Airworthiness Directives; Airbus Airplanes, 11960-11963 [2015-04504]
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Federal Register / Vol. 80, No. 43 / Thursday, March 5, 2015 / Proposed Rules
Conclusion
This action affects only certain novel
or unusual design features on two
model series of airplanes. It is not a rule
of general applicability.
List of Subjects in 14 CFR Part 25
Aircraft, Aviation safety, Reporting
and recordkeeping requirements.
The authority citation for these
special conditions is as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701,
44702, 44704.
The Proposed Special Conditions
Accordingly, the Federal Aviation
Administration proposes the following
special conditions as part of the type
certification basis for Bombardier
Aerospace BD–500–1A10 and BD–500–
1A11 series airplanes.
1. Electronic Flight Control System:
Lateral-Directional and Longitudinal
Stability and Low-Energy Awareness. In
lieu of the requirements of §§ 25.171,
25.173, 25.175, and 25.177:
(a) The airplane must be shown to
have suitable static lateral, directional,
and longitudinal stability in any
condition normally encountered in
service, including the effects of
atmospheric disturbance. The showing
of suitable static lateral, directional, and
longitudinal stability must be based on
the airplane handling qualities,
including pilot workload and pilot
compensation, for specific test
procedures during the flight test
evaluations.
(b) The airplane must provide
adequate awareness to the pilot of a low
energy (low speed/low thrust/low
height) state when fitted with flight
control laws presenting neutral
longitudinal stability significantly
below the normal operating speeds.
‘‘Adequate awareness’’ means warning
information must be provided to alert
the crew of unsafe operating conditions
and to enable them to take appropriate
corrective action.
(c) The static directional stability (as
shown by the tendency to recover from
a skid with the rudder free) must be
positive for any landing gear and flap
position and symmetrical power
condition, at speeds from 1.13 VSR1, up
to VFE, VLE, or VFC/MFC (as appropriate).
(d) The static lateral stability (as
shown by the tendency to raise the low
wing in a sideslip with the aileron
controls free), for any landing-gear and
wing-flap position and symmetricpower condition, may not be negative at
any airspeed (except that speeds higher
than VFE need not be considered for
wing-flaps-extended configurations nor
speeds higher than VLE for landing-gear-
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extended configurations) in the
following airspeed ranges:
i. From 1.13 VSR1 to VMO/MMO.
ii. From VMO/MMO to VFC/MFC, unless
the divergence is—
(1) Gradual;
(2) Easily recognizable by the pilot;
and
(3) Easily controllable by the pilot.
(e) In straight, steady sideslips over
the range of sideslip angles appropriate
to the operation of the airplane, but not
less than those obtained with one half
of the available rudder control
movement (but not exceeding a rudder
control force of 180 pounds), rudder
control movements and forces must be
substantially proportional to the angle
of sideslip in a stable sense; and the
factor of proportionality must lie
between limits found necessary for safe
operation. This requirement must be
met for the configurations and speeds
specified in paragraph (c) of this
section.
(f) For sideslip angles greater than
those prescribed by paragraph (e) of this
section, up to the angle at which full
rudder control is used or a rudder
control force of 180 pounds is obtained,
the rudder control forces may not
reverse, and increased rudder deflection
must be needed for increased angles of
sideslip. Compliance with this
requirement must be shown using
straight, steady sideslips, unless full
lateral control input is achieved before
reaching either full rudder control input
or a rudder control force of 180 pounds;
a straight, steady sideslip need not be
maintained after achieving full lateral
control input. This requirement must be
met at all approved landing gear and
wing-flap positions for the range of
operating speeds and power conditions
appropriate to each landing gear and
wing-flap position with all engines
operating.
Issued in Renton, Washington, on February
24, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2015–05048 Filed 3–4–15; 8:45 am]
BILLING CODE 4910–13–P
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–0251; Directorate
Identifier 2014–NM–200–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for all
Airbus Model A318, A319, A320, and
A321 series airplanes. This proposed
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
could result in detachment of the
vertical tail plane. This proposed AD
would require modification of the pin
programming 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. We are
proposing this AD to prevent
detachment of the vertical tail plane and
consequent loss of control of the
airplane.
SUMMARY:
We must receive comments on
this proposed AD by April 20, 2015.
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 proposed 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
DATES:
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Federal Register / Vol. 80, No. 43 / Thursday, March 5, 2015 / Proposed Rules
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–2015–
0251; 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:
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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–2015–0251; Directorate Identifier
2014–NM–200–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
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, has issued EASA
Airworthiness Directive 2014–0217,
dated September 26, 2014 (referred to
after this as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
for all Model A318, A319, A320, and
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Model 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
plane could be reached and possibly
exceeded.
This condition, if not corrected, could lead,
in the worst case, to detachment of the
vertical tail plane in flight and consequent
loss of the aeroplane.
To prevent such a possibility, Airbus has
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.
For the reasons described above, this
[EASA] AD requires installation and
activation of the stop rudder input warning
(SRIW) logic.
In addition, this [EASA] AD requires, prior
to or concurrent with modification of an
aeroplane with the activation of the SRIW,
upgrades of the FAC and FWC, to introduce
the SRIW logic and SRIW aural capability,
respectively. After modification, this [EASA]
AD prohibits installation of certain Part
Number (P/N) FWC and FAC.
You may examine the MCAI in the AD
docket on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2015–
0251.
Related Service Information Under 1
CFR Part 51
Airbus has issued Service Bulletin
A320–22–1480, dated July 9, 2014. The
service information describes
procedures for modifying the pin
programming to activate the SRIW logic.
Airbus has also issued the following
service bulletins. The service
information describes procedures for
replacing FWCs and FACs.
• Airbus Service Bulletin A320–22–
1375, dated January 15, 2014.
• Airbus Service Bulletin A320–22–
1427, Revision 04, dated February 11,
2014.
• Airbus Service Bulletin A320–22–
1447, Revision 01, dated September 18,
2014.
• Airbus Service Bulletin A320–22–
1461, Revision 04, dated September 15,
2014.
• Airbus Service Bulletin A320–31–
1414, Revision 03, dated September 15,
2014.
The actions described in this service
information are intended to correct the
unsafe condition identified in the
MCAI. This service information is
reasonably available; see ADDRESSES for
ways to access this service information.
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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.
Explanation of ‘‘RC’’ Procedures and
Tests in Service Information
The FAA worked in conjunction with
industry, under the Airworthiness
Directives Implementation Aviation
Rulemaking Committee (AD ARC), to
enhance the AD system. One
enhancement was a new process for
annotating which procedures and tests
in the service information are required
for compliance with an AD.
Differentiating these procedures and
tests from other tasks in the service
information is expected to improve an
owner’s/operator’s understanding of
crucial AD requirements and help
provide consistent judgment in AD
compliance. The actions specified in the
service information identified
previously include procedures and tests
that are identified as RC (required for
compliance) because these procedures
have a direct effect on detecting,
preventing, resolving, or eliminating an
identified unsafe condition.
As specified in a NOTE under the
Accomplishment Instructions of the
specified service information,
procedures and tests identified as RC
must be done to comply with the
proposed AD. However, procedures and
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 alternative method of compliance
(AMOC), provided the procedures and
tests identified as RC can be done and
the airplane can be put back in a
serviceable condition. Any substitutions
or changes to procedures or tests
identified as RC will require approval of
an AMOC.
Costs of Compliance
We estimate that this proposed AD
affects 953 airplanes of U.S. registry.
We also estimate that it would take
about 3 work-hours per product to
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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 $243,015, or $255 per product.
In addition, we estimate that any
necessary follow-on actions would take
about 6 work-hours (3 work-hours for an
FWC and 3 work-hours for an FAC), for
a cost of up to $510 per product. We
have received no definitive data that
would enable us to provide part cost
estimates for the on-condition actions
specified in this proposed AD. We have
no way of determining the number of
aircraft that might need these actions.
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.
§ 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:
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
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Authority for This Rulemaking
(d) Subject
Air Transport Association (ATA) of
America Code 22, Auto flight; 31,
Instruments.
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.
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[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
Airbus: Docket No. FAA–2015–0251;
Directorate Identifier 2014–NM–200–AD.
(a) Comments Due Date
We must receive comments by April 20,
2015.
(b) Affected ADs
None.
(c) Applicability
This AD applies to the airplanes,
certificated in any category, identified in
paragraphs (c)(1) through (c)(4) of this AD, 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.
(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 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) Pin Programming Modification
Within 48 months after the effective date
of this AD, 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, dated July 9,
2014.
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(h) Inspection To Determine Part Numbers
(P/Ns), Flight Warning Computer (FWC) and
Flight Augmentation Computer (FAC)
Replacement
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 paragraph (h)(3) of this
AD, in accordance with the Accomplishment
Instructions of the applicable Airbus service
bulletins specified in paragraph (i) of this
AD.
(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 (H1D1).
(ii) 350E053020303 (H2E3).
(iii) 350E016187171 (C5).
(iv) 350E053020404 (H2E4).
(v) 350E017248685 (H1D2).
(vi) 350E053020606 (H2F2).
(vii) 350E017251414 (H1E1).
(viii) 350E053020707 (H2F3).
(ix) 350E017271616 (H1E2).
(x) 350E053021010 (H2F3P).
(xi) 350E018291818 (H1E3CJ).
(xii) 350E053020808 (H2F4).
(xiii) 350E018301919 (H1E3P).
(xiv) 350E053020909 (H2–F5).
(xv) 350E018312020 (H1E3Q).
(xvi) 350E053021111 (H2–F6).
(xvii) 350E053020202 (H2E2).
(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.
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(xxxi) B397AAM0510.
(xxxii) B397BAM0511.
(xxxiii) B397CAM0102.
(xxxiv) Soft P/N G2856AAA01 installed on
hard P/N C13206AA00.
(3) Paragraphs (h)(3)(i) through (h)(3)(iv) of
this AD identify the FWCs and FACs having
the part numbers that are compatible with
SRIW activation required by paragraph (g) of
this AD.
(i) For airplane configurations with no
sharklet, an FAC having P/N B397BAM0621
(621 hard B).
(ii) For airplanes configured with sharklet
A320 and A319, an FAC having P/N
B397BAM0622 (622 hard B).
(iii) For airplanes configured with sharklet
A321, an FAC having P/N B397BAM0623
(623 hard B).
(iv) For all airplane configurations, an FAC
having soft P/N G2856AAA02 installed on
hard P/N C13206AA00 (CAA02 hard C) and
FWC having P/N 350E053021212 (H2–F7).
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(i) Service Bulletins for Actions Required by
Paragraph (h) of This AD
Do the actions required by paragraph (h) of
this AD in accordance with the
Accomplishment Instructions of the
applicable Airbus service bulletin specified
in paragraphs (i)(1) through (i)(5) 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 04, dated February 11, 2014 (FAC
622 Hard B).
(3) Airbus Service Bulletin A320–22–1447,
Revision 01, dated September 18, 2014 (FAC
A02 Hard C).
(4) Airbus Service Bulletin A320–22–1461,
Revision 04, dated September 15, 2014 (FAC
623 Hard B).
(5) Airbus Service Bulletin A320–31–1414,
Revision 03, dated September 15, 2014 (FWC
H–F7).
(j) Exclusion From Actions Required by
Paragraphs (g) and (h) of This AD
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 the effective date
of this AD, 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 part number listed in 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 postmodification 154473 airplane: Within 30
days after the effective date of this AD, do the
replacement required by paragraph (h) of this
AD.
(k) Parts Installation Prohibitions
After modification of an airplane as
required by paragraphs (g), (h), and (j) of this
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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.
(l) Later Approved Parts
Installation of a version (part number) of
the FWC or FAC approved after the effective
date of this AD 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 the European Aviation
Safety Agency (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
This paragraph provides credit for actions
required by paragraph (h) of this AD, if those
actions were performed before the effective
date of this AD using the Airbus service
information identified in paragraphs (m)(1)
through (m)(12) of this AD. This service
information is not incorporated by reference
in this AD.
(1) Airbus Service Bulletin A320–22–1427,
dated January 25, 2013.
(2) Airbus Service Bulletin A320–22–1427,
Revision 01, dated July 30, 2013.
(3) Airbus Service Bulletin A320–22–1427,
Revision 02, dated October 14, 2013.
(4) Airbus Service Bulletin A320–22–1427,
Revision 03, dated November 8, 2013.
(5) Airbus Service Bulletin A320–22–1447,
dated October 18, 2013.
(6) Airbus Service Bulletin A320–22–1461,
dated October 31, 2013.
(7) Airbus Service Bulletin A320–22–1461,
Revision 01, dated February 25, 2014.
(8) Airbus Service Bulletin A320–22–1461,
Revision 02, dated April 30, 2014.
(9) Airbus Service Bulletin A320–22–1461,
Revision 03, dated July 17, 2014.
(10) Airbus Service Bulletin A320–31–
1414, dated December 19, 2012.
(11) Airbus Service Bulletin A320–31–
1414, Revision 01, dated March 21, 2013.
(12) Airbus Service Bulletin A320–31–
1414, Revision 02, dated July 30, 2013.
(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;
PO 00000
Frm 00018
Fmt 4702
Sfmt 9990
11963
telephone 425–227–1405; fax 425–227–1149.
Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov. Before using
any approved AMOC, notify your appropriate
principal inspector, or lacking a principal
inspector, the manager of the local flight
standards district office/certificate holding
district office. The AMOC approval letter
must specifically reference this AD.
(2) Required for Compliance (RC): If the
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 and 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 a serviceable condition.
Any substitutions or changes to procedures
or tests identified as RC require approval of
an AMOC.
(3) Contacting the Manufacturer: 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.
(o) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2014–0217, dated
September 26, 2014, for related information.
This MCAI may be found in the AD docket
on the Internet at https://www.regulations.gov
by searching for and locating Docket No.
FAA–2015–0251.
(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 February
19, 2015.
John P. Piccola, Jr.,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2015–04504 Filed 3–4–15; 8:45 am]
BILLING CODE 4910–13–P
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]]>Agencies
[Federal Register Volume 80, Number 43 (Thursday, March 5, 2015)]
[Proposed Rules]
[Pages 11960-11963]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2015-04504]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2015-0251; Directorate Identifier 2014-NM-200-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to adopt a new airworthiness directive (AD) for all
Airbus Model A318, A319, A320, and A321 series airplanes. This proposed
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 could result in
detachment of the vertical tail plane. This proposed AD would require
modification of the pin programming 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. We are
proposing this AD to prevent detachment of the vertical tail plane and
consequent loss of control of the airplane.
DATES: We must receive comments on this proposed AD by April 20, 2015.
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 proposed 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
[[Page 11961]]
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-2015-
0251; 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-2015-0251;
Directorate Identifier 2014-NM-200-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
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued EASA
Airworthiness Directive 2014-0217, dated September 26, 2014 (referred
to after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition for all Model A318, A319,
A320, and Model 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
plane could be reached and possibly exceeded.
This condition, if not corrected, could lead, in the worst case,
to detachment of the vertical tail plane in flight and consequent
loss of the aeroplane.
To prevent such a possibility, Airbus has 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.
For the reasons described above, this [EASA] AD requires
installation and activation of the stop rudder input warning (SRIW)
logic.
In addition, this [EASA] AD requires, prior to or concurrent
with modification of an aeroplane with the activation of the SRIW,
upgrades of the FAC and FWC, to introduce the SRIW logic and SRIW
aural capability, respectively. After modification, this [EASA] AD
prohibits installation of certain Part Number (P/N) FWC and FAC.
You may examine the MCAI in the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2015-
0251.
Related Service Information Under 1 CFR Part 51
Airbus has issued Service Bulletin A320-22-1480, dated July 9,
2014. The service information describes procedures for modifying the
pin programming to activate the SRIW logic.
Airbus has also issued the following service bulletins. The service
information describes procedures for replacing FWCs and FACs.
Airbus Service Bulletin A320-22-1375, dated January 15,
2014.
Airbus Service Bulletin A320-22-1427, Revision 04, dated
February 11, 2014.
Airbus Service Bulletin A320-22-1447, Revision 01, dated
September 18, 2014.
Airbus Service Bulletin A320-22-1461, Revision 04, dated
September 15, 2014.
Airbus Service Bulletin A320-31-1414, Revision 03, dated
September 15, 2014.
The actions described in this service information are intended to
correct the unsafe condition identified in the MCAI. This service
information is reasonably available; see ADDRESSES for ways to access
this service information.
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.
Explanation of ``RC'' Procedures and Tests in Service Information
The FAA worked in conjunction with industry, under the
Airworthiness Directives Implementation Aviation Rulemaking Committee
(AD ARC), to enhance the AD system. One enhancement was a new process
for annotating which procedures and tests in the service information
are required for compliance with an AD. Differentiating these
procedures and tests from other tasks in the service information is
expected to improve an owner's/operator's understanding of crucial AD
requirements and help provide consistent judgment in AD compliance. The
actions specified in the service information identified previously
include procedures and tests that are identified as RC (required for
compliance) because these procedures have a direct effect on detecting,
preventing, resolving, or eliminating an identified unsafe condition.
As specified in a NOTE under the Accomplishment Instructions of the
specified service information, procedures and tests identified as RC
must be done to comply with the proposed AD. However, procedures and
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 alternative method
of compliance (AMOC), provided the procedures and tests identified as
RC can be done and the airplane can be put back in a serviceable
condition. Any substitutions or changes to procedures or tests
identified as RC will require approval of an AMOC.
Costs of Compliance
We estimate that this proposed AD affects 953 airplanes of U.S.
registry.
We also estimate that it would take about 3 work-hours per product
to
[[Page 11962]]
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 $243,015, or $255
per product.
In addition, we estimate that any necessary follow-on actions would
take about 6 work-hours (3 work-hours for an FWC and 3 work-hours for
an FAC), for a cost of up to $510 per product. We have received no
definitive data that would enable us to provide part cost estimates for
the on-condition actions specified in this proposed AD. 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 adding the following new airworthiness
directive (AD):
Airbus: Docket No. FAA-2015-0251; Directorate Identifier 2014-NM-
200-AD.
(a) Comments Due Date
We must receive comments by April 20, 2015.
(b) Affected ADs
None.
(c) Applicability
This AD applies to the airplanes, certificated in any category,
identified in paragraphs (c)(1) through (c)(4) of this AD, 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
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) Pin Programming Modification
Within 48 months after the effective date of this AD, 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, dated July 9, 2014.
(h) Inspection To Determine Part Numbers (P/Ns), Flight Warning
Computer (FWC) and Flight Augmentation Computer (FAC) Replacement
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
paragraph (h)(3) of this AD, in accordance with the Accomplishment
Instructions of the applicable Airbus service bulletins specified in
paragraph (i) of this AD.
(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 (H1D1).
(ii) 350E053020303 (H2E3).
(iii) 350E016187171 (C5).
(iv) 350E053020404 (H2E4).
(v) 350E017248685 (H1D2).
(vi) 350E053020606 (H2F2).
(vii) 350E017251414 (H1E1).
(viii) 350E053020707 (H2F3).
(ix) 350E017271616 (H1E2).
(x) 350E053021010 (H2F3P).
(xi) 350E018291818 (H1E3CJ).
(xii) 350E053020808 (H2F4).
(xiii) 350E018301919 (H1E3P).
(xiv) 350E053020909 (H2-F5).
(xv) 350E018312020 (H1E3Q).
(xvi) 350E053021111 (H2-F6).
(xvii) 350E053020202 (H2E2).
(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.
[[Page 11963]]
(xxxi) B397AAM0510.
(xxxii) B397BAM0511.
(xxxiii) B397CAM0102.
(xxxiv) Soft P/N G2856AAA01 installed on hard P/N C13206AA00.
(3) Paragraphs (h)(3)(i) through (h)(3)(iv) of this AD identify
the FWCs and FACs having the part numbers that are compatible with
SRIW activation required by paragraph (g) of this AD.
(i) For airplane configurations with no sharklet, an FAC having
P/N B397BAM0621 (621 hard B).
(ii) For airplanes configured with sharklet A320 and A319, an
FAC having P/N B397BAM0622 (622 hard B).
(iii) For airplanes configured with sharklet A321, an FAC having
P/N B397BAM0623 (623 hard B).
(iv) For all airplane configurations, an FAC having soft P/N
G2856AAA02 installed on hard P/N C13206AA00 (CAA02 hard C) and FWC
having P/N 350E053021212 (H2-F7).
(i) Service Bulletins for Actions Required by Paragraph (h) of This AD
Do the actions required by paragraph (h) of this AD in
accordance with the Accomplishment Instructions of the applicable
Airbus service bulletin specified in paragraphs (i)(1) through
(i)(5) 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 04, dated
February 11, 2014 (FAC 622 Hard B).
(3) Airbus Service Bulletin A320-22-1447, Revision 01, dated
September 18, 2014 (FAC A02 Hard C).
(4) Airbus Service Bulletin A320-22-1461, Revision 04, dated
September 15, 2014 (FAC 623 Hard B).
(5) Airbus Service Bulletin A320-31-1414, Revision 03, dated
September 15, 2014 (FWC H-F7).
(j) Exclusion From Actions Required by Paragraphs (g) and (h) of This
AD
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 the effective date of this AD, 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 part number
listed in 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-modification 154473 airplane: Within 30 days after the
effective date of this AD, do the replacement required by paragraph
(h) of this AD.
(k) Parts Installation Prohibitions
After modification of an airplane as required by paragraphs (g),
(h), and (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.
(l) Later Approved Parts
Installation of a version (part number) of the FWC or FAC
approved after the effective date of this AD 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 the European Aviation Safety Agency (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
This paragraph provides credit for actions required by paragraph
(h) of this AD, if those actions were performed before the effective
date of this AD using the Airbus service information identified in
paragraphs (m)(1) through (m)(12) of this AD. This service
information is not incorporated by reference in this AD.
(1) Airbus Service Bulletin A320-22-1427, dated January 25,
2013.
(2) Airbus Service Bulletin A320-22-1427, Revision 01, dated
July 30, 2013.
(3) Airbus Service Bulletin A320-22-1427, Revision 02, dated
October 14, 2013.
(4) Airbus Service Bulletin A320-22-1427, Revision 03, dated
November 8, 2013.
(5) Airbus Service Bulletin A320-22-1447, dated October 18,
2013.
(6) Airbus Service Bulletin A320-22-1461, dated October 31,
2013.
(7) Airbus Service Bulletin A320-22-1461, Revision 01, dated
February 25, 2014.
(8) Airbus Service Bulletin A320-22-1461, Revision 02, dated
April 30, 2014.
(9) Airbus Service Bulletin A320-22-1461, Revision 03, dated
July 17, 2014.
(10) Airbus Service Bulletin A320-31-1414, dated December 19,
2012.
(11) Airbus Service Bulletin A320-31-1414, Revision 01, dated
March 21, 2013.
(12) Airbus Service Bulletin A320-31-1414, Revision 02, dated
July 30, 2013.
(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. Before using any
approved AMOC, notify your appropriate principal inspector, or
lacking a principal inspector, the manager of the local flight
standards district office/certificate holding district office. The
AMOC approval letter must specifically reference this AD.
(2) Required for Compliance (RC): If the 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 and 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 a serviceable
condition. Any substitutions or changes to procedures or tests
identified as RC require approval of an AMOC.
(3) Contacting the Manufacturer: 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.
(o) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2014-0217, dated September 26,
2014, for related information. This MCAI may be found in the AD
docket on the Internet at https://www.regulations.gov by searching
for and locating Docket No. FAA-2015-0251.
(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 February 19, 2015.
John P. Piccola, Jr.,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2015-04504 Filed 3-4-15; 8:45 am]
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