[Federal Register Volume 61, Number 166 (Monday, August 26, 1996)]
[Rules and Regulations]
[Pages 43650-43652]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-21458]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 95-NM-263-AD; Amendment 39-9724; AD 96-17-14]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A300 B2 and B4 Series
Airplanes, Excluding Model A300-600 Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment supersedes an existing airworthiness directive
(AD), applicable to certain Airbus Model A300 B2 and B4 series
airplanes, that currently requires repetitive visual inspections to
detect cracks in the forward intermediate section skin at frame 30A
where it joins stringer 30, and repair, if necessary. This amendment
adds a requirement for eddy current inspection(s) to detect cracks of
the outer skin of the fuselage; accomplishment of this inspection
terminates the repetitive visual inspections. This amendment also
requires repair of any cracked area and modification of the structure
at certain frames. This amendment is prompted by in-service experience
which has identified fatigue cracks in this area. The actions specified
by this AD are intended to prevent fatigue cracking, which could result
in rapid decompression of the airplane.
DATES: Effective September 30, 1996.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of September 30, 1996.
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: Tim Backman, Aerospace Engineer,
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (206)
227-2797; fax (206) 227-1149.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) by superseding AD 90-11-09,
[[Page 43651]]
amendment 39-6611 (55 FR 21185, May 23, 1990), which is applicable to
certain Airbus Model A300 B2 and B4 series airplanes, was published in
the Federal Register on April 30, 1996 (61 FR 18995). That action
proposed to continue to require repetitive detailed visual inspections
to detect cracks of the forward intermediate section skin of the
fuselage at the junction of frame 30A and stringer 30. However, that
action also proposed to add a requirement to accomplish eddy current
inspections to detect cracks of the outer skin of the fuselage at
frames 28A and 30A above stringer 30. Accomplishment of this inspection
action would constitute terminating action for the currently-required
repetitive detailed visual inspections. The action also proposed to
require the repair of any cracked area, and modification of the
structure at frames 28A and 30A between stringer 27 and 30 (left- and
right-hand).
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the two comments received.
Both commenters support the proposed rule.
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 as proposed.
Cost Impact
There are approximately 24 Airbus Model A300 B2 and B4 series
airplanes, excluding Model A300-600 series airplanes, of U.S. registry
that will be affected by this proposed AD.
The detailed visual inspections that are currently required by AD
90-11-09 take approximately 1 work hour per airplane to accomplish, at
an average labor rate of $60 per work hour. Based on these figures, the
cost impact on U.S. operators of the currently required detailed visual
inspections is estimated to be $1,440, or $60 per airplane, per
inspection cycle.
The eddy current inspection that is required by this new AD action
will take approximately 1 work hour per airplane to accomplish, at an
average labor rate of $60 per work hour. Based on these figures, the
cost impact on U.S. operators of the eddy current inspection
requirements of this AD is estimated to be $1,440, or $60 per airplane,
per inspection cycle.
The cost impact figures discussed above are 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.
Regulatory Impact
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 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by removing amendment 39-6611 (55 FR
21185, May 23, 1990), and by adding a new airworthiness directive (AD),
amendment 39-9724, to read as follows:
96-17-14 Airbus Industrie: Amendment 39-9724. Docket 95-NM-263-AD.
Supersedes AD 90-11-09, Amendment 39-6611.
Applicability: Model A300 B2 and B4 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 (f) 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.
Note 2: Airbus Model A300-600 series airplanes are not subject
to this AD.
Compliance: Required as indicated, unless accomplished
previously.
To prevent fatigue cracking, which could result in rapid
decompression of the airplane, accomplish the following:
(a) For airplanes on which Airbus All Operators Telex (AOT) 53/
90/01, dated April 12, 1990 has been accomplished: Prior to the
accumulation of 18,000 total landings or 24,000 total hours time-in-
service, whichever occurs first, or within 100 landings after June
11, 1990 (the effective date of AD 90-11-09, amendment 39-6611),
whichever occurs later, perform a detailed visual inspection to
detect cracks of the forward intermediate section skin of the
fuselage at the junction of frame 30A and stringer 30, in accordance
with Airbus All Operators Telex 53/90/01, dated April 12, 1990.
(1) If no cracks are detected, repeat the detailed visual
inspection thereafter at intervals not to exceed 2,000 landings
until the requirements of paragraph (b) of this AD are accomplished.
(2) If any crack is detected, prior to further flight, repair it
in accordance with the AOT. Prior to the accumulation of 15,000
landings or 20,000 total hours time-in-service, whichever occurs
first, after the crack is repaired repeat the detailed visual
inspection at an interval not to exceed 2,000 landings until the
requirements of paragraph (b) of this AD are accomplished.
(b) For all airplanes: Perform an eddy current inspection to
detect cracks of the outer skin of the fuselage at frames 28A and
30A above stringer 30, in accordance with Airbus Service Bulletin
A300-53-283, Revision 2, dated March 17, 1994, at the time specified
in either paragraph (b)(1) or (b)(2) of this AD, as applicable.
Accomplishment of the eddy current inspection terminates the
repetitive visual inspection requirements of paragraph (a) of this
AD.
(1) For airplanes on which the requirements of paragraph (a) of
this AD have been initiated: Perform the eddy current inspection
prior to the accumulation of 2,000 landings since the last
inspection performed in accordance with paragraph (a) of this AD, or
within 100 landings after the effective date of this AD, whichever
occurs later.
(2) For airplanes other than those identified in paragraph
(b)(1) of this AD: Perform the eddy current inspection at the later
of the times specified in paragraph (b)(2)(i) or (b)(2)(ii):
(i) Prior to the accumulation of 14,100 total landings or 22,000
total flight hours after the
[[Page 43652]]
effective date of this AD, whichever occurs first; or
(ii) Within 100 landings after the effective date of this AD.
(c) If no crack is detected during the eddy current inspection
required by paragraph (b) of this AD, repeat the eddy current
inspection thereafter at intervals not to exceed 3,000 landings.
(d) If any crack is detected during any eddy current inspection
required by this AD, prior to further flight, repair it in
accordance with Airbus All Operators Telex 53/90/01, dated April 12,
1990, or Airbus Service Bulletin A300-53-283, Revision 2, dated
March 17, 1994. After accomplishing the repair, within 15,000
landings or 20,000 flight hours after repair, whichever occurs
first, modify the structure at frames 28A and 30A between stringers
27 and 30 (left- and right-hand), in accordance with Airbus Service
Bulletin A300-53-285, Revision 1, dated November 22, 1993.
Accomplishment of this reinforcement constitutes terminating action
for this AD.
(e) Except for airplanes on which the repair required by
paragraph (d) of this AD has been accomplished: Modify the structure
at frames 28A and 30A between stringers 27 and 30 (left- and right-
hand), in accordance with Airbus Service Bulletin A300-53-285,
Revision 1, dated November 22, 1993, at the later of the times
specified in paragraphs (e)(1) or (e)(2) of this AD. Accomplishment
of this modification constitutes terminating action for the eddy
current inspection requirements of paragraph (c) of this AD.
(1) Prior to the accumulation of 25,000 total landings or 40,000
total flight hours, whichever occurs first.
(2) Within 1,000 landings after the effective date of this AD.
(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,
FAA, Transport Airplane Directorate. Operators shall submit their
requests through an appropriate FAA Principal Maintenance Inspector,
who may add comments and then send it to the Manager,
Standardization Branch, ANM-113.
Note 3: 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 actions shall be done in accordance with one of the
following Airbus service documents, which contain the specified list
of effective pages:
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Service document referenced and Revision level shown
date Page No. on page- Date shown on page
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All Operators Telex (AOT) 53/90/01 1, 2-................. Original-............. April 12, 1990.
April 12, 1990-.
Service Bulletin A300-53-283, 1-17-................. 2..................... March 17, 1994.
Revision 2, March 17, 1994.
Service Bulletin A300-53-285, 1-3, 6, 13, 14, 18, 1..................... November 22, 1993. -
Revision 1, November 22, 1993. 20, 29-31, 35, 36,
51, 52, 57, 58, 61,
62, 71, 72, 75, 76,
107, 108, 111, 112,
115-120.
- 4, 5, 7-12, 15-17, 19, Original.............. August 19, 1992.
21-28, 32-34, 37-50,
53-56, 59, 60, 63-70,
73, 74, 77-106, 109,
110, 113, 114, 121.
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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 September 30, 1996.
Issued in Renton, Washington, on August 16, 1996.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 96-21458 Filed 8-23-96; 8:45 am]
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