AD 2001-08-06

[Federal Register Volume 66, Number 78 (Monday, April 23, 2001)]
[Rules and Regulations]
[Pages 20379-20380]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 01-9665]



[[Page 20379]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-223-AD; Amendment 39-12183; AD 2001-08-06]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 B4-620, A310-203, 
A310-221, and A310-222 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 A300 B4-620, A310-203, A310-221, and 
A310-222 series airplanes, that requires repetitive inspections of 
fuselage frame 07 in the upper frame section assemblies of the lateral 
cockpit windows, and corrective action, if necessary. Accomplishment of 
certain corrective actions extends the repetitive inspection interval. 
The actions specified by this AD are intended to detect and correct 
fatigue cracking in that area, which could result in reduced structural 
integrity of the airplane.

DATES: Effective May 29, 2001.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of May 29, 2001.

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: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, FAA, 1601 Lind Avenue, SW., Renton, 
Washington 98055-4056; telephone (425) 227-2125; 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 A300 B4-620, 
A310-203, A310-221, and A310-222 series airplanes was published in the 
Federal Register on January 9, 2001 (66 FR 1610). That action proposed 
to require repetitive inspections of fuselage frame 07 in the upper 
frame section assemblies of the lateral cockpit windows, and corrective 
action, if necessary. That action also proposed to require 
accomplishment of certain corrective actions, which would extend the 
repetitive inspection interval.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the single comment received.

Other Models Subject to Unsafe Condition

    The commenter, Airbus, advises that Model A300 B2 and A300 B4 
series airplanes are also subject to the unsafe condition identified by 
this AD. However, the area included in the inspection required by this 
AD is also included in the A300 Supplemental Structural Inspection 
Document (SSID). Airbus further advises that the Direction Generale de 
l'Aviation Civile (DGAC), which is the airworthiness authority for 
France, will mandate this inspection by a separate French airworthiness 
directive.
    The FAA acknowledges that, while there may be merit to the 
commenter's concerns, this AD is not the appropriate context in which 
to address those concerns. Adding airplanes to the applicability would 
alter the requirements of the proposed AD, so additional rulemaking 
would be required. The FAA finds that to delay this action would be 
inappropriate in light of the identified unsafe condition. No change to 
this final rule is necessary in this regard.

Change to Repair/Inspection Approval

    Paragraph (b) of the proposed AD would have required follow-on 
corrective actions to be accomplished in accordance with a method 
approved by the FAA. However the DGAC was inadvertently omitted as an 
additional acceptable approval source for the actions identified in 
paragraph (b). In light of the type of repair or inspection that would 
be required to address the identified unsafe condition, and in 
consonance with existing bilateral airworthiness agreements, the FAA 
has determined that, for this AD, a repair or inspection approved by 
either the FAA or the DGAC would be acceptable for compliance with this 
AD. Paragraph (b) of the final rule has been revised accordingly.

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 with the changes previously 
described.

Cost Impact

    The FAA estimates that 27 airplanes of U.S. registry will be 
affected by this AD, that it will take approximately 1 work hour per 
airplane to accomplish the inspection, and that the average labor rate 
is $60 per work hour. Based on these figures, the cost impact of the AD 
on U.S. operators is estimated to be $1,620, or $60 per airplane, per 
inspection cycle.
    The cost impact figure discussed above is based on assumptions that 
no operator has yet accomplished any of the requirements of this AD 
action, and that no operator would accomplish those actions in the 
future if this AD were not adopted. The cost impact figures discussed 
in AD rulemaking actions represent only the time necessary to perform 
the specific actions actually required by the AD. These figures 
typically do not include incidental costs, such as the time required to 
gain access and close up, planning time, or time necessitated by other 
administrative actions.

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 in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

[[Page 20380]]

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:

2001-08-06  Airbus Industrie: Amendment 39-12183. Docket 2000-NM-
223-AD.

    Applicability: Model A300 B4-620, A310-203, A310-221, and A310-
222 series airplanes; certificated in any category; as listed in 
Airbus Service Bulletin A300-53-6120 or A310-53-2109, both dated May 
5, 2000; excluding airplanes on which Airbus Modification 3632 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 (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 fuselage frame 07 in 
the upper frame section assembly of the lateral cockpit windows, 
which could result in reduced structural integrity of the airplane, 
accomplish the following:

Inspection and Corrective Actions

    (a) Before the accumulation of 25,000 total flight cycles, or 
within 3,000 flight cycles after the effective date of this AD, 
whichever occurs later: Perform a detailed visual inspection to 
detect cracking of fuselage frame 07 in the left and right upper 
frame section assemblies of the lateral cockpit windows, in 
accordance with Airbus Service Bulletin A300-53-6120 (for Model 
A300-600 series airplanes) or A310-53-2109 (for Model A310 series 
airplanes), both dated May 5, 2000; 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 found: Repeat the inspection thereafter at 
least every 7,000 flight cycles.
    (2) If any cracking is found and the cracking is only in ``area 
A,'' as depicted in view B of Figure 4 of the service bulletin: 
Before further flight, do the actions specified by either paragraph 
(a)(2)(i) or (a)(2)(ii) of this AD.
    (i) Do a temporary repair per the applicable service bulletin. 
Within 3,000 flight cycles thereafter, do a permanent repair per the 
applicable service bulletin. Within 32,000 flight cycles thereafter, 
except as required by paragraph (b) of this AD, repeat the 
inspection specified by paragraph (a) of this AD.
    (ii) Do a permanent repair per the applicable service bulletin. 
Within 32,000 flight cycles thereafter, except as required by 
paragraph (b) of this AD, repeat the inspection specified by 
paragraph (a) of this AD.
    (3) If any cracking is in ``area B,'' or in both ``area A'' and 
``area B'' as depicted in view B of Figure 4 of the service 
bulletin: Before further flight, do a permanent repair per the 
applicable service bulletin. Within 32,000 flight cycles thereafter, 
except as required by paragraph (b) of this AD, repeat the 
inspection specified by paragraph (a) of this AD.
    (b) If the service bulletin specifies to contact Airbus for 
further instructions for a repair or inspection: Prior to further 
flight, perform a repair or inspection per 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).

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 
Secs. 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

    (e) Except as required by paragraph (b) of this AD, the actions 
shall be done in accordance with Airbus Service Bulletin A300-53-
6120, dated May 5, 2000; or Airbus Service Bulletin A310-53-2109, 
dated May 5, 2000; 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 directive 2000-263-314(B), dated June 28, 2000.

Effective Date

    (f) This amendment becomes effective on May 29, 2001.

    Issued in Renton, Washington, on April 12, 2001.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 01-9665 Filed 4-20-01; 8:45 am]
BILLING CODE 4910-13-U