Airworthiness Directives; Airbus Model A330 and A340 Series Airplanes

[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]
BILLING CODE 4910-13-U

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