[Federal Register Volume 62, Number 7 (Friday, January 10, 1997)]
[Rules and Regulations]
[Pages 1383-1384]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-536]
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Rules and Regulations
Federal Register
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This section of the FEDERAL REGISTER contains regulatory documents
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to and codified in the Code of Federal Regulations, which is published
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Federal Register / Vol. 62, No. 7 / Friday, January 10, 1997 / Rules
and Regulations
[[Page 1383]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 92-NM-225-AD; Amendment 39-9882; AD 97-01-11]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A300 Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; correction.
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SUMMARY: This document corrects information in an existing
airworthiness directive (AD) that is applicable to certain Airbus Model
A320 series. The AD requires detailed visual inspections to detect
cracking of a certain fuselage frame, and repair, if necessary; and
provides for an optional terminating action for the repetitive
inspections. The AD was prompted by reports of a fatigue crack found
initiating at hole ``I'' of frame 47 on two of these airplanes. The
actions specified by the AD are intended to detect and correct such
fatigue cracking, which could result in reduced structural integrity of
the airplane. This action corrects the applicability of the currently
existing AD to cite an airplane model that was inadvertently omitted.
DATES: Effective February 10, 1997.
The incorporation by reference of certain publications listed in
the regulations was previously approved by the Director of the Federal
Register as of November 4, 1996 (61 FR 50988, September 30, 1996).
FOR FURTHER INFORMATION CONTACT: Charles D. Huber, Aerospace Engineer,
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (206)
227-2589; fax (206) 227-1149.
SUPPLEMENTARY INFORMATION: On September 19, 1996, the FAA issued AD 96-
20-02, amendment 39-9768 (61 FR 50988, September 30, 1996) that is
applicable to certain Airbus Model A300 series airplanes. That AD
requires repetitive detailed visual inspections to detect cracking of
fuselage frame 47, and repair, if necessary. It also provides for an
optional terminating action for the repetitive inspections.
That action was prompted by reports of a fatigue crack found
initiating at hole ``I'' of frame 47 on two of these airplanes. The
actions specified by that AD are intended to detect and correct such
fatigue cracking, which could result in reduced structural integrity of
the airplane.
Actions Since Issuance of AD 96-20-02
Recently, the FAA has become aware of an incongruity between the
stated applicability for AD 96-20-02 and certain of the requirements of
that AD. Specifically, the applicability statement for AD 96-20-02 was
published as follows:
``Applicability: Model A300 B2-1C, B2K-3C, B2-203, B4-2C, and
B4-103, series airplanes, on which Modification 2626 has not been
installed; certificated in any category.''
Paragraph (a)(3) of that AD, however, states:
``(3) For Model A300 B4-203 series airplanes: Perform the
inspection prior to the accumulation of 14,100 total landings, or
within 50 landings after the effective date of this AD, whichever
occurs later.''
Because Model A300 B4-203 series airplanes were not cited in the
applicability statement of AD 96-20-02, the only U.S. operator of those
models was unsure whether it was required to perform the actions stated
in paragraph (a)(3) of the AD. That operator contacted the FAA to
resolve this issue.
The FAA acknowledges the discrepancy between the applicability of
AD 96-20-02 and the applicability of paragraph (a)(3) of that AD. A
typographical error on FAA's part resulted in the Model A300 B4-203
being omitted inadvertently from the applicability statement of that
AD. In all other respects, the AD is correct as published.
FAA's Determination
Although the single U.S. operator of Model A300 B4-203 series
airplanes has advised the FAA that it will comply with AD 96-20-02
within the compliance time that is stated in that AD, the FAA has
determined that it is appropriate to take action to correct AD 96-20-02
to include the Model A300 B4-203 in the applicability statement. Since
those airplanes are subject to the unsafe condition addressed by that
AD, correction of the applicability of the AD is necessary to ensure
that any airplane that is imported and placed on the U.S. Register in
the future will be inspected as required.
Corrections Made to the Current AD
This action revises the applicability of AD 96-20-02 by correcting
the applicability statement to include Model A300 B4-203 series
airplanes.
In making this correction, the formatting of the text of the AD has
been revised somewhat: Paragraph (a)(3) that appeared in AD 96-20-02
has been designated as new paragraph (b); it pertains only to the
initial inspection action required of Model A300 B4-203 series
airplanes. Accordingly, all other paragraphs of the AD have been
redesignated to account for the new paragraph (b).
Since this action only clarifies the applicability of an existing
rule, it has no additional economic impact and imposes no additional
burden on any person. Therefore, notice and public procedures hereon
are unnecessary.
Cost Impact
The economic analysis that was iterated in the preamble to AD 96-
20-02 correctly included affected Model A300 B4-203 series airplanes in
its figures. This correction of the previously-issued AD poses no new,
additional economic burden on any operator.
However, for the convenience of all affected operators, the cost
impact information is repeated below:
The FAA estimates that 20 airplanes of U.S. registry will be
affected by this AD. (Of this number, 2 are Model A300 B4-203 series
airplanes.) It will take approximately 10 work hours per airplane to
accomplish the required actions, at an average labor rate of $60 per
work hour. Based on these figures, the cost impact of the AD on U.S.
operators is estimated to be $12,000, or $600 per airplane.
[[Page 1384]]
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 Correction
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 39-9768 (61 FR
50988, September 30, 1996), and by adding a new airworthiness directive
(AD), amendment 39-9882, to read as follows:
97-01-11 Airbus Industrie: Amendment 39-9882. Docket 92-NM-225-AD.
Supersedes AD 96-20-02, amendment 39-9768.
Applicability: Model A300 B2-1C, B2K-3C, B2-203, B4-2C, B4-103,
and B4-203 series airplanes, on which Modification 2626 has not been
installed; certificated in any category.
Compliance: Required as indicated, unless accomplished
previously.
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.
Compliance: Required as indicated, unless accomplished
previously.
To prevent fatigue cracking, which could result in reduced
structural integrity of the airplane, accomplish the following:
(a) For Model A300 B2-1C, B2K-3C, B2-203, B4-2C, and B4-103
series airplanes: Perform a detailed visual inspection to detect
cracking of the fuselage, frame 47 at hole ``I'', in accordance with
Airbus All Operator Telex (AOT) 53-02, dated November 2, 1992, at
the times specified in paragraphs (a)(1) or (a)(2), as applicable.
(1) For Model A300 B2-1C, B2K-3C, and B2-203 series airplanes:
Perform the inspection prior to the accumulation of 15,000 total
landings, or within 50 landings after November 4, 1996 (the
effective date of AD 96-20-02, amendment 39-9768), whichever occurs
later.
(2) For Model A300 B4-2C and B4-103 series airplanes: Perform
the inspection prior to the accumulation of 18,700 total landings,
or within 50 landings after November 4, 1996, whichever occurs
later.
(b) For Model A300 B4-203 series airplanes: Prior to the
accumulation of 14,100 total landings, or within 50 landings after
the effective date of this AD, whichever occurs later, perform a
detailed visual inspection to detect cracking of the fuselage, frame
47 at hole ``I'', in accordance with Airbus All Operator Telex (AOT)
53-02, dated November 2, 1992.
(c) If no crack is detected during the inspection required by
paragraph (a) or (b) of this AD, repeat the detailed visual
inspection at intervals not to exceed 200 landings.
(d) If a crack is detected during any inspection required by
paragraph (a), (b), or (c) of this AD, prior to further flight,
repair in accordance with either paragraph (d)(1), (d)(2), or (d)(3)
of this AD:
(1) Repair in accordance with a method approved by the Manager,
Standardization Branch, ANM-113, FAA, Transport Airplane
Directorate; or
(2) Repair in accordance with crack repair procedures specified
in Airbus A300 Service Bulletin 53-265, Revision 2, dated March 10,
1992; or
(3) Repair in accordance with crack repair procedures specified
in Airbus Service Bulletin A300-53-299, dated December 14, 1993.
(e) Conducting a repetitive Rototest inspection of hole ``I'' in
accordance with Airbus A300 Service Bulletin 53-265, Revision 2,
dated March 10, 1992, or Airbus Service Bulletin A300-53-299, dated
December 14, 1993, constitutes terminating action for the detailed
visual inspections required by this AD. If any crack is found during
a Rototest inspection, prior to further flight, repair it in
accordance with that service bulletin.
(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
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 visual inspection shall be done in accordance with
Airbus All Operator Telex (AOT) 53-02, dated November 2, 1992. This
incorporation by reference was approved previously by the Director
of the Federal Register, in accordance with 5 U.S.C.
552(a) and 1 CFR part 51, as of November 4, 1996 (61 FR 50988,
September 30, 1996). 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 February 10, 1997.
Issued in Renton, Washington, on January 3, 1997.
S.R. Miller,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 97-536 Filed 1-9-97; 8:45 am]
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