[Federal Register Volume 62, Number 87 (Tuesday, May 6, 1997)]
[Rules and Regulations]
[Pages 24568-24570]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-11525]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 96-NM-60-AD; Amendment 39-10013; AD 97-10-01]
RIN 2120-AA64
Airworthiness Directives; Airbus Industrie Model A310 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 A310 series airplanes, that requires
repetitive inspections to detect discrepancies or damage of the steady
bearing assemblies of the flap transmission system, and replacement of
any discrepant or damaged assembly with a new, like assembly. This
amendment also requires eventual replacement of all the steady bearing
assemblies with new, improved assemblies, which terminates the
repetitive inspection requirements. This amendment is prompted by
reports of cracking of the hardened steel inner race, and broken or
missing inner races of the steady bearing assemblies. The actions
specified by this AD are intended to prevent such discrepancies and
damage of the shafts of the steady bearing assemblies, which could
cause the shafts to fail; failure of the steady bearing shafts during a
subsequent assymetric stop could result in an uncommanded assymetric
retraction of the flap, and subsequent reduced controllability of the
airplane.
DATES: Effective June 10, 1997.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of June 10, 1997.
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: Tom Groves, Aerospace Engineer,
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (206)
227-1503; 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 A310 series
airplanes was published in the Federal Register on January 14, 1997 (62
FR 1859). That action proposed to require repetitive visual inspections
to detect any discrepancy or damage to the steady bearing assemblies of
the flap transmission system, and replacement of any damaged or
discrepant assembly with a new, like assembly. That action also
proposed to require eventual
[[Page 24569]]
replacement of all steady bearing assemblies with the new, improved
assemblies, which terminates the repetitive inspection requirement.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the single comment received.
The commenter supports the proposed rule.
Conclusion
After careful review of the available data, including the comment
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 26 Airbus Model A310 series airplanes of
U.S. registry will be affected by this AD, that it will take
approximately 15 work hours per airplane to accomplish the required
inspections, and that the average labor rate is $60 per work hour.
Based on these figures, the cost impact of the inspections required by
this AD on U.S. operators is estimated to be $23,400, or $900 per
airplane, per inspection cycle.
It will take approximately 8 work hours per airplane to accomplish
the required replacement, at an average labor rate of $60 per work
hour. Required parts will cost approximately $16,872 per airplane.
Based on these figures, the cost impact of the required replacement on
U.S. operators is estimated to be $451,152, or $17,352 per airplane.
The cost impact figures discussed above are 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:
97-10-01 Airbus Industrie: Amendment 39-10013. Docket 96-NM-60-AD.
Applicability: Model A310 series airplanes, on which Airbus
Modification 10962 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
otherwise 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 been
eliminated, the request should include specific proposed actions to
address it.
Compliance: Required as indicated, unless accomplished
previously.
To prevent failure of the flap transmission shaft due to damaged
steady bearing assemblies, which could cause an uncommanded
asymmetric retraction of the flap, and result in reduced
controllability of the airplane, accomplish the following:
(a) Prior to the accumulation of 2,000 total landings or within
500 flight hours after the effective date of this AD, whichever
occurs later: Perform a visual inspection to detect damage or any
discrepancy of the steady bearing assemblies of the flap
transmission system, in accordance with Airbus Service Bulletin
A310-27-2067, Revision 1, dated January 5, 1995.
(1) If no damage or discrepancy is detected: Repeat the
inspection thereafter at intervals not to exceed 2,000 landings,
until the requirements of paragraph (b) of this AD are accomplished.
(2) If any damage or discrepancy is detected and the groove
depth of the shaft is less than 1 mm (.04 inch): Prior to the
accumulation of 50 landings after detection of this discrepancy,
replace the steady bearing assembly with a new, like assembly in
accordance with Airbus Service Bulletin A310-27-2067, Revision 1,
dated January 5, 1995.
(3) If any damage or discrepancy is detected and the groove
depth on the shaft is 1 mm or more: Prior to further flight, replace
the steady bearing assembly with a new, like assembly, in accordance
with Airbus Service Bulletin A310-27-2067, Revision 1, dated January
5, 1995.
(b) Within 5 years after the effective date of this AD, replace
all steady bearing assemblies of the flap transmission system with
new, improved assemblies, in accordance with Airbus A310-27-2074,
dated November 18, 1994. Accomplishment of the replacement
constitutes terminating action for the requirements of this AD.
Note 2: Airbus Service Bulletin A310-27-2074 references Lucas
Liebherr Service Bulletin 551A-27-M551-03 as an additional source of
service information for replacement of the steady bearing assemblies
with the new, improved assemblies.
(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,
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 3: 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 inspection and certain replacements shall be done in
accordance with Airbus Service Bulletin A310-27-2067, Revision 1,
dated January 5, 1995. Certain other replacements shall be done in
accordance with Airbus Service Bulletin A310-27-2074, dated November
18, 1994. 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
[[Page 24570]]
Office of the Federal Register, 800 North Capitol Street, NW., suite
700, Washington, DC.
(f) This amendment becomes effective on June 10, 1997.
Issued in Renton, Washington, on April 28, 1997.
Neil D. Schalekamp,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 97-11525 Filed 5-5-97; 8:45 am]
BILLING CODE 4910-13-U
