[Federal Register Volume 66, Number 6 (Tuesday, January 9, 2001)]
[Proposed Rules]
[Pages 1612-1616]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-511]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NM-86-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 B2 and A300 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: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes the adoption of a new airworthiness 
directive (AD) that is applicable to all Airbus Model A300 B2 and A300 
B4 series airplanes, and all A300 B4-600, A300 B4-600R, and A300 F4-
600R (A300-600) series airplanes. For certain airplanes, this proposal 
would require modifying the frame 40 aft fittings. For all airplanes, 
this proposal would require repetitive nondestructive test inspections 
to detect cracking of the frame 40 aft fittings; a modification would 
be required as corrective action for cracking or provided as optional 
terminating action for the repetitive inspections. 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 detect and correct propagation of 
cracks on the frame 40 aft fittings due to local stress concentrations 
at the frame 40 upper flange runout, which could result in reduced 
structural integrity of the airplane.

DATES: Comments must be received by February 8, 2001.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 99-NM-86-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.
    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; e.g., discuss a request 
to change a compliance time and a request to change a service bulletin 
reference as two issues.
     For each issue, state the specific change requested to the 
proposed AD.
     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 ++.'' 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. 99-NM-86-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    The Direction Generale de l'Aviation Civile (DGAC), which is the 
airworthiness authority for France,

[[Page 1613]]

notified the FAA that an unsafe condition may exist on all Airbus Model 
A300 B2 and A300 B4 series airplanes, and all Model A300 B4-600, A300 
B4-600R, and A300 F4-600R (A300-600) series airplanes. The DGAC reports 
that cracks have been found on the frame 40 aft fittings at stringer 33 
on the left and right sides of the fuselage. The cracks were caused by 
a local stress concentration at the frame 40 upper flange runout. This 
condition, if not corrected, could result in reduced structural 
integrity of the airplane.

Explanation of Relevant Service Information

    Airbus has issued the following service bulletins:

----------------------------------------------------------------------------------------------------------------
               Model                       Service bulletin          Revision level              Date
----------------------------------------------------------------------------------------------------------------
A300..............................  A300-53-0296                                  01  Sep. 30, 1998.
                                                                                  02  May 12, 1999.
A300-600..........................  A300-53-6048                                  01  Sep. 30, 1998.
                                                                                  03  Feb. 21, 2000.
A300..............................  A300-53-0268                                   4  Aug. 16, 1995.
A300-600..........................  A300-57-6052                                  02  April 4, 1997.
A300..............................  A300-53-0297                                   2  Oct. 31, 1995.
A300-600..........................  A300-57-6053                                   1  Oct. 31, 1995.
                                                                                  02  June 2, 1999.
----------------------------------------------------------------------------------------------------------------

    Service Bulletins A300-53-0296 and A300-53-6048 describe procedures 
for modification of the frame 40 aft fittings on certain airplanes, and 
repetitive nondestructive test inspections to detect cracking of the 
frame 40 aft fittings on all airplanes. Corrective actions for cracking 
involve trimming the front spar angle and vertical stiffener; drilling, 
reaming, and spotfacing attachment holes; installing a new frame 40 aft 
fitting and pick-up angles; and inspecting (by a detailed visual, high 
frequency eddy current, or liquid penetrant method) to detect cracking 
of the frame 40 forward fittings.
    Those service bulletins refer to Service Bulletins A300-53-0268 and 
A300-57-6052 as additional sources of service information for 
corrective actions if cracking is found in the frame 40 aft fitting. 
Service Bulletins A300-53-0268 and A300-57-6052 describe procedures 
for, among other things, an inspection (detailed visual, eddy current, 
or liquid penetrant) to detect cracking of the forward fitting at frame 
40.
    Service Bulletins A300-53-0296 and A300-53-6048 also refer to 
Service Bulletins A300-53-0297 and A300-57-6053 as additional sources 
of service information to modify the aft angle fittings at frame 40. 
The modification involves replacing the angle fittings with new larger 
fittings. The service bulletins recommend the modification to repair 
cracked fittings and eliminate the need for the repetitive inspections.
    Accomplishment of the actions specified in the service bulletins 
described above is intended to adequately address the identified unsafe 
condition. The DGAC classified Airbus Service Bulletins A300-53-0296 
and A300-53-6048 as mandatory, and issued French airworthiness 
directive 1998-481-270(B) R1, dated July 12, 2000, 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

    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 require accomplishment of 
the actions specified in the service bulletins described previously, 
except as discussed below.
    For airplanes on which no cracking is found, this proposed AD would 
also provide for optional terminating action for the repetitive 
inspections. Operators should note that, to be consistent with the 
findings of the DGAC, the FAA has determined that the repetitive 
inspections proposed by this AD can be allowed to continue in lieu of 
accomplishment of a terminating action. In making this determination, 
the FAA considers that, in this case, long-term continued operational 
safety will be adequately ensured by accomplishing the repetitive 
inspections to detect cracking before it represents a hazard to the 
airplane.

Differences Between Proposed AD and Relevant Service Information

    Operators should note that the service bulletins provide a method 
of adjustment of the inspection thresholds and intervals, relative to 
average flight times, of various groups of airplanes. The service 
bulletins provide a complicated method of determining the thresholds 
and intervals for various groups of airplanes. The FAA has determined 
that it would be difficult to enforce the implementation of that method 
for determining the compliance times. Therefore, this proposed AD does 
not provide for adjustments to the compliance times to accommodate 
average flight times that vary among operators. The FAA has established 
a single threshold and interval for each identified group of airplanes. 
In developing appropriate compliance times for this AD, the FAA 
considered not only the manufacturer's method for determining the 
compliance times, but the degree of urgency associated with addressing 
the subject unsafe condition and the average utilization of the 
affected fleet. The compliance times in this proposed AD are derived 
from the average flight times for affected airplanes as follows:

------------------------------------------------------------------------
                                                          Average flight
                         Model                              time  (in
                                                             minutes)
------------------------------------------------------------------------
A300 B2 series.........................................               65
A300 B4-100 series.....................................               80
A300 B4-200 series.....................................              125
A300-600 series........................................              125
------------------------------------------------------------------------

    In light of these factors, the FAA finds the proposed thresholds 
and intervals to be warranted, in that they represent appropriate 
intervals of time for affected

[[Page 1614]]

airplanes to continue to operate without compromising safety. However, 
the provisions of paragraph (e) of this proposed AD would enable the 
FAA to approve requests for adjustments to the compliance time if data 
are submitted that substantiate an acceptable level of safety provided 
by such an adjustment.
    Operators should further note that, unlike the procedures described 
in Airbus Service Bulletins A300-57-6052 and A300-53-0268, this 
proposed AD would not permit further flight if cracking is detected in 
the frame 40 forward fitting. The FAA has determined that, because of 
the safety implications and consequences associated with such cracking, 
any cracked subject fitting must be repaired or modified before further 
flight.
    In addition, although the service bulletins specify that the 
manufacturer may be contacted for disposition of certain repair 
conditions, this proposal would require that those conditions be 
repaired in accordance with a method approved by either the FAA or the 
DGAC (or its delegated agent). In light of the type of repair that 
would be required to address the identified unsafe condition, and, in 
consonance with existing bilateral airworthiness agreements, the FAA 
has determined that, for this proposed AD, a repair approved by either 
the FAA or the DGAC would be acceptable for compliance with this 
proposed AD.

Cost Impact

    The FAA estimates that 70 airplanes of U.S. registry would be 
affected by this proposed AD.
    For affected airplanes, it would take approximately 92 work hours 
per airplane to accomplish the proposed modification, at an average 
labor rate of $60 per work hour. Required parts would cost as much as 
$874 per airplane. Based on these figures, the cost impact of the 
proposed modification is estimated to be as much as $6,394 per 
airplane.
    It would take approximately 10 work hours per airplane to 
accomplish the proposed inspection, at an average labor rate of $60 per 
work hour. Based on these figures, the cost impact of the proposed 
inspection on U.S. operators is estimated to be $42,000, or $600 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 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 planning time, time 
required to gain access and close up, 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 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 99-NM-86-AD.

    Applicability: All Model A300 B2 and A300 B4 series airplanes, 
and Model A300 B4-600, A300 B4-600R, and A300 F4-600R (A300-600) 
series 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 (e) 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 propagation of cracks on the frame 40 aft 
fittings due to local stress concentrations at the upper flange 
runout of frame 40, which could result in reduced structural 
integrity of the airplane, accomplish the following:

Modification

    (a) For airplanes on which Airbus Modification 10430 has not 
been done before the effective date of this AD: When you do the 
inspection required by paragraph (b) of this AD, modify the profile 
of frame 40 aft fittings per the service information specified in 
Table 1 of this AD. Table 1 is as follows:

                          Table 1.--Service Information for Modification and Inspection
----------------------------------------------------------------------------------------------------------------
              Model                      Service Bulletin           Revision level                Date
----------------------------------------------------------------------------------------------------------------
A300.............................  A300-53-0296                  Revision 01.........  Sept. 30, 1998.
                                                                 Or Revision 02......  May 12, 1999.
A300-600.........................  A300-53-6048                  Revision 01.........  Sept. 30, 1998.
                                                                 Or Revision 03......  Feb. 21, 2000
----------------------------------------------------------------------------------------------------------------


[[Page 1615]]

    Note 2: Modification per Airbus Service Bulletin A300-53-6048, 
Revision 02, dated May 12, 1999, is acceptable for compliance with 
paragraph (a) of this AD for Model A300-600 series airplanes.

Inspection

    (b) For all airplanes, inspect the airplane per Table 2 of this 
AD, as follows:

                    Table 2.--Inspection Requirements
------------------------------------------------------------------------
              Requirements                         Description
------------------------------------------------------------------------
(1) Area to inspect....................  The frame 40 aft fitting.
(2) Type of inspection.................  Nondestructive test (NDT).
(3) Compliance time....................  As specified by paragraph (c)
                                          of this AD.
(4) Discrepancies to detect............  Cracking.
(5) Required service information.......  As specified by Table 1 of this
                                          AD.
(6) Follow-on actions if you find no     Repeat the inspection
 cracking.                                thereafter at the intervals
                                          specified by Table 3 of this
                                          AD.
(7) Corrective actions if you find       Do the actions specified by
 cracking.                                paragraph (d) of this AD.
(8) Terminating action.................  Paragraph (d) terminates
                                          paragraph (b) of this AD.
------------------------------------------------------------------------

    Note 3: A nondestructive test (NDT) per Part 6 53-15-30 
procedure C of the NDT manual, is also acceptable for compliance 
with paragraph (b) of this AD.
    Note 4: Accomplishment of an inspection per Airbus Service 
Bulletin A300-53-6048, Revision 02, dated May 12, 1999, is 
acceptable for compliance with the requirements of paragraph (b) of 
this AD for Model A300-600 series airplanes.
    (c) Perform the inspection of paragraph (b) of this AD per the 
schedule in Table 3, as follows:

                                 Table 3.--Compliance Thresholds for Inspection
----------------------------------------------------------------------------------------------------------------
                                    If the total flight
                                    cycles accumulated                            And repeat the inspection at
         For model . . .           on the airplane is .   Then inspect . . .           least every . . .
                                            . .
----------------------------------------------------------------------------------------------------------------
A300-600 series airplanes, pre-    Fewer than 6,200....  Before the airplane   7,500 flight cycles.
 Modification 10430S20428.                                accumulates 7,700
                                                          total flight cycles.
                                   At least 6,200 and    Within 1,500 flight
                                    fewer than 9,700.     cycles after the
                                                          effective date of
                                                          this AD.
                                   At least 9,700......  Within 750 flight
                                                          cycles after the
                                                          effective date of
                                                          this AD.
A300-600 series airplanes, post-   Fewer than 19,600...  Before the airplane   7,500 flight cycles.
 Modification 10430S20428.                                accumulates 21,100
                                                          total flight cycles.
                                   At least 19,600 and   Within 1,500 flight
                                    fewer than 23,100.    cycles after the
                                                          effective date of
                                                          this AD.
                                   At least 23,100.....  Within 750 flight
                                                          cycles after the
                                                          effective date of
                                                          this AD.
A300 B2 series airplanes.........  Fewer than 12,000...  Before the airplane   5,500 flight cycles.
                                                          accumulates 14,000
                                                          total flight cycles.
                                   At least 12,000 and   Within 2,000 flight
                                    fewer than 17,000.    cycles after the
                                                          effective date of
                                                          this AD.
                                   At least 17,000.....  Within 1,000 flight
                                                          cycles after the
                                                          effective date of
                                                          this AD.
A300 B4-100 series airplanes.....  Fewer than 9,500....  Before the airplane   4,500 flight cycles.
                                                          accumulates 11,500
                                                          total flight cycles.
                                   At least 9,500 and    Within 2,000 flight
                                    fewer than 14,500.    cycles after the
                                                          effective date of
                                                          this AD.
                                   At least 14,500.....  Within 1,000 flight
                                                          cycles after the
                                                          effective date of
                                                          this AD.
A300 B4-200 series airplanes.....  Fewer than 8,500....  Before the airplane   4,000 flight cycles.
                                                          accumulates 10,500
                                                          total flight cycles.
                                   At least 8,500 and    Within 2,000 flight
                                    fewer than 13,500.    cycles after the
                                                          effective date of
                                                          this AD.
                                   At least 13,500.....  Within 1,000 flight
                                                          cycles after the
                                                          effective date of
                                                          this AD.
----------------------------------------------------------------------------------------------------------------


    Note 5: An NDT inspection is also required by AD 98-25-07, 
amendment 39-10933, to be repetitively performed on Model A300-600 
series airplanes on which Airbus Modification 10453 has not been 
installed. For those airplanes, if the inspection is done within the 
applicable compliance time specified by paragraph (c) of this AD, 
the threshold for the initial inspection of paragraph (b) of this AD 
may be extended by 1,500 flight cycles.

Corrective Actions

    (d) If any crack is found during any inspection of a frame 40 
aft fitting required by this AD, prior to further flight, accomplish 
the actions specified by paragraph (d)(1) or (d)(2), as applicable, 
and paragraph (d)(3) of this AD. Accomplishment of the actions of 
this paragraph terminates the repetitive inspection requirements of 
paragraph (b) of this AD.
    (1) For Model A300-600 series airplanes: Replace the angle 
fittings with new, larger

[[Page 1616]]

fittings, in accordance with Airbus Service Bulletin A300-57-6053, 
Revision 1, dated October 31, 1995, or Revision 02, dated June 2, 
1999.
    (2) For Model A300 series airplanes listed in Airbus Service 
Bulletin A300-53-0297, Revision 2, dated October 31, 1995: Replace 
the angle fittings with new, larger fittings, in accordance with the 
service bulletin.
    (3) For all airplanes: Perform a detailed visual, high frequency 
eddy current (HFEC), or liquid penetrant inspection, as applicable, 
to detect cracking in the frame 40 forward fitting in accordance 
with Airbus Service Bulletin A300-57-6052, Revision 02, dated April 
4, 1997 (for Model A300-600 series airplanes), or Airbus Service 
Bulletin A300-53-0268, Revision 4, dated August 16, 1995 (for Model 
A300 series airplanes); as applicable.
    (i) If no crack is found: No further action is required by this 
AD.
    (ii) Except as provided by paragraph (d)(3)(iii) of this AD: If 
any crack is found, during an inspection required by paragraph 
(d)(3) of this AD, prior to further flight, repair per the 
applicable service bulletin.
    (iii) If any crack is detected during any inspection required by 
paragraph (d)(3) of this AD, and the applicable service bulletin 
specifies to contact the manufacturer for an appropriate action. 
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 Gonorale de l'Aviation Civile 
(DGAC) (or its delegated agent). For a repair method to be approved 
by the Manager, International Branch, ANM-116, as required by this 
paragraph, the Manager's approval letter must specifically reference 
this AD.

Alternative Methods of Compliance

    (e) 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.

    Note 6: 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

    (f) 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 7: The subject of this AD is addressed in French 
airworthiness directive 1998-481-270(B) R1, dated July 12, 2000.


    Issued in Renton, Washington, on January 3, 2001.
Dorenda D. Baker,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 01-511 Filed 1-8-01; 8:45 am]
BILLING CODE 4910-13-U