[Federal Register Volume 66, Number 7 (Wednesday, January 10, 2001)]
[Proposed Rules]
[Pages 1919-1921]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-662]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-306-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 B4-601, B4-603, B4-
620, B4-605R, B4-622R, and F4-605R (A300-600) Series 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 all Airbus Model A300-600 series 
airplanes, that currently requires repetitive ultrasonic inspections to 
detect cracks on the forward fittings in the radius of frame 40 
adjacent to the tension bolts in the center section of the wings, and 
various follow-on actions. That AD was prompted by reports of cracking 
due to fatigue-related stress in the radius of frame 40 adjacent to the 
tension bolts at the center/outer wing junction. The actions specified 
by that AD are intended to detect and correct fatigue cracking on the 
forward fittings in the radius of frame 40 adjacent to the tension 
bolts in the center section of the wings, which could result in reduced 
structural integrity of the wings. 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-306-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-306-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 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

[[Page 1920]]

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-306-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-306-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    On February 11, 2000, the FAA issued AD 2000-03-20, amendment 39-
11580 (65 FR 8642, February 22, 2000), applicable to all Airbus Model 
A300-600 series airplanes, to require repetitive ultrasonic inspections 
to detect cracks on the forward fittings in the radius of frame 40 
adjacent to the tension bolts in the center section of the wings, and 
various follow-on actions. That action was prompted by reports of 
cracking due to fatigue-related stress in the radius of frame 40 
adjacent to the tension bolts at the center/outer wing junction. The 
requirements of that AD are intended to detect and correct fatigue 
cracking on the forward fittings in the radius of frame 40 adjacent to 
the tension bolts in the center section of the wings, which could 
result in reduced structural integrity of the wings.

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 1995-063-177(B) R4, 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 unsafe 
condition specified previously for other Model 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 2000-03-20 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 2000-03-20 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 35 airplanes of U.S. registry would be 
affected by this proposed AD, that it would take approximately 2 work 
hours per airplane (1 work hour per side) to accomplish the proposed 
ultrasonic 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 $4,200, or $120 per 
airplane, per inspection cycle.
    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.

The Proposed Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation

[[Page 1921]]

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 39-11580 (65 FR 
8642, February 22, 2000), and by adding a new airworthiness directive 
(AD), to read as follows:

Airbus Industrie: Docket 2000-NM-306-AD. Revises AD 2000-03-20, 
Amendment 39-11580.

    Applicability: 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 
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)(1) 
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 fatigue cracking on the forward fittings 
in the radius of frame 40 adjacent to the tension bolts in the 
center section of the wings, which could result in reduced 
structural integrity of the wings, accomplish the following:

Inspections and Corrective Actions

    (a) Perform an ultrasonic inspection to detect cracking on the 
forward fittings in the radius of frame 40 adjacent to the tension 
bolts in the center section of the wings, in accordance with Airbus 
Service Bulletin A300-57-6062, Revision 02, dated January 29, 1997, 
at the applicable time specified in either paragraph (a)(1) or 
(a)(2) of this AD.
    (1) For airplanes that have accumulated fewer than 9,100 total 
landings or 22,300 total flight hours as of March 28, 2000 (the 
effective date of AD 2000-03-20, amendment 39-11580): Inspect at the 
later of the times specified in either paragraph (a)(1)(i) or 
(a)(1)(ii) of this AD.
    (i) Prior to the accumulation of 7,250 total landings or 17,700 
total flight hours, whichever occurs first.
    (ii) Within 1,500 landings after March 28, 2000.
    (2) For airplanes that have accumulated 9,100 total landings or 
more and 22,300 total flight hours or more as of March 28, 2000: 
Inspect within 750 landings after March 28, 2000.

    Note 2: Inspections that were accomplished prior to March 28, 
2000, in accordance with Airbus Service Bulletin A300-57-6062, 
Revision 1, dated July 23, 1995, are considered acceptable for 
compliance with paragraph (a) of this AD.

    (b) If no crack is detected during the inspection required by 
paragraph (a) of this AD, repeat the ultrasonic inspection required 
by that paragraph thereafter at intervals not to exceed 6,500 
landings or 16,000 flight hours, whichever occurs first; in 
accordance with Airbus Service Bulletin A300-57-6062, Revision 02, 
dated January 29, 1997.
    (c) If any crack is detected during any inspection required by 
paragraph (a) or (b) of this AD, prior to further flight, install an 
access door, and perform an eddy current inspection to confirm the 
presence of a crack; in accordance with Airbus Service Bulletin 
A300-57-6062, Revision 02, dated January 29, 1997. Accomplishment of 
this eddy current inspection terminates the repetitive inspection 
requirement of paragraph (b) of this AD.
    (1) If no crack is detected during the eddy current inspection, 
repeat the eddy current inspection, in accordance with the service 
bulletin, thereafter at intervals not to exceed 6,500 landings or 
16,000 flight hours, whichever occurs first.
    (2) If any crack is detected during any eddy current inspection 
performed in accordance with paragraph (c) or (c)(1) of this AD, 
prior to further flight, blend out the crack and repeat the eddy 
current inspection in accordance with the service bulletin.
    (i) If the eddy current inspection performed after the blend-out 
shows that the crack has been removed, and if the blend-out is equal 
to or less than 50 millimeters (mm) long and equal to or less than 2 
mm deep, thereafter repeat the eddy current inspection at intervals 
not to exceed 2,800 landings or 7,000 flight hours, whichever occurs 
first.
    (ii) If the eddy current inspection performed after the blend-
out shows that the crack has not been removed, or if the blend-out 
is more than 50 mm long or more than 2 mm deep, prior to further 
flight, repair in accordance with a method approved by the Manager, 
International Branch, ANM-116, FAA, Transport Airplane Directorate; 
or the Direction Generale de l'Aviation Civile (or its delegated 
agent).

Alternative Methods of Compliance

    (d)(1) 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. 
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.
    (2) Operators may request an extension to the compliance times 
of this AD in accordance with the ``adjustment-for-range'' formula 
found in Paragraph 1.B.(5) of Airbus Service Bulletin A300-57-6062, 
Revision 02, dated January 29, 1997; and provided in A300-600 
Maintenance Review Board, Section 5, Paragraph 5.4. The average 
flight time per flight cycle (landing) in hours used in this formula 
should be for an individual airplane. Average flight time for a 
group of airplanes may be used if all airplanes of the group have 
flight times differing by no more than 10 percent. If compliance 
times are based on the average flight time for a group of airplanes, 
the flight times for individual airplanes of the group must be 
included for FAA review.

    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 
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 4: The subject of this AD is addressed in French 
airworthiness directive 1995-063-177(B) R4, 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. 01-662 Filed 1-9-01; 8:45 am]
BILLING CODE 4910-13-U