[Federal Register Volume 66, Number 32 (Thursday, February 15, 2001)]
[Proposed Rules]
[Pages 10382-10384]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-3855]



[[Page 10382]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-160-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A310, and Model A300 B4-
600, A300 B4-600R, and A300 F4-600R (Collectively Called A300-600) 
Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes the supersedure of an existing 
airworthiness directive (AD), applicable to certain Airbus Model A310 
and A300-600 series airplanes. The existing AD requires a detailed 
visual inspection to detect damage to the terminal lugs on the 12XC and 
15XE connectors and the mounting lugs on the 15XE connector; corrective 
actions, if necessary; and certain conditional repetitive inspections. 
This action would add requirements for installation of a new mounting 
bracket for the 15XE connector, modification of the cable attachment 
adjacent to the connector, and replacement of certain terminal lugs on 
the 15XE connector by terminal lugs with a thicker contact area. This 
proposal is prompted by issuance of mandatory continuing airworthiness 
information by a foreign civil airworthiness authority. The actions 
specified by the proposed AD are intended to prevent excessive 
vibrations generated by the mounting configuration of the 15XE 
connector, which could cause breakage of the terminal and mounting lugs 
on the 15XE connectors in the 101VU panel in the avionics compartment, 
resulting in loss of electrical power from the standby generator.

DATES: Comments must be received by March 19, 2001.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2000-NM-160-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: 
[email protected]. Comments sent via fax or the Internet must 
contain ``Docket No. 2000-NM-160-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, 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:
     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.
     For each issue, state what specific change to the proposed 
AD is being requested.
     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 action. 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 Number 2000-NM-160-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 No. 2000-NM-160-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    On September 10, 1999, the FAA issued AD 99-19-40, amendment 39-
11327 (64 FR 51190, September 22, 1999), applicable to certain Model 
A310 and Model A300-600 series airplanes. That AD requires a detailed 
visual inspection to detect damage to the terminal lugs on the 12XC and 
15XE connectors and the mounting lugs on the 15XE connector; and repair 
or replacement of the terminal lugs or the 15XE connector with new 
parts, if necessary. That action was prompted by issuance of mandatory 
continuing airworthiness information by a foreign civil airworthiness 
authority. The requirements of that AD are intended to detect and 
correct broken terminal and mounting lugs on the 12XC and the 15XE 
connectors in the 101VU panel in the avionics compartment, which could 
result in loss of electrical power from the standby generator.

Actions Since Issuance of AD 99-19-40

    In the Notice of Proposed Rule Making that preceded issuance of AD 
99-19-40, the FAA stated that preliminary indications were that the 
mounting configuration of connector 12XE was transmitting vibration to 
the terminal lugs of both connectors and to the mounting lugs of 
connector 15XE. Subsequently, in the preamble to AD 99-19-40, the FAA 
stated that the actions required by that AD were considered ``interim 
action'' until final action was identified, at which time the agency 
might consider further rulemaking.
    Since the issuance of that AD, laboratory analyses and flight tests 
conducted by Airbus have shown that excessive vibration is generated by 
the mounting configuration of the 15XE connector. That condition, if 
not corrected, could result in breakage of the mounting lugs on the 
15XE connector and the terminal lugs on the 15XE and 12XC connectors in 
the 101VU panel in the avionics compartment, resulting in loss of 
electrical power from the standby generator to the AC essential bus. 
Therefore, the FAA has determined that

[[Page 10383]]

further rulemaking action is indeed necessary, and this proposed AD 
follows from that determination.

Explanation of Relevant Service Information

    Airbus has issued Service Bulletins A310-24-2080 (for Model A310 
series airplanes) and A300-24-6070 (for Model A300-600 series 
airplanes), both dated December 15, 1999. The service bulletins 
describe procedures for replacing the mounting bracket for the 15XE 
connector, modifying the cable attachment adjacent to the connector, 
and replacing certain terminal lugs on the 15XE connector with lugs 
having a thicker contact area. The modification is intended to 
eliminate excessive vibration and prevent the possible consequent 
breakage of the mounting lugs on the 15XE connector and the terminal 
lugs on the 15XE and 12XC connectors. The Direction Generale de 
l'Aviation Civile (DGAC), which is the airworthiness authority for 
France, classified these service bulletins as mandatory and issued 
French airworthiness directive 2000-145-306(B), dated April 5, 2000, in 
order to ensure the continued airworthiness of these airplanes in 
France.

FAA's Conclusions

    These airplane models are manufactured in France and are 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.

Explanation of Requirements of Proposed Rule

    An unsafe condition has been identified that is likely to exist or 
develop on other airplanes of the same type design registered in the 
United States. The proposed AD would supersede AD 99-19-40 to continue 
to require inspecting the terminal lugs on the 12XC and 15XE connectors 
and the mounting lugs on the 15XE connectors for damage, and corrective 
action, if necessary. The proposed AD would add requirements for 
installation of a new mounting bracket for the 15XE connector, 
modification of the cable attachment adjacent to the connector, and 
replacement of certain terminal lugs on the 15XE connector with lugs 
having a thicker contact area. The proposed AD would require 
accomplishment of the actions specified in the service bulletins 
described previously, as applicable.

Explanation of Applicability of the Proposed AD

    Sections of AD 99-19-40 that pertain to applicability identify 
certain Airbus modifications by incorrect numbers. Those modification 
numbers have been corrected in this proposed AD.
    Because of this error in modification numbers in AD 99-19-40, it is 
possible that certain airplanes--Model A310 series airplanes on which 
Airbus Modification 05910 had been installed and Model A300-600 series 
airplanes on which Airbus Modification 06213 had been installed--did 
not comply with that AD. Therefore, the requirements of AD 99-19-40 are 
re-stated in the proposed AD. The compliance time for the inspection 
would be reset from the effective date of the AD.
    Operators of these airplanes who did comply with the requirements 
of AD 99-19-40 need not repeat the detailed visual inspections and 
corrective action required by that AD. However, such operators who 
elected to repair rather than replace a 15XE connector with damaged 
mounting lugs must continue to perform periodic inspections and 
periodic re-repairs of the connector until it is replaced with a new 
15XE connector.

Additional Changes to Applicability

    This proposed AD and AD 99-19-40 are applicable to the same 
airplane models. However, the model designation of the affected 
airplanes has been revised to conform to the type certificate data 
sheet listing for these airplanes. This proposed AD identifies these 
airplanes as ``Model A310, and Model A300 B4-600, A300 B4-600R, and 
A300 F4-600R series airplanes.''

Cost Impact

    There are approximately 109 airplanes of U.S. registry that would 
be affected by this proposed AD. The following information describes 
the estimated cost impact on U.S. operators of the proposed actions:

----------------------------------------------------------------------------------------------------------------
                                                                                            Per-
                     Action                       Work hours     Hourly     Parts cost    airplane    Fleet cost
                                                               labor rate                   cost
----------------------------------------------------------------------------------------------------------------
Inspection.....................................            2          $60           $0         $120      $13,080
Modification...................................            5           60          490          790       86,110
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    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 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.

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.

[[Page 10384]]

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 removing amendment 39-11327 (64 FR 
51190, September 22, 1999), and by adding a new airworthiness directive 
(AD), to read as follows:

Airbus Industrie: Docket 2000-NM-160-AD. Supersedes AD 99-19-40, 
Amendment 39-11327.

    Applicability: The following airplanes, certificated in any 
category and equipped with a standby generator (FIN 25XE); excluding 
airplanes on which Airbus Modification 12135 has been accomplished: 
Model A310 series airplanes on which Airbus Modification 05910 has 
been installed, and Model A300 B4-600, A300 B4-600R, and A300 F4-
600R (Collectively Called A300-600) series airplanes on which Airbus 
Modification 06213 has been installed.

    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 excessive vibrations generated by the mounting 
configuration of the 15XE connector, which could cause breakage of 
the terminal and mounting lugs on the 15XE connector in the 101VU 
panel in the avionics compartment, resulting in loss of electrical 
power from the standby generator, accomplish the following:

Restatement of Certain Actions Required by AD 99-19-40

Inspection and Corrective Actions

    (a) Prior to the accumulation of 5,000 total flight hours, or 
within 600 flight hours after the effective date of this AD, 
whichever occurs later: Accomplish the actions required by 
paragraphs (a)(1) and (a)(2) of this AD in accordance with Airbus 
All Operators Telex (AOT) 24-09, Revision 01, dated August 13, 1998.
    (1) Perform a detailed visual inspection of the terminal lugs on 
the 12XC and 15XE connectors to detect damage (i.e., overheat, 
cracking, twisting, or total rupture). If any damage is detected, 
prior to further flight, replace the terminal lugs with new terminal 
lugs, part number (P/N) NSA936501TA1004.
    (2) Perform a detailed visual inspection of the mounting lugs on 
the 15XE connector to detect damage (i.e., cracking or breaking). If 
any damage is detected, prior to further flight, accomplish the 
requirements of either paragraph (a)(2)(i) or (a)(2)(ii) of this AD.

    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.''

    (i) Replace connector 15XE with a new connector, P/N 
25811BOSHUNTKL, vendor code F0214 ECE. Or,
    (ii) Repair connector 15XE in accordance with Airbus AOT 24-09, 
Section 4.2.2.3. Repeat the detailed visual inspection required by 
paragraph (a)(2) of this AD of the repaired connector thereafter at 
intervals not to exceed 1 week, and repeat the repair with new cable 
ties thereafter at intervals not to exceed 3 months, until the 
replacement required by paragraph (a)(2)(i) of this AD is 
accomplished.

New Actions Required by This AD

Installation

    (b) Within 20 months after the effective date of this AD, 
install a new mounting bracket for the 15XE connector, modify the 
cable attachment adjacent to the connector, and replace certain 
terminal lugs with lugs having a thicker contact area, in accordance 
with Airbus Service Bulletin A310-24-2080 (for Model A310 series 
airplanes) or A300-24-6070 (for Model A300-600 series airplanes), 
both dated December 15, 1999, as applicable.

Replacement

    (c) Continue the detailed visual inspection of a repaired 15XE 
connector which is required by paragraph (a)(2)(ii) of this AD at 
intervals not to exceed 1 week, and continue the repair with new 
cable ties at intervals not to exceed 3 months, until the repaired 
15XE connector is replaced by a new 15XE connector.

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, 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, International 
Branch, ANM-116.

    Note 3: 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.

    Note 4: The subject of this AD is addressed in French 
airworthiness directive 2000-145-306(B), dated April 5, 2000.


    Issued in Renton, Washington, on February 9, 2001.
Vi L. Lipski,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 01-3855 Filed 2-14-01; 8:45 am]
BILLING CODE 4910-13-P