[Federal Register Volume 63, Number 122 (Thursday, June 25, 1998)]
[Rules and Regulations]
[Pages 34576-34578]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-16472]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 95-NM-78-AD; Amendment 39-10614; AD 98-13-23]
RIN 2120-AA64
Airworthiness Directives; Airbus 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 A300-600 series airplanes, that
requires inspections to detect corrosion and cracking of the lower
horizontal stabilizer cutout longeron, the corner fitting, the skin
strap, and the outer skin; and repair, if necessary. This amendment is
prompted by cracking found at the lower corner of the horizontal
stabilizer cutout longeron during a full scale fatigue test. The
actions specified by this AD are intended to prevent such cracking,
which could result in reduced structural integrity of the horizontal-
stabilizer cutout longeron.
DATES: Effective July 30, 1998.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of July 30, 1998.
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: Norman B. Martenson, Manager,
International Branch, ANM-116 FAA, Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 227-
2110; fax (425) 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 A300-600
series airplanes was published in the Federal Register on December 12,
1995 (60 FR 63665). That action proposed to require repetitive visual
and eddy current inspections to detect corrosion and fatigue cracking
of the lower horizontal stabilizer cutout longeron, the corner fitting,
the skin strap, and the skin between FR87 and FR89 and between STGR24
and STGR27, left-hand and right-hand. That action also proposed to
require repetitive rotating probe inspections to detect cracks in the
fastener holes at the same locations; and repair or certain follow-on
actions, if necessary.
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
One commenter has no objection to the proposed rule.
Request to Revise Compliance Time to Permit ``Adjustment of Range''
One commenter, the manufacturer, requests that the compliance times
for the inspection threshold and the repetitive intervals proposed be
revised to follow the recommendations of the Airbus service bulletin
specified in the proposed rule. That service bulletin specifies that
inspection thresholds and intervals may be adjusted based on certain
average flight operations of the airplane. The commenter states that
this approach was approved by the Direction Generale de l'Aviation
Civile (DGAC), which is the airworthiness authority for France, in its
approval of the service bulletin.
The FAA does not concur that the compliance times should be
revised. As explained in the proposal, the FAA has determined that such
adjustments may not address the unsafe condition in a timely manner. In
developing appropriate compliance times for the proposed rule, the FAA
considered not only the manufacturer's recommendation, but the safety
implications involved with cracking of the horizontal stabilizer cutout
longeron and the number of landings that had been accumulated when
cracking was detected. Therefore, this AD does not permit such
adjustments, and no change to the compliance times of the final rule
has been made. However, operators may request approval of an adjustment
of the compliance time under the provisions of paragraph (f) of this
AD, provided that such adjustment provides an acceptable level of
safety.
Remove Touch-and-Go Landings From the Total Number of Landings
This same commenter requests that touch-and-go landings not be
included in calculating the total number of
[[Page 34577]]
airplane landings. The commenter points out that most of the relevant
fatigue parameters for touch-and-go flights are less significant than
for conditions of normal flight. Further, the commenter states that
including touch-and-go's in the total landing count for an individual
airplane is too conservative, considering the high penalty of counting
each touch-and-go.
The FAA does not concur. Fatigue cracking has been found at the
lower corner of the horizontal stabilizer cutout longeron. Since
fatigue cracking in that area is aggravated by landing, the FAA finds
that all touch-and-go landings must be counted in determining the total
number of landings between consecutive inspections.
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 2 Airbus Model A300-600 series airplanes of
U.S. registry will be affected by this AD, that it will take
approximately 268 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 $32,160, or $16,080 per airplane.
The cost impact figure discussed above is based on assumptions that
no operator has yet accomplished any of the proposed 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:
98-13-23 Airbus Industrie: Amendment 39-10614. Docket 95-NM-78-AD.
Applicability: Model A300-600 series airplanes on which Airbus
Modification No. 6146 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 use the authority
provided in paragraph (f) of this AD to request approval from the
FAA. This approval may address either no action, if the current
configuration eliminates the unsafe condition; or different actions
necessary to address the unsafe condition described in this AD. Such
a request should include an assessment of the effect of the changed
configuration on the unsafe condition addressed by this AD. In no
case does the presence of any modification, alteration, or repair
remove any airplane from the applicability of this AD.
Compliance: Required as indicated, unless accomplished
previously.
To prevent reduced structural integrity of the horizontal
stabilizer cutout longeron due to fatigue cracking, accomplish the
following:
(a) Prior to the accumulation of 18,000 total landings, or
within 2,000 landings after the effective date of this AD, whichever
occurs later: Perform a visual and an eddy current inspection to
detect cracks and/or corrosion of Areas 1 and 2 of the lower
horizontal stabilizer cutout longeron, as defined in Airbus Service
Bulletin A300-53-6042, Revision 1, dated February 20, 1995. Perform
the inspections in accordance with the service bulletin.
(b) Perform a visual and an eddy current inspection to detect
cracks and/or corrosion of Area 3 of the lower horizontal stabilizer
cutout longeron, as defined in Airbus Service Bulletin A300-53-6042,
Revision 1, dated February 20, 1995. Perform these inspections in
accordance with the service bulletin, at the later of the times
specified in paragraphs (b)(1) and (b)(2) of this AD.
(1) Prior to the accumulation of 24,000 total landings, but not
before the accumulation of 18,000 total landings; or
(2) Prior to the accumulation of 2,000 landings after the
effective date of this AD.
(c) If no cracking is detected during any inspection required by
this AD: Prior to further flight, cold work and ream the vacated
fastener holes, in accordance with Airbus Service Bulletin A300-53-
6042, Revision 1, dated February 20, 1995; and perform the
requirements of paragraph (c)(1) or (c)(2) of this AD, as
applicable.
(1) For airplanes on which no cracking is found in Area 1 or 2:
Repeat the inspections required by paragraph (a) of this AD
thereafter at intervals not to exceed 6,000 flight cycles.
(2) For airplanes on which no cracking is found in Area 3:
Perform the various follow-on actions in accordance with the service
bulletin. (The follow-on actions include installing a new corner
fitting, installing a new longeron, and performing a cold working
procedure.) After accomplishment of these follow-on actions, no
further action is required by this AD.
(d) If any cracking is detected during any inspection required
by this AD, perform the requirements of paragraph (d)(1) or (d)(2)
of this AD, as applicable.
(1) If any cracking is found in Area 1 or 3 that is within the
limits specified in Airbus Service Bulletin A300-53-6042, Revision
1, dated February 20, 1995: Prior to further flight, repair in
accordance with the service bulletin.
(2) If any cracking is found in Area 2, or if any cracking is
found in any area and that cracking is beyond the limits described
in Airbus Service Bulletin A300-53-6042, Revision 1, dated February
20, 1995: Prior to further flight, repair in accordance with a
method approved by the Manager, International Branch, ANM-116, FAA,
Transport Airplane Directorate.
(e) If any corrosion is detected during any inspection required
by this AD, prior to further flight, repair the corrosion in
accordance with Airbus Service Bulletin A300-53-6042, Revision 1,
dated February 20, 1995.
(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, International Branch, ANM-116.
Operators shall submit their requests through an appropriate FAA
Principal Maintenance Inspector, who may add comments and then send
it to the Manager, International Branch, ANM-116.
Note 2: Information concerning the existence of approved
alternative methods of
[[Page 34578]]
compliance with this AD, if any, may be obtained from the Manager,
International Branch, ANM-116.
(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) Except as provided by paragraph (d)(2) of this AD, the
actions shall be done in accordance with Airbus Service Bulletin
A300-53-6042, Revision 1, dated February 20, 1995. 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.
Note 3: The subject of this AD is addressed in French
airworthiness directive 94-269-171(B)R1, dated March 29, 1995.
(i) This amendment becomes effective on July 30, 1998.
Issued in Renton, Washington, on June 15, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 98-16472 Filed 6-24-98; 8:45 am]
BILLING CODE 4910-13-U
