AD Amdt-39-12298

[Federal Register Volume 66, Number 126 (Friday, June 29, 2001)]
[Rules and Regulations]
[Pages 34530-34532]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 01-16202]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-306-AD; Amendment 39-12298; AD 2000-03-20 R1]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 B4-601, B4-603, B4-
620, B4-605R, B4-622R, and F4-605R (Collectively Called A300-600) 
Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment revises an existing airworthiness directive 
(AD), applicable to all Airbus Model A300 B4-601, B4-603, B4-620, B4-
605R, B4-622R, and F4-605R (collectively called A300-600) series 
airplanes, that currently requires repetitive ultrasonic inspections to 
detect cracks on the forward fittings in the radius of frame 40 
adjacent to the tension bolts in the center section of the wings, and 
various follow-on actions. That AD was prompted by reports of cracking 
due to fatigue-related stress in the radius of frame 40 adjacent to the 
tension bolts at the center/outer wing junction. The actions specified 
by that AD are intended to detect and correct fatigue cracking on the 
forward fittings in the radius of frame 40 adjacent to the tension 
bolts in the center section of the wings, which could result in reduced 
structural integrity of the wings. This amendment removes airplanes 
from the applicability of the existing AD.

DATES: Effective August 3, 2001.
    The incorporation by reference of certain publications, as listed 
in the regulations, was approved previously by the Director of the 
Federal Register as of March 28, 2000 (65 FR 8642, February 22, 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 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) by revising AD 2000-03-20, 
amendment 39-11580 (65 FR 8642, February 22, 2000), which is applicable 
to Airbus Model A300 B4-601, B4-603, B4-620, B4-605R, B4-622R, and F4-
605R (collectively called A300-600) series airplanes, was published in 
the Federal Register on January 10, 2001 (66 FR 1919). The action 
proposed to continue to require repetitive ultrasonic inspections to 
detect cracks on the forward fittings in the radius of frame 40 
adjacent to the tension bolts in the center section of the wings, and 
various follow-on actions. The action also proposed to remove Model 
A300 F4-622R from the applicability of the existing AD.

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

    Since this AD merely deletes Model A300 F4-622R airplanes from the 
applicability of AD 2000-03-02, it adds no additional costs, and will 
require no additional work to be performed by affected operators. The 
current costs associated with this AD are reiterated in their entirety 
(as follows) for the convenience of affected operators:
    The FAA estimates that 35 airplanes of U.S. registry will be 
affected by this AD, that it will take approximately 2 work hours per 
airplane (1 work hour per side) to accomplish the required ultrasonic 
inspection, and that the average labor rate is $60 per work hour. Based 
on these figures, the cost impact of the required inspection on U.S. 
operators is estimated to be $4,200, or $120 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

[[Page 34531]]

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.

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 removing amendment 39-11580 (65 FR 
8642, February 22, 2000), and by adding a new airworthiness directive 
(AD), amendment 39-12298, to read as follows:

2000-03-20 R1  Airbus Industries: Amendment 39-12298. Docket 2000-
NM-306-AD. Revises AD 2000-03-20, Amendment 39-11580.

    Applicability: All Model A300 B4-601, B4-603, B4-620, B4-605R, 
B4-622R, and F4-605R series airplanes, certificated in any category.

    Note 1: This AD applies to each airplane identified in the 
preceding applicability provision, regardless of whether it has been 
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 (d)(1) 
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 on the forward fittings 
in the radius of frame 40 adjacent to the tension bolts in the 
center section of the wings, which could result in reduced 
structural integrity of the wings, accomplish the following:

Inspections and Corrective Actions

    (a) Perform an ultrasonic inspection to detect cracking on the 
forward fittings in the radius of frame 40 adjacent to the tension 
bolts in the center section of the wings, in accordance with Airbus 
Service Bulletin A300-57-6062, Revision 02, dated January 29, 1997, 
at the applicable time specified in either paragraph (a)(1) or 
(a)(2) of this AD.
    (1) For airplanes that have accumulated fewer than 9,100 total 
landings or 22,300 total flight hours as of March 28, 2000 (the 
effective date of AD 2000-03-20, amendment 39-11580): Inspect at the 
later of the times specified in either paragraph (a)(1)(i) or 
(a)(1)(ii) of this AD.
    (i) Prior to the accumulation of 7,250 total landings or 17,700 
total flight hours, whichever occurs first.
    (ii) Within 1,500 landings after March 28, 2000.
    (2) For airplanes that have accumulated 9,100 total landings or 
more and 22,300 total flight hours or more as of March 28, 2000: 
Inspect within 750 landings after March 28, 2000.

    Note 2: Inspections that were accomplished prior to March 28, 
2000, in accordance with Airbus Service Bulletin A300-57-6062, 
Revision 1, dated July 23, 1995, are considered acceptable for 
compliance with paragraph (a) of this AD.

    (b) If no crack is detected during the inspection required by 
paragraph (a) of this AD, repeat the ultrasonic inspection required 
by that paragraph thereafter at intervals not to exceed 6,500 
landings or 16,000 flight hours, whichever occurs first; in 
accordance with Airbus Service Bulletin A300-57-6062, Revision 02, 
dated January 29, 1997.
    (c) If any crack is detected during any inspection required by 
paragraph (a) or (b) of this AD, prior to further flight, install an 
access door, and perform an eddy current inspection to confirm the 
presence of a crack; in accordance with Airbus Service Bulletin 
A300-57-6062, Revision 02, dated January 29, 1997. Accomplishment of 
this eddy current inspection terminates the repetitive inspection 
requirement of paragraph (b) of this AD.
    (1) If no crack is detected during the eddy current inspection, 
repeat the eddy current inspection, in accordance with the service 
bulletin, thereafter at intervals not to exceed 6,500 landings or 
16,000 flight hours, whichever occurs first.
    (2) If any crack is detected during any eddy current inspection 
performed in accordance with paragraph (c) or (c)(1) of this AD, 
prior to further flight, blend out the crack and repeat the eddy 
current inspection in accordance with the service bulletin.
    (i) If the eddy current inspection performed after the blend-out 
shows that the crack has been removed, and if the blend-out is equal 
to or less than 50 millimeters (mm) long and equal to or less than 2 
mm deep, thereafter repeat the eddy current inspection at intervals 
not to exceed 2,800 landings or 7,000 flight hours, whichever occurs 
first.
    (ii) If the eddy current inspection performed after the blend-
out shows that the crack has not been removed, or if the blend-out 
is more than 50 mm long or more than 2 mm deep, prior to further 
flight, 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 (or its delegated 
agent).

Alternative Methods of Compliance

    (d)(1) 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.
    (2) Operators may request an extension to the compliance times 
of this AD in accordance with the ``adjustment-for-range'' formula 
found in Paragraph 1.B.(5) of Airbus Service Bulletin A300-57-6062, 
Revision 02, dated January 29, 1997; and provided in A300-600 
Maintenance Review Board, Section 5, Paragraph 5.4. The average 
flight time per flight cycle (landing) in hours used in this formula 
should be for an individual airplane. Average flight time for a 
group of airplanes may be used if all airplanes of the group have 
flight times differing by no more than 10 percent. If compliance 
times are based on the average flight time for a group of airplanes, 
the flight times for individual airplanes of the group must be 
included for FAA review.

    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

    (e) 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.

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Incorporation by Reference

    (f) Except as provided by paragraph (c)(2)(ii) of this AD, the 
actions shall be done in accordance with Airbus Service Bulletin 
A300-57-6062, Revision 02, dated January 29, 1997. This 
incorporation by reference was approved previously by the Director 
of the Federal Register as of March 28, 2000 (65 FR 8642, February 
22, 2000). 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 1995-063-177(B) R4, dated July 12, 2000.

Effective Date

    (g) This amendment becomes effective on August 3, 2001.


    Issued in Renton, Washington, on June 21, 2001.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 01-16202 Filed 6-28-01; 8:45 am]
BILLING CODE 4910-13-P