[Federal Register Volume 59, Number 88 (Monday, May 9, 1994)]
[Unknown Section]
[Page 0]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 94-10507]
[[Page Unknown]]
[Federal Register: May 9, 1994]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 93-NM-55-AD; Amendment 39-8904; AD 94-09-15]
Airworthiness Directives; Airbus Industrie Model A300 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 series airplanes, that
currently requires repetitive inspections of the aft bulkhead to detect
cracks, and repair, if necessary. This amendment requires expansion of
the inspection area and modification of the aft pressure bulkhead,
which terminates the inspection requirements. This amendment is
prompted by a tear down inspection conducted by the manufacturer, which
revealed fatigue cracking in additional areas of the aft pressure
bulkhead. The actions specified by this AD are intended to prevent
potential loss of cabin pressurization.
DATES: Effective June 8, 1994.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of June 8, 1994.
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: Stephen Slotte, Aerospace Engineer,
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (206)
227-2797; fax (206) 227-1320.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations by superseding AD 84-08-03, Amendment 39-4848 (49
FR 16762, April 20, 1984), which is applicable to certain Airbus Model
A300 series airplanes, was published in the Federal Register on
September 3, 1993 (58 FR 46914). The action proposed to supersede AD
84-08-03 to require expansion of the inspection area to include areas 3
and 4 of the aft pressure bulkhead, and repair, if necessary; and
modification of the aft pressure bulkhead, which will terminate the
inspection requirements of this AD. This modification entails
increasing the strength of the aft pressure bulkhead by attaching
additional stiffeners. (This modification was optional in AD 84-08-03,
Amendment 39-4848.)
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the three comments received.
All of the commenters support the proposed rule.
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.
The FAA estimates that 6 airplanes of U.S. registry will be
affected by this AD, that it will take approximately 738 work hours per
airplane to accomplish the required actions, and that the average labor
rate is $55 per work hour. Required parts will cost approximately
$4,000 per airplane. Based on these figures, the total cost impact of
the AD on U.S. operators is estimated to be $267,540, or $44,590 per
airplane.
The total 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 14 CFR part
39 of the Federal Aviation Regulations as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. App. 1354(a), 1421 and 1423; 49 U.S.C.
106(g); and 14 CFR 11.89.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by removing amendment 39-4848 (49 FR
16762, April 20, 1984), and by adding a new airworthiness directive
(AD), amendment 39-8904, to read as follows:
94-09-15 Airbus Industrie: Amendment 39-8904. Docket 93-NM-55-AD.
Supersedes AD 84-08-03, Amendment 39-4848.
Applicability: Model A300 B2-1A, B2-1C, B2-203, B2K-3C, B4-2C,
B4-103, and B4-203 series airplanes, on which Airbus Modification
2476/D1842 and Airbus Modification 2476/D1869 have not been
accomplished; certificated in any category.
Compliance: Required as indicated, unless accomplished
previously.
To prevent loss of cabin pressurization, accomplish the
following:
Note 1: Paragraph (a) of this AD restates the requirement for an
initial and repetitive inspections contained in paragraph A. of AD
84-08-03. Therefore, for operators who have previously accomplished
at least the initial inspection in accordance with AD 84-08-03,
paragraph (a) of this AD requires that the next scheduled inspection
be performed within the 6,000 flight cycles after the last
inspection performed in accordance with paragraph A. of AD 84-08-03.
(a) Prior to the accumulation of 12,000 total flight cycles, or
within 180 days after June 11, 1984 (the effective date of AD 84-08-
03, Amendment 39-4848), whichever occurs later, inspect the aft
bulkhead in areas 1 and 2 to detect fatigue cracking, in accordance
with Airbus Service Bulletin A300-53-152, Revision 1, dated January
30, 1981; or Revision 4, dated March 13, 1992. -
(1) If no crack is detected, repeat the inspection thereafter at
intervals not to exceed 6,000 flight cycles.
(2) If any crack is detected as a result of any inspection
required by paragraph (a) of this AD, prior to further flight,
repair the crack, in accordance with Airbus Service Bulletin A300-
53-152, Revision 1, dated January 30, 1981; or Revision 4, dated
March 13, 1992. Subsequent to repair, repeat the inspection
thereafter at intervals not to exceed 6,000 flight cycles.
(b) Prior to the accumulation of 17,000 total flight cycles, or
within 1 year after June 11, 1984 (the effective date of AD 84-08-
03, Amendment 39-4848), whichever occurs later, accomplish Airbus
Modification 2476/D1869, in accordance with Airbus Service Bulletin
A300-53-122, Revision 2, dated January 30, 1981.
(c) Prior to the accumulation of 32,000 total flight cycles, or
within 1 year after the effective date of this AD, whichever occurs
later, inspect the aft pressure bulkhead in areas 3 and 4 to detect
fatigue cracking, in accordance with Airbus Service Bulletin A300-
53-152, Revision 4, dated March 13, 1992.
(1) If no crack is detected, repeat the inspection at intervals
not to exceed 9,000 flight cycles.
(2) If any crack is detected as a result of any inspection
required by paragraph (b) of this AD, prior to further flight,
repair the crack in accordance with Airbus Structural Repair Manual
51-41-30. Subsequent to repair, repeat the inspection thereafter at
intervals not to exceed 9,000 flight cycles.
(d) Within 6 years after the effective date of this AD,
accomplish Airbus Modification 2476/D1842, in accordance with Airbus
Service Bulletin A300-53-121, Revision 3, dated January 30, 1981.
Accomplishment of this modification constitutes terminating action
for the inspections required by this AD.
(e) Accomplishment of Airbus Modification 2476/D1842, in
accordance with Airbus Service Bulletin A300-53-121, Revision 3,
dated January 30, 1981, constitutes terminating action for the
inspection requirements 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 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
Federal Aviation Regulations (FAR) 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
the following Airbus service bulletins, as applicable, which contain
the specified effective pages:
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Service bulletin Revision level shown
referenced and date Page No. on page Date shown on page
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A300-53-121, Revision 1-4................... 3..................... January 30, 1981.
3, January 30, 1981.
2, 7, 10-15, 17....... 2..................... December 30, 1980.
6, 8, 9, 16, 18....... 1..................... September 30, 1980.
5..................... Original.............. April 10, 1980.
A300-53-152, Revision 1-2................... 1..................... January 30, 1981.
1, January 30, 1981.
3-18.................. Original.............. October 24, 1980.
A300-53-152, revision 1-10, 18.............. 4..................... March 13, 1992.
4, March 13, 1992.
11-17, 19-21.......... 3..................... (These pages are not dated.)
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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 June 8, 1994.
Issued in Renton, Washington, on April 26, 1994.
James V. Devany,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 94-10507 Filed 5-6-94; 8:45 am]
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