[Federal Register Volume 72, Number 12 (Friday, January 19, 2007)]
[Proposed Rules]
[Pages 2464-2469]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E7-702]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-26857; Directorate Identifier 2006-NM-126-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 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. The existing AD also provides for optional terminating 
action for certain inspections. This proposed AD would retain all 
requirements of the existing AD, mandate the previously optional 
terminating action, and reduce the applicability of the existing AD.

[[Page 2465]]

This proposed AD results from a determination that further rulemaking 
is necessary to improve the fatigue behavior of the cabin door 
surroundings. We are proposing this AD to prevent corrosion between the 
scuff plates at exit and cargo doors and fatigue cracks originating 
from certain fastener holes located in adjacent structure, which could 
result in reduced structural integrity of the door surroundings.

DATES: We must receive comments on this proposed AD by February 20, 
2007.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD.
    <bullet> DOT Docket Web site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
    <bullet> Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your 
comments electronically.
    <bullet> Mail: Docket Management Facility; U.S. Department of 
Transportation, 400 Seventh Street SW., Nassif Building, Room PL-401, 
Washington, DC 20590.
    <bullet> Fax: (202) 493-2251.
    <bullet> 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.
    Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, 
France, for service information identified in this proposed AD.

FOR FURTHER INFORMATION CONTACT: Tom Stafford, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
227-1622; 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 in the ADDRESSES section. Include the docket number ``Docket No. 
FAA-2007-26857; Directorate Identifier 2006-NM-126-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 received 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 
that 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 may review the DOT's complete Privacy Act Statement in the 
Federal Register published on April 11, 2000 (65 FR 19477-78), or you 
may visit http://dms.dot.gov.

Examining the Docket

    You may 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 Docket Management System 
receives them.

Discussion

    On July 24, 1998, we issued AD 98-16-06, amendment 39-10682 (63 FR 
40819, July 31, 1998), for all Airbus Model A310 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 provides 
for optional terminating action for certain inspections. That AD 
resulted from reports indicating that corrosion was found between the 
scuff plates at exit and cargo doors, and fatigue cracks originated 
from certain fastener holes located in adjacent structure. We issued 
that AD to detect and correct such corrosion and fatigue cracking, 
which could result in reduced structural integrity of the door 
surroundings.

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.

Actions Since Existing AD Was Issued

    Since we issued AD 98-16-06, the Direction G[eacute]n[eacute]rale 
de l'Aviation Civile (DGAC), which is the airworthiness authority for 
France, issued French airworthiness directives 1991-132-124(B) R1, 
dated November 29, 2000 (to replace French airworthiness directive 91-
132-124(B), dated June 26, 1992, which is referred to in AD 98-16-06), 
and F-2004-103, dated July 7, 2004. The DGAC advises that further 
rulemaking is necessary to improve the fatigue behavior of the cabin 
door surroundings on certain Airbus Model A310 series airplanes and to 
remove certain airplanes from the applicability of the existing French 
airworthiness directive 91-132-124(B) that are no longer subject to the 
existing requirements. Corrosion between the scuff plates at exit and 
cargo doors and fatigue cracks originating from certain fastener holes 
located in adjacent structure, if not corrected, could result in 
reduced structural integrity of the door surroundings.
    After the DGAC issued French airworthiness directive 1991-132-
124(B) R1 on November 29, 2000, we determined at that time that further 
rulemaking was not necessary, because the changes to AD 98-16-06 would 
be relieving in nature. However, since French airworthiness directive 
F-2004-103 mandates the previously optional modification, we now agree 
with the DGAC that further rulemaking is indeed necessary to improve 
the fatigue behavior of the cabin door surroundings, and this proposed 
AD follows from that determination.

Relevant Service Information

    Airbus has issued and revised the service bulletins in the 
following table:

[[Page 2466]]



                            Service Bulletins
------------------------------------------------------------------------
     Airbus Service Bulletin--           Describes procedures for--
------------------------------------------------------------------------
A310-53-2030, Revision 06, dated    Doing initial inspections for cracks
 July 2, 1996 (Revision 5 of the     and corrosion of the areas behind
 service bulletin was referenced     the scuff plates below the
 in AD 98-16-06 as an appropriate    passenger/crew doors and bulk cargo
 source of service information).     door, and repairing any cracked or
                                     corroded part. The inspection and
                                     repair are essentially identical to
                                     those specified in Revisions 2
                                     through 5 of the service bulletin.
A310-53-2037, Revision 02, dated    Doing repetitive inspections for
 November 27, 2000 (Revision 1 of    cracks of the holes of the corner
 the service bulletin was            doublers, the fail-safe ring, and
 referenced in AD 98-16-06 as an     the door frames of the passenger/
 appropriate source of service       crew door structures, and repairing
 information).                       any cracked part. The inspection
                                     and repair are essentially
                                     identical to those specified in
                                     Revision 1 of the service bulletin.
A310-53-2017, Revision 09, dated    Modifying the passenger/crew door
 May 17, 2004 (Revision 7 of the     structures, which ends the
 service bulletin was referenced     repetitive inspections of the holes
 in AD 98-16-06 as an appropriate    of the corner doublers specified in
 source of service information).     Airbus Service Bulletin A310-53-
                                     2037, the 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. The modification is
                                     essentially identical to that
                                     specified in Revisions 7 and 08 of
                                     the service bulletin.
------------------------------------------------------------------------

    In addition, Airbus previously issued Service Bulletin A310-53-
2041, Revision 02, dated July 2, 1996 (which was referenced in AD 98-
16-06 as an appropriate source of service information). The service 
bulletin describes procedures for doing repetitive inspections 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.
    Accomplishing the actions specified in the service information is 
intended to adequately address the unsafe condition. The DGAC mandated 
the service information to ensure the continued airworthiness of these 
airplanes in France.

FAA's Determination and Requirements of the Proposed AD

    This airplane model is manufactured in France and is 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 AD action is 
necessary for airplanes of this type design that are certificated for 
operation in the United States.
    This proposed AD would supersede AD 98-16-06 and would retain the 
requirements of the existing AD. This proposed AD would also require 
accomplishing the actions specified in service information described 
previously.

Difference Between French Airworthiness Directives and This Proposed AD

    The applicability of French airworthiness directives 1991-132-
124(B) R1 and F-2004-103 exclude airplanes on which Airbus Service 
Bulletin A310-53-2017 at Revision 1 (or any other later approved 
revision) has been done in service. However, we have not excluded those 
airplanes in the applicability of this proposed AD; rather, this 
proposed AD includes a requirement to accomplish the actions specified 
in Revision 09 of that service bulletin. This requirement would ensure 
that the actions specified in the service bulletin and required by this 
proposed AD are accomplished on all affected airplanes. Operators must 
continue to operate the airplane in the configuration required by this 
proposed AD unless an alternative method of compliance is approved.

Change to Existing AD

    This proposed AD would retain all requirements of AD 98-16-06. 
Since AD 98-16-06 was issued, the AD format has been revised, and 
certain paragraphs and a note 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 paragraphs in
    Paragraphs and note in AD 98-16-06            this proposed AD
------------------------------------------------------------------------
Paragraph (a).............................  Paragraph (f).
Paragraph (b).............................  Paragraph (g).
Paragraph (c).............................  Paragraph (h).
Paragraph (d).............................  Paragraph (i).
NOTE 2....................................  Paragraph (j).
Paragraph (e).............................  Paragraph (k).
Paragraph (f).............................  Paragraph (l).
Paragraph (g).............................  Paragraph (m).
Paragraph (h).............................  Paragraph (o).
------------------------------------------------------------------------

    The DGAC revised the applicability of French airworthiness 
directives 1991-132-124(B) R1 and F-2004-103 to exclude Model A310 
series airplanes on which Airbus Modification 5068, 7201, and 7298 have 
been incorporated in production. Therefore, the applicability of the 
proposed AD parallels the French airworthiness directives in that 
regard.
    We have revised the affected airplanes in paragraphs (f)(1) through 
(f)(3) of this proposed AD (paragraphs (a)(1) through (a)(3) of AD 98-
16-06) to include ``and Modification 5382D4741 for all other doors.'' 
This information is specified in the referenced service bulletin, but 
was inadvertently omitted from those paragraphs in AD 98-16-06. This 
change reduces the number of affected airplanes.

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 work hour 
is $80.

[[Page 2467]]



                                                                     Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                                                                                 Number of U.S.-
               Action                        Work hours                 Parts              Cost per airplane       registered           Fleet cost
                                                                                                                    airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Repetitive inspections behind scuff   26.....................  None...................  $2,080................                46  $95,680.
 plates (required by AD 98-16-06).
Repetitive inspections of corner      Between 4 and 100        None...................  Between $320 and                      46  Between $14,720, and
 doublers, fail-safe ring, and door    depending on kit                                  $8,000.                                   $368,000 per
 frames (required by AD 98-16-06).     purchased.                                                                                  inspection cycle.
Terminating modification for          Between 8 and 55         Between $506 and $6,098  Between $1,146 and                    46  Between $52,716 and
 repetitive inspection of corner       depending on kit         depending on kit         $10,498.                                  $482,908.
 doublers, fail-safe ring, and door    purchased.               purchased.
 frames.
--------------------------------------------------------------------------------------------------------------------------------------------------------

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, Section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We have determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify that the proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979); and
    3. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this proposed AD and placed it in the AD docket. See the 
ADDRESSES section for a location to examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

    2. The Federal Aviation Administration (FAA) amends Sec.  39.13 by 
removing amendment 39-10682 (63 FR 40819, July 31, 1998) and adding the 
following new airworthiness directive (AD):

Airbus: Docket No. FAA-2007-26857; Directorate Identifier 2006-NM-
126-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by February 
20, 2007.

Affected ADs

    (b) This AD supersedes AD 98-16-06.

Applicability

    (c) This AD applies to Airbus Model A310 series 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 results from a determination that further rulemaking 
is necessary to improve the fatigue behavior of the cabin door 
surroundings. We are issuing this AD to prevent corrosion between 
the scuff plates at exit and cargo doors and fatigue cracks 
originating from certain fastener holes located in adjacent 
structure, 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.

Requirements of AD 98-16-06

Initial Inspection Behind Scuff Plates and Repair If Necessary With 
Revised Affected Doors

    (f) Perform an initial inspection of the areas behind the scuff 
plates below the passenger/crew doors and bulk cargo door to detect 
cracks and corrosion, in accordance with Airbus Service Bulletin 
A310-53-2030, Revision 5, dated March 6, 1991, at the applicable 
time specified in paragraph (f)(1), (f)(2), or (f)(3) of this AD. If 
any crack or corrosion is found during this inspection, prior to 
further flight, repair in accordance with the service bulletin. 
Accomplishment of this inspection is not required for the aft 
passenger/crew doors if a steel doubler that covers the entire 
inspection area is installed.
    (1) For any door on which Modification 5382 and Modification 
5382D4741 for all other doors have been accomplished: Perform the 
initial inspection within 9 years since airplane manufacture, or 
within 1 year after September 4, 1998 (the effective date of AD 98-
16-06), whichever occurs later.
    (2) For any door on which Modification 5382 and Modification 
5382D4741 for all other doors have not been accomplished, and on 
which the procedures described in Airbus Service Bulletin A310-53-
2004, Revision 2, dated June 17, 1985, or Airbus Service Information 
Letter 53-033, Revision 2, dated November 23, 1984, have been 
accomplished: Perform the initial inspection within 5 years since 
airplane manufacture, or within 1 year after September 4, 1998, 
whichever occurs later.
    (3) For any door on which Modification 5382 and Modification 
5382D4741 for all other doors have not been accomplished, and on 
which the procedures described in Airbus Service Bulletin A310-53-
2004, Revision 2, dated June 17, 1985, or Airbus Service Information 
Letter 53-033, Revision 2, dated November 23, 1984, have not been 
accomplished: Perform the initial inspection within 4 years since 
airplane manufacture, or within 1 year after September 4, 1998, 
whichever occurs later.

[[Page 2468]]

Repetitive Inspections Behind Scuff Plates

    (g) Perform repetitive inspections of the areas behind the scuff 
plates below the passenger/crew doors and bulk cargo door to detect 
cracks and corrosion, in accordance with Airbus Service Bulletin 
A310-53-2041, Revision 02, dated July 2, 1996, at the applicable 
times specified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD. 
Accomplishment of these inspections is not required for the aft 
passenger/crew doors if a steel doubler that covers the entire 
inspection area is installed.
    (1) For the forward passenger/crew doors, the bulk cargo door, 
and the aft passenger/crew doors, except the upper and lower edges 
of the fail-safe ring and the upper edges of the corner doubler, on 
all Model A310-200 and -300 series airplanes: Perform the first 
inspection within 5 years after accomplishing the inspection 
required by paragraph (f) of this AD; and repeat the inspection 
thereafter at intervals not to exceed 5 years.
    (2) For the upper and lower edges of the fail-safe ring and the 
upper edges of the corner doubler of the aft passenger/crew door on 
all Model A310-200 series airplanes: Perform the first inspection 
within 5 years or 12,000 landings after accomplishing the inspection 
required by paragraph (f) of this AD, whichever occurs first; and 
repeat the inspection thereafter at intervals not to exceed 5 years 
or 12,000 landings, whichever occurs first.
    (3) For the upper and lower edges of the fail-safe ring and the 
upper edges of the corner doubler of the aft passenger/crew door on 
all Model A310-300 series airplanes: Perform the first inspection 
within 5 years or 7,000 landings after accomplishing the inspection 
required by paragraph (f) of this AD, whichever occurs first; and 
repeat the inspection thereafter at intervals not to exceed 5 years 
or 7,000 landings, whichever occurs first.

Repair of Scuff Plates If Necessary

    (h) If any crack is found during any inspection required by 
paragraph (g) or (n) of this AD, prior to further flight, repair in 
accordance with Airbus Service Bulletin A310-53-2041, Revision 02, 
dated July 2, 1996. Thereafter, perform the repetitive inspections 
required by paragraph (g) of this AD at the applicable times 
specified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD.
    (i) If any corrosion is found during any inspection required by 
paragraph (g) of this AD, prior to further flight, repair in 
accordance with Airbus Service Bulletin A310-53-2041, Revision 02, 
dated July 2, 1996. Thereafter, perform the repetitive inspections 
required by paragraph (g) of this AD at the applicable time 
specified in paragraph (i)(1) or (i)(2) of this AD.
    (1) For Model A310-200 series airplanes: Inspect at intervals 
not to exceed 5 years or 9,600 landings, whichever occurs first.
    (2) For Model A310-300 series airplanes: Inspect at intervals 
not to exceed 5 years or 5,600 landings, whichever occurs first.
    (j) Accomplishment of the actions required by paragraph (g), 
(h), or (i) of this AD in accordance with Airbus Service Bulletin 
A310-53-2041, dated December 5, 1990; or Revision 1, dated March 6, 
1991, prior to September 4, 1998, is acceptable for compliance with 
that paragraph.

Initial Inspection of Corner Doublers, Fail-Safe Ring, and Door 
Frames

    (k) Perform an inspection to detect cracking of the holes of the 
corner doublers, the fail-safe ring, and the door frames of the 
left- and right-hand forward, mid, and aft passenger/crew door 
structures, in accordance with Airbus Service Bulletin A310-53-2037, 
Revision 1, dated April 29, 1992, and at the applicable times 
specified in paragraphs (k)(1), (k)(2), and (k)(3) of this AD.
    (1) For the upper corners of the forward doors: Inspect prior to 
the accumulation of 20,000 total landings, or within 2,000 landings 
after September 4, 1998, whichever occurs later.
    (2) For the lower corners of the forward doors: Inspect prior to 
the accumulation of 20,000 total landings, or within 4,000 landings 
after September 4, 1998, whichever occurs later.
    (3) For the upper and lower corners of the aft doors, and for 
the parts underneath the corners of the upper door frames: Inspect 
prior to the accumulation of 20,000 total landings, or within 4,000 
landings after September 4, 1998, whichever occurs later.

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

    (l) Repeat the inspections required by paragraph (k) of this AD 
at the applicable times specified in paragraphs (l)(1), (l)(2), 
(l)(3), (l)(4), and (l)(5).
    (1) For the upper corners of the forward doors: Inspect at 
intervals not to exceed 6,000 landings.
    (2) For the lower corners of the forward doors: Inspect at 
intervals not to exceed 10,000 landings.
    (3) For the upper and lower corners of the aft doors on which an 
inspection required by paragraph (k) of this AD was accomplished 
using a ROTO test technique: Inspect at intervals not to exceed 
8,000 landings.
    (4) For the upper and lower corners of the aft doors on which an 
inspection required by paragraph (k) of this AD was accomplished 
using an X-ray technique: Inspect at intervals not to exceed 3,500 
landings.
    (5) For the areas around the fasteners in the vicinity of 
stringer 12 on the upper door frames of the aft doors on which an 
inspection required by paragraph (k) of this AD was accomplished 
using a visual technique: Inspect at intervals not to exceed 6,900 
landings.

Repair of Corner Doublers, Fail-Safe Ring, and/or Door Frames If 
Necessary

    (m) If any crack is found during any inspection required by 
paragraph (k) or (l) of this AD: Prior to further flight, accomplish 
the requirement of paragraph (m)(1) or (m)(2) of this AD, as 
applicable.
    (1) If any crack is found, and the crack can be eliminated using 
the method specified in Airbus Service Bulletin A310-53-2037, 
Revision 1, dated April 29, 1992; or Revision 02, dated November 27, 
2000: Prior to further flight, repair the crack in accordance with 
that service bulletin.
    (2) If any crack is found, and the crack cannot be eliminated 
using the method specified in Airbus Service Bulletin A310-53-2037, 
Revision 1, dated April 29, 1992; or Revision 02, dated November 27, 
2000: Prior to further flight, repair the crack in accordance with a 
method approved by the Manager, International Branch, ANM-116, FAA, 
Transport Airplane Directorate.

New Requirements of This AD

New Revision of Service Bulletins

    (n) As of the effective date of this AD, use only the service 
bulletin specified in Table 1 of this AD.

               Table 1.--New Revision of Service Bulletins
------------------------------------------------------------------------
                                           In accordance with the
  Do the action(s) required by--       accomplishment instructions of
                                          Airbus Service Bulletin--
------------------------------------------------------------------------
(1) Paragraph (f) of this AD......  A310-53-2030, Revision 06, dated
                                     July 2, 1996.
(2) Paragraph (k) and (m)(1) of     A310-53-2037, Revision 02, dated
 this AD.                            November 27, 2000.
------------------------------------------------------------------------

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

    (o) 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 (o)(1) or (o)(2) of Table 2 of this AD. 
Accomplishment of this modification constitutes terminating action 
for the repetitive inspections required by paragraph (l) of this AD. 
The inspections required by paragraph (f) of this AD must be done 
before accomplishing this modification.

[[Page 2469]]



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

Earlier Revision of Service Bulletins

    (p) Actions done before the effective date of this AD in 
accordance with the service bulletins identified in Table 3 of this 
AD, are acceptable for compliance with the corresponding 
requirements of this AD.

             Table 3.--Earlier Revision of Service Bulletins
------------------------------------------------------------------------
                                  Revision
    Airbus service bulletin        level                 Date
------------------------------------------------------------------------
(1) A310-53-2017..............            7  February 25, 1992.
(2) A310-53-2017..............           08  September 7, 2000.
------------------------------------------------------------------------

Alternative Methods of Compliance (AMOCs)

    (q)(1) The Manager, International Branch, ANM-116, has the 
authority to approve AMOCs for this AD, if requested in accordance 
with the procedures found in 14 CFR 39.19.
    (2) Alternative methods of compliance, approved previously in 
accordance with AD 98-16-06 are approved as alternative methods of 
compliance with the corresponding provisions of paragraphs (f) 
through (m) of this AD.
    (3) 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

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

    Issued in Renton, Washington, on January 8, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E7-702 Filed 1-18-07; 8:45 am]
BILLING CODE 4910-13-P