[Federal Register: October 27, 2005 (Volume 70, Number 207)]
[Proposed Rules]
[Page 61927-61930]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr27oc05-14]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-22812; Directorate Identifier 2005-NM-134-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A330-200, A330-300, A340-
200, and A340-300 Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for certain Airbus Model A330-200, A330-300, A340-200, and A340-300
series airplanes. This proposed AD would 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. This proposed AD would also provide for
an optional modification, which would extend a certain inspection
threshold. This proposed AD results from a report of significant
cracking found in the aft web of support rib 6 on both wings. We are
proposing 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: We must receive comments on this proposed AD by November 28,
2005.
ADDRESSES: Use one of the following addresses to submit comments on
this proposed AD.
DOT Docket Web site: Go to http://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to http://www.regulations.gov
and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility, U.S. Department of
Transportation, 400 Seventh Street SW., Nassif Building, Room PL-401,
Washington, DC 20590.
Fax: (202) 493-2251.
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street SW., Washington, DC, between 9 a.m.
and 5 p.m., Monday through Friday, except Federal holidays.
Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex,
France, for the service information identified in this proposed AD.
FOR FURTHER INFORMATION CONTACT: Tim Backman, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-2797; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any relevant written data, views, or
arguments regarding this proposed AD. Include the docket number ``FAA-
2005-22812; Directorate Identifier 2005-NM-134-AD'' at the beginning of
your comments. We specifically invite comments on the overall
regulatory, economic, environmental, and energy aspects of the proposed
AD. We will consider all comments received by the closing date and may
amend the proposed AD in light of those comments.
We will post all comments we receive, without change, to http://dms.dot.gov
, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact with FAA
personnel concerning this proposed AD. Using the search function of
that Web site, anyone can find and read the comments in any of our
dockets, including the name of the individual who sent the comment (or
signed the comment on behalf of an association, business, labor union,
etc.). You may review DOT's complete Privacy Act Statement in the
Federal Register published on April 11, 2000 (65 FR 19477-78), or you
may visit http://dms.dot.gov.
Examining the Docket
You may examine the AD docket on the Internet at http://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 DOT
street address stated in the ADDRESSES section. Comments will be
available in the AD docket shortly after the Docket Management System
receives them.
Discussion
The Direction G[eacute]n[eacute]rale de l'Aviation Civile (DGAC),
which is the airworthiness authority for France, notified us that an
unsafe condition may exist on certain Airbus Model A330-200, A330-300,
A340-200, and A340-300 series airplanes. The DGAC advises that a report
was received indicating significant cracking in the aft web of support
rib 6 on the left and right wings on a Model A330 series airplane. When
the cracking was found, during an 8C-check, the airplane had
accumulated 10,441 total flight cycles and 40,153 total flight hours.
The cracking was located in the lower part of the rib 6 aft hole
between bottom skin stringers 18 and 20. The cracking extended from the
fuel pipe fastener holes to the lower edge of the rib 6 hole and into
the refuel pipe hole where the cracking had gone through the full
thickness of the rib. Subsequent inspections on several Model A330 and
A340 series airplanes revealed similar cracking in the same area. These
conditions, if not corrected, could result in overloading of adjacent
ribs and the surrounding wing structure and consequent reduced
structural integrity of the wing.
Relevant Service Information
Airbus has issued Service Bulletins A330-57-3085 (for Model A330
series airplanes) and A340-57-4093 (for Model A340 series airplanes),
both Revision 01, both dated March 25, 2005. The service bulletins
describe procedures for detailed inspections 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 (HFEC) inspections for cracking
[[Page 61928]]
of the attachment holes of the fuel pipe (including a rototest
inspection of the attachment holes of the fuel pipe mounting). The
service bulletins also recommend contacting the manufacturer for repair
instructions if any cracking is found, and reporting inspection
information to the manufacturer. If no cracking is found, the service
bulletins specify accomplishing the optional modification specified in
Service Bulletin A330-57-3087 or A340-57-4095, as applicable.
The compliance thresholds for the initial inspections specified in
Service Bulletin A330-57-3085 range from between 8,000 and 19,200
flight cycles or between 25,000 and 57,800 flight hours. The compliance
thresholds for the initial inspections specified in Service Bulletin
A340-57-4093 range from between 8,000 and 12,200 flight cycles or
between 30,200 and 53,500 flight hours.
Airbus has also issued Service Bulletins A330-57-3087 (for Model
A330 series airplanes) and A340-57-4095 (for Model A340 series
airplanes), both dated February 15, 2005. The service bulletins
describe procedures for modifying the fuel pipe connector and the
fastener holes of support rib 6. The modification includes, among other
things, enlarging and cold expanding certain attachment holes of the
fuel pipe connector, installing interference bolts, and a HFEC
inspection (rotating probe test) of the fastener holes for cracking. If
no cracking is found during the inspections specified in Service
Bulletin A330-57-3085 or A340-57-4093, this optional modification may
be done.
The DGAC mandated the service information and issued French
airworthiness directives F-2005-071 and F-2005-072, both dated April
27, 2005, to ensure the continued airworthiness of these airplanes in
France.
FAA's Determination and Requirements of the Proposed AD
These airplane models are manufactured in France and are type
certificated for operation in the United States under the provisions of
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and
the applicable bilateral airworthiness agreement. Pursuant to this
bilateral airworthiness agreement, the DGAC has kept the FAA informed
of the situation described above. We have examined the DGAC's findings,
evaluated all pertinent information, and determined that we need to
issue an AD for airplanes of this type design that are certificated for
operation in the United States.
Therefore, we are proposing this AD, which would require
accomplishing the actions specified in the service information
described previously, except as discussed under Differences Among the
Proposed AD, Service Information, and French Airworthiness Directives.
Differences Among the Proposed AD, Service Information, and French
Airworthiness Directives
Service Bulletins A330-57-3085 and A340-57-4093 and the French
airworthiness directives specify to contact the manufacturer for repair
instructions and an inspection schedule if any crack or damage is
found; this proposed AD requires you to repair any cracking (and obtain
a schedule for subsequent inspections) by using a method that we or the
DGAC (or its delegated agent) approve. In light of the type of repair
required to address the unsafe condition, and consistent with existing
bilateral airworthiness agreements, we have determined that, for this
proposed AD, a repair and inspection schedule we or the DGAC approve is
acceptable for compliance with this proposed AD.
Figure 4, Sheet 1, ``Inspection Flow Chart,'' of Service Bulletins
A330-57-3085 and A340-57-4093 specifies initial inspection thresholds
for airplanes on which the actions in those service bulletins have been
accomplished, or Airbus Modification 53882 was done during production.
This proposed AD would require you to perform the initial inspection at
the earliest of those thresholds or within 6 months after the effective
date of the AD, whichever is later. We have included a 6-month grace
period to ensure that any airplane that is close to or has passed the
initial inspection threshold is not grounded as of the effective date
of the AD.
Clarification of Procedures for Certain Inspections
The French airworthiness directives require certain follow-on
inspections prior to next flight for airplanes above 8,000 flight
cycles or 30,200 flight hours with at least one wing rib 6 not repaired
or modified after a hard or overweight landing of the airplane;
however, there are no procedures specified in Service Bulletins A330-
57-3085 and A340-57-4093 for accomplishing those inspections.
Therefore, we have determined that, for this proposed AD, inspections
we or the DGAC approve are acceptable for compliance with the
inspections required by the French airworthiness directives. We have
provided other methods to comply, as specified in the French
airworthiness directives.
Interim Action
We consider this proposed AD interim action. The manufacturer is
currently developing a modification that will address the unsafe
condition identified in this proposed AD. Once this modification is
developed, approved, and available, we may consider additional
rulemaking.
Costs of Compliance
This proposed AD would affect about 25 airplanes of U.S. registry.
The proposed inspections would take about 4 work hours per
airplane, at an average labor rate of $65 per work hour. Based on these
figures, the estimated cost of the proposed inspections for U.S.
operators is $6,500, or $260 per airplane, per inspection cycle.
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 proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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 the proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
3. Will not have a significant economic impact, positive or
negative,
[[Page 61929]]
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 proposed 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, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
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]
2. The Federal Aviation Administration (FAA) amends Sec. 39.13 by
adding the following new airworthiness directive (AD):
Airbus: Docket No. FAA-2005-22812; Directorate Identifier 2005-NM-
134-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by November
28, 2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Airbus Model A330-201, -202, -203, -223,
and -243; A330-301, -321, -322, -323, -341, -342, and -343; A340-
211, -212, and -213; and A340-311, -312, and -313 airplanes,
certificated in any category; on which Airbus Modification 41114 or
44599 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 01, dated March 25, 2005.
Repeat the inspections thereafter at intervals not to exceed 8,000
flight cycles or 25,000 flight hours, whichever is first.
(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 after the effective date of this AD,
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 flight cycles or 30,000
flight hours after the effective date of this AD, 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 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, 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 01, dated March 25, 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.
(h) For Model A340 series airplanes on which Airbus Modification
53882 was not done during production: Perform 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 01, dated March 25, 2005. Repeat the inspections thereafter
at intervals not to exceed 8,000 flight cycles or 30,200 flight
hours, whichever is first.
(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 after the effective date of this AD,
whichever is first.
(ii) Within 8 months after the effective date of this AD.
(2) For airplanes that have accumulated 8,000 or more but fewer
than 10,000 total flight cycles or 30,200 or more but less 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 after the effective date of this AD,
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, 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 01, dated March 25, 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.
Optional Modification
(j) For airplanes on which no cracking is found during any
inspection required by this AD: 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, both dated February 15, 2005, as applicable, would extend the
interval for the next inspection to the applicable post-mod
inspection threshold specified in Figure 4, Sheet 1, ``Inspection
Flow Chart'' of Airbus Service Bulletins A330-57-3085 and A340-57-
4093, both Revision 01, both dated March 25, 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.
Note 2: There is currently no terminating action available for
the repetitive inspections required by this AD.
[[Page 61930]]
Inspections Accomplished According to Previous Issue of Service
Bulletins
(k) Inspections accomplished before the effective date of this
AD according to Airbus All Operator Telexes A330-57-3085 and A340-
57-4093, both dated December 15, 2004; are considered acceptable for
compliance with the corresponding inspections specified in this AD.
Repair
(l) Except as required by paragraph (m) of this AD: If any
cracking is found during any inspection required by this AD: Repair
before further flight and get a schedule for subsequent inspections,
according to a method approved by either the Manager, International
Branch, ANM-116, Transport Airplane Directorate; or the Direction
G[eacute]n[eacute]rale de l'Aviation (DGAC) (or its delegated
agent).
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 (j) 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 DGAC (or its delegated agent). Accomplishing
the inspections in Airbus A330/A340 Airplane Maintenance Manual,
Chapter 05-51-11, dated April 1, 2005, titled ``Inspection After
Hard/Overweight Landing--Inspection/Check,'' or Airbus Technical
Disposition (TD) TD/J1/S3/00608/2005, dated April 26, 2005, titled
``Inspections following hard landing, both wings,'' is considered
one approved method. (Operators can obtain the TD from Airbus.)
Reporting Requirement
(n) If any crack is found during any inspection required by this
AD: Submit a report of the findings to Airbus Repair Engineering,
Dept SER-1, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex,
France. Submit the report at the applicable time specified in
paragraph (n)(1) or (n)(2) of this AD. The report must include the
inspection results, a description of any discrepancies found, the
airplane serial number, and the number of landings and flight hours
on the airplane. Under the provisions of the Paperwork Reduction Act
of 1980 (44 U.S.C. 3501 et seq.), the Office of Management and
Budget (OMB) has approved the information collection requirements
contained in this AD and has assigned OMB Control Number 2120-0056.
(1) If the inspection was done after the effective date of this
AD: Submit the report within 30 days after the inspection.
(2) If the inspection was done before the effective date of this
AD: Submit the report within 30 days after the effective date of
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-2005-071 and F-2005-072,
both dated April 27, 2005, also address the subject of this AD.
Issued in Renton, Washington, on October 20, 2005.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-21429 Filed 10-26-05; 8:45 am]
BILLING CODE 4910-13-P