[Federal Register Volume 70, Number 223 (Monday, November 21, 2005)]
[Proposed Rules]
[Pages 70048-70052]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-22971]


 ========================================================================
 Proposed Rules
                                                 Federal Register
 ________________________________________________________________________
 
 This section of the FEDERAL REGISTER contains notices to the public of 
 the proposed issuance of rules and regulations. The purpose of these 
 notices is to give interested persons an opportunity to participate in 
 the rule making prior to the adoption of the final rules.
 
 ========================================================================
 

  Federal Register / Vol. 70, No. 223 / Monday, November 21, 2005 / 
Proposed Rules  

[[Page 70048]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-23007; Directorate Identifier 2005-NM-013-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A310-200 and -300 Series 
Airplanes

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

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for certain Airbus Model A310-200 and -300 series airplanes. This 
proposed AD would require repetitive inspections for cracks and 
corrosion of the areas behind the scuff plates below the passenger/crew 
doors and bulk cargo door, and repair of any cracked or corroded part. 
This proposed AD also would require repetitive inspections for cracks 
of the holes of the corner doublers, the fail-safe ring, and the door 
frames of the passenger/crew door structures. This proposed AD is 
prompted by reports of corrosion behind the scuff plates at passenger/
crew doors and the bulk cargo door and fatigue cracks on the corner 
doublers of the forward and aft passenger/crew door frames. We are 
proposing this AD to prevent such corrosion and fatigue cracking, which 
could result in reduced structural integrity of the door surroundings.

DATES: We must receive comments on this proposed AD by December 21, 
2005.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD.
     DOT Docket Web site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility, U.S. Department of 
Transportation, 400 Seventh Street SW., Nassif Building, room PL-401, 
Washington, DC 20590.
     By fax: (202) 493-2251.
     Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street SW., Washington, DC, between 9 a.m. 
and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact 
Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France.
    You can examine the contents of this AD docket on the Internet at 
http://dms.dot.gov, or in person at the Docket Management Facility, 
U.S. Department of Transportation, 400 Seventh Street SW., room PL-401, 
on the plaza level of the Nassif Building, Washington, DC. This docket 
number is FAA-2005-23007; the directorate identifier for this docket is 
2005-NM-013-AD.

FOR FURTHER INFORMATION CONTACT: Rosanne Ryburn, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2139; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to submit any relevant written data, views, or 
arguments regarding this proposed AD. Send your comments to an address 
listed under ADDRESSES. Include ``Docket No. FAA-2005-23007; 
Directorate Identifier 2005-NM-013-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the proposed AD. We will 
consider all comments submitted by the closing date and may amend the 
proposed AD in light of those comments.
    We will post all comments we receive, without change, to http://dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact with FAA 
personnel concerning this proposed AD. Using the search function of our 
docket Web site, anyone can find and read the comments in any of our 
dockets, including the name of the individual who sent the comment (or 
signed the comment on behalf of an association, business, labor union, 
etc.). You can review the DOT's complete Privacy Act Statement in the 
Federal Register published on April 11, 2000 (65 FR 19477-78), or you 
can visit http://dms.dot.gov.

Examining the Docket

    You can examine the AD docket on the Internet at http://dms.dot.gov, or in person at the Docket Management Facility Office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The Docket Management Facility Office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the DOT 
street address stated in the ADDRESSES section. Comments will be 
available in the AD docket shortly after the DMS receives them.

Discussion

    The Direction G[eacute]n[eacute]rale de l'Aviation Civile (DGAC), 
which is the airworthiness authority for France, notified us that an 
unsafe condition may exist on certain Airbus Model A310-200 and -300 
series airplanes. The DGAC advises that it received reports indicating 
that corrosion was found behind the scuff plates at passenger/crew 
doors and the bulk cargo door. The DGAC also advises that results of 
structural fatigue testing have revealed that cracks were found on the 
corner doublers of the forward and aft passenger/crew door frames; and, 
after various simulated flights, on the fail-safe ring and frames 14 
and 16A of the forward passenger/crew door. After 50,000 simulated 
flights, cracks measuring between 8.0 millimeters (mm) and 109.0 mm 
were found on the forward door frames and fail-safe ring. After 60,493 
simulated flights, a 53.0 mm crack was found on the mid door frame. 
After 106,000 simulated flights, a 32.0 mm crack was found on the aft 
door frame. In all cases, the cracks originated at the fastener holes. 
In addition, cracks originating from corner doubler edges were found at 
the aft passenger/crew doors.
    Such corrosion and fatigue cracking, if not detected and corrected, 
could result in reduced structural integrity of the door surroundings.

[[Page 70049]]

Other Relevant Rulemaking

    We have previously issued AD 97-11-03, amendment 39-10032 (62 FR 
28325, May 23, 1997), applicable to all Airbus Model A300 series 
airplanes. That AD requires inspections of the lower door surrounding 
structure to detect cracks and corrosion; inspections to detect 
cracking of the holes of the corner doublers, the fail-safe ring, and 
the door frames of the door structures; and repair if necessary. That 
AD also requires modification of the passenger/crew door frames, which 
terminates certain inspections.
    We also previously issued AD 98-16-05, amendment 39-10680 (63 FR 
40812, July 31, 1998), applicable to all Airbus Model A300-600 series 
airplanes. That AD requires inspections of the areas behind the scuff 
plates below the passenger/crew doors and bulk cargo door to detect 
cracks and corrosion; inspections to detect cracking of the holes of 
the corner doublers, the fail-safe ring, and the door frames of the 
door structures; and repair if necessary. In addition, that AD provides 
for an optional terminating action for certain inspections. We are 
considering further rulemaking to mandate the optional terminating 
action.

Relevant Service Information

    Airbus has issued the service bulletins in the following table:

                            Service Bulletins
------------------------------------------------------------------------
       Airbus Service Bulletin--            Describes procedures for--
------------------------------------------------------------------------
A310-53-2030, Revision 06, dated July    Doing initial inspections for
 2, 1996.                                 cracks and corrosion of the
                                          areas behind the scuff plates
                                          below the passenger/crew doors
                                          and bulk cargo door, and
                                          repairing any cracked or
                                          corroded part.
A310-53-2041, Revision 02, dated July    Doing repetitive inspections
 2, 1996.                                 for cracks and corrosion of
                                          the areas behind the scuff
                                          plates below the passenger/
                                          crew doors and bulk cargo
                                          door, and repairing any
                                          cracked or corroded part.
A310-53-2037, Revision 02, dated         Doing repetitive inspections
 November 27, 2000.                       for cracks of the holes of the
                                          corner doublers, the fail-safe
                                          ring, and the door frames of
                                          the passenger/crew door
                                          structures, and repairing any
                                          cracked part.
A310-53-2017, Revision 09, dated May     Modifying the passenger/crew
 17, 2004.                                door structures, which ends
                                          the repetitive inspections of
                                          the holes of the corner
                                          doublers, fail-safe ring, and
                                          the door frames for certain
                                          airplanes. The modification
                                          includes cold expansion of
                                          fastener holes; a ROTO test;
                                          installation of new oversize
                                          fasteners and modified
                                          brackets; and installation of
                                          an additional steel doubler.
------------------------------------------------------------------------

Accomplishing the actions specified in the service information is 
intended to adequately address the unsafe condition. The DGAC mandated 
the service information and issued French airworthiness directives 
1991-132-124(B) R1, issued November 29, 2000, and F-2004-103, issued 
July 7, 2004, to ensure the continued airworthiness of these airplanes 
in France.

FAA's Determination and Requirements of the Proposed AD

    These airplane models are manufactured in France and are type 
certificated for operation in the United States under the provisions of 
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and 
the applicable bilateral airworthiness agreement. Pursuant to this 
bilateral airworthiness agreement, the DGAC has kept the FAA informed 
of the situation described above. We have examined the DGAC's findings, 
evaluated all pertinent information, and determined that we need to 
issue an AD for products of this type design that are certificated for 
operation in the United States. Therefore, we are proposing this AD, 
which would require accomplishing the applicable actions specified in 
the service information described previously, except as discussed under 
``Differences Between the Proposed AD, French Airworthiness Directive, 
and Service Bulletins.''

Differences Between the Proposed AD, French Airworthiness Directive, 
and Service Bulletins

    Airbus Service Bulletin A310-53-2030 also does not list a grace 
period for certain compliance times. This proposed AD adds a grace 
period to certain compliance times. We find that a grace period will 
keep airplanes from being grounded unnecessarily.
    Airbus Service Bulletins A310-53-2041 and A310-53-2037 specify 
repetitive inspections at ``every'' specified interval; however, this 
proposed AD would require compliance ``at intervals not to exceed'' the 
time specified in the service bulletin. These service bulletins also 
specify compliance times in ``flights.'' This proposed AD would specify 
those times as flight cycles. In addition, Airbus Service Bulletin 
A310-53-2037 does not specify a starting date for the threshold for the 
initial inspections. This proposed AD would require compliance before 
the specified compliance time after the effective date of this AD.

Costs of Compliance

    The following table provides the estimated costs for U.S. operators 
to comply with this proposed AD. The average labor rate per hour is 
$65.

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                 Number of U.S.-
           Action                Work hours         Parts           Cost per       registered       Fleet cost
                                                                    airplane        airplanes
----------------------------------------------------------------------------------------------------------------
Initial inspections behind    26.............  None...........  $1,690.........              46  $77,740.
 scuff plates (for all
 airplanes).
Repetitive inspections        26.............  None...........  $1,690.........              46  $77,740, per
 behind scuff plates, per                                                                         inspection
 inspection cycle (for all                                                                        cycle.
 airplanes).

[[Page 70050]]

 
Inspections of corner         Between 4 and    None...........  Between $260                 46  Between
 doublers, fail-safe ring,     50 depending                      and $3,250.                      $11,960, and
 and door frames, per          on kit                                                             $149,500 per
 inspection cycle.             purchased.                                                         inspection
                                                                                                  cycle.
Terminating modification for  Between 8 and    Between $506     Between $1,026               46  Between $47,196
 repetitive inspection of      55 depending     and $6,098       and $9,673.                      and $444,958.
 corner doublers, fail-safe    on kit           depending on
 ring, and door frames.        purchased.       kit purchased.
----------------------------------------------------------------------------------------------------------------

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 0130132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify that the proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979); and
    3. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this proposed AD. See the ADDRESSES section for a location 
to examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

    1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 401013, 44701.


Sec.  39.13  [Amended]

    2. The Federal Aviation Administration (FAA) amends Sec.  39.13 by 
adding the following new airworthiness directive (AD):

Airbus: Docket No. FAA-2005-23007; Directorate Identifier 2005-NM-
013-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by December 
21, 2005.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Airbus Model A310-203, -204, -221, and -
222 airplanes; and Airbus Model A310-304, -322, -324, and -325 
airplanes; certificated in any category; excluding those airplanes 
on which Airbus Modification 5068, 7201, and 7298 have been 
incorporated in production.

Unsafe Condition

    (d) This AD was prompted by reports of corrosion behind the 
scuff plates at passenger/crew doors and the bulk cargo door and 
fatigue cracks on the corner doublers of the forward and aft 
passenger/crew door frames. We are issuing this AD to prevent such 
corrosion and fatigue cracking, which could result in reduced 
structural integrity of the door surroundings.

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.

Initial Inspections Behind Scuff Plates

    (f) Do initial inspections (i.e., non-destructive tests) for 
cracks and corrosion of the areas behind the scuff plates below the 
passenger/crew doors and bulk cargo door, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A310-53-2030, 
Revision 06, dated July 2, 1996. Do the inspections at the 
applicable time specified in paragraphs (f)(1) and (f)(2) of Table 1 
of this AD. If a records check cannot positively identify if the 
applicable modification or service information specified in 
paragraphs (f)(1) and (f)(2) of this AD has been done, assume that 
it has not.

  Table 1.--Compliance Time Requirements for Initial Inspections Behind
                              Scuff Plates
------------------------------------------------------------------------
   For airplanes on which
 Modification 5382S6526 for
    the forward doors and             And--               Inspect--
 Modification 5382D4741 for
      all other doors--
------------------------------------------------------------------------
(1) Have been incorporated    None................  Within 108 months
 in production.                                      after first flight.
(2) Have not been             (i) Airbus Service    Within 48 months
 incorporated in production.   Information Letter    since the date of
                               (SIL) A300-53-033,    issuance of the
                               Revision 2, dated     original standard
                               November 23, 1984,    Airworthiness
                               for all doors, was    Certificate or the
                               not followed; or      date of issuance of
                               Airbus Service        the original Export
                               Bulletin A310-53-     Certificate of
                               2004, Revision 2,     Airworthiness, or
                               March 9, 1984 (only   within 12 months
                               applicable for the    after the effective
                               forward doors), was   date of this AD,
                               not done.             whichever occurs
                                                     later.

[[Page 70051]]

 
                              (ii) Airbus SIL A300- Within 60 months
                               53-033, Revision 2,   since the date of
                               dated November 23,    issuance of the
                               1984, for all         original
                               doors, was            Airworthiness
                               followed; or Airbus   Certificate or the
                               Service Bulletin      date of issuance of
                               A310-53-2004,         the original Export
                               Revision 2, dated     Certificate of
                               March 9, 1984 (only   Airworthiness, or
                               applicable for the    within 12 months
                               forward doors), was   after the effective
                               done.                 date of this AD,
                                                     whichever occurs
                                                     later.
                              (iii) Airbus SIL      Within 12 months
                               A300-53-033,          after the effective
                               Revision 2, dated     date of this AD.
                               November 23, 1984,
                               for all doors, was
                               followed; or Airbus
                               Service Bulletin
                               A310-53-2004,
                               Revision 2, dated
                               March 9, 1984 (only
                               applicable for the
                               forward doors), was
                               done more than 48
                               months ago as of
                               the effective date
                               of this AD.
------------------------------------------------------------------------

Repetitive Inspections Behind Scuff Plates

    (g) Following the initial inspection required by paragraph (f) 
of this AD, do repetitive inspections (i.e., non-destructive tests) 
for cracks and corrosion of the areas behind the scuff plates below 
the passenger/crew doors and bulk cargo door, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A310-53-2041, 
Revision 02, dated July 2, 1996. Repeat the inspections at the 
applicable times specified in paragraphs (g)(1) through (g)(4) of 
Table 2 of this AD.

              Table 2.--Compliance Time Requirements for Repetitive Inspections Behind Scuff Plates
----------------------------------------------------------------------------------------------------------------
                                                                                             Unless in case of
                                                                                            corrosion removal,
               For--                             At--              Inspect at intervals       then inspect at
                                                                      not to exceed--        intervals not to
                                                                                                 exceed--
----------------------------------------------------------------------------------------------------------------
(1) All airplanes..................  The forward passenger/crew   60 months.............  None.
                                      doors and the bulk cargo
                                      door.
(2) All airplanes..................  The aft passenger/crew       60 months.............  None.
                                      doors, except the upper
                                      and lower edges of the
                                      door frame panel cutout.
(3) Model A310-203, -204, -221, and  The aft passenger/crew       60 months or 12,000     60 months or 9,600
 -222 airplanes.                      doors, the upper and lower   flight cycles,          flight cycles,
                                      edges of the door frame      whichever occurs        whichever occurs
                                      panel cutout.                first.                  first.
(4) Model A310-304, -322, -324, and  The aft passenger/crew       60 months or 7,000      60 months or 5,600
 -325 airplanes.                      doors, the upper and lower   flight cycles,          flight cycles,
                                      edges of the door frame      whichever occurs        whichever occurs
                                      panel cutout.                first.                  first.
----------------------------------------------------------------------------------------------------------------

Repetitive Inspections of Corner Doublers, Fail-Safe Ring, and Door 
Frames

    (h) Do inspections (i.e., rotating probe, x-ray, and general 
visual, as applicable) for cracks of the holes of the corner 
doublers, the fail-safe ring, and the door frames of the passenger/
crew door structures, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A310-53-2037, Revision 02, 
dated November 27, 2000. Do the inspections at the applicable times 
specified in paragraphs (h)(1) through (h)(3) of Table 3 of this AD, 
until the modification required by paragraph (k) of this AD is done.

  Table 3.--Compliance Time Requirements for Repetitive Inspections of
            Corner Doublers, Fail-Safe Ring, and Door Frames
------------------------------------------------------------------------
            For--                   Inspect--               And--
------------------------------------------------------------------------
(1) The upper corners of the  Before the            Do rotating probe
 forward doors.                accumulation of       inspections at
                               20,000 total flight   intervals not to
                               cycles, or within     exceed 6,000 flight
                               2,000 flight cycles   cycles.
                               after the effective
                               date of this AD,
                               whichever occurs
                               later.
(2) The lower corners of the  Before the            Do rotating probe
 forward doors.                accumulation of       inspections at
                               20,000 total flight   intervals not to
                               cycles, or within     exceed 10,000
                               4,000 flight cycles   flight cycles.
                               after the effective
                               date of this AD,
                               whichever occurs
                               later.
(3) The upper and lower       Before the            Do rotating probe
 corners and parts             accumulation of       inspections at
 underneath the corners of     20,000 total flight   intervals not to
 the upper door frames of      cycles, or within     exceed 8,000 flight
 the aft doors.                4,000 flight cycles   cycles or do x-ray
                               after the effective   inspections at
                               date of this AD,      intervals not to
                               whichever occurs      exceed 3,500 flight
                               later.                cycles; and do
                                                     general visual
                                                     inspections of
                                                     areas around
                                                     fasteners in
                                                     vicinity of
                                                     stringer 12 of the
                                                     upper door frames
                                                     at intervals not to
                                                     exceed 6,900 flight
                                                     cycles.
------------------------------------------------------------------------



[[Page 70052]]

    Note 1: For the purposes of this AD, a general visual inspection 
is: ``A visual examination of an interior or exterior area, 
installation, or assembly to detect obvious damage, failure, or 
irregularity. This level of inspection is made from within touching 
distance unless otherwise specified. A mirror may be necessary to 
ensure visual access to all surfaces in the inspection area. This 
level of inspection is made under normally available lighting 
conditions such as daylight, hangar lighting, flashlight, or 
droplight and may require removal or opening of access panels or 
doors. Stands, ladders, or platforms may be required to gain 
proximity to the area being checked.''

Corrective Actions

    (i) If any crack or corrosion is found during any inspection 
required by this AD, before further flight, do the applicable 
corrective action in paragraph (i)(1) through (i)(3) of Table 4 of 
this AD, except as provided by paragraph (j) of this AD.

                      Table 4.--Corrective Actions
------------------------------------------------------------------------
                                                     In accordance with
            If--                     Then--          the accomplishment
                                                      instructions of--
------------------------------------------------------------------------
(1) Any crack or corrosion    Repair the cracked    Airbus Service
 is found during any           or corroded part.     Bulletin A310-53-
 inspection required by                              2030, Revision 06,
 paragraph (f) of this AD.                           dated July 2, 1996.
(2) Any crack or corrosion    Repair the cracked    Airbus Service
 is found during any           or corroded part.     Bulletin A310-53-
 repetitive inspection                               2041, Revision 02,
 required by paragraph (g)                           dated July 2, 1996.
 of this AD.
(3) Any crack is found        Repair the cracked    Airbus Service
 during any inspection         part.                 Bulletin A310-53-
 required by paragraph (h)                           2037, Revision 02,
 of this AD.                                         dated November 27,
                                                     2000.
------------------------------------------------------------------------

    (j) If any crack or corrosion is found during any inspection 
required by this AD, and the service bulletin recommends contacting 
Airbus for appropriate action: Before further flight, repair the 
cracked or corroded part in accordance with a method approved by 
either the Manager, International Branch, ANM-116, FAA, Transport 
Airplane Directorate; or the Direction G[eacute]n[eacute]rale de 
l'Aviation Civile (DGAC) (or its delegated agent).

Terminating Modification for Repetitive Inspection of Corner Doublers, 
Fail-Safe Ring, and Door Frames

    (k) Modify the passenger/crew door structures in accordance with 
the Accomplishment Instructions of Airbus Service Bulletin A310-53-
2017, Revision 09, dated May 17, 2004. Do the modification at the 
applicable time in paragraph (k)(1) or (k)(2) of Table 5 of this AD. 
Accomplishment of this modification constitutes terminating action 
for the repetitive inspections required by paragraph (h) of this AD. 
The inspections required by paragraph (f) of this AD must be done 
before accomplishing this modification.

         Table 5.--Compliance Time for Terminating Modification
------------------------------------------------------------------------
              For model--                        Compliance time
------------------------------------------------------------------------
(1) A310-203, -204, -221, and -222       Before the accumulation of
 airplanes.                               40,000 flight cycles since the
                                          date of issuance of the
                                          original standard
                                          Airworthiness Certificate or
                                          the date of issuance of the
                                          original Export Certificate of
                                          Airworthiness, or during the
                                          next inspection required by
                                          paragraph (h) of this AD,
                                          whichever occurs later.
(2) A310-304, -322, -324, and -325        Before the accumulation of
 airplanes.                               35,000 flight cycles since the
                                          date of issuance of the
                                          original standard
                                          Airworthiness Certificate or
                                          the date of issuance of the
                                          original Export Certificate of
                                          Airworthiness, or during the
                                          next inspection required by
                                          paragraph (h) of this AD,
                                          whichever occurs later.
------------------------------------------------------------------------

Alternative Methods of Compliance (AMOCs)

    (l)(1) The Manager, International Branch, ANM-116, FAA, has the 
authority to approve AMOCs for this AD, if requested in accordance 
with the procedures found in 14 CFR 39.19.
    (2) Before using any AMOC approved in accordance with Sec.  
39.19 on any airplane to which the AMOC applies, notify the 
appropriate principal inspector in the FAA Flight Standards 
Certificate Holding District Office.

Related Information

    (m) French airworthiness directives 1991-132-124(B) R1, issued 
November 29, 2000, and F-2004-103, issued July 7, 2004, also address 
the subject of this AD.

    Issued in Renton, Washington, on November 9, 2005.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-22971 Filed 11-18-05; 8:45 am]
BILLING CODE 4910-13-P