[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]
BILLING CODE 4910-13-U
