Airworthiness Directives; Airbus Industrie Model A300, A310, and A300-600 Series Airplanes

[Federal Register Volume 61, Number 112 (Monday, June 10, 1996)]
[Rules and Regulations]
[Pages 29267-29269]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-14230]



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Federal Register / Vol. 61, No. 112 / Monday, June 10, 1996 / Rules 
and Regulations

[[Page 29267]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 93-NM-133-AD; Amendment 39-9658; AD 96-12-15]
RIN 2120-AA64


Airworthiness Directives; Airbus Industrie Model A300, A310, and 
A300-600 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to certain Airbus Model A300, A310, and A300-600 series 
airplanes, that requires inspections to detect missing fasteners, 
cracked fitting angles, and elongated fastener holes in certain frames, 
and correction of discrepancies. It also provides an optional 
terminating action. This amendment is prompted by discrepancies found 
at the fitting angles on the frame at which a certain electronic rack 
is attached. The actions specified by this AD are intended to prevent 
damage propagation that could lead to failure of the rack-to-structure 
attachment points, and subsequently could result in loss of airplane 
systems, structural damage, and possible electrical arcing.

DATES: Effective July 15, 1996.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of July 15, 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, 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: Tim Backman, Aerospace Engineer, 
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (206) 
227-2797; 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 A300, A310, 
and A300-600 series airplanes was published in the Federal Register as 
a supplemental notice of proposed rulemaking on February 12, 1996 (61 
FR 5326). That action proposed to require inspections to detect missing 
fasteners, cracked fitting angles, and elongated fastener holes in 
certain frames, and correction of discrepancies. It also proposed to 
provide an optional terminating action.

Discussion of Comments

    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 78 Airbus Model A300, A310, and A300-600 
series airplanes of U.S. registry will be affected by this AD, that it 
will take approximately 1.5 work hours per airplane to accomplish the 
required inspections, at an average labor rate of $60 per work hour. 
Based on these figures, the cost impact of the AD on U.S. operators is 
estimated to be $7,020, or $90 per airplane, per inspection.
    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.
    Should an operator elect to accomplish the optional terminating 
action that is provided by this AD action, rather than continue the 
repetitive inspections, it will take approximately 7 work hours to 
accomplish it, at an average labor rate of $60 per work hour. The cost 
of required parts will be approximately $1,615 per airplane. Based on 
these figures, the cost impact of the optional terminating action will 
be $2,035 per airplane.

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:

[[Page 29268]]

PART 39--AIRWORTHINESS DIRECTIVES

    1. The authority citation for part 39 continues to read as follows:

    Authority: 49 USC 106(g), 40113, 44701.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by adding the following new 
airworthiness directive:

96-12-15  Airbus Industrie: Amendment 39-9658. Docket 93-NM-133-AD.

    Applicability: Model A300 series airplanes listed in Airbus 
Service Bulletin A300-53-0300, dated October 28, 1993; Model A310 
series airplanes listed in Airbus Service Bulletin A310-53-2077, 
dated October 28, 1993; and Model A300-600 series airplanes listed 
in Airbus Service Bulletin A300-53-6055, dated October 28, 1993; on 
which Airbus Modification No. 10414 or production equivalent 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 (g) 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 electric rack-to-structure attachment 
points, which could subsequently result in loss of airplane systems, 
structural damage, and possible electrical arcing, accomplish the 
following:
    (a) Prior to the accumulation of 7,000 total flight cycles, or 
within 50 flight cycles after the effective date of this AD, 
whichever occurs later, perform a detailed visual inspection of the 
right-and left-hand lower attachments of electric rack 101VU, 
including the crossbeams at frames 15A and 16, to detect missing 
fasteners, cracked fitting angles, or elongated fastener holes, in 
accordance with Airbus Service Bulletin A300-53-0300 (for Model A300 
series airplanes), dated October 28, 1993; Airbus Service Bulletin 
A310-53-2077 (for Model A310 series airplanes), dated October 28, 
1993; or Airbus Service Bulletin A300-53-6055 (for Model A300-600 
series airplanes), dated October 28, 1993; as applicable.

    Note 2: Inspections accomplished in accordance with Airbus 
Industrie All Operator Telex (AOT) 53-03, Revision 3, dated December 
23, 1992, prior to the effective date of this AD, are considered 
acceptable for compliance with the inspection requirements of this 
paragraph.

    (b) If no discrepancies are identified during the inspection 
required by paragraph (a) of this AD, repeat the detailed visual 
inspection thereafter at intervals not to exceed 2,300 flight 
cycles.
    (c) If any fastener is missing or is found to be damaged during 
any inspection required by this AD, prior to further flight, replace 
the fastener in accordance with Airbus Service Bulletin A300-53-0300 
(for Model A300 series airplanes), dated October 28, 1993; Airbus 
Service Bulletin A310-53-2077 (for Model A310 series airplanes), 
dated October 28, 1993; or Airbus Service Bulletin A300-53-6055 (for 
Model A300-600 series airplanes), dated October 28, 1993; as 
applicable.
    (d) If any fitting angle is found to be cracked during any 
inspection required by this AD, prior to further flight, install 
Modification No. 10414 in accordance with Airbus Service Bulletin 
A300-53-0294 (for Model A300 series airplanes), dated May 17, 1993; 
Airbus Service Bulletin A310-53-2076 (for Model A310 series 
airplanes), dated May 17, 1993; or Airbus Service Bulletin A300-53-
6046 (for Model A300-600 series airplanes), dated May 17, 1993; as 
applicable. Installation of this modification constitutes 
terminating action for the inspections required by this AD.
    (e) If any crossbeam is found damaged during any inspection 
required by this AD, prior to further flight, repair it in 
accordance with a method approved by the Manager, Standardization 
Branch, ANM-113, FAA, Transport Airplane Directorate.
    (f) Installation of Modification No. 10414 in accordance with 
Airbus Service Bulletin A300-53-0294 (for Model A300 series 
airplanes), dated May 17, 1993; Airbus Service Bulletin A310-53-2076 
(for Model A310 series airplanes), dated May 17, 1993; or Airbus 
Service Bulletin A300-53-6046 (for Model A300-600 series airplanes), 
dated May 17, 1993; as applicable; constitutes terminating action 
for the inspections required by this AD.
    (g) 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.

    (h) 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. (i) The inspections 
and replacement shall be done in accordance with Airbus Service 
Bulletin A300-53-0300, dated October 28, 1993; Airbus Service 
Bulletin A310-53-2077, dated October 28, 1993; or Airbus Service 
Bulletin A300-53-6055, dated October 28, 1993; as applicable. The 
modification shall be done in accordance with the following Airbus 
service bulletins, which contain the specified effective pages:

----------------------------------------------------------------------------------------------------------------
  Service bulletin referenced                                        Revision level shown                       
           and date                          Page No.                      on page           Date shown on page 
----------------------------------------------------------------------------------------------------------------
A300-53-0294, May 17, 1993....  1-34,.............................  Original.............  May 17, 1993.        
A310-53-2076, May 17, 1993....  1-34..............................  Original.............  May 17, 1993.        
A300-53-6046, Revision 1, Apr.  1, 4, 11, 14-18, 21, 22, 25-31....  1....................  Apr. 5, 1994         
 5, 1994.                                                                                                       
                                2, 3, 5-10, 12, 13, 19, 20, 23,     Original.............  May 17, 1993.        
                                 24, 32.                                                                        
----------------------------------------------------------------------------------------------------------------


[[Page 29269]]


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.
    (j) This amendment becomes effective on July 15, 1996.

    Issued in Renton, Washington, on May 31, 1996.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 96-14230 Filed 6-7-96; 8:45 am]
BILLING CODE 4910-13-U

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