Airworthiness Directives; Airbus Airplanes, 64701-64704 [2012-25675]
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Federal Register / Vol. 77, No. 205 / Tuesday, October 23, 2012 / Rules and Regulations
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.
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.
64701
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
(h) Additional Information
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
The subject of this AD is addressed in
European Aviation Safety Agency AD No.
2009–0264, dated December 15, 2009.
[Docket No. FAA–2012–0144; Directorate
Identifier 2011–NM–152–AD; Amendment
39–17220; AD 2012–21–04]
RIN 2120–AA64
2012–21–07—AGUSTA S.p.A. (Agusta):
Amendment 39–17223; Docket No.
FAA–2012–0448; Directorate Identifier
2010–SW–016–AD.
(i) Subject
Airworthiness Directives; Airbus
Airplanes
Joint Aircraft Service Component (JASC)
Code: 2460, DC Power/Distribution System.
AGENCY:
§ 39.13
[Amended]
■
(a) Applicability
This AD applies to Agusta Model A109S
helicopters, serial numbers up to and
including 22151, certificated in any category.
(b) Unsafe Condition
This AD defines the unsafe condition as
failure of the 35 ampere (amp) ‘‘BATT BUS,’’
which could result in an electrical failure
and fire, loss of electrical power to
instruments powered by the ‘‘BATT BUS’’
system, and subsequent loss of control of the
helicopter.
(c) Effective Date
This AD becomes effective November 27,
2012.
(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 50 hours time-in-service, modify
the electrical power distribution system by
installing the ‘‘BATT BUS’’ Circuit Breaker
Modification Kit, part number 109–0824–73–
107, as depicted in Figures 1 through 3 and
by following the Compliance Instructions,
paragraphs 4. through 7., of Agusta Bollettino
Tecnico No. 109S–35, dated December 11,
2009 (ASB). Thereafter, operationally test the
electrical system by following paragraphs
19.1 through 19.7 of the ASB.
tkelley on DSK3SPTVN1PROD with RULES
(f) Special Flight Permits
Special flight permits may be issued in
accordance with 14 CFR 21.197 and 21.199
to operate the helicopter to a location where
the requirements of this AD can be
accomplished provided that you do not
simultaneously operate the landing light and
the search light.
(j) 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 the AD specifies otherwise.
(i) Agusta Bollettino Tecnico No. 109S–35,
dated December 11, 2009.
(ii) Reserved.
(3) For Agusta service information
identified in this AD, contact Agusta, S.p.A.,
Via Giovanni Agusta 520, 21017 Cascina
Costa di Samarate (VA), Italy, ATTN:
Giovanni Cecchelli; telephone 39–0331–
711133; fax 39–0331–711180; or at https://
www.agustawestland.com/technicalbullettins.
(4) You may view this service information
at FAA, Office of the Regional Counsel,
Southwest Region, 2601 Meacham Blvd.,
Room 663, Fort Worth, Texas 76137. 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
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 12,
2012.
Kim Smith,
Manager, Rotorcraft Directorate, Aircraft
Certification Service.
[FR Doc. 2012–25896 Filed 10–22–12; 8:45 am]
BILLING CODE 4910–13–P
(g) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Safety Management
Group, FAA, may approve AMOCs for this
AD. Send your proposal to: Mark F. Wiley,
Aviation Safety Engineer, Regulations and
Policy Group, Rotorcraft Directorate, FAA,
2601 Meacham Blvd., Fort Worth, Texas
76137; telephone (817) 222–5110; email
mark.wiley@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
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PO 00000
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
We are adopting a new
airworthiness directive (AD) for all
Airbus Model A300 series airplanes;
Model A310 series airplanes; and 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). This AD was prompted by
reports of cracked fuel pump canister
hoods located in fuel tanks. This AD
requires replacing any cracked hood
halves of fuel pump canisters. We are
issuing this AD to prevent any detached
canister hood fragments/debris from
being ingested into the fuel feed system,
and becoming a potential source of
ignition with consequent fire or
explosion.
DATES: This AD becomes effective
November 27, 2012.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of November 27, 2012.
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov or in person at the
U.S. Department of Transportation,
Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue SE.,
Washington, DC.
FOR FURTHER INFORMATION CONTACT: Dan
Rodina, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton,
Washington 98057–3356; telephone
(425) 227–2125; fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
SUMMARY:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
apply to the specified products. That
NPRM was published in the Federal
Register on February 22, 2012 (77 FR
10409). That NPRM proposed to correct
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an unsafe condition for the specified
products. The MCAI states:
This [European Aviation Safety Agency
(EASA)] AD results from findings of cracked
fuel pump canister hoods located in fuel
tanks.
From the analyses, laboratory testing and
examinations made so far, it is presently
thought that vibration-induced fatigue can be
identified as the root cause for the cracks
found on in-service aeroplanes. However,
current data does not yet permit to exclude
some other potential contributing factors.
This condition, if not detected and
corrected, could lead to detached canister
hood fragments/debris to be ingested into the
fuel feed system. Also, the metallic debris
inside the fuel tank could result in a
potential source of ignition and consequent
fire or explosion.
For the reasons described above, this
[EASA] AD requires repetitive [detailed]
inspections of all fuel pump canister hood
halves and their replacement if any
[cracking] damage is found. This [EASA] AD
also requires the inspection results to be
reported.
This [EASA] AD is considered to be an
interim action. The reports that are required
by this [EASA] AD will enable the
manufacturer to obtain better insight into the
nature, cause, and extent of the fuel pump
canister hood cracking, and eventually to
develop final action to address the unsafe
condition. Once final action has been
identified, further AD actions could be
considered.
You may obtain further information by
examining the MCAI in the AD docket.
Comments
We gave the public the opportunity to
participate in developing this AD. We
have considered the comments received.
tkelley on DSK3SPTVN1PROD with RULES
Request To Extend Reporting Time
FedEx requested that the time for
submitting reports, proposed in the
NPRM (77 FR 10409, February 22, 2012)
as 30 days, be extended to 90 days,
because it might not have immediate
access to maintenance vendors’ records
of the completed tasks, and system-wide
reporting can sometimes require longer
times.
Although EASA AD 2011–0124, dated
June 30, 2011, specifies a 30-day
compliance time for submitting reports,
we agree with the commenter’s request
to extend the compliance time for
reporting because a delay will not
compromise safety. We have changed
paragraphs (j)(1) and (j)(2) of this final
rule accordingly. This difference has
been coordinated with EASA.
Request for Specific Contact
Information for Reporting
FedEx requested that we provide
specific information for submitting the
reports proposed in the NPRM (77 FR
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16:04 Oct 22, 2012
Jkt 229001
10409, February 22, 2012), including an
email address, to facilitate reporting.
We agree with the commenter’s
request for the reason given, and have
added that information in paragraph (j)
of this final rule.
Request To Delay the Final Rule
Effective Date and Extend the
Compliance Time
UPS requested that the AD be
effective after Airbus completes
certifying the improved design for the
fuel pump half hood, projected to be
completed in late 2012. UPS also
requested an initial compliance time of
36 months (versus the 30 months
proposed in the NPRM (77 FR 10409,
February 22, 2012)) to allow for
purchasing and part lead time. UPS
stated that these changes to the NPRM
would enable a one-time through-thefleet solution without the need for
repetitive inspections.
We do not agree with the commenter’s
request for extending the compliance
time. In developing an appropriate
compliance time for this action, we
considered not only the degree of
urgency associated with addressing the
subject unsafe condition, but the
manufacturer’s and EASA’s
recommendations for an appropriate
compliance time, and the availability of
required parts. We have not changed the
AD in this regard.
Further, we do not agree with the
request for delaying the AD. For
continued operational safety, operators
need to begin the inspections, and not
delay the inspections until the part is
certified. We will consider an
alternative method of compliance
(AMOC) when parts are available.
Operators may request approval of an
AMOC in accordance with paragraph
(k)(1) of this final rule, if sufficient data
are submitted to substantiate that the
method would provide an acceptable
level of safety. We have not changed the
AD in this regard.
Airplane Models Added to This AD
We have determined that Model A300
B2–1A and A300 B4–601 airplanes were
inadvertently omitted from the
Applicability of the NPRM (77 FR
10409, February 22, 2012). We have
added those models to the Applicability
of this AD in paragraphs (c)(1) and (c)(3)
respectively. However, none of the
airplanes added to the Applicability of
this AD are on the U.S. Register.
Therefore, additional notice and
opportunity for public comment before
issuing this AD are unnecessary.
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Explanation of Updated Credit
Language
We have revised the heading and
wording for paragraph (i) of this AD to
provide appropriate credit for previous
accomplishment of certain actions. This
change does not affect the intent of that
paragraph.
Conclusion
We reviewed the available data,
including the comments received, and
determined that air safety and the
public interest require adopting the AD
with the changes described previously,
and minor editorial changes. We have
determined that these changes:
• Are consistent with the intent that
was proposed in the NPRM (77 FR
10409, February 22, 2012) for correcting
the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM (77 FR 10409,
February 22, 2012).
Costs of Compliance
We estimate that this AD will affect
about 221 products of U.S. registry. We
also estimate that it will take up to 12
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 to the U.S. operators to
be $225,420, or $1,020 per product.
In addition, we estimate that any
necessary follow-on actions would take
about 1 work-hour. We have no way of
determining the number of products
that may need these actions.
We have received no definitive data
that would enable us to provide cost
estimates for certain parts required for
the on-condition actions (replacing fuel
pump canister hood halves) specified in
this AD.
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
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that is likely to exist or develop on
products identified in this rulemaking
action.
2012–21–04 Airbus: Amendment 39–17220.
Docket No. FAA–2012–0144; Directorate
Identifier 2011–NM–152–AD.
Regulatory Findings
(a) Effective Date
This airworthiness directive (AD) becomes
effective November 27, 2012.
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.
We prepared a regulatory evaluation
of the estimated costs to comply with
this AD and placed it in the AD docket.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Operations office between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains the NPRM (77 FR 10409,
February 22, 2012), the regulatory
evaluation, any comments received, and
other information. The street address for
the Docket Operations office (telephone
(800) 647–5527) is in the ADDRESSES
section. Comments will be available in
the AD docket shortly after receipt.
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:
tkelley on DSK3SPTVN1PROD with RULES
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 AD:
■
VerDate Mar<15>2010
16:04 Oct 22, 2012
Jkt 229001
(c) Applicability
This AD applies to the airplanes identified
in paragraphs (c)(1), (c)(2), and (c)(3) of this
AD, certificated in any category, all
certificated models, all serial numbers.
(1) Airbus Model A300 B2–1A, B2–1C,
B2K–3C, B2–203, B4–2C, B4–103, and B4–
203 airplanes.
(2) Airbus Model A310–203, –204, –221,
–222, –304, –322, –324, and –325 airplanes.
(3) Airbus Model A300 B4–601, B4–603,
B4–620, and B4–622 airplanes, Model A300
B4–605R and B4–622R airplanes, Model
A300 F4–605R and F4–622R airplanes, and
Model A300 C4–605R Variant F airplanes.
(d) Subject
Air Transport Association (ATA) of
America Code 28: Fuel.
(e) Reason
This AD was prompted by reports of
cracked fuel pump canister hoods located in
fuel tanks. We are issuing this AD to prevent
any detached canister hood fragments/debris
from being ingested into the fuel feed system,
and becoming a potential source of ignition
with consequent fire or explosion.
(f) Compliance
You are responsible for having the actions
required by this AD performed within the
compliance times specified, unless the
actions have already been done.
(g) Initial Inspection and Replacement
Within 30 months after the effective date
of this AD, do a detailed inspection for
cracking of the fuel pump canister hood
halves installed on all fuel pump canisters
having part numbers (P/N) 2052C11,
2052C12, and C93R51–601, in accordance
with the Accomplishment Instructions of the
service bulletin specified in paragraph (g)(1),
(g)(2), or (g)(3) of this AD, as applicable. If
any crack is found on any fuel pump canister
hood half during any inspection, before
further flight, replace the fuel pump canister
hood half, in accordance with the
Accomplishment Instructions of the service
bulletin specified in paragraph (g)(1), (g)(2),
or (g)(3) of this AD, as applicable.
(1) For Model A300 series airplanes:
Airbus Mandatory Service Bulletin A300–28–
0089, Revision 01, including Inspection
Findings—Reporting Sheet, dated April 15,
2011.
(2) For Model A300–600 series airplanes:
Airbus Mandatory Service Bulletin A300–28–
6106, Revision 01, including Inspection
Findings—Reporting Sheet, dated April 15,
2011.
(3) For Model A310 series airplanes:
Airbus Mandatory Service Bulletin A310–28–
2173, Revision 01, including Inspection
Findings—Reporting Sheet, dated April 15,
2011.
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(h) Repetitive Inspections
Within 30 months after accomplishing the
actions specified in paragraph (g) of this AD,
and thereafter at intervals not to exceed 30
months, repeat the detailed inspection
specified in paragraph (g) of this AD.
(i) Credit for Previous Actions
(b) Affected ADs
None.
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64703
Sfmt 4700
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 Airbus Mandatory Service Bulletins
specified in paragraph (i)(1), (i)(2), or
(i)(3) of this AD, which are not
incorporated by reference in this AD.
(1) Airbus Mandatory Service Bulletin
A300–28–0089, dated January 13, 2011.
(2) Airbus Mandatory Service Bulletin
A300–28–6106, dated January 13, 2011.
(3) Airbus Mandatory Service Bulletin
A310–28–2173, dated January 13, 2011.
(j) Reporting to Airbus
Submit reports of the findings (both
positive and negative) of the inspections
required by paragraphs (g) and (h) of
this AD to Airbus at the applicable time
specified in paragraph (j)(1) or (j)(2) of
this AD, using the form ‘‘Inspection
Findings—Reporting Sheet’’ provided in
the service bulletin identified in
paragraph (g)(1), (g)(2), or (g)(3) of this
AD, as applicable. Submit information
to Airbus, SDC32 Technical Data and
Documentation Services, fax (+33) 5 61
93 28 06, email
sb.reporting@airbus.com, or via the
operator’s Resident Customer Support
Office.
(1) If the inspection was done on or
after the effective date of this AD:
Submit the report within 90 days after
the inspection.
(2) If the inspection was done before
the effective date of this AD: Submit the
report within 90 days after the effective
date of this AD.
(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: Dan Rodina,
Aerospace Engineer, International
Branch, ANM–116, Transport Airplane
Directorate, FAA, 1601 Lind Avenue
SW., Renton, Washington 98057–3356;
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telephone (425) 227–2125; fax (425)
227–1149. Information may be emailed
to: 9-ANM-116-AMOCREQUESTS@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) Airworthy Product: For any
requirement in this AD to obtain
corrective actions from a manufacturer
or other source, use these actions if they
are FAA-approved. Corrective actions
are considered FAA-approved if they
are approved by the State of Design
Authority (or their delegated agent). You
are required to assure the product is
airworthy before it is returned to
service.
(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.
tkelley on DSK3SPTVN1PROD with RULES
(l) Related Information
Refer to MCAI European Aviation
Safety Agency Airworthiness Directive
2011–0124, dated June 30, 2011; and the
Airbus mandatory service bulletins
identified in paragraphs (l)(1), (l)(2), and
(l)(3) of this AD; for related information.
(1) Airbus Mandatory Service Bulletin
A300–28–0089, Revision 01, including
Inspection Findings—Reporting Sheet,
dated April 15, 2011.
(2) Airbus Mandatory Service Bulletin
A300–28–6106, Revision 01, including
Inspection Findings—Reporting Sheet,
dated April 15, 2011.
(3) Airbus Mandatory Service Bulletin
A310–28–2173, Revision 01, including
Inspection Findings—Reporting Sheet,
dated April 15, 2011.
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(m) Material Incorporated by Reference
DEPARTMENT OF TRANSPORTATION
(1) The Director of the Federal
Register approved the incorporation by
reference (IBR) of the following service
information under 5 U.S.C. 552(a) and 1
CFR part 51.
(2) You must use the following service
information to do the actions required
by this AD, unless the AD specifies
otherwise.
(i) Airbus Mandatory Service Bulletin
A300–28–0089, Revision 01, including
Inspection Findings—Reporting Sheet,
dated April 15, 2011.
(ii) Airbus Mandatory Service Bulletin
A300–28–6106, Revision 01, including
Inspection Findings—Reporting Sheet,
dated April 15, 2011.
(iii) Airbus Mandatory Service
Bulletin A310–28–2173, Revision 01,
including Inspection Findings—
Reporting Sheet, dated April 15, 2011.
(3) For Airbus service information
identified in this AD, contact Airbus
SAS—EAW (Airworthiness Office), 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.
(4) You may review copies of the
service information at the FAA,
Transport Airplane Directorate, 1601
Lind Avenue SW., Renton, Washington.
For information on the availability of
this material at the FAA, call 425–227–
1221.
(5) You may also review copies of the
service information that is incorporated
by reference at the National Archives
and Records Administration (NARA).
For information on the availability of
this material at an NARA facility, call
202–741–6030, or go to https://
www.archives.gov/federal-register/cfr/
ibr-locations.html.
Federal Aviation Administration
Issued in Renton, Washington, on October
5, 2012.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2012–25675 Filed 10–22–12; 8:45 am]
BILLING CODE 4910–13–P
PO 00000
14 CFR Part 39
[Docket No. FAA–2008–0619; Directorate
Identifier 2007–NM–356–AD; Amendment
39–17219; AD 2012–21–03]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for all The
Boeing Company Model 747–100, 747–
100B, 747–100B SUD, 747–200B, 747–
200C, 747–200F, 747–300, 747SR, and
747SP series airplanes. This AD was
prompted by reports of two in-service
occurrences on Model 737–400
airplanes of total loss of boost pump
pressure of the fuel feed system,
followed by loss of fuel system suction
feed capability on one engine, and inflight shutdown of the engine. This AD
requires repetitive operational tests, and
corrective actions if necessary. We are
issuing this AD to detect and correct
loss of the engine fuel suction feed
capability of the fuel system, which, in
the event of total loss of the fuel boost
pumps, could result in dual engine
flameout, inability to restart the engines,
and consequent forced landing of the
airplane.
SUMMARY:
This AD is effective November
27, 2012.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of November 27, 2012.
ADDRESSES: For service information
identified in this AD, contact Boeing
Commercial Airplanes, Attention: Data
& Services Management, P. O. Box 3707,
MC 2H–65, Seattle, WA 98124–2207;
telephone 206–544–5000, extension 1;
fax 206–766–5680; Internet https://
www.myboeingfleet.com. You may
review copies of the referenced service
information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue
SW., Renton, Washington. For
information on the availability of this
material at the FAA, call 425–227–1221.
DATES:
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Management Facility between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
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]]>Agencies
[Federal Register Volume 77, Number 205 (Tuesday, October 23, 2012)]
[Rules and Regulations]
[Pages 64701-64704]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-25675]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2012-0144; Directorate Identifier 2011-NM-152-AD;
Amendment 39-17220; AD 2012-21-04]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for all
Airbus Model A300 series airplanes; Model A310 series airplanes; and
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). This AD was prompted by reports of cracked fuel pump
canister hoods located in fuel tanks. This AD requires replacing any
cracked hood halves of fuel pump canisters. We are issuing this AD to
prevent any detached canister hood fragments/debris from being ingested
into the fuel feed system, and becoming a potential source of ignition
with consequent fire or explosion.
DATES: This AD becomes effective November 27, 2012.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of November 27,
2012.
ADDRESSES: You may examine the AD docket on the Internet at https://www.regulations.gov or in person at the U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC.
FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, Washington 98057-3356; telephone (425)
227-2125; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would apply to the specified products.
That NPRM was published in the Federal Register on February 22, 2012
(77 FR 10409). That NPRM proposed to correct
[[Page 64702]]
an unsafe condition for the specified products. The MCAI states:
This [European Aviation Safety Agency (EASA)] AD results from
findings of cracked fuel pump canister hoods located in fuel tanks.
From the analyses, laboratory testing and examinations made so
far, it is presently thought that vibration-induced fatigue can be
identified as the root cause for the cracks found on in-service
aeroplanes. However, current data does not yet permit to exclude
some other potential contributing factors.
This condition, if not detected and corrected, could lead to
detached canister hood fragments/debris to be ingested into the fuel
feed system. Also, the metallic debris inside the fuel tank could
result in a potential source of ignition and consequent fire or
explosion.
For the reasons described above, this [EASA] AD requires
repetitive [detailed] inspections of all fuel pump canister hood
halves and their replacement if any [cracking] damage is found. This
[EASA] AD also requires the inspection results to be reported.
This [EASA] AD is considered to be an interim action. The
reports that are required by this [EASA] AD will enable the
manufacturer to obtain better insight into the nature, cause, and
extent of the fuel pump canister hood cracking, and eventually to
develop final action to address the unsafe condition. Once final
action has been identified, further AD actions could be considered.
You may obtain further information by examining the MCAI in the AD
docket.
Comments
We gave the public the opportunity to participate in developing
this AD. We have considered the comments received.
Request To Extend Reporting Time
FedEx requested that the time for submitting reports, proposed in
the NPRM (77 FR 10409, February 22, 2012) as 30 days, be extended to 90
days, because it might not have immediate access to maintenance
vendors' records of the completed tasks, and system-wide reporting can
sometimes require longer times.
Although EASA AD 2011-0124, dated June 30, 2011, specifies a 30-day
compliance time for submitting reports, we agree with the commenter's
request to extend the compliance time for reporting because a delay
will not compromise safety. We have changed paragraphs (j)(1) and
(j)(2) of this final rule accordingly. This difference has been
coordinated with EASA.
Request for Specific Contact Information for Reporting
FedEx requested that we provide specific information for submitting
the reports proposed in the NPRM (77 FR 10409, February 22, 2012),
including an email address, to facilitate reporting.
We agree with the commenter's request for the reason given, and
have added that information in paragraph (j) of this final rule.
Request To Delay the Final Rule Effective Date and Extend the
Compliance Time
UPS requested that the AD be effective after Airbus completes
certifying the improved design for the fuel pump half hood, projected
to be completed in late 2012. UPS also requested an initial compliance
time of 36 months (versus the 30 months proposed in the NPRM (77 FR
10409, February 22, 2012)) to allow for purchasing and part lead time.
UPS stated that these changes to the NPRM would enable a one-time
through-the-fleet solution without the need for repetitive inspections.
We do not agree with the commenter's request for extending the
compliance time. In developing an appropriate compliance time for this
action, we considered not only the degree of urgency associated with
addressing the subject unsafe condition, but the manufacturer's and
EASA's recommendations for an appropriate compliance time, and the
availability of required parts. We have not changed the AD in this
regard.
Further, we do not agree with the request for delaying the AD. For
continued operational safety, operators need to begin the inspections,
and not delay the inspections until the part is certified. We will
consider an alternative method of compliance (AMOC) when parts are
available. Operators may request approval of an AMOC in accordance with
paragraph (k)(1) of this final rule, if sufficient data are submitted
to substantiate that the method would provide an acceptable level of
safety. We have not changed the AD in this regard.
Airplane Models Added to This AD
We have determined that Model A300 B2-1A and A300 B4-601 airplanes
were inadvertently omitted from the Applicability of the NPRM (77 FR
10409, February 22, 2012). We have added those models to the
Applicability of this AD in paragraphs (c)(1) and (c)(3) respectively.
However, none of the airplanes added to the Applicability of this AD
are on the U.S. Register. Therefore, additional notice and opportunity
for public comment before issuing this AD are unnecessary.
Explanation of Updated Credit Language
We have revised the heading and wording for paragraph (i) of this
AD to provide appropriate credit for previous accomplishment of certain
actions. This change does not affect the intent of that paragraph.
Conclusion
We reviewed the available data, including the comments received,
and determined that air safety and the public interest require adopting
the AD with the changes described previously, and minor editorial
changes. We have determined that these changes:
Are consistent with the intent that was proposed in the
NPRM (77 FR 10409, February 22, 2012) for correcting the unsafe
condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM (77 FR 10409, February 22, 2012).
Costs of Compliance
We estimate that this AD will affect about 221 products of U.S.
registry. We also estimate that it will take up to 12 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 to the U.S. operators to be $225,420, or $1,020 per
product.
In addition, we estimate that any necessary follow-on actions would
take about 1 work-hour. We have no way of determining the number of
products that may need these actions.
We have received no definitive data that would enable us to provide
cost estimates for certain parts required for the on-condition actions
(replacing fuel pump canister hood halves) specified in this AD.
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
[[Page 64703]]
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.
We prepared a regulatory evaluation of the estimated costs to
comply with this AD and placed it in the AD docket.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov; or in person at the Docket Operations office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains the NPRM (77 FR 10409, February 22,
2012), the regulatory evaluation, any comments received, and other
information. The street address for the Docket Operations office
(telephone (800) 647-5527) is in the ADDRESSES section. Comments will
be available in the AD docket shortly after receipt.
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 AD:
2012-21-04 Airbus: Amendment 39-17220. Docket No. FAA-2012-0144;
Directorate Identifier 2011-NM-152-AD.
(a) Effective Date
This airworthiness directive (AD) becomes effective November 27,
2012.
(b) Affected ADs
None.
(c) Applicability
This AD applies to the airplanes identified in paragraphs
(c)(1), (c)(2), and (c)(3) of this AD, certificated in any category,
all certificated models, all serial numbers.
(1) Airbus Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-
103, and B4-203 airplanes.
(2) Airbus Model A310-203, -204, -221, -222, -304, -322, -324,
and -325 airplanes.
(3) Airbus Model A300 B4-601, B4-603, B4-620, and B4-622
airplanes, Model A300 B4-605R and B4-622R airplanes, Model A300 F4-
605R and F4-622R airplanes, and Model A300 C4-605R Variant F
airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 28: Fuel.
(e) Reason
This AD was prompted by reports of cracked fuel pump canister
hoods located in fuel tanks. We are issuing this AD to prevent any
detached canister hood fragments/debris from being ingested into the
fuel feed system, and becoming a potential source of ignition with
consequent fire or explosion.
(f) Compliance
You are responsible for having the actions required by this AD
performed within the compliance times specified, unless the actions
have already been done.
(g) Initial Inspection and Replacement
Within 30 months after the effective date of this AD, do a
detailed inspection for cracking of the fuel pump canister hood
halves installed on all fuel pump canisters having part numbers (P/
N) 2052C11, 2052C12, and C93R51-601, in accordance with the
Accomplishment Instructions of the service bulletin specified in
paragraph (g)(1), (g)(2), or (g)(3) of this AD, as applicable. If
any crack is found on any fuel pump canister hood half during any
inspection, before further flight, replace the fuel pump canister
hood half, in accordance with the Accomplishment Instructions of the
service bulletin specified in paragraph (g)(1), (g)(2), or (g)(3) of
this AD, as applicable.
(1) For Model A300 series airplanes: Airbus Mandatory Service
Bulletin A300-28-0089, Revision 01, including Inspection Findings--
Reporting Sheet, dated April 15, 2011.
(2) For Model A300-600 series airplanes: Airbus Mandatory
Service Bulletin A300-28-6106, Revision 01, including Inspection
Findings--Reporting Sheet, dated April 15, 2011.
(3) For Model A310 series airplanes: Airbus Mandatory Service
Bulletin A310-28-2173, Revision 01, including Inspection Findings--
Reporting Sheet, dated April 15, 2011.
(h) Repetitive Inspections
Within 30 months after accomplishing the actions specified in
paragraph (g) of this AD, and thereafter at intervals not to exceed
30 months, repeat the detailed inspection specified in paragraph (g)
of this AD.
(i) Credit for Previous Actions
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 Airbus Mandatory Service Bulletins
specified in paragraph (i)(1), (i)(2), or (i)(3) of this AD, which are
not incorporated by reference in this AD.
(1) Airbus Mandatory Service Bulletin A300-28-0089, dated January
13, 2011.
(2) Airbus Mandatory Service Bulletin A300-28-6106, dated January
13, 2011.
(3) Airbus Mandatory Service Bulletin A310-28-2173, dated January
13, 2011.
(j) Reporting to Airbus
Submit reports of the findings (both positive and negative) of the
inspections required by paragraphs (g) and (h) of this AD to Airbus at
the applicable time specified in paragraph (j)(1) or (j)(2) of this AD,
using the form ``Inspection Findings--Reporting Sheet'' provided in the
service bulletin identified in paragraph (g)(1), (g)(2), or (g)(3) of
this AD, as applicable. Submit information to Airbus, SDC32 Technical
Data and Documentation Services, fax (+33) 5 61 93 28 06, email
sb.reporting@airbus.com, or via the operator's Resident Customer
Support Office.
(1) If the inspection was done on or after the effective date of
this AD: Submit the report within 90 days after the inspection.
(2) If the inspection was done before the effective date of this
AD: Submit the report within 90 days after the effective date of this
AD.
(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: Dan Rodina, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, Washington 98057-3356;
[[Page 64704]]
telephone (425) 227-2125; 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) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer or other source, use these
actions if they are FAA-approved. Corrective actions are considered
FAA-approved if they are approved by the State of Design Authority (or
their delegated agent). You are required to assure the product is
airworthy before it is returned to service.
(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.
(l) Related Information
Refer to MCAI European Aviation Safety Agency Airworthiness
Directive 2011-0124, dated June 30, 2011; and the Airbus mandatory
service bulletins identified in paragraphs (l)(1), (l)(2), and (l)(3)
of this AD; for related information.
(1) Airbus Mandatory Service Bulletin A300-28-0089, Revision 01,
including Inspection Findings--Reporting Sheet, dated April 15, 2011.
(2) Airbus Mandatory Service Bulletin A300-28-6106, Revision 01,
including Inspection Findings--Reporting Sheet, dated April 15, 2011.
(3) Airbus Mandatory Service Bulletin A310-28-2173, Revision 01,
including Inspection Findings--Reporting Sheet, dated April 15, 2011.
(m) Material Incorporated by Reference
(1) The Director of the Federal Register approved the incorporation
by reference (IBR) of the following service information under 5 U.S.C.
552(a) and 1 CFR part 51.
(2) You must use the following service information to do the
actions required by this AD, unless the AD specifies otherwise.
(i) Airbus Mandatory Service Bulletin A300-28-0089, Revision 01,
including Inspection Findings--Reporting Sheet, dated April 15, 2011.
(ii) Airbus Mandatory Service Bulletin A300-28-6106, Revision 01,
including Inspection Findings--Reporting Sheet, dated April 15, 2011.
(iii) Airbus Mandatory Service Bulletin A310-28-2173, Revision 01,
including Inspection Findings--Reporting Sheet, dated April 15, 2011.
(3) For Airbus service information identified in this AD, contact
Airbus SAS--EAW (Airworthiness Office), 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.
(4) You may review copies of the service information at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue SW., Renton,
Washington. For information on the availability of this material at the
FAA, call 425-227-1221.
(5) You may also review copies of the service information that is
incorporated by reference at the National Archives and Records
Administration (NARA). For information on the availability of this
material at an NARA facility, call 202-741-6030, or go to https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on October 5, 2012.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2012-25675 Filed 10-22-12; 8:45 am]
BILLING CODE 4910-13-P
