Airworthiness Directives; Airbus Airplanes, 79750-79754 [2015-30821]
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Federal Register / Vol. 80, No. 246 / Wednesday, December 23, 2015 / Proposed Rules
TABLE 1 TO PARAGRAPH (I) OF THIS
AD—REPLACEMENT
COMPLIANCE
TIMES—Continued
Year of
manufacture
Compliance time
2009 ...............
Before exceeding 10 years
since date of manufacture
of the passenger chemical
oxygen generator.
(j) Definition of Serviceable
For the purpose of this AD, a serviceable
unit is a passenger chemical oxygen
generator having P/N 117042–XX (XX
represents any numerical value) with a
manufacturing date not older than 10 years,
or any other approved part number, provided
that the generator has not exceeded the life
limit established for that generator by the
manufacturer.
(k) Reporting
At the applicable time specified in
paragraph (k)(1) or (k)(2) of this AD, submit
a report of the findings (both positive and
negative) of the inspection required by
paragraph (g) of this AD, in accordance with
paragraph 7, ‘‘Reporting,’’ of Airbus AOT
A35W008–14, dated December 18, 2014. The
report must include the information specified
in Appendix 1 of Airbus AOT A35W008–14,
dated December 18, 2014.
(1) If the inspection was done on or after
the effective date of this AD: Submit the
report within 30 days after the inspection.
(2) If the inspection was done before the
effective date of this AD: Submit the report
within 30 days after the effective date of this
AD.
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(l) Parts Installation Limitation
As of the effective date of this AD, no
person may install a passenger chemical
oxygen generator, unless it is determined,
prior to installation, that the oxygen
generator is a serviceable unit (as defined in
paragraph (j) of this AD).
(m) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
In accordance with 14 CFR 39.19, send your
request to your principal inspector or local
Flight Standards District Office, as
appropriate. If sending information directly
to the International Branch, send it to ATTN:
Dan Rodina, Aerospace Engineer,
International Branch, ANM–116 Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone: 425–227–2125; fax: 425–227–
1149. Information may be emailed to: 9ANM-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/
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certificate holding district office. The AMOC
approval letter must specifically reference
this AD.
(2) 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 European Aviation Safety Agency
(EASA); or Airbus’s EASA Design
Organization Approval (DOA). If approved by
the DOA, the approval must include the
DOA-authorized signature.
(3) Reporting Requirements: A federal
agency may not conduct or sponsor, and a
person is not required to respond to, nor
shall a person be subject to a penalty for
failure to comply with a collection of
information subject to the requirements of
the Paperwork Reduction Act unless that
collection of information displays a current
valid OMB Control Number. The OMB
Control Number for this information
collection is 2120–0056. Public reporting for
this collection of information is estimated to
be approximately 5 minutes per response,
including the time for reviewing instructions,
completing and reviewing the collection of
information. All responses to this collection
of information are mandatory. Comments
concerning the accuracy of this burden and
suggestions for reducing the burden should
be directed to the FAA at: 800 Independence
Ave. SW., Washington, DC 20591, Attn:
Information Collection Clearance Officer,
AES–200.
(n) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2015–0118, dated
June 24, 2015, for related information. This
MCAI may be found in the AD docket on the
Internet at https://www.regulations.gov by
searching for and locating Docket No. FAA–
2015–7528.
(2) For Airbus service information
identified in this AD, contact Airbus SAS,
Airworthiness Office—EAW, 1 Rond Point
Maurice Bellonte, 31707 Blagnac Cedex,
France; telephone: +33 5 61 93 36 96; fax:
+33 5 61 93 44 51; email: account.airwortheas@airbus.com; Internet https://
www.airbus.com. For B/E service identified
in this AD, contact B/E Aerospace Inc., 10800
Pflumm Road, Lenexa, KS 66215; telephone:
913–338–9800; fax: 913–469–8419; Internet
https://beaerospace.com/home/globalsupport.
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
December 11, 2015.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2015–32084 Filed 12–22–15; 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–2015–0250; Directorate
Identifier 2014–NM–216–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Supplemental notice of
proposed rulemaking (NPRM);
reopening of comment period.
AGENCY:
We are revising an earlier
proposed airworthiness directive (AD)
for all Airbus Model A318, A319, A320,
and A321 series airplanes. The NPRM
proposed to require replacing certain
pitot probes on the captain, first officer,
and standby sides with certain new
pitot probes. The NPRM was prompted
by reports of airspeed indication
discrepancies while flying at high
altitudes in inclement weather. This
action revises the NPRM by reducing
the proposed compliance time for
replacing certain pitot probes based on
a risk assessment due to additional
reports of airspeed indication
discrepancies while flying at high
altitudes in inclement weather. We are
proposing this supplemental NPRM
(SNPRM) to prevent airspeed indication
discrepancies during inclement
weather, which, depending on the
prevailing altitude, could lead to
unknown accumulation of ice crystals
and consequent reduced controllability
of the airplane. Since these actions
impose an additional burden over those
proposed in the NPRM, we are
reopening the comment period to allow
the public the chance to comment on
these proposed changes.
DATES: We must receive comments on
this SNPRM by January 22, 2016.
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
SUMMARY:
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Federal Register / Vol. 80, No. 246 / Wednesday, December 23, 2015 / Proposed Rules
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
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–
0250; 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 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–2015–0250; Directorate Identifier
2014–NM–216–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.
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Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to all Airbus Model A318, A319,
A320, and A321 series airplanes. The
NPRM published in the Federal
Register on March 6, 2015 (80 FR
12094) (‘‘the NPRM’’). The NPRM was
prompted by reports of airspeed
indication discrepancies while flying at
high altitudes in inclement weather.
The NPRM proposed to require
replacing certain pitot probes on the
captain, first officer, and standby sides
with certain new pitot probes.
Consequently, EASA issued AD 2014–0237
(later revised) [https://ad.easa.europa.eu/
blob/easa_ad_2014_0237.pdf/AD_20140237], retaining the requirements of DGAC
France AD 2001–362, which was superseded,
and cancelling two other DGAC ADs, to
require replacement of Thales Avionics pitot
probes P/N C16195AA and P/N C16195BA.
Since EASA issued AD 2014–0237R1
[https://ad.easa.europa.eu/ad/2014-0237R1]
was issued, results of further analyses have
determined that the compliance time (48
months) of that AD has to be reduced in
relation to the risk assessment.
For the reasons described above, this
[EASA] AD retains the requirements of EASA
AD 2014–0237R1, which is superseded, but
reduces the compliance time.
Actions Since Previous NPRM (80 FR
12094, March 6, 2015) Was Issued
Since we issued the NPRM (80 FR
12094, March 6, 2015), we have
determined it is necessary to reduce the
compliance time for replacing certain
pitot probes based on a risk assessment
due to additional reports of airspeed
indication discrepancies while flying at
high altitudes in inclement weather.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, issued EASA Airworthiness
Directive 2015–0205, dated October 9,
2015 (referred to after this as the
Mandatory Continuing Airworthiness
Information, or ‘‘the MCAI’’), to correct
an unsafe condition on all Airbus Model
A318, A319, A320, and A321 series
airplanes. The MCAI states:
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–
0250.
Occurrences have been reported on A320
family aeroplanes of airspeed indication
discrepancies while flying at high altitudes
in inclement weather conditions.
Investigation results indicated that A320
aeroplanes equipped with Thales Avionics
Part Number (P/N) 50620–10 or P/N
C16195AA pitot probes appear to have a
greater susceptibility to adverse
environmental conditions that aeroplanes
equipped with certain other pitot probes.
Prompted by earlier occurrences, DGAC
´ ´
[Direction Generale de l’Aviation Civile]
France issued [DGAC] AD 2001-362 [https://
ad.easa.europa.eu/blob/easa_ad_2001_
362.pdf/AD_2001-362] [which corresponds to
paragraph (f) of FAA AD 2004-03-33,
Amendment 39-13477 (69 FR 9936, March 3,
2004)] to require replacement of Thales
(formerly known as Sextant) P/N 50620-10
pitot probes with Thales P/N C16195AA
probes.
Since that [DGAC] AD was issued, Thales
pitot probe P/N C15195BA was designed,
which improved airspeed indication
behavior in heavy rain conditions, but did
not demonstrate the same level of robustness
to withstand high-altitude ice crystals. Based
on these findings, EASA have decided to
implement replacement of the affected
Thales [pitot] probes as a precautionary
measure to improve the safety level of the
affected aeroplanes.
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Related Rulemaking
On February 4, 2004, we issued AD
2004–03–33, Amendment 39–13477 (69
FR 9936, March 3, 2004), applicable to
certain Airbus Model A300 B2 and B4
series airplanes; Model A300 B4–600,
A300 B4–600R, and A300 F4–600R
series airplanes; Model A310 series
Airplanes; Model A319, A320, and
A321 series airplanes; Model A330–301,
–321, –322, –341, and –342 airplanes;
and Model A340 series airplanes. That
AD requires, among other actions,
replacement of certain pitot probes with
certain new pitot probes. That AD was
issued to prevent loss or fluctuation of
indicated airspeed, which could result
in misleading information being
provided to the flightcrew.
Accomplishing the replacement
specified in paragraph (g) of this
SNPRM would terminate the
requirements of paragraph (f) of AD
2004–03–33, for that airplane only.
Related Service Information Under 1
CFR Part 51
Airbus has issued the following
service information:
• Service Bulletin A320–34–1170,
Revision 30, dated June 18, 2015.
• Service Bulletin A320–34–1456,
Revision 01, dated May 15, 2012.
• Service Bulletin A320–34–1463,
Revision 01, dated May 15, 2012.
The service information describes
procedures for replacing certain Thales
Avionics pitot probes on the captain,
first officer, and standby sides. This
service information is reasonably
available because the interested parties
have access to it through their normal
course of business or by the means
identified in the ADDRESSES section of
this SNPRM.
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Federal Register / Vol. 80, No. 246 / Wednesday, December 23, 2015 / Proposed Rules
Comments
We gave the public the opportunity to
participate in developing this SNPRM.
We considered the comments received.
American Airlines supports the
proposed compliance time of 48 months
for retrofit.
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Request To Refer To Revised Service
Information
United Airlines (UAL) and Virgin
America asked that the NPRM be
revised to refer to Airbus Service
Bulletin A320–34–1170, Revision 29,
dated February 16, 2015. (The NPRM
(80 FR 12094, March 6, 2015) referred
to Airbus Service Bulletin A320–34–
1170, Revision 28, dated September 1,
2014, as the appropriate source of
service information for replacing the
pitot probes.) UAL stated that Airbus
Service Bulletin A320–34–1170,
Revision 29, dated February 16, 2015,
includes UAL effectivity, as well as all
A320 family airplanes fitted with Thales
Pitot Probes. Virgin America stated that
Airbus Service Bulletin A320–34–1170,
Revision 28, dated September 1, 2014, is
available only to select operators who
previously purchased the change;
Airbus Service Bulletin A320–34–1170,
Revision 29, dated February 16, 2015, is
available to all operators with airplanes
having Thales pitot probes installed.
American Airlines (AAL) asked that we
refer to Airbus Service Bulletin A320–
34–1170, Revision 30, which is
scheduled for release in the near future.
AAL added that the effectivity in Airbus
Service Bulletin A320–34–1170,
Revision 28, dated September 1, 2014, is
incomplete.
We agree to refer to Airbus Service
Bulletin A320–34–1170, Revision 30,
dated June 18, 2015, for the pitot probe
replacement. Airbus Service Bulletin
A320–34–1170, Revision 30, dated June
18, 2015, was issued to update the
operator list and related information in
the effectivity, and does not include
additional work. We have changed
paragraph (g) of this SNPRM to refer to
Airbus Service Bulletin A320–34–1170,
Revision 30, dated June 18, 2015. In
addition, to give credit for using Airbus
Service Bulletin A320–34–1170,
Revision 28, dated September 1, 2014,
and Airbus Service Bulletin A320–34–
1170, Revision 29, dated February 16,
2015, we added new paragraphs
(i)(1)(xxv) and (i)(1)(xxvi) to this
SNPRM.
Request To Reduce the Compliance
Time
The Airline Pilots Association
International (ALPA) asked that the
compliance time for replacement of the
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pitot probes, as specified in paragraph
(g) of the proposed AD (80 FR 12094,
March 6, 2015), be reduced to 24
months or less. ALPA stated that it
recognizes the potential flight safety risk
of operating an airplane with reduced
controllability characteristics, which
justifies reducing the compliance time.
We agree with the request to reduce
the compliance time for replacement of
the pitot probes. As specified under
‘‘Actions Since Previous NPRM was
Issued,’’ we have reduced the proposed
compliance time for replacing certain
pitot probes based on a risk assessment
due to additional reports of airspeed
indication discrepancies while flying at
high altitudes in inclement weather.
EASA has issued Airworthiness
Directive 2015–0205, dated October 9,
2015, to reduce the compliance time for
replacement of the pitot probes to 24
months. We have changed the
compliance time in paragraph (g) of this
SNPRM accordingly.
Request for Clarification
AAL stated the use of a pitot probe
which meets the current icing
specification, as specified in the NPRM
(80 FR 12094, March 6, 2015), should
note that a new icing specification is
forthcoming. In addition, the UTAS
(formerly Goodrich) pitot probe having
part number 0851HL is built to the
current specification. AAL noted that
the data available today shows that pitot
probes on which the new icing
requirement is met should be available
for retrofit in 2016.
We acknowledge the commenter’s
statement about the NPRM proposing
the use of a pitot probe that meets the
current icing airworthiness
requirements and not the new icing
airworthiness requirements of
Amendment 25–140 (79 FR 65508,
November 4, 2014) to 14 CFR part 25.
Since we are currently not aware of any
pitot probes certified to the new icing
airworthiness requirements, this
SNPRM would mandate Goodrich pitot
probes having part number 0851HL,
which meet the icing airworthiness
requirements in effect at the time of
establishing the certification basis for
Airbus Model A318, A319, A320, and
A321 series airplanes. AAL may request
approval for an alternative method of
compliance for the installation of pitot
probes that meet the new certification
standards once the pitot probes are
available for installation, under the
provisions of paragraph (k)(1) of this
proposed AD.
AAL also asked the following related
questions and we have provided a
response to each comment:
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• What FAA activities are scheduled
with suppliers to meet the expectations
of the new icing requirement? FAA
activities associated with the new icing
requirements are related to new design
modifications. At this time we are not
mandating installation of pitot probes
which meet the new icing certification
standards.
• Does the FAA anticipate issuing a
new AD mandating a retrofit/forward fit
to the new icing requirement? We do
not plan to issue further rulemaking
mandating a retrofit/forward fit to the
new icing requirement at this time.
• Would the FAA extend the
compliance time if another pitot probe
supplier demonstrates compliance to
the new icing requirement? We would
not extend the compliance time because
this SNPRM does not require installing
pitot probes that meet the new icing
requirement; therefore, the compliance
time for the installation is considered
adequate to address the unsafe
condition.
FAA’s Determination and Requirements
of This SNPRM
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.
Certain changes described above
expand the scope of the proposed AD
(80 FR 12094, March 6, 2015). As a
result, we have determined that it is
necessary to reopen the comment period
to provide additional opportunity for
the public to comment on this SNPRM.
Explanation of ‘‘RC’’ Procedures and
Tests in Service Information
The FAA worked in conjunction with
industry, under the Airworthiness
Directive Implementation Aviation
Rulemaking Committee (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 procedures and tests
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Federal Register / Vol. 80, No. 246 / Wednesday, December 23, 2015 / Proposed Rules
identified as RC (required for
compliance) in any service information
have a direct effect on detecting,
preventing, resolving, or eliminating an
identified unsafe condition.
As specified in a NOTE under the
Accomplishment Instructions of Airbus
Service Bulletin A320–34–1170,
Revision 30, dated June 18, 2015,
procedures and tests that are identified
as RC in any service information 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 an
airworthy 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 4 work-hours per product to
comply with the new basic
requirements of this proposed AD. The
average labor rate is $85 per work-hour.
Required parts would cost about
$21,930 per product. Based on these
figures, we estimate the cost of this
proposed AD on U.S. operators to be
$21,223,310, or $22,270 per product.
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Authority for This Rulemaking
17:28 Dec 22, 2015
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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.
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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.
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
Airbus: Docket No. FAA–2015–0250;
Directorate Identifier 2014–NM–216–AD.
(a) Comments Due Date
We must receive comments by January 22,
2016.
(b) Affected ADs
This AD affects AD 2004–03–33,
Amendment 39–13477 (69 FR 9936, March 3,
2004).
(c) Applicability
This AD applies to the airplanes identified
in paragraphs (c)(1), (c)(2), (c)(3), and (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.
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(4) Airbus Model A321–111, –112, –131,
–211, –212, –213, –231, and –232 airplanes.
(d) Subject
Air Transport Association (ATA) of
America Code 34, Navigation.
(e) Reason
This AD was prompted by reports of
airspeed indication discrepancies while
flying at high altitudes in inclement weather.
We are issuing this AD to prevent airspeed
indication discrepancies during inclement
weather, which, depending on the prevailing
altitude, could lead to unknown
accumulation of ice crystals and consequent
reduced controllability of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Replacement of Certain Pitot Probes on
the Captain, First Officer, and Standby Sides
Within 24 months after the effective date
of this AD: Replace any Thales pitot probe
having part number (P/N) C16195AA or P/N
C16195BA, with a Goodrich pitot probe
having P/N 0851HL, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–34–1170, Revision 30,
dated June 18, 2015. Accomplishing the
replacement in this paragraph terminates the
requirements of paragraph (f) of AD 2004–
03–33, Amendment 39–13477 (69 FR 9936,
March 3, 2004), for that airplane only.
(h) Optional Methods of Compliance for
Replacement Required by Paragraph (g) of
This AD
(1) Replacement of the pitot probes in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320–
34–1456, Revision 01, dated May 15, 2012
(pitot probes on the captain and standby
sides); and Airbus Service Bulletin A320–34–
1463, Revision 01, dated May 15, 2012 (pitot
probes on the first officer side); is an
acceptable method of compliance with the
requirements of paragraph (g) of this AD.
(2) Airplanes on which Airbus
Modification 25578 was embodied in
production, except for post-modification
25578 airplanes on which Airbus
Modification 155737 (installation of Thales
pitot probes) was also embodied in
production, are compliant with the
requirements of paragraph (g) of this AD,
provided it can be conclusively determined
that no Thales pitot probe having P/N
C16195AA, P/N C16195BA, or P/N 50620–10
has been installed since the date of issuance
of the original certificate of airworthiness or
the date of issuance of the original export
certificate of airworthiness. Post-modification
25578 airplanes on which Airbus
Modification 155737 (installation of Thales
pitot probes) was also embodied in
production must be in compliance with the
requirements of paragraph (g) of this AD.
(i) Credit for Previous Actions
(1) This paragraph provides credit for the
actions required by paragraph (g) of this AD,
if those actions were performed before the
effective date of this AD using the service
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information identified in paragraph (i)(1)(i)
through (i)(1)(xxvi) of this AD. This service
information is not incorporated by reference
in this AD.
(i) Airbus Service Bulletin A320–34–1170,
Revision 04, dated May 24, 2000.
(ii) Airbus Service Bulletin A320–34–1170,
Revision 05, dated September 11, 2000.
(iii) Airbus Service Bulletin A320–34–
1170, Revision 06, dated October 18, 2001.
(iv) Airbus Service Bulletin A320–34–
1170, Revision 07, dated December 4, 2001.
(v) Airbus Service Bulletin A320–34–1170,
Revision 08, dated January 15, 2003.
(vi) Airbus Service Bulletin A320–34–
1170, Revision 09, dated February 17, 2003.
(vii) Airbus Service Bulletin A320–34–
1170, Revision 10, dated November 21, 2003.
(viii) Airbus Service Bulletin A320–34–
1170, Revision 11, dated August 18, 2004.
(ix) Airbus Service Bulletin A320–34–
1170, Revision 12, dated December 2, 2004.
(x) Airbus Service Bulletin A320–34–1170,
Revision 13, dated January 18, 2005.
(xi) Airbus Service Bulletin A320–34–
1170, Revision 14, dated April 21, 2005.
(xii) Airbus Service Bulletin A320–34–
1170, Revision 15, dated July 19, 2005.
(xiii) Airbus Service Bulletin A320–34–
1170, Revision 16, dated November 23, 2006.
(xiv) Airbus Service Bulletin A320–34–
1170, Revision 17, dated February 14, 2007.
(xv) Airbus Service Bulletin A320–34–
1170, Revision 18, dated October 9, 2009.
(xvi) Airbus Service Bulletin A320–34–
1170, Revision 19, dated November 9, 2009.
(xvii) Airbus Service Bulletin A320–34–
1170, Revision 20, dated December 1, 2010.
(xviii) Airbus Service Bulletin A320–34–
1170, Revision 21, dated March 24, 2011.
(xix) Airbus Service Bulletin A320–34–
1170, Revision 22, dated July 19, 2011.
(xx) Airbus Service Bulletin A320–34–
1170, Revision 23, dated February 3, 2012.
(xxi) Airbus Service Bulletin A320–34–
1170, Revision 24, dated April 12, 2012.
(xxii) Airbus Service Bulletin A320–34–
1170, Revision 25, dated September 4, 2012.
(xxiii) Airbus Service Bulletin A320–34–
1170, Revision 26, dated September 16, 2013.
(xxiv) Airbus Service Bulletin A320–34–
1170, Revision 27, dated March 18, 2014.
(xxv) Airbus Service Bulletin A320–34–
1170, Revision 28, dated September 1, 2014.
(xxvi) Airbus Service Bulletin A320–34–
1170, Revision 29, dated February 16, 2015.
(2) This paragraph provides credit for the
replacement of pitot probes on the captain
and standby sides specified in paragraph
(h)(1) of this AD, if the replacement was
performed before the effective date of this AD
using Airbus Service Bulletin A320–34–1456,
dated December 2, 2009, which is not
incorporated by reference in this AD.
(3) This paragraph provides credit for the
replacement of pitot probes on the first
officer side as specified in paragraph (h)(1) of
this AD, if those actions were performed
before the effective date of this AD using
Airbus Service Bulletin A320–34–1463,
dated March 9, 2010, which is not
incorporated by reference in this AD.
(j) Parts Installation Limitations
(1) At the applicable time specified in
paragraph (j)(1)(i) or (j)(1)(ii) of this AD: No
VerDate Sep<11>2014
17:28 Dec 22, 2015
Jkt 238001
person may install on any airplane a Thales
pitot probe having P/N C16195AA or P/N
C16195BA.
(i) For airplanes with a Thales pitot probe
having P/N C16195AA or P/N C16195BA
installed: After accomplishing the
replacement required by paragraph (g) of this
AD.
(ii) For airplanes without a Thales pitot
probe having P/N C16195AA or P/N
C16195BA installed: As of the effective date
of this AD.
(2) As of the effective date of this AD, no
person may install on any airplane a Thales
pitot probe having part number P/N 50620–
10.
(k) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
In accordance with 14 CFR 39.19, send your
request to your principal inspector or local
Flight Standards District Office, as
appropriate. If sending information directly
to the International Branch, send it to ATTN:
Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone 425–227–1405; fax 425–227–1149.
Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov. 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) 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 European Aviation Safety Agency
(EASA); or Airbus’s EASA Design
Organization Approval (DOA). If approved by
the DOA, the approval must include the
DOA-authorized signature.
(3) Required for Compliance (RC): If any
service information contains procedures or
tests that are identified as RC, those
procedures and tests must be done to comply
with this AD; any procedures or tests that are
not identified as RC are recommended. Those
procedures and tests that are not identified
as RC may be deviated from using accepted
methods in accordance with the operator’s
maintenance or inspection program without
obtaining approval of an AMOC, provided
the procedures and tests identified as RC can
be done and the airplane can be put back in
an airworthy condition. Any substitutions or
changes to procedures or tests identified as
RC require approval of an AMOC.
(l) Related Information
(1) Refer to EASA Airworthiness Directive
2015–0205, dated October 9, 2015, for related
information. This MCAI may be found in the
PO 00000
Frm 00036
Fmt 4702
Sfmt 4702
AD docket on the Internet at https://
www.regulations.gov by searching for and
locating Docket No. FAA–2015–0250.
(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
November 25, 2015.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2015–30821 Filed 12–22–15; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–7527; Directorate
Identifier 2015–NM–094–AD]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for certain
The Boeing Company Model 777–200,
–200LR, –300, and –300ER series
airplanes. This proposed AD was
prompted by a report indicating that the
manufacturer discovered locations
where the control components and
wiring of the left and right engine fuel
spar valves do not have adequate
physical separation to meet the
redundant system separation
requirements. This proposed AD would
require modifying the wiring, and
installing a new relay bracket and new
location for the relay on the left and
right engine fuel spar valves. This
proposed AD would also require an
inspection to identify the part number
of the motor operated valve (MOV)
actuators for the left and right engine
fuel spar valves; replacement of
specified MOV actuators with new MOV
actuators; certain bonding resistance
measurements; and applicable
corrective actions. We are proposing
this AD to prevent loss of control of
both the left and right engine fuel spar
valves during a single event, such as
SUMMARY:
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]]>Agencies
[Federal Register Volume 80, Number 246 (Wednesday, December 23, 2015)]
[Proposed Rules]
[Pages 79750-79754]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-30821]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2015-0250; Directorate Identifier 2014-NM-216-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Supplemental notice of proposed rulemaking (NPRM); reopening of
comment period.
-----------------------------------------------------------------------
SUMMARY: We are revising an earlier proposed airworthiness directive
(AD) for all Airbus Model A318, A319, A320, and A321 series airplanes.
The NPRM proposed to require replacing certain pitot probes on the
captain, first officer, and standby sides with certain new pitot
probes. The NPRM was prompted by reports of airspeed indication
discrepancies while flying at high altitudes in inclement weather. This
action revises the NPRM by reducing the proposed compliance time for
replacing certain pitot probes based on a risk assessment due to
additional reports of airspeed indication discrepancies while flying at
high altitudes in inclement weather. We are proposing this supplemental
NPRM (SNPRM) to prevent airspeed indication discrepancies during
inclement weather, which, depending on the prevailing altitude, could
lead to unknown accumulation of ice crystals and consequent reduced
controllability of the airplane. Since these actions impose an
additional burden over those proposed in the NPRM, we are reopening the
comment period to allow the public the chance to comment on these
proposed changes.
DATES: We must receive comments on this SNPRM by January 22, 2016.
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
[[Page 79751]]
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 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-
0250; 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
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-2015-0250;
Directorate Identifier 2014-NM-216-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
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would apply to all Airbus Model A318,
A319, A320, and A321 series airplanes. The NPRM published in the
Federal Register on March 6, 2015 (80 FR 12094) (``the NPRM''). The
NPRM was prompted by reports of airspeed indication discrepancies while
flying at high altitudes in inclement weather. The NPRM proposed to
require replacing certain pitot probes on the captain, first officer,
and standby sides with certain new pitot probes.
Actions Since Previous NPRM (80 FR 12094, March 6, 2015) Was Issued
Since we issued the NPRM (80 FR 12094, March 6, 2015), we have
determined it is necessary to reduce the compliance time for replacing
certain pitot probes based on a risk assessment due to additional
reports of airspeed indication discrepancies while flying at high
altitudes in inclement weather. The European Aviation Safety Agency
(EASA), which is the Technical Agent for the Member States of the
European Union, issued EASA Airworthiness Directive 2015-0205, dated
October 9, 2015 (referred to after this as the Mandatory Continuing
Airworthiness Information, or ``the MCAI''), to correct an unsafe
condition on all Airbus Model A318, A319, A320, and A321 series
airplanes. The MCAI states:
Occurrences have been reported on A320 family aeroplanes of
airspeed indication discrepancies while flying at high altitudes in
inclement weather conditions. Investigation results indicated that
A320 aeroplanes equipped with Thales Avionics Part Number (P/N)
50620-10 or P/N C16195AA pitot probes appear to have a greater
susceptibility to adverse environmental conditions that aeroplanes
equipped with certain other pitot probes.
Prompted by earlier occurrences, DGAC [Direction
G[eacute]n[eacute]rale de l'Aviation Civile] France issued [DGAC] AD
2001[dash]362 [https://ad.easa.europa.eu/blob/easa_ad_2001_362.pdf/AD_2001-362] [which corresponds to paragraph (f) of FAA AD
2004[dash]03[dash]33, Amendment 39[dash]13477 (69 FR 9936, March 3,
2004)] to require replacement of Thales (formerly known as Sextant)
P/N 50620[dash]10 pitot probes with Thales P/N C16195AA probes.
Since that [DGAC] AD was issued, Thales pitot probe P/N C15195BA
was designed, which improved airspeed indication behavior in heavy
rain conditions, but did not demonstrate the same level of
robustness to withstand high[dash]altitude ice crystals. Based on
these findings, EASA have decided to implement replacement of the
affected Thales [pitot] probes as a precautionary measure to improve
the safety level of the affected aeroplanes.
Consequently, EASA issued AD 2014-0237 (later revised) [https://ad.easa.europa.eu/blob/easa_ad_2014_0237.pdf/AD_2014-0237],
retaining the requirements of DGAC France AD 2001-362, which was
superseded, and cancelling two other DGAC ADs, to require
replacement of Thales Avionics pitot probes P/N C16195AA and P/N
C16195BA.
Since EASA issued AD 2014-0237R1 [https://ad.easa.europa.eu/ad/2014-0237R1] was issued, results of further analyses have determined
that the compliance time (48 months) of that AD has to be reduced in
relation to the risk assessment.
For the reasons described above, this [EASA] AD retains the
requirements of EASA AD 2014-0237R1, which is superseded, but
reduces the compliance time.
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-
0250.
Related Rulemaking
On February 4, 2004, we issued AD 2004-03-33, Amendment 39-13477
(69 FR 9936, March 3, 2004), applicable to certain Airbus Model A300 B2
and B4 series airplanes; Model A300 B4-600, A300 B4-600R, and A300 F4-
600R series airplanes; Model A310 series Airplanes; Model A319, A320,
and A321 series airplanes; Model A330-301, -321, -322, -341, and -342
airplanes; and Model A340 series airplanes. That AD requires, among
other actions, replacement of certain pitot probes with certain new
pitot probes. That AD was issued to prevent loss or fluctuation of
indicated airspeed, which could result in misleading information being
provided to the flightcrew. Accomplishing the replacement specified in
paragraph (g) of this SNPRM would terminate the requirements of
paragraph (f) of AD 2004-03-33, for that airplane only.
Related Service Information Under 1 CFR Part 51
Airbus has issued the following service information:
Service Bulletin A320-34-1170, Revision 30, dated June 18,
2015.
Service Bulletin A320-34-1456, Revision 01, dated May 15,
2012.
Service Bulletin A320-34-1463, Revision 01, dated May 15,
2012.
The service information describes procedures for replacing certain
Thales Avionics pitot probes on the captain, first officer, and standby
sides. This service information is reasonably available because the
interested parties have access to it through their normal course of
business or by the means identified in the ADDRESSES section of this
SNPRM.
[[Page 79752]]
Comments
We gave the public the opportunity to participate in developing
this SNPRM. We considered the comments received.
American Airlines supports the proposed compliance time of 48
months for retrofit.
Request To Refer To Revised Service Information
United Airlines (UAL) and Virgin America asked that the NPRM be
revised to refer to Airbus Service Bulletin A320-34-1170, Revision 29,
dated February 16, 2015. (The NPRM (80 FR 12094, March 6, 2015)
referred to Airbus Service Bulletin A320-34-1170, Revision 28, dated
September 1, 2014, as the appropriate source of service information for
replacing the pitot probes.) UAL stated that Airbus Service Bulletin
A320-34-1170, Revision 29, dated February 16, 2015, includes UAL
effectivity, as well as all A320 family airplanes fitted with Thales
Pitot Probes. Virgin America stated that Airbus Service Bulletin A320-
34-1170, Revision 28, dated September 1, 2014, is available only to
select operators who previously purchased the change; Airbus Service
Bulletin A320-34-1170, Revision 29, dated February 16, 2015, is
available to all operators with airplanes having Thales pitot probes
installed. American Airlines (AAL) asked that we refer to Airbus
Service Bulletin A320-34-1170, Revision 30, which is scheduled for
release in the near future. AAL added that the effectivity in Airbus
Service Bulletin A320-34-1170, Revision 28, dated September 1, 2014, is
incomplete.
We agree to refer to Airbus Service Bulletin A320-34-1170, Revision
30, dated June 18, 2015, for the pitot probe replacement. Airbus
Service Bulletin A320-34-1170, Revision 30, dated June 18, 2015, was
issued to update the operator list and related information in the
effectivity, and does not include additional work. We have changed
paragraph (g) of this SNPRM to refer to Airbus Service Bulletin A320-
34-1170, Revision 30, dated June 18, 2015. In addition, to give credit
for using Airbus Service Bulletin A320-34-1170, Revision 28, dated
September 1, 2014, and Airbus Service Bulletin A320-34-1170, Revision
29, dated February 16, 2015, we added new paragraphs (i)(1)(xxv) and
(i)(1)(xxvi) to this SNPRM.
Request To Reduce the Compliance Time
The Airline Pilots Association International (ALPA) asked that the
compliance time for replacement of the pitot probes, as specified in
paragraph (g) of the proposed AD (80 FR 12094, March 6, 2015), be
reduced to 24 months or less. ALPA stated that it recognizes the
potential flight safety risk of operating an airplane with reduced
controllability characteristics, which justifies reducing the
compliance time.
We agree with the request to reduce the compliance time for
replacement of the pitot probes. As specified under ``Actions Since
Previous NPRM was Issued,'' we have reduced the proposed compliance
time for replacing certain pitot probes based on a risk assessment due
to additional reports of airspeed indication discrepancies while flying
at high altitudes in inclement weather. EASA has issued Airworthiness
Directive 2015-0205, dated October 9, 2015, to reduce the compliance
time for replacement of the pitot probes to 24 months. We have changed
the compliance time in paragraph (g) of this SNPRM accordingly.
Request for Clarification
AAL stated the use of a pitot probe which meets the current icing
specification, as specified in the NPRM (80 FR 12094, March 6, 2015),
should note that a new icing specification is forthcoming. In addition,
the UTAS (formerly Goodrich) pitot probe having part number 0851HL is
built to the current specification. AAL noted that the data available
today shows that pitot probes on which the new icing requirement is met
should be available for retrofit in 2016.
We acknowledge the commenter's statement about the NPRM proposing
the use of a pitot probe that meets the current icing airworthiness
requirements and not the new icing airworthiness requirements of
Amendment 25-140 (79 FR 65508, November 4, 2014) to 14 CFR part 25.
Since we are currently not aware of any pitot probes certified to the
new icing airworthiness requirements, this SNPRM would mandate Goodrich
pitot probes having part number 0851HL, which meet the icing
airworthiness requirements in effect at the time of establishing the
certification basis for Airbus Model A318, A319, A320, and A321 series
airplanes. AAL may request approval for an alternative method of
compliance for the installation of pitot probes that meet the new
certification standards once the pitot probes are available for
installation, under the provisions of paragraph (k)(1) of this proposed
AD.
AAL also asked the following related questions and we have provided
a response to each comment:
What FAA activities are scheduled with suppliers to meet
the expectations of the new icing requirement? FAA activities
associated with the new icing requirements are related to new design
modifications. At this time we are not mandating installation of pitot
probes which meet the new icing certification standards.
Does the FAA anticipate issuing a new AD mandating a
retrofit/forward fit to the new icing requirement? We do not plan to
issue further rulemaking mandating a retrofit/forward fit to the new
icing requirement at this time.
Would the FAA extend the compliance time if another pitot
probe supplier demonstrates compliance to the new icing requirement? We
would not extend the compliance time because this SNPRM does not
require installing pitot probes that meet the new icing requirement;
therefore, the compliance time for the installation is considered
adequate to address the unsafe condition.
FAA's Determination and Requirements of This SNPRM
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.
Certain changes described above expand the scope of the proposed AD
(80 FR 12094, March 6, 2015). As a result, we have determined that it
is necessary to reopen the comment period to provide additional
opportunity for the public to comment on this SNPRM.
Explanation of ``RC'' Procedures and Tests in Service Information
The FAA worked in conjunction with industry, under the
Airworthiness Directive Implementation Aviation Rulemaking Committee
(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 procedures
and tests
[[Page 79753]]
identified as RC (required for compliance) in any service information
have a direct effect on detecting, preventing, resolving, or
eliminating an identified unsafe condition.
As specified in a NOTE under the Accomplishment Instructions of
Airbus Service Bulletin A320-34-1170, Revision 30, dated June 18, 2015,
procedures and tests that are identified as RC in any service
information 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
an airworthy 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 4 work-hours per product
to comply with the new basic requirements of this proposed AD. The
average labor rate is $85 per work-hour. Required parts would cost
about $21,930 per product. Based on these figures, we estimate the cost
of this proposed AD on U.S. operators to be $21,223,310, or $22,270 per
product.
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-2015-0250; Directorate Identifier 2014-NM-
216-AD.
(a) Comments Due Date
We must receive comments by January 22, 2016.
(b) Affected ADs
This AD affects AD 2004-03-33, Amendment 39-13477 (69 FR 9936,
March 3, 2004).
(c) Applicability
This AD applies to the airplanes identified in paragraphs
(c)(1), (c)(2), (c)(3), and (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 34, Navigation.
(e) Reason
This AD was prompted by reports of airspeed indication
discrepancies while flying at high altitudes in inclement weather.
We are issuing this AD to prevent airspeed indication discrepancies
during inclement weather, which, depending on the prevailing
altitude, could lead to unknown accumulation of ice crystals and
consequent reduced controllability of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Replacement of Certain Pitot Probes on the Captain, First Officer,
and Standby Sides
Within 24 months after the effective date of this AD: Replace
any Thales pitot probe having part number (P/N) C16195AA or P/N
C16195BA, with a Goodrich pitot probe having P/N 0851HL, in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A320-34-1170, Revision 30, dated June 18, 2015.
Accomplishing the replacement in this paragraph terminates the
requirements of paragraph (f) of AD 2004-03-33, Amendment 39-13477
(69 FR 9936, March 3, 2004), for that airplane only.
(h) Optional Methods of Compliance for Replacement Required by
Paragraph (g) of This AD
(1) Replacement of the pitot probes in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A320-34-1456,
Revision 01, dated May 15, 2012 (pitot probes on the captain and
standby sides); and Airbus Service Bulletin A320-34-1463, Revision
01, dated May 15, 2012 (pitot probes on the first officer side); is
an acceptable method of compliance with the requirements of
paragraph (g) of this AD.
(2) Airplanes on which Airbus Modification 25578 was embodied in
production, except for post-modification 25578 airplanes on which
Airbus Modification 155737 (installation of Thales pitot probes) was
also embodied in production, are compliant with the requirements of
paragraph (g) of this AD, provided it can be conclusively determined
that no Thales pitot probe having P/N C16195AA, P/N C16195BA, or P/N
50620-10 has been installed since the date of issuance of the
original certificate of airworthiness or the date of issuance of the
original export certificate of airworthiness. Post-modification
25578 airplanes on which Airbus Modification 155737 (installation of
Thales pitot probes) was also embodied in production must be in
compliance with the requirements of paragraph (g) of this AD.
(i) Credit for Previous Actions
(1) This paragraph provides credit for the actions required by
paragraph (g) of this AD, if those actions were performed before the
effective date of this AD using the service
[[Page 79754]]
information identified in paragraph (i)(1)(i) through (i)(1)(xxvi)
of this AD. This service information is not incorporated by
reference in this AD.
(i) Airbus Service Bulletin A320-34-1170, Revision 04, dated May
24, 2000.
(ii) Airbus Service Bulletin A320-34-1170, Revision 05, dated
September 11, 2000.
(iii) Airbus Service Bulletin A320-34-1170, Revision 06, dated
October 18, 2001.
(iv) Airbus Service Bulletin A320-34-1170, Revision 07, dated
December 4, 2001.
(v) Airbus Service Bulletin A320-34-1170, Revision 08, dated
January 15, 2003.
(vi) Airbus Service Bulletin A320-34-1170, Revision 09, dated
February 17, 2003.
(vii) Airbus Service Bulletin A320-34-1170, Revision 10, dated
November 21, 2003.
(viii) Airbus Service Bulletin A320-34-1170, Revision 11, dated
August 18, 2004.
(ix) Airbus Service Bulletin A320-34-1170, Revision 12, dated
December 2, 2004.
(x) Airbus Service Bulletin A320-34-1170, Revision 13, dated
January 18, 2005.
(xi) Airbus Service Bulletin A320-34-1170, Revision 14, dated
April 21, 2005.
(xii) Airbus Service Bulletin A320-34-1170, Revision 15, dated
July 19, 2005.
(xiii) Airbus Service Bulletin A320-34-1170, Revision 16, dated
November 23, 2006.
(xiv) Airbus Service Bulletin A320-34-1170, Revision 17, dated
February 14, 2007.
(xv) Airbus Service Bulletin A320-34-1170, Revision 18, dated
October 9, 2009.
(xvi) Airbus Service Bulletin A320-34-1170, Revision 19, dated
November 9, 2009.
(xvii) Airbus Service Bulletin A320-34-1170, Revision 20, dated
December 1, 2010.
(xviii) Airbus Service Bulletin A320-34-1170, Revision 21, dated
March 24, 2011.
(xix) Airbus Service Bulletin A320-34-1170, Revision 22, dated
July 19, 2011.
(xx) Airbus Service Bulletin A320-34-1170, Revision 23, dated
February 3, 2012.
(xxi) Airbus Service Bulletin A320-34-1170, Revision 24, dated
April 12, 2012.
(xxii) Airbus Service Bulletin A320-34-1170, Revision 25, dated
September 4, 2012.
(xxiii) Airbus Service Bulletin A320-34-1170, Revision 26, dated
September 16, 2013.
(xxiv) Airbus Service Bulletin A320-34-1170, Revision 27, dated
March 18, 2014.
(xxv) Airbus Service Bulletin A320-34-1170, Revision 28, dated
September 1, 2014.
(xxvi) Airbus Service Bulletin A320-34-1170, Revision 29, dated
February 16, 2015.
(2) This paragraph provides credit for the replacement of pitot
probes on the captain and standby sides specified in paragraph
(h)(1) of this AD, if the replacement was performed before the
effective date of this AD using Airbus Service Bulletin A320-34-
1456, dated December 2, 2009, which is not incorporated by reference
in this AD.
(3) This paragraph provides credit for the replacement of pitot
probes on the first officer side as specified in paragraph (h)(1) of
this AD, if those actions were performed before the effective date
of this AD using Airbus Service Bulletin A320-34-1463, dated March
9, 2010, which is not incorporated by reference in this AD.
(j) Parts Installation Limitations
(1) At the applicable time specified in paragraph (j)(1)(i) or
(j)(1)(ii) of this AD: No person may install on any airplane a
Thales pitot probe having P/N C16195AA or P/N C16195BA.
(i) For airplanes with a Thales pitot probe having P/N C16195AA
or P/N C16195BA installed: After accomplishing the replacement
required by paragraph (g) of this AD.
(ii) For airplanes without a Thales pitot probe having P/N
C16195AA or P/N C16195BA installed: As of the effective date of this
AD.
(2) As of the effective date of this AD, no person may install
on any airplane a Thales pitot probe having part number P/N 50620-
10.
(k) 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) 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
European Aviation Safety Agency (EASA); or Airbus's EASA Design
Organization Approval (DOA). If approved by the DOA, the approval
must include the DOA-authorized signature.
(3) Required for Compliance (RC): If any service information
contains procedures or tests that are identified as RC, those
procedures and tests must be done to comply with this AD; any
procedures or tests that are not identified as RC are recommended.
Those procedures and tests that are not identified as RC may be
deviated from using accepted methods in accordance with the
operator's maintenance or inspection program without obtaining
approval of an AMOC, provided the procedures and tests identified as
RC can be done and the airplane can be put back in an airworthy
condition. Any substitutions or changes to procedures or tests
identified as RC require approval of an AMOC.
(l) Related Information
(1) Refer to EASA Airworthiness Directive 2015-0205, dated
October 9, 2015, for related information. This MCAI may be found in
the AD docket on the Internet at https://www.regulations.gov by
searching for and locating Docket No. FAA-2015-0250.
(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 November 25, 2015.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2015-30821 Filed 12-22-15; 8:45 am]
BILLING CODE 4910-13-P
