Airworthiness Directives; Airbus Model A310 and A300-600 Series Airplanes, 29423-29426 [E8-10978]
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Federal Register / Vol. 73, No. 99 / Wednesday, May 21, 2008 / Rules and Regulations
could result in rapid decompression of the
airplane.
Compliance
(e) You are responsible for having the
actions required by this AD performed within
the compliance times specified, unless the
actions have already been done.
Repetitive Inspections
(f) Except as provided by paragraph (g) of
this AD, at the applicable times specified in
paragraph 1.E. of Boeing Alert Service
Bulletin 737–53A1200, dated April 13, 2006,
do external detailed, low frequency eddy
current, high frequency eddy current, and
high frequency eddy current rotary probe
inspections, as applicable, for cracks in and
around the upper and lower hinge cutouts of
the forward entry and forward galley service
doorways, in accordance with the
Accomplishment Instructions of the service
bulletin, except as provided by paragraphs
(h) and (i) of this AD. Do not exceed the
applicable repetitive interval for the previous
inspection, as specified in the service
bulletin as Option A or Option B. Repair any
crack before further flight using a method
approved in accordance with the procedures
specified in paragraph (i) of this AD.
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Exceptions to Service Bulletin Specifications
(g) Where Boeing Alert Service Bulletin
737–53A1200, dated April 13, 2006, specifies
a compliance time after the release date of
the service bulletin, this AD requires
compliance within the specified compliance
time after the effective date of this AD.
(h) Although Boeing Alert Service Bulletin
737–53A1200, dated April 13, 2006, specifies
contacting Boeing for information about
installing an optional preventive
modification that would terminate the
repetitive inspections specified in this AD,
this AD requires that any terminating action
be done by using a method approved in
accordance with the procedures specified in
paragraph (j) of this AD.
(i) The inspections specified in paragraph
(f) of this AD may be terminated at areas
repaired in accordance with Boeing 737–100/
–200 SRM 53–30–1, Figures 20, 21, 31, or 32;
or Boeing 737–300/–400/–500 SRM 53–10–
01, Repair 5, 6, or 8; as applicable.
Alternative Methods of Compliance
(AMOCs)
(j)(1) The Manager, Seattle Aircraft
Certification Office (ACO), FAA, has the
authority to approve AMOCs for this AD, if
requested in accordance with the procedures
found in 14 CFR 39.19.
(2) To request a different method of
compliance or a different compliance time
for this AD, follow the procedures in 14 CFR
39.19. 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.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair
required by this AD, if it is approved by an
Authorized Representative for the Boeing
Commercial Airplanes Delegation Option
Authorization Organization who has been
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Jkt 214001
authorized by the Manager, Seattle ACO, to
make those findings. For a repair method to
be approved, the repair must meet the
certification basis of the airplane, and the
approval must specifically refer to this AD.
Material Incorporated by Reference
(k) You must use Boeing Alert Service
Bulletin 737–53A1200, dated April 13, 2006,
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 Boeing Commercial
Airplanes, P.O. Box 3707, Seattle,
Washington 98124–2207.
(3) You may review copies of the service
information incorporated by reference 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/code_of_
federal_regulations/ibr_locations.html.
Issued in Renton, Washington, on May 9,
2008.
Michael J. Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. E8–11118 Filed 5–20–08; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–0048; Directorate
Identifier 2007–NM–276–AD; Amendment
39–15527; AD 2008–11–05]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A310 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)
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:
Based on some recent in-service findings
for fluid ingress and/or inner skin disbond
damage on rudders, AIRBUS decided to
introduce some further structural inspections
to specific rudder areas. This type of damage
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29423
could result in reduced structural integrity of
the rudder.
*
*
*
*
*
We are issuing this AD to require
actions to correct the unsafe condition
on these products.
DATES: This AD becomes effective June
25, 2008.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of June 25, 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,
Transport Airplane Directorate, FAA,
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 January 22, 2008 (73 FR
3656). That NPRM proposed to correct
an unsafe condition for the specified
products. The MCAI states:
Based on some recent in-service findings
for fluid ingress and/or inner skin disbond
damage on rudders, AIRBUS decided to
introduce some further structural inspections
to specific rudder areas. This type of damage
could result in reduced structural integrity of
the rudder.
For the reasons stated above, this AD
requires the accomplishment of a thorough
inspection program [a one-time inspection
and repetitive inspections for damage of the
rudder] by ultrasonic and/or t[h]ermographic
methods, compared to the inspections
already required by Airworthiness Directive
(AD) 2006–0066, issued on 24 March 2006
[which corresponds to FAA AD 2006–07–13]
as a precautionary measure, in order to verify
the structural integrity of the rudder.
*
*
*
*
*
The corrective actions include
reporting both positive and negative
findings to Airbus, doing a temporary
repair, and contacting Airbus for repair
instructions and doing a permanent
repair. The compliance times for doing
the repairs range from before further
flight to within 4,500 flight cycles after
doing the inspection, depending on the
inspection type and the configuration of
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the airplane. The repetitive inspection
intervals range from 1,200 flight cycles
to 5,000 flight cycles, depending on the
inspection type and the configuration of
the airplane. You may obtain further
information by examining the MCAI in
the AD docket.
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Comments
We gave the public the opportunity to
participate in developing this AD. We
considered the comments received.
Request To Reduce the Compliance
Time
The Allied Pilots Association (APA)
requests that we reduce the compliance
time to do the initial inspections
specified in the NPRM from ‘‘500 flight
cycles or 6 months’’ to ‘‘before further
flight.’’ The APA states that it is unclear
why any grace period is given for doing
the inspections; the APA notes that
statements by the Transportation Safety
Board of Canada, and damage sustained
during an earlier accident that resulted
in destruction of the rudder and damage
to the vertical fin due to an unknown
quantity and type of damage, indicate
the urgency of the inspections. The APA
states that the affected rudders have
been inspected only by visual means
and have not been inspected by an
effective means such as ultrasonic,
infrared, and other sophisticated
penetrating inspection methods. The
APA concludes that the rudders subject
to this AD are in unknown condition
and at risk of an in-flight incident.
We do not agree with reducing the
compliance time. Airbus has analyzed
its data in order to calculate the ‘‘500
flight cycles or six months’’ compliance
time. The analysis included a review of
previous inspections of the rudders that
partially checked the affected area and
no detectable disbond was found. In
developing the compliance time for this
AD action, we considered not only the
safety implications of the identified
unsafe condition, but the average
utilization rate of the affected fleet, the
practical aspects of inspecting the fleet
during the compliance time, and the
availability of required parts. In
addition, we have coordinated with the
European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community. We have determined that
the ‘‘500 flight cycles or six months’’
compliance time ensures an adequate
level of safety for the affected fleet. No
change is necessary for this AD in this
regard.
Request To Exempt Certain Airplanes
The Air Transport Association (ATA),
on behalf of one of its members,
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14:17 May 20, 2008
Jkt 214001
American Airlines, requests that
airplanes on which the modification
specified in Airbus Service Bulletin
A300–55–6015 has been accomplished
be exempted from the requirements of
the NPRM. American Airlines states that
airplanes on which Airbus Modification
08827 has not been incorporated in
production have rudders in the part
number series A55471500 (which are
subject to the requirements of the
NPRM). American Airlines states that
Modification 08827 is a modification
that applies only to the rudder.
American Airlines notes that the
modification specified in Airbus Service
Bulletin A300–55–6015 allows the
installation of a post-modification 08827
rudder and therefore, airplanes on
which Modification 08827 has not been
incorporated in production may have a
post-modification rudder.
We acknowledge that Airbus Service
Bulletins A300–55–6015, Revision 02,
dated February 23, 2004; Revision 03,
dated March 28, 2007; and Revision 04,
dated November 14, 2007 specify
procedures to do a modification that
allows a post-modification 08827 rudder
to be installed. However, we do not
agree that a change to the applicability
of this AD is necessary. An airplane on
which a post-modification 08827 rudder
is installed is not subject to this AD. The
applicability of this AD specifies that
only airplanes on which rudder part
number (P/N) A55471500 series is fitted
are subject to the AD. Airplanes fitted
with a post-modification 08827 rudder
will have a rudder part number other
than P/N A55471500. No change has
been made to this AD in this regard.
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
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.
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Costs of Compliance
We estimate that this AD will affect
123 products of U.S. registry. We also
estimate that it will take about 22 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 $216,480, or $1,760 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
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Federal Register / Vol. 73, No. 99 / Wednesday, May 21, 2008 / Rules and Regulations
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
2008–11–05 AIRBUS: Amendment 39–
15527. Docket No. FAA–2008–0048;
Directorate Identifier 2007–NM–276–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective June 25, 2008.
Affected ADs
(b) The proposed AD supersedes AD 2006–
07–13, Amendment 39–14540.
Applicability
(c) This AD applies to AIRBUS Model
A310 and A300–600 series airplanes,
certificated in any category, all certified
models, all serial numbers, on which rudder
Part Number (P/N) A55471500 series is fitted,
except for those airplanes on which AIRBUS
modification number 08827 has been
incorporated in production.
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Subject
(d) Air Transport Association (ATA) of
America Code 55: Stabilizers.
Reason
(e) The mandatory continuing
airworthiness information (MCAI) states:
Based on some recent in-service findings for
fluid ingress and/or inner skin disbond
damage on rudders, AIRBUS decided to
introduce some further structural inspections
to specific rudder areas. This type of damage
could result in reduced structural integrity of
the rudder.
For the reasons stated above, this AD
requires the accomplishment of a thorough
inspection program [a one-time inspection
and repetitive inspections for damage of the
rudder] by ultrasonic and/or t[h]ermographic
methods, compared to the inspections
already required by Airworthiness Directive
(AD) 2006–0066, issued on 24 March 2006
[which corresponds to FAA AD 2006–07–13]
VerDate Aug<31>2005
14:17 May 20, 2008
Jkt 214001
as a precautionary measure, in order to verify
the structural integrity of the rudder.
*
*
*
*
*
*
*
The corrective actions include reporting
both positive and negative findings to Airbus,
doing a temporary repair, and contacting
Airbus for repair and doing a permanent
repair.
Actions and Compliance
(f) Unless already done, do the following
actions.
(1) Within 500 flight cycles or 6 months
after the effective date of this AD, whichever
occurs first, perform a special detailed onetime inspection in the areas of rudder
hoisting points and trailing edge screws, in
accordance with the instructions given in
Airbus Service Bulletin A310–55–2045 or
A300–55–6044, both Revision 01, both dated
December 20, 2007, as applicable.
(i) If no damage is found, within 30 days
after the inspection or 30 days after the
effective date of this AD, whichever occurs
later, report to Airbus using Appendix 1 or
2, as applicable to the airplane configuration,
of Airbus Service Bulletin A310–55–2045 or
A300–55–6044, both Revision 01, as
applicable.
(ii) If any damage is found, within the
timescale(s) indicated in Airbus Service
Bulletin A310–55–2045 or A300–55–6044,
both Revision 01, as applicable, report to
Airbus using Appendix 1 or 2, as applicable
to the airplane configuration, of Airbus
Service Bulletin A310–55–2045 or A300–55–
6044, both Revision 01, as applicable, to get
further instructions for repair. Accomplish
the repair within the timescale(s) indicated
in, and in accordance with, the instructions
given in paragraph 3.B.(1)(a) or 3.B.(2)(a), as
applicable to the airplane configuration, of
Airbus Service Bulletin A310–55–2045 or
A300–55–6044, both Revision 01, as
applicable.
(2) Within 500 flight cycles or 6 months
after the effective date of this AD, whichever
occurs first, perform a special detailed
inspection along the rudder Z-profile, in
accordance with the instructions given in
Airbus Service Bulletin A310–55–2044 or
A300–55–6043, both Revision 01, both dated
December 3, 2007, as applicable. For
airplanes identified as Configuration 01 in
the service bulletins, repeat the inspection
thereafter at intervals not to exceed 1,400
flight cycles. For airplanes identified as
Configuration 02 in the service bulletins,
repeat the inspection thereafter at intervals
not to exceed 5,000 flight cycles. For
temporary repair along the rudder Z-profile
for both airplanes identified as
Configurations 01 and 02, refer to paragraph
3.C.(1) of Airbus Service Bulletin A310–55–
2044 or A300–55–6043, both Revision 01, as
applicable.
(i) If no damage is found, within 30 days
after the inspection or 30 days after the
effective date of this AD, whichever occurs
later, report to AIRBUS using Appendix 1 or
2, as applicable to the airplane configuration,
of Airbus Service Bulletin A310–55–2044 or
A300–55–6043, both Revision 01, as
applicable.
(ii) If any damage is found, verify the
findings and apply all applicable corrective
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29425
actions within the timescale(s) indicated in,
and in accordance with instructions given in
paragraph 3.B.(1)(a) or 3.B.(2)(a), as
applicable to the airplane configuration, of
Airbus Service Bulletin A310–55–2044 or
A300–55–6043, both Revision 01, as
applicable. Within 30 days after the
inspection or corrective action or 30 days
after the effective date of this AD, whichever
occurs later, submit a report to Airbus using
Appendix 1 or 2, as applicable to the airplane
configuration, of Airbus Service Bulletin
A310–55–2044 or A300–55–6043, both
Revision 01, as applicable.
Note 1: For rudder configuration
identification, refer to Appendices 3 and 4 of
Airbus Service Bulletin A310–55–2044,
A310–55–2045, A300–55–6043, and A300–
55–6044, as applicable to the airplane model
and configuration.
(3) As of 30 days after the effective date of
this AD: No person shall install a P/N
A55471500 series rudder on any airplane as
a replacement, unless it has been inspected
and repaired, as applicable, in accordance
with the instructions of Airbus Service
Bulletins A310–55–2045, Revision 01, dated
December 20, 2007, and A310–55–2044,
Revision 01, dated December 3, 2007; or
Airbus Service Bulletins A300–55–6044,
Revision 01, dated December 20, 2007, and
A300–55–6043, Revision 01, dated December
3, 2007; as applicable.
(4) Actions accomplished before the
effective date of this AD in accordance with
Airbus Service Bulletin A300–55–6044 or
A310–55–2045, both dated July 23, 2007, are
considered acceptable for compliance with
the corresponding actions specified in
paragraph (f)(1) of this AD.
(5) Actions accomplished before the
effective date of this AD in accordance with
Airbus Service Bulletin A300–55–6043 or
A310–55–2044, both dated July 23, 2007, are
considered acceptable for compliance with
the corresponding actions specified in
paragraph (f)(2) of this AD.
FAA AD Differences
Note 2: 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, Transport Airplane Directorate,
FAA, 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
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Federal Register / Vol. 73, No. 99 / Wednesday, May 21, 2008 / Rules and Regulations
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 2007–0266, dated October 8, 2007,
and the service bulletins listed in Table 1 of
this AD, for related information.
TABLE 1.—AIRBUS SERVICE INFORMATION
Airbus service bulletin
A300–55–6043
A300–55–6044
A310–55–2044
A310–55–2045
Revision
....................................................................................................................................
....................................................................................................................................
....................................................................................................................................
....................................................................................................................................
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
Date
01
01
01
01
December
December
December
December
3, 2007.
20, 2007.
3, 2007.
20, 2007.
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
A300–55–6043,
A300–55–6044,
A310–55–2044,
A310–55–2045,
including
including
including
including
Appendices
Appendices
Appendices
Appendices
1
1
1
1
through
through
through
through
Issued in Renton, Washington, on May 6,
2008.
Michael J. Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. E8–10978 Filed 5–20–08; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Office of the Secretary
[Docket No. RITA 2007–28522]
RIN 2139–AA12
Revision of Airline Service Quality
Performance Reports and Disclosure
Requirements
Office of the Secretary, DOT.
ACTION: Final rule.
cprice-sewell on PROD1PC69 with RULES
AGENCY:
SUMMARY: The U.S. Department of
Transportation (Department) will collect
additional data elements when flights
are cancelled, diverted, or experience
gate returns. The additional data
elements will close data gaps and
provide consumers a more accurate
portrayal of arrival and tarmac delays.
The previous NPRM was inadvertently
published under RIN 2139–AA13.
14:17 May 20, 2008
Jkt 214001
...........................................................................
...........................................................................
...........................................................................
...........................................................................
This rule will be effective on
October 1, 2008.
FOR FURTHER INFORMATION CONTACT: Mr.
Bernard Stankus, Office of Airline
Information, RTS–42, Bureau of
Transportation Statistics, Research and
Innovative Technology Administration,
Telephone Number (202) 366–4387, Fax
Number (202) 366–3383, or E-mail
bernard.stankus@dot.gov.
SUPPLEMENTARY INFORMATION:
DATES:
Electronic Access
An electronic copy of this rule, a copy
of the notice of proposed rulemaking,
and copies of the comments may be
downloaded at https://
www.regulations.gov, by searching
docket RITA 2007–28522.
14 CFR Part 234
VerDate Aug<31>2005
4
4
4
4
Revision
Background
The regulation (14 CFR part 234)
requiring airlines that account for at
least one percent of the domestic
scheduled passenger revenues to submit
monthly service quality performance
reports was issued on September 9,
1987 (52 FR 34071). At that time, close
to 40 percent of all flights were either
late or cancelled. On-time performance
reporting created a market-based
incentive for carriers to improve their
service and scheduling practices. The
immediate result of this action was an
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Date
01
01
01
01
December
December
December
December
3, 2007.
20, 2007.
3, 2007.
20, 2007.
improvement in carriers’ on-time
performance. For the remainder of 1987,
the industry had an on-time arrival rate
of over 74 percent.
The Department added data elements
to the reporting system in 1995 to
enable the Federal Aviation
Administration (FAA) to identify choke
points within the air traffic control
system (60 FR 66722, December 26,
1995). Aircraft tail number, wheels-off
time and wheels-on time gave the FAA
information concerning aircraft routings
through the air traffic control system
and detailed data on tarmac and
airborne delays. A tarmac delay is one
that takes place on the ground, such as
on the ramp or taxiway.
In 1999 and 2000, airline delays
increased dramatically with the increase
in airline operations. Consumer
complaints concerning flight delays
increased by 58%. Section 227 of the
Aviation Investment and Reform Act for
the 21st Century (AIR–21) called upon
the Secretary of Transportation to
disclose to the public the source of
delayed and cancelled flights. During
this period, the Air Transport
Association of America also petitioned
the Department to report the causes of
delays and cancellations. In August
2000, an Air Carrier On-time Reporting
Advisory Committee was established to
E:\FR\FM\21MYR1.SGM
21MYR1
]]>Agencies
[Federal Register Volume 73, Number 99 (Wednesday, May 21, 2008)]
[Rules and Regulations]
[Pages 29423-29426]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-10978]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-0048; Directorate Identifier 2007-NM-276-AD;
Amendment 39-15527; AD 2008-11-05]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A310 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:
Based on some recent in-service findings for fluid ingress and/
or inner skin disbond damage on rudders, AIRBUS decided to introduce
some further structural inspections to specific rudder areas. This
type of damage could result in reduced structural integrity of the
rudder.
* * * * *
We are issuing this AD to require actions to correct the unsafe
condition on these products.
DATES: This AD becomes effective June 25, 2008.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of June 25,
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, Transport Airplane Directorate, FAA,
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 January 22, 2008 (73
FR 3656). That NPRM proposed to correct an unsafe condition for the
specified products. The MCAI states:
Based on some recent in-service findings for fluid ingress and/
or inner skin disbond damage on rudders, AIRBUS decided to introduce
some further structural inspections to specific rudder areas. This
type of damage could result in reduced structural integrity of the
rudder.
For the reasons stated above, this AD requires the
accomplishment of a thorough inspection program [a one-time
inspection and repetitive inspections for damage of the rudder] by
ultrasonic and/or t[h]ermographic methods, compared to the
inspections already required by Airworthiness Directive (AD) 2006-
0066, issued on 24 March 2006 [which corresponds to FAA AD 2006-07-
13] as a precautionary measure, in order to verify the structural
integrity of the rudder.
* * * * *
The corrective actions include reporting both positive and negative
findings to Airbus, doing a temporary repair, and contacting Airbus for
repair instructions and doing a permanent repair. The compliance times
for doing the repairs range from before further flight to within 4,500
flight cycles after doing the inspection, depending on the inspection
type and the configuration of
[[Page 29424]]
the airplane. The repetitive inspection intervals range from 1,200
flight cycles to 5,000 flight cycles, depending on the inspection type
and the configuration of the airplane. 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 Reduce the Compliance Time
The Allied Pilots Association (APA) requests that we reduce the
compliance time to do the initial inspections specified in the NPRM
from ``500 flight cycles or 6 months'' to ``before further flight.''
The APA states that it is unclear why any grace period is given for
doing the inspections; the APA notes that statements by the
Transportation Safety Board of Canada, and damage sustained during an
earlier accident that resulted in destruction of the rudder and damage
to the vertical fin due to an unknown quantity and type of damage,
indicate the urgency of the inspections. The APA states that the
affected rudders have been inspected only by visual means and have not
been inspected by an effective means such as ultrasonic, infrared, and
other sophisticated penetrating inspection methods. The APA concludes
that the rudders subject to this AD are in unknown condition and at
risk of an in-flight incident.
We do not agree with reducing the compliance time. Airbus has
analyzed its data in order to calculate the ``500 flight cycles or six
months'' compliance time. The analysis included a review of previous
inspections of the rudders that partially checked the affected area and
no detectable disbond was found. In developing the compliance time for
this AD action, we considered not only the safety implications of the
identified unsafe condition, but the average utilization rate of the
affected fleet, the practical aspects of inspecting the fleet during
the compliance time, and the availability of required parts. In
addition, we have coordinated with the European Aviation Safety Agency
(EASA), which is the Technical Agent for the Member States of the
European Community. We have determined that the ``500 flight cycles or
six months'' compliance time ensures an adequate level of safety for
the affected fleet. No change is necessary for this AD in this regard.
Request To Exempt Certain Airplanes
The Air Transport Association (ATA), on behalf of one of its
members, American Airlines, requests that airplanes on which the
modification specified in Airbus Service Bulletin A300-55-6015 has been
accomplished be exempted from the requirements of the NPRM. American
Airlines states that airplanes on which Airbus Modification 08827 has
not been incorporated in production have rudders in the part number
series A55471500 (which are subject to the requirements of the NPRM).
American Airlines states that Modification 08827 is a modification that
applies only to the rudder. American Airlines notes that the
modification specified in Airbus Service Bulletin A300-55-6015 allows
the installation of a post-modification 08827 rudder and therefore,
airplanes on which Modification 08827 has not been incorporated in
production may have a post-modification rudder.
We acknowledge that Airbus Service Bulletins A300-55-6015, Revision
02, dated February 23, 2004; Revision 03, dated March 28, 2007; and
Revision 04, dated November 14, 2007 specify procedures to do a
modification that allows a post-modification 08827 rudder to be
installed. However, we do not agree that a change to the applicability
of this AD is necessary. An airplane on which a post-modification 08827
rudder is installed is not subject to this AD. The applicability of
this AD specifies that only airplanes on which rudder part number (P/N)
A55471500 series is fitted are subject to the AD. Airplanes fitted with
a post-modification 08827 rudder will have a rudder part number other
than P/N A55471500. No change has been made to this AD in this regard.
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
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 123 products of U.S. registry.
We also estimate that it will take about 22 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 $216,480, or $1,760 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
[[Page 29425]]
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:
2008-11-05 AIRBUS: Amendment 39-15527. Docket No. FAA-2008-0048;
Directorate Identifier 2007-NM-276-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective June 25,
2008.
Affected ADs
(b) The proposed AD supersedes AD 2006-07-13, Amendment 39-
14540.
Applicability
(c) This AD applies to AIRBUS Model A310 and A300-600 series
airplanes, certificated in any category, all certified models, all
serial numbers, on which rudder Part Number (P/N) A55471500 series
is fitted, except for those airplanes on which AIRBUS modification
number 08827 has been incorporated in production.
Subject
(d) Air Transport Association (ATA) of America Code 55:
Stabilizers.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states: Based on some recent in-service findings for fluid ingress
and/or inner skin disbond damage on rudders, AIRBUS decided to
introduce some further structural inspections to specific rudder
areas. This type of damage could result in reduced structural
integrity of the rudder.
For the reasons stated above, this AD requires the
accomplishment of a thorough inspection program [a one-time
inspection and repetitive inspections for damage of the rudder] by
ultrasonic and/or t[h]ermographic methods, compared to the
inspections already required by Airworthiness Directive (AD) 2006-
0066, issued on 24 March 2006 [which corresponds to FAA AD 2006-07-
13] as a precautionary measure, in order to verify the structural
integrity of the rudder.
* * * * * * *
The corrective actions include reporting both positive and
negative findings to Airbus, doing a temporary repair, and
contacting Airbus for repair and doing a permanent repair.
Actions and Compliance
(f) Unless already done, do the following actions.
(1) Within 500 flight cycles or 6 months after the effective
date of this AD, whichever occurs first, perform a special detailed
one-time inspection in the areas of rudder hoisting points and
trailing edge screws, in accordance with the instructions given in
Airbus Service Bulletin A310-55-2045 or A300-55-6044, both Revision
01, both dated December 20, 2007, as applicable.
(i) If no damage is found, within 30 days after the inspection
or 30 days after the effective date of this AD, whichever occurs
later, report to Airbus using Appendix 1 or 2, as applicable to the
airplane configuration, of Airbus Service Bulletin A310-55-2045 or
A300-55-6044, both Revision 01, as applicable.
(ii) If any damage is found, within the timescale(s) indicated
in Airbus Service Bulletin A310-55-2045 or A300-55-6044, both
Revision 01, as applicable, report to Airbus using Appendix 1 or 2,
as applicable to the airplane configuration, of Airbus Service
Bulletin A310-55-2045 or A300-55-6044, both Revision 01, as
applicable, to get further instructions for repair. Accomplish the
repair within the timescale(s) indicated in, and in accordance with,
the instructions given in paragraph 3.B.(1)(a) or 3.B.(2)(a), as
applicable to the airplane configuration, of Airbus Service Bulletin
A310-55-2045 or A300-55-6044, both Revision 01, as applicable.
(2) Within 500 flight cycles or 6 months after the effective
date of this AD, whichever occurs first, perform a special detailed
inspection along the rudder Z-profile, in accordance with the
instructions given in Airbus Service Bulletin A310-55-2044 or A300-
55-6043, both Revision 01, both dated December 3, 2007, as
applicable. For airplanes identified as Configuration 01 in the
service bulletins, repeat the inspection thereafter at intervals not
to exceed 1,400 flight cycles. For airplanes identified as
Configuration 02 in the service bulletins, repeat the inspection
thereafter at intervals not to exceed 5,000 flight cycles. For
temporary repair along the rudder Z-profile for both airplanes
identified as Configurations 01 and 02, refer to paragraph 3.C.(1)
of Airbus Service Bulletin A310-55-2044 or A300-55-6043, both
Revision 01, as applicable.
(i) If no damage is found, within 30 days after the inspection
or 30 days after the effective date of this AD, whichever occurs
later, report to AIRBUS using Appendix 1 or 2, as applicable to the
airplane configuration, of Airbus Service Bulletin A310-55-2044 or
A300-55-6043, both Revision 01, as applicable.
(ii) If any damage is found, verify the findings and apply all
applicable corrective actions within the timescale(s) indicated in,
and in accordance with instructions given in paragraph 3.B.(1)(a) or
3.B.(2)(a), as applicable to the airplane configuration, of Airbus
Service Bulletin A310-55-2044 or A300-55-6043, both Revision 01, as
applicable. Within 30 days after the inspection or corrective action
or 30 days after the effective date of this AD, whichever occurs
later, submit a report to Airbus using Appendix 1 or 2, as
applicable to the airplane configuration, of Airbus Service Bulletin
A310-55-2044 or A300-55-6043, both Revision 01, as applicable.
Note 1: For rudder configuration identification, refer to
Appendices 3 and 4 of Airbus Service Bulletin A310-55-2044, A310-55-
2045, A300-55-6043, and A300-55-6044, as applicable to the airplane
model and configuration.
(3) As of 30 days after the effective date of this AD: No person
shall install a P/N A55471500 series rudder on any airplane as a
replacement, unless it has been inspected and repaired, as
applicable, in accordance with the instructions of Airbus Service
Bulletins A310-55-2045, Revision 01, dated December 20, 2007, and
A310-55-2044, Revision 01, dated December 3, 2007; or Airbus Service
Bulletins A300-55-6044, Revision 01, dated December 20, 2007, and
A300-55-6043, Revision 01, dated December 3, 2007; as applicable.
(4) Actions accomplished before the effective date of this AD in
accordance with Airbus Service Bulletin A300-55-6044 or A310-55-
2045, both dated July 23, 2007, are considered acceptable for
compliance with the corresponding actions specified in paragraph
(f)(1) of this AD.
(5) Actions accomplished before the effective date of this AD in
accordance with Airbus Service Bulletin A300-55-6043 or A310-55-
2044, both dated July 23, 2007, are considered acceptable for
compliance with the corresponding actions specified in paragraph
(f)(2) of this AD.
FAA AD Differences
Note 2: 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,
Transport Airplane Directorate, FAA, 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
[[Page 29426]]
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 2007-0266, dated
October 8, 2007, and the service bulletins listed in Table 1 of this
AD, for related information.
Table 1.--Airbus Service Information
----------------------------------------------------------------------------------------------------------------
Airbus service bulletin Revision Date
----------------------------------------------------------------------------------------------------------------
A300-55-6043................................. 01 December 3, 2007.
A300-55-6044................................. 01 December 20, 2007.
A310-55-2044................................. 01 December 3, 2007.
A310-55-2045................................. 01 December 20, 2007.
----------------------------------------------------------------------------------------------------------------
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 Date
----------------------------------------------------------------------------------------------------------------
A300-55-6043, including Appendices 1 through 01 December 3, 2007.
4.
A300-55-6044, including Appendices 1 through 01 December 20, 2007.
4.
A310-55-2044, including Appendices 1 through 01 December 3, 2007.
4.
A310-55-2045, including Appendices 1 through 01 December 20, 2007.
4.
----------------------------------------------------------------------------------------------------------------
Issued in Renton, Washington, on May 6, 2008.
Michael J. Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E8-10978 Filed 5-20-08; 8:45 am]
BILLING CODE 4910-13-P
