[Federal Register Volume 60, Number 227 (Monday, November 27, 1995)]
[Rules and Regulations]
[Pages 58213-58215]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-28798]



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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 95-NM-04-AD; Amendment 39-9436; AD 95-24-04]


Airworthiness Directives; Airbus Model A300 and A300-600 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 all Airbus Model A300 and A300-600 series airplanes, that 
requires repetitive eddy current inspections to detect cracks at the 
aft spar web of the wings, and repair, if necessary. This amendment is 
prompted by reports indicating that cracks have been found in the rear 
spar web of the wings between ribs 1 and 2 of an in-service airplane 
and during testing on the fatigue test wing; the cracking occurred due 
to fatigue-related high shear stress. The actions specified by this AD 
are intended to prevent such fatigue-related cracking, which could 
result in reduced structural integrity of the wing.

DATES: Effective December 27, 1995. -
    The incorporation by reference of certain publications listed in 
the 

[[Page 58214]]
regulations is approved by the Director of the Federal Register as of 
December 27, 1995.

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: Phil Forde, Aerospace Engineer, 
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (206) 
227-2146; fax (206) 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 and A300-600 
series airplanes was published in the Federal Register on May 4, 1995 
(60 FR 22011). That action proposed to require repetitive eddy current 
inspections to detect cracks at the aft spar web of the wings, and 
repair, if necessary. -
    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. -
    The commenter supports the proposed rule. -
    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. -
    The FAA estimates that 89 airplanes of U.S. registry will be 
affected by this AD, that it will take approximately 3 work hours per 
airplane to accomplish the required actions, 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 $16,020, or $180 per 
airplane. -
    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 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 USC 106(g), 40101, 40113, 44701.


Sec. 39.13  [Amended] -

    2. Section 39.13 is amended by adding the following new 
airworthiness directive:

95-24-04 Airbus Industrie: Amendment 39-9436. Docket 95-NM-04-AD.

    -Applicability: All Model A300 and Model A300-600 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 use the authority 
provided in paragraph (f) of this AD to request approval from the 
FAA. This approval may address either no action, if the current 
configuration eliminates the unsafe condition; or different actions 
necessary to address the unsafe condition described in this AD. Such 
a request should include an assessment of the effect of the changed 
configuration on the unsafe condition addressed by this AD. In no 
case does the presence of any modification, alteration, or repair 
remove any airplane from the applicability of this AD.
    -Compliance: Required as indicated, unless accomplished 
previously.
    -To prevent fatigue-related cracking in the rear spar web of the 
wings, which could result in reduced structural integrity of the 
wing, accomplish the following:
    -(a) For Model A300 B2 series airplanes: Prior to the 
accumulation of 18,000 total flight cycles or within 1,400 flight 
cycles after the effective date of this AD, whichever occurs later, 
perform a high frequency eddy current (HFEC) inspection to detect 
cracks at the aft spar web of the wings, in accordance with Airbus 
Service Bulletin A300-57-0213, dated August 12, 1994. Repeat the 
inspection thereafter at intervals not to exceed 5,000 flight 
cycles.
    -(b) For Model A300 B4-103, and B4-2C series airplanes: Prior to 
the accumulation of 19,000 total flight cycles or within 1,400 
flight cycles after the effective date of this AD, whichever occurs 
later, perform an HFEC inspection to detect cracks at the aft spar 
web of the wings, in accordance with Airbus Service Bulletin A300-
57-0213, dated August 12, 1994. Repeat the inspection thereafter at 
intervals not to exceed 6,000 flight cycles.
    -(c) For Model A300 B4-200 series airplanes: Prior to the 
accumulation of 17,000 total flight cycles or within 1,400 flight 
cycles after the effective date of this AD, whichever occurs later, 
perform an HFEC inspection to detect cracks at the aft spar web of 
the wings, in accordance with Airbus Service Bulletin A300-57-0213, 
dated August 12, 1994. Repeat the inspection thereafter at intervals 
not to exceed 5,000 flight cycles.
    -(d) For Model A300-600 B4-601, B4-603, B4-620, B4-622, B4-605R, 
B4-622R, and F4-605R series airplanes: Prior to the accumulation of 
21,600 flight cycles, perform an HFEC inspection to detect cracks at 
the aft spar web of the wings, in accordance with Airbus Service 
Bulletin A300-57-6059, dated August 12, 1994. Repeat the inspection 
thereafter at intervals not to exceed 5,700 flight cycles.
    -(e) If any crack is detected during any inspection required by 
this AD, prior to further flight, repair the crack in accordance 
with Airbus Service Bulletin A300-57-0213, dated August 12, 1994, or 
Airbus Service Bulletin A300-57-6059, dated August 12, 1994, as 
applicable; or in accordance with a method approved by the Manager, 
Standardization Branch, ANM-113, FAA, Transport Airplane 
Directorate.
    -(f) 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, Standardization Branch, ANM-113. 
Operators shall submit their requests through an appropriate FAA 
Principal Maintenance Inspector, who may add comments and then 

[[Page 58215]]

send it to the Manager, Standardization Branch, ANM-113.

    -Note 2: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Standardization Branch, ANM-113.

    -(g) 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.
    -(h) The inspections and repairs shall be done in accordance 
with Airbus Service Bulletin A300-57-0213, dated August 12, 1994, or 
Airbus Service Bulletin A300-57-6059, dated August 12, 1994, 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.
    (i) This amendment becomes effective on December 27, 1995.

    Issued in Renton, Washington, on November 9, 1995.
S. R. Miller,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 95-28798 Filed 11-24-95; 8:45 am]
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