Airworthiness Directives; Airbus Airplanes, 29363-29368 [2017-13407]
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29363
Rules and Regulations
Federal Register
Vol. 82, No. 124
Thursday, June 29, 2017
This section of the FEDERAL REGISTER
contains regulatory documents having general
applicability and legal effect, most of which
are keyed to and codified in the Code of
Federal Regulations, which is published under
50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by
the Superintendent of Documents.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–9573; Directorate
Identifier 2016–NM–149–AD; Amendment
39–18938; AD 2017–13–08]
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) 2015–23–
13, for all Airbus Model A318 and A319
series airplanes, Model A320–211, –212,
–214, –231, –232, and –233 airplanes,
and Model A321–111, –112, –131, –211,
–212, –213, –231, and –232 airplanes.
AD 2015–23–13 required 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. This new AD, for certain
airplanes, also requires accomplishment
of additional modification instructions
to install the minimum FWC and FAC
configuration compatible with SRIW
activation. 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. We are issuing
this AD to address the unsafe condition
on these products.
DATES: This AD is effective August 3,
2017.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of August 3, 2017.
The Director of the Federal Register
approved the incorporation by reference
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SUMMARY:
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of certain other publications listed in
this AD as of December 29, 2015 (80 FR
73099, November 24, 2015).
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–
9573.
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 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 2015–23–13,
Amendment 39–18330 (80 FR 73099,
November 24, 2015) (‘‘AD 2015–23–
13’’). AD 2015–23–13 applied to all
Airbus Model A318 and A319 series
airplanes, Model A320–211, –212, –214,
–231, –232, and –233 airplanes, and
Model A321–111, –112, –131, –211,
–212, –213, –231, and –232 airplanes.
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The NPRM published in the Federal
Register on February 15, 2017 (82 FR
10721) (‘‘the NPRM’’). The NPRM was
prompted by a determination 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 NPRM proposed to
continue to require modification of the
pin programming of the FWC to activate
the SRIW logic; and an inspection to
determine the part numbers of the FWC
and the FAC, and replacement of the
FWC and FAC if necessary. The NPRM
also proposed, for certain airplanes, to
also require accomplishment of
additional modification instructions to
install the minimum FWC and FAC
configuration compatible with SRIW
activation. We are issuing this AD to
prevent detachment of the vertical tail
plane and consequent loss of control 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 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 and A319
series airplanes, Model A320–211, –212,
–214, –231, –232, and –233 airplanes,
and Model A321–111, –112, –131, –211,
–212, –213, –231, and –232 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
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
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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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Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comments
received on the NPRM and the FAA’s
response to each comment.
Request for Technical Details
Mr. Geoffrey Barrance stated that the
public disclosure in the NPRM did not
provide sufficient technical details and
disclosure relative to the unsafe
condition; and that, presumably, the
actions required by this proposed AD
are to improve the protection provided
by the SRIW logic. Mr. Barrance noted
that the purpose of publication in the
Federal Register is to provide public
disclosure. We infer the commenter is
requesting that we provide additional
technical details.
We do not agree with the commenter’s
request. The technical details associated
with correcting the unsafe condition
were already provided in the previously
published AD, AD 2015–23–13. That
AD and all service information that was
incorporated by reference in AD 2015–
23–13 is posted on the public docket in
the Federal Docket Management System
and is available on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2015–
0251. This superseding AD only
mandates accomplishment of additional
modification instructions to ensure
design compatibility. We have not
revised this AD in this regard.
Request for Review of Design Approval
Process and Compliance Time
Determination
Mr. Geoffrey Barrance asserted that
this rulemaking action is a result of
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failure of design, development,
oversight and approval processes at the
EASA and the FAA. Mr. Barrance
asserted that the FAA must do a
comprehensive review of these
processes and evaluate the extent that
the flying public has been exposed to
risks due to delayed processes in
releasing this AD.
We do not agree with Mr. Geoffrey
Barrance’s comments. Mr. Barrance has
submitted no data to substantiate his
claims. This rulemaking action simply
supersedes a previous AD in order to
mandate accomplishment of additional
modification instructions to ensure
design compatibility. Furthermore, we
and our bilateral partner, EASA, work
closely with Airbus to ensure that
design solutions are certificated based
on applicable airworthiness regulations
prior to mandating those solutions to
mitigate safety risks. We also ensure that
all appropriate instructions and parts
are available at the appropriate time to
comply with AD requirements. As a
component of our safety management
system, we continuously evaluate our
certification system and procedures and
improve them when problems are
found. We have not revised this AD in
this regard.
Request for Compliance Time Review
The Air Line Pilots Association,
International (ALPA) stated that it
agrees with the NPRM, but requested
that we revisit the compliance
timeframe to ensure it is aligned with
the intent of the AD.
The EASA has determined the
compliance times based on the overall
risk to the fleet, including the severity
of the failure and the likelihood of the
failure’s occurrence. The FAA and
EASA worked with Airbus to ensure
that all appropriate action(s) are taken at
appropriate times to mitigate the risk to
the fleet. We have not changed this AD
in this regard.
Request for Correction of
Typographical Error
Jetblue Airways (Jetblue) requested
that we correct a typographical error in
paragraph (i)(10) of the NPRM. Jetblue
stated that it should be ‘‘FWC H2–F7,’’
not ‘‘FWC H–F7.’’
We agree with the commenter’s
request and have revised this AD
accordingly.
Request for an Alternative Method of
Compliance (AMOC)
Jetblue requested that we include an
AMOC for FWC standard H2–F9D (P/N
350E053021818) in this AD.
We do not agree to include an AMOC
in this AD because certain later
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approved parts are already addressed in
paragraph (l) of this AD. To clarify,
FWCs approved after March 5, 2015, are
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. We have not
changed this AD in this regard.
Conclusion
We reviewed the available data,
including the comments received, and
determined that air safety and the
public interest require adopting this AD
with the change described previously
and minor editorial changes. We have
determined that these 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
A320–22–1480, Revision 02, dated
March 30, 2015, and 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. These
documents are distinct due to editorial
revisions.
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
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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 will affect
1,032 airplanes of U.S. registry.
The actions required by AD 2015–23–
13, and retained in this 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 AD. The average labor rate is $85
per work-hour. Based on these figures,
we estimate the cost of this 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
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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:
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List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Airworthiness Directive (AD)
2015–23–13, Amendment 39–18330 (80
FR 73099, November 24, 2015), and
adding the following new AD:
■
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.
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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.
2017–13–08 Airbus: Amendment 39–18938;
Docket No. FAA–2016–9573; Directorate
Identifier 2016–NM–149–AD.
(a) Effective Date
This AD is effective August 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
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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).
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(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.
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(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.
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(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
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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 H2–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
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.
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(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 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)(2)(i) through (m)(2)(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.
PO 00000
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Fmt 4700
Sfmt 4700
29367
(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.
(3) 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 the
attention of the person identified in
paragraph (o)(2) of this AD. Information may
be emailed to: 9-ANM-116-AMOCREQUESTS@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
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
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Federal Register / Vol. 82, No. 124 / Thursday, June 29, 2017 / Rules and Regulations
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.
nlaroche on DSK30NT082PROD with RULES
(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 more information about this AD,
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.
(3) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (p)(5) and (p)(6) of this AD.
(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 August 3, 2017.
(i) Airbus Service Bulletin A320–22–1480,
Revision 03, dated October 13, 2015.
(ii) Airbus Service Bulletin A320–22–1539,
Revision 01, dated February 24, 2016.
(iii) Airbus Service Bulletin A320–22–
1553, dated March 21, 2016.
(iv) Airbus Service Bulletin A320–22–
1554, dated April 19, 2016.
(4) The following service information was
approved for IBR on December 29, 2015 (80
FR 73099, November 24, 2015).
(i) Airbus Service Bulletin A320–22–1375,
dated January 15, 2014.
(ii) Airbus Service Bulletin A320–22–1427,
Revision 05, including Appendix 01, dated
November 24, 2014.
(iii) Airbus Service Bulletin A320–22–
1447, Revision 03, dated April 21, 2015.
(iv) Airbus Service Bulletin A320–22–
1454, dated February 12, 2014.
(v) Airbus Service Bulletin A320–22–1461,
Revision 07, including Appendix 01, dated
March 23, 2015.
(vi) Airbus Service Bulletin A320–22–
1480, Revision 02, dated March 30, 2015.
(vii) Airbus Service Bulletin A320–22–
1502, dated November 14, 2014.
(viii) Airbus Service Bulletin A320–31–
1414, Revision 03, dated September 15, 2014.
(5) For service information identified in
this AD, contact Airbus, Airworthiness
Office—EIAS, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France;
telephone +33 5 61 93 36 96; fax +33 5 61
93 44 51; email account.airworth-eas@
airbus.com; Internet https://www.airbus.com.
(6) You may view this service information
at the FAA, Transport Airplane Directorate,
VerDate Sep<11>2014
15:31 Jun 28, 2017
Jkt 241001
1601 Lind Avenue SW., Renton, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
(7) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on June 16,
2017.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2017–13407 Filed 6–28–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–9437; Directorate
Identifier 2016–NM–131–AD; Amendment
39–18941; AD 2017–13–11]
RIN 2120–AA64
Airworthiness Directives; Gulfstream
Aerospace Corporation Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for all
Model G–IV airplanes. This AD was
prompted by a report indicating that the
G–IV gust lock system allows more
throttle travel than was intended and
could allow the throttle to be advanced
to reach take-off thrust. This AD
requires modification of the gust lock
system, and a revision of the
maintenance or inspection program to
incorporate functional tests. We are
issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective August 3,
2017.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of August 3, 2017.
ADDRESSES: For service information
identified in this final rule, contact
Gulfstream Aerospace Corporation,
Technical Publications Dept., P.O. Box
2206, Savannah, GA 31402–2206;
telephone 800–810–4853; fax 912–965–
3520; email pubs@gulfstream.com;
Internet https://www.gulfstream.com/
product_support/technical_pubs/pubs/
index.htm. You may view this
referenced service information at the
FAA, Transport Airplane Directorate,
SUMMARY:
PO 00000
Frm 00006
Fmt 4700
Sfmt 4700
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–2016–9437.
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–
9437; 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 (phone: 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:
Gideon Jose, Aerospace Engineer,
Systems and Equipment Branch, ACE–
119A, FAA, Atlanta Aircraft
Certification Office (ACO), 1701
Columbia Avenue, College Park, GA
30337; phone: 404–474–5569; fax: 404–
474–5606; email: gideon.jose@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to all Gulfstream Aerospace
Corporation Model G–IV airplanes. The
NPRM published in the Federal
Register on December 12, 2016 (81 FR
89397) (‘‘the NPRM’’). The NPRM was
prompted by a report indicating that the
G–IV gust lock system allows more
throttle travel than was intended and
could allow the throttle to be advanced
to reach take-off thrust. The intended
function of the gust lock system is to
restrict throttle lever movement to a
maximum of 6 degrees of forward travel,
which provides an unmistakable
warning to the pilot that the gust lock
system is still engaged, prohibiting the
use of the primary flight control
surfaces. The NPRM proposed to require
modification of the gust lock system,
and a revision of the maintenance or
inspection program to incorporate
functional tests. We are issuing this AD
to prevent the throttle lever movement
from advancing more than 6 degrees of
forward travel, which could result in the
aircraft reaching near take-off thrust and
high velocities without primary flight
E:\FR\FM\29JNR1.SGM
29JNR1
Agencies
[Federal Register Volume 82, Number 124 (Thursday, June 29, 2017)]
[Rules and Regulations]
[Pages 29363-29368]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-13407]
========================================================================
Rules and Regulations
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains regulatory documents
having general applicability and legal effect, most of which are keyed
to and codified in the Code of Federal Regulations, which is published
under 50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by the Superintendent of Documents.
========================================================================
Federal Register / Vol. 82, No. 124 / Thursday, June 29, 2017 / Rules
and Regulations
[[Page 29363]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2016-9573; Directorate Identifier 2016-NM-149-AD;
Amendment 39-18938; AD 2017-13-08]
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) 2015-23-13,
for all Airbus Model A318 and A319 series airplanes, Model A320-211, -
212, -214, -231, -232, and -233 airplanes, and Model A321-111, -112, -
131, -211, -212, -213, -231, and -232 airplanes. AD 2015-23-13 required
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. This new AD, for certain airplanes, also requires
accomplishment of additional modification instructions to install the
minimum FWC and FAC configuration compatible with SRIW activation. 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. We are issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective August 3, 2017.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of August 3,
2017.
The Director of the Federal Register approved the incorporation by
reference of certain other publications listed in this AD as of
December 29, 2015 (80 FR 73099, November 24, 2015).
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-
9573.
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 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 2015-23-13, Amendment 39-18330 (80 FR 73099,
November 24, 2015) (``AD 2015-23-13''). AD 2015-23-13 applied to all
Airbus Model A318 and A319 series airplanes, Model A320-211, -212, -
214, -231, -232, and -233 airplanes, and Model A321-111, -112, -131, -
211, -212, -213, -231, and -232 airplanes. The NPRM published in the
Federal Register on February 15, 2017 (82 FR 10721) (``the NPRM''). The
NPRM was prompted by a determination 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 NPRM proposed to continue to require modification
of the pin programming of the FWC to activate the SRIW logic; and an
inspection to determine the part numbers of the FWC and the FAC, and
replacement of the FWC and FAC if necessary. The NPRM also proposed,
for certain airplanes, to also require accomplishment of additional
modification instructions to install the minimum FWC and FAC
configuration compatible with SRIW activation. We are issuing this AD
to prevent detachment of the vertical tail plane and consequent loss of
control 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 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 and A319 series airplanes, Model
A320-211, -212, -214, -231, -232, and -233 airplanes, and Model A321-
111, -112, -131, -211, -212, -213, -231, and -232 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
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
[[Page 29364]]
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.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the NPRM and
the FAA's response to each comment.
Request for Technical Details
Mr. Geoffrey Barrance stated that the public disclosure in the NPRM
did not provide sufficient technical details and disclosure relative to
the unsafe condition; and that, presumably, the actions required by
this proposed AD are to improve the protection provided by the SRIW
logic. Mr. Barrance noted that the purpose of publication in the
Federal Register is to provide public disclosure. We infer the
commenter is requesting that we provide additional technical details.
We do not agree with the commenter's request. The technical details
associated with correcting the unsafe condition were already provided
in the previously published AD, AD 2015-23-13. That AD and all service
information that was incorporated by reference in AD 2015-23-13 is
posted on the public docket in the Federal Docket Management System and
is available on the Internet at https://www.regulations.gov by searching
for and locating Docket No. FAA-2015-0251. This superseding AD only
mandates accomplishment of additional modification instructions to
ensure design compatibility. We have not revised this AD in this
regard.
Request for Review of Design Approval Process and Compliance Time
Determination
Mr. Geoffrey Barrance asserted that this rulemaking action is a
result of failure of design, development, oversight and approval
processes at the EASA and the FAA. Mr. Barrance asserted that the FAA
must do a comprehensive review of these processes and evaluate the
extent that the flying public has been exposed to risks due to delayed
processes in releasing this AD.
We do not agree with Mr. Geoffrey Barrance's comments. Mr. Barrance
has submitted no data to substantiate his claims. This rulemaking
action simply supersedes a previous AD in order to mandate
accomplishment of additional modification instructions to ensure design
compatibility. Furthermore, we and our bilateral partner, EASA, work
closely with Airbus to ensure that design solutions are certificated
based on applicable airworthiness regulations prior to mandating those
solutions to mitigate safety risks. We also ensure that all appropriate
instructions and parts are available at the appropriate time to comply
with AD requirements. As a component of our safety management system,
we continuously evaluate our certification system and procedures and
improve them when problems are found. We have not revised this AD in
this regard.
Request for Compliance Time Review
The Air Line Pilots Association, International (ALPA) stated that
it agrees with the NPRM, but requested that we revisit the compliance
timeframe to ensure it is aligned with the intent of the AD.
The EASA has determined the compliance times based on the overall
risk to the fleet, including the severity of the failure and the
likelihood of the failure's occurrence. The FAA and EASA worked with
Airbus to ensure that all appropriate action(s) are taken at
appropriate times to mitigate the risk to the fleet. We have not
changed this AD in this regard.
Request for Correction of Typographical Error
Jetblue Airways (Jetblue) requested that we correct a typographical
error in paragraph (i)(10) of the NPRM. Jetblue stated that it should
be ``FWC H2-F7,'' not ``FWC H-F7.''
We agree with the commenter's request and have revised this AD
accordingly.
Request for an Alternative Method of Compliance (AMOC)
Jetblue requested that we include an AMOC for FWC standard H2-F9D
(P/N 350E053021818) in this AD.
We do not agree to include an AMOC in this AD because certain later
approved parts are already addressed in paragraph (l) of this AD. To
clarify, FWCs approved after March 5, 2015, are 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. We have not changed this AD in this regard.
Conclusion
We reviewed the available data, including the comments received,
and determined that air safety and the public interest require adopting
this AD with the change described previously and minor editorial
changes. We have determined that these 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 A320-22-1480, Revision 02, dated
March 30, 2015, and 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. These
documents are distinct due to editorial revisions.
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
[[Page 29365]]
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 will affect 1,032 airplanes of U.S.
registry.
The actions required by AD 2015-23-13, and retained in this 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 AD. The average labor
rate is $85 per work-hour. Based on these figures, we estimate the cost
of this 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 AD will not have federalism implications
under Executive Order 13132. This AD will not have a substantial direct
effect on the States, on the relationship between the national
government and the States, or on the distribution of power and
responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in Alaska; and
4. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD)
2015-23-13, Amendment 39-18330 (80 FR 73099, November 24, 2015), and
adding the following new AD:
2017-13-08 Airbus: Amendment 39-18938; Docket No. FAA-2016-9573;
Directorate Identifier 2016-NM-149-AD.
(a) Effective Date
This AD is effective August 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).
[[Page 29366]]
(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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(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 H2-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 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 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)(2)(i) through (m)(2)(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.
(3) 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 the attention of
the person identified in paragraph (o)(2) of this AD. 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 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
[[Page 29368]]
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 more information about this AD, 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.
(3) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (p)(5) and (p)(6) of this AD.
(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
August 3, 2017.
(i) Airbus Service Bulletin A320-22-1480, Revision 03, dated
October 13, 2015.
(ii) Airbus Service Bulletin A320-22-1539, Revision 01, dated
February 24, 2016.
(iii) Airbus Service Bulletin A320-22-1553, dated March 21,
2016.
(iv) Airbus Service Bulletin A320-22-1554, dated April 19, 2016.
(4) The following service information was approved for IBR on
December 29, 2015 (80 FR 73099, November 24, 2015).
(i) Airbus Service Bulletin A320-22-1375, dated January 15,
2014.
(ii) Airbus Service Bulletin A320-22-1427, Revision 05,
including Appendix 01, dated November 24, 2014.
(iii) Airbus Service Bulletin A320-22-1447, Revision 03, dated
April 21, 2015.
(iv) Airbus Service Bulletin A320-22-1454, dated February 12,
2014.
(v) Airbus Service Bulletin A320-22-1461, Revision 07, including
Appendix 01, dated March 23, 2015.
(vi) Airbus Service Bulletin A320-22-1480, Revision 02, dated
March 30, 2015.
(vii) Airbus Service Bulletin A320-22-1502, dated November 14,
2014.
(viii) Airbus Service Bulletin A320-31-1414, Revision 03, dated
September 15, 2014.
(5) For service information identified in this AD, contact
Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5
61 93 44 51; email account.airworth-eas@airbus.com; Internet https://www.airbus.com.
(6) You may view this service information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For
information on the availability of this material at the FAA, call
425-227-1221.
(7) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on June 16, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2017-13407 Filed 6-28-17; 8:45 am]
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