[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]
BILLING CODE 4910-13-U
