[Federal Register Volume 61, Number 29 (Monday, February 12, 1996)]
[Proposed Rules]
[Pages 5326-5329]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-2998]



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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 93-NM-133-AD]


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

AGENCY: Federal Aviation Administration, DOT.

ACTION: Supplemental notice of proposed rulemaking; reopening of 
comment period.

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SUMMARY: This document revises an earlier proposed airworthiness 
directive (AD), applicable to certain Airbus Model A300, A310, and 
A300-600 series airplanes, that would have required inspections to 
detect missing fasteners, cracked fitting angles, and elongated 
fastener holes in certain frames, and correction of discrepancies. That 
proposal was prompted by discrepancies found at the fitting angles on 
the frame at which a certain electronic rack is attached. This action 
revises the proposed rule by revising the inspection thresholds and 
repetitive intervals; providing an optional terminating action; and 
deleting certain airplanes from the applicability. The actions 
specified by this proposed 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: Comments must be received by March 4, 1996.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-103, 
Attention: Rules Docket No. 93-NM-133-AD, 1601 Lind Avenue SW., Renton, 
Washington 98055-4056. Comments may be inspected at this location 
between 9:00 a.m. and 3:00 p.m., Monday through Friday, except Federal 
holidays.
    The service information referenced in the proposed rule may be 
obtained from Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 
Blagnac Cedex, France. This information may be examined at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington.

FOR FURTHER INFORMATION CONTACT: Tim Backman, Aerospace Engineer, 
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate, 
1601 Lind Avenue SW., Renton, 

[[Page 5327]]
Washington 98055-4056; telephone (206) 227-2797; fax (206) 227-1149.

SUPPLEMENTARY INFORMATION:

Comments Invited

    Interested persons are invited to participate in the making of the 
proposed rule by submitting such written data, views, or arguments as 
they may desire. Communications shall identify the Rules Docket number 
and be submitted in triplicate to the address specified above. All 
communications received on or before the closing date for comments, 
specified above, will be considered before taking action on the 
proposed rule. The proposals contained in this notice may be changed in 
light of the comments received.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the proposed rule. All 
comments submitted will be available, both before and after the closing 
date for comments, in the Rules Docket for examination by interested 
persons. A report summarizing each FAA-public contact concerned with 
the substance of this proposal will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this notice must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 93-NM-133-AD.'' The postcard will be date stamped and 
returned to the commenter.

Availability of NPRMs

    Any person may obtain a copy of this NPRM by submitting a request 
to the FAA, Transport Airplane Directorate, ANM-103, Attention: Rules 
Docket No. 93-NM-133-AD, 1601 Lind Avenue SW., Renton, Washington 
98055-4056.

Discussion

    A proposal to amend part 39 of the Federal Aviation Regulations (14 
CFR part 39) to add an airworthiness directive (AD), applicable to all 
Airbus Model A300, A310, and A300-600 series airplanes, was published 
as a notice of proposed rulemaking (NPRM) in the Federal Register on 
September 13, 1993 (58 FR 47837). That NPRM would have required 
repetitive inspections to detect missing fasteners, cracked fitting 
angles, and elongated fastener holes in certain frames; and the 
correction of any discrepancies identified. The initial inspection 
would have been required to be performed prior to the accumulation of 
8,000 total flight cycles; repetitive inspections would have been 
required every 850 flight cycles thereafter.
    That NPRM was prompted by various discrepancies that were found on 
three airplanes at the fitting angles on frame 16 at the lower 
attachments of electric rack 101VU. These discrepancies included 
missing fasteners, elongated fastener holes, and cracks. Discrepancies 
such as those found in the subject area, if not detected and corrected 
in a timely manner, could lead to failure of the attachment points to 
secure the electric rack to the adjacent structure. This condition 
could result in loss of airplane systems, structural damage, and 
possible electrical arcing.
    Since the issuance of that NPRM, the Direction Generale de 
l'Aviation Civile (DGAC), which is the airworthiness authority for 
France, and Airbus Industrie have notified the FAA that additional 
analysis has been conducted relative to the identified problem. The 
results of this analysis, together with in-service data that were 
gathered in the interim, indicate that the initial inspection of the 
subject area must be conducted earlier than previously considered, but 
subsequent inspections may be conducted at greater intervals.
    Airbus has issued the following service bulletins, which concern 
this subject:
    1. Airbus Service Bulletin A300-53-0300, dated October 28, 1993, 
which pertains to Model A300 series airplanes;
    2. Airbus Service Bulletin A310-53-2077, dated October 28, 1993, 
which pertains to Model A310 series airplanes; and
    3. Airbus Service Bulletin A300-53-6055, dated October 28, 1993, 
which pertains to Model A300-600 series airplanes.
    Each of these service bulletins describe procedures for performing 
a detailed visual inspection to detect damage of the lower attachments 
of electric rack 101VU, and the replacement of any missing or damaged 
fasteners identified. These service bulletins recommend that the 
initial inspection be performed prior to the accumulation of 7,000 
total flight cycles, and that repetitive inspection be performed every 
2,300 flight cycles.
    The DGAC classified these service bulletins as mandatory and issued 
French airworthiness directive (CN) 92-253-138(B), dated February 2, 
1994, in order to assure the continued airworthiness of these airplanes 
in France.
    Airbus has also issued the following service bulletins:
    1. Airbus Service Bulletin A300-53-0294, dated May 17, 1993, which 
pertains to Model A300 series airplanes;
    2. Airbus Service Bulletin A310-53-2076, dated May 17, 1993, which 
pertains to Model A310 series airplanes; and
    3. Airbus Service Bulletin A300-53-6046, dated May 17, 1993, which 
pertains to Model A300-600 series airplanes.
    These service bulletins describe procedures for installing 
Modification No. 10414. This modification entails installation of new 
thicker attachments and new plates on the front face of frames 15A and 
16. Accomplishment of this modification eliminates the need for the 
repetitive inspections of the subject area. The DGAC classified these 
service bulletins as recommended.
    This airplane model is manufactured in France and is type 
certificated for operation in the United States under the provisions of 
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and 
the applicable bilateral airworthiness agreement. Pursuant to this 
bilateral airworthiness agreement, the DGAC has kept the FAA informed 
of the situation described above. The FAA has examined the findings of 
the DGAC, reviewed all available information, and determined that AD 
action is necessary for products of this type design that are 
certificated for operation in the United States.
    Since an unsafe condition has been identified that is likely to 
exist or develop on other airplanes of the same type design, the 
proposed action would revise the previously issued NPRM to require that 
an initial inspection to detect discrepancies be conducted prior to the 
accumulation of 7,000 total flight cycles (or within 50 flight cycles 
after the effective date of the final rule, whichever is later). This 
inspection would be required to be repeated thereafter at intervals not 
to exceed 2,300 flight cycles. Any missing or damaged fasteners would 
be required to be replaced prior to further flight. These actions would 
be required to be accomplished in accordance with the Airbus service 
bulletins described previously.
    This revised proposal also would require that any cross beam found 
damaged be repaired prior to further flight in accordance with a method 
approved by the FAA.
    This revised proposal also would require that, if any one or more 
angle fitting is found to be cracked, Modification No. 10414 must be 
installed prior to further flight. Operators should note that this 
particular proposed requirement would differ from the procedures 
described in the relevant Airbus service bulletins, which allow 
airplanes to continue to be 

[[Page 5328]]
flown if one or more angle fitting is cracked. The FAA finds that, 
since each of the four angle fittings that secure the electric rack to 
the frame is subject to the same potential for cracking, the decreased 
load-carrying ability of a cracked fitting(s) may lead to faster crack 
growth in the remaining fittings. Therefore, the FAA has determined 
that continued flight with one or more unrepaired cracked fittings is 
inappropriate.
    Installation of Modification No. 10414 would constitute terminating 
action for the inspections that would be required by this proposed AD.
    Additionally, this action revises the applicability of the proposed 
rule to delete those airplanes on which Modification No. 10414 or its 
equivalent has been installed previously.
    Since these changes expand the scope of the originally proposed 
rule, the FAA has determined that it is necessary to reopen the comment 
period to provide additional opportunity for public comment.
    The FAA estimates that 78 Model A300, A310, and A300-600 series 
airplanes of U.S. registry would be affected by this proposed AD. It 
would take approximately 1.5 work hours per airplane to accomplish the 
proposed inspections, at an average labor rate of $60 per work hour. 
Based on these figures, the cost impact of the proposed AD on U.S. 
operators is estimated to be $7,020, or $90 per airplane, per 
inspection.
    This cost impact figure 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.
    Should an operator elect to accomplish the optional terminating 
action that would be provided by this AD action, rather than continue 
the repetitive inspections, it would take approximately 7 work hours to 
accomplish it, at an average labor rate of $60 per work hour. The cost 
of required parts would be approximately $1,615 per airplane. Based on 
these figures, the cost impact of the optional terminating action would 
be $2,035 per airplane.
    The regulations proposed herein would 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 
proposal would not have sufficient federalism implications to warrant 
the preparation of a Federalism Assessment.
    For the reasons discussed above, I certify that this proposed 
regulation (1) is not a ``significant regulatory action'' under 
Executive Order 12866; (2) is not a ``significant rule'' under the DOT 
Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 
and (3) if promulgated, 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 copy of the draft 
regulatory evaluation prepared for this action is contained in the 
Rules Docket. A copy of it may be obtained by contacting the Rules 
Docket at the location provided under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39 -

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration proposes to amend 
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 USC 106(g), 40113, 44701.


Sec. 39.13  [Amended]

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

Airbus: 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 use the authority 
provided in paragraph (g) 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 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.

[[Page 5329]]

    (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.

    Issued in Renton, Washington, on February 6, 1996.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 96-2998 Filed 2-9-96; 8:45 am]
BILLING CODE 4910-13-U