[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
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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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