[Federal Register Volume 61, Number 190 (Monday, September 30, 1996)]
[Rules and Regulations]
[Pages 50988-50990]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-24654]


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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 92-NM-225-AD; Amendment 39-9768; AD 96-20-02]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 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 series airplanes, that requires 
detailed visual inspections to detect cracking of a certain fuselage 
frame, and repair, if necessary. This AD also provides for an optional 
terminating action for the repetitive inspections. This amendment is 
prompted by reports of a fatigue crack found initiating at hole ``I'' 
of frame 47 on two of these airplanes. The actions specified by this AD 
are intended to prevent such fatigue cracking, which could result in 
reduced structural integrity of the airplane.

DATES: Effective November 4, 1996.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of November 4, 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,

[[Page 50989]]

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: Phil Forde, Aerospace Engineer, 
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (206) 
227-2146; 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 A320 series 
airplanes was published in the Federal Register on April 12, 1993 (58 
FR 19068). That action proposed to require detailed visual inspections 
to detect cracking of a certain fuselage frame, and repair, if 
necessary. That action also proposed to provide for an optional 
terminating action for the repetitive inspection requirements.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comments received.

Support for the Proposal

    Two commenters support the proposed rule.

Request to Revise the Applicability of the Proposed Rule

    One commenter requests that the applicability of paragraphs (a)(2) 
and (a)(3) of the proposal be revised to include Model A300 B4-120, B4-
220, C4-203, and F4-203 series airplanes. The FAA does not concur. As 
of the effective date of this AD, those models are not type 
certificated for operation in the United States; further, the FAA 
cannot assume continued airworthiness responsibilities (via AD action) 
for airplanes that do not have a U.S. Type Certificate.

Request to Withdraw Proposed Rule

    The same commenter states that, since issuance of the NPRM, Airbus 
has issued Revision 3 of Airbus A300 Service Bulletin 53-265. The 
commenter points out that this revision no longer contains the 
inspection of the rear spar 47 lower flange at holes ``H'' and ``I'', 
as specified in Revision 2 of that service bulletin. This inspection 
has been transferred to Airbus Service Bulletin A300-53-299. The 
commenter also points out that Service Bulletin A300-53-299 cancels and 
supersedes Airbus Industrie All Operators Telex (AOT) 53-02, dated 
November 2, 1992 . (AOT 53-02 and Revision 2 of Service Bulletin 53-265 
are referenced in this AD as the appropriate source of service 
information.) The commenter also states that Revision 3 of Service 
Bulletin 53-265 has been incorporated in Revision 2 of the Airbus 
Industrie A300 Supplemental Structural Inspection Document (SSID); the 
procedures specified in the SSID are currently required by AD 96-13-11, 
amendment 39-9679 (61 FR 35122, July 5, 1996).
    From this comment the FAA infers that the commenter is requesting 
that the proposed AD be withdrawn. The FAA does not concur. The FAA 
acknowledges that the procedures specified in Revision 3 of Service 
Bulletin 53-265 and Service Bulletin A300-53-299 are incorporated in 
the Airbus A300 SSID. However, AD 96-13-11, which mandates the SSID 
program for U.S. operators, provides a ``grace period'' of one year to 
incorporate the SSID into the operator's maintenance program; the 
``grace period'' effectively delays initiation of the inspections by at 
least that amount of time. Additionally, Airbus Service Bulletin A300-
53-299 recommends inspection compliance times with additional ``grace 
periods'' for affected airplanes that have surpassed the number of 
flight cycles at which cracking is likely to initiate. Several 
airplanes already have accumulated as much as 8,000 flight cycles above 
that flight cycle threshold. In light of these items, and in 
consideration of the amount of time that has already elapsed since 
issuance of the original notice, the FAA has determined that the 
inspections required by this AD must be initiated as soon as 
practicable (as specified in the AD), and that further delay of this 
final rule action is not appropriate.

New Relevant Service Information

    Since issuance of the NPRM, Airbus has issued Service Bulletin 
A300-53-299, dated December 14, 1993. The rototest inspection in this 
service bulletin is identical to that described in Airbus Service 
Bulletin 53-265, Revision 1, dated March 10, 1992 (which was referenced 
in the NPRM as the appropriate source of service information). 
Therefore, the FAA has revised paragraph (d) of the final rule to 
include reference to Service Bulletin A300-53-299 as an additional 
source of service information for accomplishing the optional rototest 
inspection.
    Additionally, the FAA has determined that the crack repair 
procedures specified in Airbus Service Bulletin A300-53-299, dated 
December 14, 1993, and in Airbus Service Bulletin 53-265, Revision 1, 
dated March 10, 1992, are appropriate for repair cracks found during 
the visual inspection(s) required by paragraph (a) and (b). The FAA has 
revised paragraph (c) of the final rule to indicate this.

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 with the changes previously 
described. The FAA has determined that this change will neither 
increase the economic burden on any operator nor increase the scope of 
the AD.

Cost Impact

    The FAA estimates that 20 airplanes of U.S. registry will be 
affected by this AD, that it will take approximately 10 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 $12,000, or $600 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.
    The FAA has recently reviewed the figures it has used over the past 
several years in calculating the economic impact of AD activity. In 
order to account for various inflationary costs in the airline 
industry, the FAA has determined that it is necessary to increase the 
labor rate used in these calculations from $55 per work hour to $60 per 
work hour. The economic impact information, below, has been revised to 
reflect this increase in the specified hourly labor rate.

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)

[[Page 50990]]

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:

96-20-02 Airbus Industrie: Amendment 39-9768. Docket 92-NM-225-AD.

    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.

    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 (e) 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) 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), (a)(2), or (a)(3), 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 the effective date of this AD, 
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 the effective date of this AD, whichever 
occurs later.
    (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.
    (b) If no crack is detected during the inspection required by 
paragraph (a) of this AD, repeat the detailed visual inspection at 
intervals not to exceed 200 landings.
    (c) If a crack is detected during any inspection required by 
paragraph (a) or (b) of this AD, prior to further flight, repair in 
accordance with either paragraph (c)(1), (c)(2), or (c)(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.
    (d) 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, prior 
to further flight, repair it in accordance with that service 
bulletin.
    (e) 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.

    (f) 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.
    (g) 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 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.
    (h) This amendment becomes effective on November 4, 1996.

    Issued in Renton, Washington, on September 19, 1996.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 96-24654 Filed 9-27-96; 8:45 am]
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