Airworthiness Directives; Airbus Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, and Model C4-605R Variant F Airplanes (Collectively Called A300-600 Series Airplanes); and Model A310 Series Airplanes, 39248-39251 [2011-15991]
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39248
Federal Register / Vol. 76, No. 129 / Wednesday, July 6, 2011 / Rules and Regulations
OTS REGULATIONS THAT WILL BE ENFORCED BY THE FDIC—TITLE 12
Part or section
Chapter V—Office of Thrift Supervision, Department of the Treasury
Part 507 (except 507.3(b)) .................................
Part 508 ..............................................................
Part 509 (except 509.1(e)(3), 509.100(b),
509.103(b)(2), and Subparts C and D).
Part 512 ..............................................................
Part 513 ..............................................................
Part 516 (except 516.45(a)(3), and 516.290(b))
Part 528 ..............................................................
Part 533 (except 533.1(b)(2) and 533.10) ..........
Part 536 ..............................................................
Part 550 (only 550.10(b)) ...................................
Part 551 ..............................................................
Part 555 (only Subpart B, except 555.310(b)) ...
Part 557 (only Subpart C) ..................................
Part 558 ..............................................................
Part 559 (only Subpart B) ...................................
Part 560 (only 560.1, 560.3 and Subpart B) ......
Part 561 (except 561.18(b) and 561.34) ............
Part 562 (except 562.4(b)(2)) .............................
Part 563 12 (except 563.161 as to service corporations,
563.172(b)(1),
563.180(d)(4),
563.555 (definition of ‘‘Troubled condition’’
(2)).
Part 563b ............................................................
Part 563c ............................................................
Part 563d (except 563d.2) ..................................
Part 563e ............................................................
Part 563f (except 563f.2(o)(1)) ...........................
Part 563g ............................................................
Part 564 ..............................................................
Part 565 (except 565.5(h)) .................................
Part 567 ..............................................................
Part 568 ..............................................................
Part 569 ..............................................................
Part 570 ..............................................................
Part 57113 (except 571.30(a)(1)(iii), (iv), and (v))
Part 572 ..............................................................
Part 573 14 ...........................................................
Part 574 (except provisions applicable to
SLHCs).
Part 590 ..............................................................
Part 591 ..............................................................
Restrictions on Post-Employment Activities of Senior Examiners.
Removals, Suspensions and Prohibitions where a Crime is Charged.
Rules of Practice and Procedure in Adjudicatory Proceedings.
Rules for Investigative Proceedings and Formal Examination Proceedings.
Practice Before the Office.
Application Processing Procedure.
Nondiscrimination Requirements.
Disclosure and Reporting of CRA-related Agreements.
Consumer Protection in Sales of Insurance.
Fiduciary Powers of Savings Associations.
Recordkeeping for Securities Transactions.
Electronic Operations.
Deposits.
Possession by Conservators and Receivers for Federal and State Savings Associations.
Subordinate Organizations.
Lending and Investment.
Definitions for Regulations Affecting All Savings Associations.
Regulatory Reporting Standards.
Savings Associations—Operations.
Conversions from Mutual to Stock Form.
Accounting Requirements.
Securities of Savings Associations.
Community Reinvestment.
Management Official Interlocks.
Securities Offerings.
Appraisals.
Prompt Corrective Action.
Capital.
Security Procedures.
Proxies.
Safety and Soundness Guidelines Establishing Standards for Safety and Soundness.
Fair Credit Reporting.
Loans in Areas Having Special Flood Hazards.
Privacy of Consumer Information.
Acquisition of Control of Savings Associations.
Preemption of State Usury Laws.
Preemption of Due-on-Sale Laws.
Dated: June 15, 2011.
John Walsh,
Acting Comptroller of the Currency.
By order of the Board of Directors.
Dated at Washington, DC, this 14th day of
June, 2011.
Federal Deposit Insurance Corporation.
Robert E. Feldman,
Executive Secretary.
DEPARTMENT OF TRANSPORTATION
[FR Doc. 2011–16875 Filed 7–5–11; 8:45 am]
Airworthiness Directives; Airbus Model
A300 B4–600, B4–600R, and F4–600R
Series Airplanes, and Model C4–605R
Variant F Airplanes (Collectively Called
A300–600 Series Airplanes); and Model
A310 Series Airplanes
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BILLING CODE 4810–33–P; 6714–01–P
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2010–1197; Directorate
Identifier 2010–NM–044–AD; Amendment
39–16736; AD 2011–14–01]
RIN 2120–AA64
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for the
SUMMARY:
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17:43 Jul 05, 2011
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products listed above. This AD results
from mandatory continuing
airworthiness information (MCAI)
originated by an aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as:
An operator of an A300–600 aeroplane
reported finding a cracked pylon fuel drain
pipe on engine #1. * * *
* * * The pipe drains the double wall of
the wing-to-pylon junction in the event of
fuel leakage.
After investigation, it was concluded that
the damage of the pylon fuel drain pipe had
been caused by chafing of the pipe against
over-length screws that had been installed in
accordance with the Illustrated Parts
Catalogue (IPC) during a maintenance phase
of the Lower Aft Pylon Fairing (LAPF).
This condition, if not detected and
corrected, could, in combination with fuel
leakage in the pylon, lead to an accumulation
of fuel in the lowest point of the LAPF. As
high temperatures are present within the
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Federal Register / Vol. 76, No. 129 / Wednesday, July 6, 2011 / Rules and Regulations
LAPF, and without ventilation, this could
result in fuel (vapour) ignition and
consequent fire.
*
*
*
*
*
We are issuing this AD to require
actions to correct the unsafe condition
on these products.
DATES: This AD becomes effective
August 10, 2011.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of August 10, 2011.
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:
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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 December 10, 2010 (75 FR
76926). That NPRM proposed to correct
an unsafe condition for the specified
products. The MCAI states:
An operator of an A300–600 aeroplane
reported finding a cracked pylon fuel drain
pipe on engine #1.The pipe, Part Number
(P/N) A71715020, had separated and the end
was found 5.5 inches from the pylon aft
bulkhead. A similar case was also reported
on an A300F4–608ST aeroplane.
The affected pylon fuel drain pipe runs
from the top of the pylon primary structure
to the aft part of the pylon rear secondary
structure and is partly attached under the
pylon lower spar. The pipe drains the double
wall of the wing-to-pylon junction in the
event of fuel leakage.
After investigation, it was concluded that
the damage of the pylon fuel drain pipe had
been caused by chafing of the pipe against
over-length screws that had been installed in
accordance with the Illustrated Parts
Catalogue (IPC) during a maintenance phase
of the Lower Aft Pylon Fairing (LAPF).
This condition, if not detected and
corrected, could, in combination with fuel
leakage in the pylon, lead to an accumulation
of fuel in the lowest point of the LAPF. As
high temperatures are present within the
LAPF, and without ventilation, this could
result in fuel (vapour) ignition and
consequent fire.
To address and correct this unsafe
condition, EASA * * * required an
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17:43 Jul 05, 2011
Jkt 223001
inspection [for missing pipes, or distortions
or holes] of the pylon fuel drain pipe and the
attachment screws and, depending on
findings, the necessary corrective actions. In
case over-length screws are found to be
installed, depending on location and
aeroplane configuration, these must be
replaced.
*
*
*
*
*
Required actions also include visually
inspecting to determine the length and
part number of the drain pipe
attachment screws on the LAPF on the
left- and right-hand pylons. Corrective
actions include replacing or repairing
the pipe, or replacing screws with
incorrect part numbers with new
screws. 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
considered the comments received.
Request To Extend the Compliance
Time
UPS requested that we extend the
compliance time from 30 days to 30
months after the effective date of the
AD. Per the commenter, the NPRM
stated that the over-length screws
installed on the affected aircraft were
installed in accordance with the
illustrated parts catalog (IPC), and that
the correct attachment screws are
clearly identified in the UPS A300–600
IPC, so there is a minimal probability of
installing an over-length screw. The
commenter stated that the compliance
time of 30 days is too restrictive and
believes that extending the threshold to
30 months for those operators whose
IPC does not list an over-length fastener
would provide an equivalent level of
safety and better fit within an operator’s
routine maintenance program and
eliminate any undue burden associated
with a restrictive timetable.
We do not agree to extend the
compliance time. The FAA received
information confirming that over-length
screws could have been introduced in
production due to some erroneous
drawings. Further, before 2007, not all
IPCs were correct. Some of the IPCs for
aircraft fitted with Pratt & Whitney
engines were corrected in 2007. All IPCs
were checked in 2010, and remaining
erroneous IPCs were corrected.
Although UPS may have the correct IPC,
since some over-length screws could
have been installed during production,
a fleet inspection is needed to address
the identified unsafe condition.
However, under the provisions of
paragraph (k) of this AD, we will
consider requests for approval of an
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39249
extension of the compliance time if
sufficient data are submitted to
substantiate that the new compliance
time would provide an acceptable level
of safety. We have not changed the AD
in this regard.
Request To Use Thicker Washer as
Advised in Service Information Letter
UPS requested FAA concurrence that
using an alternative washer, P/N
NSA5149–3, as recommended by Airbus
in Service Information Letter 54–035,
Revision 01, dated July 9, 2010, will not
have an impact on the AD. This washer
would be used in lieu of P/N NSA5149–
4 under the head of the attachment
screws, to prevent cracking of the LAPF.
We partially agree with the
commenter’s request. The alternative
washer is a recommended improvement,
but not a modification addressing an
unsafe condition/airworthiness issue.
As the Service Information Letter
mentions, both washers are fully
interchangeable; the last IPC update
(2010) also reflects this
interchangeability. Therefore, we
confirm that use of either washer is
adequate. In this regard, and to avoid
the need for an alternative method of
compliance (AMOC) on this issue in the
future, we have added the washer
having P/N NSA5149–3 to paragraphs
(g)(1) and (g)(2) of this AD.
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 change described previously.
We determined that this change will not
increase the economic burden on any
operator or increase the scope of the AD.
Differences Between This AD and the
MCAI or Service Information
We have reviewed the MCAI and
related service information and, in
general, agree with their substance. But
we might have found it necessary to use
different words from those in the MCAI
to ensure the AD is clear for U.S.
operators and is enforceable. In making
these changes, we do not intend to differ
substantively from the information
provided in the MCAI and related
service information.
We might also have required different
actions in this AD from those in the
MCAI in order to follow our FAA
policies. Any such differences are
highlighted in a NOTE within the AD.
Costs of Compliance
We estimate that this AD will affect
168 products of U.S. registry. We also
estimate that it will take about 4 work-
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06JYR1
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Federal Register / Vol. 76, No. 129 / Wednesday, July 6, 2011 / Rules and Regulations
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 $57,120, or $340 per product.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. ‘‘Subtitle VII:
Aviation Programs,’’ describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in ‘‘Subtitle VII,
Part A, Subpart III, Section 44701:
General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
We determined that this 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 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); and
3. 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.
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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, the regulatory
evaluation, any comments received, and
other information. The street address for
the Docket Operations office (telephone
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17:43 Jul 05, 2011
Jkt 223001
(800) 647–5527) is in the ADDRESSES
section. Comments will be available in
the AD docket shortly after receipt.
result in fuel (vapour) ignition and
consequent fire.
List of Subjects in 14 CFR Part 39
Compliance
(f) You are responsible for having the
actions required by this AD performed within
the compliance times specified, unless the
actions have already been done.
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 AD:
■
2011–14–01 Airbus: Amendment 39–16736.
Docket No. FAA–2010–1197; Directorate
Identifier 2010–NM–044–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective August 10, 2011.
Affected ADs
(b) None.
Applicability
(c) This AD applies to 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; Model A300 C4–605R
Variant F airplanes; and Model A310–203,
–204, –221, –222, –304, –322, –324, and –325
airplanes; certificated in any category; all
serial numbers.
Subject
(d) Air Transport Association (ATA) of
America Code 54: Nacelles/pylons.
Reason
(e) The mandatory continuing
airworthiness information (MCAI) states:
An operator of an A300–600 aeroplane
reported finding a cracked pylon fuel drain
pipe on engine #1. * * *
* * * The pipe drains the double wall of
the wing-to-pylon junction in the event of
fuel leakage.
After investigation, it was concluded that
the damage of the pylon fuel drain pipe had
been caused by chafing of the pipe against
over-length screws that had been installed in
accordance with the Illustrated Parts
Catalogue (IPC) during a maintenance phase
of the Lower Aft Pylon Fairing (LAPF).
This condition, if not detected and
corrected, could, in combination with fuel
leakage in the pylon, lead to an accumulation
of fuel in the lowest point of the LAPF. As
high temperatures are present within the
LAPF, and without ventilation, this could
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Sfmt 4700
*
*
*
*
*
Inspection and Corrective Actions
(g) Within 30 days after the effective date
of this AD, do a general visual inspection for
missing pipes, or distortions or holes, of the
fuel drain pipes of the LAPF, and if no
missing pipes, distortions, and holes are
found, do a general visual inspection to
determine the length and part number of the
drain pipe attachment screws on the LAPF
on the left-hand and right-hand pylons, in
accordance with the Accomplishment
Instructions of Airbus Mandatory Service
Bulletin A300–54A6039, Revision 01, dated
March 11, 2010 (for Model A300–600 series
airplanes); or A310–54A2040, Revision 02,
dated June 10, 2010 (for Model A310 series
airplanes).
(1) If missing pipes, distortions, or holes of
the fuel drain pipes are detected during any
inspection required by paragraph (g) of this
AD, before further flight, replace the drain
pipe, in accordance with the
Accomplishment Instructions of Airbus
Mandatory Service Bulletin A300–54A6039,
Revision 01, dated March 11, 2010 (for Model
A300–600 series airplanes); or A310–
54A2040, Revision 02, dated June 10, 2010
(for Model A310 series airplanes); or contact
Airbus for repair instructions and do the
repair; except where the applicable service
bulletin specifies using washers having part
number (P/N) NSA5149–4, washers having
P/N NSA5149–3 may alternatively be used.
(2) If screw length is outside the
measurement specified in the
Accomplishment Instructions of Airbus
Mandatory Service Bulletin A300–54A6039,
Revision 01, dated March 11, 2010 (for Model
A300–600 series airplanes); or A310–
54A2040, Revision 02, dated June 10, 2010
(for Model A310 series airplanes); or screws
having incorrect part numbers are found
during any inspection required by paragraph
(g) of this AD, before further flight, replace
the screws with screws having P/N
NAS1102E3–10, NAS1102E3–12, or
NAS560HK3–2, as applicable to location and
airplane (engine) configuration, in
accordance with the Accomplishment
Instructions of Airbus Mandatory Service
Bulletin A300–54A6039, Revision 01, dated
March 11, 2010 (for Model A300–600 series
airplanes); or A310–54A2040, Revision 02,
dated June 10, 2010 (for Model A310 series
airplanes); except where the applicable
service bulletin specifies using washers
having P/N NSA5149–4, washers having P/N
NSA5149–3 may alternatively be used.
(h) As of the effective date of this AD, do
not install screws on the LAPF, other than
screws having P/N NAS1102E3–10,
NAS1102E3–12, or NAS560HK3–2, as
applicable to location and airplane (engine)
configuration, in accordance with the
Accomplishment Instructions of Airbus
Mandatory Service Bulletin A300–54A6039,
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Federal Register / Vol. 76, No. 129 / Wednesday, July 6, 2011 / Rules and Regulations
Revision 01, dated March 11, 2010 (for Model
A300–600 series airplanes); or A310–
54A2040, Revision 02, dated June 10, 2010
(for Model A310 series airplanes).
Credit for Actions Accomplished in
Accordance With Previous Service
Information
(i) Actions accomplished before the
effective date of this AD in accordance with
39251
the service bulletins identified in table 1 of
this AD are considered acceptable for
compliance with the corresponding actions
specified in this AD.
TABLE 1—CREDIT SERVICE BULLETINS
For model—
Airbus Mandatory Service Bulletin—
Revision—
Dated—
A300–600 series airplanes ...................................
A310 series airplanes ...........................................
A310 series airplanes ...........................................
A300–54A6039 ....................................................
A310–54A2040 ....................................................
A310–54A2040 ....................................................
Original ..................
Original ..................
01 ...........................
January 19, 2010.
January 19, 2010.
March 11, 2010.
No Reporting
(j) Although Airbus Mandatory Service
Bulletins A300–54A6039, Revision 01, dated
March 11, 2010; and A310–54A2040,
Revision 02, dated June 10, 2010; specify to
submit certain information to the
manufacturer, this AD does not include that
requirement.
FAA AD Differences
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Note 1: This AD differs from the MCAI
and/or service information as follows:
Although the MCAI or service information
tells you to submit information to the
manufacturer, paragraph (j) of this AD does
not require that information.
Other FAA AD Provisions
(k) 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; telephone (425) 227–2125; fax (425)
227–1149. Before using any approved AMOC
on any airplane to which the AMOC applies,
notify your principal maintenance inspector
(PMI) or principal avionics inspector (PAI),
as appropriate, or lacking a principal
inspector, your local Flight Standards 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.
Service Bulletin A310–54A2040, Revision 02,
dated June 10, 2010; for related information.
DEPARTMENT OF TRANSPORTATION
Material Incorporated by Reference
Federal Aviation Administration
(m) You must use Airbus Mandatory
Service Bulletin A300–54A6039, Revision 01,
excluding Appendix 01 and including
Appendices 02 and 03, dated March 11,
2010; or Airbus Mandatory Service Bulletin
A310–54A2040, Revision 02, excluding
Appendix 01 and including Appendices 02
and 03, dated June 10, 2010; as applicable;
to do the actions required by this AD, unless
the AD specifies otherwise.
(1) The Director of the Federal Register
approved the incorporation by reference of
this service information under 5 U.S.C.
552(a) and 1 CFR part 51.
(2) For 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; e-mail: account.airwortheas@airbus.com; Internet https://
www.airbus.com.
(3) 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.
(4) 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 NARA, call 202–741–6030, or go
to: https://www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html.
Issued in Renton, Washington, on June 16,
2011.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2011–15991 Filed 7–5–11; 8:45 am]
BILLING CODE 4910–13–P
Related Information
(l) Refer to MCAI European Aviation Safety
Agency Airworthiness Directive 2010–0085,
dated May 3, 2010; Airbus Mandatory
Service Bulletin A300–54A6039, Revision 01,
dated March 11, 2010; and Airbus Mandatory
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17:43 Jul 05, 2011
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14 CFR Part 39
[Docket No. FAA–2010–1203; Directorate
Identifier 2010–NM–168–AD; Amendment
39–16738; AD 2011–14–03]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Model DC–9–81 (MD–81),
DC–9–82 (MD–82), DC–9–83 (MD–83),
DC–9–87 (MD–87), and MD–88
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for the
products listed above. This AD requires
repetitive inspections for cracking of the
left and right upper center skin panels
of the horizontal stabilizer, and
corrective action if necessary. This AD
was prompted by a report of a crack
found in the upper center skin panel at
the aft inboard corner of a right
horizontal stabilizer. We are issuing this
AD to detect and correct cracks in the
horizontal stabilizer upper center skin
panel. Uncorrected cracks might
ultimately lead to the loss of overall
structural integrity of the horizontal
stabilizer.
DATES: This AD is effective August 10,
2011.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of August 10, 2011.
ADDRESSES: For service information
identified in this AD, contact Boeing
Commercial Airplanes, Attention: Data
& Services Management, 3855
Lakewood Boulevard, MC D800–0019,
Long Beach, California 90846–0001;
phone: 206–544–5000, extension 2; fax:
206–766–5683; e-mail:
dse.boecom@boeing.com; Internet
https://www.myboeingfleet.com. You
may review copies of the referenced
SUMMARY:
E:\FR\FM\06JYR1.SGM
06JYR1
]]>Agencies
[Federal Register Volume 76, Number 129 (Wednesday, July 6, 2011)]
[Rules and Regulations]
[Pages 39248-39251]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-15991]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2010-1197; Directorate Identifier 2010-NM-044-AD;
Amendment 39-16736; AD 2011-14-01]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A300 B4-600, B4-600R, and
F4-600R Series Airplanes, and Model C4-605R Variant F Airplanes
(Collectively Called A300-600 Series Airplanes); and Model A310 Series
Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
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SUMMARY: We are adopting a new airworthiness directive (AD) for the
products listed above. This AD results from mandatory continuing
airworthiness information (MCAI) originated by an aviation authority of
another country to identify and correct an unsafe condition on an
aviation product. The MCAI describes the unsafe condition as:
An operator of an A300-600 aeroplane reported finding a cracked
pylon fuel drain pipe on engine 1. * * *
* * * The pipe drains the double wall of the wing-to-pylon
junction in the event of fuel leakage.
After investigation, it was concluded that the damage of the
pylon fuel drain pipe had been caused by chafing of the pipe against
over-length screws that had been installed in accordance with the
Illustrated Parts Catalogue (IPC) during a maintenance phase of the
Lower Aft Pylon Fairing (LAPF).
This condition, if not detected and corrected, could, in
combination with fuel leakage in the pylon, lead to an accumulation
of fuel in the lowest point of the LAPF. As high temperatures are
present within the
[[Page 39249]]
LAPF, and without ventilation, this could result in fuel (vapour)
ignition and consequent fire.
* * * * *
We are issuing this AD to require actions to correct the unsafe
condition on these products.
DATES: This AD becomes effective August 10, 2011.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of August 10,
2011.
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 December 10, 2010
(75 FR 76926). That NPRM proposed to correct an unsafe condition for
the specified products. The MCAI states:
An operator of an A300-600 aeroplane reported finding a cracked
pylon fuel drain pipe on engine 1.The pipe, Part Number (P/
N) A71715020, had separated and the end was found 5.5 inches from
the pylon aft bulkhead. A similar case was also reported on an
A300F4-608ST aeroplane.
The affected pylon fuel drain pipe runs from the top of the
pylon primary structure to the aft part of the pylon rear secondary
structure and is partly attached under the pylon lower spar. The
pipe drains the double wall of the wing-to-pylon junction in the
event of fuel leakage.
After investigation, it was concluded that the damage of the
pylon fuel drain pipe had been caused by chafing of the pipe against
over-length screws that had been installed in accordance with the
Illustrated Parts Catalogue (IPC) during a maintenance phase of the
Lower Aft Pylon Fairing (LAPF).
This condition, if not detected and corrected, could, in
combination with fuel leakage in the pylon, lead to an accumulation
of fuel in the lowest point of the LAPF. As high temperatures are
present within the LAPF, and without ventilation, this could result
in fuel (vapour) ignition and consequent fire.
To address and correct this unsafe condition, EASA * * *
required an inspection [for missing pipes, or distortions or holes]
of the pylon fuel drain pipe and the attachment screws and,
depending on findings, the necessary corrective actions. In case
over-length screws are found to be installed, depending on location
and aeroplane configuration, these must be replaced.
* * * * *
Required actions also include visually inspecting to determine the
length and part number of the drain pipe attachment screws on the LAPF
on the left- and right-hand pylons. Corrective actions include
replacing or repairing the pipe, or replacing screws with incorrect
part numbers with new screws. 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 considered the comments received.
Request To Extend the Compliance Time
UPS requested that we extend the compliance time from 30 days to 30
months after the effective date of the AD. Per the commenter, the NPRM
stated that the over-length screws installed on the affected aircraft
were installed in accordance with the illustrated parts catalog (IPC),
and that the correct attachment screws are clearly identified in the
UPS A300-600 IPC, so there is a minimal probability of installing an
over-length screw. The commenter stated that the compliance time of 30
days is too restrictive and believes that extending the threshold to 30
months for those operators whose IPC does not list an over-length
fastener would provide an equivalent level of safety and better fit
within an operator's routine maintenance program and eliminate any
undue burden associated with a restrictive timetable.
We do not agree to extend the compliance time. The FAA received
information confirming that over-length screws could have been
introduced in production due to some erroneous drawings. Further,
before 2007, not all IPCs were correct. Some of the IPCs for aircraft
fitted with Pratt & Whitney engines were corrected in 2007. All IPCs
were checked in 2010, and remaining erroneous IPCs were corrected.
Although UPS may have the correct IPC, since some over-length screws
could have been installed during production, a fleet inspection is
needed to address the identified unsafe condition. However, under the
provisions of paragraph (k) of this AD, we will consider requests for
approval of an extension of the compliance time if sufficient data are
submitted to substantiate that the new compliance time would provide an
acceptable level of safety. We have not changed the AD in this regard.
Request To Use Thicker Washer as Advised in Service Information Letter
UPS requested FAA concurrence that using an alternative washer, P/N
NSA5149-3, as recommended by Airbus in Service Information Letter 54-
035, Revision 01, dated July 9, 2010, will not have an impact on the
AD. This washer would be used in lieu of P/N NSA5149-4 under the head
of the attachment screws, to prevent cracking of the LAPF.
We partially agree with the commenter's request. The alternative
washer is a recommended improvement, but not a modification addressing
an unsafe condition/airworthiness issue. As the Service Information
Letter mentions, both washers are fully interchangeable; the last IPC
update (2010) also reflects this interchangeability. Therefore, we
confirm that use of either washer is adequate. In this regard, and to
avoid the need for an alternative method of compliance (AMOC) on this
issue in the future, we have added the washer having P/N NSA5149-3 to
paragraphs (g)(1) and (g)(2) of this AD.
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 change described previously. We determined that this
change will not increase the economic burden on any operator or
increase the scope of the AD.
Differences Between This AD and the MCAI or Service Information
We have reviewed the MCAI and related service information and, in
general, agree with their substance. But we might have found it
necessary to use different words from those in the MCAI to ensure the
AD is clear for U.S. operators and is enforceable. In making these
changes, we do not intend to differ substantively from the information
provided in the MCAI and related service information.
We might also have required different actions in this AD from those
in the MCAI in order to follow our FAA policies. Any such differences
are highlighted in a NOTE within the AD.
Costs of Compliance
We estimate that this AD will affect 168 products of U.S. registry.
We also estimate that it will take about 4 work-
[[Page 39250]]
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 $57,120, or
$340 per product.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We determined that this 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 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); and
3. 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, 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:
2011-14-01 Airbus: Amendment 39-16736. Docket No. FAA-2010-1197;
Directorate Identifier 2010-NM-044-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective August
10, 2011.
Affected ADs
(b) None.
Applicability
(c) This AD applies to 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; Model A300 C4-605R Variant
F airplanes; and Model A310-203, -204, -221, -222, -304, -322, -324,
and -325 airplanes; certificated in any category; all serial
numbers.
Subject
(d) Air Transport Association (ATA) of America Code 54:
Nacelles/pylons.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
An operator of an A300-600 aeroplane reported finding a cracked
pylon fuel drain pipe on engine 1. * * *
* * * The pipe drains the double wall of the wing-to-pylon
junction in the event of fuel leakage.
After investigation, it was concluded that the damage of the
pylon fuel drain pipe had been caused by chafing of the pipe against
over-length screws that had been installed in accordance with the
Illustrated Parts Catalogue (IPC) during a maintenance phase of the
Lower Aft Pylon Fairing (LAPF).
This condition, if not detected and corrected, could, in
combination with fuel leakage in the pylon, lead to an accumulation
of fuel in the lowest point of the LAPF. As high temperatures are
present within the LAPF, and without ventilation, this could result
in fuel (vapour) ignition and consequent fire.
* * * * *
Compliance
(f) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Inspection and Corrective Actions
(g) Within 30 days after the effective date of this AD, do a
general visual inspection for missing pipes, or distortions or
holes, of the fuel drain pipes of the LAPF, and if no missing pipes,
distortions, and holes are found, do a general visual inspection to
determine the length and part number of the drain pipe attachment
screws on the LAPF on the left-hand and right-hand pylons, in
accordance with the Accomplishment Instructions of Airbus Mandatory
Service Bulletin A300-54A6039, Revision 01, dated March 11, 2010
(for Model A300-600 series airplanes); or A310-54A2040, Revision 02,
dated June 10, 2010 (for Model A310 series airplanes).
(1) If missing pipes, distortions, or holes of the fuel drain
pipes are detected during any inspection required by paragraph (g)
of this AD, before further flight, replace the drain pipe, in
accordance with the Accomplishment Instructions of Airbus Mandatory
Service Bulletin A300-54A6039, Revision 01, dated March 11, 2010
(for Model A300-600 series airplanes); or A310-54A2040, Revision 02,
dated June 10, 2010 (for Model A310 series airplanes); or contact
Airbus for repair instructions and do the repair; except where the
applicable service bulletin specifies using washers having part
number (P/N) NSA5149-4, washers having P/N NSA5149-3 may
alternatively be used.
(2) If screw length is outside the measurement specified in the
Accomplishment Instructions of Airbus Mandatory Service Bulletin
A300-54A6039, Revision 01, dated March 11, 2010 (for Model A300-600
series airplanes); or A310-54A2040, Revision 02, dated June 10, 2010
(for Model A310 series airplanes); or screws having incorrect part
numbers are found during any inspection required by paragraph (g) of
this AD, before further flight, replace the screws with screws
having P/N NAS1102E3-10, NAS1102E3-12, or NAS560HK3-2, as applicable
to location and airplane (engine) configuration, in accordance with
the Accomplishment Instructions of Airbus Mandatory Service Bulletin
A300-54A6039, Revision 01, dated March 11, 2010 (for Model A300-600
series airplanes); or A310-54A2040, Revision 02, dated June 10, 2010
(for Model A310 series airplanes); except where the applicable
service bulletin specifies using washers having P/N NSA5149-4,
washers having P/N NSA5149-3 may alternatively be used.
(h) As of the effective date of this AD, do not install screws
on the LAPF, other than screws having P/N NAS1102E3-10, NAS1102E3-
12, or NAS560HK3-2, as applicable to location and airplane (engine)
configuration, in accordance with the Accomplishment Instructions of
Airbus Mandatory Service Bulletin A300-54A6039,
[[Page 39251]]
Revision 01, dated March 11, 2010 (for Model A300-600 series
airplanes); or A310-54A2040, Revision 02, dated June 10, 2010 (for
Model A310 series airplanes).
Credit for Actions Accomplished in Accordance With Previous Service
Information
(i) Actions accomplished before the effective date of this AD in
accordance with the service bulletins identified in table 1 of this
AD are considered acceptable for compliance with the corresponding
actions specified in this AD.
Table 1--Credit Service Bulletins
----------------------------------------------------------------------------------------------------------------
Airbus Mandatory
For model-- Service Bulletin-- Revision-- Dated--
----------------------------------------------------------------------------------------------------------------
A300-600 series airplanes....... A300-54A6039....... Original.................... January 19, 2010.
A310 series airplanes........... A310-54A2040....... Original.................... January 19, 2010.
A310 series airplanes........... A310-54A2040....... 01.......................... March 11, 2010.
----------------------------------------------------------------------------------------------------------------
No Reporting
(j) Although Airbus Mandatory Service Bulletins A300-54A6039,
Revision 01, dated March 11, 2010; and A310-54A2040, Revision 02,
dated June 10, 2010; specify to submit certain information to the
manufacturer, this AD does not include that requirement.
FAA AD Differences
Note 1: This AD differs from the MCAI and/or service information
as follows: Although the MCAI or service information tells you to
submit information to the manufacturer, paragraph (j) of this AD
does not require that information.
Other FAA AD Provisions
(k) 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; telephone (425) 227-2125; fax (425) 227-1149. Before
using any approved AMOC on any airplane to which the AMOC applies,
notify your principal maintenance inspector (PMI) or principal
avionics inspector (PAI), as appropriate, or lacking a principal
inspector, your local Flight Standards 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.
Related Information
(l) Refer to MCAI European Aviation Safety Agency Airworthiness
Directive 2010-0085, dated May 3, 2010; Airbus Mandatory Service
Bulletin A300-54A6039, Revision 01, dated March 11, 2010; and Airbus
Mandatory Service Bulletin A310-54A2040, Revision 02, dated June 10,
2010; for related information.
Material Incorporated by Reference
(m) You must use Airbus Mandatory Service Bulletin A300-54A6039,
Revision 01, excluding Appendix 01 and including Appendices 02 and
03, dated March 11, 2010; or Airbus Mandatory Service Bulletin A310-
54A2040, Revision 02, excluding Appendix 01 and including Appendices
02 and 03, dated June 10, 2010; as applicable; to do the actions
required by this AD, unless the AD specifies otherwise.
(1) The Director of the Federal Register approved the
incorporation by reference of this service information under 5
U.S.C. 552(a) and 1 CFR part 51.
(2) For 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; e-mail: account.airworth-eas@airbus.com;
Internet https://www.airbus.com.
(3) 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.
(4) 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 NARA, call 202-741-6030, or go to: https://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.
Issued in Renton, Washington, on June 16, 2011.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2011-15991 Filed 7-5-11; 8:45 am]
BILLING CODE 4910-13-P
