[Federal Register Volume 73, Number 166 (Tuesday, August 26, 2008)]
[Proposed Rules]
[Pages 50250-50253]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E8-19715]


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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]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A310 Series 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 Airbus Model A310 series airplanes. 
The existing 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 proposed AD 
would revise the intervals for accomplishing the repetitive detailed 
inspections and would provide for an optional terminating modification 
for the repetitive inspections. This proposed 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 proposing 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: We must receive comments on this proposed AD by September 25, 
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

[[Page 50251]]

available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT:
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.

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-2008-0908; 
Directorate Identifier 2007-NM-190-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 December 22, 2000, we issued AD 2000-26-14, amendment 39-12064 
(66 FR 1031, January 5, 2001), for all Airbus Model A310 series 
airplanes. That AD requires repetitive detailed visual 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 AD resulted 
from a report indicating that structural damage was found on the pick-
up angles at the junction between the wing lower surface and the 
fuselage skin at frame 40. We issued that AD to prevent reduced 
structural integrity of the airplane due to fatigue damage and 
consequent cracking of the pick-up angles at frame 40.

Actions Since Existing AD Was Issued

    Since we issued AD 2000-26-14, European Aviation Safety Agency 
(EASA), which is the Technical Agent for the Member States of the 
European Community, has informed us that, as a result of A310 extended 
service goal activities, the thresholds and repetitive intervals for 
the existing repetitive detailed visual inspections required by AD 
2000-26-14 must be modified to adequately address the identified unsafe 
condition.

Relevant Service Information

    Airbus has issued Revision 03 of Service Bulletin A310-53-2111, 
dated May 21, 2007 (AD 2000-26-14 refers to Airbus Service Bulletin 
A310-53-2111, Revision 01, dated June 21, 2000, as the appropriate 
source of service information for accomplishing the required actions). 
The inspection procedures specified in Revision 03 are essentially 
identical to those specified in Revision 01. Revision 03 revises the 
thresholds and repetitive intervals for the inspections and thresholds 
for replacing pick-up angles. No additional work is required by 
Revision 03 for airplanes inspected in accordance with earlier 
revisions. Accomplishing the actions specified in the service 
information is intended to adequately address the unsafe condition. The 
EASA mandated Service Bulletin A310-53-2111, Revision 03, and issued 
airworthiness directive 2007-0184, dated July 3, 2007, to ensure the 
continued airworthiness of these airplanes in the European Union.
    Airbus also issued Service Bulletin A310-53-2119, Revision 01, 
dated February 27, 2007. The service bulletin describes procedures for 
removing the existing pick-up angles and installing a reinforced 
doubler between frames (FR) FR40 and FR41, and doing applicable related 
investigative and corrective actions. The related investigative actions 
include inspecting the diameters of the holes, and doing a rotating 
probe inspection of the holes 1 through 70. The corrective actions 
involve contacting the airplane manufacturer for repair procedures. 
EASA airworthiness directive 2007-0184 refers to this service bulletin 
as an optional terminating action for the repetitive inspections 
specified in Service Bulletin A310-53-2111, Revision 03.

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 2000-26-14 and would continue 
to require repetitive detailed inspections to detect cracks propagating 
from the fasteners 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 proposed AD would revise the 
intervals for accomplishing the repetitive detailed inspections and 
would provide for an optional terminating modification for the 
repetitive inspections.

Change to Existing AD

    This proposed AD would retain all requirements of AD 2000-26-14. 
Since AD 2000-26-14 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 in
      Requirement in AD 2000-26-14               this proposed AD
------------------------------------------------------------------------
paragraph (a)...........................  paragraph (f).
paragraph (b)...........................  paragraph (g).
paragraph (c)...........................  paragraph (h).
paragraph (d)...........................  paragraph (i).
paragraph (e)...........................  paragraph (j).
paragraph (f)...........................  paragraph (k).
------------------------------------------------------------------------

    We also have 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 68 Model A310 series airplanes 
of U.S. registry.
    The inspections that are required by AD 2000-26-14 and retained in 
this proposed 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.

[[Page 50252]]

    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 39-12064 (66 FR 1031, January 5, 2001) and adding 
the following new airworthiness directive (AD):

Airbus: Docket No. FAA-2008-0908; Directorate Identifier 2007-NM-
190-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by September 
25, 2008.

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, 
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.''


[[Page 50253]]



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

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

    Issued in Renton, Washington, on August 18, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E8-19715 Filed 8-25-08; 8:45 am]
BILLING CODE 4910-13-P