Airworthiness Directives; Airbus Model A330 Airplanes and Model A340-200 and -300 Series Airplanes, 64881-64884 [E6-18471]
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64881
Rules and Regulations
Federal Register
Vol. 71, No. 214
Monday, November 6, 2006
This section of the FEDERAL REGISTER
contains regulatory documents having general
applicability and legal effect, most of which
are keyed to and codified in the Code of
Federal Regulations, which is published under
50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by
the Superintendent of Documents. Prices of
new books are listed in the first FEDERAL
REGISTER issue of each week.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–22812; Directorate
Identifier 2005–NM–134–AD; Amendment
39–14811; AD 2006–22–14]
RIN 2120–AA64
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
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AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for certain
Airbus Model A330 airplanes and
Model A340–200 and –300 series
airplanes. This AD requires repetitive
detailed inspections for cracking in the
aft web of support rib 6 between certain
bottom skin stringers on both wings;
high frequency eddy current inspections
for cracking of the attachment holes of
the fuel pipes, and repair if necessary.
This AD also provides for an optional
modification, which extends a certain
inspection threshold, and mandates, for
certain airplanes, a new modification of
support rib 6 on both wings, which ends
the repetitive inspection requirement.
This AD results from a report of
significant cracking found in the aft web
of support rib 6 on both wings. We are
issuing this AD to prevent cracking in
the aft web of support rib 6, which
could result in overloading of adjacent
ribs and the surrounding wing structure
and consequent reduced structural
integrity of the wing.
DATES: This AD becomes effective
December 11, 2006.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of December 11, 2006.
15:39 Nov 03, 2006
Tim
Backman, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 227–2797; fax (425) 227–1149.
FOR FURTHER INFORMATION CONTACT:
SUPPLEMENTARY INFORMATION:
Examining the Docket
Airworthiness Directives; Airbus Model
A330 Airplanes and Model A340–200
and –300 Series Airplanes
VerDate Aug<31>2005
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 the service information identified in
this AD.
ADDRESSES:
Jkt 211001
You may examine the 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 supplemental
notice of proposed rulemaking (NPRM)
to amend 14 CFR part 39 to include an
AD that would apply to certain Airbus
Model A330 airplanes and Model A340–
200 and –300 series airplanes. That
supplemental NPRM was published in
the Federal Register on May 26, 2006
(71 FR 30340). That supplemental
NPRM proposed to require repetitive
detailed inspections for cracking in the
aft web of support rib 6 between certain
bottom skin stringers on both wings;
high frequency eddy current inspections
for cracking of the attachment holes of
the fuel pipes, and repair if necessary.
The supplemental NPRM also provided
for an optional modification, which
would extend a certain inspection
threshold. For certain airplanes, the
supplemental NPRM proposed to
require a new modification of support
rib 6 on both wings, which would end
the repetitive inspection requirement.
The supplemental NPRM also proposed
to reduce the applicability in the
original NPRM.
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Comment
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comment received.
Request for Credit for Terminating
Modification
The Air Transport Association (ATA),
on behalf of its member Northwest
Airlines (NWA), asks that we recognize
Airbus Modification 54432 as
terminating action for the repetitive
inspection requirements in the
supplemental NPRM. NWA states that
this modification is being incorporated
by Airbus in production as the
‘‘production solution’’ for the fatigue
cracking problems. NWA adds that the
modification will be installed on its
Model A330 airplanes delivered with
manufacturer’s serial number 0778 and
subsequent.
We agree that Airbus Modification
54432 will be terminating action for the
referenced repetitive inspections.
However, that modification is not yet
approved by either the European
Aviation Safety Agency (EASA), which
is the airworthiness authority for the
European Union, or the FAA. The
modification is currently in the
approval process with the EASA. This
modification is the production solution
that installs a re-designed rib for
production airplanes with a new wing
build. Once the modification is
approved, the referenced EASA
airworthiness directive will be revised
to include this terminating action. After
the modification is approved and
available, operators may request an
alternative method of compliance for
installing the modification. We have not
changed the AD in this regard.
Explanation of Change to the
Supplemental NPRM
Airbus Service Bulletins A300–57–
3085 and A340–57–4093, both Revision
02, both dated September 29, 2005, were
included in the service information
section of the supplemental NPRM as
the sources of service information for
accomplishing the inspections.
However, Revision 02 was inadvertently
omitted from paragraph (l) of the
supplemental NPRM; we have added
Revision 02 to paragraph (l) accordingly.
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Federal Register / Vol. 71, No. 214 / Monday, November 6, 2006 / Rules and Regulations
Conclusion
We have carefully reviewed the
available data, including the comment
received, and determined that air safety
and the public interest require adopting
the AD with the change described
previously. This change will neither
increase the economic burden on any
operator nor increase the scope of the
AD.
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Costs of Compliance
This AD affects about 25 airplanes of
U.S. registry.
The inspections take about 4 work
hours per airplane, at an average labor
rate of $80 per work hour. Based on
these figures, the estimated cost of the
inspections for U.S. operators is $8,000,
or $320 per airplane, per inspection
cycle.
The modification of support rib 6 on
the left-hand wing takes about 38 work
hours per airplane, at an average labor
rate of $80 per work hour. Required
parts cost about $5,020 per airplane.
Based on these figures, the estimated
cost of this modification of the left-hand
wing on U.S. operators is $201,500, or
$8,060 per airplane.
The modification of support rib 6 on
the right-hand wing takes about 38 work
hours per airplane, at an average labor
rate of $80 per work hour. Required
parts cost about $5,020 per airplane.
Based on these figures, the estimated
cost of this modification of the righthand wing on U.S. operators is
$201,500, or $8,060 per airplane.
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
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15:39 Nov 03, 2006
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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
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 Federal Aviation
Administration (FAA) amends § 39.13
by adding the following new
airworthiness directive (AD):
I
2006–22–14 Airbus: Amendment 39–14811.
Docket No. FAA–2005–22812;
Directorate Identifier 2005–NM–134–AD.
Effective Date
(a) This AD becomes effective December
11, 2006.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Airbus Model A330
airplanes and Model A340–200 and –300
series airplanes, certificated in any category;
on which Airbus Modification 41114 or
44599 was done during production; except
those airplanes on which Airbus
Modification 53883 was done during
production.
Unsafe Condition
(d) This AD results from a report of
significant cracking found in the aft web of
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support rib 6 on both wings. We are issuing
this AD to prevent cracking in the aft web of
support rib 6, which could result in
overloading of adjacent ribs and the
surrounding wing structure and consequent
reduced structural integrity of the wing.
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.
Note 1: For the purposes of this AD, a
detailed inspection is: ‘‘An intensive
examination of a specific item, installation,
or assembly to detect damage, failure, or
irregularity. Available lighting is normally
supplemented with a direct source of good
lighting at an intensity deemed appropriate.
Inspection aids such as mirror, magnifying
lenses, etc., may be necessary. Surface
cleaning and elaborate procedures may be
required.’’
Repetitive Inspections
(f) For Model A330 series airplanes on
which Airbus Modification 53882 was not
done during production: At the applicable
time specified in paragraph (f)(1), (f)(2), or
(f)(3) of this AD, perform a detailed
inspection for cracking in the aft web of
support rib 6 between bottom skin stringers
18 and 20 on both wings, and high frequency
eddy current inspections for cracking of the
attachment holes of the fuel pipe and fuel
pipe mounting, by doing all the actions in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A330–
57–3085, Revision 02, dated September 29,
2005. If no crack is found during the initial
inspections, repeat the inspections thereafter
at intervals not to exceed 8,000 flight cycles
or 25,000 flight hours, whichever is first,
until the terminating action specified in
paragraph (n) of this AD is done. If any crack
is found during any inspection, repair as
specified in paragraph (k) of this AD, or
before further flight do the terminating action
specified in paragraph (n) of this AD.
(1) For airplanes that have accumulated
7,999 or fewer total flight cycles, and 24,999
or fewer total flight hours, as of the effective
date of this AD: Do the inspections at the
later of the times specified in paragraphs
(f)(1)(i) and (f)(1)(ii) of this AD.
(i) Before the accumulation of 8,000 total
flight cycles or 25,000 total flight hours,
whichever is first.
(ii) Within 8 months after the effective date
of this AD.
(2) For airplanes that have accumulated
8,000 or more total flight cycles, but fewer
than 10,000 total flight cycles; or 25,000 or
more total flight hours, but fewer than 30,000
total flight hours; as of the effective date of
this AD: Do the inspections at the later of the
times specified in paragraphs (f)(2)(i) and
(f)(2)(ii) of this AD.
(i) Before the accumulation of 10,000 total
flight cycles or 30,000 total flight hours,
whichever is first.
(ii) Within 8 months after the effective date
of this AD.
(3) For airplanes that have accumulated
10,000 or more total flight cycles or 30,000
or more total flight hours as of the effective
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Federal Register / Vol. 71, No. 214 / Monday, November 6, 2006 / Rules and Regulations
date of this AD: Do the inspections within 3
months after the effective date of this AD.
(g) For Model A330 series airplanes on
which Airbus Modification 53882 was done
during production or on which Airbus
Service Bulletin A330–57–3087, dated
February 15, 2005, or Revision 01, dated
September 22, 2005, has been done: Perform
the applicable inspections required by
paragraph (f) of this AD at the earliest of the
initial inspection thresholds specified in
Figure 4, Sheet 1, ‘‘Inspection Flow Chart’’ of
Airbus Service Bulletin A330–57–3085,
Revision 02, dated September 29, 2005; or
within 6 months after the effective date of
this AD, whichever is later. Repeat the
inspections required by paragraph (f) of this
AD at the time specified in paragraph (f) of
this AD, until the terminating action
specified in paragraph (n) of this AD is done.
(h) For Model A340 series airplanes on
which Airbus Modification 53882 was not
done during production: Perform the
inspections required by paragraph (f) of this
AD at the applicable time specified in
paragraph (h)(1), (h)(2), or (h)(3) of this AD.
Perform the inspections by doing all the
actions in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A340–57–4093, Revision 02,
dated September 29, 2005. Repeat the
inspections thereafter at intervals not to
exceed 8,000 flight cycles or 30,200 flight
hours, whichever is first, until the
terminating action specified in paragraph (n)
of this AD is done.
(1) For airplanes that have accumulated
7,999 or fewer total flight cycles, and 30,199
or fewer total flight hours, as of the effective
date of this AD: Do the inspections at the
later of the times specified in paragraphs
(h)(1)(i) and (h)(1)(ii) of this AD.
(i) Before the accumulation of 8,000 total
flight cycles or 30,200 total flight hours,
whichever is first.
(ii) Within 8 months after the effective date
of this AD.
(2) For airplanes that have accumulated
8,000 or more total flight cycles, but fewer
than 10,000 total flight cycles; or 30,200 or
more total flight cycles, but fewer than
43,700 total flight hours, as of the effective
date of this AD: Do the inspections at the
later of the times specified in paragraphs
(h)(2)(i) and (h)(2)(ii) of this AD.
(i) Before the accumulation of 10,000 total
flight cycles or 43,700 total flight hours,
whichever is first.
(ii) Within 8 months after the effective date
of this AD.
(3) For airplanes that have accumulated
10,000 or more total flight cycles or 43,700
or more total flight hours as of the effective
date of this AD: Do the inspections within 3
months after the effective date of this AD.
(i) For Model A340 series airplanes on
which Airbus Modification 53882 was done
during production or on which Airbus
Service Bulletin A340–57–4095, dated
February 15, 2005, or Revision 01, dated
September 22, 2005, has been done: Perform
the applicable inspections required by
paragraph (f) of this AD at the earliest of the
initial inspection thresholds specified in
Figure 4, Sheet 1, ‘‘Inspection Flow Chart’’ of
Airbus Service Bulletin A340–57–4093,
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15:39 Nov 03, 2006
Jkt 211001
Revision 02, dated September 29, 2005; or
within 6 months after the effective date of
this AD, whichever is later. Repeat the
inspections required by paragraph (f) of this
AD at the time specified in paragraph (h) of
this AD, until the terminating action
specified in paragraph (n) of this AD is done.
Inspections Accomplished According to
Previous Issue of Service Bulletins
(j) Inspections accomplished before the
effective date of this AD according to Airbus
All Operator Telex A330–57A3085 or A340–
57A4093, each dated December 15, 2004; or
Airbus Service Bulletin A330–57–3085 or
A340–57–4093, each Revision 01, each dated
March 25, 2005; are considered acceptable
for compliance with the corresponding
inspections specified in this AD.
Repair
(k) If any cracking is found during any
inspection required by this AD: Before
further flight, either repair and get a schedule
for subsequent inspections, according to a
method approved by either the Manager,
International Branch, ANM–116, Transport
Airplane Directorate, FAA; or the European
Aviation Safety Agency (EASA) (or its
delegated agent); or accomplish the
terminating action specified in paragraph (n)
of this AD.
Optional Modification
(l) Accomplishing the modification of the
fuel pipe connector and the fastener holes of
support rib 6 on both wings by doing all the
actions specified in the Accomplishment
Instructions of Airbus Service Bulletin A330–
57–3087 or A340–57–4095, each dated
February 15, 2005, or Revision 01, each dated
September 22, 2005, as applicable, extends
the interval for the next inspection to the
applicable post-modification inspection
threshold specified in Figure 4, Sheet 1,
‘‘Inspection Flow Chart’’ of Airbus Service
Bulletins A330–57–3085 or A340–57–4093,
each Revision 02, each dated September 29,
2005, as applicable. After accomplishing that
inspection, repeat the applicable inspections
required by paragraph (f) or (h) of this AD at
the applicable repetitive inspection interval
specified in Figure 4 of the Accomplishment
Instructions of the applicable service
bulletin, until the terminating action
specified in paragraph (n) of this AD is done.
Hard or Overweight Landing
(m) For Model A330 series airplanes with
8,000 or more total flight cycles or 25,000 or
more total flight hours, and Model A340
series airplanes with 8,000 or more total
flight cycles or 30,200 or more total flight
hours that have not been modified in
accordance with paragraph (n) of this AD:
Before further flight after any hard or
overweight landing of the airplane,
accomplish the applicable follow-on
inspections and any applicable corrective
actions according to a method approved by
either the Manager, International Branch,
ANM–116; or the EASA (or its delegated
agent). Accomplishing the inspections in
Chapter 05–51–11, titled ‘‘Inspection After
Hard/Overweight Landing—Inspection/
Check,’’ dated April 1, 2005, or July 1, 2006,
of the Airbus A330 Aircraft Maintenance
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64883
Manual (AMM); or Chapter 05–51–11, titled
‘‘Inspection After Hard/Overweight
Landing—Inspection/Check,’’ dated July 1,
2006, of the Airbus A340 AMM; as
applicable; and Airbus A330/A340 Technical
Disposition (TD) TD/J1/S3/00608/2005, Issue
C, dated April 26, 2005, titled ‘‘Inspections
following hard landing, both wings,’’ are
approved methods. Operators can obtain the
TD from Airbus.
Terminating Modification
(n) For airplanes on which support rib 6 on
both wings has not been repaired in
accordance with paragraph (k) of this AD:
Within 60 months after the effective date of
this AD, modify the fuel pipe connector and
the fastener holes of support rib 6 on both
wings by doing all the actions specified in
the Accomplishment Instructions of Airbus
Service Bulletin A330–57–3088 or A340–57–
4096, each including Appendix 01, each
dated September 21, 2005, as applicable.
Accomplishing the modification in this
paragraph ends the repetitive inspections
required by this AD. Repair of support rib 6
on both wings before the effective date of this
AD using Airbus A330/A340 Repair
Instruction R572–57023, Issue D, dated May
11, 2005; or R572–57026, Issue C, dated
December 2005; as applicable, ends the
repetitive inspections required by this AD.
Alternative Methods of Compliance
(AMOCs)
(o)(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
(p) French airworthiness directives F–
2006–008 and F–2006–009, both dated
January 4, 2006, also address the subject of
this AD.
Material Incorporated by Reference
(q) You must use the applicable Airbus
service bulletins specified in Table 1 of this
AD to perform the actions that are required
by this AD, unless the AD specifies
otherwise. 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.
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Federal Register / Vol. 71, No. 214 / Monday, November 6, 2006 / Rules and Regulations
TABLE 1.—MATERIAL INCORPORATED BY REFERENCE
Airbus Service Bulletin
Revision level
Date
A330–57–3085 ....................................................................................................................................
A330–57–3087 ....................................................................................................................................
A330–57–3087 ....................................................................................................................................
A330–57–3088, including Appendix 01 ..............................................................................................
A340–57–4093 ....................................................................................................................................
A340–57–4095 ....................................................................................................................................
A340–57–4095 ....................................................................................................................................
A340–57–4096, including Appendix 01 ..............................................................................................
02 .............................
Original ....................
01 .............................
Original ....................
02 .............................
Original ....................
01 .............................
Original ....................
September 29, 2005.
February 15, 2005.
September 22, 2005.
September 21, 2005.
September 29, 2005.
February 15, 2005.
September 22, 2005.
September 21, 2005.
Issued in Renton, Washington, on October
25, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. E6–18471 Filed 11–3–06; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–23921; Directorate
Identifier 2005–NM–205–AD; Amendment
39–14812; AD 2006–22–15]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 747 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
The FAA is superseding an
existing airworthiness directive (AD),
which applies to all Boeing Model 747
series airplanes. That AD currently
requires repetitive inspections for
cracking of the top and side panel webs
and panel stiffeners of the nose wheel
well (NWW), and corrective actions if
necessary. This new AD reduces the
interval for certain repetitive
inspections and removes a certain
optional inspection. This new AD also
requires replacing the NWW side and
top panels with new panels, which
terminates the repetitive inspections.
This AD results from the development
of a new modification. We are issuing
this AD to prevent fatigue cracks in the
top and side panel webs and stiffeners
of the NWW, which could compromise
the structural integrity of the NWW and
could lead to the rapid decompression
of the airplane.
DATES: This AD becomes effective
December 11, 2006.
The Director of the Federal Register
approved the incorporation by reference
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SUMMARY:
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15:39 Nov 03, 2006
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of a certain publication listed in the AD
as of December 11, 2006.
On May 10, 2005 (70 FR 21141, April
25, 2005), the Director of the Federal
Register approved the incorporation by
reference of Boeing Alert Service
Bulletin 747–53A2465, Revision 4,
dated February 24, 2005.
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 Boeing Commercial
Airplanes, P.O. Box 3707, Seattle,
Washington 98124–2207, for service
information identified in this AD.
FOR FURTHER INFORMATION CONTACT: Nick
Kusz, Airframe Branch, ANM–120S,
FAA, Seattle Aircraft Certification
Office, 1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 917–6432; fax (425) 917–6590.
SUPPLEMENTARY INFORMATION:
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
supersedes AD 2005–09–02, amendment
39–14070 (70 FR 21141, April 25, 2005).
[A correction of that AD was published
in the Federal Register on May 25, 2005
(70 FR 29940).] The existing AD applies
to all Boeing Model 747 series airplanes.
That NPRM was published in the
Federal Register on February 15, 2006
(71 FR 7883). That NPRM proposed to
continue to require repetitive
inspections for cracking of the top and
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side panel webs and panel stiffeners of
the nose wheel well (NWW), and
corrective actions if necessary. That
NPRM also proposed to reduce the
interval for certain repetitive
inspections and remove a certain
optional inspection. That NPRM also
proposed to require replacing the NWW
side and top panels with new panels,
which would terminate the repetitive
inspections.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comments that have
been received on the NPRM.
Support for the NPRM
Boeing, the airplane manufacturer,
agrees with the contents of the NPRM.
Request To Remove Actions for Group
2 Airplanes or Extend Compliance
Time
The Air Transport Association (ATA),
on behalf of one of its members,
Northwest Airlines (NWA), requests that
either the proposed requirement for
terminating action for Group 2 airplanes
be removed from the NPRM or the
compliance time for doing the
termination action be extended from
four years to six years. The ATA notes
that there are no service instructions for
the terminating action for Group 2
airplanes. The ATA also states that
extending the compliance time will
allow the development of the service
instructions and an assessment of the
requirement’s impact. NWA adds that it
has not experienced extensive cracking
that would warrant serious
consideration or justification to mandate
the terminating action (replacement of
the NWW side and top panels). NWA
also states that it would be very difficult
to accomplish the replacement without
a service bulletin.
We agree with the commenter’s
concern regarding lack of availability of
service instructions for Group 2
airplanes; however, we do not consider
that removing the terminating action or
delaying this action until after the
E:\FR\FM\06NOR1.SGM
06NOR1
]]>Agencies
[Federal Register Volume 71, Number 214 (Monday, November 6, 2006)]
[Rules and Regulations]
[Pages 64881-64884]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-18471]
========================================================================
Rules and Regulations
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains regulatory documents
having general applicability and legal effect, most of which are keyed
to and codified in the Code of Federal Regulations, which is published
under 50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by the Superintendent of Documents.
Prices of new books are listed in the first FEDERAL REGISTER issue of each
week.
========================================================================
Federal Register / Vol. 71, No. 214 / Monday, November 6, 2006 /
Rules and Regulations
[[Page 64881]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-22812; Directorate Identifier 2005-NM-134-AD;
Amendment 39-14811; AD 2006-22-14]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A330 Airplanes and Model
A340-200 and -300 Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain Airbus Model A330 airplanes and Model A340-200 and -300 series
airplanes. This AD requires repetitive detailed inspections for
cracking in the aft web of support rib 6 between certain bottom skin
stringers on both wings; high frequency eddy current inspections for
cracking of the attachment holes of the fuel pipes, and repair if
necessary. This AD also provides for an optional modification, which
extends a certain inspection threshold, and mandates, for certain
airplanes, a new modification of support rib 6 on both wings, which
ends the repetitive inspection requirement. This AD results from a
report of significant cracking found in the aft web of support rib 6 on
both wings. We are issuing this AD to prevent cracking in the aft web
of support rib 6, which could result in overloading of adjacent ribs
and the surrounding wing structure and consequent reduced structural
integrity of the wing.
DATES: This AD becomes effective December 11, 2006.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of December 11,
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 the 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 98057-3356; telephone (425)
227-2797; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Examining the Docket
You may examine the 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 supplemental notice of proposed rulemaking (NPRM)
to amend 14 CFR part 39 to include an AD that would apply to certain
Airbus Model A330 airplanes and Model A340-200 and -300 series
airplanes. That supplemental NPRM was published in the Federal Register
on May 26, 2006 (71 FR 30340). That supplemental NPRM proposed to
require repetitive detailed inspections for cracking in the aft web of
support rib 6 between certain bottom skin stringers on both wings; high
frequency eddy current inspections for cracking of the attachment holes
of the fuel pipes, and repair if necessary. The supplemental NPRM also
provided for an optional modification, which would extend a certain
inspection threshold. For certain airplanes, the supplemental NPRM
proposed to require a new modification of support rib 6 on both wings,
which would end the repetitive inspection requirement. The supplemental
NPRM also proposed to reduce the applicability in the original NPRM.
Comment
We provided the public the opportunity to participate in the
development of this AD. We have considered the comment received.
Request for Credit for Terminating Modification
The Air Transport Association (ATA), on behalf of its member
Northwest Airlines (NWA), asks that we recognize Airbus Modification
54432 as terminating action for the repetitive inspection requirements
in the supplemental NPRM. NWA states that this modification is being
incorporated by Airbus in production as the ``production solution'' for
the fatigue cracking problems. NWA adds that the modification will be
installed on its Model A330 airplanes delivered with manufacturer's
serial number 0778 and subsequent.
We agree that Airbus Modification 54432 will be terminating action
for the referenced repetitive inspections. However, that modification
is not yet approved by either the European Aviation Safety Agency
(EASA), which is the airworthiness authority for the European Union, or
the FAA. The modification is currently in the approval process with the
EASA. This modification is the production solution that installs a re-
designed rib for production airplanes with a new wing build. Once the
modification is approved, the referenced EASA airworthiness directive
will be revised to include this terminating action. After the
modification is approved and available, operators may request an
alternative method of compliance for installing the modification. We
have not changed the AD in this regard.
Explanation of Change to the Supplemental NPRM
Airbus Service Bulletins A300-57-3085 and A340-57-4093, both
Revision 02, both dated September 29, 2005, were included in the
service information section of the supplemental NPRM as the sources of
service information for accomplishing the inspections. However,
Revision 02 was inadvertently omitted from paragraph (l) of the
supplemental NPRM; we have added Revision 02 to paragraph (l)
accordingly.
[[Page 64882]]
Conclusion
We have carefully reviewed the available data, including the
comment received, and determined that air safety and the public
interest require adopting the AD with the change described previously.
This change will neither increase the economic burden on any operator
nor increase the scope of the AD.
Costs of Compliance
This AD affects about 25 airplanes of U.S. registry.
The inspections take about 4 work hours per airplane, at an average
labor rate of $80 per work hour. Based on these figures, the estimated
cost of the inspections for U.S. operators is $8,000, or $320 per
airplane, per inspection cycle.
The modification of support rib 6 on the left-hand wing takes about
38 work hours per airplane, at an average labor rate of $80 per work
hour. Required parts cost about $5,020 per airplane. Based on these
figures, the estimated cost of this modification of the left-hand wing
on U.S. operators is $201,500, or $8,060 per airplane.
The modification of support rib 6 on the right-hand wing takes
about 38 work hours per airplane, at an average labor rate of $80 per
work hour. Required parts cost about $5,020 per airplane. Based on
these figures, the estimated cost of this modification of the right-
hand wing on U.S. operators is $201,500, or $8,060 per airplane.
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):
2006-22-14 Airbus: Amendment 39-14811. Docket No. FAA-2005-22812;
Directorate Identifier 2005-NM-134-AD.
Effective Date
(a) This AD becomes effective December 11, 2006.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Airbus Model A330 airplanes and Model
A340-200 and -300 series airplanes, certificated in any category; on
which Airbus Modification 41114 or 44599 was done during production;
except those airplanes on which Airbus Modification 53883 was done
during production.
Unsafe Condition
(d) This AD results from a report of significant cracking found
in the aft web of support rib 6 on both wings. We are issuing this
AD to prevent cracking in the aft web of support rib 6, which could
result in overloading of adjacent ribs and the surrounding wing
structure and consequent reduced structural integrity of the wing.
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.
Note 1: For the purposes of this AD, a detailed inspection is:
``An intensive examination of a specific item, installation, or
assembly to detect damage, failure, or irregularity. Available
lighting is normally supplemented with a direct source of good
lighting at an intensity deemed appropriate. Inspection aids such as
mirror, magnifying lenses, etc., may be necessary. Surface cleaning
and elaborate procedures may be required.''
Repetitive Inspections
(f) For Model A330 series airplanes on which Airbus Modification
53882 was not done during production: At the applicable time
specified in paragraph (f)(1), (f)(2), or (f)(3) of this AD, perform
a detailed inspection for cracking in the aft web of support rib 6
between bottom skin stringers 18 and 20 on both wings, and high
frequency eddy current inspections for cracking of the attachment
holes of the fuel pipe and fuel pipe mounting, by doing all the
actions in accordance with the Accomplishment Instructions of Airbus
Service Bulletin A330-57-3085, Revision 02, dated September 29,
2005. If no crack is found during the initial inspections, repeat
the inspections thereafter at intervals not to exceed 8,000 flight
cycles or 25,000 flight hours, whichever is first, until the
terminating action specified in paragraph (n) of this AD is done. If
any crack is found during any inspection, repair as specified in
paragraph (k) of this AD, or before further flight do the
terminating action specified in paragraph (n) of this AD.
(1) For airplanes that have accumulated 7,999 or fewer total
flight cycles, and 24,999 or fewer total flight hours, as of the
effective date of this AD: Do the inspections at the later of the
times specified in paragraphs (f)(1)(i) and (f)(1)(ii) of this AD.
(i) Before the accumulation of 8,000 total flight cycles or
25,000 total flight hours, whichever is first.
(ii) Within 8 months after the effective date of this AD.
(2) For airplanes that have accumulated 8,000 or more total
flight cycles, but fewer than 10,000 total flight cycles; or 25,000
or more total flight hours, but fewer than 30,000 total flight
hours; as of the effective date of this AD: Do the inspections at
the later of the times specified in paragraphs (f)(2)(i) and
(f)(2)(ii) of this AD.
(i) Before the accumulation of 10,000 total flight cycles or
30,000 total flight hours, whichever is first.
(ii) Within 8 months after the effective date of this AD.
(3) For airplanes that have accumulated 10,000 or more total
flight cycles or 30,000 or more total flight hours as of the
effective
[[Page 64883]]
date of this AD: Do the inspections within 3 months after the
effective date of this AD.
(g) For Model A330 series airplanes on which Airbus Modification
53882 was done during production or on which Airbus Service Bulletin
A330-57-3087, dated February 15, 2005, or Revision 01, dated
September 22, 2005, has been done: Perform the applicable
inspections required by paragraph (f) of this AD at the earliest of
the initial inspection thresholds specified in Figure 4, Sheet 1,
``Inspection Flow Chart'' of Airbus Service Bulletin A330-57-3085,
Revision 02, dated September 29, 2005; or within 6 months after the
effective date of this AD, whichever is later. Repeat the
inspections required by paragraph (f) of this AD at the time
specified in paragraph (f) of this AD, until the terminating action
specified in paragraph (n) of this AD is done.
(h) For Model A340 series airplanes on which Airbus Modification
53882 was not done during production: Perform the inspections
required by paragraph (f) of this AD at the applicable time
specified in paragraph (h)(1), (h)(2), or (h)(3) of this AD. Perform
the inspections by doing all the actions in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A340-57-4093,
Revision 02, dated September 29, 2005. Repeat the inspections
thereafter at intervals not to exceed 8,000 flight cycles or 30,200
flight hours, whichever is first, until the terminating action
specified in paragraph (n) of this AD is done.
(1) For airplanes that have accumulated 7,999 or fewer total
flight cycles, and 30,199 or fewer total flight hours, as of the
effective date of this AD: Do the inspections at the later of the
times specified in paragraphs (h)(1)(i) and (h)(1)(ii) of this AD.
(i) Before the accumulation of 8,000 total flight cycles or
30,200 total flight hours, whichever is first.
(ii) Within 8 months after the effective date of this AD.
(2) For airplanes that have accumulated 8,000 or more total
flight cycles, but fewer than 10,000 total flight cycles; or 30,200
or more total flight cycles, but fewer than 43,700 total flight
hours, as of the effective date of this AD: Do the inspections at
the later of the times specified in paragraphs (h)(2)(i) and
(h)(2)(ii) of this AD.
(i) Before the accumulation of 10,000 total flight cycles or
43,700 total flight hours, whichever is first.
(ii) Within 8 months after the effective date of this AD.
(3) For airplanes that have accumulated 10,000 or more total
flight cycles or 43,700 or more total flight hours as of the
effective date of this AD: Do the inspections within 3 months after
the effective date of this AD.
(i) For Model A340 series airplanes on which Airbus Modification
53882 was done during production or on which Airbus Service Bulletin
A340-57-4095, dated February 15, 2005, or Revision 01, dated
September 22, 2005, has been done: Perform the applicable
inspections required by paragraph (f) of this AD at the earliest of
the initial inspection thresholds specified in Figure 4, Sheet 1,
``Inspection Flow Chart'' of Airbus Service Bulletin A340-57-4093,
Revision 02, dated September 29, 2005; or within 6 months after the
effective date of this AD, whichever is later. Repeat the
inspections required by paragraph (f) of this AD at the time
specified in paragraph (h) of this AD, until the terminating action
specified in paragraph (n) of this AD is done.
Inspections Accomplished According to Previous Issue of Service
Bulletins
(j) Inspections accomplished before the effective date of this
AD according to Airbus All Operator Telex A330-57A3085 or A340-
57A4093, each dated December 15, 2004; or Airbus Service Bulletin
A330-57-3085 or A340-57-4093, each Revision 01, each dated March 25,
2005; are considered acceptable for compliance with the
corresponding inspections specified in this AD.
Repair
(k) If any cracking is found during any inspection required by
this AD: Before further flight, either repair and get a schedule for
subsequent inspections, according to a method approved by either the
Manager, International Branch, ANM-116, Transport Airplane
Directorate, FAA; or the European Aviation Safety Agency (EASA) (or
its delegated agent); or accomplish the terminating action specified
in paragraph (n) of this AD.
Optional Modification
(l) Accomplishing the modification of the fuel pipe connector
and the fastener holes of support rib 6 on both wings by doing all
the actions specified in the Accomplishment Instructions of Airbus
Service Bulletin A330-57-3087 or A340-57-4095, each dated February
15, 2005, or Revision 01, each dated September 22, 2005, as
applicable, extends the interval for the next inspection to the
applicable post-modification inspection threshold specified in
Figure 4, Sheet 1, ``Inspection Flow Chart'' of Airbus Service
Bulletins A330-57-3085 or A340-57-4093, each Revision 02, each dated
September 29, 2005, as applicable. After accomplishing that
inspection, repeat the applicable inspections required by paragraph
(f) or (h) of this AD at the applicable repetitive inspection
interval specified in Figure 4 of the Accomplishment Instructions of
the applicable service bulletin, until the terminating action
specified in paragraph (n) of this AD is done.
Hard or Overweight Landing
(m) For Model A330 series airplanes with 8,000 or more total
flight cycles or 25,000 or more total flight hours, and Model A340
series airplanes with 8,000 or more total flight cycles or 30,200 or
more total flight hours that have not been modified in accordance
with paragraph (n) of this AD: Before further flight after any hard
or overweight landing of the airplane, accomplish the applicable
follow-on inspections and any applicable corrective actions
according to a method approved by either the Manager, International
Branch, ANM-116; or the EASA (or its delegated agent). Accomplishing
the inspections in Chapter 05-51-11, titled ``Inspection After Hard/
Overweight Landing--Inspection/Check,'' dated April 1, 2005, or July
1, 2006, of the Airbus A330 Aircraft Maintenance Manual (AMM); or
Chapter 05-51-11, titled ``Inspection After Hard/Overweight
Landing--Inspection/Check,'' dated July 1, 2006, of the Airbus A340
AMM; as applicable; and Airbus A330/A340 Technical Disposition (TD)
TD/J1/S3/00608/2005, Issue C, dated April 26, 2005, titled
``Inspections following hard landing, both wings,'' are approved
methods. Operators can obtain the TD from Airbus.
Terminating Modification
(n) For airplanes on which support rib 6 on both wings has not
been repaired in accordance with paragraph (k) of this AD: Within 60
months after the effective date of this AD, modify the fuel pipe
connector and the fastener holes of support rib 6 on both wings by
doing all the actions specified in the Accomplishment Instructions
of Airbus Service Bulletin A330-57-3088 or A340-57-4096, each
including Appendix 01, each dated September 21, 2005, as applicable.
Accomplishing the modification in this paragraph ends the repetitive
inspections required by this AD. Repair of support rib 6 on both
wings before the effective date of this AD using Airbus A330/A340
Repair Instruction R572-57023, Issue D, dated May 11, 2005; or R572-
57026, Issue C, dated December 2005; as applicable, ends the
repetitive inspections required by this AD.
Alternative Methods of Compliance (AMOCs)
(o)(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
(p) French airworthiness directives F-2006-008 and F-2006-009,
both dated January 4, 2006, also address the subject of this AD.
Material Incorporated by Reference
(q) You must use the applicable Airbus service bulletins
specified in Table 1 of this AD to perform the actions that are
required by this AD, unless the AD specifies otherwise. 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.
[[Page 64884]]
Table 1.--Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
Airbus Service Bulletin Revision level Date
----------------------------------------------------------------------------------------------------------------
A330-57-3085.......................... 02................................. September 29, 2005.
A330-57-3087.......................... Original........................... February 15, 2005.
A330-57-3087.......................... 01................................. September 22, 2005.
A330-57-3088, including Appendix 01... Original........................... September 21, 2005.
A340-57-4093.......................... 02................................. September 29, 2005.
A340-57-4095.......................... Original........................... February 15, 2005.
A340-57-4095.......................... 01................................. September 22, 2005.
A340-57-4096, including Appendix 01... Original........................... September 21, 2005.
----------------------------------------------------------------------------------------------------------------
Issued in Renton, Washington, on October 25, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E6-18471 Filed 11-3-06; 8:45 am]
BILLING CODE 4910-13-P
