Airworthiness Directives; Airbus Model A330-300, A340-200, and A340-300 Series Airplanes, 73925-73930 [05-23901]
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Federal Register / Vol. 70, No. 239 / Wednesday, December 14, 2005 / Rules and Regulations
the Manager’s approval letter must
specifically refer to this AD.
DEPARTMENT OF TRANSPORTATION
Actions Accomplished Previously
(l) Inspections and corrective actions
accomplished before the effective date of this
AD in accordance with the original issue of
Sabreliner NA–265 Service Bulletin 83–2,
dated March 4, 1983; or Sabreliner NA–265
Service Bulletin 83–2, revised February 29,
1996; are acceptable for compliance with the
corresponding actions required by
paragraphs (j) and (k) of this AD.
Federal Aviation Administration
No Reporting Requirement
(m) Although the service bulletins
referenced in this AD specify to submit
certain information to the manufacturer, this
AD does not include that requirement.
Alternative Methods of Compliance
(AMOCs)
(n)(1) The Manager, Wichita ACO, 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.
Material Incorporated by Reference
(o) You must use Sabreliner NA–265
Service Bulletin 73–11, revised June 1, 1978;
or Sabreliner NA–265 Service Bulletin 83–2,
revised January 31, 2005; to perform the
actions that are required by this AD, unless
the AD specifies otherwise. Sabreliner NA–
265 Service Bulletin 73–11, revised June 1,
1978, contains the following effective pages:
Page No.
1 .........................................
2–14 ...................................
Date shown on
page
June 1, 1978.
June 15, 1973.
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 Sabreliner
Corporation, 18118 Chesterfield Airport
Road, Chesterfield, Missouri 63005–1121, 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
December 2, 2005.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 05–23904 Filed 12–13–05; 8:45 am]
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14 CFR Part 39
[Docket No. FAA–2005–23251; Directorate
Identifier 2002–NM–20–AD; Amendment 39–
14413; AD 2005–25–20]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A330–300, A340–200, and A340–300
Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
AGENCY:
SUMMARY: The FAA is superseding an
existing airworthiness directive (AD),
which applies to certain Airbus Model
A330–300, A340–200, and 340–300
series airplanes. The existing AD
requires repetitive inspections to detect
cracking of the fuselage skin in the area
of the VHF2 antenna, and repair if
necessary. The existing AD also
provides for optional terminating action
for the repetitive inspections. This new
AD requires accomplishment of the
previously optional terminating action,
and revises the applicability by
removing certain airplanes. This AD is
prompted by the need to change the
applicability of the existing AD and to
mandate the formerly optional
terminating action. We are issuing this
AD to prevent cracking of the fuselage
skin in the area of the VHF2 antenna,
which could result in depressurization
of the airplane.
DATES: Effective December 29, 2005.
The incorporation by reference of
certain publications listed in the
regulations is approved by the Director
of the Federal Register as of December
29, 2005.
The incorporation by reference of
certain other publications, as listed in
the regulations, was approved
previously by the Director of the Federal
Register as of April 12, 2000 (65 FR
12075, March 8, 2000).
We must receive comments on this
AD by February 13, 2006.
ADDRESSES: Use one of the following
addresses to submit comments on this
AD.
• DOT Docket Web site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically.
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73925
• 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.
For service information identified in
this AD, contact Airbus, 1 Rond Point
Maurice Bellonte, 31707 Blagnac Cedex,
France. You can examine this
information at the National Archives
and Records Administration (NARA).
For information on the availability of
this material at NARA, call (202) 741–
6030, or go to
https://www.archives.gov/
federal_register/
code_of_federal_regulations/
ibr_locations.html.
You can examine the contents of this
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., room PL–401, on the plaza level of
the Nassif Building, Washington, DC.
This docket number is FAA–2005–
23251; the directorate identifier for this
docket is 2002–NM–20–AD.
Examining the Docket
You can 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 DOT
street address stated in the ADDRESSES
section. Comments will be available in
the AD docket shortly after the DMS
receives them.
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: On
February 29, 2000, the FAA issued AD
2000–05–04, amendment 39–11613 (65
FR 12075, March 8, 2000). That AD
applies to certain Airbus Model A330
and A340 series airplanes and requires
repetitive inspections to detect cracking
of the fuselage skin in the area of the
VHF2 antenna, and repair if necessary.
That AD also provides for optional
terminating action for the repetitive
inspections. That action was prompted
by issuance of mandatory continuing
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airworthiness information by the French
civil aviation authority. We issued that
AD to detect and correct such cracking,
which could result in depressurization
of the airplane.
Actions Since Issuance of Previous Rule
Since we issued AD 2000–05–04, the
´ ´
Direction Generale de l’Aviation Civile
(DGAC), which is the airworthiness
authority for France, has revised the
parallel French airworthiness directives
to exclude airplanes that have been
modified by Airbus Modification 46025,
46849, or 46900; and to mandate the
previously optional terminating action.
Explanation of Relevant New Service
Information
Airbus has issued the following
service bulletins:
SERVICE INFORMATION
Describes procedures for
repetitive detailed inspections of—
Airbus Service Bulletin—
A330–53–3094, Revision 03, dated February 22,
2001; and Revision 04, dated July 23, 2001.
A340–53–4105, Revision 03, dated February 22,
2001, and Revision 04, dated July 23, 2001.
The revised service bulletins for the
terminating modification are essentially
the same: They remove certain life
limits, but add no new procedures. The
DGAC classified Service Bulletins
A330–53–3097 and A340–53–4108 as
mandatory and issued French
airworthiness directives 2001–041(B)
and 2001–040(B), both dated January 24,
2001, to ensure the continued
airworthiness of these airplanes in
France.
Airbus has also issued Service
Bulletins A330–53–3112 and A340–53–
4124, both dated February 15, 2001,
which describe procedures for
relocating the VHF2 antenna between
stringer 51 and stringer 52, away from
the outlet air flow of the air
conditioning packs. These service
bulletins provide for alternative
procedures to those specified in Service
Bulletins A330–53–3097 and A340–53–
4108 to eliminate the need for the
repetitive inspections. The DGAC has
approved Service Bulletins A330–53–
3112 and A340–53–4124 and considers
them optional terminating action for the
repetitive inspections.
FAA’s Determination and Requirements
of This 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. According to this bilateral
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Model A330–300 series
airplanes.
Model A340 series airplanes.
Which could be eliminated by the modification specified in—
Airbus Service Bulletin—
02
November 21, 2000.
A340–53–4108
02
December 6, 2000.
Additional Changes to AD
We have made the following
additional changes to the AD:
1. We revised the applicability in this
AD by updating the service bulletin
references to match the applicability of
the corresponding French airworthiness
directives.
2. The FAA has changed all references
to a ‘‘detailed visual inspection’’ in the
existing AD to ‘‘detailed inspection’’ in
this new AD. Note 1 in this AD defines
that inspection.
3. We have reviewed the figures we
have used over the past several years to
calculate AD costs to operators. To
account for various inflationary costs in
the airline industry, we find it necessary
to increase the labor rate used in these
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Dated—
A330–53–3097
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 products of this
type design that are certificated for
operation in the United States.
For this reason, we are issuing this
AD to supersede AD 2000–05–04. This
AD retains the requirements of the
existing AD, requires accomplishment
of the previously optional terminating
action, and adds an alternative
terminating action. This AD removes
certain airplanes from the applicability
of the existing AD. The actions are
required to be done in accordance with
the service bulletins described
previously, except as described below.
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Revision—
calculations from $60 per work hour to
$65 per work hour. The cost impact
information, below, reflects this
increase in the specified hourly labor
rate.
4. Since we issued AD 2000–05–04,
the type certificate data sheet for
affected airplanes has been updated. We
have revised the applicability of this AD
accordingly.
Differences Between AD and Service
Bulletins
The revised service bulletins provide
repair procedures for cracks up to 14.17
inches. However, no data have been
presented that would justify the
acceptability of the increased crack
length. This AD requires that operators
contact the FAA or DGAC for repair
instructions of cracks exceeding 9.45
inches.
Costs of Compliance
None of the airplanes affected by this
action are on the U.S. Register. All
airplanes affected by this AD are
currently operated by non-U.S.
operators under foreign registry;
therefore, they are not directly affected
by this AD action. However, we
consider this AD necessary to ensure
that the unsafe condition is addressed if
any affected airplane is imported and
placed on the U.S. Register in the future.
The following table provides the
estimated costs to comply with this AD
for any affected airplane that might be
imported and placed on the U.S.
Register in the future.
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73927
ESTIMATED COSTS
Hourly labor
rate
(dollars)
Parts cost
(dollars)
Cost per airplane
(dollars)
65
None required
107
65
0
390, per inspection
cycle.
6,955.
109
65
2,850
Action
Applicable Airbus Service Bulletin
Work hours
Inspection ...................
A330–53–3094 or A340–53–4105 .................
6
Fuselage skin reinforcement.
Antenna relocation ......
A330–53–3097 or A340–53–4108 .................
A330–53–3112 or A340–53–4124 .................
FAA’s Determination of the Effective
Date
2000 (65 FR 19477–78), or you can visit
https://dms.dot.gov.
No airplane affected by this AD is
currently on the U.S. Register.
Therefore, providing notice and
opportunity for public comment is
unnecessary before this AD is issued,
and this AD may be made effective in
less than 30 days after it is published in
the Federal Register.
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.
Comments Invited
Although this is a final rule that was
not preceded by notice and an
opportunity for public comment, we
invite you to submit any relevant
written data, views, or arguments
regarding this AD. Send your comments
to an address listed under ADDRESSES.
Include ‘‘Docket No. FAA–2005–23251;
Directorate Identifier 2002–NM–20–AD’’
at the beginning of your comments. We
specifically invite comments on the
overall regulatory, economic,
environmental, and energy aspects of
the AD. We will consider all comments
received by the closing date and may
amend the AD in light of those
comments.
We will post all comments we
receive, without change, to https://
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 AD. Using the
search function of our docket 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 can review the DOT’s
complete Privacy Act Statement in the
Federal Register published on April 11,
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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 the 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,
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9,935.
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. 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 FAA amends § 39.13 by
removing amendment 39–11613 (65 FR
12075, March 8, 2000) and adding the
following new airworthiness directive
(AD):
I
2005–25–20 Airbus: Amendment 39–14413.
Docket No. FAA–2005–23251;
Directorate Identifier 2002–NM–20–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective December 29, 2005.
Affected ADs
(b) This AD supersedes AD 2000–05–04.
Applicability
(c) This AD applies to the airplanes,
certificated in any category, listed in Table 1
of this AD.
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TABLE 1.—APPLICABILITY
Except those modified in accordance with any applicable service information listed below:
Model—
Airbus Service Bulletin—
Airbus Model A330–301, –321, –322,
–323, –341, –342, and –343 airplanes.
Airbus Model A340–211, –212, and
–213 airplanes, and Airbus Model
A340–311, –312, and –313 airplanes.
A330–53–3097, Revision 02, dated
November 21, 2000 (Airbus Modification 46025).
A340–53–4108, Revision 02, dated
December 6, 2000 (Airbus Modification 46025).
Unsafe Condition
(d) This AD was prompted by the need to
change the applicability of the existing AD
and to mandate the formerly optional
terminating action. We are issuing this AD to
prevent cracking of the fuselage skin in the
area of the VHF2 antenna, which could result
in depressurization of the airplane.
Compliance
(e) You are responsible for having the
actions required by this AD performed within
the compliance times specified, unless the
actions have already been done.
Restatement of Requirements of AD 2000–
05–04
Detailed Inspection
(f) At the latest of the times specified in
paragraphs (f)(1), (f)(2), (f)(3), and (f)(4) of
this AD, as applicable: Perform a detailed
inspection (without removal of the VHF2
antenna) of the fuselage skin aft of frame 54,
between the airplane centerline and stringer
56R in the area of the VHF2 antenna to detect
cracks, in accordance with Airbus Service
Bulletin A330–53–3094, Revision 02, dated
May 28, 1998, Revision 03, dated February
22, 2001, or Revision 04, dated July 23, 2001
(for Model A330 series airplanes); or Airbus
Service Bulletin A340–53–4105, Revision 02,
dated May 25, 1998, Revision 03, dated
February 22, 2001, or Revision 04, dated July
23, 2001 (for Model A340 series airplanes).
Thereafter, if no cracks are detected, repeat
the detailed inspection every 36 flight hours
until accomplishment of the high frequency
eddy current (HFEC) inspection required by
paragraph (g) of this AD.
(1) Prior to the accumulation of 900 total
flight hours.
(2) Within 1,250 flight hours since
accomplishment of the interim repair
specified by paragraph C.(4) of the
Accomplishment Instructions of the
applicable service bulletin, if the interim
repair has been accomplished prior to April
12, 2000 (the effective date of AD 2000–05–
04).
(3) Within 300 flight hours since the most
recent HFEC inspection accomplished in
accordance with the applicable service
bulletin, if the most recent HFEC inspection
has been accomplished prior to April 12,
2000.
(4) Within 36 flight hours after April 12,
2000.
Note 1: For the purposes of this AD, a
detailed inspection is: ‘‘An intensive
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A330–53–3112, dated February 15,
2001 (Airbus Modification 46849).
46900.
A340–53–4124, dated February 15,
2001 (Airbus Modification 46849).
46900.
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.’’
High Frequency Eddy Current Inspection
(g) Perform an HFEC inspection to detect
cracks of the fuselage skin aft of frame 54,
between the airplane centerline and stringer
56R in the area of the VHF2 antenna, in
accordance with Airbus Service Bulletin
A330–53–3094, Revision 02, dated May 28,
1998, Revision 03, dated February 22, 2001,
or Revision 04, dated July 23, 2001; or
Service Bulletin A340–53–4105, Revision 02,
dated May 25, 1998, Revision 03, dated
February 22, 2001, or Revision 04, dated July
23, 2001; at the applicable time specified by
paragraph (g)(1) or (g)(2) of this AD.
Accomplishment of this inspection
terminates the requirements of paragraph (f)
of this AD.
(1) For airplanes on which the interim
repair specified by paragraph C.(4) of the
Accomplishment Instructions of the
applicable service bulletin has not been
accomplished before April 12, 2000: Prior to
the accumulation of 900 total flight hours on
the airplane, or within 500 flight hours after
April 12, 2000, whichever occurs later.
Thereafter, accomplish the follow-on actions
of paragraph (h) or (i) of this AD, as
applicable.
(2) For airplanes on which the interim
repair specified by paragraph C.(4) of the
Accomplishment Instructions of the
applicable service bulletin has been
accomplished before April 12, 2000: Within
1,250 flight hours after accomplishment of
the interim repair, or within 500 flight hours
after April 12, 2000, whichever occurs later.
Repetitive Inspections
(h) If no crack is detected during the HFEC
inspection required by paragraph (g) of this
AD, accomplish the repetitive inspections
required by paragraph (h)(1) or (h)(2) of this
AD, as applicable, until the terminating
action required by paragraph (k) of this AD
has been done.
(1) For airplanes on which the interim
repair specified by paragraph C.(4) of the
Accomplishment Instructions of Airbus
Service Bulletin A330–53–3094, Revision 02,
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Or Airbus production
modification—
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dated May 28, 1998, Revision 03, dated
February 22, 2001, or Revision 04, dated July
23, 2001; or Service Bulletin A340–53–4105,
Revision 02, dated May 25, 1998, Revision
03, dated February 22, 2001, or Revision 04,
dated July 23, 2001; has not been
accomplished before April 12, 2000:
Accomplish the actions specified by
paragraphs (h)(1)(i) and (h)(1)(ii) of this AD.
(i) Repeat the HFEC inspection specified by
paragraph (g) at intervals not to exceed 500
flight hours.
(ii) Within 300 flight hours after each
HFEC inspection required by this AD:
Perform a detailed inspection (without
removal of the VHF2 antenna) of the fuselage
skin aft of frame 54, between the airplane
centerline and stringer 56R in the area of the
VHF2 antenna to detect cracks, in accordance
with the applicable service bulletin.
Thereafter, if no cracks are detected, repeat
the detailed inspection at intervals not to
exceed 36 flight hours until accomplishment
of the next HFEC inspection required by
paragraph (h)(1)(i) of this AD.
(2) For airplanes on which the interim
repair specified by paragraph C.(4) of the
Accomplishment Instructions of the
applicable service bulletin has been
accomplished before April 12, 2000: Repeat
the HFEC inspection specified by paragraph
(g) of this AD at intervals not to exceed 1,250
flight hours.
Corrective Actions
(i) If any crack is detected during any
inspection required by paragraph (k), (l), or
(m) of this AD, and the interim repair
specified by paragraph C.(4) of the
Accomplishment Instructions of Airbus
Service Bulletin A330–53–3094, Revision 02,
dated May 28, 1998, Revision 03, dated
February 22, 2001, or Revision 04, dated July
23, 2001; or Service Bulletin A340–53–4105,
Revision 02, dated May 25, 1998, Revision
03, dated February 22, 2001, or Revision 04,
dated July 23, 2001; has not been
accomplished: Prior to further flight,
accomplish the actions specified by
paragraph (i)(1) or (i)(2) of this AD, as
applicable.
(1) If only one crack is detected and that
crack is 9.45 inches or less, and is within the
limits specified by the applicable service
bulletin: Install the interim repair specified
in paragraph C.(4) of the Accomplishment
Instructions of the applicable service
bulletin. Thereafter, repeat the HFEC
inspection specified by paragraph (g) of this
AD at intervals not to exceed 1,250 flight
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hours, until the terminating action required
by paragraph (k) of this AD has been done.
Note 2: The interim repair referenced by
this AD consists of cutting out the cracked
portion of the fuselage skin, and installing a
filler plate in the skin cutout, two doublers,
and shims, as described in paragraph C.(4) of
the Accomplishment Instructions of Airbus
Service Bulletin A330–53–3094, Revision 02,
dated May 28, 1998, Revision 03, dated
February 22, 2001, or Revision 04, dated July
23, 2001 (for Model A330 series airplanes);
or Airbus Service Bulletin A340–53–4105,
Revision 02, dated May 25, 1998, Revision
03, dated February 22, 2001, or Revision 04,
dated July 23, 2001 (for Model A340 series
airplanes).
Note 3: Accomplishment of the interim
repair in accordance with paragraph 4.3 of
Airbus Industrie All Operator Telex (AOT)
53–10, dated September 24, 1997, is
acceptable for compliance with the
requirements of paragraph (i)(1) of this AD.
than one crack is detected: Repair in
accordance with a method approved by the
Manager, International Branch, ANM–116,
Transport Airplane Directorate, FAA; or the
´ ´
Direction Generale de l’Aviation Civile
(DGAC) (or its delegated agent).
(j) If any crack is detected during any
inspection required by paragraph (f), (g), or
(h) of this AD, and the interim repair
specified by paragraph C.(4) of the
Accomplishment Instructions of Airbus
Service Bulletin A330–53–3094, Revision 02,
dated May 28, 1998, Revision 03, dated
February 22, 2001, or Revision 04, dated July
23, 2001; or Airbus Service Bulletin A340–
53–4105, Revision 02, dated May 25, 1998,
Revision 03, dated February 22, 2001, or
Revision 04, dated July 23, 2001; has been
accomplished: Prior to further flight, repair
in accordance with a method approved by
the Manager, International Branch, ANM–
116; or the DGAC (or its delegated agent).
New Requirements of This AD
Terminating Action
(k) Within 18 months after the effective
date of this AD: Do the actions specified in
(2) If any crack is detected that is longer
than 9.45 inches, or is outside the limits
specified by the service bulletin, or if more
either paragraph (k)(1) or (k)(2).
Accomplishment of either action terminates
the repetitive inspections required by
paragraphs (f), (g), (h) and (i)(1) of this AD.
(1) Reinforce the fuselage skin between
FR54 and FR55 in the area of the VHF2
antenna, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A330–53–3097, Revision 02,
dated November 21, 2000 (for Model A330
series airplanes); or A340–53–4108, Revision
02, dated December 6, 2000 (for Model A340
series airplanes); as applicable.
(2) Relocate the VHF2 antenna between
stringer 51 and stringer 52, in accordance
with Airbus Service Bulletin A330–53–3112
(for Model A330 series airplanes) or A340–
53–4124 (for Model A340 series airplanes),
both dated February 15, 2001; as applicable.
(l) Work done before the effective date of
this AD in accordance with an applicable
source listed in Table 2 of this AD is
acceptable for compliance with the
corresponding requirements of paragraph (k)
of this AD.
TABLE 2.—CREDIT FOR PRIOR MODIFICATION
Model
Service information
A330–300 .....................................
A330–300, A340 ...........................
A340 .............................................
Airbus Service Bulletin A330–53–3097 ..............................................
Airbus production Modification 46025 ................................................
Airbus Service Bulletin A340–53–4108 ..............................................
Alternative Methods of Compliance
Revision
airplane to which the AMOC applies, notify
the appropriate principal inspector in the
FAA Flight Standards Certificate Holding
District Office.
(m)(1) In accordance with 14 CFR 39.19,
the Manager, International Branch, ANM–
116, is authorized to approve alternative
methods of compliance for this AD.
(2) Before using any AMOC approved in
accordance with 14 CFR 39.19 on any
Related Information
(n) The subject of this AD is addressed in
French airworthiness directives 2001–040(B)
Date
Original ............... July 29, 1998.
(done in production)
Original ............... July 31, 1998.
and 2001–041(B), both dated January 24,
2001.
Material Incorporated by Reference
(o) Unless otherwise specified in this AD,
the actions must be done in accordance with
the service information listed in Table 3 of
this AD, as applicable.
TABLE 3.—MATERIAL INCORPORATED BY REFERENCE
Airbus Service Bulletin
A330–53–3094
A330–53–3094
A330–53–3094
A330–53–3097
A330–53–3112
A340–53–4105
A340–53–4105
A340–53–4105
A340–53–4108
A340–53–4124
Revision level
.....................................................................................................
.....................................................................................................
.....................................................................................................
.....................................................................................................
.....................................................................................................
.....................................................................................................
.....................................................................................................
.....................................................................................................
.....................................................................................................
.....................................................................................................
(1) The incorporation by reference of the
service information listed in Table 4 of this
AD is approved by the Director of the Federal
02 ..........................................................
03 ..........................................................
04 ..........................................................
02 ..........................................................
Original ..................................................
02 ..........................................................
03 ..........................................................
04 ..........................................................
02 ..........................................................
Original ..................................................
Date
May 28, 1998.
February 22, 2001.
July 23, 2001.
November 21, 2000.
February 15, 2001.
May 25, 1998.
February 22, 2001.
July 23, 2001.
December 6, 2000.
February 15, 2001.
Register in accordance with 5 U.S.C. 552(a)
and 1 CFR part 51.
TABLE 4.—MATERIAL NEWLY INCORPORATED BY REFERENCE
Airbus Service Bulletin
A330–53–3094
A330–53–3094
A330–53–3097
A330–53–3112
VerDate Aug<31>2005
Revision level
.....................................................................................................
.....................................................................................................
.....................................................................................................
.....................................................................................................
15:23 Dec 13, 2005
Jkt 208001
PO 00000
Frm 00025
Fmt 4700
03 ..........................................................
04 ..........................................................
02 ..........................................................
Original ..................................................
Sfmt 4700
E:\FR\FM\14DER1.SGM
14DER1
Date
February 22, 2001.
July 23, 2001.
November 21, 2000.
February 15, 2001.
73930
Federal Register / Vol. 70, No. 239 / Wednesday, December 14, 2005 / Rules and Regulations
TABLE 4.—MATERIAL NEWLY INCORPORATED BY REFERENCE—Continued
Airbus Service Bulletin
A340–53–4105
A340–53–4105
A340–53–4108
A340–53–4124
Revision level
.....................................................................................................
.....................................................................................................
.....................................................................................................
.....................................................................................................
(2) The incorporation by reference of the
service information listed in Table 5 of this
AD was approved previously by the Director
Date
03 ..........................................................
04 ..........................................................
02 ..........................................................
Original ..................................................
February 22, 2001.
July 23, 2001.
December 6, 2000.
February 15, 2001.
of the Federal Register as of April 12, 2000
(65 FR 12075, March 8, 2000).
TABLE 5.—MATERIAL PREVIOUSLY INCORPORATED BY REFERENCE
Revision
level
Airbus Service Bulletin
A330–53–3094 .................................................................................................................................................
A340–53–4105 .................................................................................................................................................
(3) Copies may be obtained from Airbus, 1
Rond Point Maurice Bellonte, 31707 Blagnac
Cedex, France. Copies may be inspected at
the FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton,
Washington; or at the National Archives and
Records Administration (NARA). For
information on the availability of this
material at NARA, call (202) 741–6030, or go
to https://www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html.
Issued in Renton, Washington, on
December 2, 2005.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 05–23901 Filed 12–13–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–22384; Directorate
Identifier 2005–NM–131–AD; Amendment
39–14412; AD 2005–25–19]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A300 B2 Series Airplanes, Model A300
B4 Series Airplanes, Model A310–200
Series Airplanes, Model A310–300
Series Airplanes; and Model A300 B4–
600, B4–600R, and F4–600R Series
Airplanes, and Model C4–605R Variant
F Airplanes (Collectively Called A300–
600 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 certain
VerDate Aug<31>2005
15:23 Dec 13, 2005
Jkt 208001
Airbus transport category airplanes.
This AD requires repetitive eddy current
inspections for cracks of the stiffener
fittings of the fuselage at frame (FR)
12A, and corrective actions if necessary.
This AD also provides a terminating
action for the inspections. This AD
results from reports of cracks on the
upper attachment fitting of the stiffener
fitting at FR12A. We are issuing this AD
to prevent failure of the stiffener fittings,
which could result in the reduced
structural integrity of the floor and rods
around FR 12A.
DATES: This AD becomes effective
January 18, 2006.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of January 18, 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 Jacques Leborgne, Airbus
Customer Service Directorate, 1 Rond
Point Maurice Bellonte, 31707 Blagnac
Cedex, France, fax (+33) 5 61 93 36 14,
for service information identified in this
AD for Model A300 B2 series airplanes
and Model A300 B4 series airplanes.
Contact Airbus, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France,
for service information identified in this
AD for Model A310–200 series
airplanes, Model A310–300 series
airplanes, and Model A300–600 series
airplanes.
FOR FURTHER INFORMATION CONTACT: Dan
Rodina, Aerospace Engineer,
International Branch, ANM–116, FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington
PO 00000
Frm 00026
Fmt 4700
Sfmt 4700
02
02
Date
May 28, 1998.
May 25, 1998.
98055–4056; telephone (425) 227–2125;
fax (425) 227–1149.
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 would
apply to certain Airbus transport
category airplanes. That NPRM was
published in the Federal Register on
September 12, 2005 (70 FR 53739). That
NPRM proposed to require repetitive
eddy current inspections for cracks of
the stiffener fittings of the fuselage at
frame (FR) 12A, and corrective actions
if necessary. The NPRM also provided a
terminating action for the inspections.
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.
Clarification of Alternative Method of
Compliance (AMOC) Paragraph
We have revised this action to clarify
the appropriate procedure for notifying
the principal inspector before using any
approved AMOC on any airplane to
which the AMOC applies.
E:\FR\FM\14DER1.SGM
14DER1
]]>Agencies
[Federal Register Volume 70, Number 239 (Wednesday, December 14, 2005)]
[Rules and Regulations]
[Pages 73925-73930]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-23901]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-23251; Directorate Identifier 2002-NM-20-AD;
Amendment 39-14413; AD 2005-25-20]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A330-300, A340-200, and
A340-300 Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: The FAA is superseding an existing airworthiness directive
(AD), which applies to certain Airbus Model A330-300, A340-200, and
340-300 series airplanes. The existing AD requires repetitive
inspections to detect cracking of the fuselage skin in the area of the
VHF2 antenna, and repair if necessary. The existing AD also provides
for optional terminating action for the repetitive inspections. This
new AD requires accomplishment of the previously optional terminating
action, and revises the applicability by removing certain airplanes.
This AD is prompted by the need to change the applicability of the
existing AD and to mandate the formerly optional terminating action. We
are issuing this AD to prevent cracking of the fuselage skin in the
area of the VHF2 antenna, which could result in depressurization of the
airplane.
DATES: Effective December 29, 2005.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of December 29, 2005.
The incorporation by reference of certain other publications, as
listed in the regulations, was approved previously by the Director of
the Federal Register as of April 12, 2000 (65 FR 12075, March 8, 2000).
We must receive comments on this AD by February 13, 2006.
ADDRESSES: Use one of the following addresses to submit comments on
this AD.
DOT Docket Web site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to https://
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.
For service information identified in this AD, contact Airbus, 1
Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. You can
examine this information at the National Archives and Records
Administration (NARA). For information on the availability of this
material at NARA, call (202) 741-6030, or go to https://
www.archives.gov/federal_register/code_of_federal_regulations/ibr_
locations.html.
You can examine the contents of this 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., room PL-
401, on the plaza level of the Nassif Building, Washington, DC. This
docket number is FAA-2005-23251; the directorate identifier for this
docket is 2002-NM-20-AD.
Examining the Docket
You can 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 DOT
street address stated in the ADDRESSES section. Comments will be
available in the AD docket shortly after the DMS receives them.
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: On February 29, 2000, the FAA issued AD
2000-05-04, amendment 39-11613 (65 FR 12075, March 8, 2000). That AD
applies to certain Airbus Model A330 and A340 series airplanes and
requires repetitive inspections to detect cracking of the fuselage skin
in the area of the VHF2 antenna, and repair if necessary. That AD also
provides for optional terminating action for the repetitive
inspections. That action was prompted by issuance of mandatory
continuing
[[Page 73926]]
airworthiness information by the French civil aviation authority. We
issued that AD to detect and correct such cracking, which could result
in depressurization of the airplane.
Actions Since Issuance of Previous Rule
Since we issued AD 2000-05-04, the Direction G[eacute]n[eacute]rale
de l'Aviation Civile (DGAC), which is the airworthiness authority for
France, has revised the parallel French airworthiness directives to
exclude airplanes that have been modified by Airbus Modification 46025,
46849, or 46900; and to mandate the previously optional terminating
action.
Explanation of Relevant New Service Information
Airbus has issued the following service bulletins:
Service Information
--------------------------------------------------------------------------------------------------------------------------------------------------------
Describes procedures for Which could be eliminated by the modification specified in--
Airbus Service Bulletin-- repetitive detailed --------------------------------------------------------------------------------------
inspections of-- Airbus Service Bulletin-- Revision-- Dated--
--------------------------------------------------------------------------------------------------------------------------------------------------------
A330-53-3094, Revision 03, dated Model A330-300 series A330-53-3097 02 November 21, 2000.
February 22, 2001; and Revision 04, airplanes.
dated July 23, 2001.
A340-53-4105, Revision 03, dated Model A340 series A340-53-4108 02 December 6, 2000.
February 22, 2001, and Revision 04, airplanes.
dated July 23, 2001.
--------------------------------------------------------------------------------------------------------------------------------------------------------
The revised service bulletins for the terminating modification are
essentially the same: They remove certain life limits, but add no new
procedures. The DGAC classified Service Bulletins A330-53-3097 and
A340-53-4108 as mandatory and issued French airworthiness directives
2001-041(B) and 2001-040(B), both dated January 24, 2001, to ensure the
continued airworthiness of these airplanes in France.
Airbus has also issued Service Bulletins A330-53-3112 and A340-53-
4124, both dated February 15, 2001, which describe procedures for
relocating the VHF2 antenna between stringer 51 and stringer 52, away
from the outlet air flow of the air conditioning packs. These service
bulletins provide for alternative procedures to those specified in
Service Bulletins A330-53-3097 and A340-53-4108 to eliminate the need
for the repetitive inspections. The DGAC has approved Service Bulletins
A330-53-3112 and A340-53-4124 and considers them optional terminating
action for the repetitive inspections.
FAA's Determination and Requirements of This 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. According 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 products of this type design that are certificated for
operation in the United States.
For this reason, we are issuing this AD to supersede AD 2000-05-04.
This AD retains the requirements of the existing AD, requires
accomplishment of the previously optional terminating action, and adds
an alternative terminating action. This AD removes certain airplanes
from the applicability of the existing AD. The actions are required to
be done in accordance with the service bulletins described previously,
except as described below.
Additional Changes to AD
We have made the following additional changes to the AD:
1. We revised the applicability in this AD by updating the service
bulletin references to match the applicability of the corresponding
French airworthiness directives.
2. The FAA has changed all references to a ``detailed visual
inspection'' in the existing AD to ``detailed inspection'' in this new
AD. Note 1 in this AD defines that inspection.
3. We have reviewed the figures we have used over the past several
years to calculate AD costs to operators. To account for various
inflationary costs in the airline industry, we find it necessary to
increase the labor rate used in these calculations from $60 per work
hour to $65 per work hour. The cost impact information, below, reflects
this increase in the specified hourly labor rate.
4. Since we issued AD 2000-05-04, the type certificate data sheet
for affected airplanes has been updated. We have revised the
applicability of this AD accordingly.
Differences Between AD and Service Bulletins
The revised service bulletins provide repair procedures for cracks
up to 14.17 inches. However, no data have been presented that would
justify the acceptability of the increased crack length. This AD
requires that operators contact the FAA or DGAC for repair instructions
of cracks exceeding 9.45 inches.
Costs of Compliance
None of the airplanes affected by this action are on the U.S.
Register. All airplanes affected by this AD are currently operated by
non-U.S. operators under foreign registry; therefore, they are not
directly affected by this AD action. However, we consider this AD
necessary to ensure that the unsafe condition is addressed if any
affected airplane is imported and placed on the U.S. Register in the
future.
The following table provides the estimated costs to comply with
this AD for any affected airplane that might be imported and placed on
the U.S. Register in the future.
[[Page 73927]]
Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Applicable Airbus Service Hourly labor Parts cost
Action Bulletin Work hours rate (dollars) (dollars) Cost per airplane (dollars)
--------------------------------------------------------------------------------------------------------------------------------------------------------
Inspection............................ A330-53-3094 or A340-53-4105. 6 65 None required 390, per inspection cycle.
Fuselage skin reinforcement........... A330-53-3097 or A340-53-4108. 107 65 0 6,955.
Antenna relocation.................... A330-53-3112 or A340-53-4124. 109 65 2,850 9,935.
--------------------------------------------------------------------------------------------------------------------------------------------------------
FAA's Determination of the Effective Date
No airplane affected by this AD is currently on the U.S. Register.
Therefore, providing notice and opportunity for public comment is
unnecessary before this AD is issued, and this AD may be made effective
in less than 30 days after it is published in the Federal Register.
Comments Invited
Although this is a final rule that was not preceded by notice and
an opportunity for public comment, we invite you to submit any relevant
written data, views, or arguments regarding this AD. Send your comments
to an address listed under ADDRESSES. Include ``Docket No. FAA-2005-
23251; Directorate Identifier 2002-NM-20-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the AD. We will consider
all comments received by the closing date and may amend the AD in light
of those comments.
We will post all comments we receive, without change, to https://
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 AD. Using the search function of our docket
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 can review the DOT's complete Privacy Act Statement in the Federal
Register published on April 11, 2000 (65 FR 19477-78), or you can visit
https://dms.dot.gov.
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 the 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, 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. 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 FAA amends Sec. 39.13 by removing amendment 39-11613 (65 FR
12075, March 8, 2000) and adding the following new airworthiness
directive (AD):
2005-25-20 Airbus: Amendment 39-14413. Docket No. FAA-2005-23251;
Directorate Identifier 2002-NM-20-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective December
29, 2005.
Affected ADs
(b) This AD supersedes AD 2000-05-04.
Applicability
(c) This AD applies to the airplanes, certificated in any
category, listed in Table 1 of this AD.
[[Page 73928]]
Table 1.--Applicability
----------------------------------------------------------------------------------------------------------------
----------------------------------------------------------------------------------------------------------------
Except those modified in accordance with any applicable service information
listed below:
------------------------
Model-- Airbus Service Bulletin-- Or Airbus production
modification--
-----------------------------------
Airbus Model A330-301, -321, -322, A330-53-3097, A330-53-3112, dated 46900.
-323, -341, -342, and -343 Revision 02, dated February 15, 2001
airplanes. November 21, 2000 (Airbus
(Airbus Modification Modification 46849).
46025).
Airbus Model A340-211, -212, and - A340-53-4108, A340-53-4124, dated 46900.
213 airplanes, and Airbus Model Revision 02, dated February 15, 2001
A340-311, -312, and -313 December 6, 2000 (Airbus
airplanes. (Airbus Modification Modification 46849).
46025).
----------------------------------------------------------------------------------------------------------------
Unsafe Condition
(d) This AD was prompted by the need to change the applicability
of the existing AD and to mandate the formerly optional terminating
action. We are issuing this AD to prevent cracking of the fuselage
skin in the area of the VHF2 antenna, which could result in
depressurization of the airplane.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Restatement of Requirements of AD 2000-05-04
Detailed Inspection
(f) At the latest of the times specified in paragraphs (f)(1),
(f)(2), (f)(3), and (f)(4) of this AD, as applicable: Perform a
detailed inspection (without removal of the VHF2 antenna) of the
fuselage skin aft of frame 54, between the airplane centerline and
stringer 56R in the area of the VHF2 antenna to detect cracks, in
accordance with Airbus Service Bulletin A330-53-3094, Revision 02,
dated May 28, 1998, Revision 03, dated February 22, 2001, or
Revision 04, dated July 23, 2001 (for Model A330 series airplanes);
or Airbus Service Bulletin A340-53-4105, Revision 02, dated May 25,
1998, Revision 03, dated February 22, 2001, or Revision 04, dated
July 23, 2001 (for Model A340 series airplanes). Thereafter, if no
cracks are detected, repeat the detailed inspection every 36 flight
hours until accomplishment of the high frequency eddy current (HFEC)
inspection required by paragraph (g) of this AD.
(1) Prior to the accumulation of 900 total flight hours.
(2) Within 1,250 flight hours since accomplishment of the
interim repair specified by paragraph C.(4) of the Accomplishment
Instructions of the applicable service bulletin, if the interim
repair has been accomplished prior to April 12, 2000 (the effective
date of AD 2000-05-04).
(3) Within 300 flight hours since the most recent HFEC
inspection accomplished in accordance with the applicable service
bulletin, if the most recent HFEC inspection has been accomplished
prior to April 12, 2000.
(4) Within 36 flight hours after April 12, 2000.
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.''
High Frequency Eddy Current Inspection
(g) Perform an HFEC inspection to detect cracks of the fuselage
skin aft of frame 54, between the airplane centerline and stringer
56R in the area of the VHF2 antenna, in accordance with Airbus
Service Bulletin A330-53-3094, Revision 02, dated May 28, 1998,
Revision 03, dated February 22, 2001, or Revision 04, dated July 23,
2001; or Service Bulletin A340-53-4105, Revision 02, dated May 25,
1998, Revision 03, dated February 22, 2001, or Revision 04, dated
July 23, 2001; at the applicable time specified by paragraph (g)(1)
or (g)(2) of this AD. Accomplishment of this inspection terminates
the requirements of paragraph (f) of this AD.
(1) For airplanes on which the interim repair specified by
paragraph C.(4) of the Accomplishment Instructions of the applicable
service bulletin has not been accomplished before April 12, 2000:
Prior to the accumulation of 900 total flight hours on the airplane,
or within 500 flight hours after April 12, 2000, whichever occurs
later. Thereafter, accomplish the follow-on actions of paragraph (h)
or (i) of this AD, as applicable.
(2) For airplanes on which the interim repair specified by
paragraph C.(4) of the Accomplishment Instructions of the applicable
service bulletin has been accomplished before April 12, 2000: Within
1,250 flight hours after accomplishment of the interim repair, or
within 500 flight hours after April 12, 2000, whichever occurs
later.
Repetitive Inspections
(h) If no crack is detected during the HFEC inspection required
by paragraph (g) of this AD, accomplish the repetitive inspections
required by paragraph (h)(1) or (h)(2) of this AD, as applicable,
until the terminating action required by paragraph (k) of this AD
has been done.
(1) For airplanes on which the interim repair specified by
paragraph C.(4) of the Accomplishment Instructions of Airbus Service
Bulletin A330-53-3094, Revision 02, dated May 28, 1998, Revision 03,
dated February 22, 2001, or Revision 04, dated July 23, 2001; or
Service Bulletin A340-53-4105, Revision 02, dated May 25, 1998,
Revision 03, dated February 22, 2001, or Revision 04, dated July 23,
2001; has not been accomplished before April 12, 2000: Accomplish
the actions specified by paragraphs (h)(1)(i) and (h)(1)(ii) of this
AD.
(i) Repeat the HFEC inspection specified by paragraph (g) at
intervals not to exceed 500 flight hours.
(ii) Within 300 flight hours after each HFEC inspection required
by this AD: Perform a detailed inspection (without removal of the
VHF2 antenna) of the fuselage skin aft of frame 54, between the
airplane centerline and stringer 56R in the area of the VHF2 antenna
to detect cracks, in accordance with the applicable service
bulletin. Thereafter, if no cracks are detected, repeat the detailed
inspection at intervals not to exceed 36 flight hours until
accomplishment of the next HFEC inspection required by paragraph
(h)(1)(i) of this AD.
(2) For airplanes on which the interim repair specified by
paragraph C.(4) of the Accomplishment Instructions of the applicable
service bulletin has been accomplished before April 12, 2000: Repeat
the HFEC inspection specified by paragraph (g) of this AD at
intervals not to exceed 1,250 flight hours.
Corrective Actions
(i) If any crack is detected during any inspection required by
paragraph (k), (l), or (m) of this AD, and the interim repair
specified by paragraph C.(4) of the Accomplishment Instructions of
Airbus Service Bulletin A330-53-3094, Revision 02, dated May 28,
1998, Revision 03, dated February 22, 2001, or Revision 04, dated
July 23, 2001; or Service Bulletin A340-53-4105, Revision 02, dated
May 25, 1998, Revision 03, dated February 22, 2001, or Revision 04,
dated July 23, 2001; has not been accomplished: Prior to further
flight, accomplish the actions specified by paragraph (i)(1) or
(i)(2) of this AD, as applicable.
(1) If only one crack is detected and that crack is 9.45 inches
or less, and is within the limits specified by the applicable
service bulletin: Install the interim repair specified in paragraph
C.(4) of the Accomplishment Instructions of the applicable service
bulletin. Thereafter, repeat the HFEC inspection specified by
paragraph (g) of this AD at intervals not to exceed 1,250 flight
[[Page 73929]]
hours, until the terminating action required by paragraph (k) of
this AD has been done.
Note 2: The interim repair referenced by this AD consists of
cutting out the cracked portion of the fuselage skin, and installing
a filler plate in the skin cutout, two doublers, and shims, as
described in paragraph C.(4) of the Accomplishment Instructions of
Airbus Service Bulletin A330-53-3094, Revision 02, dated May 28,
1998, Revision 03, dated February 22, 2001, or Revision 04, dated
July 23, 2001 (for Model A330 series airplanes); or Airbus Service
Bulletin A340-53-4105, Revision 02, dated May 25, 1998, Revision 03,
dated February 22, 2001, or Revision 04, dated July 23, 2001 (for
Model A340 series airplanes).
Note 3: Accomplishment of the interim repair in accordance with
paragraph 4.3 of Airbus Industrie All Operator Telex (AOT) 53-10,
dated September 24, 1997, is acceptable for compliance with the
requirements of paragraph (i)(1) of this AD.
(2) If any crack is detected that is longer than 9.45 inches, or
is outside the limits specified by the service bulletin, or if more
than one crack is detected: Repair in accordance with a method
approved by 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).
(j) If any crack is detected during any inspection required by
paragraph (f), (g), or (h) of this AD, and the interim repair
specified by paragraph C.(4) of the Accomplishment Instructions of
Airbus Service Bulletin A330-53-3094, Revision 02, dated May 28,
1998, Revision 03, dated February 22, 2001, or Revision 04, dated
July 23, 2001; or Airbus Service Bulletin A340-53-4105, Revision 02,
dated May 25, 1998, Revision 03, dated February 22, 2001, or
Revision 04, dated July 23, 2001; has been accomplished: Prior to
further flight, repair in accordance with a method approved by the
Manager, International Branch, ANM-116; or the DGAC (or its
delegated agent).
New Requirements of This AD
Terminating Action
(k) Within 18 months after the effective date of this AD: Do the
actions specified in either paragraph (k)(1) or (k)(2).
Accomplishment of either action terminates the repetitive
inspections required by paragraphs (f), (g), (h) and (i)(1) of this
AD.
(1) Reinforce the fuselage skin between FR54 and FR55 in the
area of the VHF2 antenna, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A330-53-3097, Revision 02,
dated November 21, 2000 (for Model A330 series airplanes); or A340-
53-4108, Revision 02, dated December 6, 2000 (for Model A340 series
airplanes); as applicable.
(2) Relocate the VHF2 antenna between stringer 51 and stringer
52, in accordance with Airbus Service Bulletin A330-53-3112 (for
Model A330 series airplanes) or A340-53-4124 (for Model A340 series
airplanes), both dated February 15, 2001; as applicable.
(l) Work done before the effective date of this AD in accordance
with an applicable source listed in Table 2 of this AD is acceptable
for compliance with the corresponding requirements of paragraph (k)
of this AD.
Table 2.--Credit for Prior Modification
----------------------------------------------------------------------------------------------------------------
Model Service information Revision Date
----------------------------------------------------------------------------------------------------------------
A330-300........................ Airbus Service Bulletin Original................. July 29, 1998.
A330-53-3097.
A330-300, A340.................. Airbus production (done in production)
Modification 46025.
A340............................ Airbus Service Bulletin Original................. July 31, 1998.
A340-53-4108.
----------------------------------------------------------------------------------------------------------------
Alternative Methods of Compliance
(m)(1) In accordance with 14 CFR 39.19, the Manager,
International Branch, ANM-116, is authorized to approve alternative
methods of compliance for this AD.
(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
(n) The subject of this AD is addressed in French airworthiness
directives 2001-040(B) and 2001-041(B), both dated January 24, 2001.
Material Incorporated by Reference
(o) Unless otherwise specified in this AD, the actions must be
done in accordance with the service information listed in Table 3 of
this AD, as applicable.
Table 3.--Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
Airbus Service Bulletin Revision level Date
----------------------------------------------------------------------------------------------------------------
A330-53-3094............................. 02.......................... May 28, 1998.
A330-53-3094............................. 03.......................... February 22, 2001.
A330-53-3094............................. 04.......................... July 23, 2001.
A330-53-3097............................. 02.......................... November 21, 2000.
A330-53-3112............................. Original.................... February 15, 2001.
A340-53-4105............................. 02.......................... May 25, 1998.
A340-53-4105............................. 03.......................... February 22, 2001.
A340-53-4105............................. 04.......................... July 23, 2001.
A340-53-4108............................. 02.......................... December 6, 2000.
A340-53-4124............................. Original.................... February 15, 2001.
----------------------------------------------------------------------------------------------------------------
(1) The incorporation by reference of the service information
listed in Table 4 of this AD is approved by the Director of the
Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part
51.
Table 4.--Material Newly Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
Airbus Service Bulletin Revision level Date
----------------------------------------------------------------------------------------------------------------
A330-53-3094............................. 03.......................... February 22, 2001.
A330-53-3094............................. 04.......................... July 23, 2001.
A330-53-3097............................. 02.......................... November 21, 2000.
A330-53-3112............................. Original.................... February 15, 2001.
[[Page 73930]]
A340-53-4105............................. 03.......................... February 22, 2001.
A340-53-4105............................. 04.......................... July 23, 2001.
A340-53-4108............................. 02.......................... December 6, 2000.
A340-53-4124............................. Original.................... February 15, 2001.
----------------------------------------------------------------------------------------------------------------
(2) The incorporation by reference of the service information
listed in Table 5 of this AD was approved previously by the Director
of the Federal Register as of April 12, 2000 (65 FR 12075, March 8,
2000).
Table 5.--Material Previously Incorporated by Reference
------------------------------------------------------------------------
Revision
Airbus Service Bulletin level Date
------------------------------------------------------------------------
A330-53-3094.................. 02 May 28, 1998.
A340-53-4105.................. 02 May 25, 1998.
------------------------------------------------------------------------
(3) Copies may be obtained from Airbus, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France. Copies may be inspected at
the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW.,
Renton, Washington; or at the National Archives and Records
Administration (NARA). For information on the availability of this
material at NARA, call (202) 741-6030, or go to https://
www.archives.gov/federal_register/code_of_federal_regulations/
ibr_locations.html.
Issued in Renton, Washington, on December 2, 2005.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-23901 Filed 12-13-05; 8:45 am]
BILLING CODE 4910-13-P
