[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