[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]



=======================================================================
-----------------------------------------------------------------------

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.

-----------------------------------------------------------------------

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