AD 2001-06-10

[Federal Register Volume 66, Number 63 (Monday, April 2, 2001)]
[Rules and Regulations]
[Pages 17490-17491]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 01-7699]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-105-AD; Amendment 39-12157; AD 2001-06-10]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 B4-601, A300 B4-603, 
A300 B4-620, A300 B4-605R, A300 B4-622R, and A300 F4-605R Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to all Airbus Model A300 B4-601, A300 B4-603, A300 B4-620, 
A300 B4-605R, A300 B4-622R, and A300 F4-605R airplanes. This AD 
requires repetitive high frequency eddy current (HFEC) or rototest 
inspections to detect cracking in the area surrounding the frame feet 
attachment holes between fuselage frames (FR) 41 and FR46; installation 
of new fasteners for certain airplanes; and follow-on corrective 
actions, if necessary. This AD is prompted by issuance of mandatory 
continuing airworthiness information by a foreign civil airworthiness 
authority. The actions specified by this AD are intended to prevent 
cracking of the center section of the fuselage, which could result in 
rupture of the frame foot and reduced structural integrity of the 
airplane.

DATES: Effective May 7, 2001.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of May 7, 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: Norman B. Martenson, Manager, 
International Branch, ANM-116, 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 all Airbus Model A300-600 series 
airplanes was published in the Federal Register on May 16, 2000 (65 FR 
31113). That action proposed to require repetitive high frequency eddy 
current (HFEC) or rototest inspections to detect cracking in the area 
surrounding the frame feet attachment holes between fuselage frames 
(FR) 41 and FR46; installation of new fasteners for certain airplanes; 
and follow-on corrective actions, if necessary.

Comments

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

Request To Extend Grace Period

    The commenters state that the 1,000-flight-cycle ``grace period'' 
specified for the initial inspection is unreasonably short. The 
commenters state that the airplane on which cracks were found is an 
exceptional example that does not realistically represent normal 
airplane utilization. That airplane had accumulated 26,200 flight 
cycles and 32,160 flight hours. The commenter notes that its own fleet 
has no airplane with more than 13,600 total flight cycles--about half 
the total flight cycles on the airplane on which the cracks were found. 
The commenter states that the 1,000-flight-cycle inspection 
requirement, combined with the specialized support required for any 
repair, will require special unscheduled visits to the heavy 
maintenance base. The commenter estimates that inspection costs will 
exceed $830,000, excluding any repair action.
    The FAA infers that the commenters request an extension of the 
``grace period.'' The FAA does not concur. Since the issuance of the 
service bulletin, the manufacturer has reported in-service findings of 
cracks found on airplanes near the threshold proposed in the Notice of 
Proposed Rulemaking. Although there is no damage tolerance 
justification for any grace period related to the identified unsafe 
condition, a grace period of 1,000 flight cycles is necessary to 
provide operators sufficient time to order the kits and plan the 
inspection for airplanes close to or exceeding the threshold as of the 
effective date of the AD. In light of the recent findings, no extension 
of the grace period is warranted.

Explanation of Change in Applicability of the AD

    Since the proposed AD was issued, the Direction Geneale de 
l'Aviation Civile (DGAC), which is the airworthiness authority for 
France, has revised its parallel airworthiness directive to exclude 
Airbus Model A300 F4-622R airplanes from the applicability. Because 
those airplanes are not subject to the unsafe condition identified in 
this AD, the FAA has accordingly revised the applicability of this 
final rule to exclude them.

Change to Note Reference

    Additionally, Note 3 of the AD has been revised to refer to the 
revised French airworthiness directive described previously.

Conclusion

    After careful review of the available data, including the comments 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule with the changes described 
previously. The FAA has determined that these changes will neither 
increase the economic burden on any operator nor increase the scope of 
the AD.

Cost Impact

    The FAA estimates that 75 airplanes of U.S. registry will be 
affected by this AD, that it will take approximately 6 work hours per 
airplane to accomplish the required inspections, 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 $27,000, or $360 
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.

[[Page 17491]]

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 adding the following new 
airworthiness directive:

2001-06-10  Airbus Industrie: Amendment 39-12157. Docket 2000-NM-
105-AD.

    Applicability: All Model A300 B4-601, A300 B4-603, A300 B4-620, 
A300 B4-605R, A300 B4-622R, and A300 F4-605R 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 (e) 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 prevent cracking of the center section of the fuselage, which 
could result in rupture of the frame foot and reduced structural 
integrity of the airplane, accomplish the following:

High Frequency Eddy Current (HFEC) or Rototest Inspection

    (a) Perform a HFEC or rototest inspection to detect cracking in 
the area surrounding the frame feet attachment holes between 
fuselage frames (FR) 41 and FR46 from stringers 24 to 28, left-and 
right-hand sides, in accordance with Airbus Service Bulletin A300-
53-6122, dated February 9, 2000, at the time specified in paragraph 
(a)(1) or (a)(2), as applicable.
    (1) For airplanes on which Task 53-15-54 in Maintenance Review 
Board Document (MRBD), Revision 3, dated April 1998, has NOT been 
accomplished as of the effective date of this AD: Perform the 
inspection at the later of the times specified in paragraphs 
(a)(1)(i) and (a)(1)(ii) of this AD.
    (i) Prior to the accumulation of the total flight-cycle or 
flight-hour threshold, whichever occurs first, specified in 
paragraph 1.E. (``Compliance'') of the service bulletin; or
    (ii) Within the applicable grace period specified in paragraph 
1.E. (``Compliance'') of the service bulletin.
    (2) For airplanes on which Task 53-15-54 in Maintenance Review 
Board Document (MRBD), Revision 3, dated April 1998, has been 
accomplished as of the effective date of this AD: Perform the next 
repetitive inspection at the later of the times specified in 
paragraphs (a)(2)(i) and (a)(2)(ii) of this AD.
    (i) Within the flight-cycle or flight-hour interval, whichever 
occurs first, specified in paragraph 1.E. (``Compliance'') of the 
service bulletin, following the latest inspection accomplished in 
accordance with the MRBD; or
    (ii) Within the grace period specified in paragraph 1.E. 
(``Compliance'') of the service bulletin.
    (b) For airplanes on which no cracking is detected during the 
inspection required by paragraph (a) of this AD, prior to further 
flight, install new fasteners as applicable, in accordance with 
Airbus Service Bulletin A300-53-6122, dated February 9, 2000; and 
repeat the inspection required by paragraph (a) of this AD 
thereafter at intervals not to exceed the applicable intervals 
specified in paragraph 1.E. (``Compliance'') of the service 
bulletin.

Corrective Actions

    (c) For airplanes on which cracking is detected during any 
inspection required by this AD: Prior to further flight, except as 
required by paragraph (d) of this AD, accomplish corrective actions 
(e.g., performing rotating probe inspections, reaming out cracks, 
cold working fastener holes, and installing oversized fasteners) in 
accordance with Airbus Service Bulletin A300-53-6122, dated February 
9, 2000. Repeat the inspection required by paragraph (a) of this AD 
thereafter at intervals not to exceed the applicable intervals 
specified in paragraph 1.E. (``Compliance'') of the service 
bulletin.
    (d) If cracking is detected during any inspection required by 
this AD, and the service bulletin specifies to contact the 
manufacturer for an appropriate corrective action: 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 (DGAC) (or its 
delegated agent).

Alternative Methods of Compliance

    (e) 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 2: 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

    (f) 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

    (g) Except as required by paragraph (d) of this AD, the actions 
must be done in accordance with Airbus Service Bulletin A300-53-
6122, dated February 9, 2000. 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 3: The subject of this AD is addressed in French 
airworthiness directive 2000-060-303(B) R1, dated July 12, 2000.

Effective Date

    (h) This amendment becomes effective on May 7, 2001.

    Issued in Renton, Washington, on March 22, 2001.
Vi L. Lipski,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 01-7699 Filed 3-30-01; 8:45 am]
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