Airworthiness Directives; Airbus Model A310-200 and -300 Series Airplanes, 25921-25924 [06-4052]
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Federal Register / Vol. 71, No. 85 / Wednesday, May 3, 2006 / Rules and Regulations
Note 1: This AD requires revisions to
certain operator maintenance documents to
include new inspections. Compliance with
these inspections is required by 14 CFR
91.403(c). For airplanes that have been
previously modified, altered, or repaired in
the areas addressed by these inspections, the
operator may not be able to accomplish the
inspections described in the revisions. In this
situation, to comply with 14 CFR 91.403(c),
the operator must request approval for an
alternative method of compliance according
to paragraph (h) of this AD. The request
should include a description of changes to
the required inspections that will ensure the
continued damage tolerance of the affected
structure. The FAA has provided guidance
for this determination in Advisory Circular
25–1529.
Unsafe Condition
(d) This AD results from a revision to
subsection 9–1 of the Airbus A330 and A340
Maintenance Planning Documents (MPD) for
Life limits/Monitored parts, and subsection
9–2 of the Airbus A330 MPD for
Airworthiness Limitations Items. We are
issuing this AD to prevent fatigue cracking,
damage, or corrosion, which could result in
reduced structural integrity of these
airplanes.
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.
Airworthiness Limitations Revision
(f) Within 3 months after the effective date
of this AD, revise the Airworthiness
Limitations section (ALS) of the Instructions
for Continued Airworthiness by
incorporating into the ALS the documents in
paragraph (f)(1) and (f)(2) of this AD, as
applicable.
(1) Airbus Document AI/SE–M4/95A.0089/
97, ‘‘A330 Airworthiness Limitations Items,’’
Issue 12, dated November 1, 2003, as
specified in Section 9–2 of the Airbus A330
MPD.
(2) Section 9–1, ‘‘Life limits/Monitored
parts,’’ Revision 05, dated April 7, 2005, of
the Airbus A330 and A340 MPDs.
(g) Except as provided by paragraph (h) of
this AD: After the actions in paragraph (f) of
this AD have been accomplished, no
alternative inspections or inspection
intervals may be approved for the structural
elements specified in the documents listed in
paragraph (f) of this AD.
sroberts on PROD1PC70 with RULES
Alternative Methods of Compliance
(AMOCs)
(h)(1) The Manager, International Branch,
ANM–116, Transport Airplane Directorate,
FAA, has the authority to approve AMOCs
for this AD, if requested in accordance with
the procedures found in 14 CFR 39.19.
(2) Before using any AMOC approved in
accordance with § 39.19 on any airplane to
which the AMOC applies, notify the
appropriate principal inspector in the FAA
Flight Standards Certificate Holding District
Office.
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Jkt 208001
Related Information
DEPARTMENT OF TRANSPORTATION
(i) French airworthiness directives F–
2004–024, dated February 18, 2004; F–2005–
069, dated April 27, 2005; and F–2005–070,
dated April 27, 2005; also address the subject
of this AD.
Material Incorporated by Reference
(j) You must use Airbus Document AI/SE–
M4/95A.0089/97, ‘‘A330 Airworthiness
Limitations Items,’’ Issue 12, dated November
1, 2003; Section 9–1, ‘‘Life limits/Monitored
parts,’’ Revision 05, dated April 7, 2005, of
the Airbus A330 Maintenance Planning
Document; and Section 9–1, ‘‘Life limits/
Monitored parts,’’ Revision 05, dated April 7,
2005, of the Airbus A340 Maintenance
Planning Document; as applicable, to
perform the actions that are required by this
AD, unless the AD specifies otherwise. (The
document and issue number of Airbus
Document AI/SE–M4/95A.0089/97 are
contained only on the Title, Record of
Revision, Summary of Changes, List of
Effective Pages, Table of Contents, and
Section 1 pages; no other page of this
document contains this information. The
revision number of Section 9–1 of the Airbus
A330 Maintenance Planning Document and
Section 9–1 of the Airbus A340 Maintenance
Planning Document is contained only in the
Record of Revisions page; no other page of
these documents contains this information.
The issue date on the title page of section 9–
1 of the Airbus A340 Maintenance Planning
Document should be ‘‘April 7, 2005.’’) The
Director of the Federal Register approved the
incorporation by reference of these
documents in accordance with 5 U.S.C.
552(a) and 1 CFR part 51. Contact Airbus, 1
Rond Point Maurice Bellonte, 31707 Blagnac
Cedex, France, for a copy of this service
information. You may review copies at the
Docket Management Facility, U.S.
Department of Transportation, 400 Seventh
Street, SW., room PL–401, Nassif Building,
Washington, DC; on the Internet at https://
dms.dot.gov; or at the National Archives and
Records Administration (NARA). For
information on the availability of this
material at the 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 April 20,
2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 06–4051 Filed 5–2–06; 8:45 am]
BILLING CODE 4910–13–P
PO 00000
25921
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–23870; Directorate
Identifier 2005–NM–022–AD; Amendment
39–14575; AD 2006–09–05]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A310–200 and –300 Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for all
Airbus Model A310–200 and –300 series
airplanes. This AD requires doing
repetitive rotating probe inspections for
any crack of the rear spar internal angle
and the left and right sides of the tee
fitting, and doing related investigative/
corrective actions if necessary. This AD
also requires modifying the holes in the
internal angle and tee fitting by cold
expansion. This AD results from fullscale fatigue tests, which revealed
cracks in the lower rear spar internal
angle, and tee fitting. We are issuing this
AD to detect and correct fatigue cracks
of the rear spar internal angle and tee
fitting, which could lead to the rupture
of the internal angle, tee fitting, and rear
spar, and consequent reduced structural
integrity of the wings.
DATES: This AD becomes effective June
7, 2006.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of June 7, 2006.
ADDRESSES: You may examine the AD
docket on the Internet at https://
dms.dot.gov or in person at the Docket
Management Facility, U.S. Department
of Transportation, 400 Seventh Street,
SW., Nassif Building, Room PL–401,
Washington, DC.
Contact Airbus, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France,
for service information identified in this
AD.
FOR FURTHER INFORMATION CONTACT: Tim
Backman, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton,
Washington 98055–4056; telephone
(425) 227–2797; fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Examining the Docket
You may examine the airworthiness
directive (AD) docket on the Internet at
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25922
Federal Register / Vol. 71, No. 85 / Wednesday, May 3, 2006 / Rules and Regulations
https://dms.dot.gov or in person at the
Docket Management Facility office
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The Docket Management Facility office
(telephone (800) 647–5227) is located on
the plaza level of the Nassif Building at
the street address stated in the
ADDRESSES section.
Discussion
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
apply to all Airbus Model A310–200
and –300 series airplanes. That NPRM
was published in the Federal Register
on February 13, 2006 (71 FR 7449). That
NPRM proposed to require doing
repetitive rotating probe inspections for
any crack of the rear spar internal angle
and the left and right sides of the tee
fitting, and doing related investigative/
corrective actions if necessary. That
NPRM also proposed to require
modifying the holes in the internal
angle and tee fitting by cold expansion.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We received no
comments on the NPRM or on the
determination of the cost to the public.
Conclusion
We have carefully reviewed the
available data and determined that air
safety and the public interest require
adopting the AD as proposed.
Costs of Compliance
The following table provides the
estimated costs for U.S. operators to
comply with this AD. This AD will
affect about 56 airplanes of U.S. registry.
Work hours and parts costs vary
according to the configuration of the
airplane.
ESTIMATED COSTS
Action
Work hour
Average
labor rate
per hour
Parts
Cost per airplane
Inspection ...............
16–306
$65
$618–$18,489
Modification ............
146–381
65
4,350–15,501
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.
sroberts on PROD1PC70 with RULES
Regulatory Findings
We have 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 that this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
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Fleet cost
$1,658–$38,379, per inspection
cycle.
$13,840–$40,266 ..........................
$92,848–$2,149,224, per inspection cycle.
$775,040–$2,254,896.
(2) Is not a ‘‘significant rule’’ under
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.
See the ADDRESSES section for a location
to examine the regulatory evaluation.
Effective Date
(a) This AD becomes effective June 7, 2006.
Affected ADs
(b) Certain requirements of this AD
terminate certain requirements of AD 98–26–
01, amendment 39–10942.
Applicability
(c) This AD applies to all Airbus Model
A310–203, –204, –221, and –222 airplanes;
and Model A310–304, –322, –324, and –325
airplanes; certificated in any category.
I
Unsafe Condition
(d) This AD results from full-scale fatigue
tests, which revealed cracks in the lower rear
spar internal angle and tee fitting. We are
issuing this AD to detect and correct fatigue
cracks of the rear spar internal angle and tee
fitting, which could lead to the rupture of the
internal angle, tee fitting, and rear spar, and
consequent reduced structural integrity of the
wings.
PART 39—AIRWORTHINESS
DIRECTIVES
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.
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:
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 Federal Aviation
Administration (FAA) amends § 39.13
by adding the following new
airworthiness directive (AD):
I
2006–09–05 Airbus: Amendment 39–14575.
Docket No. FAA–2006–23870;
Directorate Identifier 2005–NM–022–AD.
PO 00000
Frm 00004
Fmt 4700
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Initial and Repetitive Inspections
(f) At the later of the times specified in
paragraphs (f)(1) and (f)(2) of this AD, do a
rotating probe inspection for any crack of the
rear spar internal angle located in the center
wing box and do all applicable related
investigative and corrective actions in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A310–
57–2047, Revision 06, dated July 13, 2004,
except as required by paragraphs (k), (l), and
(m) of this AD. Do all applicable related
investigative and corrective actions before
further flight.
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Federal Register / Vol. 71, No. 85 / Wednesday, May 3, 2006 / Rules and Regulations
(1) Within 1,000 flight cycles or 1,600
flight hours after the effective date of this AD,
whichever is first.
25923
(2) At the applicable time specified in
Table 1 of this AD.
TABLE 1.—INITIAL COMPLIANCE TIMES FOR THE REAR SPAR INTERNAL ANGLE
Airplane model and configuration
Threshold
Model A310–203, –204, –221, and –222 airplanes that are not modified
by Airbus Modifications 06672S6812 and 07387S7974.
Model A310–203, –204, –221, and –222 airplanes that are modified by
Airbus Modifications 06672S6812 and 07387S7974 (modified either
in production or in accordance with Airbus Service Bulletin A310–57–
2035).
Model A310–304, –322, –324, and –325 airplanes that are not modified
by Airbus Modifications 06672S6812 and 07387S7974.
Model A310–304, –322, –324, and –325 airplanes that are modified by
Airbus Modifications 06672S6812 and 07387S7974 (modified either
in production or according to Airbus Service Bulletin A310–57–2035).
(g) Repeat the inspection specified in
paragraph (f) of this AD thereafter at the
applicable time specified in paragraph (g)(1)
or (g)(2) of this AD.
(1) For Model A310–203, –204, –221, and
–222 airplanes: Repeat thereafter at intervals
not to exceed 9,100 flight cycles or 14,650
flight hours, whichever is first.
Before
flight
Before
flight
the accumulation of 10,300 total flight cycles or 16,600 total
hours, whichever is first.
the accumulation of 23,400 total flight cycles or 37,700 total
hours, whichever is first.
Before the accumulation of 9,500 total flight cycles or 15,000 total flight
hours, whichever is first.
Before the accumulation of 21,500 total flight cycles or 34,000 total
flight hours, whichever is first.
(2) For Model A310–304, –322, –324, and
–325 airplanes: Repeat thereafter at intervals
not to exceed 9,500 flight cycles or 15,000
flight hours, whichever is first.
(h) At the applicable time specified in
Table 2 of this AD or within 6 months after
the effective date of this AD, whichever
occurs later: Do a rotating probe inspection
for any crack of the left and right sides of the
tee fitting, and do all applicable related
investigative and corrective actions in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A310–
57–2047, Revision 06, dated July 13, 2004,
except as required by paragraphs (k), (l), and
(m) of this AD. Do all applicable related
investigative and corrective actions before
further flight.
TABLE 2.—INITIAL COMPLIANCE TIMES FOR THE TEE FITTING
Airplane model and configuration
Threshold
Model A310–203, –204, –221, and –222 airplanes that are not modified
by Airbus Modification 06673S6813.
Model A310–203, –204, –221, and –222 airplanes that are modified by
Airbus Modification 06673S6813 (modified either in production or in
accordance with Airbus Service Bulletin A310–57–2035).
Model A310–304, –322, –324, and –325 airplanes that are not modified
by Airbus Modification 06673S6813.
Model A310–304, –322, –324, and –325 airplanes that are modified by
Airbus Modification 06673S6813 (modified either in production or in
accordance with Airbus Service Bulletin A310–57–2035).
(i) Repeat the inspection specified in
paragraph (h) of this AD thereafter at the
applicable time specified in paragraph (i)(1)
or (i)(2) of this AD.
(1) For Model A310–203, –204, –221, and
–222 airplanes: Repeat thereafter at intervals
not to exceed 10,800 flight cycles or 17,400
flight hours, whichever is first.
(2) For Model A310–304, –322, –324, and
–325 airplanes: Repeat thereafter at intervals
not to exceed 8,800 flight cycles or 13,900
flight hours, whichever is first.
sroberts on PROD1PC70 with RULES
Modification
(j) For all airplanes except those that are
modified by Airbus Modifications
06672S6812, 06673S6813, and 07387S7974
in production: Within 60 months after the
effective date of this AD, modify the holes in
the internal angle and tee fitting and do all
applicable related investigative and
corrective actions by accomplishing all the
actions specified in the Accomplishment
Instructions of Airbus Service Bulletin A310–
57–2035, Revision 08, dated September 19,
2005, except as required by paragraph (k) of
this AD. Do all applicable related
VerDate Aug<31>2005
18:14 May 02, 2006
Jkt 208001
Before
flight
Before
flight
the accumulation of 21,600 total flight cycles or 34,800 total
hours, whichever is first.
the accumulation of 41,300 total flight cycles or 66,500 total
hours, whichever is first.
Before
flight
Before
flight
the accumulation of 17,100 total flight cycles or 27,000 total
hours, whichever is first.
the accumulation of 32,300 total flight cycles or 51,000 total
hours, whichever is first.
investigative and corrective actions before
further flight.
to the manufacturer, this AD does not
include that requirement.
Contact the FAA
Actions Accomplished According to
Previous Issues of Service Bulletins
(k) Where Airbus Service Bulletin A310–
57–2035, Revision 08, dated September 19,
2005; and Airbus Service Bulletin A310–57–
2047, Revision 06, dated July 13, 2004;
specify to contact the manufacturer if certain
cracks are found, before further flight, repair
those conditions according to a method
approved by either the Manager,
International Branch, ANM–116, Transport
Airplane Directorate, FAA; or the Direction
´ ´
Generale de l’Aviation Civile (DGAC) (or its
delegated agent).
Touch-and-Go Flights
(l) All touch-and-go landings must be
counted in determining the total number of
flight cycles between consecutive
inspections.
No Reporting Required
(m) Although Airbus Service Bulletin
A310–57–2047, Revision 06, dated July 13,
2004, specifies to submit certain information
PO 00000
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(n) Actions accomplished before the
effective date of this AD in accordance with
Airbus Service Bulletin A310–57–2047,
Revision 03, dated November 26, 1997;
Revision 04, dated March 5, 1999; or
Revision 05, dated August 3, 2000; are
considered acceptable for compliance with
the corresponding actions specified in
paragraphs (f) through (i) of this AD.
(o) Actions accomplished before the
effective date of this AD in accordance with
Airbus Service Bulletin A310–57–2035,
Revision 1, dated October 13, 1989; Revision
2, dated February 26, 1990; Revision 3, dated
May 23, 1990; Revision 4, dated April 15,
1991; Revision 5, dated May 27, 1992;
Revision 6, dated March 8, 1994; or Revision
7, dated April 17, 1996; are considered
acceptable for compliance with the
corresponding actions specified in paragraph
(j) of this AD.
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Federal Register / Vol. 71, No. 85 / Wednesday, May 3, 2006 / Rules and Regulations
Related AD
accordance with the procedures found in 14
CFR 39.19.
(2) Before using any AMOC approved in
accordance with 14 CFR 39.19 on any
airplane to which the AMOC applies, notify
the appropriate principal inspector in the
FAA Flight Standards Certificate Holding
District Office.
(p) Accomplishing the initial inspections
specified in paragraphs (f) and (g) of this AD
terminates the requirements specified in
paragraph (o) of AD 98–26–01.
Alternative Methods of Compliance
(AMOCs)
Related Information
(r) French airworthiness directive F–2005–
001, dated January 5, 2005, also addresses the
subject of this AD.
(q)(1) The Manager, International Branch,
ANM–116, has the authority to approve
AMOCs for this AD, if requested in
Material Incorporated by Reference
(s) You must use Airbus Service Bulletin
A310–57–2047, Revision 06, dated July 13,
2004; and Airbus Service Bulletin A310–57–
2035, Revision 08, dated September 19, 2005;
as applicable, to perform the actions that are
required by this AD, unless the AD specifies
otherwise. Airbus Service Bulletin A310–57–
2047, Revision 06, dated July 13, 2004,
includes the following effective pages:
Page Nos.
Revision level
shown on page
Date shown on page
1–8, 10–15, 17, 18, 22–25, 33, 37 ...........................................................................................................
9, 16, 21, 30, 45, 46, 75–80, 95, 96 ........................................................................................................
19, 20, 27–29, 35, 36, 47–56, 61–74 .......................................................................................................
26, 31, 32, 34, 39–44, 59, 60, 81–94 .......................................................................................................
38 ..............................................................................................................................................................
57, 58 ........................................................................................................................................................
06 .....................
05 .....................
Original .............
04 .....................
1 .......................
2 .......................
July 13, 2004.
August 3, 2000.
February 26, 1991.
March 5, 1999.
January 4, 1996.
January 22, 1997.
The Director of the Federal Register
approved the incorporation by reference of
these documents in accordance with 5 U.S.C.
552(a) and 1 CFR part 51. Contact Airbus, 1
Rond Point Maurice Bellonte, 31707 Blagnac
Cedex, France, for a copy of this service
information. You may review copies at the
Docket Management Facility, U.S.
Department of Transportation, 400 Seventh
Street, SW., Room PL–401, Nassif Building,
Washington, DC; on the Internet at https://
dms.dot.gov; or at the National Archives and
Records Administration (NARA). For
information on the availability of this
material at the 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 April 20,
2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 06–4052 Filed 5–2–06; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–23886; Directorate
Identifier 2005–NM–255–AD; Amendment
39–14574; AD 2006–09–04]
RIN 2120–AA64
sroberts on PROD1PC70 with RULES
Airworthiness Directives; Dassault
Model Falcon 900EX Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
VerDate Aug<31>2005
18:14 May 02, 2006
Jkt 208001
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for certain
Dassault Model Falcon 900EX airplanes.
This AD requires inspecting the number
2 engine left- and right-hand forward
mounts for missing rivets, and installing
rivets if necessary. This AD results from
reports of two missing rivets in the front
section of the central engine mast
discovered on airplanes in service and
in production. We are issuing this AD
to detect and correct missing rivets in
the front section of the central engine
mast, which could result in reduced
structural integrity of the central engine
mast, possible separation of the engine
from the airplane during flight, and
consequent loss of control of the
airplane.
DATES: This AD becomes effective June
7, 2006.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of June 7, 2006.
ADDRESSES: You may examine the AD
docket on the Internet at https://
dms.dot.gov or in person at the Docket
Management Facility, U.S. Department
of Transportation, 400 Seventh Street,
SW., Nassif Building, Room PL–401,
Washington, DC.
Contact Dassault Falcon Jet, P.O. Box
2000, South Hackensack, New Jersey
07606, for service information identified
in this AD.
FOR FURTHER INFORMATION CONTACT: Tom
Rodriguez, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton, WA
98055–4056; telephone (425) 227–1137;
fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
PO 00000
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Examining the Docket
You may examine the airworthiness
directive (AD) docket on the Internet at
https://dms.dot.gov or in person at the
Docket Management Facility office
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The Docket Management Facility office
(telephone (800) 647–5227) is located on
the plaza level of the Nassif Building at
the street address stated in the
ADDRESSES section.
Discussion
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
apply to certain Dassault Model Falcon
900EX airplanes. That NPRM was
published in the Federal Register on
February 15, 2006 (71 FR 7874). That
NPRM proposed to require inspecting
the number 2 engine left- and right-hand
forward mounts for missing rivets, and
installing rivets if necessary.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We received no
comments on the NPRM or on the
determination of the cost to the public.
Conclusion
We have carefully reviewed the
available data and determined that air
safety and the public interest require
adopting the AD as proposed.
Costs of Compliance
The following table provides the
estimated costs for U.S. operators to
comply with this AD.
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]]>Agencies
[Federal Register Volume 71, Number 85 (Wednesday, May 3, 2006)]
[Rules and Regulations]
[Pages 25921-25924]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 06-4052]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-23870; Directorate Identifier 2005-NM-022-AD;
Amendment 39-14575; AD 2006-09-05]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A310-200 and -300 Series
Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for all
Airbus Model A310-200 and -300 series airplanes. This AD requires doing
repetitive rotating probe inspections for any crack of the rear spar
internal angle and the left and right sides of the tee fitting, and
doing related investigative/corrective actions if necessary. This AD
also requires modifying the holes in the internal angle and tee fitting
by cold expansion. This AD results from full-scale fatigue tests, which
revealed cracks in the lower rear spar internal angle, and tee fitting.
We are issuing this AD to detect and correct fatigue cracks of the rear
spar internal angle and tee fitting, which could lead to the rupture of
the internal angle, tee fitting, and rear spar, and consequent reduced
structural integrity of the wings.
DATES: This AD becomes effective June 7, 2006.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of June 7, 2006.
ADDRESSES: You may examine the AD docket on the Internet at https://
dms.dot.gov or in person at the Docket Management Facility, U.S.
Department of Transportation, 400 Seventh Street, SW., Nassif Building,
Room PL-401, Washington, DC.
Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex,
France, for service information identified in this AD.
FOR FURTHER INFORMATION CONTACT: Tim Backman, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-2797; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Examining the Docket
You may examine the airworthiness directive (AD) docket on the
Internet at
[[Page 25922]]
https://dms.dot.gov or in person at the Docket Management Facility
office between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the
street address stated in the ADDRESSES section.
Discussion
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to include an AD that would apply to all Airbus Model A310-
200 and -300 series airplanes. That NPRM was published in the Federal
Register on February 13, 2006 (71 FR 7449). That NPRM proposed to
require doing repetitive rotating probe inspections for any crack of
the rear spar internal angle and the left and right sides of the tee
fitting, and doing related investigative/corrective actions if
necessary. That NPRM also proposed to require modifying the holes in
the internal angle and tee fitting by cold expansion.
Comments
We provided the public the opportunity to participate in the
development of this AD. We received no comments on the NPRM or on the
determination of the cost to the public.
Conclusion
We have carefully reviewed the available data and determined that
air safety and the public interest require adopting the AD as proposed.
Costs of Compliance
The following table provides the estimated costs for U.S. operators
to comply with this AD. This AD will affect about 56 airplanes of U.S.
registry. Work hours and parts costs vary according to the
configuration of the airplane.
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Average
Action Work hour labor rate Parts Cost per airplane Fleet cost
per hour
----------------------------------------------------------------------------------------------------------------
Inspection................. 16-306 $65 $618-$18,489 $1,658-$38,379, $92,848-$2,149,224
per inspection , per inspection
cycle. cycle.
Modification............... 146-381 65 4,350-15,501 $13,840-$40,266... $775,040-$2,254,89
6.
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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 have 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 that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866;
(2) Is not a ``significant rule'' under 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. See the ADDRESSES
section for a location to examine the regulatory evaluation.
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 Federal Aviation Administration (FAA) amends Sec. 39.13 by
adding the following new airworthiness directive (AD):
2006-09-05 Airbus: Amendment 39-14575. Docket No. FAA-2006-23870;
Directorate Identifier 2005-NM-022-AD.
Effective Date
(a) This AD becomes effective June 7, 2006.
Affected ADs
(b) Certain requirements of this AD terminate certain
requirements of AD 98-26-01, amendment 39-10942.
Applicability
(c) This AD applies to all Airbus Model A310-203, -204, -221,
and -222 airplanes; and Model A310-304, -322, -324, and -325
airplanes; certificated in any category.
Unsafe Condition
(d) This AD results from full-scale fatigue tests, which
revealed cracks in the lower rear spar internal angle and tee
fitting. We are issuing this AD to detect and correct fatigue cracks
of the rear spar internal angle and tee fitting, which could lead to
the rupture of the internal angle, tee fitting, and rear spar, and
consequent reduced structural integrity of the wings.
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.
Initial and Repetitive Inspections
(f) At the later of the times specified in paragraphs (f)(1) and
(f)(2) of this AD, do a rotating probe inspection for any crack of
the rear spar internal angle located in the center wing box and do
all applicable related investigative and corrective actions in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A310-57-2047, Revision 06, dated July 13, 2004, except as
required by paragraphs (k), (l), and (m) of this AD. Do all
applicable related investigative and corrective actions before
further flight.
[[Page 25923]]
(1) Within 1,000 flight cycles or 1,600 flight hours after the
effective date of this AD, whichever is first.
(2) At the applicable time specified in Table 1 of this AD.
Table 1.--Initial Compliance Times for the Rear Spar Internal Angle
------------------------------------------------------------------------
Airplane model and configuration Threshold
------------------------------------------------------------------------
Model A310-203, -204, -221, and -222 Before the accumulation of
airplanes that are not modified by 10,300 total flight cycles or
Airbus Modifications 06672S6812 and 16,600 total flight hours,
07387S7974. whichever is first.
Model A310-203, -204, -221, and -222 Before the accumulation of
airplanes that are modified by Airbus 23,400 total flight cycles or
Modifications 06672S6812 and 37,700 total flight hours,
07387S7974 (modified either in whichever is first.
production or in accordance with
Airbus Service Bulletin A310-57-2035).
Model A310-304, -322, -324, and -325 Before the accumulation of
airplanes that are not modified by 9,500 total flight cycles or
Airbus Modifications 06672S6812 and 15,000 total flight hours,
07387S7974. whichever is first.
Model A310-304, -322, -324, and -325 Before the accumulation of
airplanes that are modified by Airbus 21,500 total flight cycles or
Modifications 06672S6812 and 34,000 total flight hours,
07387S7974 (modified either in whichever is first.
production or according to Airbus
Service Bulletin A310-57-2035).
------------------------------------------------------------------------
(g) Repeat the inspection specified in paragraph (f) of this AD
thereafter at the applicable time specified in paragraph (g)(1) or
(g)(2) of this AD.
(1) For Model A310-203, -204, -221, and -222 airplanes: Repeat
thereafter at intervals not to exceed 9,100 flight cycles or 14,650
flight hours, whichever is first.
(2) For Model A310-304, -322, -324, and -325 airplanes: Repeat
thereafter at intervals not to exceed 9,500 flight cycles or 15,000
flight hours, whichever is first.
(h) At the applicable time specified in Table 2 of this AD or
within 6 months after the effective date of this AD, whichever
occurs later: Do a rotating probe inspection for any crack of the
left and right sides of the tee fitting, and do all applicable
related investigative and corrective actions in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A310-57-2047,
Revision 06, dated July 13, 2004, except as required by paragraphs
(k), (l), and (m) of this AD. Do all applicable related
investigative and corrective actions before further flight.
Table 2.--Initial Compliance Times for the Tee Fitting
------------------------------------------------------------------------
Airplane model and configuration Threshold
------------------------------------------------------------------------
Model A310-203, -204, -221, and -222 Before the accumulation of
airplanes that are not modified by 21,600 total flight cycles or
Airbus Modification 06673S6813. 34,800 total flight hours,
whichever is first.
Model A310-203, -204, -221, and -222 Before the accumulation of
airplanes that are modified by Airbus 41,300 total flight cycles or
Modification 06673S6813 (modified 66,500 total flight hours,
either in production or in accordance whichever is first.
with Airbus Service Bulletin A310-57-
2035).
Model A310-304, -322, -324, and -325 Before the accumulation of
airplanes that are not modified by 17,100 total flight cycles or
Airbus Modification 06673S6813. 27,000 total flight hours,
whichever is first.
Model A310-304, -322, -324, and -325 Before the accumulation of
airplanes that are modified by Airbus 32,300 total flight cycles or
Modification 06673S6813 (modified 51,000 total flight hours,
either in production or in accordance whichever is first.
with Airbus Service Bulletin A310-57-
2035).
------------------------------------------------------------------------
(i) Repeat the inspection specified in paragraph (h) of this AD
thereafter at the applicable time specified in paragraph (i)(1) or
(i)(2) of this AD.
(1) For Model A310-203, -204, -221, and -222 airplanes: Repeat
thereafter at intervals not to exceed 10,800 flight cycles or 17,400
flight hours, whichever is first.
(2) For Model A310-304, -322, -324, and -325 airplanes: Repeat
thereafter at intervals not to exceed 8,800 flight cycles or 13,900
flight hours, whichever is first.
Modification
(j) For all airplanes except those that are modified by Airbus
Modifications 06672S6812, 06673S6813, and 07387S7974 in production:
Within 60 months after the effective date of this AD, modify the
holes in the internal angle and tee fitting and do all applicable
related investigative and corrective actions by accomplishing all
the actions specified in the Accomplishment Instructions of Airbus
Service Bulletin A310-57-2035, Revision 08, dated September 19,
2005, except as required by paragraph (k) of this AD. Do all
applicable related investigative and corrective actions before
further flight.
Contact the FAA
(k) Where Airbus Service Bulletin A310-57-2035, Revision 08,
dated September 19, 2005; and Airbus Service Bulletin A310-57-2047,
Revision 06, dated July 13, 2004; specify to contact the
manufacturer if certain cracks are found, before further flight,
repair those conditions according to a method approved by either the
Manager, International Branch, ANM-116, Transport Airplane
Directorate, FAA; or the Direction G[eacute]n[eacute]rale de
l'Aviation Civile (DGAC) (or its delegated agent).
Touch-and-Go Flights
(l) All touch-and-go landings must be counted in determining the
total number of flight cycles between consecutive inspections.
No Reporting Required
(m) Although Airbus Service Bulletin A310-57-2047, Revision 06,
dated July 13, 2004, specifies to submit certain information to the
manufacturer, this AD does not include that requirement.
Actions Accomplished According to Previous Issues of Service Bulletins
(n) Actions accomplished before the effective date of this AD in
accordance with Airbus Service Bulletin A310-57-2047, Revision 03,
dated November 26, 1997; Revision 04, dated March 5, 1999; or
Revision 05, dated August 3, 2000; are considered acceptable for
compliance with the corresponding actions specified in paragraphs
(f) through (i) of this AD.
(o) Actions accomplished before the effective date of this AD in
accordance with Airbus Service Bulletin A310-57-2035, Revision 1,
dated October 13, 1989; Revision 2, dated February 26, 1990;
Revision 3, dated May 23, 1990; Revision 4, dated April 15, 1991;
Revision 5, dated May 27, 1992; Revision 6, dated March 8, 1994; or
Revision 7, dated April 17, 1996; are considered acceptable for
compliance with the corresponding actions specified in paragraph (j)
of this AD.
[[Page 25924]]
Related AD
(p) Accomplishing the initial inspections specified in
paragraphs (f) and (g) of this AD terminates the requirements
specified in paragraph (o) of AD 98-26-01.
Alternative Methods of Compliance (AMOCs)
(q)(1) The Manager, International Branch, ANM-116, has the
authority to approve AMOCs for this AD, if requested in accordance
with the procedures found in 14 CFR 39.19.
(2) Before using any AMOC approved in accordance with 14 CFR
39.19 on any airplane to which the AMOC applies, notify the
appropriate principal inspector in the FAA Flight Standards
Certificate Holding District Office.
Related Information
(r) French airworthiness directive F-2005-001, dated January 5,
2005, also addresses the subject of this AD.
Material Incorporated by Reference
(s) You must use Airbus Service Bulletin A310-57-2047, Revision
06, dated July 13, 2004; and Airbus Service Bulletin A310-57-2035,
Revision 08, dated September 19, 2005; as applicable, to perform the
actions that are required by this AD, unless the AD specifies
otherwise. Airbus Service Bulletin A310-57-2047, Revision 06, dated
July 13, 2004, includes the following effective pages:
----------------------------------------------------------------------------------------------------------------
Page Nos. Revision level shown on page Date shown on page
----------------------------------------------------------------------------------------------------------------
1-8, 10-15, 17, 18, 22-25, 33, 37....... 06............................. July 13, 2004.
9, 16, 21, 30, 45, 46, 75-80, 95, 96.... 05............................. August 3, 2000.
19, 20, 27-29, 35, 36, 47-56, 61-74..... Original....................... February 26, 1991.
26, 31, 32, 34, 39-44, 59, 60, 81-94.... 04............................. March 5, 1999.
38...................................... 1.............................. January 4, 1996.
57, 58.................................. 2.............................. January 22, 1997.
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The Director of the Federal Register approved the incorporation
by reference of these documents in accordance with 5 U.S.C. 552(a)
and 1 CFR part 51. Contact Airbus, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France, for a copy of this service information.
You may review copies at the Docket Management Facility, U.S.
Department of Transportation, 400 Seventh Street, SW., Room PL-401,
Nassif Building, Washington, DC; on the Internet at https://
dms.dot.gov; or at the National Archives and Records Administration
(NARA). For information on the availability of this material at the
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 April 20, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 06-4052 Filed 5-2-06; 8:45 am]
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