Document ID: FAA-2008-0657-0006
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Airbus Model A300, A310, and A300-600 Series Airplanes
Posted Date: 2009-02-20T05:00Z

[Federal Register: February 20, 2009 (Volume 74, Number 33)]
[Rules and Regulations]               
[Page 7804-7808]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr20fe09-13]                         

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-0657; Directorate Identifier 2007-NM-296-AD; 
Amendment 39-15787; AD 2009-01-08]
RIN 2120-AA64

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

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

ACTION: Final rule.

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

SUMMARY: The FAA is superseding an existing airworthiness directive 
(AD), which applies to certain Airbus Model A300, A310, and A300-600 
series airplanes. That 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 new AD reduces the threshold and 
repetitive intervals for the detailed inspection for certain airplanes 
and reduces the applicability of the existing AD. 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.

DATES: This AD becomes effective March 27, 2009.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the AD as of March 27, 
2009.

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 AD, the regulatory evaluation, 
any comments received, and other information. The address for the 
Docket Office (telephone 800-647-5527) is the Document Management 
Facility, U.S. Department of Transportation, Docket Operations, M-30, 
West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE., 
Washington, DC 20590.

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:

Discussion

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to include an AD that supersedes AD 98-16-11, amendment 39-
10687 (63 FR 40816, July 31, 1998). The existing AD applies to certain 
Airbus Model A300, A310, and A300-600 series airplanes. That NPRM was 
published in the Federal Register on June 17, 2008 (73 FR 34224). That 
NPRM proposed to continue to require 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 NPRM also proposed to require reducing 
the threshold and repetitive intervals for the detailed inspection for 
certain airplanes and would reduce the applicability of the existing 
AD.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We considered the comments received from the three commenters.

[[Page 7805]]

Request for Definition Paragraph

    An anonymous commenter requests that we revise the NPRM to add a 
``definitions'' paragraph since Table 2 and Table 3 of the NPRM refer 
to both the long range and short range Model A310-300 series airplanes. 
The commenter suggests defining the average flight times.
    We do not agree. The Office of the Federal Register has approved 
the incorporation by reference of Airbus Mandatory Service Bulletin 
A310-57-2075, Revision 03, dated December 1, 2006. Therefore, we have 
determined that it is not necessary to incorporate a definitions 
paragraph since paragraph 1.E. of this service bulletin includes an 
explanation of short-range and long-range airplanes, and their average 
flight times. We have not changed the final rule regarding this issue.

Request To Mandate the Inspection Section of the Service Bulletins

    Air Transport Association, on behalf of American Airlines (AA), 
requests that, since the safety issue is detecting cracks in the 
fitting, the AD should mandate only the ``inspection section'' of 
Airbus Mandatory Service Bulletin A300-57-0232, Revision 02, dated 
February 21, 2000; Airbus Mandatory Service Bulletin A300-57-6079, 
Revision 04, dated February 21, 2000; and Airbus Mandatory Service 
Bulletin A310-57-2075, Revision 03, dated December 1, 2006; instead of 
the entire accomplishment instructions of these service bulletins. AA 
believes that mandating the ``inspection section'' would still correct 
the unsafe condition and allow operators to modify other steps as 
required, while maintaining a safe work environment.
    We disagree. We are mandating the entire Accomplishment 
Instructions of these service bulletins because they include the 
inspection, repair, and other necessary instructions to correct the 
unsafe condition. Affected operators may request approval for an 
alternative method of compliance, under the provisions of paragraph (k) 
of the AD. We have not changed the final rule regarding this issue.

Request To Retain Inspection Requirements, Provide Terminating Action, 
and Provide Approval Authority

    FedEx Express requests that we include the following requirements 
in the NPRM: Keep the current inspection method and interval if the 
airplane has not reached the design service goal (the economic impact 
will increase due to additional inspections); terminate the inspections 
if the pylon sideload fitting is replaced with a fitting made using 
improved manufacturing techniques; and provide an alternative means of 
compliance repair approval authority to the European Aviation Safety 
Agency (EASA) or its delegated agent.
    We disagree with keeping the current inspection method and interval 
for airplanes that have not reached the design service goal because we 
have determined that the new intervals are necessary to address the 
unsafe condition. We have not changed the final rule regarding this 
issue.
    We disagree with terminating the inspections if the pylon sideload 
fitting is replaced with a fitting made using improved manufacturing 
techniques. At this time we have not received sufficient information 
from the manufacturer or EASA to determine if the manufacturing 
techniques are adequate and the inspections can be terminated. We have 
not changed the final rule regarding this issue.
    We agree with FedEx Express that, as a method of compliance with 
paragraph (g) of this AD, repair approval authority can be given to 
EASA or its delegated agent. Affected operators may request an optional 
approval method, under the provisions of paragraph (j) of the AD. We 
have changed the final rule regarding this issue.

Conclusion

    We have carefully reviewed the available data, including the 
comments that have been received, and determined that air safety and 
the public interest require adopting the AD with the change described 
previously. We have determined that this change will neither increase 
the economic burden on any operator nor increase the scope of the AD.

Costs of Compliance

    This AD affects 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 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 AD will not have federalism 
implications under Executive Order 13132. This AD will 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 this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866;
    (2) Is not a ``significant rule'' under 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 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, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
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]

0
2. The Federal Aviation Administration (FAA) amends Sec.  39.13 by 
removing amendment 39-10687 (63 FR 40816, July 31, 1998) and by adding

[[Page 7806]]

the following new airworthiness directive (AD):

2009-01-08 Airbus: Amendment 39-15787. Docket No. FAA-2008-0657; 
Directorate Identifier 2007-NM-296-AD.

Effective Date

    (a) This AD becomes effective March 27, 2009.

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
                Model--                    Mandatory Service 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 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 at
         For Model--            inspection at the     intervals not to
                                   later of--             exceed--
------------------------------------------------------------------------
A310-200 series airplanes.    Within 1,500 flight   1,500 flight cycles
                               cycles or 3,000       or 3,000 flight
                               flight hours since    hours, whichever
                               the last detailed     occurs first.
                               inspection,
                               whichever 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 cycles
 (short range).                cycles or 3,800       or 3,800 flight
                               flight hours since    hours, whichever
                               the last detailed     occurs first.
                               inspection,
                               whichever 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 cycles or
 (long range).                 cycles or 4,000       4,000 flight hours,
                               flight hours since    whichever occurs
                               the last detailed     first.
                               inspection,
                               whichever 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 paragraphs (h) and (j) of this AD.

[[Page 7807]]

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 mandatory Service Bulletin--              For model--
------------------------------------------------------------------------
(1) A300-57-0232, Revision 02, dated      A300 series airplanes.
 February 21, 2000.
(2) A300-57-6079, Revision 04, dated      A300-600 series airplanes.
 February 21, 2000.
(3) A310-57-2075, Revision 03, dated      A310 series airplanes.
 December 1, 2006.
------------------------------------------------------------------------

    (i) Actions done before the effective date of this AD in 
accordance with Airbus Service Bulletin 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.

Optional Approval Method

    (j) Repairing the pylon thrust and sideload fitting of the wing, 
using a method approved by either the Manager, International Branch, 
ANM-116, Transport Airplane Directorate, FAA; or the European 
Aviation Safety Agency (EASA), or its delegated agent, is acceptable 
for compliance with the replacement required by paragraph (g) of 
this AD.

Alternative Methods of Compliance (AMOCs)

    (k) 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

    (l) EASA airworthiness directive 2007-0243, dated September 4, 
2007, also addresses the subject of this AD.

Material Incorporated by Reference

    (m) You must use service bulletins identified in Table 5 of this 
AD to do the actions required by this AD, as applicable, unless the 
AD specifies otherwise.

                                 Table 5--All Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
          Airbus service information              Revision                            Date
----------------------------------------------------------------------------------------------------------------
Airbus Mandatory Service Bulletin A300-57-                 02  February 21, 2000.
 0232.
Airbus Mandatory Service Bulletin A300-57-                 04  February 21, 2000.
 6079.
Airbus Mandatory Service Bulletin A310-57-                 03  December 1, 2006.
 2075.
Airbus Service Bulletin A300-57-0232.........              01  January 12, 1998.
Airbus Service Bulletin A300-57-6079.........              02  January 12, 1998.
Airbus Service Bulletin A310-57-2075.........              01  January 12, 1998.
----------------------------------------------------------------------------------------------------------------

    (1) The Director of the Federal Register approved the 
incorporation by reference of the service bulletins identified in 
Table 6 of this AD in accordance with 5 U.S.C. 552(a) and 1 CFR part 
51.

                                 Table 6--New Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
     Airbus mandatory Service Bulletin--         Revision--                         Dated--
----------------------------------------------------------------------------------------------------------------
A300-57-0232.................................              02  February 21, 2000.
A300-57-6079.................................              04  February 21, 2000.
A310-57-2075.................................              03  December 1, 2006.
----------------------------------------------------------------------------------------------------------------

    (2) On September 4, 1998 (63 FR 40816, July 31, 1998) the 
Director of the Federal Register approved the incorporation by 
reference of the service bulletins identified in Table 7 of this AD.

                             Table 7--Material Previously Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
          Airbus Service Bulletin--              Revision--                         Dated--
----------------------------------------------------------------------------------------------------------------
A300-57-0232.................................              01  January 12, 1998.
A310-57-2075.................................              01  January 12, 1998.
A300-57-6079.................................              02  January 12, 1998.
----------------------------------------------------------------------------------------------------------------

    (3) For service information identified in this AD, contact 
Airbus SAS--EAW (Airworthiness Office), 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; 
fax +33 5 61 93 44 51; e-mail: account.airworth-

[[Page 7808]]

eas@airbus.com; Internet http://www.airbus.com.
    (4) You may review copies of the service information that is 
incorporated by reference at the FAA, Transport Airplane 
Directorate, 1601 Lind Avenue, SW., Renton, Washington. For 
information on the availability of this material at the FAA, call 
425-227-1221 or 425-227-1152.
    (5) You may also review copies of the service information at the 
National Archives and Records Administration (NARA). For information 
on the availability of this material at NARA, call 202-741-6030, or 
go to: http://www.archives.gov/federal_register/code_of_federal_
regulations/ibr_locations.html.

    Issued in Renton, Washington, on December 18, 2008.
Stephen P. Boyd,
Assistant Manager, Transport Airplane Directorate, Aircraft 
Certification Service.
[FR Doc. E9-3276 Filed 2-19-09; 8:45 am]

BILLING CODE 4910-13-P