[Federal Register Volume 71, Number 95 (Wednesday, May 17, 2006)]
[Proposed Rules]
[Pages 28615-28619]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E6-7477]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-23690; Directorate Identifier 2004-NM-133-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 B2 and B4 Series 
Airplanes; and Model A300 B4-600, B4-600R, and F4-600R Series 
Airplanes, and Model C4-605R Variant F Airplanes (Collectively Called 
A300-600 Series Airplanes)

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

ACTION: Supplemental notice of proposed rulemaking (NPRM); reopening of 
comment period.

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SUMMARY: The FAA is revising an earlier NPRM for an airworthiness 
directive (AD) that applies to certain Airbus Model A300 B2, A300 B4, 
and A300-600 series airplanes. The original NPRM would have superseded 
two existing ADs. One AD currently requires an inspection for cracks of 
the lower outboard flange of gantry No. 4 in the main landing gear 
(MLG) bay area, and repair if necessary. The other AD currently 
requires, among other actions, repetitive inspections of the gantry 
lower flanges, and repair if necessary. The original NPRM proposed to 
require new repetitive inspections for cracks in the lower flange of 
certain gantries, and repair if necessary, which ends the existing 
inspection requirements. The original NPRM also provided for optional 
terminating actions for the new repetitive inspections. This new action 
revises the original NPRM by including additional airplanes that were 
excluded from the applicability. We are proposing

[[Page 28616]]

this supplemental NPRM to detect and correct fatigue cracks in the 
lower flanges of gantries 1 through 5 inclusive in the MLG bay area, 
which could result in reduced structural integrity of the fuselage, and 
consequent rapid decompression of the airplane.

DATES: We must receive comments on this supplemental NPRM by June 12, 
2006.

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.
     Governmentwide 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.
     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.
    Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, 
France, for service information identified in this proposed AD.

FOR FURTHER INFORMATION CONTACT: Thomas Stafford, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; 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 proposal. Send your comments to an address 
listed in the ADDRESSES section. Include the docket number ``Docket No. 
FAA-2006-23690; Directorate Identifier 2004-NM-133-AD'' at the 
beginning of your comments. We specifically invite comments on the 
overall regulatory, economic, environmental, and energy aspects of this 
supplemental NPRM. We will consider all comments received by the 
closing date and may amend this supplemental NPRM in light of those 
comments.
    We will post all comments submitted, 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 ADDRESSES. Comments will be available in the 
AD docket shortly after the Docket Management System receives them.

Discussion

    The FAA issued a notice of proposed rulemaking (NPRM) (the 
``original NPRM'') to amend 14 CFR part 39 to include an AD that 
supersedes AD 2003-26-10, amendment 39-13408 (69 FR 867, January 7, 
2004), and AD 2004-18-13, amendment 39-13792 (69 FR 55329, September 
14, 2004). The original NPRM applied to certain Airbus Model A300 B2 
and A300 B4 series airplanes; and Model A300 B4-600, B4-600R, and F4-
600R series airplanes, and Model C4-605R Variant F airplanes 
(collectively called A300-600 series airplanes). The original NPRM was 
published in the Federal Register on January 26, 2006 (71 FR 4313). The 
original NPRM proposed to continue to require an inspection for cracks 
of the lower outboard flange of gantry No. 4 in the main landing gear 
(MLG) bay area, and repair if necessary. The original NPRM also 
proposed to continue to require repetitive inspections of the gantry 
lower flanges, and repair if necessary. In addition, the original NPRM 
proposed to require new repetitive inspections for cracks in the lower 
flange of certain gantries, and repair if necessary, which ends the 
existing inspection requirements. The original NPRM also proposed 
optional terminating actions for the new repetitive inspections.

Comments

    We have considered the following comment on the original NPRM.

Request To Revise the Applicability

    Airbus requests that airplanes on which Airbus Modifications 13037 
(Airbus Service Bulletins A300-53-0380 and A300-53-6153) and 12413 
(Airbus Service Bulletins A300-53-0360 and A300-53-6132), as 
applicable, have been installed in service, and airplanes on which 
Airbus Modification 12924 has been incorporated in production be 
excluded from Table 1--Applicability of the original NPRM. The 
commenter states that the effectivity of French airworthiness directive 
F-2005-091 R1, issued September 28, 2005, takes these modification into 
account, except for Airbus Modification 12924. The commenter states 
that the Direction G[eacute]n[eacute]rale de l'Aviation Civile (DGAC), 
which is the airworthiness authority for France, plans to revise French 
airworthiness directive F-2005-091 R1 to address Airbus Modification 
12924.
    We do not agree with Airbus to exclude airplanes on which a 
particular modification or service bulletin has been accomplished in 
service. Paragraph (m) of this supplemental NPRM includes an optional 
terminating action for accomplishing the actions specified in Airbus 
Service Bulletin A300-53-0380, dated August 5, 2005; Airbus Service 
Bulletin A300-53-0360, dated May 3, 2002; Airbus Service Bulleitn A300-
53-6132, dated February 5, 2002; or Airbus Service Bulletin A300-53-
6153, dated August 24, 2005; as applicable. If an operator chooses to 
accomplish this optional terminating action, it must continue to 
operate the airplane in that configuration unless an alternative method 
of compliance is approved. Therefore, we have determined that excluding 
those airplanes from the applicability of this supplemental NPRM is not 
appropriate. This difference between French airworthiness directive F-
2005-091 R1 and this supplemental NPRM has been coordinated with the 
DGAC.
    We also do not agree with the commenter to exclude airplanes on 
which Airbus Modification 12924 has been incorporated in production. We 
have confirmed with the DGAC that the omission of this modification in 
French airworthiness directive F-2005-091 R1 was an oversight. However, 
since the issuance of the original NPRM, we have determined that all 
combinations of the Airbus modifications specified in the effectivity 
of French airworthiness directive F-2005-091 R1 include an in-service 
service bulletin. Therefore, we have revised Table 1 of the 
applicability of this supplemental NPRM to not include any exceptions 
for

[[Page 28617]]

accomplishing those Airbus modifications.

Change to Labor Rate

    After the original NPRM was issued, we reviewed the figures we have 
used over the past several years to calculate AD costs to operators. To 
account for various inflationary costs in the airline industry, we find 
it necessary to increase the labor rate used in these calculations from 
$65 per work hour to $80 per work hour. The cost impact information, 
below, reflects this increase in the specified hourly labor rate.

FAA's Determination and Proposed Requirements of the Supplemental NPRM

    The change to the applicability discussed above expands the scope 
of the original NPRM; therefore, we have determined that it is 
necessary to reopen the comment period to provide additional 
opportunity for public comment on this supplemental NPRM.

Costs of Compliance

    This proposed AD would affect about 165 airplanes of U.S. registry. 
The following table provides the estimated costs for U.S. operators to 
comply with this proposed AD. Not all actions must be completed on all 
airplanes.

                                                          Estimated Costs for Required Actions
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                                                                                                                         Number of
                                                                  Average                                                  U.S.-
             Action                        Work hours           labor rate          Parts          Cost per airplane    registered        Fleet cost
                                                                 per hour                                                airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
One-time inspection (required by  1..........................           $80  None...............  $80................            23  $1,840.
 AD 2003-26-10).
One-time inspection (required by  4..........................            80  None...............  $320...............            43  $13,760.
 AD 2004-18-13).
Repetitive inspections (required  12.........................            80  None...............  $960, per                      78  $74,880, per
 by AD 2004-18-13).                                                                                inspection cycle.                  inspection cycle.
Repetitive inspections (new       16.........................            80  None...............  $1,280, per                    78  $99,840, per
 proposed actions).                                                                                inspection cycle.                  inspection cycle.
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                                      Estimated Costs for Optional Actions
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                                                                                                      Number of
                                                     Average                          Cost per          U.S.-
        Optional action            Work hours      labor rate         Parts           airplane       registered
                                                    per hour                                          airplanes
----------------------------------------------------------------------------------------------------------------
Reinforcement specified in      807.............           $80  Between $87,100   Between $151,660            23
 Airbus Service Bulletin A300-                                   and $121,560      and $186,120
 53-0380, dated August 5, 2005.                                  depending on      depending on
                                                                 kit purchased.    airplane
                                                                                   configuration.
Reinforcement specified in      807.............            80  Between $82,460   Between $147,020           120
 Airbus Service Bulletin A300-                                   and $87,070       and $151,630
 53-6153, dated August 24,                                       depending on      depending on
 2005.                                                           kit purchased.    airplane
                                                                                   configuration.
Reinforcement specified in      Between 24 and              80  Between $250 and  Between $2,170              23
 Airbus Service Bulletin A300-   128 depending                   $1,000            and $11,240
 53-0360, dated May 3, 2002.     on airplane                     depending on      depending on
                                 configuration.                  kit purchased.    airplane
                                                                                   configuration.
Reinforcement specified in      109.............            80  Between $260 and  Between $8,980             120
 Airbus Service Bulletin A300-                                   $950 depending    and $9,670
 53-6132, dated February 5,                                      on kit            depending on
 2002.                                                           purchased.        airplane
                                                                                   configuration.
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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;

[[Page 28618]]

    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 supplemental NPRM 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 amendments 39-13408 (69 FR 867, January 7, 2004) and 39-13792 
(69 FR 55329, September 14, 2004) and adding the following new 
airworthiness directive (AD):

Airbus: Docket No. FAA-2006-23690; Directorate Identifier 2004-NM-
133-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by June 12, 
2006.

Affected ADs

    (b) This AD supersedes ADs 2003-26-10 and 2004-18-13.

Applicability

    (c) This AD applies to Airbus airplanes identified in Table 1 of 
this AD, certificated in any category.

                         Table 1.--Applicability
------------------------------------------------------------------------
                        Affected Airbus airplanes
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(1) All Model A300 B2-1A, B2-1C, B2K-3C, and B2-203 airplanes
(2) All Model A300 B4-2C, B4-103, and B4-203 airplanes
(3) All Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes
(4) All Model A300 B4-605R and B4-622R airplanes
(5) All Model A300 F4-605R and F4-622R airplanes
(6) All Model A300 C4-605R Variant F airplanes
------------------------------------------------------------------------

Unsafe Condition

    (d) This AD results from a report of a large fatigue crack along 
the outboard flange of beam No. 4. We are issuing this AD to detect 
and correct fatigue cracks in the lower flanges of the left and 
right gantries 1 through 5 inclusive in the main landing gear (MLG) 
bay area, which could result in reduced structural integrity of the 
fuselage, and consequent rapid decompression of the airplane.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

Restatement of Requirements of AD 2003-26-10

One-Time Inspection

    (f) For airplanes on which Airbus Modification 10147 has not 
been done: At the later of the times specified in paragraphs (f)(1) 
and (f)(2) of this AD: Do a one-time detailed inspection for 
cracking of the lower outboard flange of gantry No. 4 in the MLG bay 
area per paragraph 4.2.1 of Airbus All Operators Telex (AOT) A300-
53A0371, Revision 01 (for Model A300 B2 and B4 series airplanes); or 
AOT A300-53A6145, Revision 01 (for Model A300-600 series airplanes); 
both dated September 10, 2003; as applicable.
    (1) Before the accumulation of 8,000 total flight cycles since 
the date of issuance of the original Airworthiness Certificate or 
the date of issuance of the Export Certificate of Airworthiness, 
whichever is first.
    (2) Within 30 days after January 22, 2004 (the effective date AD 
2003-26-10).

    Note 1: 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.''

Repair

    (g) Repair any cracking found during the inspection required by 
paragraph (f) of this AD before further flight, per a method 
approved by either the Manager, International Branch, ANM-116, 
Transport Airplane Directorate, FAA; or the Direction 
G[eacute]n[eacute]rale de l'Aviation Civile (DGAC) (or its delegated 
agent).

Restatement of Requirements of AD 2004-18-13

One-Time Inspection and Corrective Action

    (h) For Model A300 B2-1A, B2-1C, B2K-3C, and B2-203 airplanes, 
and Model A300 B4-2C, B4-103, and B4-203 airplanes, on which Airbus 
Modification 3474 has been done: Prior to the accumulation of 16,300 
total flight cycles, or within 500 flight cycles after July 30, 1998 
(the effective date of AD 98-13-37), whichever occurs later, perform 
a one-time ultrasonic inspection for cracking of the gantry lower 
flanges in the MLG bay area, in accordance with Airbus AOT 53-11, 
dated October 13, 1997.
    (1) If any cracking is detected, prior to further flight, repair 
in accordance with the AOT.
    (2) If no cracking is detected, no further action is required by 
this paragraph.

Repetitive Inspections and Corrective Actions

    (i) For Model A300 B4-601, B4-603, B4-605R, B4-620, B4-622R, C4-
605R Variant F airplanes, and F4-605R airplanes, on which Airbus 
Modification 12169 has not been done in production: Perform the 
requirements of paragraphs (i)(1), (i)(2), (i)(3), and (i)(4) of 
this AD, in accordance with Airbus Service Bulletin A300-53-6128, 
dated March 5, 2001.
    (1) At the later of the times specified in paragraphs (i)(1)(i) 
and (i)(1)(ii) of this AD, perform initial ultrasonic inspections or 
high frequency eddy current inspections (HFEC) for cracks of the 
lower flanges of gantries 3, 4, and 5 between fuselage frames FR47 
and FR54, in accordance with the Accomplishment Instructions, 
including the Synoptic Chart contained in Figure 2, sheets 1 through 
5 inclusive, of the service bulletin.
    (i) In accordance with the thresholds specified in the Synoptic 
Chart contained in Figure 2, sheets 1 through 5 inclusive, of the 
service bulletin; or
    (ii) Within 200 flight cycles after October 19, 2004 (the 
effective date AD 2004-18-13).
    (2) Perform repetitive ultrasonic inspections or high-frequency 
eddy current inspections for cracks of the lower flanges of gantries 
3, 4, and 5 between fuselage frames FR47 and FR54, in accordance 
with the thresholds and Accomplishment Instructions, including the 
Synoptic Chart contained in Figure 2, sheets 1 through 5 inclusive, 
of the service bulletin.
    (3) Perform repairs and reinforcements, in accordance with the 
thresholds and the Accomplishment Instructions, including the 
Synoptic Chart contained in Figure 2, sheets 1 through 5 inclusive, 
of the service bulletin, except as specified in paragraph (i)(4) of 
this AD.
    (4) If a new crack is found during any action required by 
paragraph (i)(1), (i)(2), or (i)(3) of this AD and the Synoptic 
Chart contained in Figure 2, sheets 1 through 5 inclusive, of the 
service bulletin specifies to contact Airbus for appropriate action: 
Prior to further flight, repair per a method approved by the 
Manager, International Branch, ANM-116, or the DGAC (or its 
delegated agent).

Credit for Inspections Accomplished in Accordance with AOT

    (j) Any inspection accomplished before October 19, 2004, in 
accordance with Airbus AOT 53-11, dated October 13, 1997, is 
acceptable for compliance with the corresponding inspection 
specified in paragraph (i)(1) of this AD, for that inspection area 
only. Operators must do the applicable inspections in paragraph 
(i)(1) of this AD for the remaining inspection areas.

[[Page 28619]]

New Requirements of This AD

Repetitive Inspections

    (k) At the later of the applicable times specified in the 
``Threshold (FC)'' and ``Grace Period'' columns of Tables 1 and 2 in 
paragraph 1.E of the applicable service bulletin specified in Table 
2 of this AD: Do an ultrasonic inspection or HFEC inspection, 
including rework of the pressure diaphragm, for cracks in the lower 
flanges of the left and right gantries 1 through 5 inclusive between 
FR47 and FR54, in accordance with the Accomplishment Instructions of 
the applicable service bulletin in Table 2 of this AD. Repeat the 
inspection at the applicable times specified in the ``Interval 
(FC)'' column of Tables 1 and 2 in paragraph 1.E of the applicable 
service bulletin in Table 2 of this AD. Accomplishment of the 
initial inspection ends the inspections required by paragraphs (f), 
(h), and (i) of this AD.

                       Table 2.--Service Bulletins
------------------------------------------------------------------------
       Airbus service bulletin--          For airplanes identified in--
------------------------------------------------------------------------
(1) A300-53-0379, Revision 01, dated     Paragraphs (c)(1) and (c)(2) of
 October 4, 2005.                         this AD.
(2) A300-53-6152, Revision 01, dated     Paragraphs (c)(3) through
 October 4, 2005.                         (c)(6) of this AD inclusive.
------------------------------------------------------------------------

Corrective Action

    (l) If any crack is detected during any ultrasonic or HFEC 
inspection required by paragraph (k) of this AD, before further 
flight, repair the crack in accordance with the Accomplishment 
Instructions of the applicable service bulletin in Table 2 of this 
AD, except as provided by paragraph (n) of this AD.

Optional Terminating Actions

    (m) Accomplishment of the actions specified in Table 3 of this 
AD ends the repetitive inspections required by paragraph (k) of this 
AD.

                                     Table 3.--Optional Terminating Actions
----------------------------------------------------------------------------------------------------------------
                                                                    By doing all the
                                                                 actions in accordance
  Before or at the same time with--          Reinforce--        with the Accomplishment       For airplanes
                                                                 Instructions of Airbus      identified in--
                                                                   Service Bulletin--
----------------------------------------------------------------------------------------------------------------
(1) The actions required by paragraph  The flanges of the left  A300-53-0380, dated      Paragraphs (c)(1) and
 (k) of this AD and the action          and right portals 1      August 5, 2005, except   (c)(2) of this AD.
 specified in paragraph (m)(2) of       through 5 inclusive      as provided by          .......................
 this AD.                               between FR47 and FR54    paragraph (n) of this   Paragraphs (c)(3)
                                        of the landing gear,     AD.                      through (c)(6) of this
                                        including a rotating    A300-53-6153, dated       AD inclusive.
                                        probe inspection for     August 24, 2005,
                                        cracks of holes and      except as provided by
                                        repair if necessary.     paragraph (n) of this
                                                                 AD.
(2) The actions required by paragraph  Portals 3, 4, and 5 of   A300-53-0360, dated May  Paragraphs (c)(1) and
 (k) of this AD.                        the plates/skin.         3, 2002, except as       (c)(2) of this AD
                                                                 provided by paragraph
                                                                 (n) of this AD.
                                        >                       A300-53-6132, dated      Paragraphs (c)(3)
                                                                 February 5, 2002,        through (c)(6) of this
                                                                 except as provided by    AD inclusive
                                                                 paragraph (n) of this
                                                                 AD.
----------------------------------------------------------------------------------------------------------------

Repair of Certain Cracks

    (n) Where the applicable service bulletin recommends contacting 
Airbus for appropriate action: Before further flight, repair the 
crack in accordance with a method approved by the Manager, 
International Branch, ANM-116; or the DGAC (or its delegated agent).

Credit for Original Service Bulletins

    (o) Accomplishing the inspections and repair before the 
effective date of this AD in accordance with Airbus Service Bulletin 
A300-53-0379, dated May 9, 2005, or Airbus Service Bulletin A300-53-
6152, dated May 9, 2005, as applicable, is acceptable for compliance 
with the corresponding requirements of paragraphs (k) and (l) of 
this AD.

No Inspection Report

    (p) Although the service bulletins in this AD specify to submit 
certain information to the manufacturer, this AD does not include 
that requirement.

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) 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 directive F-2005-091 R1, issued 
September 28, 2005, also addresses the subject of this AD.

    Issued in Renton, Washington, on May 8, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E6-7477 Filed 5-16-06; 8:45 am]
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