[Federal Register Volume 61, Number 109 (Wednesday, June 5, 1996)]
[Rules and Regulations]
[Pages 28497-28498]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-13798]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 95-NM-161-AD; Amendment 39-9644; AD 96-12-02]
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 adopts a new airworthiness directive (AD),
applicable to certain Airbus Model A300 B2 and B4 series airplanes,
that requires measurements of the thickness of the inner skin of the
longitudinal lap joint from the inside of the fuselage at certain
stringers. This amendment also requires inspections to detect stress
corrosion cracking in the subject area, and repair, if necessary. This
amendment is prompted by reports of stress corrosion cracking found in
the skin at the longitudinal lap joint at certain stringers of the
fuselage, which was caused by the increased stress level in the subject
area when it was reworked beyond certain limits. The actions specified
by this AD are intended to prevent such stress corrosion cracking
which, if not detected and corrected in a timely manner, could result
in rapid depressurization of the airplane.
DATES: Effective July 10, 1996.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of July 10, 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) to include an airworthiness
directive (AD) that is applicable to certain Airbus Model A300 B2 and
B4 series airplanes was published in the Federal Register on February
28, 1996 (61 FR 7444). That action proposed to require measurements of
the thickness of the inner skin of the longitudinal lap joint from the
inside of the fuselage at certain stringers using the ultrasonic
thickness measurement method. That action also proposed to require high
frequency eddy current (HFEC) inspections to detect cracking in the
subject area, 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 two comments received.
Support for the Proposal
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
The FAA estimates that 17 airplanes of U.S. registry will be
affected by this AD, that it will take approximately 32 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 $32,640, or $1,920 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.
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 adding the following new
airworthiness directive:
96-12-02 Airbus Industrie: Amendment 39-9644. Docket 95-NM-161-AD.
Applicability: Model A300 B2 and B4 series airplanes,
manufacturer serial numbers 003 through 156 inclusive; on which
Airbus Modification 2611 has not been installed; 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 (c) 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
[[Page 28498]]
been eliminated, the request should include specific proposed
actions to address it.
Note 2: Model A300-600 series airplanes are not subject to the
requirements of this AD.
Compliance: Required as indicated, unless accomplished
previously.
To prevent stress corrosion cracking in the longitudinal lap
joints of the fuselage, which could result in rapid depressurization
of the airplane, accomplish the following:
Note 3: Any of the inspections and measurements required by this
AD that were performed before the effective date of this AD in
accordance with Airbus All Operator Telex (AOT) 53-05 (original
issue), dated August 16, 1995, are considered acceptable for
compliance with the applicable requirements of this AD.
(a) Within 60 days after the effective date of this AD,
accomplish paragraphs (a)(1) and (a)(2) of this AD in accordance
with Airbus All Operator Telex (AOT) 53-05, Revision 1, dated August
16, 1993.
(1) Measure the thickness of the inner skin of the longitudinal
lap joint from the inside of the fuselage at stringer 57 between
frames 65 and 72 using the ultrasonic thickness measurement method,
in accordance with the AOT. If the thickness is less than or equal
to the limits specified in the AOT, prior to further flight, repair
the longitudinal lap joint in accordance with a method approved by
the Manager, Standardization Branch, ANM-113, FAA, Transport
Airplane Directorate.
(2) Perform a high frequency eddy current (HFEC) inspection to
detect cracking of the longitudinal lap joint at stringer 57 between
frames 65 and 72, in accordance with the AOT. If any cracking is
detected, prior to further flight, repair the longitudinal lap joint
in accordance with a method approved by the Manager, Standardization
Branch, ANM-113.
(b) Within 6 months after the effective date of this AD,
accomplish paragraphs (b)(1) and (b)(2) of this AD in accordance
with Airbus AOT 53-05, Revision 1, dated August 16, 1993.
(1) Measure the thickness of the inner skin of the longitudinal
lap joint from the inside of the fuselage at stringer 52 (left-and
right-hand) between frames 58 and 65 using the ultrasonic thickness
measurement method, in accordance with the AOT. If the thickness is
less than or equal to the limits specified in the AOT, prior to
further flight, repair the longitudinal lap joint in accordance with
a method approved by the Manager, Standardization Branch, ANM-113.
(2) Perform a HFEC inspection to detect cracking of the
longitudinal lap joint at stringer 52 (left- and right-hand) between
frames 58 and 65, in accordance with the AOT. If any cracking is
detected, prior to further flight, repair the longitudinal lap joint
in accordance with a method approved by the Manager, Standardization
Branch, ANM-113.
(c) 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 send
it to the Manager, Standardization Branch, ANM-113.
Note 4: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Standardization Branch, ANM-113.
(d) 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.
(e) The measurements and inspections shall be done in accordance
with Airbus All Operator Telex (AOT) 53-05, Revision 1, dated August
16, 1993. 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.
(f) This amendment becomes effective on July 10, 1996.
Issued in Renton, Washington, on May 28, 1996.
Bill R. Boxwell,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 96-13798 Filed 6-4-96; 8:45 am]
BILLING CODE 4910-13-P
