Airworthiness Directives; Airbus Airplanes, 71593-71596 [2016-23647]
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Federal Register / Vol. 81, No. 201 / Tuesday, October 18, 2016 / Rules and Regulations
(2) Is not a ‘‘significant rule’’ under
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979);
(3) Will not affect intrastate aviation
in Alaska to the extent that it justifies
making a regulatory distinction; 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.
We prepared an economic evaluation
of the estimated costs to comply with
this AD and placed it in the AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
2016–21–02 Sikorsky Aircraft Corporation:
Amendment 39–18683; Docket No.
FAA–2016–6640; Directorate Identifier
2015–SW–084–AD.
(b) Unsafe Condition
This AD defines the unsafe condition as
inadvertent tripping of a fire bottle inertiaswitch. This condition results in an
unintentional and undetected fire bottle
discharge and subsequent unavailability of
fire suppression in the event of a fire.
(c) Effective Date
This AD becomes effective November 22,
2016.
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(d) Compliance
You are responsible for performing each
action required by this AD within the
specified compliance time unless it has
already been accomplished prior to that time.
(e) Required Actions
Within 90 days:
(1) Alter each fire bottle inertia switch by
following the Accomplishment Instructions,
paragraph 3.B., of Sikorsky Alert Service
Bulletin 92–26–005A, Revision A, dated June
27, 2014.
(2) Perform a cartridge functional test.
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Jkt 241001
(g) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Boston Aircraft
Certification Office, FAA, may approve
AMOCs for this AD. Send your proposal to:
Kris Greer, Aviation Safety Engineer, Boston
Aircraft Certification Office, Engine &
Propeller Directorate,1200 District Avenue,
Burlington, Massachusetts 01803; telephone
(781) 238–7799; email kristopher.greer@
faa.gov.
(2) For operations conducted under a 14
CFR part 119 operating certificate or under
14 CFR part 91, subpart K, we suggest that
you notify your principal inspector, or
lacking a principal inspector, the manager of
the local flight standards district office or
certificate holding district office before
operating any aircraft complying with this
AD through an AMOC.
(h) Additional Information
Sikorsky Alert Service Bulletin 92–26–005,
Basic Issue, dated June 18, 2014, which is not
incorporated by reference, contains
additional information about the subject of
this final rule. For service information
identified in this final rule, contact Sikorsky
Aircraft Corporation, Customer Service
Engineering, 124 Quarry Road, Trumbull, CT
06611; telephone 1–800–Winged–S or 203–
416–4299; email wcs_cust_service_eng.grsik@lmco.com. You may review a copy of
this service information at the FAA, Office of
the Regional Counsel, Southwest Region,
10101 Hillwood Pkwy., Room 6N–321, Fort
Worth, TX 76177.
(i) Subject
Joint Aircraft Service Component (JASC)
Code: 2621 Fire Bottle, Fixed.
(a) Applicability
This AD applies to Model S–92A
helicopters, serial number 920006 through
920250, certificated in any category.
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(f) Credit for Actions Previously Completed
Compliance with Sikorsky Alert Service
Bulletin 92–26–005, Basic Issue, dated June
18, 2014, before the effective date of this AD
is considered acceptable for compliance with
the actions specified in paragraph (e) of this
AD.
(j) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference of
the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(i) Sikorsky Alert Service Bulletin 92–26–
005A, Revision A, dated June 27, 2014.
(ii) Reserved.
(3) For Sikorsky service information
identified in this final rule, contact Sikorsky
Aircraft Corporation, Customer Service
Engineering, 124 Quarry Road, Trumbull, CT
06611; telephone 1–800–Winged–S or 203–
416–4299; email wcs_cust_service_eng.grsik@lmco.com.
(4) You may view this service information
at FAA, Office of the Regional Counsel,
Southwest Region, 10101 Hillwood Pkwy.,
Room 6N–321, Fort Worth, TX 76177. For
information on the availability of this
material at the FAA, call (817) 222–5110.
(5) You may view this service information
that is incorporated by reference at the
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National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
(202) 741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Fort Worth, Texas, on October 3,
2016.
Lance T. Gant,
Manager, Rotorcraft Directorate, Aircraft
Certification Service.
[FR Doc. 2016–24738 Filed 10–17–16; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–6418; Directorate
Identifier 2015–NM–158–AD; Amendment
39–18676; AD 2016–20–10]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for all
Airbus Model A330–200 Freighter,
–200, and –300 series airplanes; and
Airbus Model A340–200, –300, –500,
and –600 series airplanes. This AD was
prompted by reports of fuel leaking
through fuel pump electrical connectors
and of fuel pump electrical connector
damage caused by the build-up of
moisture behind the electrical
connectors. This AD requires an
inspection of the fuel pumps to identify
their part numbers and replacement of
affected pumps. We are issuing this AD
to prevent a potential ignition source
and a fuel leak through damaged fuel
pump electrical connectors, which
creates a flammability risk in an area
adjacent to the fuel tank.
DATES: This AD is effective November
22, 2016.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of November 22, 2016.
ADDRESSES: For service information
identified in this final rule, contact
Airbus SAS, Airworthiness Office—
EAL, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone
+33 5 61 93 36 96; fax +33 5 61 93 45
80; email airworthiness.A330-A340@
airbus.com; Internet https://
www.airbus.com. You may view this
referenced service information at the
SUMMARY:
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FAA, Transport Airplane Directorate,
1601 Lind Avenue SW., Renton, WA.
For information on the availability of
this material at the FAA, call 425–227–
1221. It is also available on the Internet
at https://www.regulations.gov by
searching for and locating Docket No.
FAA–2016–6418.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2016–
6418; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this AD, the regulatory
evaluation, any comments received, and
other information. The street address for
the Docket Office (telephone 800–647–
5527) is Docket Management Facility,
U.S. Department of Transportation,
Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue SE.,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT:
Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA
98057–3356; telephone: 425–227–1138;
fax: 425–227–1149.
SUPPLEMENTARY INFORMATION:
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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 A330–200
Freighter, –200, and –300 series
airplanes; and Airbus Model A340–200,
–300, –500, and –600 series airplanes.
The NPRM published in the Federal
Register on May 9, 2016 (81 FR 28033)
(‘‘the NPRM’’). The NPRM was
prompted by reports of fuel leaking
through fuel pump electrical connectors
and of fuel pump electrical connector
damage caused by the build-up of
moisture behind the electrical
connectors. The NPRM proposed to
require an inspection of the fuel pumps
to identify their part numbers and
replacement of affected pumps. We are
issuing this AD to prevent a potential
ignition source and a fuel leak through
damaged fuel pump electrical
connectors. This condition creates a
flammability risk in an area adjacent to
the fuel tank.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA AD 2015–0194,
dated September 22, 2015, to correct an
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12:31 Oct 17, 2016
Jkt 241001
unsafe condition for all Airbus Model
A330–200 Freighter, –200, and –300
series airplanes; and Airbus Model
A340–200, –300, –500, and –600 series
airplanes. The MCAI states:
Operators reported cases of fuel leak
through fuel pump electrical connectors.
Subsequent investigation revealed fuel pump
electrical connector damage caused by
moisture build up behind the electrical
connector.
This condition, if not detected and
corrected, could create concurrently an
ignition source and fuel leak as a result of a
single failure, resulting in exposure to a
flammability risk in an adjacent area to the
fuel tank.
To address this unsafe condition, Airbus
published Service Bulletins (SB) A330–28–
3127, SB A340–28–4138 and SB A340–28–
5060, providing inspection/identification
instructions, and instructions for
replacement of the fuel pumps.
For the reasons described above, this
[EASA] AD requires identification and
replacement of the affected fuel pumps.
You may examine the MCAI in the
AD docket on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2016–
6418.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comment
received on the NPRM and the FAA’s
response to the comment.
Request To Clarify Compliance for
Affected Pumps
American Airlines (AAL) requested
that we clarify which groups of pumps
paragraphs (h)(1) and (h)(2) of the
proposed AD are intended to control.
Where individual items begin with ‘‘All
of the affected pumps. . . .’’ AAL
explained that paragraph (h) of the
proposed AD must be intended to refer
to all of the affected pumps on each
airplane. AAL pointed out that this
language creates a requirement for all
airplanes that have one or more pumps
having part number (P/N) 568–1–
28300–001 or 568–1–28300–002
installed to be modified in accordance
with the service information within 72
months. AAL asserted that consistent
references to ‘‘each affected pump’’
confuse that interpretation and seem to
imply that each pump is treated
separately. If the intent is to control the
compliance time for replacement at the
pump level, AAL stated that it would be
more efficient to simply state that –001
and –002 pumps must be replaced
within 72 months, while –100 and –101
pumps must be replaced within 96
months. If the intent is to control the
compliance time at the airplane level,
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AAL stated that the language throughout
paragraph (h) of the proposed AD
should be revised to reflect that intent;
American provided some example
language.
We agree that this AD should specify
the compliance times at the airplane
level. Therefore, we have revised
paragraphs (h)(1) and (h)(2) of this AD
by replacing the text in the beginning of
the sentences, ‘‘For affected fuel pumps
that have . . . , ’’ with the text ‘‘For
airplanes with fuel pumps that have
. . .’’ in order to clearly identify the
airplane configuration.
Conclusion
We reviewed the relevant data,
considered the comment received, and
determined that air safety and the
public interest require adopting this AD
with the changes described previously
and minor editorial changes. We have
determined that these minor changes:
• Are consistent with the intent that
was proposed in the NPRM for
correcting the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM.
We also determined that these
changes will not increase the economic
burden on any operator or increase the
scope of this AD.
Related Service Information Under 1
CFR Part 51
Airbus has issued the following
service information:
• Airbus Service Bulletin A330–28–
3127, Revision 02, dated April 14, 2016.
• Airbus Service Bulletin A340–28–
4138, Revision 01, dated September 24,
2015.
• Airbus Service Bulletin A340–28–
5060, Revision 01, dated September 24,
2015.
The service information describes
procedures to identify and replace
affected fuel pumps with serviceable
fuel pumps. These documents are
distinct since they apply to different
airplane models. This service
information is reasonably available
because the interested parties have
access to it through their normal course
of business or by the means identified
in the ADDRESSES section.
Costs of Compliance
We estimate that this AD affects 99
airplanes of U.S. registry.
We also estimate that it will take
about 4 work-hours per product to
comply with the basic requirements of
this AD. The average labor rate is $85
per work-hour. Based on these figures,
we estimate the cost of this AD on U.S.
operators to be $33,660, or $340 per
product.
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In addition, we estimate that any
necessary follow-on actions would take
about 17 work-hours and require parts
costing $10,400, for a cost of $11,845
per product. We have no way of
determining the number of airplanes
that might need these actions.
Authority for This Rulemaking
Regulatory Findings
We determined that this AD will not
have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
the States, on the relationship between
the national government and the States,
or on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in
Alaska; and
4. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
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List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
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12:31 Oct 17, 2016
Jkt 241001
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. ‘‘Subtitle VII:
Aviation Programs,’’ describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in ‘‘Subtitle VII,
Part A, Subpart III, Section 44701:
General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Adoption of the Amendment
PART 39—AIRWORTHINESS
DIRECTIVES
2016–20–10 Airbus: Amendment 39–18676;
Docket No. FAA–2016–6418; Directorate
Identifier 2015–NM–158–AD.
(a) Effective Date
This AD is effective November 22, 2016.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Airbus Model A330–
223F and –243F airplanes; Model A330–201,
–202, –203, –223, and –243 airplanes; Model
A330–301, –302, –303, –321, –322, –323,
–341, –342, and –343 airplanes; Model
A340–211, –212, and –213 airplanes; Model
A340–311, –312, and –313 airplanes; Model
A340–541 and A340–642 airplanes;
certificated in any category; all manufacturer
serial numbers.
(d) Subject
Air Transport Association (ATA) of
America Code 28, Fuel.
(e) Reason
This AD was prompted by reports of fuel
leaking through fuel pump electrical
connectors and of fuel pump electrical
connector damage caused by the build-up of
moisture behind the electrical connectors.
Electrical connections that become damaged
by moisture can create an ignition source and
a fuel leak. We are issuing this AD to prevent
a potential ignition source and a fuel leak
through damaged fuel pump electrical
connectors, which creates a flammability risk
in an area adjacent to the fuel tank.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Identify Part Numbers (P/Ns)
Within 48 months after the effective date
of this AD, inspect each fuel pump to
identify the part number, in accordance with
the Accomplishment Instructions of Airbus
Service Bulletin A330–28–3127, Revision 02,
dated April 14, 2016; Airbus Service Bulletin
A340–28–4138, Revision 01, dated
September 24, 2015; or Airbus Service
Bulletin A340–28–5060, Revision 01, dated
September 24, 2015; as applicable to airplane
model. A review of airplane delivery or
maintenance records is acceptable in lieu of
this inspection if the part number of the fuel
pump can be conclusively determined from
that review.
(h) Modification
If, during the inspection required by
paragraph (g) of this AD, it is determined that
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71595
any affected fuel pump is installed: Within
the compliance time specified in paragraph
(h)(1) or (h)(2) of this AD, depending on the
configuration of the affected fuel pumps
installed, replace each affected fuel pump
with a serviceable fuel pump, in accordance
with the Accomplishment Instructions of
Airbus Service Bulletin A330–28–3127,
Revision 02, dated April 14, 2016; Airbus
Service Bulletin A340–28–4138, Revision 01,
dated September 24, 2015; or Airbus Service
Bulletin A340–28–5060, Revision 01, dated
September 24, 2015; as applicable to airplane
model.
(1) For airplanes with fuel pumps that have
a part number or combination of part
numbers that are specified in paragraphs
(h)(1)(i) through (h)(1)(vi) of this AD: Do the
replacement within 72 months after the
effective date of this AD.
(i) All installed fuel pumps have P/N 568–
1–28300–001.
(ii) All installed fuel pumps have P/N 568–
1–28300–002.
(iii) Installed fuel pumps have a
combination of P/Ns 568–1–28300–001 and
568–1–28300–002.
(iv) Installed fuel pumps have a
combination of P/Ns 568–1–28300–001 and
568–1–28300–101.
(v) Installed fuel pumps have a
combination of P/Ns 568–1–28300–002 and
568–1–28300–101.
(vi) Installed fuel pumps have a
combination of P/Ns 568–1–28300–001, 568–
1–28300–002, and 568–1–28300–101.
(2) For airplanes with fuel pumps that have
a part number or combination of part
numbers that are specified in paragraphs
(h)(2)(i) through (h)(2)(iii) of this AD: Do the
replacement within 96 months after the
effective date of this AD.
(i) All installed fuel pumps have P/N 568–
1–28300–100.
(ii) All installed fuel pumps have P/N 568–
1–28300–101.
(iii) Installed fuel pumps have a
combination of P/Ns 568–1–28300–100 and
568–1–28300–101.
(i) Definitions
(1) For the purpose of this AD, an ‘‘affected
fuel pump’’ is defined as any pump having
P/N 568–1–28300–001, 568–1–28300–002,
568–1–28300–100, or 568–1–28300–101.
(2) For the purpose of this AD, a
‘‘serviceable fuel pump’’ is a pump having a
part number not listed in paragraph (i)(1) of
this AD.
(j) No Reporting Requirement
Although Airbus Service Bulletin A330–
28–3127, Revision 02, dated April 14, 2016;
Airbus Service Bulletin A340–28–4138,
Revision 01, dated September 24, 2015; and
Airbus Service Bulletin A340–28–5060,
Revision 01, dated September 24, 2015;
specify submitting certain information to the
manufacturer, and specifies that action as
‘‘RC’’ (Required for Compliance), this AD
does not include that requirement.
(k) Parts Installation Prohibition
After the identification of the fuel pump
part numbers required by paragraph (g) of
this AD, comply with the prohibition
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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) Credit for Previous Actions
This paragraph provides credit for actions
required by paragraphs (g) and (h) of this AD,
if those actions were performed before the
effective date of this AD using the applicable
service information specified in paragraphs
(l)(1), (l)(2), (l)(3), and (l)(4) of this AD. This
service information is not incorporated by
reference in this AD.
(1) Airbus Service Bulletin A330–28–3127,
dated July 14, 2015.
(2) Airbus Service Bulletin A330–28–3127,
Revision 01, dated September 24, 2015.
(3) Airbus Service Bulletin A340–28–4138,
dated July 14, 2015.
(4) Airbus Service Bulletin A340–28–5060,
dated July 14, 2015.
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required by paragraph (k)(1) or (k)(2) of this
AD, as applicable.
(1) For an airplane that does not have an
affected fuel pump installed: After the
identification of the fuel pump part numbers
required by paragraph (g) of this AD, no
person may install an affected fuel pump on
the airplane.
(2) For an airplane that has an affected fuel
pump installed: After modification of the
airplane as required by paragraph (h) of this
AD, no person may install an affected fuel
pump on the airplane.
(n) Related Information
(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:
Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone: 425–227–1138; 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/
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): Except
as provide by paragraph (j) of this AD, if any
service information contains procedures or
tests that are identified as RC, those
procedures and tests must be done to comply
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12:31 Oct 17, 2016
Jkt 241001
(1) Refer to Continuing Airworthiness
Information (MCAI) EASA AD 2015–0194,
dated September 22, 2015, for related
information. You may examine the MCAI on
the Internet at https://www.regulations.gov by
searching for and locating Docket No. FAA–
2016–6418.
(o) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless this AD specifies otherwise.
(i) Airbus Service Bulletin A330–28–3127,
Revision 02, dated April 14, 2016.
(ii) Airbus Service Bulletin A340–28–4138,
Revision 01, dated September 24, 2015.
(iii) Airbus Service Bulletin A340–28–
5060, Revision 01, dated September 24, 2015.
(3) For service information identified in
this AD, contact Airbus SAS, Airworthiness
Office—EAL, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone: +33
5 61 93 36 96; fax: +33 5 61 93 45 80; email:
airworthiness.A330–A340@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.
(4) 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.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on
September 26, 2016.
Dionne Palermo,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2016–23647 Filed 10–17–16; 8:45 am]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–8470; Directorate
Identifier 2013–NM–199–AD; Amendment
39–18674; AD 2016–20–08]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are superseding
Airworthiness Directive (AD) 95–21–09
for all Airbus Model A300 series
airplanes, and Airbus Model A300 B4–
600, B4–600R, and F4–600R series
airplanes, and Model A300 C4–605R
Variant F airplanes (collectively called
Model A300–600 series airplanes). AD
95–21–09 required repetitive
inspections for cracking of the No. 2 flap
beams, and replacement of the flap
beams, if necessary; and provided
optional modifications for extending
certain inspection thresholds, and an
optional terminating modification for
certain inspections. This new AD
requires reduced compliance times for
inspections and also reduces the
number of airplanes affected. This AD
was prompted by a determination that
the compliance times must be reduced.
We are issuing this AD to detect and
correct cracking of the No. 2 flap beams,
which could result in rupture of the flap
beams and reduced structural integrity
of the airplane.
DATES: This AD is effective November
22, 2016.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of November 22, 2016.
The Director of the Federal Register
approved the incorporation by reference
of certain other publications listed in
this AD as of November 17, 1995 (60 FR
53847, October 18, 1995).
ADDRESSES: For service information
identified in this final rule, 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.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
SUMMARY:
E:\FR\FM\18OCR1.SGM
18OCR1
]]>Agencies
[Federal Register Volume 81, Number 201 (Tuesday, October 18, 2016)]
[Rules and Regulations]
[Pages 71593-71596]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-23647]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2016-6418; Directorate Identifier 2015-NM-158-AD;
Amendment 39-18676; AD 2016-20-10]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for all
Airbus Model A330-200 Freighter, -200, and -300 series airplanes; and
Airbus Model A340-200, -300, -500, and -600 series airplanes. This AD
was prompted by reports of fuel leaking through fuel pump electrical
connectors and of fuel pump electrical connector damage caused by the
build-up of moisture behind the electrical connectors. This AD requires
an inspection of the fuel pumps to identify their part numbers and
replacement of affected pumps. We are issuing this AD to prevent a
potential ignition source and a fuel leak through damaged fuel pump
electrical connectors, which creates a flammability risk in an area
adjacent to the fuel tank.
DATES: This AD is effective November 22, 2016.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of November 22,
2016.
ADDRESSES: For service information identified in this final rule,
contact Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax
+33 5 61 93 45 80; email airworthiness.A330-A340@airbus.com; Internet
https://www.airbus.com. You may view this referenced service information
at the
[[Page 71594]]
FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA.
For information on the availability of this material at the FAA, call
425-227-1221. It is also available on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2016-
6418.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2016-
6418; or in person at the Docket Management Facility between 9 a.m. and
5 p.m., Monday through Friday, except Federal holidays. The AD docket
contains this AD, the regulatory evaluation, any comments received, and
other information. The street address for the Docket Office (telephone
800-647-5527) is Docket Management Facility, U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone: 425-227-1138;
fax: 425-227-1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would apply to all Airbus Model A330-200
Freighter, -200, and -300 series airplanes; and Airbus Model A340-200,
-300, -500, and -600 series airplanes. The NPRM published in the
Federal Register on May 9, 2016 (81 FR 28033) (``the NPRM''). The NPRM
was prompted by reports of fuel leaking through fuel pump electrical
connectors and of fuel pump electrical connector damage caused by the
build-up of moisture behind the electrical connectors. The NPRM
proposed to require an inspection of the fuel pumps to identify their
part numbers and replacement of affected pumps. We are issuing this AD
to prevent a potential ignition source and a fuel leak through damaged
fuel pump electrical connectors. This condition creates a flammability
risk in an area adjacent to the fuel tank.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA AD
2015-0194, dated September 22, 2015, to correct an unsafe condition for
all Airbus Model A330-200 Freighter, -200, and -300 series airplanes;
and Airbus Model A340-200, -300, -500, and -600 series airplanes. The
MCAI states:
Operators reported cases of fuel leak through fuel pump
electrical connectors. Subsequent investigation revealed fuel pump
electrical connector damage caused by moisture build up behind the
electrical connector.
This condition, if not detected and corrected, could create
concurrently an ignition source and fuel leak as a result of a
single failure, resulting in exposure to a flammability risk in an
adjacent area to the fuel tank.
To address this unsafe condition, Airbus published Service
Bulletins (SB) A330-28-3127, SB A340-28-4138 and SB A340-28-5060,
providing inspection/identification instructions, and instructions
for replacement of the fuel pumps.
For the reasons described above, this [EASA] AD requires
identification and replacement of the affected fuel pumps.
You may examine the MCAI in the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2016-
6418.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comment received on the NPRM and
the FAA's response to the comment.
Request To Clarify Compliance for Affected Pumps
American Airlines (AAL) requested that we clarify which groups of
pumps paragraphs (h)(1) and (h)(2) of the proposed AD are intended to
control. Where individual items begin with ``All of the affected pumps.
. . .'' AAL explained that paragraph (h) of the proposed AD must be
intended to refer to all of the affected pumps on each airplane. AAL
pointed out that this language creates a requirement for all airplanes
that have one or more pumps having part number (P/N) 568-1-28300-001 or
568-1-28300-002 installed to be modified in accordance with the service
information within 72 months. AAL asserted that consistent references
to ``each affected pump'' confuse that interpretation and seem to imply
that each pump is treated separately. If the intent is to control the
compliance time for replacement at the pump level, AAL stated that it
would be more efficient to simply state that -001 and -002 pumps must
be replaced within 72 months, while -100 and -101 pumps must be
replaced within 96 months. If the intent is to control the compliance
time at the airplane level, AAL stated that the language throughout
paragraph (h) of the proposed AD should be revised to reflect that
intent; American provided some example language.
We agree that this AD should specify the compliance times at the
airplane level. Therefore, we have revised paragraphs (h)(1) and (h)(2)
of this AD by replacing the text in the beginning of the sentences,
``For affected fuel pumps that have . . . , '' with the text ``For
airplanes with fuel pumps that have . . .'' in order to clearly
identify the airplane configuration.
Conclusion
We reviewed the relevant data, considered the comment received, and
determined that air safety and the public interest require adopting
this AD with the changes described previously and minor editorial
changes. We have determined that these minor changes:
Are consistent with the intent that was proposed in the
NPRM for correcting the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM.
We also determined that these changes will not increase the
economic burden on any operator or increase the scope of this AD.
Related Service Information Under 1 CFR Part 51
Airbus has issued the following service information:
Airbus Service Bulletin A330-28-3127, Revision 02, dated
April 14, 2016.
Airbus Service Bulletin A340-28-4138, Revision 01, dated
September 24, 2015.
Airbus Service Bulletin A340-28-5060, Revision 01, dated
September 24, 2015.
The service information describes procedures to identify and
replace affected fuel pumps with serviceable fuel pumps. These
documents are distinct since they apply to different airplane models.
This service information is reasonably available because the interested
parties have access to it through their normal course of business or by
the means identified in the ADDRESSES section.
Costs of Compliance
We estimate that this AD affects 99 airplanes of U.S. registry.
We also estimate that it will take about 4 work-hours per product
to comply with the basic requirements of this AD. The average labor
rate is $85 per work-hour. Based on these figures, we estimate the cost
of this AD on U.S. operators to be $33,660, or $340 per product.
[[Page 71595]]
In addition, we estimate that any necessary follow-on actions would
take about 17 work-hours and require parts costing $10,400, for a cost
of $11,845 per product. We have no way of determining the number of
airplanes that might need these actions.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We determined that this AD will not have federalism implications
under Executive Order 13132. This AD will not have a substantial direct
effect on the States, on the relationship between the national
government and the States, or on the distribution of power and
responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in Alaska; and
4. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
2016-20-10 Airbus: Amendment 39-18676; Docket No. FAA-2016-6418;
Directorate Identifier 2015-NM-158-AD.
(a) Effective Date
This AD is effective November 22, 2016.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Airbus Model A330-223F and -243F airplanes;
Model A330-201, -202, -203, -223, and -243 airplanes; Model A330-
301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes;
Model A340-211, -212, and -213 airplanes; Model A340-311, -312, and
-313 airplanes; Model A340-541 and A340-642 airplanes; certificated
in any category; all manufacturer serial numbers.
(d) Subject
Air Transport Association (ATA) of America Code 28, Fuel.
(e) Reason
This AD was prompted by reports of fuel leaking through fuel
pump electrical connectors and of fuel pump electrical connector
damage caused by the build-up of moisture behind the electrical
connectors. Electrical connections that become damaged by moisture
can create an ignition source and a fuel leak. We are issuing this
AD to prevent a potential ignition source and a fuel leak through
damaged fuel pump electrical connectors, which creates a
flammability risk in an area adjacent to the fuel tank.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Identify Part Numbers (P/Ns)
Within 48 months after the effective date of this AD, inspect
each fuel pump to identify the part number, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A330-28-3127,
Revision 02, dated April 14, 2016; Airbus Service Bulletin A340-28-
4138, Revision 01, dated September 24, 2015; or Airbus Service
Bulletin A340-28-5060, Revision 01, dated September 24, 2015; as
applicable to airplane model. A review of airplane delivery or
maintenance records is acceptable in lieu of this inspection if the
part number of the fuel pump can be conclusively determined from
that review.
(h) Modification
If, during the inspection required by paragraph (g) of this AD,
it is determined that any affected fuel pump is installed: Within
the compliance time specified in paragraph (h)(1) or (h)(2) of this
AD, depending on the configuration of the affected fuel pumps
installed, replace each affected fuel pump with a serviceable fuel
pump, in accordance with the Accomplishment Instructions of Airbus
Service Bulletin A330-28-3127, Revision 02, dated April 14, 2016;
Airbus Service Bulletin A340-28-4138, Revision 01, dated September
24, 2015; or Airbus Service Bulletin A340-28-5060, Revision 01,
dated September 24, 2015; as applicable to airplane model.
(1) For airplanes with fuel pumps that have a part number or
combination of part numbers that are specified in paragraphs
(h)(1)(i) through (h)(1)(vi) of this AD: Do the replacement within
72 months after the effective date of this AD.
(i) All installed fuel pumps have P/N 568-1-28300-001.
(ii) All installed fuel pumps have P/N 568-1-28300-002.
(iii) Installed fuel pumps have a combination of P/Ns 568-1-
28300-001 and 568-1-28300-002.
(iv) Installed fuel pumps have a combination of P/Ns 568-1-
28300-001 and 568-1-28300-101.
(v) Installed fuel pumps have a combination of P/Ns 568-1-28300-
002 and 568-1-28300-101.
(vi) Installed fuel pumps have a combination of P/Ns 568-1-
28300-001, 568-1-28300-002, and 568-1-28300-101.
(2) For airplanes with fuel pumps that have a part number or
combination of part numbers that are specified in paragraphs
(h)(2)(i) through (h)(2)(iii) of this AD: Do the replacement within
96 months after the effective date of this AD.
(i) All installed fuel pumps have P/N 568-1-28300-100.
(ii) All installed fuel pumps have P/N 568-1-28300-101.
(iii) Installed fuel pumps have a combination of P/Ns 568-1-
28300-100 and 568-1-28300-101.
(i) Definitions
(1) For the purpose of this AD, an ``affected fuel pump'' is
defined as any pump having P/N 568-1-28300-001, 568-1-28300-002,
568-1-28300-100, or 568-1-28300-101.
(2) For the purpose of this AD, a ``serviceable fuel pump'' is a
pump having a part number not listed in paragraph (i)(1) of this AD.
(j) No Reporting Requirement
Although Airbus Service Bulletin A330-28-3127, Revision 02,
dated April 14, 2016; Airbus Service Bulletin A340-28-4138, Revision
01, dated September 24, 2015; and Airbus Service Bulletin A340-28-
5060, Revision 01, dated September 24, 2015; specify submitting
certain information to the manufacturer, and specifies that action
as ``RC'' (Required for Compliance), this AD does not include that
requirement.
(k) Parts Installation Prohibition
After the identification of the fuel pump part numbers required
by paragraph (g) of this AD, comply with the prohibition
[[Page 71596]]
required by paragraph (k)(1) or (k)(2) of this AD, as applicable.
(1) For an airplane that does not have an affected fuel pump
installed: After the identification of the fuel pump part numbers
required by paragraph (g) of this AD, no person may install an
affected fuel pump on the airplane.
(2) For an airplane that has an affected fuel pump installed:
After modification of the airplane as required by paragraph (h) of
this AD, no person may install an affected fuel pump on the
airplane.
(l) Credit for Previous Actions
This paragraph provides credit for actions required by
paragraphs (g) and (h) of this AD, if those actions were performed
before the effective date of this AD using the applicable service
information specified in paragraphs (l)(1), (l)(2), (l)(3), and
(l)(4) of this AD. This service information is not incorporated by
reference in this AD.
(1) Airbus Service Bulletin A330-28-3127, dated July 14, 2015.
(2) Airbus Service Bulletin A330-28-3127, Revision 01, dated
September 24, 2015.
(3) Airbus Service Bulletin A340-28-4138, dated July 14, 2015.
(4) Airbus Service Bulletin A340-28-5060, dated July 14, 2015.
(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: Vladimir
Ulyanov, Aerospace Engineer, International Branch, ANM-116,
Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton,
WA 98057-3356; telephone: 425-227-1138; 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): Except as provide by paragraph
(j) of this AD, 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.
(n) Related Information
(1) Refer to Continuing Airworthiness Information (MCAI) EASA AD
2015-0194, dated September 22, 2015, for related information. You
may examine the MCAI on the Internet at https://www.regulations.gov
by searching for and locating Docket No. FAA-2016-6418.
(o) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless this AD specifies otherwise.
(i) Airbus Service Bulletin A330-28-3127, Revision 02, dated
April 14, 2016.
(ii) Airbus Service Bulletin A340-28-4138, Revision 01, dated
September 24, 2015.
(iii) Airbus Service Bulletin A340-28-5060, Revision 01, dated
September 24, 2015.
(3) For service information identified in this AD, contact
Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96;
fax: +33 5 61 93 45 80; email: airworthiness.A330-A340@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.
(4) 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.
(5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on September 26, 2016.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2016-23647 Filed 10-17-16; 8:45 am]
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