Document ID: FAA-2008-0657-0001
Agency: faa
Document Type: Rule
Title: Airworthiness Directives; Airbus Model A300, A310, and A300-600 Series Airplanes
Posted Date: 2008-06-17T04:00Z

[Federal Register: June 17, 2008 (Volume 73, Number 117)]
[Proposed Rules]               
[Page 34224-34228]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr17jn08-12]                         

=======================================================================
-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-0657; Directorate Identifier 2007-NM-296-AD]
RIN 2120-AA64

 
Airworthiness Directives; Airbus Model A300, A310, and A300-600 
Series Airplanes

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

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: The FAA proposes to supersede an existing airworthiness 
directive (AD) that applies to certain Airbus Model A300, A310, and 
A300-600 series airplanes. The existing AD currently requires 
repetitive detailed visual inspections to detect cracks in the pylon 
thrust and sideload fitting of the wing, and replacement of any cracked 
pylon thrust and sideload fitting with a new fitting. This proposed AD 
would

[[Page 34225]]

reduce the threshold and repetitive intervals for the detailed 
inspection for certain airplanes and would reduce the applicability of 
the existing AD. This proposed AD results from issuance of mandatory 
continuing airworthiness information by a foreign civil airworthiness 
authority. We are proposing this AD to detect and correct cracks in the 
pylon thrust and sideload fitting of the wing, which could result in 
reduced structural integrity of the airplane.

DATES: We must receive comments on this proposed AD by July 17, 2008.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://
www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    For service information identified in this AD, contact Airbus, 1 
Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://
www.regulations.gov; or in person at the Docket Management Facility 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this proposed AD, the regulatory 
evaluation, any comments received, and other information. The street 
address for the Docket Office (telephone 800-647-5527) is in the 
ADDRESSES section. Comments will be available in the AD docket shortly 
after receipt.

FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
227-1138; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2008-0657; 
Directorate Identifier 2007-NM-296-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD because of those comments.
    We will post all comments we receive, without change, to http://
www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    On July 24, 1998, we issued AD 98-16-11, amendment 39-10687 (63 FR 
40816, July 31, 1998), for certain Airbus Model A300, A310, and A300-
600 series airplanes. That AD requires repetitive detailed visual 
inspections to detect cracks in the pylon thrust and sideload fitting 
of the wing, and replacement of any cracked pylon thrust and sideload 
fitting with a new fitting. That AD resulted from issuance of mandatory 
continuing airworthiness information by a foreign civil airworthiness 
authority. We issued that AD to detect and correct cracks in the pylon 
thrust and sideload fitting of the wing, which could result in reduced 
structural integrity of the airplane.

Actions Since Existing AD Was Issued

    Since we issued AD 98-16-11, Airbus has issued the following 
service bulletins:

                      Table.--New Service Bulletins
------------------------------------------------------------------------
   Airbus service bulletin--                   For model--
------------------------------------------------------------------------
A300-57-0232, Revision 02,       A300 series airplanes.
 dated February 21, 2000.
A300-57-6079, Revision 04,       A300-600 series airplanes.
 dated February 21, 2000.
A310-57-2075, Revision 03,       A310 series airplanes.
 dated December 1, 2006.
------------------------------------------------------------------------

    The repetitive detailed inspections and replacement procedures are 
essentially identical to those specified in previous issues of the 
service bulletins. (AD 98-16-11 refers to Airbus Service Bulletins 
A300-57-0232, Revision 01 (for Model A300 series airplanes); A310-57-
2075, Revision 01 (for Model A310 series airplanes); and A300-57-6079, 
Revision 02 (for Model A300-600 series airplanes); all dated January 
12, 1998; as the appropriate sources of service information for 
accomplishing the required actions.) Revision 03 of Airbus Service 
Bulletin A310-57-2075 reduces the detailed inspection thresholds and 
repeat intervals for certain airplanes. In addition, the effectivity 
listing of all three service bulletins has been revised to remove 
airplanes that have been scrapped. No more work is necessary for 
airplanes on which previous issues of the service bulletins were done.
    Accomplishing the actions specified in the service information is 
intended to adequately address the unsafe condition. The European 
Aviation Safety Agency (EASA), which is the Technical Agent for the 
Member States of the European Community, mandated the service 
information and issued EASA airworthiness directive 2007-0243, dated 
September 4, 2007, to ensure the continued airworthiness of these 
airplanes in the European Union.

FAA's Determination and Requirements of the Proposed AD

    These airplanes 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. As described in FAA 
Order 8100.14A, ``Interim Procedures for Working with the European 
Community on Airworthiness Certification and Continued Airworthiness,'' 
dated August 12, 2005, the EASA has kept the FAA informed of the 
situation described above. We have examined the EASA'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 98-16-11 and would continue to 
require, at reduced thresholds and repetitive intervals for certain 
airplanes, repetitive detailed visual inspections to detect cracks in 
the pylon thrust and

[[Page 34226]]

sideload fitting of the wing, and would continue to require replacement 
of any cracked pylon thrust and sideload fitting with a new fitting. 
This proposed AD would also require accomplishing the actions specified 
in service information described previously.

Differences Between Proposed Rule and EASA AD

    The proposed AD would differ from the parallel EASA airworthiness 
directive in that it would not allow for adjustment in compliance time 
based on airplane utilization. In developing an appropriate compliance 
time for this proposed AD, the FAA considered not only the 
manufacturer's recommendation, but the degree of urgency associated 
with addressing the subject unsafe condition, and the average 
utilization of the affected fleet. In light of these factors, we find 
the compliance times specified in paragraphs (f)(1) and (f)(2) of this 
proposed AD to be warranted, in that they represent an appropriate 
interval of time allowable for affected airplanes to continue to 
operate without compromising safety.

Change to Existing AD

    This proposed AD would retain all requirements of AD 98-16-11. 
Since AD 98-16-11 was issued, the AD format has been revised, and 
certain paragraphs have been rearranged. As a result, the corresponding 
paragraph identifiers have changed in this proposed AD, as listed in 
the following table:

                      Revised Paragraph Identifiers
------------------------------------------------------------------------
                                             Corresponding  requirement
        Requirement in AD 98-16-11              in this  proposed AD
------------------------------------------------------------------------
paragraph (a).............................  paragraph (f).
paragraph (b).............................  paragraph (g).
------------------------------------------------------------------------

    In addition, we have revised the applicability of this proposed AD 
to refer to the latest revisions of the service information described 
previously.
    We also changed all references to a ``detailed visual inspection'' 
in the existing AD to ``detailed inspection'' in this action.

Costs of Compliance

    This proposed AD would affect about 164 Model A300, A310, and A300-
600 series airplanes of U.S. registry.
    The inspections that are required by AD 98-16-11 and retained in 
this proposed AD take about 3 work hours per airplane, at an average 
labor rate of $80 per work hour. Based on these figures, the estimated 
cost of the currently required actions is $39,360, or $240 per 
airplane, per inspection cycle.

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 and placed it in the AD docket. 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 Federal Aviation Administration (FAA) amends Sec.  39.13 by 
removing amendment 39-10687 (63 FR 40816, July 31, 1998) and adding the 
following new airworthiness directive (AD):

Airbus: Docket No. FAA-2008-0657; Directorate Identifier 2007-NM-
296-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by July 17, 
2008.

Affected ADs

    (b) This AD supersedes AD 98-16-11.

Applicability

    (c) This AD applies to Airbus airplanes identified in Table 1 of 
this AD, certificated in any category.

                         Table 1.--Applicability
------------------------------------------------------------------------
                                        As identified in Airbus service
               Model--                             bulletin--
------------------------------------------------------------------------
(1) A300 series airplanes............  A300-57-0232, Revision 02, dated
                                        February 21, 2000.
(2) A310 series airplanes............  A310-57-2075, Revision 03, dated
                                        December 1, 2006.
(3) A300-600 series airplanes........  A300-57-6079, Revision 04, dated
                                        February 21, 2000.
------------------------------------------------------------------------

Unsafe Condition

    (d) This AD results from issuance of mandatory continuing 
airworthiness information by a foreign civil airworthiness 
authority. We are issuing this AD to detect and correct cracks in 
the pylon thrust and sideload fitting of the wing, which could 
result in reduced structural integrity of the airplane.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within

[[Page 34227]]

the compliance times specified, unless the actions have already been 
done.

Requirements of AD 98-16-11:

Repetitive Detailed Inspections at Reduced Thresholds and Repeat 
Intervals for Certain Airplanes

    (f) At the applicable time specified in paragraph (f)(1) or 
(f)(2) of this AD: Perform a detailed inspection to detect cracks in 
the pylon thrust and sideload fitting of the wing, in accordance 
with Airbus Service Bulletin A300-57-0232, Revision 01 (for Model 
A300 series airplanes); A310-57-2075, Revision 01 (for Model A310 
series airplanes); or A300-57-6079, Revision 02 (for Model A300-600 
series airplanes); all dated January 12, 1998; as applicable; except 
as provided by paragraph (h) of this AD.
    (1) For Model A300 and A300-600 series airplanes: Inspect prior 
to the accumulation of 2,800 total flight cycles, or within 18 
months after September 4, 1998 (the effective date AD 98-16-11), 
whichever occurs later, and thereafter at intervals not to exceed 
2,800 flight cycles.
    (2) For Model A310 series airplanes: Inspect at the earlier of 
the times specified in paragraph (f)(2)(i) and (f)(2)(ii) of this 
AD. Repeat thereafter at the applicable intervals specified in Table 
3 of this AD.
    (i) Prior to the accumulation of 2,800 total flight cycles, or 
within 18 months after September 4, 1998, whichever occurs later.
    (ii) At the applicable time specified in Table 2 of this AD.

 Table 2.--Reduced Inspection Thresholds for Model A310 Series Airplanes
------------------------------------------------------------------------
                               Compliance time (whichever occurs later)
            Model            -------------------------------------------
                                    Threshold           Grace period
------------------------------------------------------------------------
A310-200 series airplanes...  Before the            Within 800 flight
                               accumulation of       cycles or 1,600
                               1,500 total flight    flight hours after
                               cycles or 3,000       the effective date
                               total flight hours    of this AD,
                               since first flight,   whichever occurs
                               whichever occurs      first.
                               first.
A310-300 series airplanes     Before the            Within 800 flight
 (short range).                accumulation of       cycles or 1,600
                               1,300 total flight    flight hours after
                               cycles or 3,800       the effective date
                               total flight hours    of this AD,
                               since first flight,   whichever occurs
                               whichever occurs      first.
                               first.
A310-300 series airplanes     Before the            Within 800 flight
 (long range).                 accumulation of 800   cycles or 1,600
                               total flight cycles   flight hours after
                               or 4,000 total        the effective date
                               flight hours since    of this AD,
                               first flight,         whichever occurs
                               whichever occurs      first.
                               first.
------------------------------------------------------------------------

   Table 3.--Reduced Repeat Intervals for Model A310 Series Airplanes
------------------------------------------------------------------------
                                  Repeat the detailed    And, thereafter
          For Model--              inspection at the    at intervals not
                                      later of--           to exceed--
------------------------------------------------------------------------
A310-200 series airplanes.....  Within 1,500 flight     1,500 flight
                                 cycles or 3,000         cycles or 3,000
                                 flight hours since      flight hours,
                                 the last detailed       whichever
                                 inspection, whichever   occurs first.
                                 occurs first; or
                                 within 800 flight
                                 cycles or 1,600
                                 flight hours after
                                 the effective date of
                                 this AD, whichever
                                 occurs first.
A310-300 series airplanes       Within 1,300 flight     1,300 flight
 (short range).                  cycles or 3,800         cycles or 3,800
                                 flight hours since      flight hours,
                                 the last detailed       whichever
                                 inspection, whichever   occurs first.
                                 occurs first; or
                                 within 800 flight
                                 cycles or 1,600
                                 flight hours after
                                 the effective date of
                                 this AD, whichever
                                 occurs first.
A310-300 series airplanes       Within 800 flight       800 flight
 (long range).                   cycles or 4,000         cycles or 4,000
                                 flight hours since      flight hours,
                                 the last detailed       whichever
                                 inspection, whichever   occurs first.
                                 occurs first; or
                                 within 800 flight
                                 cycles or 1,600
                                 flight hours after
                                 the effective date of
                                 this AD, whichever
                                 occurs first.
------------------------------------------------------------------------

Corrective Action

    (g) If any crack is detected during any inspection required by 
paragraph (f) of this AD, prior to further flight, replace the pylon 
thrust and sideload fitting with a new fitting in accordance with 
Airbus Service Bulletin A300-57-0232, Revision 01 (for Model A300 
series airplanes); A310-57-2075, Revision 01 (for Model A310 series 
airplanes); or A300-57-6079, Revision 02 (for Model A300-600 series 
airplanes); all dated January 12, 1998; as applicable; except as 
provided by paragraph (h) of this AD.

New Actions Required by This AD:

New Service Information

    (h) For all airplanes: As of the effective date of this AD, use 
only the Accomplishment Instructions of the applicable service 
bulletin specified in Table 4 of this AD to do the repetitive 
detailed inspections required by paragraph (f) of this AD and the 
replacement required by paragraph (g) of this AD.

                     Table 4.--New Service Bulletins
------------------------------------------------------------------------
  Airbus service bulletin--                   For model--
------------------------------------------------------------------------
(1) A300-57-0232, Revision     A300 series airplanes.
 02, dated February 21, 2000.
(2) A300-57-6079, Revision     A300-600 series airplanes.
 04, dated February 21, 2000.
(3) A310-57-2075, Revision     A310 series airplanes.
 03, dated December 1, 2006.
------------------------------------------------------------------------

    (i) Actions done before the effective date of this AD in 
accordance with Airbus Service Bulletins A300-57-6079, Revision 02, 
dated January 12, 1998, or Revision 03, dated October 25, 1999 (for 
Model A300-600 series airplanes); A310-57-2075, Revision 01, dated 
January 12, 1998, or Revision 02, dated February 21, 2000 (for Model 
A310 series airplanes); or A300-57-0232, Revision 01, dated January 
12, 1998 (for Model A300 series airplanes); are acceptable for 
compliance with the corresponding requirements of this AD.

[[Page 34228]]

Alternative Methods of Compliance (AMOCs)

    (j) The Manager, International Branch, ANM-116, FAA, has the 
authority to approve AMOCs for this AD, if requested using the 
procedures found in 14 CFR 39.19. Send information to ATTN: Vladimir 
Ulyanov, Aerospace Engineer, International Branch, ANM-116, 
Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, 
Washington 98057-3356; telephone (425) 227-1138; fax (425) 227-1149. 
Before using any approved AMOC on any airplane to which the AMOC 
applies, notify your appropriate principal inspector (PI) in the FAA 
Flight Standards District Office (FSDO), or lacking a PI, your local 
FSDO.

Related Information

    (k) European Aviation Safety Agency (EASA) airworthiness 
directive 2007-0243, dated September 4, 2007, also addresses the 
subject of this AD.

    Issued in Renton, Washington, on June 10, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E8-13566 Filed 6-16-08; 8:45 am]

BILLING CODE 4910-13-P