[Federal Register Volume 67, Number 1 (Wednesday, January 2, 2002)]
[Proposed Rules]
[Pages 40-44]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-32197]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-205-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 B2 and A300 B4 Series 
Airplanes; Model A300 F4-605R Airplanes; Model A300 B4-600 and A300 B4-
600R Series Airplanes; and Model A310 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

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

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[[Page 41]]

SUMMARY: This document revises an earlier proposed airworthiness 
directive (AD), applicable to certain Airbus Model A300 B2 and A300 B4 
series airplanes; certain Model A300 F4-605R airplanes and Model A300 
B4-600 and A300 B4-600R series airplanes; and certain Model A310 series 
airplanes. That earlier proposed AD would have required repetitive 
inspections to detect damage of the fillet seals and feeder cables, and 
of the wiring looms in the wing/pylon interface area; and corrective 
action, if necessary. That earlier proposed AD also would have provided 
for optional terminating action for the repetitive inspections. This 
new action would retain those proposed actions but require that actions 
be done in accordance with newly revised service bulletins. This new 
action also would revise the applicability. The actions specified by 
this new proposed AD are intended to prevent wire chafing and short 
circuits in the wing leading edge/pylon interface area, which could 
result in loss of the power supply generator and/or system functions. 
This action is intended to address the identified unsafe condition.

DATES: Comments must be received by January 28, 2002.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2001-NM-205-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9 a.m. and 3 p.m., Monday through Friday, except 
Federal holidays. Comments may be submitted via fax to (425) 227-1232. 
Comments may also be sent via the Internet using the following address: 
<a href="/cdn-cgi/l/email-protection#ac9581cdc2c181c2dcdec1cfc3c1c1c9c2d8eccacdcd82cbc3da"><span class="__cf_email__" data-cfemail="9ba2b6faf5f6b6f5ebe9f6f8f4f6f6fef5efdbfdfafab5fcf4ed">[email protected]</span></a>. Comments sent via fax or the Internet must 
contain ``Docket No. 2001-NM-205-AD'' in the subject line and need not 
be submitted in triplicate. Comments sent via the Internet as attached 
electronic files must be formatted in Microsoft Word 97 for Windows or 
ASCII text.
    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: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2125; fax (425) 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 action may be changed in 
light of the comments received.
    Submit comments using the following format:
    <bullet> Organize comments issue-by-issue. For example, discuss a 
request to change the compliance time and a request to change the 
service bulletin reference as two separate issues.
    <bullet> For each issue, state what specific change to the proposed 
AD is being requested.
    <bullet> Include justification (e.g., reasons or data) for each 
request.
    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 action must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket 2001-NM-205-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-114, Attention: Rules 
Docket 2001-NM-205-AD, 1601 Lind Avenue, SW., Renton, Washington 98055-
056.

Discussion

    A proposal to amend part 39 of the Federal Aviation Regulations (14 
CFR part 39) to add an airworthiness directive (AD), applicable to 
certain Airbus Model A300 B2 and A300 B4 series airplanes; certain 
Model A300 F4-605R airplanes and Model A300 B4-600 and A300 B4-600R 
series airplanes; and certain Model A310 series airplanes; was 
published as a notice of proposed rulemaking (NPRM) in the Federal 
Register on October 4, 2001 (66 FR 50588). That original NPRM would 
have required repetitive inspections to detect damage of the fillet 
seals and feeder cables, and of the wiring looms in the wing/pylon 
interface area; and corrective action, if necessary. The original 
proposed AD also would have provided for optional terminating action 
for the repetitive inspections. The original NPRM was prompted by 
reports of wire chafing and short circuits in the wing leading edge/
pylon interface area. That condition, if not corrected, could result in 
loss of the power supply generator and/or system functions.

Since Issuance of the Original NPRM

    Since the original NPRM was issued, Airbus has issued new service 
information that would affect the requirements proposed by that NPRM.

Explanation of Relevant Service Information

    Airbus Service Bulletin A300-24-0053, Revision 05, was cited in the 
original NPRM as the appropriate source of service information for the 
inspection of the fillet seals and feeder cables for Model A300 series 
airplanes. Airbus has since issued Revision 06 of the service bulletin, 
dated September 10, 2001, which describes the basic pylon and common 
pylon configurations and distinguishes the procedures for repairing 
damaged fillet seals for the two configurations.
    The original NPRM cited Airbus Service Bulletin A300-54-0095, 
Revision 01, as the appropriate source of service information for the 
optional replacement of the fillet panel assemblies on Model A300 
series airplanes. Airbus has since issued Revision 02 of the service 
bulletin, dated September 7, 2001, to include a new kit for airplanes 
in the basic pylon configuration. Either Revision 01 or Revision 02 
would eliminate the need for the repetitive inspections for airplanes 
in the common pylon configuration; only Revision 02 would eliminate the 
need for the repetitive inspections for airplanes in the basic pylon 
configuration.
    The original NPRM cited Airbus Service Bulletin A300-24-6039, 
Revision 06, as the appropriate source of service information for the 
inspection and repair of the wiring looms for Model A300-600 series 
airplanes. Airbus has since issued Revision 07 of the service bulletin, 
dated August 9,

[[Page 42]]

2001, which includes minor changes only.
    The Direction Generale de l'Aviation Civile (DGAC), which is the 
airworthiness authority for France, approved these service bulletin 
revisions.
    Accomplishment of the actions specified in Airbus Service Bulletins 
A300-24-0053, Revision 06, A300-24-6001, Revision 05, A310-24-2021, 
Revision 06, A300-24-0083, Revision 03, A300-24-6039, Revision 07, and 
A310-24-2052, Revision 04, is intended to adequately address the 
identified unsafe condition.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comments received.

Request to Extend the Compliance Time for the Inspection

    One commenter requests that the compliance time specified by the 
original NPRM be extended from 500 flight hours to 600 flight hours. 
According to the commenter, a ``600 FH ``grace period'' is compatible 
with the highest existing interval for an A-check.''
    The FAA concurs with the request. The FAA finds it appropriate to 
extend the compliance time to 600 flight hours and has determined that 
such an extension would not adversely affect the safety of the fleet. 
Paragraphs (a) and (b) of this supplemental NPRM have been revised 
accordingly.

Requests to Cite Latest Service Bulletin Revisions

    The commenters request that the original NPRM be revised to refer 
to the latest service bulletin revisions (described previously). Airbus 
Service Bulletins A300-24-0053, Revision 06, and A300-54-0095, Revision 
02, have included procedures for the inspection and repair of airplanes 
in the basic pylon configuration. One commenter states that the earlier 
revisions of these service bulletins properly cover the common pylon 
configuration but are not suitable for the basic pylon configuration. 
The commenters also request that Revision 07 of Service Bulletin A300-
24-6039 be cited as the primary service information for the wiring loom 
inspection for Model A300-600 series airplanes.
    The FAA partially concurs with the requests. Although 
accomplishment of the actions specified by earlier service bulletin 
revisions may be acceptable for certain airplanes, the FAA has 
determined that, for simplicity, this supplemental NPRM will cite only 
the latest service bulletin revisions for the proposed actions 
specified in paragraphs (a) and (b) of this supplemental NPRM. As a 
result, paragraphs (a) and (b) of this supplemental NPRM have been 
revised, and Note 3 and Note 5 of the original NPRM have been removed 
(and the remaining Notes have been renumbered). However, paragraph (c) 
of this supplemental NPRM has been revised to specify accomplishment of 
the terminating action in accordance with either Revision 01 or 
Revision 02 of Airbus Service Bulletin A300-54-0095 for airplanes in 
the common pylon configuration, but would require Revision 02 for 
airplanes in the basic pylon configuration. Operators should note that 
the provisions of paragraph (d) of this supplemental NPRM would enable 
the FAA to approve requests for alternative methods of compliance 
(e.g., per an alternative service bulletin revision) if data are 
submitted to substantiate that such alternative methods would provide 
an acceptable level of safety.

Request to Disallow Credit for Repair Per Certain Service Bulletin 
Versions

    One commenter requests that the original NPRM be revised to 
specifically exclude credit for repairs done in accordance with 
revisions prior to Revision 05 of Airbus Service Bulletin A300-24-6011 
and Revision 06 of Airbus Service Bulletin A310-24-2021. Note 3 of the 
original NPRM would have provided this credit. Note 3 of the original 
NPRM refers to paragraph (a) of the original NPRM. The commenter states 
that earlier revisions of these service bulletins are acceptable for 
accomplishment of detailed visual inspections to detect damage 
(including erosion and tearing) and deterioration of the fillet seals 
and feeder cables, but not the repairs of damage on applicable affected 
airplanes.
    The FAA partially concurs. The FAA agrees that the repair 
procedures described in those earlier revised service bulletins are not 
acceptable for the basic pylon configuration, and notes that the repair 
procedures have been deleted from Airbus Service Bulletins A300-24-
6011, Revision 05, and A310-24-2021, Revision 06. However, as stated 
earlier, Note 3 and Note 5 of the original NPRM, which provided credit 
for prior accomplishment of the earlier service bulletin revisions, 
have been removed from this supplemental NPRM, but operators may 
request approval of an alternative method of compliance in accordance 
with paragraph (d) of this supplemental NPRM. No additional change is 
necessary in this regard.

Request to Change Inspection Type

    One commenter, the manufacturer, requests that the original NPRM be 
revised to change the inspection type from a general visual inspection 
to a detailed visual inspection. According to the manufacturer, ``even 
if not always clearly stated in the Airbus SBs, visual inspection means 
detailed visual inspection and not general visual inspection.''
    The FAA finds that detailed visual inspections are appropriate to 
address the identified unsafe condition, and concurs with the 
commenter's request. Paragraphs (a) and (b) of this supplemental NPRM 
have been revised to specify detailed, rather than general, visual 
inspections. In addition, Note 2 of this supplemental NPRM has been 
revised to define a detailed visual inspection.

Request to Revise Applicability of Proposed AD

    One commenter requests that Table 1 of the original NPRM be revised 
to reflect the correct applicability. The original NPRM indicates that 
airplanes would be excluded from the applicability if either of two 
specified modifications had been accomplished. The commenter states 
that the applicability should exclude only airplanes on which both of 
the specified modifications have been accomplished.
    The FAA concurs. The original NPRM inadvertently substituted the 
conjunction ``or'' for ``and'' between the modification numbers listed 
in Table 1. The applicability of this supplemental NPRM has been 
revised to exclude airplanes only if both of the specified 
modifications have been accomplished.

Conclusion

    Since these changes expand the scope of the original NPRM, the FAA 
has determined that it is necessary to reopen the comment period to 
provide additional opportunity for public comment.

Cost Impact

    The FAA estimates that 107 airplanes of U.S. registry would be 
affected by this supplemental NPRM.
    It would take approximately 6 work hours per airplane to inspect 
the seals/cables at an average labor rate of $60 per work hour. Based 
on these figures, the cost impact of this proposed inspection on U.S. 
operators is estimated to be $38,520, or $360 per airplane, per 
inspection cycle.

[[Page 43]]

    It would take approximately 5 work hours per airplane to inspect 
the wiring looms and apply the protection, at an average labor rate of 
$60 per work hour. Based on these figures, the cost impact of this 
proposed inspection on U.S. operators is estimated to be $32,100, or 
$300 per airplane, per inspection cycle.
    The cost impact figures discussed above are 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 proposed AD were not adopted. The cost impact 
figures discussed in AD rulemaking actions represent only the time 
necessary to perform the specific actions actually required by the AD. 
These figures typically do not include incidental costs, such as the 
time required to gain access and close up, planning time, or time 
necessitated by other administrative actions.
    Should an operator elect to perform the optional terminating 
action, it would take approximately 5 work hours per airplane to 
replace the fillet panel assemblies, at an average labor rate of $60 
per work hour. Required parts would cost approximately $350 to $470 per 
airplane. Based on these figures, the cost impact of the optional 
terminating action is estimated to be $650 to $770 per airplane.

Regulatory Impact

    The regulations proposed herein would not have a substantial direct 
effect 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, it 
is determined that this proposal would not have federalism implications 
under Executive Order 13132.
    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 U.S.C. 106(g), 40113, 44701.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by adding the following new 
airworthiness directive:
Airbus Industrie: Docket 2001-NM-205-AD.
    Applicability: The following airplanes, certificated in any 
category:

------------------------------------------------------------------------
                                   Excluding those modified per Airbus
             Model                             modification
------------------------------------------------------------------------
A300 B2-1C, A300 B2-203, A300    11349 and airplanes 12309.
 B2K-3C, and A300 B4 series.
A300 F4-605R airplanes, A300 B4- 11348 and 12303.
 600 series airplanes, and A300
 B4-600R series airplanes.
A310 series airplanes..........  11350 and 12310.
------------------------------------------------------------------------


    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 (d) 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 wire chafing and short circuits in the wing leading 
edge/pylon interface area, which could result in loss of the power 
supply generator and/or system functions, accomplish the following:

Inspections

    (a) Within 600 flight hours after the effective date of this AD, 
perform a detailed visual inspection to detect damage (including 
erosion and tearing) and deterioration of the fillet seals and 
feeder cables, in accordance with Airbus Service Bulletin A300-24-
0053, Revision 06, dated September 10, 2001 (for Model A300 series 
airplanes); A300-24-6011, Revision 05, dated May 18, 2001 (for Model 
A300 F4-605R airplanes and Model A300 B4-600 and A300 B4-600R series 
airplanes); or A310-24-2021, Revision 06, dated May 18, 2001 (for 
Model A310 series airplanes). Repeat the inspection thereafter at 
intervals not to exceed 1,000 flight hours, until the actions 
specified by paragraph (c) are accomplished.
    (1) If no damage is detected: Prior to further flight following 
the initial inspection only, apply protection to each feeder cable 
in accordance with the applicable service bulletin.
    (2) If any damage is detected: Prior to further flight, repair 
in accordance with the applicable service bulletin.

    Note 2: For the purposes of this AD, a detailed visual 
inspection is defined as: ``An intensive visual examination of a 
specific structural area, system, installation, or assembly to 
detect damage, failure, or irregularity. Available lighting is 
normally supplemented with a direct source of good lighting at 
intensity deemed appropriate by the inspector. Inspection aids such 
as mirror, magnifying lenses, etc., may be used. Surface cleaning 
and elaborate access procedures may be required.''


    Note 3: Airbus Service Bulletins A300-24-0053, A300-24-6011, and 
A310-24-2021 refer to Airbus Service Bulletins A300-24-0054, A300-
24-6013, and A310-24-2024, respectively, as additional sources of 
service information for repair.

    (b) Within 600 flight hours after the effective date of this AD: 
Perform a detailed visual inspection of the wiring looms in the area 
of the wing leading edge/pylon interface to detect damage (including 
chafing, burning, and short circuits), in accordance with Airbus 
Service Bulletin A300-24-0083, Revision 03, dated January 3, 2001 
(for Model A300 series airplanes); A300-24-6039, Revision 07, dated 
August 9, 2001 (for Model A300 F4-605R airplanes and Model A300 B4-
600 and A300 B4-600R series airplanes); or A310-24-2052, Revision 
04, dated April 6, 2001 (for Model A310 series airplanes); as 
applicable. Repeat the inspection thereafter at least every 1,000 
flight hours, until the actions specified by paragraph (c) of this 
AD have been accomplished.
    (1) If no damage is detected: Prior to further flight following 
the initial inspection only, apply protection in accordance with the 
applicable service bulletin.
    (2) If any damage is detected: Prior to further flight, repair 
in accordance with the applicable service bulletin.

Optional Terminating Action

    (c) Replacement of the fillet panel assemblies with new, 
improved assemblies,

[[Page 44]]

as specified by paragraphs (c)(1), (c)(2), or (c)(3) of this AD, as 
applicable, terminates the requirements of this AD.
    (1) For Model A300 series airplanes: Replacement of the fillet 
panel assemblies, if accomplished, must be done as specified by 
paragraph (c)(1)(i) or (c)(1)(ii) of this AD.
    (i) For airplanes in the common pylon configuration: In 
accordance with Airbus Service Bulletin A300-54-0095, Revision 01, 
dated January 3, 2001, or Revision 02, dated September 7, 2001.
    (ii) For airplanes in the basic pylon configuration: In 
accordance with Airbus Service Bulletin A300-54-0095, Revision 02, 
dated September 7, 2001.
    (2) For Model A300 F4-605R airplanes and Model A300 B4-600 and 
A300 B4-600R series airplanes: Replacement of the fillet panel 
assemblies, if accomplished, must be done in accordance with Airbus 
Service Bulletin A300-54-6032, Revision 03, dated January 3, 2001.
    (3) For Model A310 series airplanes: Replacement of the fillet 
panel assemblies, if accomplished, must be done in accordance with 
Airbus Service Bulletin A310-54-2033, Revision 01, dated January 3, 
2001.

Alternative Methods of Compliance

    (d) 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, 
Transport Airplane Directorate, FAA. 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 4: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the International Branch, ANM-116.

Special Flight Permits

    (e) 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 December 26, 2001.
Ali Bahrami,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 01-32197 Filed 12-31-01; 8:45 am]
BILLING CODE 4910-13-U


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