Airworthiness Directives; Airbus Model A300 B2 and B4 Series Airplanes, and Model A300 B4-600, A300 B4-600R, and A300 F4-600R (A300-600) Series Airplanes

[Federal Register Volume 65, Number 233 (Monday, December 4, 2000)]
[Rules and Regulations]
[Pages 75589-75591]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-30395]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-96-AD; Amendment 39-12025; AD 2000-24-18]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 B2 and B4 Series 
Airplanes, and Model A300 B4-600, A300 B4-600R, and A300 F4-600R (A300-
600) Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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[[Page 75590]]

SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to certain Airbus Model A300 B2 and B4 series airplanes, and 
Model A300-600 series airplanes, that requires repetitive inspections 
to detect chafing and the existence of repairs of the harness of the 
high-level sensor of the fuel surge tanks, and to detect chafe marks on 
the support canisters of the magnetic level indicators; and follow-on 
corrective actions, if necessary. This amendment also requires 
modification of the harness for the high-level sensor of the outer wing 
fuel tanks, which terminates certain repetitive inspections. This 
amendment is prompted by issuance of mandatory continuing airworthiness 
information by a foreign civil airworthiness authority. The actions 
specified by this AD are intended to prevent chafing of the harness of 
the high-level sensor, which could result in a short circuit and 
consequent fuel ignition source inside the outer wing fuel tanks.

DATES: Effective January 8, 2001.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of January 8, 2001.

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: Norman B. Martenson, Manager, 
International Branch, ANM-116, Transport Airplane Directorate, 1601 
Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 227-
2110; fax (425) 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 B2 and 
B4 series airplanes, and Model A300 B4-600, A300 B4-600R, and A300 F4-
600R (A300-600) series airplanes, was published in the Federal Register 
on June 13, 2000 (65 FR 37084). That action proposed to require 
repetitive inspections to detect chafing and the existence of repairs 
of the harness of the high-level sensor of the fuel surge tanks, and to 
detect chafe marks on the support canisters of the magnetic level 
indicators; and follow-on corrective actions, if necessary. That action 
also proposed to require modification of the harness for the high-level 
sensor of the outer wing fuel tanks, which would terminate certain 
repetitive inspections.

Clarification of Model Designation

    Since the issuance of the proposed AD, the FAA has changed the 
manner in which it identifies the airplane models referred to as 
``Airbus Model A300 and A300-600 series airplanes'' to reflect the 
model designation specified on the type certificate data sheet. This 
final rule has been revised to show the appropriate model designations 
for those airplanes.

Comments Received

    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 recommends that the FAA only mandate the inspection 
service bulletins, and not the modification service bulletins. The 
commenter is convinced that the inspections alone are sufficient to 
ensure safety.
    The FAA does not concur with the commenter's request. The FAA is 
aware that the Direction Generale de l'Aviation Civile (DGAC), which is 
the airworthiness authority for France, did not mandate the 
modification in the French airworthiness directive that addresses the 
identified unsafe condition. However, as explained in the proposal, the 
FAA has determined that long-term continued operational safety will be 
better assured by design changes to remove the source of the problem, 
rather than by repetitive inspections. No additional data were 
submitted by the commenter that would cause the FAA to change its 
position in this regard. No change to the final rule is necessary.

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 with the change described 
previously. The FAA has determined that this change will neither 
increase the economic burden on any operator nor increase the scope of 
the AD.

Cost Impact

    The FAA estimates that 37 airplanes of U.S. registry will be 
affected by this AD, that it will take approximately 1 work hour 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 $2,220, or $60 per airplane, per inspection cycle.
    It will take approximately 1 work hour per airplane to accomplish 
the required modification, at an average labor rate of $60 per work 
hour. Based on these figures, the cost impact of the modification 
required by this AD on U.S. operators is estimated to be $2,220, or $60 
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 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 final rule does not have federalism 
implications under Executive Order 13132.
    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:


[[Page 75591]]


    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:

2000-24-18  Airbus Industrie: Amendment 39-12025. Docket 2000-NM-96-
AD.

    Applicability: Model A300 B2 and B4 series airplanes, and Model 
A300 B4-600, A300 B4-600R, and A300 F4-600R (A300-600) series 
airplanes; certificated in any category; except those airplanes on 
which Airbus Modification 04489 has been installed during 
production.

    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 (b) 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 chafing of the wire harnesses of the high-level 
sensors, which could result in a short circuit and consequent fuel 
ignition source inside the outer wing fuel tanks, accomplish the 
following:

Detailed Visual Inspection

    (a) Within 500 flight hours after the effective date of this AD, 
perform a detailed visual inspection to detect chafing and the 
existence of repairs of the harness (cable) of the high-level sensor 
of the fuel surge tanks, and to detect chafe marks on the support 
canisters of the magnetic level indicators, in accordance with 
Airbus Service Bulletin A300-28-0077 (for Model A300 series 
airplanes) or A300-28-6062 (for Model A300-600 series airplanes), 
each dated July 19, 1999, as applicable.
    (1) For airplanes on which modification of the harness in 
accordance with Airbus Service Bulletin A300-28-0058 (for Model A300 
series airplanes) or A300-28-6020 (for Model A300-600 series 
airplanes), as applicable, HAS NOT been accomplished: Accomplish the 
requirements of paragraphs (a)(1)(i) and (a)(1)(ii) of this AD.
    (i) Repeat the detailed visual inspection thereafter at 
intervals not to exceed 500 flight hours until the requirements of 
paragraph (a)(1)(ii) of this AD are accomplished. If any wire 
chafing, chafe mark, or existing repair is detected during any 
inspection, prior to further flight, determine the appropriate 
repair and/or condition of repair as specified in Inspection Table 1 
of the Accomplishment Instructions of Airbus Service Bulletin A300-
28-0077 or A300-28-6062, as applicable. At the times specified in 
Inspection Table I, accomplish corrective actions (e.g., temporary 
or permanent repairs, and follow-on inspections and repairs) in 
accordance with the applicable service bulletin. If any discrepancy 
is found during any follow-on inspection, prior to further flight, 
repair the discrepancy in accordance with the applicable service 
bulletin.
    (ii) Within 18 months after the effective date of this AD, 
modify the harness of the high-level sensor in the outer wing fuel 
tanks in accordance with Airbus Service Bulletin A300-28-0058, 
Revision 02 (for Model A300 series airplanes), or A300-28-6020, 
Revision 01 (for Model A300-600 series airplanes), each dated 
September 28, 1999. Accomplishment of the modification terminates 
the 500-flight-hour repetitive inspection required by paragraph 
(a)(1) of this AD. However, if a temporary repair is installed, the 
10,000-flight-hour detailed visual inspection specified in the 
follow-on corrective actions of Table 1 continues to be required by 
this AD.
    (2) For airplanes on which modification of the harness in 
accordance with Airbus Service Bulletin A300-28-0058 (for Model A300 
series airplanes) or A300-28-6020 (for Model A300-600 series 
airplanes), as applicable, HAS been accomplished: Accomplish the 
requirements of paragraph (a)(2)(i) or (a)(2)(ii), as applicable.
    (i) If no wire chafing, chafe marks, or existing repairs are 
detected, no further action is required by this AD.
    (ii) If any wire chafing, chafe mark, or existing repair is 
detected, prior to further flight, determine the appropriate repair 
and/or condition of repair specified in Inspection Table 2 of the 
Accomplishment Instructions of Airbus Service Bulletin A300-28-0077 
or A300-28-6062, as applicable. At the times specified in Inspection 
Table 2, accomplish corrective actions (e.g., temporary or permanent 
repairs and follow-on inspections) in accordance with the applicable 
service bulletin. If any discrepancy is found during any follow-on 
inspection, prior to further flight, repair the discrepancy 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 mirrors, magnifying lenses, etc., may be used. Surface cleaning 
and elaborate access procedures may be required.''


    Note 3: Modification accomplished prior to the effective date of 
this AD in accordance with Airbus Service Bulletin A300-28-0058, 
dated December 15, 1988, or Revision 01, dated October 1, 1991 (for 
Model A300 series airplanes); or A300-28-6020, dated December 15, 
1988 (for Model A300-600 series airplanes); is considered acceptable 
for compliance with the action specified in paragraph (a)(1)(ii) of 
this AD.

Alternative Methods of Compliance

    (b) 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 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

    (c) 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.

Incorporation by Reference

    (d) The actions shall be done in accordance with Airbus Service 
Bulletin A300-28-0077, dated July 19, 1999; Airbus Service Bulletin 
A300-28-0058, Revision 02, dated September 28, 1999; Airbus Service 
Bulletin A300-28-6062, dated July 19, 1999; or Airbus Service 
Bulletin A300-28-6020, Revision 01, dated September 28, 1999; as 
applicable. 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.

    Note 5: The subject of this AD is addressed in French 
airworthiness directive 1999-404-293(B), dated October 6, 1999.

Effective Date

    (e) This amendment becomes effective on January 8, 2001.


    Issued in Renton, Washington, on November 22, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-30395 Filed 12-1-00; 8:45 am]
BILLING CODE 4910-13-P

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