[Federal Register Volume 69, Number 136 (Friday, July 16, 2004)]
[Proposed Rules]
[Pages 42612-42616]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-16174]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2004-18593; Directorate Identifier 2004-NM-21-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 B2, A300 B4, A300 B4-
600, and A300 B4-600R Series Airplanes; and Model A300 C4-605R Variant 
F and A300 F4-605R Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to supersede an existing airworthiness 
directive (AD) for all Airbus Model A300 B4-601, A300 B4-603, A300 B4-
620, A300 B4-605R, A300 B4-622R, and A300 F4-605R airplanes. That AD 
currently requires repetitive inspections for cracking in the area 
surrounding certain fuselage attachment holes, installation of new 
fasteners for certain airplanes, and certain follow-on corrective 
actions if necessary. This proposed AD would require modifying certain 
fuselage frames, which would terminate certain repetitive inspections. 
This proposed AD would also add airplanes to the applicability. This 
proposed AD is prompted by the development of a modification intended 
to prevent cracking of the center section of the fuselage, which could 
result in a ruptured frame foot and reduced structural integrity of the 
airplane.

DATES: We must receive comments on this proposed AD by August 16, 2004.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD.
     DOT Docket web site: Go to  http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide rulemaking web site: Go to http://www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility; U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, 
Washington, DC 20590.
     Fax: (202) 493-2251.
     Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For the service information identified in this proposed AD, contact 
Airbus, 1

[[Page 42613]]

Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France.
    You can examine the contents of this AD docket on the Internet at 
http://dms.dot.gov, or at the Docket Management Facility, U.S. 
Department of Transportation, 400 Seventh Street, SW., room PL-401, on 
the plaza level of the Nassif Building, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, 1601 
Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 227-
2125; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Docket Management System

    We have implemented new procedures for maintaining AD dockets 
electronically. As of May 17, 2004, new AD actions are posted on DMS 
and assigned a docket number. We track each AD action and assign an 
additional identifier, which identifies the directorate issuing the 
action. The DMS AD docket number is in the form ``Docket No. FAA-2004-
99999.'' The FAA directorate identifier is in the form ``Directorate 
Identifier 2004-NM-999-AD.'' Each DMS AD docket also lists the 
directorate identifier (``Old Docket Number'') as a cross-reference for 
searching purposes.

Comments Invited

    We invite you to submit any written relevant data, views, or 
arguments regarding this proposal. Send your comments to an address 
listed under ADDRESSES. Include ``Docket No. FAA-2004-18593; 
Directorate Identifier 2004-NM-21-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the proposed AD. We will 
consider all comments received by the closing date and may amend the 
proposed AD in light of those comments.
    We will post all comments we receive, without change, to http://dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact with FAA 
personnel concerning this proposed rulemaking. Using the search 
function of our docket web site, anyone can find and read the comments 
in any of our dockets, including the name of the individual who sent 
the comment (or signed the comment on behalf of an association, 
business, labor union, etc.). You can review the DOT's complete Privacy 
Act Statement in the Federal Register published on April 11, 2000 (65 
FR 19477-78), or you may visit http://dms.dot.gov.
    We are reviewing the writing style we currently use in regulatory 
documents. We are interested in your comments on whether the style of 
this document is clear, and your suggestions to improve the clarity of 
our communications that affect you. You can get more information about 
plain language at http://www.faa.gov/language and http://www.plainlanguage.gov.

Examining the Dockets

    The AD docket contains the proposed AD, comments, and any final 
disposition. You can examine the AD docket in person at the Docket 
Management Facility office between 9 a.m. and 5 p.m., Monday through 
Friday, except Federal holidays. The Docket Management Facility office 
(telephone (800) 647-5227) is located on the plaza level of the Nassif 
Building at the DOT street address stated in the ADDRESSES section. 
Comments will be available in the AD docket shortly after the DMS 
receives them.

Discussion

    On March 22, 2001, we issued AD 2001-06-10, amendment 39-12157 (66 
FR 17490, April 2, 2001), for all Airbus Model A300 B4-601, A300 B4-
603, A300 B4-620, A300 B4-605R, A300 B4-622R, and A300 F4-605R 
airplanes. That AD requires repetitive high-frequency eddy-current 
(HFEC) or rototest inspections to detect cracking in the area 
surrounding the frame feet attachment holes between fuselage frame (FR) 
41 and FR46, installation of new fasteners for certain airplanes, and 
follow-on corrective actions if necessary. That AD was prompted by 
issuance of mandatory continuing airworthiness information by the 
airworthiness authority for France. We issued AD 2001-06-10 to prevent 
cracking of the center section of the fuselage, which could result in a 
ruptured frame foot and reduced structural integrity of the airplane.

Related AD

    AD 96-13-11, amendment 39-9679 (61 FR 35122, July 5, 1996), 
requires revising the supplemental structural inspection program for 
all Airbus Model A300 B2 and A300 B4 series airplanes.

Actions Since Existing AD Was Issued

    Since we issued AD 96-13-11 and AD 2001-06-10, the Direction 
G[eacute]n[eacute]rale de l'Aviation Civile (DGAC), which is the 
airworthiness authority for France, advises that the unsafe condition 
identified in AD 2001-06-10 may also exist on all Airbus Model A300 B2 
and A300 B4 series airplanes. In addition, Airbus has developed a new 
modification that will improve the life of the frame feet attachments.

Relevant Service Information

    Airbus has issued Service Bulletins A300-53-0271, Revision 03 (for 
Model A300 B2 and B4 series airplanes), and A300-53-6125, Revision 01 
(for affected Model A300-600 series airplanes), both dated June 13, 
2003. The service bulletins describe procedures for modifying certain 
fuselage frames (FRs). The inspection thresholds range from 6,800 to 
56,200 flight cycles, or 14,100 to 62,400 flight hours. The 
modification involves the following actions:
     Cold expanding fastener holes of the frames on the center 
box upper fuselage bent sections, between FR41 and FR54 for Model A300 
B2 and A300 B4 series airplanes, and between FR41 and FR46 for the 
affected Model A300-600 series airplanes;
     Inspecting for cracks using rotating-probe and eddy-
current methods;
     Repairing certain crack conditions; and
     Flap peening certain frames or reaming certain holes.
    The service bulletins recommend contacting Airbus for repair 
instructions for:
     Holes that exceed certain limits;
     Holes that were previously repaired by installing bushes;
     Cracks found during the rotating probe inspection on Model 
A300 series airplanes; and
     Cracks found during the rotating probe inspection that 
exceed certain limits on the affected Model A300-600 series airplanes.
    For the affected Model A300-600 series airplanes, the modification 
eliminates the need for the repetitive inspections specified in Airbus 
Service Bulletin A300-53-6122 (and required by AD 2001-06-10).
    For Model A300 B2 and A300 B4 series airplanes, the modification 
eliminates the need to repeat the inspection of the frame feet holes 
for frames 41 to 46, as specified in Airbus Service Bulletin A300-53-
0345; and frames 48 to 54, as specified in Airbus Service Bulletin 
A300-53-238. However, Service Bulletin A300-53-0271 recommends that 
operators continue to repeat the inspection of the frame foot angle 
radius (as specified in Service Bulletin A300-53-238). Those 
inspections are required by AD 96-13-11.
    We have determined that accomplishment of the actions specified in 
Service Bulletins A300-53-6125 and

[[Page 42614]]

A300-53-0271 will adequately address the unsafe condition. The DGAC 
mandated the service bulletins and issued French airworthiness 
directives F-2004-001 and F-2004-002, both dated January 7, 2004, to 
ensure the continued airworthiness of these airplanes in France.

FAA's Determination and Requirements of the Proposed AD

    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. We have examined the DGAC's findings, 
evaluated all pertinent information, and determined that AD action is 
necessary for airplanes of this type design that are certificated for 
operation in the United States.
    Therefore, we are proposing this AD, which would supersede AD 2001-
06-10. For Model A300-600 series airplanes, this proposed AD would 
continue to require repetitive high-frequency eddy-current or rototest 
inspections for cracking in the area surrounding the frame feet 
attachment holes between FR41 and FR46, installation of new fasteners 
for certain airplanes, and certain investigative/corrective actions if 
necessary. This proposed AD would require modification of certain 
fuselage frames, which would terminate certain repetitive inspections, 
and add airplanes to the applicability. The proposed AD would require 
using the service information described previously to perform these 
actions, except as discussed under ``Differences Between the Proposed 
AD and the Service Information.''

Difference Between the Proposed AD and the Service Information

    Service Bulletins A300-53-6125 and A300-53-0271 specify that 
operators may contact the manufacturer for certain instructions 
associated with the modification. The service bulletins specify this 
for holes that have been previously repaired in a certain way. However, 
this proposed AD would require operators to contact either the FAA or 
the DGAC (or its delegated agent) for an approved method. In light of 
the type of actions that would be required to address the unsafe 
condition, and consistent with existing bilateral airworthiness 
agreements, we have determined that, for this proposed AD, a 
modification approved by either the FAA or the DGAC would be acceptable 
for compliance with this proposed AD.

Additional Changes to Existing AD

    This proposed AD would retain the requirements of AD 2001-06-10. 
Since AD 2001-06-10 was issued, the AD format has been revised and 
certain paragraphs have been rearranged. As a result, the corresponding 
paragraph identifiers for the retained requirements have changed in 
this proposed AD, as listed in the following table.

                         Reidentified Paragraphs
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                                               New paragraph identifier
    Paragraph identifier in AD 2001-06-10         in this proposed AD
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(a).........................................  (f)
(b).........................................  (g)
(c).........................................  (h)
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Revised Labor Rate

    We have reviewed the figures we have used over the past several 
years to calculate AD costs to operators. To account for various 
inflationary costs in the airline industry, we find it necessary to 
increase the labor rate used in these calculations from $60 per work 
hour to $65 per work hour. The cost impact information, below, reflects 
this increase in the specified hourly labor rate.

Costs of Compliance

    The following table provides the estimated costs for U.S. operators 
to comply with this proposed AD:

                                                                     Estimated Costs
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                                                                                                          Number of
                                                            Labor rate                                      U.S.-
             Action                 Model      Work hours    per hour    Parts cost   Cost per airplane   registered              Fleet cost
                                                                                                          airplanes
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Inspection.....................     A300-600            6          $65           $0  $390, per                   106  $41,340, per inspection.
                                                                                      inspection.
Modification...................         A300           90           65        2,000  7,850.............           24  188,400.
Modification...................     A300-600           56           65        4,000  7,640.............          106  809,840.
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Regulatory Findings

    We have determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD 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.
    For the reasons discussed above, I certify that the 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. 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.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this proposed AD. See the ADDRESSES section for a location 
to examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the Federal Aviation Administration proposes to amend 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. The FAA amends Sec.  39.13 by removing amendment 39-12157 (66 FR

[[Page 42615]]

17490, April 2, 2001) and adding the following new airworthiness 
directive (AD):

Airbus: Docket No. FAA-2004-18593; Directorate Identifier 2004-NM-
21-AD.

Comments Due Date

    (a) The Federal Aviation Administration (FAA) must receive 
comments on this airworthiness directive (AD) action by August 16, 
2004.

Affected ADs

    (b) This AD supersedes AD 2001-06-10, amendment 39-12157. 
Paragraph (i) of this AD terminates certain requirements of AD 96-
13-11, amendment 39-9679.

Applicability

    (c) This AD applies to all Airbus Model A300 B2, A300 B4, A300 
B4-600, and A300 B4-600R series airplanes; and all Airbus Model A300 
C4-605R Variant F and A300 F4-605R airplanes; certificated in any 
category; except those airplanes modified by Airbus Modification 
12168.

Unsafe Condition

    (d) This AD was prompted by the development of a modification 
intended to prevent cracking of the center section of the fuselage, 
which could result in a ruptured frame foot and reduced structural 
integrity of the airplane.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

Restatement of Certain Requirements of AD 2001-06-10

Inspections

    (f) For Model A300 B4-600 and A300 B4-600R series airplanes, and 
Model A300 C4-605R Variant F and A300 F4-605R airplanes: Perform a 
high-frequency eddy-current or rototest inspection to detect 
cracking in the area surrounding the frame feet attachment holes 
between fuselage frames (FR) 41 and FR46 from stringers 24 to 28, 
left- and right-hand sides, in accordance with Airbus Service 
Bulletin A300-53-6122, dated February 9, 2000, at the time specified 
in paragraph (f)(1) or (f)(2), as applicable.
    (1) For airplanes on which Task 53-15-54 in Maintenance Review 
Board Document (MRBD), Revision 3, dated April 1998, has not been 
accomplished as of May 7, 2001 (the effective date of AD 2001-06-
10): Perform the inspection at the later of the times specified in 
paragraphs (f)(1)(i) and (f)(1)(ii) of this AD.
    (i) Prior to the accumulation of the total flight-cycle or 
flight-hour threshold, whichever occurs first, specified in 
paragraph 1.E. (``Compliance'') of the service bulletin; or
    (ii) Within the applicable grace period specified in paragraph 
1.E. (``Compliance'') of the service bulletin.
    (2) For airplanes on which Task 53-15-54 in the MRBD, Revision 
3, dated April 1998, has been accomplished as of May 7, 2001: 
Perform the next repetitive inspection at the later of the times 
specified in paragraphs (f)(2)(i) and (f)(2)(ii) of this AD.
    (i) Within the flight-cycle or flight-hour interval, whichever 
occurs first, specified in paragraph 1.E. (``Compliance'') of the 
service bulletin, following the latest inspection accomplished in 
accordance with the MRBD; or
    (ii) Within the grace period specified in paragraph 1.E. 
(``Compliance'') of the service bulletin.
    (g) For airplanes on which no cracking is detected during the 
inspection required by paragraph (f) of this AD, prior to further 
flight, install new fasteners as applicable, in accordance with 
Airbus Service Bulletin A300-53-6122, dated February 9, 2000; and 
repeat the inspection required by paragraph (f) of this AD 
thereafter at intervals not to exceed the applicable intervals 
specified in paragraph 1.E. (``Compliance'') of the service 
bulletin, until the actions required by paragraph (i) of this AD 
have been done.

Corrective Actions

    (h) For airplanes on which cracking is detected during any 
inspection required by paragraph (f) of this AD: Prior to further 
flight, except as required by paragraph (j) of this AD, accomplish 
corrective actions (e.g., performing rotating probe inspections, 
reaming out cracks, cold working fastener holes, and installing 
oversized fasteners) in accordance with Airbus Service Bulletin 
A300-53-6122, dated February 9, 2000. Repeat the inspection required 
by paragraph (f) of this AD thereafter at intervals not to exceed 
the applicable intervals specified in paragraph 1.E. 
(``Compliance'') of the service bulletin, until the actions required 
by paragraph (i) of this AD have been done.

New Requirements of This AD

Modification: All Airplanes

    (i) For all airplanes: Within the compliance times specified in 
paragraph 1.E. of the applicable service bulletin listed in Table 1 
of this AD, modify the fuselage frames in accordance with the 
Accomplishment Instructions of the applicable service bulletin. For 
airplanes that have exceeded the specified threshold, this AD 
requires compliance within the earlier of the flight-cycle and 
flight-hour grace periods specified in the service bulletin.

                                          Table 1.--Service Information
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                                                                                             Revision level(s)
                                                                                            also acceptable for
          Airplane model               Airbus service  bulletin       Required revision      compliance if done
                                                                            level           before the effective
                                                                                              date of this AD
----------------------------------------------------------------------------------------------------------------
A300 B2 and and A300 B4 series      A300-53-0271..................  Revision 03, dated     Original, dated
 airplanes.                                                          June 13, 2003.         September 10, 1991.
                                                                                           Revision 01, dated
                                                                                            February 16, 1993.
                                                                                           Revision 02, dated
                                                                                            July 13, 2000.
A300 B4-600 and A300 B4-600R        A300-53-6125..................  Revision 01, dated     Original, dated
 series airplanes, and A300 C4-605                                   June 13, 2003.         November 8, 2000.
 Variant F and A300 F4-605R
 airplanes.
----------------------------------------------------------------------------------------------------------------

    (1) For the affected Model A300 B4-600 series airplanes: 
Accomplishment of the modification terminates the requirements of 
this AD.
    (2) For Model A300 B2 and A300 B4 series airplanes: 
Accomplishment of the modification terminates certain repetitive 
inspections required by AD 96-13-11, i.e., inspections of the frame 
feet holes for frames 41 to 46 (as specified in Airbus Service 
Bulletin A300-53-0345) and frames 48 to 54 (as specified in Airbus 
Service Bulletin A300-53-238). However, the repetitive inspections 
of the frame foot angle radius (as specified in Service Bulletin 
A300-53-238), which are required by AD 96-13-11, must continue.

Exceptions to Service Bulletin Procedures

    (j) During any inspection required by this AD, if the applicable 
service bulletin specifies to contact the manufacturer for 
appropriate instructions: Before further flight, perform applicable 
corrective action in accordance with a method approved by the 
Manager, International Branch, ANM-116, Transport Airplane 
Directorate, FAA; or the Direction G[eacute]n[eacute]rale de 
l'Aviation Civile (DGAC) (or its delegated agent).

Alternative Methods of Compliance

    (k)(1) The Manager, International Branch, ANM-116, has the 
authority to approve

[[Page 42616]]

alternative methods of compliance (AMOCs) for this AD, if requested 
in accordance with the procedures found in 14 CFR 39.19.
    (2) AMOCs approved previously in accordance with AD 2001-06-10, 
amendment 39-12157, are approved as AMOCs with the applicable 
requirements of this AD.

Related Information

    (l) French airworthiness directives F-2004-001 and F-2004-02, 
both dated January 7, 2004, also address the subject of this AD.

    Issued in Renton, Washington, on July 6, 2004.
Kevin M. Mullin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.

[FR Doc. 04-16174 Filed 7-15-04; 8:45 am]
BILLING CODE 4910-13-P