Document ID: FAA-2008-0908-0005
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Airbus Model A310 Series Airplanes
Posted Date: 2009-02-26T05:00Z

[Federal Register: February 26, 2009 (Volume 74, Number 37)]
[Rules and Regulations]               
[Page 8728-8732]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr26fe09-11]                         

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-0908; Directorate Identifier 2007-NM-190-AD; 
Amendment 39-15788; AD 2009-01-09]
RIN 2120-AA64

 
Airworthiness Directives; Airbus Model A310 Series Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: The FAA is superseding an existing airworthiness directive 
(AD) that applies to all Airbus Model A310 series airplanes. That AD 
currently requires repetitive detailed inspections to detect cracks 
propagating from the fastener holes that attach the left- and right-
hand pick-up angles at frame 40 to the wing lower skin and fuselage 
panel, and corrective actions if necessary. This new AD revises the 
intervals for accomplishing the repetitive detailed inspections and 
provides for an optional terminating modification for the repetitive 
inspections. This new AD also revises the applicability of the AD to 
remove certain airplanes. This AD results from mandatory continuing 
airworthiness information originated by an aviation authority of 
another country to identify and correct an unsafe condition on an 
aviation product. We are issuing this AD to prevent reduced structural 
integrity of the airplane due to fatigue damage, and consequent 
cracking of the pick-up angles at frame 40.

DATES: This AD is effective April 2, 2009.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of April 2, 
2009.
    The Director of the Federal Register approved the incorporation by 
reference of a certain other publication listed in this AD as of 
February 9, 2001 (66 FR 1031, January 5, 2001).

ADDRESSES: 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-eas@airbus.com; Internet http://
www.airbus.com.

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: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116,

[[Page 8729]]

Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, 
Washington 98057-3356; telephone (425) 227-2125; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to include an airworthiness directive (AD) that supersedes AD 
2000-26-14, amendment 39-12064 (66 FR 1031, January 5, 2001). The 
existing AD applies to all Airbus Model A310 series airplanes. That 
NPRM was published in the Federal Register on August 26, 2008 (73 FR 
50250). A correction to that NPRM was published in the Federal Register 
on September 8, 2008 (73 FR 51961). That NPRM proposed to continue to 
require repetitive detailed inspections to detect cracks propagating 
from the fastener holes that attach the left- and right-hand pick-up 
angles at frame 40 to the wing lower skin and fuselage panel, and 
corrective actions if necessary. That NPRM also proposed to revise the 
intervals for accomplishing the repetitive detailed inspections and 
provided for an optional terminating modification for the repetitive 
inspections. That NPRM also proposed to revise the applicability of the 
AD to remove certain airplanes.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM or on the determination of 
the cost to the public.

Conclusion

    We reviewed the relevant data and determined that air safety and 
the public interest require adopting the AD as proposed.

Costs of Compliance

    This AD affects about 68 Model A310 series airplanes of U.S. 
registry.
    The inspections that are required by AD 2000-26-14 and retained in 
this AD take about 2 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 $10,880, or $160 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

    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.
    You can find our regulatory evaluation and the estimated costs of 
compliance in the AD Docket.

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 FAA amends Sec.  39.13 by removing amendment 39-12064 (66 FR 
1031, January 5, 2001) and by adding the following new AD:

2009-01-09 Airbus: Amendment 39-15788. Docket No. FAA-2008-0908; 
Directorate Identifier 2007-NM-190-AD.

Effective Date

    (a) This airworthiness directive (AD) is effective April 2, 
2009.

Affected ADs

    (b) This AD supersedes AD 2000-26-14.

Applicability

    (c) This AD applies to Airbus Model A310 series airplanes, 
certificated in any category, except those airplanes modified in-
service in accordance with Airbus Service Bulletin A310-53-2119, 
dated October 25, 2005; or Revision 01, dated February 27, 2007.

Unsafe Condition

    (d) This AD results from mandatory continuing airworthiness 
information originated by an aviation authority of another country 
to identify and correct an unsafe condition on an aviation product. 
We are issuing this AD to prevent reduced structural integrity of 
the airplane due to fatigue damage and consequent cracking of the 
pick-up angles at frame 40.

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 2000-26-14

Inspections and Corrective Actions

    (f) Perform a detailed inspection to detect cracks propagating 
from the fastener holes that attach the left- and right-hand pick-up 
angles at frame 40 to the wing lower skin and fuselage panel, at the 
time specified in paragraph (g), (h), (i), (j), or (k) of this AD, 
as applicable. Perform the actions in accordance with Figure 2, 
Sheet 1, ``Synoptic Chart,'' of Airbus Service Bulletin A310-
53A2111, Revision 01, dated June 21, 2000, except as provided by 
paragraph (l) of this AD.
    (1) If no cracking is found during the inspection required by 
paragraph (f) of this AD, repeat the detailed inspection thereafter 
at the interval specified in paragraph (f)(1)(i) or (f)(1)(ii) of 
this AD, as applicable, except as provided by paragraph (n) of this 
AD.
    (i) For Model A310-200 series airplanes: Except as provided by 
paragraph (i) of this AD, repeat the inspection thereafter at 
intervals not to exceed 1,000 flight cycles or 2,600 flight hours, 
whichever occurs first.
    (ii) For Model A310-300 series airplanes: Except as provided by 
paragraphs (i) of this AD, repeat the inspection thereafter at 
intervals not to exceed 850 flight cycles or 2,800 flight hours, 
whichever occurs first.
    (2) If any cracking is found during the inspection required by 
paragraph (f) of this AD, prior to further flight, perform 
applicable corrective actions (including repair (drilling and 
reaming a crack stop hole in the pick-up angle, performing a 
Rototest inspection and repetitive detailed inspections at the time 
specified in the service bulletin, and replacing the pick-up angle 
with a new angle at the time specified in the service bulletin,

[[Page 8730]]

except as provided by paragraph (o) of this AD); or immediate 
replacement of any cracked angle with a new angle). Perform the 
actions and repetitive inspections in accordance with Figure 2, 
Sheet 1, ``Synoptic Chart,'' of Airbus Service Bulletin A310-
53A2111, Revision 01, dated June 21, 2000, except as provided by 
paragraph (l) of this AD.

    Note 1: Accomplishment of the actions required by paragraph (f) 
of this AD in accordance with Airbus Service Bulletin A310-53A2111, 
dated April 21, 2000, is considered to be acceptable for compliance 
with the requirements of that paragraph.

Compliance Times

    (g) For Model A310-200 series airplanes: Except as provided by 
paragraphs (i), (j), and (k) of this AD, perform the initial 
inspection at the later of the times specified in paragraphs (g)(1) 
and (g)(2) of this AD.
    (1) Prior to the accumulation of 7,900 total flight cycles or 
23,600 total flight hours, whichever occurs first.
    (2) Within 700 flight cycles or 1,200 flight hours after 
February 9, 2001 (the effective date of AD 2000-26-14), whichever 
occurs first.
    (h) For Model A310-300 series airplanes: Except as provided by 
paragraphs (i), (j), and (k) of this AD, perform the initial 
inspection required by paragraph (f) of this AD at the later of the 
times specified in paragraphs (h)(1) and (h)(2) of this AD.
    (1) Prior to the accumulation of 6,700 total flight cycles or 
24,700 total flight hours, whichever occurs first.
    (2) Within 700 flight cycles or 1,200 flight hours after 
February 9, 2001, whichever occurs first.
    (i) For airplanes that have accumulated more than 18,000 total 
flight cycles or 53,000 total flight hours as of February 9, 2001: 
Perform the initial inspection required by paragraph (f) of this AD 
within 350 flight cycles or 600 flight hours after February 9, 2001, 
whichever occurs first. Repeat the inspection thereafter at 
intervals not to exceed 350 flight cycles or 600 flight hours, 
whichever occurs first.
    (j) For airplanes having manufacturer's serial number 0162 
through 0326 inclusive, on which Airbus Service Bulletin A310-53-
2014 has been accomplished prior to February 9, 2001: The initial 
inspection threshold may be counted from the date of accomplishment 
of Airbus Service Bulletin A310-53-2014.
    (k) For airplanes on which a pick-up angle has been replaced: 
For that pick-up angle only, the initial inspection threshold may be 
counted from the date of installation of the new pick-up angle.

    Note 2: For the purposes of this AD, a detailed inspection is 
defined as: ``An intensive visual examination of a specific 
structural area, system, installation, or assembly to detect damage, 
failure, or irregularity. Available lighting is normally 
supplemented with a direct source of good lighting at intensity 
deemed appropriate by the inspector. Inspection aids such as mirror, 
magnifying lenses, etc., may be used. Surface cleaning and elaborate 
access procedures may be required.''

New Requirements of This AD

New Revisions of Service Bulletin

    (l) As of the effective date of this AD, use only the 
Accomplishment Instructions of Airbus Mandatory Service Bulletin 
A310-53-2111, Revision 03, dated May 21, 2007, to do the inspections 
and corrective actions required by paragraph (f) of this AD; except 
where Figure 2 Sheet 2 of Airbus Mandatory Service Bulletin A310-53-
2111, Revision 03, dated May 21, 2007, specifies actions for crack 
length of ``<54 mm (2.126 in.)'' and ``<69 mm (2.716 in.),'' this AD 
requires the corresponding actions for crack lengths less than or 
equal to those measurements.
    (m) Inspections and applicable corrective actions done before 
the effective date of this AD in accordance with Airbus Mandatory 
Service Bulletin A310-53-2111, Revision 02, dated October 25, 2005, 
are acceptable for compliance with the requirements of paragraph (f) 
of this AD.

Revised Repetitive Intervals for Detailed Inspections

    (n) As of the effective date of this AD, repeat the detailed 
inspections for no crack findings required by paragraph (f)(1)(i), 
(f)(1)(ii), or (i) of this AD, as applicable, at the applicable 
times specified in Table 1 of this AD, until the modification 
specified in paragraph (p) of this AD is done.

                     Table 1--Revised Repetitive Intervals for Certain Detailed Inspections
----------------------------------------------------------------------------------------------------------------

----------------------------------------------------------------------------------------------------------------
For model--                            Repeat the inspection at the later of the         And thereafter at
                                        following times--                                 intervals not to
                                                                                          exceed--
----------------------------------------------------------------------------------------------------------------
(1) A310-200 series airplanes........  Within 950 flight        Within 50 flight cycles  950 flight cycles or
                                        cycles or 1,900 flight   or 250 flight hours      1,900 flight hours,
                                        hours since the last     after the effective      whichever occurs
                                        inspection required by   date of this AD,         first.
                                        paragraph (f)(1)(i) or   whichever occurs first.
                                        (i) of this AD,
                                        whichever occurs first.
----------------------------------------------------------------------------------------------------------------
(2) A310-300 series airplanes (short   Within 900 flight        Within 50 flight cycles  900 flight cycles or
 range).                                cycles or 2,550 flight   or 250 flight hours      2,550 flight hours,
                                        hours since the last     after the effective      whichever occurs
                                        inspection required by   date of this AD,         first.
                                        paragraph (f)(1)(ii)     whichever occurs first.
                                        or (i) of this AD,
                                        whichever occurs first.
----------------------------------------------------------------------------------------------------------------
(3) A310-300 series airplanes (long    Within 800 flight        Within 50 flight cycles  800 flight cycles or
 range).                                cycles or 4,000 flight   or 250 flight hours      4,000 flight hours,
                                        hours since the last     after the effective      whichever occurs
                                        inspection required by   date of this AD,         first.
                                        paragraph (f)(1)(ii)     whichever occurs first.
                                        or (i) of this AD,
                                        whichever occurs first.
----------------------------------------------------------------------------------------------------------------

Revised Threshold for Replacing the Pick-Up Angles

    (o) As of the effective date of this AD, do the replacement of 
the pick-up angle required by paragraph (f)(2) of this AD, at the 
applicable time specified in Table 2 of this AD.

[[Page 8731]]

        Table 2--Revised Thresholds for Replacing Pick-Up Angles
------------------------------------------------------------------------

------------------------------------------------------------------------
For model--                       Replace at the earlier of the
                                   following times--
------------------------------------------------------------------------
(1) A310-200 series airplanes...  At the time         Within 1,500
                                   specified in        flight cycles or
                                   paragraph (f)(2)    3,000 flight
                                   of this AD for      hours since the
                                   replacing the       last detailed
                                   pick-up angle.      inspection, or
                                                       within 30 days
                                                       after the
                                                       effective date of
                                                       this AD,
                                                       whichever occurs
                                                       later.
------------------------------------------------------------------------
(2) A310-300 series airplanes     At the time         Within 1,600
 (short range).                    specified in        flight cycles or
                                   paragraph (f)(2)    4,600 flight
                                   of this AD for      hours since the
                                   replacing the       last detailed
                                   pick-up angle.      inspection, or
                                                       within 30 days
                                                       after the
                                                       effective date of
                                                       this AD,
                                                       whichever occurs
                                                       later.
------------------------------------------------------------------------
(3) A310-300 series airplanes     At the time         Within 1,400
 (long range).                     specified in        flight cycles or
                                   paragraph (f)(2)    7,200 flight
                                   of this AD for      hours since the
                                   replacing the       last detailed
                                   pick-up angle.      inspection, or
                                                       within 30 days
                                                       after the
                                                       effective date of
                                                       this AD,
                                                       whichever occurs
                                                       later.
------------------------------------------------------------------------

Optional Terminating Modification

    (p) Remove the existing pick-up angles and install a reinforced 
doubler between frames (FR) FR40 and FR41, and perform applicable 
related investigative and corrective actions by accomplishing all 
the applicable actions specified in the Accomplishment Instructions 
of Airbus Service Bulletin A310-53-2119, Revision 01, dated February 
27, 2007; except as provided by paragraph (q) of this AD. 
Accomplishing these actions ends the repetitive inspections required 
by this AD.
    (q) If any crack is detected and Airbus Service Bulletin A310-
53-2119, Revision 01, dated February 27, 2007, specifies to contact 
Airbus: Before further flight, repair the crack 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).
    (r) Actions done before the effective date of this AD in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A310-53-2119, dated October 25, 2005, are acceptable for 
compliance with the corresponding requirements of paragraph (p) of 
this AD.

Alternative Methods of Compliance (AMOCs)

    (s) 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: Dan 
Rodina, Aerospace Engineer, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 
98057-3356; telephone (425) 227-2125; 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

    (t) EASA airworthiness directive 2007-0184, dated July 3, 2007, 
also addresses the subject of this AD.

Material Incorporated by Reference

    (u) You must use the service information identified in Table 3 
of this AD to do the actions required by this AD, unless the AD 
specifies otherwise. If you do the optional terminating modification 
provided in this AD, you must use Airbus Service Bulletin A310-53-
2119, Revision 01, including Appendix 01, dated February 27, 2007, 
to do the optional terminating modification.

Table 3--Material Incorporated by Reference for Actions required by This
                                   AD
------------------------------------------------------------------------
                                  Revision
       Service bulletin            level                 Date
------------------------------------------------------------------------
Airbus Service Bulletin A310-            01  June 21, 2000.
 53A2111, including Appendix
 01.
Airbus Mandatory Service                 03  May 21, 2007.
 Bulletin A310-53-2111,
 including Appendix 01.
------------------------------------------------------------------------

    (1) The Director of the Federal Register approved the 
incorporation by reference of the service information identified in 
Table 4 of this AD under 5 U.S.C. 552(a) and 1 CFR part 51.

             Table 4--New Material Incorporated by Reference
------------------------------------------------------------------------
                                  Revision
       Service bulletin            level                 Date
------------------------------------------------------------------------
Airbus Mandatory Service                 03  May 21, 2007.
 Bulletin A310-53-2111,
 including Appendix 01.
A310-53-2119, including                  01  February 27, 2007.
 Appendix 01.
------------------------------------------------------------------------

    (2) The Director of the Federal Register previously approved the 
incorporation by reference of Airbus Service Bulletin A310-53A2111, 
Revision 01, including Appendix 1, dated June 21, 2000, on February 
9, 2001 (66 FR 1031, January 5, 2001).
    (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-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/

[[Page 8732]]

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. E9-3765 Filed 2-25-09; 8:45 am]

BILLING CODE 4910-13-P