Airworthiness Directives; Airbus Model A300 Series Airplanes and Airbus Model A300-600 Series Airplanes, 14670-14673 [E8-5149]
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14670
Federal Register / Vol. 73, No. 54 / Wednesday, March 19, 2008 / Rules and Regulations
Within 6 months after the identification
required by paragraph (f)(1) of this AD,
replace the rudder control rods with new
rudder control rods, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A330–27–3157 or A340–27–
4156, both dated August 8, 2007, as
applicable.
(6) As of the effective date of this AD, no
person may install, on any airplane, any
rudder control rod unit having a P/N and
S/N identified in Batch 1, Batch 2a, or Batch
2b of Figure 3 of Airbus Service Bulletin
A330–27–3157 or A340–27–4156, both dated
August 8, 2007.
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/ibrlocations.html.
FAA AD Differences
Issued in Renton, Washington, on March 9,
2008.
Stephen P. Boyd,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E8–5255 Filed 3–18–08; 8:45 am]
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, 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: Vladimir
Ulyanov, Aerospace Engineer, International
Branch, ANM–116, Transport Airplane
Directorate, FAA, 1601 Lind Avenue, SW.,
Renton, Washington 98057–3356; telephone
(425) 227–1138; 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.
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Related Information
(h) Refer to MCAI European Aviation
Safety Agency (EASA) Airworthiness
Directive 2007–0246, dated September 5,
2007; Airbus Service Bulletin A330–27–3157,
dated August 8, 2007; and Airbus Service
Bulletin A340–27–4156, dated August 8,
2007; for related information.
Material Incorporated by Reference
(i) You must use Airbus Service Bulletin
A330–27–3157, excluding Appendix 01,
dated August 8, 2007; or Airbus Service
Bulletin A340–27–4156, excluding Appendix
01, dated August 8, 2007; 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
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BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–28944; Directorate
Identifier 2006–NM–239–AD; Amendment
39–15430; AD 2008–06–18]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A300 Series Airplanes and Airbus
Model 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)
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:
[T]he detection of cracks on multiple
aircraft in lower skin panel No. 2 forward of
access panel 575FB/675FB held on the rear
dummy spar, inboard of rib 9, fuselage side,
aft of the rear spar.
This area of structure has been subjected to
several repairs and modifications in previous
years.
The AIRBUS Service Bulletins (SB) A300–
57–0177 at Revision 3 and A300–57–6029 at
Revision 4 define the various configurations
for the mandatory inspections to be
conducted in order to control or correct the
development of cracks which could affect the
structural integrity of the aircraft.
We are issuing this AD to require
actions to correct the unsafe condition
on these products.
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This AD becomes effective April
23, 2008.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of April 23, 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:
DATES:
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 August 16, 2007 (72 FR
45978). That NPRM proposed to correct
an unsafe condition for the specified
products. The MCAI states:
This Airworthiness Directive (AD) is
published subsequent to the detection of
cracks on multiple aircraft in lower skin
panel No. 2 forward of access panel 575FB/
675FB held on the rear dummy spar, inboard
of rib 9, fuselage side, aft of the rear spar.
This area of structure has been subjected to
several repairs and modifications in previous
years.
The AIRBUS Service Bulletins (SB) A300–
57–0177 at Revision 3 and A300–57–6029 at
Revision 4 define the various configurations
for the mandatory inspections to be
conducted in order to control or correct the
development of cracks which could affect the
structural integrity of the aircraft.
The MCAI requires various repetitive
inspections (detailed visual, high
frequency eddy current, X-ray) of the
wing lower skin panel and associated
internal support structure for cracking
and, if necessary, corrective measures
(modifying the lower panel inboard of
rib 9 aft of the rear spar and repairing
cracks). You may obtain further
information by examining the MCAI in
the AD docket.
Comments
We gave the public the opportunity to
participate in developing this AD. We
considered the comments received.
Request To Revise Applicability of
NPRM
FedEx requests that we revise the
applicability of the NPRM to exclude
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certain airplanes which have already
been modified. FedEx states that
airplanes having post-production
modification 11178 (identified as
Config. 14 in Airbus Service Bulletin
A300–57–6029, Revision 06, dated
March 23, 2007) installed should not be
included in the service bulletin, as the
Limit of Validity (LOV) for the airframe
is close enough to the inspection
thresholds for post-production
modification 11178 to consider the
modification as sufficient without
specific follow-up maintenance
requirements. FedEx therefore requests
that we consider revising the
applicability of the NPRM to exclude
airplanes that have production
modification 11178 installed, and
asserts that if the LOV is extended, an
airworthiness limitations instruction
(ALI) could be added for the post mod
inspection requirements.
We don’t agree. These airplanes must
be inspected before they reach their
current LOV as it could not be
demonstrated that extending the
thresholds up to the revised LOV would
provide an acceptable level of safety.
Operators are provided some relief as
the inspection is estimated to be 2 workhours, which will not have significant
impact on airplane maintenance. We
have not changed the AD in this regard.
Request To Simplify Compliance
Intervals
FedEx states it has 69 A300–600
aircraft affected by the NPRM and, so
far, has had no problems with the wing
skin at the intersection of the rear spar
to the dummy spar inboard of Rib 9.
FedEx states it finds Airbus Service
Bulletin A300–57–6029, Revision 06, to
be overly complex, constituting an
undue burden to implement into its
records system. We infer that FedEx is
requesting that we reduce or streamline
the inspection thresholds and intervals
in the NPRM.
We do not agree with this request.
The fatigue load spectrum differs from
one airplane model to another. To
reduce the number of inspection
programs specified in the service
bulletin, it would be necessary to
require the more conservative
compliance times which would place an
excessive burden on some operators.
However, operators are always
permitted to accomplish the
requirements of an AD before the
required compliance time. Therefore, an
operator with several Model A300–600
airplanes may choose to streamline the
process by inspecting all those models
using the most stringent compliance
time specified in the AD. If an operator
decides that more compliance time is
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15:13 Mar 18, 2008
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needed, the operator may request an
AMOC in accordance with paragraph
(g)(1) of the AD. We have not changed
the AD in this regard.
Request To Add Optional Terminating
Action
FedEx requests that we add an
optional terminating action to the
NPRM. FedEx states that, for airplanes
not found to be cracked that have not
been previously repaired, an equivalent
level of safety could be obtained by
modifying the airplane in accordance
with Airbus Service Bulletin A300–57–
6064 (which describes procedures for
installing internal and external
reinforcing plates on bottom skin panel
No. 2, a stiffener for the support
structure, and a new cleat) prior to
accumulating 10,000 total flight cycles
or within 380 flight cycles after the
effective date of the AD, whichever is
later. FedEx states that some of its
airplanes already have this modification
installed, and asserts, therefore, that
credit should be given for installing this
modification using Revision 0 through 4
of Airbus Service Bulletin A300–57–
6064. FedEx asserts that providing this
terminating action would place the
airplane beyond the LOV and make
further follow-up inspections
unnecessary, thereby enhancing safety
and greatly simplifying compliance
tracking.
We do not agree with this request.
Fatigue and damage tolerance analysis
has shown that, after installing
modification 11178 as described in
Airbus Service Bulletin A300–57–6064,
this area must still be inspected to
control or correct the development of
cracks. Therefore, we have not changed
the AD in this regard. However,
operators may request an AMOC for
adjustments to compliance times in
accordance with paragraph (g)(1) of the
AD.
Clarification of Typographical Error in
Service Information
Airbus Service Bulletin A300–57–
0177, Revision 05, dated March 23,
2007, specifies repetitive inspections for
cracking if Airbus Service Bulletin
A300–57–022 has not been embodied.
Service Bulletin A300–57–022 does not
exist. This AD correctly requires doing
repetitive inspections for cracking if
Airbus Service Bulletin A300–57–0222
(modification 11178H5410) has not been
embodied.
Conclusion
We reviewed the available data,
including the comments received, and
determined that air safety and the
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14671
public interest require adopting the AD
as proposed.
Differences Between This AD and the
MCAI or Service Information
Conclusion
We have reviewed the MCAI and
related service information and, in
general, agree with their substance. But
we might have found it necessary to use
different words from those in the MCAI
to ensure the AD is clear for U.S.
operators and is enforceable. In making
these changes, we do not intend to differ
substantively from the information
provided in the MCAI and related
service information.
We might also have required different
actions in this AD from those in the
MCAI in order to follow our FAA
policies. Any such differences are
highlighted in a NOTE within the AD.
Costs of Compliance
We estimate that this AD will affect
162 products of U.S. registry. We also
estimate that it will take about 2 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 this AD to the U.S. operators to
be $25,920, or $160 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.
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Federal Register / Vol. 73, No. 54 / Wednesday, March 19, 2008 / Rules and Regulations
For the reasons discussed above, I
certify this AD:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
3. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared a regulatory evaluation
of the estimated costs to comply with
this AD and placed it in the AD docket.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Operations office between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains the NPRM, the regulatory
evaluation, any comments received, and
other information. The street address for
the Docket Operations office (telephone
(800) 647–5527) is in the ADDRESSES
section. Comments will be available in
the AD docket shortly after receipt.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
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
2008–06–18 Airbus: Amendment 39–15430.
Docket No. FAA–2007–28944;
Directorate Identifier 2006–NM–239–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective April 23, 2008.
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Affected ADs
(b) None.
Applicability
(c) This AD applies to Airbus Model A300
series airplanes and Model A300–600 series
airplanes; certificated in any category; all
certified models, all serial numbers.
Subject
(d) Wings.
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Jkt 214001
Reason
(e) The mandatory continuing
airworthiness information (MCAI) states:
This Airworthiness Directive (AD) is
published subsequent to the detection of
cracks on multiple aircraft in lower skin
panel No. 2 forward of access panel 575FB/
675FB held on the rear dummy spar, inboard
of rib 9, fuselage side, aft of the rear spar.
This area of structure has been subjected to
several repairs and modifications in previous
years.
The AIRBUS Service Bulletins (SB) A300–
57–0177 at Revision 3 and A300–57–6029 at
Revision 4 define the various configurations
for the mandatory inspections to be
conducted in order to control or correct the
development of cracks which could affect the
structural integrity of the aircraft.
The MCAI requires doing repetitive
inspections (detailed visual, high frequency
eddy current, x-ray) of the wing lower skin
panel and associated internal support
structure for cracking and, if necessary, doing
corrective measures (modifying the lower
panel inboard of rib 9 aft of the rear spar and
repairing cracks).
Actions and Compliance
(f) Unless already done, do the following
actions.
(1) Except as provided by paragraphs
(f)(1)(i), (f)(1)(ii), (f)(1)(iii), and (f)(1)(iv) of
this AD: At the threshold specified in
paragraph 1.E.(2) of Airbus Service Bulletin
A300–57–0177, Revision 05, dated March 23,
2007; or A300–57–6029, Revision 06, dated
March 23, 2007; as applicable; perform the
inspection of the wing lower skin panel and
associated internal support structure aft of
the rear spar and inboard of rib 9 and apply
applicable corrective measures in accordance
with Airbus Service Bulletin A300–57–0177,
Revision 05, dated March 23, 2007; or A300–
57–6029, Revision 06, dated March 23, 2007;
as applicable. All applicable corrective
measures must be done at the applicable
times specified in paragraph 1.E.(2) and the
Accomplishment Instructions of the
applicable service bulletin.
(i) Where the tables in paragraph 1.E.(2),
‘‘Accomplishment Timescale,’’ of the service
bulletins specify a grace period for doing the
actions, this AD requires that the actions be
done within the specified grace period
relative to the effective date of this AD.
(ii) Where the tables in paragraph
1.E.(2)(e), ‘‘Config 04,’’ of Airbus Service
Bulletin A300–57–0177, Revision 05, specify
an inspection interval but not an initial
threshold, this AD requires that the actions
be done within the specified interval after
inspecting in accordance with Table 1A or
1B, as applicable, for Configuration 01
airplanes described in the service bulletin
and thereafter at the inspection interval
specified in the tables in paragraph 1.E.(2)(e),
‘‘Config 04,’’ of Airbus Service Bulletin
A300–57–0177, Revision 05.
(iii) Where the tables in paragraph
1.E.(2)(f), ‘‘Config 05,’’ of Airbus Service
Bulletin A300–57–6029, Revision 06, specify
an inspection interval but not an initial
threshold, this AD requires that the actions
be done within the specified interval after
inspecting in accordance with Table 1A or
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1B, as applicable, for configuration 01 of the
service bulletin and thereafter at the
inspection interval specified in the tables in
paragraph 1.E.(2)(f), ‘‘Config 05,’’ of A300–
57–6029, Revision 06.
(iv) All crack lengths specified in Airbus
Service Bulletin A300–57–0177, Revision 05,
and A300–57–6029, Revision 06, are
considered ‘‘not to exceed’’ lengths.
(2) Repeat the inspection at the intervals
in, and according to the instructions defined
in, Airbus Service Bulletin A300–57–0177,
Revision 05, dated March 23, 2007; or A300–
57–6029, Revision 06, dated March 23, 2007;
as applicable; except where Service Bulletin
A300–57–0177, Revision 05, specifies
repetitive inspections for cracking if Airbus
Service Bulletin A300–57–022 has not been
embodied, this AD requires doing repetitive
inspections for cracking if Airbus Service
Bulletin A300–57–0222 (modification
11178H5410) has not been embodied.
(3) Report to Airbus the first inspection
results, whatever they may be, at the
applicable time specified in paragraph
(f)(3)(i) or (e)(f)(ii) of this AD.
(i) If the inspection was done after the
effective date of this AD, submit the report
within 30 days after the inspection.
(ii) If the inspection was accomplished
prior to the effective date of this AD, submit
the report within 30 days after the effective
date of this AD.
(4) Actions accomplished before the
effective date of this AD in accordance with
Airbus Service Bulletin A300–57–0177,
Revision 03, dated May 29, 2006; Airbus
Service Bulletin A300–57–0177, Revision 04,
dated January 5, 2007; Airbus Service
Bulletin A300–57–6029, Revision 04, dated
May 29, 2006; or Airbus Service Bulletin
A300–57–6029, Revision 05, dated October
23, 2006; are considered acceptable for
compliance with the corresponding action
specified in 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, 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: 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
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Federal Register / Vol. 73, No. 54 / Wednesday, March 19, 2008 / Rules and Regulations
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.
14673
Related Information
(h) Refer to MCAI European Aviation
Safety Agency Airworthiness Directive 2006–
0282, dated September 12, 2006; and the
service information in Table 1 of this AD; for
related information.
TABLE 1.—SERVICE INFORMATION
Airbus Service Bulletin
A300–57–0177
A300–57–0222
A300–57–6029
A300–57–6064
Revision level
..........................................................................................................................................
..........................................................................................................................................
..........................................................................................................................................
..........................................................................................................................................
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
05
01
06
04
Date
March
March
March
March
23, 2007.
13, 2006.
23, 2007.
9, 2006.
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
Airbus Service Bulletin
Revision level
A300–57–0177 ..........................................................................................................................................
A300–57–6029 ..........................................................................................................................................
Issued in Renton, Washington, on March 7,
2008.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E8–5149 Filed 3–18–08; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–0201; Directorate
Identifier 2007–NM–163–AD; Amendment
39–15433; AD 2008–06–21]
RIN 2120–AA64
Airworthiness Directives; McDonnell
Douglas Model DC–10–10 and DC–10–
10F Airplanes, Model DC–10–15
Airplanes, Model DC–10–30 and DC–
10–30F (KC–10A and KDC–10)
Airplanes, Model DC–10–40 and DC–
10–40F Airplanes, Model MD–10–10F
and MD–10–30F Airplanes, and Model
MD–11 and MD–11F Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
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AGENCY:
SUMMARY: We are adopting a new
airworthiness directive (AD) for all
McDonnell Douglas airplane models
identified above. This AD requires
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15:13 Mar 18, 2008
Jkt 214001
revising the FAA-approved maintenance
program, or the Airworthiness
Limitations (AWLs) section of the
Instructions for Continued
Airworthiness, as applicable, to
incorporate new AWLs for fuel tank
systems to satisfy Special Federal
Aviation Regulation No. 88
requirements. For certain airplanes, this
AD also requires the initial
accomplishment of a certain repetitive
AWL inspection to phase in that
inspection, and repair if necessary. This
AD results from a design review of the
fuel tank systems. We are issuing this
AD to prevent the potential for ignition
sources inside fuel tanks caused by
latent failures, alterations, repairs, or
maintenance actions, which, in
combination with flammable fuel
vapors, could result in a fuel tank
explosion and consequent loss of the
airplane.
DATES: This AD is effective April 23,
2008.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of April 23, 2008.
ADDRESSES: For service information
identified in this AD, contact Boeing
Commercial Airplanes, Long Beach
Division, 3855 Lakewood Boulevard,
Long Beach, California 90846, Attention:
Data and Service Management, Dept.
C1–L5A (D800–0024).
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05
06
Date
March 23, 2007.
March 23, 2007.
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:
Philip C. Kush, Aerospace Engineer,
Propulsion Branch, ANM–140L, FAA,
Los Angeles Aircraft Certification
Office, 3960 Paramount Boulevard,
Lakewood, California 90712–4137;
telephone (562) 627–5263; fax (562)
627–5210.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an airworthiness
directive (AD) that would apply to all
McDonnell Douglas Model DC–10–10
and DC–10–10F airplanes, Model DC–
10–15 airplanes, Model DC–10–30 and
DC–10–30F (KC–10A and KDC–10)
E:\FR\FM\19MRR1.SGM
19MRR1
]]>Agencies
[Federal Register Volume 73, Number 54 (Wednesday, March 19, 2008)]
[Rules and Regulations]
[Pages 14670-14673]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-5149]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-28944; Directorate Identifier 2006-NM-239-AD;
Amendment 39-15430; AD 2008-06-18]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A300 Series Airplanes and
Airbus Model 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:
[T]he detection of cracks on multiple aircraft in lower skin
panel No. 2 forward of access panel 575FB/675FB held on the rear
dummy spar, inboard of rib 9, fuselage side, aft of the rear spar.
This area of structure has been subjected to several repairs and
modifications in previous years.
The AIRBUS Service Bulletins (SB) A300-57-0177 at Revision 3 and
A300-57-6029 at Revision 4 define the various configurations for the
mandatory inspections to be conducted in order to control or correct
the development of cracks which could affect the structural
integrity of the aircraft.
We are issuing this AD to require actions to correct the unsafe
condition on these products.
DATES: This AD becomes effective April 23, 2008.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of April 23,
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 August 16, 2007 (72
FR 45978). That NPRM proposed to correct an unsafe condition for the
specified products. The MCAI states:
This Airworthiness Directive (AD) is published subsequent to the
detection of cracks on multiple aircraft in lower skin panel No. 2
forward of access panel 575FB/675FB held on the rear dummy spar,
inboard of rib 9, fuselage side, aft of the rear spar.
This area of structure has been subjected to several repairs and
modifications in previous years.
The AIRBUS Service Bulletins (SB) A300-57-0177 at Revision 3 and
A300-57-6029 at Revision 4 define the various configurations for the
mandatory inspections to be conducted in order to control or correct
the development of cracks which could affect the structural
integrity of the aircraft.
The MCAI requires various repetitive inspections (detailed visual,
high frequency eddy current, X-ray) of the wing lower skin panel and
associated internal support structure for cracking and, if necessary,
corrective measures (modifying the lower panel inboard of rib 9 aft of
the rear spar and repairing cracks). You may obtain further information
by examining the MCAI in the AD docket.
Comments
We gave the public the opportunity to participate in developing
this AD. We considered the comments received.
Request To Revise Applicability of NPRM
FedEx requests that we revise the applicability of the NPRM to
exclude
[[Page 14671]]
certain airplanes which have already been modified. FedEx states that
airplanes having post-production modification 11178 (identified as
Config. 14 in Airbus Service Bulletin A300-57-6029, Revision 06, dated
March 23, 2007) installed should not be included in the service
bulletin, as the Limit of Validity (LOV) for the airframe is close
enough to the inspection thresholds for post-production modification
11178 to consider the modification as sufficient without specific
follow-up maintenance requirements. FedEx therefore requests that we
consider revising the applicability of the NPRM to exclude airplanes
that have production modification 11178 installed, and asserts that if
the LOV is extended, an airworthiness limitations instruction (ALI)
could be added for the post mod inspection requirements.
We don't agree. These airplanes must be inspected before they reach
their current LOV as it could not be demonstrated that extending the
thresholds up to the revised LOV would provide an acceptable level of
safety. Operators are provided some relief as the inspection is
estimated to be 2 work-hours, which will not have significant impact on
airplane maintenance. We have not changed the AD in this regard.
Request To Simplify Compliance Intervals
FedEx states it has 69 A300-600 aircraft affected by the NPRM and,
so far, has had no problems with the wing skin at the intersection of
the rear spar to the dummy spar inboard of Rib 9. FedEx states it finds
Airbus Service Bulletin A300-57-6029, Revision 06, to be overly
complex, constituting an undue burden to implement into its records
system. We infer that FedEx is requesting that we reduce or streamline
the inspection thresholds and intervals in the NPRM.
We do not agree with this request. The fatigue load spectrum
differs from one airplane model to another. To reduce the number of
inspection programs specified in the service bulletin, it would be
necessary to require the more conservative compliance times which would
place an excessive burden on some operators. However, operators are
always permitted to accomplish the requirements of an AD before the
required compliance time. Therefore, an operator with several Model
A300-600 airplanes may choose to streamline the process by inspecting
all those models using the most stringent compliance time specified in
the AD. If an operator decides that more compliance time is needed, the
operator may request an AMOC in accordance with paragraph (g)(1) of the
AD. We have not changed the AD in this regard.
Request To Add Optional Terminating Action
FedEx requests that we add an optional terminating action to the
NPRM. FedEx states that, for airplanes not found to be cracked that
have not been previously repaired, an equivalent level of safety could
be obtained by modifying the airplane in accordance with Airbus Service
Bulletin A300-57-6064 (which describes procedures for installing
internal and external reinforcing plates on bottom skin panel No. 2, a
stiffener for the support structure, and a new cleat) prior to
accumulating 10,000 total flight cycles or within 380 flight cycles
after the effective date of the AD, whichever is later. FedEx states
that some of its airplanes already have this modification installed,
and asserts, therefore, that credit should be given for installing this
modification using Revision 0 through 4 of Airbus Service Bulletin
A300-57-6064. FedEx asserts that providing this terminating action
would place the airplane beyond the LOV and make further follow-up
inspections unnecessary, thereby enhancing safety and greatly
simplifying compliance tracking.
We do not agree with this request. Fatigue and damage tolerance
analysis has shown that, after installing modification 11178 as
described in Airbus Service Bulletin A300-57-6064, this area must still
be inspected to control or correct the development of cracks.
Therefore, we have not changed the AD in this regard. However,
operators may request an AMOC for adjustments to compliance times in
accordance with paragraph (g)(1) of the AD.
Clarification of Typographical Error in Service Information
Airbus Service Bulletin A300-57-0177, Revision 05, dated March 23,
2007, specifies repetitive inspections for cracking if Airbus Service
Bulletin A300-57-022 has not been embodied. Service Bulletin A300-57-
022 does not exist. This AD correctly requires doing repetitive
inspections for cracking if Airbus Service Bulletin A300-57-0222
(modification 11178H5410) has not been embodied.
Conclusion
We reviewed the available data, including the comments received,
and determined that air safety and the public interest require adopting
the AD as proposed.
Differences Between This AD and the MCAI or Service Information
Conclusion
We have reviewed the MCAI and related service information and, in
general, agree with their substance. But we might have found it
necessary to use different words from those in the MCAI to ensure the
AD is clear for U.S. operators and is enforceable. In making these
changes, we do not intend to differ substantively from the information
provided in the MCAI and related service information.
We might also have required different actions in this AD from those
in the MCAI in order to follow our FAA policies. Any such differences
are highlighted in a NOTE within the AD.
Costs of Compliance
We estimate that this AD will affect 162 products of U.S. registry.
We also estimate that it will take about 2 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
this AD to the U.S. operators to be $25,920, or $160 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.
[[Page 14672]]
For the reasons discussed above, I certify this AD:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this AD and placed it in the AD docket.
Examining the AD Docket
You may examine the AD docket on the Internet at https://
www.regulations.gov; or in person at the Docket Operations office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains the NPRM, the regulatory evaluation,
any comments received, and other information. The street address for
the Docket Operations office (telephone (800) 647-5527) is in the
ADDRESSES section. Comments will be available in the AD docket shortly
after receipt.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
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:
2008-06-18 Airbus: Amendment 39-15430. Docket No. FAA-2007-28944;
Directorate Identifier 2006-NM-239-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective April
23, 2008.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Airbus Model A300 series airplanes and
Model A300-600 series airplanes; certificated in any category; all
certified models, all serial numbers.
Subject
(d) Wings.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
This Airworthiness Directive (AD) is published subsequent to the
detection of cracks on multiple aircraft in lower skin panel No. 2
forward of access panel 575FB/675FB held on the rear dummy spar,
inboard of rib 9, fuselage side, aft of the rear spar.
This area of structure has been subjected to several repairs and
modifications in previous years.
The AIRBUS Service Bulletins (SB) A300-57-0177 at Revision 3 and
A300-57-6029 at Revision 4 define the various configurations for the
mandatory inspections to be conducted in order to control or correct
the development of cracks which could affect the structural
integrity of the aircraft.
The MCAI requires doing repetitive inspections (detailed visual,
high frequency eddy current, x-ray) of the wing lower skin panel and
associated internal support structure for cracking and, if
necessary, doing corrective measures (modifying the lower panel
inboard of rib 9 aft of the rear spar and repairing cracks).
Actions and Compliance
(f) Unless already done, do the following actions.
(1) Except as provided by paragraphs (f)(1)(i), (f)(1)(ii),
(f)(1)(iii), and (f)(1)(iv) of this AD: At the threshold specified
in paragraph 1.E.(2) of Airbus Service Bulletin A300-57-0177,
Revision 05, dated March 23, 2007; or A300-57-6029, Revision 06,
dated March 23, 2007; as applicable; perform the inspection of the
wing lower skin panel and associated internal support structure aft
of the rear spar and inboard of rib 9 and apply applicable
corrective measures in accordance with Airbus Service Bulletin A300-
57-0177, Revision 05, dated March 23, 2007; or A300-57-6029,
Revision 06, dated March 23, 2007; as applicable. All applicable
corrective measures must be done at the applicable times specified
in paragraph 1.E.(2) and the Accomplishment Instructions of the
applicable service bulletin.
(i) Where the tables in paragraph 1.E.(2), ``Accomplishment
Timescale,'' of the service bulletins specify a grace period for
doing the actions, this AD requires that the actions be done within
the specified grace period relative to the effective date of this
AD.
(ii) Where the tables in paragraph 1.E.(2)(e), ``Config 04,'' of
Airbus Service Bulletin A300-57-0177, Revision 05, specify an
inspection interval but not an initial threshold, this AD requires
that the actions be done within the specified interval after
inspecting in accordance with Table 1A or 1B, as applicable, for
Configuration 01 airplanes described in the service bulletin and
thereafter at the inspection interval specified in the tables in
paragraph 1.E.(2)(e), ``Config 04,'' of Airbus Service Bulletin
A300-57-0177, Revision 05.
(iii) Where the tables in paragraph 1.E.(2)(f), ``Config 05,''
of Airbus Service Bulletin A300-57-6029, Revision 06, specify an
inspection interval but not an initial threshold, this AD requires
that the actions be done within the specified interval after
inspecting in accordance with Table 1A or 1B, as applicable, for
configuration 01 of the service bulletin and thereafter at the
inspection interval specified in the tables in paragraph 1.E.(2)(f),
``Config 05,'' of A300-57-6029, Revision 06.
(iv) All crack lengths specified in Airbus Service Bulletin
A300-57-0177, Revision 05, and A300-57-6029, Revision 06, are
considered ``not to exceed'' lengths.
(2) Repeat the inspection at the intervals in, and according to
the instructions defined in, Airbus Service Bulletin A300-57-0177,
Revision 05, dated March 23, 2007; or A300-57-6029, Revision 06,
dated March 23, 2007; as applicable; except where Service Bulletin
A300-57-0177, Revision 05, specifies repetitive inspections for
cracking if Airbus Service Bulletin A300-57-022 has not been
embodied, this AD requires doing repetitive inspections for cracking
if Airbus Service Bulletin A300-57-0222 (modification 11178H5410)
has not been embodied.
(3) Report to Airbus the first inspection results, whatever they
may be, at the applicable time specified in paragraph (f)(3)(i) or
(e)(f)(ii) of this AD.
(i) If the inspection was done after the effective date of this
AD, submit the report within 30 days after the inspection.
(ii) If the inspection was accomplished prior to the effective
date of this AD, submit the report within 30 days after the
effective date of this AD.
(4) Actions accomplished before the effective date of this AD in
accordance with Airbus Service Bulletin A300-57-0177, Revision 03,
dated May 29, 2006; Airbus Service Bulletin A300-57-0177, Revision
04, dated January 5, 2007; Airbus Service Bulletin A300-57-6029,
Revision 04, dated May 29, 2006; or Airbus Service Bulletin A300-57-
6029, Revision 05, dated October 23, 2006; are considered acceptable
for compliance with the corresponding action specified in 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,
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: 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
[[Page 14673]]
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 European Aviation Safety Agency Airworthiness
Directive 2006-0282, dated September 12, 2006; and the service
information in Table 1 of this AD; for related information.
Table 1.--Service Information
----------------------------------------------------------------------------------------------------------------
Airbus Service Bulletin Revision level Date
----------------------------------------------------------------------------------------------------------------
A300-57-0177.................................... 05 March 23, 2007.
A300-57-0222.................................... 01 March 13, 2006.
A300-57-6029.................................... 06 March 23, 2007.
A300-57-6064.................................... 04 March 9, 2006.
----------------------------------------------------------------------------------------------------------------
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
----------------------------------------------------------------------------------------------------------------
Airbus Service Bulletin Revision level Date
----------------------------------------------------------------------------------------------------------------
A300-57-0177.................................... 05 March 23, 2007.
A300-57-6029.................................... 06 March 23, 2007.
----------------------------------------------------------------------------------------------------------------
Issued in Renton, Washington, on March 7, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E8-5149 Filed 3-18-08; 8:45 am]
BILLING CODE 4910-13-P
