Airworthiness Directives; Airbus Model A380-841, -842, and -861 Airplanes, 7931-7934 [2010-3121]
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Federal Register / Vol. 75, No. 35 / Tuesday, February 23, 2010 / Rules and Regulations
ANM–116, Transport Airplane Directorate,
FAA, 1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone (425)
227–2848; 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.
(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: For any
reporting requirement in this AD, under the
provisions of the Paperwork Reduction Act
(44 U.S.C. 3501 et seq.), the Office of
Management and Budget (OMB) has
approved the information collection
requirements and has assigned OMB Control
Number 2120–0056.
Related Information
(h) Refer to MCAI Brazilian Airworthiness
Directive 2008–10–03, effective October 21,
2008; and Embraer Service Bulletin 190–57–
0023, dated June 9, 2008; for related
information.
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Material Incorporated by Reference
(i) You must use Embraer Service Bulletin
190–57–0023, dated June 9, 2008, 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 Empresa Brasileira de
Aeronautica S.A. (EMBRAER), Technical
Publications Section (PC 060), Av. Brigadeiro
˜
Faria Lima, 2170—Putim—12227–901 Sao
Jose dos Campos—SP—BRASIL; telephone:
+55 12 3927–5852 or +55 12 3309–0732; fax:
+55 12 3927–7546; e-mail:
distrib@embraer.com.br; Internet: https://
www.flyembraer.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 or 425–227–1152.
(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 February
5, 2010.
Stephen P. Boyd,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2010–3116 Filed 2–22–10; 8:45 am]
BILLING CODE 4910–13–P
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2010–0038; Directorate
Identifier 2009–NM–110–AD; Amendment
39–16203; AD 2010–04–10]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A380–841, –842, and –861 Airplanes
AGENCY: Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
SUMMARY: The FAA is superseding an
existing 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:
During the flight test campaign of the
A380–861 model (Engine Alliance powered),
some cracks were found on the Movable Flap
Track Fairing number 6 (MFTF#6).
These cracks were located at the pivot
attachment support-ring and at the U-frame
in the attachment area to aft-kinematic. In
addition, delamination has been observed
within the monolithic Carbon Fibre
Reinforced Plastic (CFRP) structure around
the pivot support-ring.
This condition, if not corrected, could lead
to in-flight loss of the MFTF#6, potentially
resulting in injuries to persons on the
ground.
*
*
*
*
*
This AD requires actions that are
intended to address the unsafe
condition described in the MCAI.
DATES: This AD becomes effective
March 10, 2010.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of March 10, 2010.
On May 28, 2009 (74 FR 22422, May
13, 2009), the Director of the Federal
Register approved the incorporation by
reference of a certain other publication
listed in the AD.
We must receive comments on this
AD by April 9, 2010.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: (202) 493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
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30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–40, 1200 New Jersey Avenue, SE.,
Washington, DC, between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
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 this AD, the regulatory
evaluation, any comments received, and
other information. The street address for
the Docket Operations office (telephone
(800) 647–5527) is in the ADDRESSES
section. Comments will be available in
the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT:
Todd Thompson, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 227–1175; fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Discussion
On May 1, 2009, the FAA issued AD
2009–10–07, Amendment 39–15902 (74
FR 22422, May 13, 2009). That AD
required actions intended to address an
unsafe condition on the products listed
above.
Since we issued that AD, the
European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, has issued EASA
Airworthiness Directive 2009–0152,
dated July 14, 2009 (referred to after this
as ‘‘the MCAI’’), to correct an unsafe
condition for the specified products.
The MCAI states:
During the flight test campaign of the
A380–861 model (Engine Alliance powered),
some cracks were found on the Movable Flap
Track Fairing number 6 (MFTF#6).
These cracks were located at the pivot
attachment support-ring and at the U-frame
in the attachment area to aft-kinematic. In
addition, delamination has been observed
within the monolithic Carbon Fibre
Reinforced Plastic (CFRP) structure around
the pivot support-ring.
This condition, if not corrected, could lead
to in-flight loss of the MFTF#6, potentially
resulting in injuries to persons on the
ground.
To prevent the risk of a MFTF#6
detachment, EASA AD 2008–0216 (which
corresponds to FAA AD 2009–10–07)
required an inspection programme in order to
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detect cracks before they become critical and
in case of findings to replace the MFTF#6.
This AD, which supersedes EASA AD
2008–0216:
• Cancels the MFTF#6 General Visual
Inspection requirement,
• Refers to Airbus Service Bulletin A380–
57–8014 Revision 1 * * *
• Introduces an optional terminating
action [installing reinforced part].
AD 2009–10–07 applies to all Airbus
Model A380–841, –842, and –861
airplanes. This AD retains the
requirements of AD 2009–10–07.
Airplanes were removed from the
applicability of AD 2009–10–07 by
excluding airplanes on which Airbus
modification 68729 is done in
production. This AD also revises the
compliance time for the inspections of
replaced parts. The compliance time is
reduced for certain parts and extended
for certain other parts, depending on the
flight cycles since first installation of
the part. The replacement parts must be
inspected within the thresholds
specified in paragraph (f)(1) of this AD.
Relevant Service Information
Since we issued AD 2009–10–07,
Airbus has issued Mandatory Service
Bulletin A380–57–8014, Revision 01,
dated June 5, 2009; and Service Bulletin
A380–57–8017, dated June 5, 2009. The
actions described in this service
information are intended to correct the
unsafe condition identified in the
MCAI.
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FAA’s Determination and Requirements
of This AD
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
bilateral agreement with the State of
Design Authority, we have been notified
of the unsafe condition described in the
MCAI and service information
referenced above. We are issuing this
AD because we evaluated all pertinent
information and determined the unsafe
condition exists and is likely to exist or
develop on other products of the same
type design.
There are no products of this type
currently registered in the United States.
However, this rule is necessary to
ensure that the described unsafe
condition is addressed if any of these
products are placed on the U.S. Register
in the future.
Differences Between the 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
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16:17 Feb 22, 2010
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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 FAA policies.
Any such differences are highlighted in
a NOTE within the AD.
FAA’s Determination of the Effective
Date
Since there are currently no domestic
operators of this product, notice and
opportunity for public comment before
issuing this AD are unnecessary.
Comments Invited
This AD is a final rule that involves
requirements affecting flight safety, and
we did not precede it by notice and
opportunity for public comment. We
invite you to send any written relevant
data, views, or arguments about this AD.
Send your comments to an address
listed under the ADDRESSES section.
Include ‘‘Docket No. FAA–2010–0038;
Directorate Identifier 2009–NM–110–
AD’’ at the beginning of your comments.
We specifically invite comments on the
overall regulatory, economic,
environmental, and energy aspects of
this AD. We will consider all comments
received by the closing date and may
amend this AD because of those
comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this AD.
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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
■
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
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
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§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Amendment 39–15902 (74 FR
22422, May 13, 2009) and adding the
following new AD:
■
2010–04–10 Airbus: Amendment 39–16203.
Docket No. FAA–2010–0038; Directorate
Identifier 2009–NM–110–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective March 10, 2010.
Affected ADs
(b) This AD supersedes AD 2009–10–07,
Amendment 39–15902.
Applicability
(c) This AD applies to Airbus Model A380–
841, –842, and –861 airplanes, certificated in
any category, all serial numbers, except
airplanes on which Airbus modification
68729 has been done in production.
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Subject
(d) Air Transport Association (ATA) of
America Code 57: Wings.
Reason
(e) The mandatory continued airworthiness
information (MCAI) states:
During the flight test campaign of the
A380–861 model (Engine Alliance powered),
some cracks were found on the Movable Flap
Track Fairing number 6 (MFTF#6).
These cracks were located at the pivot
attachment support-ring and at the U-frame
in the attachment area to aft-kinematic. In
addition, delamination has been observed
within the monolithic Carbon Fibre
Reinforced Plastic (CFRP) structure around
the pivot support-ring.
This condition, if not corrected, could lead
to in-flight loss of the MFTF#6, potentially
resulting in injuries to persons on the
ground.
To prevent the risk of a MFTF#6
detachment, EASA AD 2008–0216 required
an inspection programme in order to detect
cracks before they become critical and in case
of findings to replace the MFTF#6.
This AD, which supersedes EASA AD
2008–0216:
• Cancels the MFTF#6 General Visual
Inspection requirement,
• Refers to Airbus Service Bulletin A380–
57–8014 Revision 1, * * *
• Introduces an optional terminating
action.
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Restatement of Requirements of AD 2009–
10–07, With Revised Inspection, Service
Information, and Compliance Time for the
Inspection of Replaced Parts
Actions and Compliance
(f) Unless already done, do the following
actions.
(1) At the applicable time specified in
paragraph (f)(1)(i) or (f)(1)(ii) of this AD for
the left- and right-hand MFTF#6, do a special
detailed (ultrasonic and high-frequency eddy
current) inspection of the filet radii of pivot
supports, monolithic carbon fibre reinforced
plastic structures, and radii of the U-frame,
for cracking and delamination in accordance
with the Accomplishment Instructions of
Airbus Service Bulletin A380–57–8014,
dated November 21, 2008; or Airbus
Mandatory Service Bulletin A380–57–8014,
Revision 01, dated June 5, 2009. After the
effective date of this AD, use only Revision
01.
(i) For Airbus Model A380–841 and –842
airplanes: Before the MFTF#6 has
accumulated 500 total flight cycles since its
first installation on an airplane, or within 30
flight hours after May 28, 2009 (the effective
date of AD 2009–10–07), whichever occurs
later.
(ii) For Model A380–861 airplanes: Before
the MFTF#6 has accumulated 100 total flight
cycles since its first installation on an
airplane, or within 30 flight hours after May
28, 2009, whichever occurs later.
(2) If no cracking and no delamination are
found during any inspection required by
paragraph (f)(1) of this AD, repeat the
inspections required by paragraph (f)(1) of
this AD thereafter at intervals not to exceed
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the applicable time specified in paragraph
(f)(2)(i) or (f)(2)(ii) of this AD.
(i) For Model A380–841 and –842
airplanes: 50 flight cycles.
(ii) For Model A380–861 airplanes: 10
flight cycles.
(3) If any cracking or delamination is found
during any inspection required by paragraph
(f)(1) or (f)(2) of this AD, before further flight,
replace the MFTF#6 with a new or
serviceable part, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A380–57–8014, dated
November 21, 2008; or Airbus Mandatory
Service Bulletin A380–57–8014, Revision 01,
dated June 5, 2009. For parts replaced before
the effective date of this AD, repeat the
inspections specified in paragraph (f)(1) of
this AD at the later of the times specified in
paragraphs (f)(3)(i) and (f)(3)(ii) of this AD.
For parts replaced on or after the effective
date of this AD, repeat the inspections
specified in paragraph (f)(1) of this AD at the
applicable time defined in paragraph (f)(1) of
this AD. After the effective date of this AD,
use only Revision 01 for the replacement.
(i) At the applicable time defined in
paragraph (f)(2) of this AD.
(ii) At the applicable time defined in
paragraph (f)(1) of this AD.
New Requirements of This AD
Actions and Compliance
(g) Unless already done, do the following
actions.
(1) In case of MFTF#6 replacement, submit
a report using Appendix 01 of Airbus Service
Bulletin A380–57–8014, dated November 21,
2008, to Airbus Central Entity, Dept SEES5,
1, Rond Point Maurice Bellonte, 31707
Blagnac, France; e-mail
Frederic.molinier@airbus.com; at the
applicable time specified in paragraph
(g)(1)(i) or (g)(1)(ii) of this AD. The report
must include the serial number of the
removed MFTF#6, the associated airplane
manufacturer serial number, and the number
of flight cycles accumulated by the MFTF#6
at the time of removal.
(i) If the MFTF#6 replacement was done on
or after the effective date of this AD: Submit
the report within 30 days after the MFTF#6
removal.
(ii) If the MFTF#6 replacement was done
before the effective date of this AD: Submit
the report within 30 days after the effective
date of this AD.
(2) Replacement of the MFTF#6 with a
reinforced MFTF#6, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A380–57–8017, dated June
5, 2009, terminates the requirements of this
AD.
FAA AD Differences
Note 1: This AD differs from the MCAI
and/or service information as follows: No
differences.
Other FAA AD Provisions
(h) 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
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7933
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
Send information to ATTN: Todd Thompson,
Aerospace Engineer, International Branch,
ANM–116, Transport Airplane Directorate,
FAA, 1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone (425)
227–1175; fax (425) 227–1149. Before using
any approved AMOC on any airplane to
which the AMOC applies, notify your
appropriate 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.
(3) Reporting Requirements: For any
reporting requirement in this AD, under the
provisions of the Paperwork Reduction Act
(44 U.S.C. 3501 et seq.), the Office of
Management and Budget (OMB) has
approved the information collection
requirements and has assigned OMB Control
Number 2120–0056.
Related Information
(i) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2009–0152, dated
July 14, 2009; Airbus Service Bulletin A380–
57–8014, dated November 21, 2008; Airbus
Mandatory Service Bulletin A380–57–8014,
Revision 01, dated June 5, 2009; and Airbus
Service Bulletin A380–57–8017, dated June
5, 2009; for related information.
Material Incorporated by Reference
(j) You must use Airbus Service Bulletin
A380–57–8014, including Appendix 01,
dated November 21, 2008; Airbus Mandatory
Service Bulletin A380–57–8014, Revision 01,
dated June 5, 2009; and Airbus Service
Bulletin A380–57–8017, dated June 5, 2009;
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
Airbus Mandatory Service Bulletin A380–57–
8014, Revision 01, dated June 5, 2009; and
Airbus Service Bulletin A380–57–8017,
dated June 5, 2009; under 5 U.S.C. 552(a) and
1 CFR part 51.
(2) The Director of the Federal Register
previously approved the incorporation by
reference of Airbus Service Bulletin A380–
57–8014, including Appendix 01, dated
November 21, 2008, on May 28, 2009 (74 FR
22422, May 13, 2009).
(3) For service information identified in
this AD, contact Airbus SAS—EANA
(Airworthiness Office); 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France;
telephone +33 562 110 253; Fax +33 562 110
307; e-mail account.airworthA380@airbus.com; Internet https://
www.airbus.com.
(4) You may review copies of the service
information at the FAA, Transport Airplane
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Directorate, 1601 Lind Avenue, SW., Renton,
Washington. For information on the
availability of this material at the FAA, call
425–227–1221 or 425–227–1152.
(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 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 February
5, 2010.
Stephen P. Boyd,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2010–3121 Filed 2–22–10; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2010–0093; Directorate
Identifier 97–ANE–06–AD; Amendment 39–
16198; AD 2010–04–05]
RIN 2120–AA64
Airworthiness Directives; McCauley
Propeller Systems 1A103/TCM Series
Propellers
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AGENCY: Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
SUMMARY: The FAA is superseding an
existing airworthiness directive (AD) for
McCauley Propeller Systems 1A103/
TCM series propellers. That AD
requires, for certain serial numbers
(S/Ns) of McCauley Propeller Systems
1A103/TCM series propellers, initial
and repetitive visual and dye penetrant
inspections for cracks in the propeller
hub, replacement of propellers with
cracks that do not meet acceptable
limits, and rework of propellers with
cracks that meet acceptable limits. This
AD requires, for all McCauley Propeller
Systems 1A103/TCM series propellers,
the same actions but at reduced
compliance times. This AD also requires
inspections of the bolt holes, reaming
holes if necessary, and inspections of
steel reinforcement plates and gaskets.
This AD results from 16 reports received
of propeller hubs found cracked since
AD 2003–12–05 was issued. We are
issuing this AD to prevent propeller
separation due to hub fatigue cracking,
which can result in loss of control of the
airplane.
DATES: Effective March 10, 2010. The
Director of the Federal Register
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16:17 Feb 22, 2010
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approved the incorporation by reference
of certain publications listed in the
regulations as of March 10, 2010.
We must receive any comments on
this AD by April 26, 2010.
ADDRESSES: Use one of the following
addresses to comment on this AD.
• Federal eRulemaking Portal: Go to
https://www.regulations.gov and follow
the instructions for sending your
comments electronically.
• Mail: Docket Management Facility,
U.S. Department of Transportation, 1200
New Jersey Avenue, SE., West Building
Ground Floor, Room W12–140,
Washington, DC 20590–0001.
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
• Fax: (202) 493–2251.
FOR FURTHER INFORMATION CONTACT:
Thomas Teplik, Aerospace Engineer,
Wichita Aircraft Certification Office,
FAA, Small Airplane Directorate, 1801
Airport Road, Room 100, Wichita, KS
67209; e-mail: thomas.teplik@faa.gov;
telephone: (316) 946–4196; fax: (316)
946–4107.
SUPPLEMENTARY INFORMATION: The FAA
amends 14 CFR part 39 by superseding
AD 2003–12–05, Amendment 39–13190
(68 FR 35155, June 12, 2003). That AD
requires, for certain S/Ns of McCauley
Propeller Systems 1A103/TCM series
propellers, initial and repetitive visual
and dye penetrant inspections for cracks
in the propeller hub, replacement of
propellers with cracks that do not meet
acceptable limits, and rework of
propellers with cracks that meet
acceptable limits. That AD was the
result of reports of hub cracking on the
camber (forward) side of the propeller
hub near the attachment bolt holes on
certain propellers. That condition, if not
corrected, could result in propeller
separation due to hub fatigue cracking,
which can result in loss of control of the
airplane.
Relevant Service Information
We have reviewed and approved the
technical contents of McCauley
Propeller Systems Alert Service Bulletin
(ASB) No. ASB221E, dated January 28,
2010. That ASB describes, for all
McCauley Propeller Systems 1A103/
TCM series propellers, procedures for
initial and repetitive visual and dye
penetrant inspections for cracks in the
propeller hub, removal from service of
propellers with cracks that do not meet
acceptable limits, and rework of
propellers with cracks that meet
acceptable limits.
Actions Since AD 2003–12–05 Was
Issued
Interim Action
These actions are interim actions and
we may take further rulemaking actions
in the future.
Since AD 2003–12–05 was issued, we
received 16 reports of propeller hubs
found cracked. Two of the cracks were
on propellers outside the propeller
range of serial numbers affected by AD
2003–12–05. These cracks began at a
bolt hole and extended through to the
hub outer surface. These propellers had
fewer than 3,000 operating hours timein-service (TIS). AD 2003–12–05
required inspections starting at 3,000
operating hours TIS. We have not yet
been able to determine the cause of the
propeller hub cracking.
PO 00000
Frm 00006
Fmt 4700
Sfmt 4700
FAA’s Determination and Requirements
of This AD
The unsafe condition described
previously is likely to exist or develop
on other McCauley Propeller Systems
1A103/TCM series propellers of the
same type design. We are issuing this
AD to prevent propeller separation due
to hub fatigue cracking, which can
result in loss of control of the airplane.
This AD requires, for all McCauley
Propeller Systems 1A103/TCM series
propellers, initial and repetitive visual
and dye penetrant inspections for cracks
in the propeller hub, including bolt
holes, reaming holes if necessary,
inspections of steel reinforcement plates
and gaskets, removal from service of
propellers with cracks that do not meet
acceptable limits, and rework of
propellers with cracks that meet
acceptable limits. You must use the
service information described
previously to perform the actions
required by this AD.
FAA’s Determination of the Effective
Date
Since an unsafe condition exists that
requires the immediate adoption of this
AD, we have found that notice and
opportunity for public comment before
issuing this AD are impracticable, and
that good cause exists for making this
amendment effective in less than 30
days.
Comments Invited
This AD is a final rule that involves
requirements affecting flight safety and
was not preceded by notice and an
opportunity for public comment;
however, we invite you to send us any
written relevant data, views, or
arguments regarding this AD. Send your
comments to an address listed under
ADDRESSES. Include ‘‘Docket No. FAA–
2010–0093; Directorate Identifier 97–
E:\FR\FM\23FER1.SGM
23FER1
]]>Agencies
[Federal Register Volume 75, Number 35 (Tuesday, February 23, 2010)]
[Rules and Regulations]
[Pages 7931-7934]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-3121]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2010-0038; Directorate Identifier 2009-NM-110-AD;
Amendment 39-16203; AD 2010-04-10]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A380-841, -842, and -861
Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: The FAA is superseding an existing 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:
During the flight test campaign of the A380-861 model (Engine
Alliance powered), some cracks were found on the Movable Flap Track
Fairing number 6 (MFTF6).
These cracks were located at the pivot attachment support-ring
and at the U-frame in the attachment area to aft-kinematic. In
addition, delamination has been observed within the monolithic
Carbon Fibre Reinforced Plastic (CFRP) structure around the pivot
support-ring.
This condition, if not corrected, could lead to in-flight loss
of the MFTF6, potentially resulting in injuries to persons
on the ground.
* * * * *
This AD requires actions that are intended to address the unsafe
condition described in the MCAI.
DATES: This AD becomes effective March 10, 2010.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of March 10,
2010.
On May 28, 2009 (74 FR 22422, May 13, 2009), the Director of the
Federal Register approved the incorporation by reference of a certain
other publication listed in the AD.
We must receive comments on this AD by April 9, 2010.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: (202) 493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-40, 1200 New
Jersey Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
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 this AD, the regulatory evaluation,
any comments received, and other information. The street address for
the Docket Operations office (telephone (800) 647-5527) is in the
ADDRESSES section. Comments will be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT: Todd Thompson, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
227-1175; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Discussion
On May 1, 2009, the FAA issued AD 2009-10-07, Amendment 39-15902
(74 FR 22422, May 13, 2009). That AD required actions intended to
address an unsafe condition on the products listed above.
Since we issued that AD, the European Aviation Safety Agency
(EASA), which is the Technical Agent for the Member States of the
European Community, has issued EASA Airworthiness Directive 2009-0152,
dated July 14, 2009 (referred to after this as ``the MCAI''), to
correct an unsafe condition for the specified products. The MCAI
states:
During the flight test campaign of the A380-861 model (Engine
Alliance powered), some cracks were found on the Movable Flap Track
Fairing number 6 (MFTF6).
These cracks were located at the pivot attachment support-ring
and at the U-frame in the attachment area to aft-kinematic. In
addition, delamination has been observed within the monolithic
Carbon Fibre Reinforced Plastic (CFRP) structure around the pivot
support-ring.
This condition, if not corrected, could lead to in-flight loss
of the MFTF6, potentially resulting in injuries to persons
on the ground.
To prevent the risk of a MFTF6 detachment, EASA AD
2008-0216 (which corresponds to FAA AD 2009-10-07) required an
inspection programme in order to
[[Page 7932]]
detect cracks before they become critical and in case of findings to
replace the MFTF6.
This AD, which supersedes EASA AD 2008-0216:
Cancels the MFTF6 General Visual Inspection
requirement,
Refers to Airbus Service Bulletin A380-57-8014 Revision
1 * * *
Introduces an optional terminating action [installing
reinforced part].
AD 2009-10-07 applies to all Airbus Model A380-841, -842, and -861
airplanes. This AD retains the requirements of AD 2009-10-07. Airplanes
were removed from the applicability of AD 2009-10-07 by excluding
airplanes on which Airbus modification 68729 is done in production.
This AD also revises the compliance time for the inspections of
replaced parts. The compliance time is reduced for certain parts and
extended for certain other parts, depending on the flight cycles since
first installation of the part. The replacement parts must be inspected
within the thresholds specified in paragraph (f)(1) of this AD.
Relevant Service Information
Since we issued AD 2009-10-07, Airbus has issued Mandatory Service
Bulletin A380-57-8014, Revision 01, dated June 5, 2009; and Service
Bulletin A380-57-8017, dated June 5, 2009. The actions described in
this service information are intended to correct the unsafe condition
identified in the MCAI.
FAA's Determination and Requirements of This AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are issuing this AD because we
evaluated all pertinent information and determined the unsafe condition
exists and is likely to exist or develop on other products of the same
type design.
There are no products of this type currently registered in the
United States. However, this rule is necessary to ensure that the
described unsafe condition is addressed if any of these products are
placed on the U.S. Register in the future.
Differences Between the 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 FAA policies. Any such differences are
highlighted in a NOTE within the AD.
FAA's Determination of the Effective Date
Since there are currently no domestic operators of this product,
notice and opportunity for public comment before issuing this AD are
unnecessary.
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety, and we did not precede it by notice and opportunity for public
comment. We invite you to send any written relevant data, views, or
arguments about this AD. Send your comments to an address listed under
the ADDRESSES section. Include ``Docket No. FAA-2010-0038; Directorate
Identifier 2009-NM-110-AD'' at the beginning of your comments. We
specifically invite comments on the overall regulatory, economic,
environmental, and energy aspects of this AD. We will consider all
comments received by the closing date and may amend this AD because of
those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this 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
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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
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 removing Amendment 39-15902 (74 FR
22422, May 13, 2009) and adding the following new AD:
2010-04-10 Airbus: Amendment 39-16203. Docket No. FAA-2010-0038;
Directorate Identifier 2009-NM-110-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective March
10, 2010.
Affected ADs
(b) This AD supersedes AD 2009-10-07, Amendment 39-15902.
Applicability
(c) This AD applies to Airbus Model A380-841, -842, and -861
airplanes, certificated in any category, all serial numbers, except
airplanes on which Airbus modification 68729 has been done in
production.
[[Page 7933]]
Subject
(d) Air Transport Association (ATA) of America Code 57: Wings.
Reason
(e) The mandatory continued airworthiness information (MCAI)
states:
During the flight test campaign of the A380-861 model (Engine
Alliance powered), some cracks were found on the Movable Flap Track
Fairing number 6 (MFTF6).
These cracks were located at the pivot attachment support-ring
and at the U-frame in the attachment area to aft-kinematic. In
addition, delamination has been observed within the monolithic
Carbon Fibre Reinforced Plastic (CFRP) structure around the pivot
support-ring.
This condition, if not corrected, could lead to in-flight loss
of the MFTF6, potentially resulting in injuries to persons
on the ground.
To prevent the risk of a MFTF6 detachment, EASA AD
2008-0216 required an inspection programme in order to detect cracks
before they become critical and in case of findings to replace the
MFTF6.
This AD, which supersedes EASA AD 2008-0216:
Cancels the MFTF6 General Visual Inspection
requirement,
Refers to Airbus Service Bulletin A380-57-8014 Revision
1, * * *
Introduces an optional terminating action.
Restatement of Requirements of AD 2009-10-07, With Revised Inspection,
Service Information, and Compliance Time for the Inspection of Replaced
Parts
Actions and Compliance
(f) Unless already done, do the following actions.
(1) At the applicable time specified in paragraph (f)(1)(i) or
(f)(1)(ii) of this AD for the left- and right-hand MFTF6,
do a special detailed (ultrasonic and high-frequency eddy current)
inspection of the filet radii of pivot supports, monolithic carbon
fibre reinforced plastic structures, and radii of the U-frame, for
cracking and delamination in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A380-57-8014, dated November
21, 2008; or Airbus Mandatory Service Bulletin A380-57-8014,
Revision 01, dated June 5, 2009. After the effective date of this
AD, use only Revision 01.
(i) For Airbus Model A380-841 and -842 airplanes: Before the
MFTF6 has accumulated 500 total flight cycles since its
first installation on an airplane, or within 30 flight hours after
May 28, 2009 (the effective date of AD 2009-10-07), whichever occurs
later.
(ii) For Model A380-861 airplanes: Before the MFTF6 has
accumulated 100 total flight cycles since its first installation on
an airplane, or within 30 flight hours after May 28, 2009, whichever
occurs later.
(2) If no cracking and no delamination are found during any
inspection required by paragraph (f)(1) of this AD, repeat the
inspections required by paragraph (f)(1) of this AD thereafter at
intervals not to exceed the applicable time specified in paragraph
(f)(2)(i) or (f)(2)(ii) of this AD.
(i) For Model A380-841 and -842 airplanes: 50 flight cycles.
(ii) For Model A380-861 airplanes: 10 flight cycles.
(3) If any cracking or delamination is found during any
inspection required by paragraph (f)(1) or (f)(2) of this AD, before
further flight, replace the MFTF6 with a new or serviceable
part, in accordance with the Accomplishment Instructions of Airbus
Service Bulletin A380-57-8014, dated November 21, 2008; or Airbus
Mandatory Service Bulletin A380-57-8014, Revision 01, dated June 5,
2009. For parts replaced before the effective date of this AD,
repeat the inspections specified in paragraph (f)(1) of this AD at
the later of the times specified in paragraphs (f)(3)(i) and
(f)(3)(ii) of this AD. For parts replaced on or after the effective
date of this AD, repeat the inspections specified in paragraph
(f)(1) of this AD at the applicable time defined in paragraph (f)(1)
of this AD. After the effective date of this AD, use only Revision
01 for the replacement.
(i) At the applicable time defined in paragraph (f)(2) of this
AD.
(ii) At the applicable time defined in paragraph (f)(1) of this
AD.
New Requirements of This AD
Actions and Compliance
(g) Unless already done, do the following actions.
(1) In case of MFTF6 replacement, submit a report using
Appendix 01 of Airbus Service Bulletin A380-57-8014, dated November
21, 2008, to Airbus Central Entity, Dept SEES5, 1, Rond Point
Maurice Bellonte, 31707 Blagnac, France; e-mail
Frederic.molinier@airbus.com; at the applicable time specified in
paragraph (g)(1)(i) or (g)(1)(ii) of this AD. The report must
include the serial number of the removed MFTF6, the
associated airplane manufacturer serial number, and the number of
flight cycles accumulated by the MFTF6 at the time of
removal.
(i) If the MFTF6 replacement was done on or after the
effective date of this AD: Submit the report within 30 days after
the MFTF6 removal.
(ii) If the MFTF6 replacement was done before the
effective date of this AD: Submit the report within 30 days after
the effective date of this AD.
(2) Replacement of the MFTF6 with a reinforced
MFTF6, in accordance with the Accomplishment Instructions
of Airbus Service Bulletin A380-57-8017, dated June 5, 2009,
terminates the requirements of this AD.
FAA AD Differences
Note 1: This AD differs from the MCAI and/or service information
as follows: No differences.
Other FAA AD Provisions
(h) 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. Send information to ATTN: Todd
Thompson, Aerospace Engineer, International Branch, ANM-116,
Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton,
Washington 98057-3356; telephone (425) 227-1175; fax (425) 227-1149.
Before using any approved AMOC on any airplane to which the AMOC
applies, notify your appropriate 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.
(3) Reporting Requirements: For any reporting requirement in
this AD, under the provisions of the Paperwork Reduction Act (44
U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has
approved the information collection requirements and has assigned
OMB Control Number 2120-0056.
Related Information
(i) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2009-0152, dated July 14, 2009;
Airbus Service Bulletin A380-57-8014, dated November 21, 2008;
Airbus Mandatory Service Bulletin A380-57-8014, Revision 01, dated
June 5, 2009; and Airbus Service Bulletin A380-57-8017, dated June
5, 2009; for related information.
Material Incorporated by Reference
(j) You must use Airbus Service Bulletin A380-57-8014, including
Appendix 01, dated November 21, 2008; Airbus Mandatory Service
Bulletin A380-57-8014, Revision 01, dated June 5, 2009; and Airbus
Service Bulletin A380-57-8017, dated June 5, 2009; 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 Airbus Mandatory Service Bulletin
A380-57-8014, Revision 01, dated June 5, 2009; and Airbus Service
Bulletin A380-57-8017, dated June 5, 2009; under 5 U.S.C. 552(a) and
1 CFR part 51.
(2) The Director of the Federal Register previously approved the
incorporation by reference of Airbus Service Bulletin A380-57-8014,
including Appendix 01, dated November 21, 2008, on May 28, 2009 (74
FR 22422, May 13, 2009).
(3) For service information identified in this AD, contact
Airbus SAS--EANA (Airworthiness Office); 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; telephone +33 562 110 253;
Fax +33 562 110 307; e-mail account.airworth-A380@airbus.com;
Internet https://www.airbus.com.
(4) You may review copies of the service information at the FAA,
Transport Airplane
[[Page 7934]]
Directorate, 1601 Lind Avenue, SW., Renton, Washington. For
information on the availability of this material at the FAA, call
425-227-1221 or 425-227-1152.
(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 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 February 5, 2010.
Stephen P. Boyd,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2010-3121 Filed 2-22-10; 8:45 am]
BILLING CODE 4910-13-P
