Airworthiness Directives; Airbus Model A330 and A340 Series Airplanes

[Federal Register Volume 64, Number 218 (Friday, November 12, 1999)]
[Rules and Regulations]
[Pages 61485-61487]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-29327]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NM-184-AD; Amendment 39-11412; AD 99-23-16]
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 detailed visual inspections to detect cracking of 
the vertical flange of the inboard Z-stiffeners of the centerline panel 
of the fuselage belly fairing; and corrective actions, 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 fatigue cracking of the vertical flange of the 
inboard Z-stiffeners of the centerline panel of the fuselage belly 
fairing, which could result in reduced structural integrity of the 
belly fairing.

DATES: Effective December 17, 1999.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of December 17, 1999.

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 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 September 10, 
1999 (64 FR 49110). That action proposed to require repetitive detailed 
visual inspections to detect cracking of the vertical flange of the 
inboard Z-stiffeners of the centerline panel of the fuselage belly 
fairing; and corrective actions, 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. Due consideration has been given to 
the comment received.
    One commenter, an operator, states that it will have the 
terminating modification incorporated prior to delivery of its 
airplanes.

Conclusion

    After careful review of the available data, including the comment 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule as proposed.

[[Page 61486]]

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 would require approximately 1 work hour to 
accomplish the required inspection, at an average labor rate of $60 per 
work hour. Based on these figures, the cost impact of this AD would be 
$60 per airplane, per inspection cycle.
    Should an operator elect to accomplish the optional terminating 
action provided by this AD, it would require approximately 7 work hours 
to accomplish the optional terminating action, at an average labor rate 
of $60 per work hour. Required parts would cost approximately $2,350 
per airplane. Based on these figures, the cost impact of the optional 
terminating action is estimated to be $2,770 per airplane.

Regulatory Impact

    The regulations adopted herein will not have substantial direct 
effects 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, in 
accordance with Executive Order 12612, it is determined that this final 
rule does not have sufficient federalism implications to warrant the 
preparation of a Federalism Assessment.
    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 in 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:

99-23-16 Airbus Industrie: Amendment 39-11412. Docket 99-NM-184-AD.

    Applicability: Model A330 and A340 series airplanes; except 
those airplanes on which Airbus Modification 42605, or Airbus 
Service Bulletin A330-53-3019 (for Model A330 series airplanes) or 
A340-53-4028 (for Model A340 series airplanes) has been 
accomplished; certificated in any category.

    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 (c) 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 fatigue cracking of the vertical flange of 
the inboard Z-stiffeners of the centerline panel of the fuselage 
belly fairing, which could result in reduced structural integrity of 
the belly fairing, accomplish the following:

Repetitive Detailed Visual Inspections

    (a) Prior to the accumulation of 5,500 total flight cycles, or 
within 500 flight hours after the effective date of this AD, 
whichever occurs later, perform a detailed visual inspection to 
detect cracking of the vertical flange of the inboard Z-stiffeners 
of the centerline panel of the fuselage belly fairing, in accordance 
with Airbus Service Bulletin A330-53-3020 (for Model A330 series 
airplanes) or A340-53-4029 (for Model A340 series airplanes); each 
dated November 30, 1995; as applicable.

    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.''

    (1) If no cracking is detected, repeat the inspection thereafter 
at intervals not to exceed 5,500 flight cycles, until the 
requirements of paragraph (b) of this AD are accomplished.

Corrective Actions

    (2) If any cracking is detected during any inspection required 
by this AD, prior to further flight, modify the vertical flange of 
both inboard Z-stiffeners of the centerline panel of the fuselage 
belly fairing and re-inspect the modified area to determine if 
cracking has been eliminated, in accordance with Airbus Service 
Bulletin A330-53-3019 (for Model A330 series airplanes) or A340-53-
4028 (for Model A340 series airplanes); each dated November 30, 
1995; as applicable.
    (i) If all cracking is not eliminated after accomplishment of 
the modification, prior to further flight, repair in accordance with 
a method approved by either 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.
    (ii) If all cracking is eliminated after the accomplishment of 
the modification, no further action is required by this AD.

Optional Terminating Action

    (b) Modification of the vertical flange of both inboard Z-
stiffeners of the centerline panel of the fuselage belly fairing in 
accordance with Airbus Service Bulletin A330-53-3019 (for Model A330 
series airplanes) or A340-53-4028 (for Model A340 series airplanes); 
each dated November 30, 1995; as applicable; constitutes terminating 
action for the requirements of this AD.

Alternative Methods of Compliance

    (c) 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 3: 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

    (d) Special flight permits may be issued in accordance with 
sections 21.197 and 21.199

[[Page 61487]]

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

    (e) The inspections and modification shall be done in accordance 
with Airbus Service Bulletin A330-53-3020, dated November 30, 1995; 
Airbus Service Bulletin A340-53-4029, dated November 30, 1995; 
Airbus Service Bulletin A330-53-3019, dated November 30, 1995; and 
Airbus Service Bulletin A340-53-4028, dated November 30, 1995; 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 4: The subject of this AD is addressed in French 
airworthiness directives 96-056-029 (B) and 96-057-042 (B); each 
dated March 13, 1996.

    (f) This amendment becomes effective on December 17, 1999.

    Issued in Renton, Washington, on November 3, 1999.
D.L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 99-29327 Filed 11-10-99; 8:45 am]
BILLING CODE 4910-13-P

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