[Federal Register Volume 70, Number 157 (Tuesday, August 16, 2005)]
[Proposed Rules]
[Pages 48085-48088]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-16178]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-22110; Directorate Identifier 2004-NM-205-AD]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to supersede an existing airworthiness 
directive (AD) that applies to all Model A300 B4-600 and A300 B4-600R 
series airplanes, and all Model A300 F4-605R airplanes. The existing AD 
currently requires repetitive inspections to detect cracks of certain 
attachment holes, installation of new fasteners, follow-on inspections 
or repair if necessary, and modification of the angle fittings of 
fuselage frame FR47. This proposed AD would revise certain inspection 
thresholds and intervals. This proposed AD would also add inspections 
to detect cracks of additional attachment holes. This proposed AD is 
prompted by reports of cracks found before the inspection thresholds in 
the existing AD and cracks found in nearby areas not inspected by the 
existing AD. We are proposing this AD to prevent fatigue cracking of 
the forward fitting of fuselage frame FR47, which could result in 
reduced structural integrity of the frame.

DATES: We must receive comments on this proposed AD by September 15, 
2005.

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 service information identified in this proposed AD, contact 
Airbus, 1 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 in person 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. This 
docket number is FAA-2005-22110; the directorate identifier for this 
docket is 2004-NM-205-AD.

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

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to submit any relevant written data, views, or 
arguments regarding this proposed AD. Send your comments to an address 
listed under ADDRESSES. Include ``Docket No. FAA-2005-22110; 
Directorate Identifier 2004-NM-205-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 AD. 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 
can visit http://dms.dot.gov.

Examining the Docket

    You can examine the AD docket on the Internet at http://dms.dot.gov, or 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 Docket Management System 
(DMS) receives them.

Discussion

    On May 22, 2002, we issued AD 2002-11-04, amendment 39-12765 (67 FR 
38193, June 3, 2002), for all Model A300 B4-600 and A300 B4-600R series 
airplanes, and all Model A300 F4-605R airplanes. That AD requires 
repetitive inspections to detect cracks of certain attachment holes, 
installation of new fasteners, follow-on inspections or repair if 
necessary, and modification of the angle fittings of fuselage frame 
FR47. That AD was prompted by reports of cracks found in the internal 
angle fittings of the wing center box at fuselage frame FR47 on 
airplanes that

[[Page 48086]]

had not reached the threshold of the fastener hole inspections required 
by AD 97-16-06, amendment 39-10097, and cracks found in additional 
fastener holes that were not required to be inspected by AD 97-16-06. 
We issued that AD to prevent fatigue cracking of the forward fitting of 
fuselage frame FR47, which could result in reduced structural integrity 
of the frame.

Actions Since Existing AD Was Issued

    Since we issued AD 2002-11-04, Direction G[eacute]n[eacute]rale de 
l'Aviation Civile (DGAC), which is the airworthiness authority for 
France, issued French airworthiness directive F-2004-159, dated 
September 29, 2004. That airworthiness directive mandates a new 
repetitive inspection program for fuselage frame FR47 at certain 
fasteners of the center wing box angle fitting. Fatigue cracking on the 
forward fitting of fuselage frame FR47 at the level of the last 
fastener of the external angle fitting, if not detected and corrected 
in a timely manner, could result in reduced structural integrity of the 
airframe.

Relevant Service Information

    Airbus has issued Service Bulletin A300-57-6049, Revision 06, dated 
July 15, 2004. Revision 06 of the service bulletin describes the same 
procedures specified in Airbus Service Bulletin A300-57-6049, Revision 
04, dated July 27, 2000 (Revision 04 was referenced as the appropriate 
source of service information for performing repetitive rotating probe 
inspections to detect cracking of the applicable attachment holes on 
the left and right internal angles of the wing center box; and for 
doing corrective actions; required by AD 2002-11-04). Revision 06 also 
specifies performing an inspection to detect cracking of additional 
holes. In addition, Revision 06 revises certain inspection thresholds 
and intervals. The service bulletin specifies thresholds ranging 
approximately from 10,400 flight cycles or 22,450 flight hours, 
whichever comes first, to 15,350 flight cycles or 23,000 flight hours, 
whichever comes first, depending on the configuration of the airplane. 
The service bulletin also specifies repetitive inspection intervals 
ranging approximately from 4,500 flight cycles or 9,700 flight hours, 
whichever comes first, to 4,850 flight cycles or 7,300 flight hours, 
whichever comes first. The service bulletin specifies a grace period of 
1,400 flight cycles or 3,500 flight hours for airplanes having between 
1,400 flight cycles or 3,500 flight hours below the threshold and 1,900 
flight cycles or 4,600 flight hours above the threshold. The service 
bulletin also specifies a grace period of 700 flight cycles or 1,700 
flight hours for airplanes that have exceeded the threshold by more 
than 1,900 flight cycles or 4,600 flight hours.
    Airbus has also issued Service Bulletin A300-57-6086, Revision 01, 
dated April 2, 2002. Revision 01 of the service bulletin describes the 
same procedures specified in the original issue of Airbus Service 
Bulletin A300-57-6086, dated June 6, 2000 (the original issue was 
referenced as the appropriate source of service information for doing 
repetitive inspections to detect cracking of the applicable attachment 
holes in the horizontal flange of the internal corner angle fitting of 
fuselage frame FR47, and for doing corrective actions, required by AD 
2002-11-04). Revision 01 of the service bulletin also revises a grace 
period for a threshold. Revision 01 of the service bulletin specifies a 
threshold of 13,400 flight cycles or 34,600 flight hours, whichever 
occurs first. The service bulletin also specifies repetitive intervals 
of 6,900 flight cycles or 17,700 flight hours, whichever occurs first. 
The service bulletin specifies a grace period of 1,400 flight cycles or 
3,500 flight hours for airplanes having between 1,400 flight cycles or 
3,500 flight hours below the threshold and 2,000 flight cycles or 5,000 
flight hours above the threshold. The service bulletin specifies a 
grace period of 750 flight cycles or 1,700 flight hours for airplanes 
having exceeded the threshold by more than 2,000 flight cycles or 5,000 
flight hours.
    Airbus has also issued Service Bulletin A300-57-6050, Revision 03, 
dated May 31, 2001. Revision 03 describes the same procedures specified 
in Airbus Service Bulletin A300-57-6050, Revision 02, dated February 
10, 2000 (Revision 02 was referenced as the appropriate source of 
service information for doing the modification of the left and right 
internal angle fittings of the wing center box required by AD 2002-11-
04). Revision 03 of the service bulletin specifies a threshold of 
15,100 flight cycles or 38,900 flight hours.
    Accomplishing the actions specified in the service information is 
intended to adequately address the unsafe condition.
    The DGAC mandated the service information and issued French 
airworthiness directive F-2004-159, dated September 29, 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 
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. 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. This proposed AD would supersede AD 
2002-11-04. This proposed AD would require accomplishing the actions 
specified in the service bulletins described previously, except as 
described in ``Differences Between the Proposed AD, Relevant Service 
Information, and French Airworthiness Directive.''

Differences Between the Proposed AD, Relevant Service Information, and 
French Airworthiness Directive

    As stated previously in AD 2002-11-04, we find that for this 
proposed AD that all touch-and-go landings must be counted in 
determining the total number of landings between two consecutive 
inspections. Airbus Service Bulletin A300-57-6049, Revision 06, dated 
July 15, 2004, and Airbus Service Bulletin A300-57-6086, Revision 01, 
dated April 2, 2002, specify that operators need not count touch-and-go 
landings in determining the total number of landings between two 
consecutive inspections, when those landings are less than five percent 
of the landings between inspection intervals. Since fatigue cracking on 
the forward fitting of fuselage frame FR47 at the level of the last 
fastener of the external angle fitting is aggravated by landing, all 
touch-and-go landings must be counted.
    Although Airbus Service Bulletin A300-57-6049, Revision 06, dated 
July 15, 2004; and Airbus Service Bulletin A300-57-6086, Revision 01, 
dated April 2, 2002; specify to submit certain information to the 
manufacturer, this proposed AD would not require those actions. We do 
not need this information from operators.
    Where any of the service bulletins specify to contact the 
manufacturer for disposition of certain corrective actions, this 
proposed AD would require repair in accordance with a method approved 
by either the Manager, International Branch, ANM-116, FAA, Transport

[[Page 48087]]

Airplane Directorate, or the Direction G[eacute]n[eacute]rale de 
l'Aviation Civile (DGAC) (or its delegated agent). In light of the type 
of repair 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 repair we or the DGAC approve 
would be acceptable for compliance with this proposed AD.
    These differences have been coordinated with the DGAC.

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
                                             Work      Average                                                      U.S.-
                 Action                     hours     labor rate        Parts             Cost per airplane       registered          Fleet cost
                                                       per hour                                                   airplanes
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Inspection Airbus per Service Bulletin           13          $65                 $0  $845......................           74  $62,530, per inspection
 A300-57-6049.                                                                                                                 cycle.
Inspection per Airbus Service Bulletin           30          $65     $6,637-$19,091  $8,587-$21,041, per                  74  $635,438-$1,557,034, per
 A300-57-6086.                                                                        inspection cycle.                        inspection cycle.
Modification per Airbus Service Bulletin     65-365          $65             $3,370  $7,595-$27,095............           74  $562,030-$2,005,030.
 A300-57-6050.
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Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
subtitle VII, part A, subpart III, section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

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 FAA 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 39-12765 (67 FR 
38193, June 3, 2002) and adding the following new airworthiness 
directive (AD):

Airbus: Docket No. FAA-2005-22110; Directorate Identifier 2004-NM-
205-AD.

Comments Due Date

    (a) The Federal Aviation Administration must receive comments on 
this AD action by September 15, 2005.

Affected ADs

    (b) This AD supersedes AD 2002-11-04, amendment 39-12765.

Applicability

    (c) This AD applies to Airbus Model A300 B4-601, B4-603, B4-620, 
and B4-622 airplanes; Model A300 B4-605R and B4-622R airplanes; A300 
F4-605R airplanes; and A300 C4-605R Variant F airplanes; 
certificated in any category; except airplanes on which Airbus 
modification 12171 or 12249 has been accomplished or on which Airbus 
Service Bulletin A300-57-6069 has been accomplished.

Unsafe Condition

    (d) This AD was prompted by reports of cracks found before the 
inspection thresholds in the existing AD and cracks found in nearby 
areas not inspected by the existing AD. We are issuing this AD to 
prevent fatigue cracking of the forward fitting of fuselage frame 
FR47, which could result in reduced structural integrity of the 
frame.

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.

Inspections for Attachment Holes on the Internal Angles of the Wing 
Center Box, and Corrective Action

    (f) Perform a rotating probe inspection to detect cracking of 
the applicable attachment holes on the left and right internal 
angles of the wing center box in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A300-57-6049, Revision 06, 
dated July 15, 2004. Do the inspection at the applicable time 
specified by paragraph 1.E.(2), Accomplishment Timescale, of 
Revision 06 of the service bulletin, except as required by paragraph 
(m) of this AD. Repeat the rotating probe inspection specified in 
this paragraph thereafter at intervals not to exceed the applicable 
interval specified in Revision 06 of the service bulletin, except 
that all touch-and-go landings must be counted in determining the 
total number of flight cycles between consecutive inspections.
    (g) If no cracking is found during any inspection required by 
paragraph (f) of this AD: Prior to further flight, install new 
fasteners in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A300-57-6049, Revision 06, dated July 15, 
2004.

[[Page 48088]]

    (h) If any cracking is found during any inspection required by 
paragraph (f) of this AD: Prior to further flight, perform 
applicable corrective actions (including reaming, drilling, drill-
stopping holes, chamfering, performing follow-on inspections, and 
installing new or oversize fasteners) in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A300-57-6049, 
Revision 06, dated July 15, 2004, except as required by paragraph 
(n) of this AD.

Inspections for Attachment Holes in the Horizontal Flange of the 
Internal Corner Angle Fitting of Fuselage Frame FR47, and Corrective 
Action

    (i) Perform a rotating probe inspection to detect cracking of 
the applicable attachment holes in the horizontal flange of the 
internal corner angle fitting of fuselage frame FR47, in accordance 
with the Accomplishment Instructions of Airbus Service Bulletin 
A300-57-6086, Revision 01, dated April 2, 2002. Do the inspection at 
the applicable time specified in paragraph 1.E., Compliance, of 
Airbus Service Bulletin A300-57-6086, Revision 01, dated April 2, 
2002, except as provided by paragraph (m) of this AD; or within 
1,500 flight cycles after July 8, 2002 (the effective date of AD 
2002-11-04, amendment 39-12765); whichever occurs later. Repeat the 
rotating probe inspection specified in this paragraph thereafter at 
intervals not to exceed the applicable interval specified in Airbus 
Service Bulletin A300-57-6086, dated June 6, 2000, except that all 
touch-and-go landings must be counted in determining the total 
number of flight cycles between consecutive inspections.
    (j) If no cracking is found during any inspection required by 
paragraph (i) of this AD: Prior to further flight, install new 
fasteners in accordance with the service bulletin.
    (k) If any cracking is found during any inspection required by 
paragraph (i) of this AD: Prior to further flight, perform 
applicable corrective actions (including inspecting hole T, reaming 
the holes, and installing oversize fasteners) in accordance with the 
service bulletin, except as required by paragraph (n) of this AD.

Modification of Angle Fittings of the Wing Center Box

    (l) Modify the left and right internal angle fittings of the 
wing center box. The modification includes performing a rotating 
probe inspection to detect cracking, repairing cracks, cold 
expanding holes, and installing medium interference fitting bolts. 
Perform the modification in accordance with Revision 03, dated May 
31, 2001; and at the applicable time specified by paragraph 1.B.(4), 
Accomplishment Timescale, of Airbus Service Bulletin A300-57-6050, 
Revision 03, dated May 31, 2001; except as required by paragraphs 
(m) and (n) of this AD.

Exceptions to Specifications in Service Bulletins

    (m) Where the service bulletins specified in paragraphs (f), 
(i), and (l) of this AD specify a grace period relative to receipt 
of the service bulletin, this AD requires compliance within the 
applicable grace period following the effective date of this AD, if 
the threshold has been exceeded.
    (n) If any crack is detected during any inspection required by 
this AD, and the applicable service bulletin specifies to contact 
the manufacturer for disposition of certain corrective actions: 
Prior to further flight, repair in accordance with a method approved 
by either the Manager, International Branch, ANM-116, FAA, Transport 
Airplane Directorate, or the Direction G[eacute]n[eacute]rale de 
l'Aviation Civile (DGAC) (or its delegated agent).

Actions Accomplished According to Previous Issue of Service Bulletins

    (o) Actions accomplished prior to the effective date of this AD 
in accordance with Airbus Service Bulletin A300-57-6086, dated June 
6, 2000, are acceptable for compliance with the requirements of 
paragraph (i) of this AD.
    (p) Modifications accomplished prior to the effective date of 
this AD in accordance with Airbus Service Bulletin A300-57-6050, 
Revision 02, dated February 10, 2000; are acceptable for compliance 
with the requirements of paragraph (l) of this AD.

No Reporting Requirement

    (q) Although Airbus Service Bulletin A300-57-6049, Revision 06, 
dated July 15, 2004; and Airbus Service Bulletin A300-57-6086, 
Revision 01, dated April 2, 2002; specify to submit certain 
information to the manufacturer, this AD does not include that 
requirement.

Alternative Methods of Compliance (AMOCs)

    (r)(1) The Manager, International Branch, ANM-116, FAA, 
Transport Airplane Directorate, has the authority to approve AMOCs 
for this AD, if requested in accordance with the procedures found in 
14 CFR 39.19.
    (2) AMOCs approved previously according to AD 2002-11-04, 
amendment 39-12765, are not approved as AMOCs with this AD.

Related Information

    (s) French airworthiness directive F-2004-159, dated September 
29, 2004, also addresses the subject of this AD.

    Issued in Renton, Washington, on August 8, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-16178 Filed 8-15-05; 8:45 am]
BILLING CODE 4910-13-P