[Federal Register Volume 66, Number 7 (Wednesday, January 10, 2001)]
[Proposed Rules]
[Pages 1917-1919]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-660]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-297-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 B2 and B4 Series 
Airplanes; and Model A300 B4-601, B4-603, B4-620, B4-605R, B4-622R, and 
F4-605R (A300-600) Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes to revise an existing airworthiness 
directive (AD), applicable to certain Airbus Model A300 series 
airplanes; and all Model A300-600 series airplanes; that currently 
requires a one-time inspection for cracking of the gantry lower flanges 
in the main landing gear (MLG) bay area; and repair, if necessary. That 
AD was prompted by issuance of mandatory continuing airworthiness 
information by a foreign civil airworthiness authority. The actions 
specified by that AD are intended to detect and correct cracking of the 
gantry lower flanges in the MLG bay area, which could result in 
decompression of the airplane. This action would remove airplanes from 
the applicability of the existing AD.

DATES: Comments must be received by February 9, 2001.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2000-NM-297-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. 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-297-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: Norman B. Martenson, Manager, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2110; 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

[[Page 1918]]

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 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 Number 2000-NM-297-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-297-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    On June 17, 1998, the FAA issued AD 98-13-37, amendment 39-10628 
(63 FR 34589, June 25, 1998), applicable to certain Airbus Model A300 
series airplanes, and all Model A300-600 series airplanes. That AD 
requires a one-time inspection for cracking of the gantry lower flanges 
in the main landing gear (MLG) bay area; and repair, if necessary. That 
action was prompted by issuance of mandatory continuing airworthiness 
information by a foreign civil aviation authority. The requirements of 
that AD are intended to detect and correct cracking of the gantry lower 
flanges in the MLG bay area, which could result in decompression of the 
airplane.

Actions Since Issuance of Previous Rule

    Since the issuance of that AD, the Direction Generale de l'Aviation 
Civile (DGAC), which is the airworthiness authority for France, has 
issued French airworthiness directive 1997-372-236(B) R1, dated July 
12, 2000. The revised French airworthiness directive removes Model A300 
F4-622R from the applicability of the original French airworthiness 
directive since that airplane model is not subject to the same unsafe 
condition specified previously for other Model A300 and A300-600 series 
airplanes.

FAA's Conclusions

    These airplane models are manufactured in France and are type 
certificated for operation in the United States under the provisions of 
Sec. 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

    Since 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 revise AD 98-13-37 to 
continue to require the actions specified in that AD. This proposed AD 
would remove Model A300 F4-622R airplanes from the applicability of the 
existing AD.

Explanation of Airplane Model Designation

    The applicability of AD 98-13-37 includes the following airplane 
models: A300 B4-601, B4-603, B4-620, B4-605R, B4-622R, F4-605R, and F4-
622R. However, since these airplanes are commonly referred to as 
``Model A300-600 series airplanes,'' that model designation was 
specified in the applicability of that AD. Since the issuance of that 
AD, the FAA has determined that these airplanes should be designated 
exactly as they appear on the type certificate data sheet. Therefore, 
the applicability of this proposed AD designates each specific model 
(excluding Model F4-622R airplanes, which are purposely removed) 
without referring to the common name of the airplane.

Cost Impact

    Since this proposed AD would merely delete airplanes from the 
applicability of the rule, it would add no additional costs, and would 
require no additional work to be performed by affected operators. The 
current costs associated with this proposed AD are reiterated in their 
entirety (as follows) for the convenience of affected operators:
    The FAA estimates that 67 airplanes of U.S. registry would be 
affected by this proposed AD, that it would take approximately 4 work 
hours per airplane to accomplish the proposed inspection, and that the 
average labor rate is $60 per work hour. Based on these figures, the 
cost impact of the proposed inspection on U.S. operators is estimated 
to be $16,080, or $240 per airplane.
    The cost impact figure discussed above 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. 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 1919]]

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 39-10628 (63 FR 
34589, June 25, 1998), and by adding a new airworthiness directive 
(AD), to read as follows:

Airbus Industrie:  Docket 2000-NM-297-AD. Revises AD 98-13-37, 
Amendment 39-10628.
    Applicability: Model A300 B2 and B4 series airplanes on which 
Airbus Modification 3474 has been accomplished; and all Model A300 
B4-601, B4-603, B4-620, B4-605R, B4-622R, and F4-605R airplanes; 
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 (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 detect and correct cracking of the gantry lower flanges in 
the main landing gear (MLG) bay area, which could result in 
decompression of the airplane, accomplish the following:

Restatement of Actions Required by AD 98-13-37

    (a) Prior to the accumulation of 16,300 total flight cycles, or 
within 500 flight cycles after July 30, 1998 (the effective date of 
AD 98-13-37, amendment 39-10628), whichever occurs later, perform a 
one-time ultrasonic inspection for cracking of the gantry lower 
flanges in the MLG bay area, in accordance with Airbus All Operators 
Telex (AOT) 53-11, dated October 13, 1997.
    (1) If any cracking is detected, prior to further flight, repair 
in accordance with the AOT.
    (2) If no cracking is detected, no further action is required by 
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 2: 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 
Secs. 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 3: The subject of this AD is addressed in French 
airworthiness directive 1997-372-236(B) R1, dated July 12, 2000.


    Issued in Renton, Washington, on January 4, 2001.
Dorenda D. Baker,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 01-660 Filed 1-9-01; 8:45 am]
BILLING CODE 4910-13-P