Airworthiness Directives; Airbus Model A300 and A300-600 Series Airplanes, 13078-13081 [E8-4480]
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13078
Federal Register / Vol. 73, No. 49 / Wednesday, March 12, 2008 / Rules and Regulations
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,
the Office of Management and Budget (OMB)
has approved the information collection
requirements and has assigned OMB Control
Number 2120–0056.
Effective Date
(a) This airworthiness directive (AD)
becomes effective on April 16, 2008.
Other Affected ADs
(b) None.
Applicability
(c) This AD applies to Model EC130 B4
helicopters, with a tail rotor drive center
section shaft, part number (P/N)
350A340202; and bearing, P/N 593404,
certificated in any category.
Reason
(d) The mandatory continuing
airworthiness information (MCAI) states:
This Airworthiness Directive (AD) is
issued following the discovery of several
cases of loosened rivets in the tube-to-flange
attachment of the tail rotor drive center
section shaft.
In one case, this loosening of rivets was
associated with a crack in the tube which
started from a loosened-rivet hole.
These occurrences can lead to failure of the
tail rotor drive center section shaft.
Actions and Compliance
(e) Within 50 hours time-in-service (TIS) or
3 months, whichever occurs first, unless
already done, do the following actions.
(1) Inspect for cracks or loosened rivets in
the tube-to-flange attachment of the tail rotor
drive center section shaft and inspect the
perpendicularity of bearing No. 1 in
compliance with the Accomplishment
Instructions, paragraph 2.B.2., of Eurocopter
Alert Service Bulletin No. 65A002, dated
November 16, 2005 (ASB).
(2) If a crack or loosened rivet is found,
replace the tail rotor drive center section
shaft before further flight.
(3) If the out-of perpendicularity of the
bearing is more than 0.1 mm, apply the
corrective procedure described in the
Accomplishment Instructions, paragraph
2.B.2., of the ASB.
Related Information
(i) MCAI European Aviation Safety Agency
(EASA) Airworthiness Directive No. F–2005–
190, Revision A, dated November 23, 2005,
contains related information.
Material Incorporated by Reference
(j) You must use the specified portions of
Eurocopter Alert Service Bulletin No.
65A002, dated November 16, 2005, 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 American Eurocopter
Corporation, 2701 Forum Drive, Grand
Prairie, Texas 75053–4005, telephone (972)
641–3460, fax (972) 641–3527.
(3) You may review copies at the FAA,
Office of the Regional Counsel, Southwest
Region, 2601 Meacham Blvd., Room 663, Fort
Worth, Texas or at the National Archives and
Records Administration (NARA). For
information on the availability of this
material at NARA, call (202) 741–6030, or go
to: https://www.archives.gov/federal-register/
cfr/ibr-locations.html.
Issued in Fort Worth, Texas, on February
14, 2008.
Mark R. Schilling,
Acting Manager, Rotorcraft Directorate,
Aircraft Certification Service.
[FR Doc. E8–4464 Filed 3–11–08; 8:45 am]
BILLING CODE 4910–13–P
Differences Between the FAA AD and the
MCAI
(f) None.
DEPARTMENT OF TRANSPORTATION
jlentini on PROD1PC65 with RULES
Subject
(g) Air Transport Association of America
(ATA) Code 65, Tail rotor drive—tail rotor
drive shaft.
Federal Aviation Administration
Other Information
(h) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, Safety Management
Group, Rotorcraft 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: Ed
Cuevas, Aviation Safety Engineer, Fort
Worth, Texas 76193–0111, telephone (817)
222–5355, fax (817) 222–5961.
(2) Airworthy Product: Use only FAAapproved corrective actions. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent) if the State of
Design has an appropriate bilateral agreement
with the United States. You are required to
[Docket No. FAA–2007–28665; Directorate
Identifier 2007–NM–081–AD; Amendment
39–15416; AD 2008–06–04]
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14 CFR Part 39
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A300 and A300–600 Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: We are adopting a new
airworthiness directive (AD) for the
products listed above. This AD results
from mandatory continuing
airworthiness information (MCAI)
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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:
Three cases of outer deflector panel found
detached or broken during ground inspection
have been reported to Airbus. * * * [A]n
operator has also reported a missing portion
of hinge on one panel. * * * Mishandling or
failure of the small portion of hinge located
inboard of the affected deflector panel is
suspected to be the main cause of the
deflector damage. This can cause
misalignment of the deflector panel followed
by hinge pin migration and possible further
damages to the deflector on flap retraction. If
not corrected, such situation could lead to
the loss of deflector panel and injured people
on the ground.
We are issuing this AD to require
actions to correct the unsafe condition
on these products.
DATES: This AD becomes effective April
16, 2008.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of April 16, 2008.
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: Tom
Stafford, Aerospace Engineer,
International Branch, ANM–116, FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington
98057–3356; telephone (425) 227–1622;
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 July 10, 2007 (72 FR 37477).
That NPRM proposed to correct an
unsafe condition for the specified
products. The MCAI states:
Three cases of outer deflector panel found
detached or broken during ground inspection
have been reported by operators to Airbus.
The affected deflector panel is the most
outboard of the two outer deflectors. In
addition, an operator has also reported a
missing portion of hinge on one panel. The
missing portion of hinge is held to the
structure through one Camloc fastener.
Mishandling or failure of the small portion
of hinge located inboard of the affected
deflector panel is suspected to be the main
cause of the deflector damage.
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Federal Register / Vol. 73, No. 49 / Wednesday, March 12, 2008 / Rules and Regulations
This can cause misalignment of the
deflector panel followed by hinge pin
migration and possible further damages to
the deflector on flap retraction. If not
corrected, such situation could lead to the
loss of deflector panel and injured people on
the ground.
The aim of this Airworthiness Directive
(AD) is to mandate the one time inspection
to detect and prevent damage to inner and
outer shroud box deflectors.
The corrective action includes repairing
any discrepancy, or removing the
affected deflector door according to the
configuration deviation list (CDL). 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 comment received.
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Request To Refer to Later Revision of
Service Bulletin
Airbus requests that we refer to
Revision 01 of Airbus Service Bulletin
A300–57–6104, dated April 27, 2007. In
the NPRM, we referred to the original
issue of that service bulletin, dated
November 7, 2006, as the appropriate
source of service information for
accomplishing the required actions.
We agree with Airbus’ request to refer
to Revision 01 of Airbus Service
Bulletin A300–57–6104. Revision 01 of
the service bulletin updates the operator
and aircraft effectivity to show the latest
information, and changes the industry
support information. No additional
work is required by this revision of the
service bulletin. Although Revision 01
notes that it adds a manufacturer serial
number (MSN) to the effectivity of the
service bulletin, that MSN was already
specified in the applicability of our
NPRM.
We have changed paragraph (f) of this
AD, and Table 1 of this AD, to refer to
Revision 01 of Airbus Service Bulletin
A300–57–6104. We have also added
paragraph (f)(3) to the AD to give credit
to operators that have done the actions
previously in accordance with Airbus
Service Bulletin A300–57–6104,
including Appendix 01, dated
November 7, 2006.
Explanation of Change to Paragraph
(f)(1)(ii)—Flight Manual References
We have revised paragraph (f)(1)(ii) of
the NPRM to specify that operators must
remove the affected deflector door
according to a method approved by
either the Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA; or the European
Aviation Safety Agency (EASA) (or its
delegated agent). That paragraph also
specifies that one approved method for
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removing the door is described in
Airbus A300 Flight Manual (FM),
Appendix—Configuration Deviation
List, Chapter 6.03.27, dated February 1,
1993; or Airbus A300–600 FM,
Appendix—Configuration Deviation
List, Chapter 6.03.27, dated May 1,
1992; as applicable.
This wording makes it clear that there
may be other approved variations of the
Configuration Deviation List and, if so,
that these other variations would also be
acceptable for compliance.
13079
Authority for This Rulemaking
We have changed paragraph (f)(2) of
the NPRM to specify that reports are
necessary only if any discrepancy is
found as a result of the inspection done
in accordance with paragraph (f). We
find that requiring reports for
inspections where no discrepancy is
found puts an undue burden on the
operator.
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.
Conclusion
Regulatory Findings
We reviewed the available data,
including the comments received, and
determined that air safety and the
public interest require adopting the AD
with the changes described previously.
We determined that these changes will
not increase the economic burden on
any operator or increase the scope of the
AD.
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.
Explanation of Change to Paragraph
(f)(2)—Reporting
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
Based on the service information, we
estimate that this AD will affect about
167 products of U.S. registry. We also
estimate that it will take about 16 workhours per product to comply with the
basic requirements of this AD. The
average labor rate is $80 per work-hour.
Based on these figures, we estimate the
cost of the AD for U.S. operators to be
$213,760, or $1,280 per product.
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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
(800) 647–5527) is in the ADDRESSES
section. Comments will be available in
the AD docket shortly after receipt.
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13080
Federal Register / Vol. 73, No. 49 / Wednesday, March 12, 2008 / Rules and Regulations
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:
I
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
I
2008–06–04 Airbus: Amendment 39–15416.
Docket No. FAA–2007–28665;
Directorate Identifier 2007–NM–081–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective April 16, 2008.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Airbus Model A300
and A300–600 series airplanes, all certified
models, all serial numbers, certificated in any
category; except Airbus Model A300–600
series airplanes from manufacturer’s serial
number 0872 onward, which received
application of Airbus modifications 13245
and 13282 during production.
Subject
(d) Air Transport Association (ATA) of
America Code 57: Wings.
Reason
(e) The mandatory continuing
airworthiness information (MCAI) states:
Three cases of outer deflector panel found
detached or broken during ground inspection
have been reported by operators to Airbus.
The affected deflector panel is the most
outboard of the two outer deflectors. In
addition, an operator has also reported a
missing portion of hinge on one panel. The
missing portion of hinge is held to the
structure through one Camloc fastener.
Mishandling or failure of the small portion
of hinge located inboard of the affected
deflector panel is suspected to be the main
cause of the deflector damage.
This can cause misalignment of the
deflector panel followed by hinge pin
migration and possible further damages to
the deflector on flap retraction. If not
corrected, such situation could lead to the
loss of deflector panel and injured people on
the ground.
The aim of this Airworthiness Directive
(AD) is to mandate the one time inspection
to detect and prevent damage to inner and
outer shroud box deflectors.
The corrective action includes repairing
any discrepancy, or removing the affected
deflector door according to the configuration
deviation list (CDL).
Actions and Compliance
(f) Within 18 months after the effective
date of this AD, unless already done, do a
detailed visual inspection of the inner and
outer shroud box flap deflectors in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A300–
57–0247, including Appendix 01, dated
November 7, 2006 (for Model A300 series
airplanes); or Airbus Service Bulletin A300–
57–6104, Revision 01, including Appendix
01, dated April 27, 2007 (for Model A300–
600 series airplanes); as applicable.
(1) If any discrepancy or damage is found,
before next flight do the action in paragraph
(f)(1)(i) or (f)(1)(ii) of this AD.
(i) Repair the affected flap deflector in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A300–
57–0247, including Appendix 01, dated
November 7, 2006; or Airbus Service Bulletin
A300–57–6104, Revision 01, including
Appendix 01, dated April 27, 2007; as
applicable.
(ii) Remove the affected deflector door
according to a method approved by either the
Manager, International Branch, ANM–116,
Transport Airplane Directorate, FAA; or the
European Aviation Safety Agency (EASA) (or
its delegated agent). One approved method is
described in Airbus A300 Flight Manual
(FM), Appendix—Configuration Deviation
List, Chapter 6.03.27, dated February 1, 1993;
or Airbus A300–600 FM, Appendix—
Configuration Deviation List, Chapter
6.03.27, dated May 1, 1992; as applicable.
The removed door may be reinstalled once it
has been repaired in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A300–57–0247, including
Appendix 01, dated November 7, 2006; or
Airbus Service Bulletin A300–57–6104,
Revision 01, including Appendix 01, dated
April 27, 2007; as applicable.
(2) Report to Airbus any discrepancy found
as a result of the inspection done in
accordance with paragraph (f) of this AD,
using the inspection report included in
Appendix 01 of the applicable service
bulletin specified in paragraph (f) of this AD.
(3) Actions done before the effective date
of this AD in accordance with Airbus Service
Bulletin A300–57–6104, including Appendix
01, dated November 7, 2006, are acceptable
for compliance with the corresponding
requirements of this AD.
FAA AD Differences
Note: This AD differs from the MCAI and/
or service information as follows: No
differences.
Other FAA AD Provisions
(g) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, ANM–116,
Transport Airplane Directorate, International
Branch, 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: Tom Stafford,
Aerospace Engineer, International Branch,
ANM–116, FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone (425)
227–1622; fax (425) 227–1149. Before using
any approved AMOC on any airplane to
which the AMOC applies, notify your
appropriate principal inspector (PI) in the
FAA Flight Standards District Office (FSDO),
or lacking a PI, your local FSDO.
(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,
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 EASA Airworthiness
Directive 2007–0062, dated March 7, 2007,
and the service information identified in
Table 1 of this AD, for related information.
TABLE 1.—AIRBUS SERVICE INFORMATION
Service information
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Airbus
Airbus
Airbus
Airbus
Date
Service Bulletin A300–57–0247, including Appendix 01 ...........................................................................................
Service Bulletin A300–57–6104, Revision 01, including Appendix 01 ......................................................................
A300 Flight Manual, Appendix—Configuration Deviation List, Page 5, Chapter 6.03.27, Revision 01 ....................
A300–600 Flight Manual, Appendix—Configuration Deviation List, Page 5, Chapter 6.03.27, Revision 01 ............
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November 7, 2006.
April 27, 2007.
February 1, 1993.
May 1, 1992.
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Federal Register / Vol. 73, No. 49 / Wednesday, March 12, 2008 / Rules and Regulations
Material Incorporated by Reference
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, 1 Rond Point
Maurice Bellonte, 31707 Blagnac Cedex,
France.
(3) You may review copies at the FAA,
Transport Airplane Directorate, 1601 Lind
(i) You must use the service information
specified in Table 2 of this AD 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
Avenue, SW., Renton, Washington; or at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
(202) 741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
TABLE 2.—MATERIAL INCORPORATED BY REFERENCE
Service information
Revision level
Airbus Service Bulletin A300–57–0247, including Appendix 01 ........................................
Airbus Service Bulletin A300–57–6104, including Appendix 01 ........................................
Original .................................
01 .........................................
Issued in Renton, Washington, on February
28, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E8–4480 Filed 3–11–08; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–28662; Directorate
Identifier 2007–NM–014–AD; Amendment
39–15415; AD 2008–06–03]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 737–600, –700, –700C, –800 and
–900 Series Airplanes; and Model 757–
200, –200PF, –200CB, and –300 Series
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
jlentini on PROD1PC65 with RULES
AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for certain
Boeing airplanes, identified above. This
AD requires inspecting to determine if
certain motor-operated shutoff valve
actuators for the fuel tanks are installed,
and related investigative and corrective
actions if necessary. This AD also
requires revising the Airworthiness
Limitations (AWLs) section of the
Instructions for Continued
Airworthiness to incorporate AWL No.
28–AWL–21, No. 28–AWL–22, and No.
28–AWL–24 (for Model 737–600, –700,
–700C, –800 and –900 series airplanes);
and No. 28–AWL–23, No. 28–AWL–24,
and No. 28–AWL–25 (for Model 757–
200, –200PF, –200CB, and –300 series
airplanes). This AD results from a
design review of the fuel tank systems.
We are issuing this AD to prevent
electrical energy from lightning, hot
shorts, or fault current from entering the
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Jkt 214001
fuel tank through the actuator shaft,
which could result in fuel tank
explosions and consequent loss of the
airplane.
This AD becomes effective April
16, 2008.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of April 16, 2008.
ADDRESSES: For service information
identified in this AD, contact Boeing
Commercial Airplanes, P.O. Box 3707,
Seattle, Washington 98124–2207.
DATES:
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Management Facility between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this AD, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (telephone 800–647–5527)
is the Document Management Facility,
U.S. Department of Transportation,
Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue, SE.,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Judy
Coyle, Aerospace Engineer, Propulsion
Branch, ANM–140S, FAA, Seattle
Aircraft Certification Office, 1601 Lind
Avenue, SW., Renton, Washington
98057–3356; telephone (425) 917–6497;
fax (425) 917–6590.
SUPPLEMENTARY INFORMATION:
Discussion
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
apply to certain Boeing Model 737–600,
–700, –700C, –800 and –900 series
airplanes; and Model 757–200, –200PF,
–200CB, and –300 series airplanes. That
NPRM was published in the Federal
Register on July 10, 2007 (72 FR 37484).
That NPRM proposed to require
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Date
November 7, 2006.
April 27, 2007.
inspecting to determine if certain motoroperated shutoff valve actuators for the
fuel tanks are installed, and related
investigative and corrective actions if
necessary. That NPRM also proposed to
require revising the Airworthiness
Limitations (AWLs) section of the
Instructions for Continued
Airworthiness to incorporate AWL No.
28–AWL–21, No. 28–AWL–22, and No.
28–AWL–24 (for Model 737–600, –700,
–700C, –800 and –900 series airplanes),
and No. 28–AWL–23, No. 28–AWL–24,
and No. 28–AWL–25 (for Model 757–
200, –200PF, –200CB, and –300 series
airplanes).
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comments received.
Request To Revise References to
Maintenance Planning Data (MPD)
Documents
Boeing requests that we revise the
applicable areas in the NPRM that
discuss the revision levels of the Boeing
737 and 757 MPD documents. Boeing
states that the references in the NPRM
should be clarified for the following
reasons:
• Revision May 2006 of the Boeing
737–600/700/700C/700IGW/800/900
MPD did not add AWLs (Airworthiness
Limitations) 28–AWL–21, –22, and –24.
Instead, AWLs 28–AWL–21 and –22
were added at Revision January 2006;
AWL 28–AWL–24 was added at
Revision October 2006.
• Revision October 2006 of the
Boeing 737–600/700/700C/700IGW/800/
900 MPD revised AWL 28–AWL–21.
• Revision October 2006 of the
Boeing 757 MPD added AWL 28–AWL–
25; AWLs 28–AWL–23 and –24 were
added at Revision February 2006 of the
Boeing 757 MPD.
• Revision January 2007 of the Boeing
757 MPD revised AWL 28–AWL–24.
Boeing points out that the
clarifications affect references in both
E:\FR\FM\12MRR1.SGM
12MRR1
]]>Agencies
[Federal Register Volume 73, Number 49 (Wednesday, March 12, 2008)]
[Rules and Regulations]
[Pages 13078-13081]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-4480]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-28665; Directorate Identifier 2007-NM-081-AD;
Amendment 39-15416; AD 2008-06-04]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A300 and A300-600 Series
Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
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:
Three cases of outer deflector panel found detached or broken
during ground inspection have been reported to Airbus. * * * [A]n
operator has also reported a missing portion of hinge on one panel.
* * * Mishandling or failure of the small portion of hinge located
inboard of the affected deflector panel is suspected to be the main
cause of the deflector damage. This can cause misalignment of the
deflector panel followed by hinge pin migration and possible further
damages to the deflector on flap retraction. If not corrected, such
situation could lead to the loss of deflector panel and injured
people on the ground.
We are issuing this AD to require actions to correct the unsafe
condition on these products.
DATES: This AD becomes effective April 16, 2008.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of April 16,
2008.
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: Tom Stafford, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
227-1622; 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 July 10, 2007 (72 FR
37477). That NPRM proposed to correct an unsafe condition for the
specified products. The MCAI states:
Three cases of outer deflector panel found detached or broken
during ground inspection have been reported by operators to Airbus.
The affected deflector panel is the most outboard of the two outer
deflectors. In addition, an operator has also reported a missing
portion of hinge on one panel. The missing portion of hinge is held
to the structure through one Camloc fastener.
Mishandling or failure of the small portion of hinge located
inboard of the affected deflector panel is suspected to be the main
cause of the deflector damage.
[[Page 13079]]
This can cause misalignment of the deflector panel followed by
hinge pin migration and possible further damages to the deflector on
flap retraction. If not corrected, such situation could lead to the
loss of deflector panel and injured people on the ground.
The aim of this Airworthiness Directive (AD) is to mandate the
one time inspection to detect and prevent damage to inner and outer
shroud box deflectors.
The corrective action includes repairing any discrepancy, or removing
the affected deflector door according to the configuration deviation
list (CDL). 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 comment received.
Request To Refer to Later Revision of Service Bulletin
Airbus requests that we refer to Revision 01 of Airbus Service
Bulletin A300-57-6104, dated April 27, 2007. In the NPRM, we referred
to the original issue of that service bulletin, dated November 7, 2006,
as the appropriate source of service information for accomplishing the
required actions.
We agree with Airbus' request to refer to Revision 01 of Airbus
Service Bulletin A300-57-6104. Revision 01 of the service bulletin
updates the operator and aircraft effectivity to show the latest
information, and changes the industry support information. No
additional work is required by this revision of the service bulletin.
Although Revision 01 notes that it adds a manufacturer serial number
(MSN) to the effectivity of the service bulletin, that MSN was already
specified in the applicability of our NPRM.
We have changed paragraph (f) of this AD, and Table 1 of this AD,
to refer to Revision 01 of Airbus Service Bulletin A300-57-6104. We
have also added paragraph (f)(3) to the AD to give credit to operators
that have done the actions previously in accordance with Airbus Service
Bulletin A300-57-6104, including Appendix 01, dated November 7, 2006.
Explanation of Change to Paragraph (f)(1)(ii)--Flight Manual References
We have revised paragraph (f)(1)(ii) of the NPRM to specify that
operators must remove the affected deflector door according to a method
approved by either the Manager, International Branch, ANM-116,
Transport Airplane Directorate, FAA; or the European Aviation Safety
Agency (EASA) (or its delegated agent). That paragraph also specifies
that one approved method for removing the door is described in Airbus
A300 Flight Manual (FM), Appendix--Configuration Deviation List,
Chapter 6.03.27, dated February 1, 1993; or Airbus A300-600 FM,
Appendix--Configuration Deviation List, Chapter 6.03.27, dated May 1,
1992; as applicable.
This wording makes it clear that there may be other approved
variations of the Configuration Deviation List and, if so, that these
other variations would also be acceptable for compliance.
Explanation of Change to Paragraph (f)(2)--Reporting
We have changed paragraph (f)(2) of the NPRM to specify that
reports are necessary only if any discrepancy is found as a result of
the inspection done in accordance with paragraph (f). We find that
requiring reports for inspections where no discrepancy is found puts an
undue burden on the operator.
Conclusion
We reviewed the available data, including the comments received,
and determined that air safety and the public interest require adopting
the AD with the changes described previously. We determined that these
changes 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
Based on the service information, we estimate that this AD will
affect about 167 products of U.S. registry. We also estimate that it
will take about 16 work-hours per product to comply with the basic
requirements of this AD. The average labor rate is $80 per work-hour.
Based on these figures, we estimate the cost of the AD for U.S.
operators to be $213,760, or $1,280 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.
[[Page 13080]]
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 adding the following new AD:
2008-06-04 Airbus: Amendment 39-15416. Docket No. FAA-2007-28665;
Directorate Identifier 2007-NM-081-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective April
16, 2008.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Airbus Model A300 and A300-600 series
airplanes, all certified models, all serial numbers, certificated in
any category; except Airbus Model A300-600 series airplanes from
manufacturer's serial number 0872 onward, which received application
of Airbus modifications 13245 and 13282 during production.
Subject
(d) Air Transport Association (ATA) of America Code 57: Wings.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
Three cases of outer deflector panel found detached or broken
during ground inspection have been reported by operators to Airbus.
The affected deflector panel is the most outboard of the two outer
deflectors. In addition, an operator has also reported a missing
portion of hinge on one panel. The missing portion of hinge is held
to the structure through one Camloc fastener.
Mishandling or failure of the small portion of hinge located
inboard of the affected deflector panel is suspected to be the main
cause of the deflector damage.
This can cause misalignment of the deflector panel followed by
hinge pin migration and possible further damages to the deflector on
flap retraction. If not corrected, such situation could lead to the
loss of deflector panel and injured people on the ground.
The aim of this Airworthiness Directive (AD) is to mandate the
one time inspection to detect and prevent damage to inner and outer
shroud box deflectors.
The corrective action includes repairing any discrepancy, or
removing the affected deflector door according to the configuration
deviation list (CDL).
Actions and Compliance
(f) Within 18 months after the effective date of this AD, unless
already done, do a detailed visual inspection of the inner and outer
shroud box flap deflectors in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A300-57-0247, including
Appendix 01, dated November 7, 2006 (for Model A300 series
airplanes); or Airbus Service Bulletin A300-57-6104, Revision 01,
including Appendix 01, dated April 27, 2007 (for Model A300-600
series airplanes); as applicable.
(1) If any discrepancy or damage is found, before next flight do
the action in paragraph (f)(1)(i) or (f)(1)(ii) of this AD.
(i) Repair the affected flap deflector in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A300-57-0247,
including Appendix 01, dated November 7, 2006; or Airbus Service
Bulletin A300-57-6104, Revision 01, including Appendix 01, dated
April 27, 2007; as applicable.
(ii) Remove the affected deflector door according to a method
approved by either the Manager, International Branch, ANM-116,
Transport Airplane Directorate, FAA; or the European Aviation Safety
Agency (EASA) (or its delegated agent). One approved method is
described in Airbus A300 Flight Manual (FM), Appendix--Configuration
Deviation List, Chapter 6.03.27, dated February 1, 1993; or Airbus
A300-600 FM, Appendix--Configuration Deviation List, Chapter
6.03.27, dated May 1, 1992; as applicable. The removed door may be
reinstalled once it has been repaired in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A300-57-0247,
including Appendix 01, dated November 7, 2006; or Airbus Service
Bulletin A300-57-6104, Revision 01, including Appendix 01, dated
April 27, 2007; as applicable.
(2) Report to Airbus any discrepancy found as a result of the
inspection done in accordance with paragraph (f) of this AD, using
the inspection report included in Appendix 01 of the applicable
service bulletin specified in paragraph (f) of this AD.
(3) Actions done before the effective date of this AD in
accordance with Airbus Service Bulletin A300-57-6104, including
Appendix 01, dated November 7, 2006, are acceptable for compliance
with the corresponding requirements of this AD.
FAA AD Differences
Note: This AD differs from the MCAI and/or service information
as follows: No differences.
Other FAA AD Provisions
(g) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager, ANM-
116, Transport Airplane Directorate, International Branch, 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: Tom
Stafford, Aerospace Engineer, International Branch, ANM-116, FAA,
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington 98057-3356; telephone (425) 227-1622; fax (425) 227-1149.
Before using any approved AMOC on any airplane to which the AMOC
applies, notify your appropriate principal inspector (PI) in the FAA
Flight Standards District Office (FSDO), or lacking a PI, your local
FSDO.
(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, 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 EASA Airworthiness Directive 2007-0062, dated
March 7, 2007, and the service information identified in Table 1 of
this AD, for related information.
Table 1.--Airbus Service Information
------------------------------------------------------------------------
Service information Date
------------------------------------------------------------------------
Airbus Service Bulletin A300-57- November 7, 2006.
0247, including Appendix 01.
Airbus Service Bulletin A300-57- April 27, 2007.
6104, Revision 01, including
Appendix 01.
Airbus A300 Flight Manual, February 1, 1993.
Appendix--Configuration Deviation
List, Page 5, Chapter 6.03.27,
Revision 01.
Airbus A300-600 Flight Manual, May 1, 1992.
Appendix--Configuration Deviation
List, Page 5, Chapter 6.03.27,
Revision 01.
------------------------------------------------------------------------
[[Page 13081]]
Material Incorporated by Reference
(i) You must use the service information specified in Table 2 of
this AD 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, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France.
(3) You may review copies at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the
National Archives and Records Administration (NARA). For information
on the availability of this material at NARA, call (202) 741-6030,
or go to: https://www.archives.gov/federal-register/cfr/ibr-
locations.html.
Table 2.--Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
Service information Revision level Date
----------------------------------------------------------------------------------------------------------------
Airbus Service Bulletin A300-57-0247, Original................... November 7, 2006.
including Appendix 01.
Airbus Service Bulletin A300-57-6104, 01......................... April 27, 2007.
including Appendix 01.
----------------------------------------------------------------------------------------------------------------
Issued in Renton, Washington, on February 28, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E8-4480 Filed 3-11-08; 8:45 am]
BILLING CODE 4910-13-P
