[Federal Register Volume 65, Number 46 (Wednesday, March 8, 2000)]
[Rules and Regulations]
[Pages 12075-12077]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-5332]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 99-NM-241-AD; Amendment 39-11613; AD 2000-05-04]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A330 and A340 Series
Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment adopts a new airworthiness directive (AD),
applicable to certain Airbus Model A330 and A340 series airplanes, that
requires repetitive inspections to detect cracking of the fuselage skin
in the area of the VHF2 antenna, and repair, if necessary. This
amendment also provides for optional terminating action for the
repetitive inspections. This amendment is prompted by issuance of
mandatory continuing airworthiness information by a foreign civil
airworthiness authority. The actions specified by this AD are intended
to detect and correct such cracking, which could result in cabin
depressurization of the airplane.
DATES: Effective April 12, 2000.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of April 12, 2000.
ADDRESSES: The service information referenced in this AD may be
obtained from Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707
Blagnac Cedex, France. This information may be examined at the Federal
Aviation Administration (FAA), Transport Airplane Directorate, Rules
Docket, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of
the Federal Register, 800 North Capitol Street, NW., suite 700,
Washington, DC.
FOR FURTHER INFORMATION CONTACT: Norman B. Martenson, Manager,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601
[[Page 12076]]
Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 227-
2110; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) to include an airworthiness
directive (AD) that is applicable to certain Airbus Model A330 and A340
series airplanes was published in the Federal Register on December 30,
1999 (64 FR 73441). That action proposed to require repetitive
inspections to detect cracking of the fuselage skin in the area of the
VHF2 antenna, and repair, if necessary. That action also proposed to
provide for optional terminating action for the repetitive inspections.
Comments
Interested persons have been afforded an opportunity to participate
in the making of this amendment. No comments were submitted in response
to the proposal or the FAA's determination of the cost to the public.
Conclusion
The FAA has determined that air safety and the public interest
require the adoption of the rule as proposed.
Cost Impact
None of the airplanes affected by this action are on the U.S.
Register. All airplanes included in the applicability of this rule
currently are operated by non-U.S. operators under foreign registry;
therefore, they are not directly affected by this AD action. However,
the FAA considers that this rule is necessary to ensure that the unsafe
condition is addressed in the event that any of these subject airplanes
are imported and placed on the U.S. Register in the future.
Should an affected airplane be imported and placed on the U.S.
Register in the future, it will require approximately 6 work hours to
accomplish the required inspections, at an average labor rate of $60
per work hour. Based on these figures, the cost impact of this AD will
be $360 per airplane, per inspection cycle.
Should an operator elect to accomplish the optional terminating
action rather than continue the repetitive inspections, it will take
approximately 112 work hours per airplane to accomplish the
modification, at an average labor rate of $60 per work hour. Based on
these figures, the cost impact of this optional terminating action is
estimated to be $6,720 per airplane.
Regulatory Impact
The regulations adopted herein 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. Therefore, it
is determined that this final rule does not have federalism
implications under Executive Order 13132.
For the reasons discussed above, I certify that this action (1) is
not a ``significant regulatory action'' under Executive Order 12866;
(2) is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979); and (3) will not have a
significant economic impact, positive or negative, on a substantial
number of small entities under the criteria of the Regulatory
Flexibility Act. A final evaluation has been prepared for this action
and it is contained in the Rules Docket. A copy of it may be obtained
from the Rules Docket at the location provided under the caption
ADDRESSES.
List of Subjects
14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration amends part 39 of
the Federal Aviation Regulations (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. Section 39.13 is amended by adding the following new
airworthiness directive:
2000-05-04 Airbus: Amendment 39-11613. Docket 99-NM-241-AD.
Applicability: Model A330 and A340 series airplanes,
certificated in any category; except those on which Airbus
production modification 46025 is installed or on which Airbus
Service Bulletin A330-53-3097, Revision 01, dated May 21, 1999 (for
Model A330 series airplanes), or Service Bulletin A340-53-4108,
Revision 01, dated May 21, 1999 (for Model A340 series airplanes),
has been accomplished.
Note 1: This AD applies to each airplane identified in the
preceding applicability provision, regardless of whether it has been
otherwise modified, altered, or repaired in the area subject to the
requirements of this AD. For airplanes that have been modified,
altered, or repaired so that the performance of the requirements of
this AD is affected, the owner/operator must request approval for an
alternative method of compliance in accordance with paragraph (g) of
this AD. The request should include an assessment of the effect of
the modification, alteration, or repair on the unsafe condition
addressed by this AD; and, if the unsafe condition has not been
eliminated, the request should include specific proposed actions to
address it.
Compliance: Required as indicated, unless accomplished
previously.
To detect and correct cracking of the fuselage skin in the area
of the VHF2 antenna, which could result in cabin depressurization of
the airplane, accomplish the following:
Detailed Visual Inspection
(a) At the latest of the times specified in paragraphs (a)(1),
(a)(2), (a)(3), and (a)(4) of this AD, as applicable: Perform a
detailed visual 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 (for Model A330 series airplanes), or Service
Bulletin A340-53-4105, Revision 02, dated May 25, 1998 (for Model
A340 series airplanes) (hereinafter referred to as the applicable
service bulletin). Thereafter, if no cracks are detected, repeat the
detailed visual inspection every 36 flight hours until
accomplishment of the high frequency eddy current (HFEC) inspection
required by paragraph (b) 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 2.C.(4) of the applicable
service bulletin, if the interim repair has been accomplished prior
to the effective date of this AD.
(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 the effective date of this AD.
(4) Within 36 flight hours after the effective date of this AD.
Note 2: For the purposes of this AD, a detailed visual
inspection is defined as: ``An intensive visual examination of a
specific structural area, system, installation, or assembly to
detect damage, failure, or irregularity. Available lighting is
normally supplemented with a direct source of good lighting at
intensity deemed appropriate by the inspector. Inspection aids such
as mirror, magnifying lenses, etc., may be used. Surface cleaning
and elaborate access procedures may be required.''
High Frequency Eddy Current Inspection
(b) Perform a high frequency eddy current (HFEC) inspection to
detect cracks of the fuselage skin aft of frame 54, between the
[[Page 12077]]
airplane centerline and stringer 56R in the area of the VHF2
antenna, in accordance with the applicable service bulletin, at the
applicable time specified by paragraph (b)(1) or (b)(2) of this AD.
Accomplishment of this inspection terminates the requirements of
paragraph (a) of this AD.
(1) For airplanes on which the interim repair specified by
paragraph 2.C.(4) of the applicable service bulletin has not been
accomplished: Prior to the accumulation of 900 total flight hours on
the airplane, or within 500 flight hours after the effective date of
this AD, whichever occurs later. Thereafter, accomplish the follow-
on actions of paragraph (c) or (d) of this AD, as applicable.
(2) For airplanes on which the interim repair specified by
paragraph 2.C.(4) of the applicable service bulletin has been
accomplished: Within 1,250 flight hours after accomplishment of the
interim repair, or within 500 flight hours after the effective date
of this AD, whichever occurs later.
Repetitive Inspections
(c) If no crack is detected during the HFEC inspection required
by paragraph (b) of this AD, accomplish the repetitive inspections
required by paragraph (c)(1) or (c)(2) of this AD, as applicable.
(1) For airplanes on which the interim repair specified by
paragraph 2.C.(4) of the applicable service bulletin has not been
accomplished, accomplish the actions specified by paragraphs
(c)(1)(i) and (c)(1)(ii) of this AD.
(i) Repeat the HFEC inspection specified by paragraph (b) at
intervals not to exceed 500 flight hours.
(ii) Within 300 flight hours after each HFEC inspection required
by this AD: Perform a detailed visual 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
visual inspection every 36 flight hours until accomplishment of the
next HFEC inspection required by paragraph (c)(1)(i) of this AD.
(2) For airplanes on which the interim repair specified by
paragraph 2.C.(4) of the applicable service bulletin has been
accomplished, repeat the HFEC inspection specified by paragraph (b)
of this AD at intervals not to exceed 1,250 flight hours.
Corrective Actions
(d) If any crack is detected during any inspection required by
paragraph (a), (b), or (c) of this AD, and the interim repair
specified by paragraph 2.C.(4) of the applicable service bulletin
has not been accomplished: Prior to further flight, accomplish the
actions specified by paragraph (d)(1) or (d)(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
2.C.(4) of the applicable service bulletin. Thereafter, repeat the
HFEC inspection specified by paragraph (b) of this AD at intervals
not to exceed 1,250 flight hours.
Note 3: 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 2.C.(4) of the applicable service bulletin.
Note 4: 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 (d)(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, FAA,
Transport Airplane Directorate; or the Direction Generale de
l'Aviation Civile (DGAC) (or its delegated agent). For a repair
method to be approved by the Manager, International Branch, ANM-116,
as required by this paragraph, the Manager's approval letter must
specifically reference this AD.
(e) If any crack is detected during any inspection required by
paragraph (a), (b), or (c) of this AD and the interim repair
specified by paragraph 2.C.(4) of the applicable service bulletin
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). For a repair method to be
approved by the Manager, International Branch, ANM-116, as required
by this paragraph, the Manager's approval letter must specifically
reference this AD.
(f) Accomplishment of the modification as described in Airbus
Service Bulletin A330-53-3097, Revision 01, dated May 21, 1999 (for
Model A330 series airplanes), or Service Bulletin A340-53-4108,
Revision 01, dated May 21, 1999 (for Model A340 series airplanes),
terminates the repetitive inspections required by paragraphs (a),
(b), and (c) of this AD.
Note 5: Accomplishment of Airbus production modification 46025,
or the modification as described in Airbus Service Bulletin A330-53-
3097, dated July 29, 1998 (for Model A330 series airplanes), or
Service Bulletin A340-53-4108, dated July 31, 1998 (for Model A340
series airplanes), also constitutes terminating action for the
repetitive inspections required by paragraphs (a), (b), and (c) of
this AD.
Alternative Methods of Compliance
(g) An alternative method of compliance or adjustment of the
compliance time that provides an acceptable level of safety may be
used if approved by the Manager, International Branch, ANM-116.
Operators shall submit their requests through an appropriate FAA
Principal Maintenance Inspector, who may add comments and then send
it to the Manager, International Branch, ANM-116.
Note 6: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the International Branch, ANM-116.
Special Flight Permits
(h) Special flight permits may be issued in accordance with
sections 21.197 and 21.199 of the Federal Aviation Regulations (14
CFR 21.197 and 21.199) to operate the airplane to a location where
the requirements of this AD can be accomplished.
Incorporation by Reference
(i) Except as provided by paragraphs (d)(2) and (e) of this AD,
the actions shall be done in accordance with Airbus Service Bulletin
A330-53-3094, Revision 02, dated May 28, 1998; or Airbus Service
Bulletin A340-53-4105, Revision 02, dated May 25, 1998; as
applicable. This incorporation by reference was approved by the
Director of the Federal Register in accordance with 5 U.S.C. 552(a)
and 1 CFR part 51. Copies may be obtained from Airbus Industrie, 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 Office of the Federal
Register, 800 North Capitol Street, NW., suite 700, Washington, DC.
Note 7: The subject of this AD is addressed in French
airworthiness directives 1998-192-071(B)R1 (for Model A330 series
airplanes) and 1998-193-089(B)R1 (for Model A340 series airplanes),
both dated March 24, 1999.
(j) This amendment becomes effective on April 12, 2000.
Issued in Renton, Washington, on February 29, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 00-5332 Filed 3-7-00; 8:45 am]
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