101.
(iii) B397BAM0512.
(iv) B397AAM0301.
(v) B397BAM0202.
(vi) B397BAM0513.
(vii) B397AAM0302.
(viii) B397BAM0203.
(ix) B397BAM0514.
(x) B397AAM0303.
(xi) B397BAM0305.
(xii) B397BAM0515.
(xiii) B397AAM0404.
(xiv) B397BAM0406.
(xv) B397BAM0616.
(xvi) B397AAM0405.
(xvii) B397BAM0407.
(xviii) B397BAM0617.
(xix) B397AAM0506.
(xx) B397BAM0507.
(xxi) B397BAM0618.
(xxii) B397AAM0507.
(xxiii) B397BAM0508.
(xxiv) B397BAM0619.
(xxv) B397AAM0508.
(xxvi) B397BAM0509.
(xxvii) B397BAM0620.
(xxviii) B397AAM0509.
(xxix) B397BAM0510.
(xxx) B397CAM0101.
(xxxi) B397AAM0510.
(xxxii) B397BAM0511.
(xxxiii) B397CAM0102.
(xxxiv) Soft P/N G2856AAA01 installed on hard P/N C13206AA00.
(3) As of the effective date of this AD, figure 1 to paragraph
(h)(3) of this AD identifies the FACs and FWCs having the part
numbers that are compatible with SRIW activation required by
paragraph (g) of this AD.
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[[Page 10724]]
[GRAPHIC] [TIFF OMITTED] TP15FE17.001
BILLING CODE 4910-13-C
(i) Retained Service Information for Actions Required by Paragraph (h)
of This AD, With New Service Information
This paragraph restates the requirements of paragraph (i) of AD
2015-23-13, with new service information. Do the actions required by
paragraph (h) of this AD in accordance with the Accomplishment
Instructions of the applicable Airbus service information specified
in paragraphs (i)(1) through (i)(10) of this AD.
(1) Airbus Service Bulletin A320-22-1375, dated January 15, 2014
(FAC 621 hard B).
(2) Airbus Service Bulletin A320-22-1427, Revision 05, including
Appendix 01, dated November 24, 2014 (FAC 622 hard B).
(3) Airbus Service Bulletin A320-22-1447, Revision 03, dated
April 21, 2015 (FAC CAA02 hard C).
(4) Airbus Service Bulletin A320-22-1454, dated February 12,
2014 (FAC CAA02).
(5) Airbus Service Bulletin A320-22-1461, Revision 07, including
Appendix 01, dated March 23, 2015 (FAC 623 hard B).
(6) Airbus Service Bulletin A320-22-1502, dated November 14,
2014 (FAC CAA02).
(7) Airbus Service Bulletin A320-22-1539, Revision 01, dated
February 24, 2016 (FAC CAA03).
(8) Airbus Service Bulletin A320-22-1553, dated March 21, 2016
(FAC B624).
(9) Airbus Service Bulletin A320-22-1554, dated April 19, 2016
(FAC CAA03).
(10) Airbus Service Bulletin A320-31-1414, Revision 03, dated
September 15, 2014 (FWC H-F7).
(j) Retained Exclusion From Actions Required by Paragraphs (g) and (h)
of This AD, With No Changes
This paragraph restates the requirements of paragraph (j) of AD
2015-23-13, with no changes. An airplane on which Airbus
Modification 154473 has been embodied in production is excluded from
the requirements of paragraphs (g) and (h) of this AD, provided that
within 30 days after December 29, 2015 (the effective date of AD
2015-23-13), an inspection of the part numbers of the FWC and the
FAC installed on the airplane is done to determine that no FWC
having a part number listed in paragraph (h)(1) of this AD, and no
FAC having a part number listed in paragraph (h)(2) of this AD, has
been installed on that airplane since date of manufacture. A review
of airplane maintenance records is acceptable
[[Page 10725]]
in lieu of this inspection if the part numbers of the FWC and FAC
can be conclusively determined from that review. If any FWC or FAC
having a part number identified in paragraph (h)(1) or (h)(2) of
this AD, as applicable, is installed on a post Airbus Modification
154473 airplane: Within 30 days after December 29, 2015, do the
replacement required by paragraph (h) of this AD.
(k) Retained Parts Installation Prohibitions, With New Requirements
This paragraph restates the parts installation prohibitions
specified in paragraph (k) of AD 2015-23-13, with new requirements.
(1) After modification of an airplane as required by paragraphs
(g), (h), or (j) of this AD: Do not install on that airplane any FWC
having a part number listed in paragraph (h)(1) of this AD or any
FAC having a part number listed in paragraph (h)(2) of this AD.
(2) For an airplane that does not have a FWC having a part
number listed in paragraph (h)(1) of this AD and does not have a FAC
having a part number listed in paragraph (h)(2) of this AD: As of
the effective date of this AD, do not install a FWC having a part
number listed in paragraph (h)(1) of this AD or a FAC having a part
number listed in paragraph (h)(2) of this AD.
(l) Retained Later Approved Parts, With a Different Effective Date
This paragraph restates the requirements of paragraph (l) of AD
2015-23-13, with a different effective date. Installation of a
version (part number) of the FWC or FAC approved after March 5, 2015
(the effective date of European Aviation Safety Agency (EASA) AD
2014-0217R1), is an approved method of compliance with the
requirements of paragraph (h) or (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 EASA; or Airbus's EASA Design Organization Approval (DOA).
(2) The installation 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.
(m) Credit for Previous Actions
(1) This paragraph restates the credit provided by paragraph
(m)(1) of AD 2015-23-13. This paragraph provides credit for actions
required by paragraph (g) of this AD, if those actions were
performed before December 29, 2015 (the effective date of AD 2015-
23-13) using the service information specified in paragraphs
(m)(1)(i) or (m)(1)(ii) of this AD.
(i) Airbus Service Bulletin A320-22-1480, dated July 9, 2014.
(ii) Airbus Service Bulletin A320-22-1480, Revision 01, dated
February 6, 2015.
(2) This paragraph provides credit for actions required by
paragraph (g) of this AD, if those actions were performed before the
effective date of this AD using Airbus Service Bulletin A320-22-
1480, Revision 02, dated March 30, 2015.
(3) This paragraph restates the credit provided by paragraph
(m)(2) of AD 2015-23-13. This paragraph provides credit for actions
required by paragraph (i) of this AD, if those actions were
performed before December 29, 2015 (the effective date of AD 2015-
23-13) using the applicable Airbus service information identified in
paragraphs (m)(3)(i) through (m)(3)(xviii) of this AD.
(i) Airbus Service Bulletin A320-22-1427, dated January 25,
2013.
(ii) Airbus Service Bulletin A320-22-1427, Revision 01, dated
July 30, 2013.
(iii) Airbus Service Bulletin A320-22-1427, Revision 02, dated
October 14, 2013.
(iv) Airbus Service Bulletin A320-22-1427, Revision 03, dated
November 8, 2013.
(v) Airbus Service Bulletin A320-22-1427, Revision 04, dated
February 11, 2014.
(vi) Airbus Service Bulletin A320-22-1447, dated October 18,
2013.
(vii) Airbus Service Bulletin A320-22-1447, Revision 01, dated
September 18, 2014.
(viii) Airbus Service Bulletin A320-22-1447, Revision 02, dated
December 2, 2014.
(ix) Airbus Service Bulletin A320-22-1461, dated October 31,
2013.
(x) Airbus Service Bulletin A320-22-1461, Revision 01, dated
February 25, 2014.
(xi) Airbus Service Bulletin A320-22-1461, Revision 02, dated
April 30, 2014.
(xii) Airbus Service Bulletin A320-22-1461, Revision 03, dated
July 17, 2014.
(xiii) Airbus Service Bulletin A320-22-1461, Revision 04, dated
September 15, 2014.
(xiv) Airbus Service Bulletin A320-22-1461, Revision 05, dated
November 13, 2014.
(xv) Airbus Service Bulletin A320-22-1461, Revision 06, dated
January 21, 2015.
(xvi) Airbus Service Bulletin A320-31-1414, dated December 19,
2012.
(xvii) Airbus Service Bulletin A320-31-1414, Revision 01, dated
March 21, 2013.
(xviii) Airbus Service Bulletin A320-31-1414, Revision 02, dated
July 30, 2013.
(4) 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 A320-22-
1539, dated December 28, 2015.
(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 2015-23-13, are approved as
AMOCs for the corresponding provisions 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
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2016-0132, dated July 5, 2016;
corrected July 20, 2016; 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-2016-9573.
(2) For service information identified in this AD, contact
Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5
61 93 44 51; email account.airworth-eas@airbus.com; Internet https://www.airbus.com. You may view this service information at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA.
For information on the availability of this material at the FAA,
call 425-227-1221.
Issued in Renton, Washington, on January 27, 2017.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2017-02662 Filed 2-14-17; 8:45 am]
BILLING CODE 4910-13-P