FR Doc 06-8224

[Federal Register: September 26, 2006 (Volume 71, Number 186)]
[Proposed Rules]
[Page 56058-56062]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr26se06-17]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-25890; Directorate Identifier 2006-NM-115-AD]
RIN 2120-AA64

Airworthiness Directives; Airbus Model A300 B2 and B4 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 A300 B2, B4-100, and
B4-200 series airplanes. The existing AD currently requires
supplemental structural inspections to detect fatigue cracking, and
repair of cracked structure. This proposed AD would require revising
the maintenance program by incorporating new and revised supplemental
structural inspections, inspection intervals, and repairs; and repair
of any damaged, cracked, or corroded structure; which would end the
existing supplement structural inspections. This proposed AD results
from a review of service history and reports received from the current
supplemental structural inspection document program. We are proposing
this AD to prevent reduced structural integrity of these airplanes due
to fatigue cracking.

DATES: We must receive comments on this proposed AD by October 26,
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

[[Page 56059]]

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.
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: 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-2006-25890; Directorate Identifier 2006-NM-115-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 June 17, 1996, we issued AD 96-13-11, amendment 39-9679 (61 FR
35122, July 5, 1996), for all Airbus Model A300 B2, B4-100, and B4-200
series airplanes. That AD requires supplemental structural inspections
to detect fatigue cracking, and repair of cracked structure. That AD
also requires revising the supplemental structural inspection document
(SSID) program by changing some of the inspection techniques, changing
some of the thresholds and intervals for inspections, expanding the
area to be inspected for some of the inspections, and revising the
Fleet Leader Program. That AD resulted from a review of service history
and reports received from existing SSID inspections. We issued that AD
to prevent reduced structural integrity of these airplanes due to
fatigue cracking.

Actions Since Existing AD Was Issued

Since we issued AD 96-13-11, the European Aviation Safety Agency
(EASA), which is the airworthiness authority for the European Union,
notified us that an unsafe condition may exist on all Airbus Model A300
B2 and B4 series airplanes. The EASA advises that, based on a review of
service history and reports received from the current SSID program,
further rulemaking is necessary in order to ensure the continued
structural integrity of these airplanes.

Relevant Service Information

Airbus has issued A300 Airworthiness Limitation Items (ALI)
Document SEM2/95A.1090/05, Issue 3, dated September 2005 (hereafter
referred to as ``Issue 3 of the ALI''). Issue 3 of the ALI defines
inspections and modifications necessary to ensure the structural
integrity applicable to the specified threshold (structural
modification point) arising from the evaluation of widespread fatigue
damage, and fatigue-related supplemental structural inspections for a
given applicability period from zero flight cycles/flight hours to the
limit of validity.
Airbus also has issued Temporary Revision (TR) 3.1, dated April
2006 (hereafter referred to as ``TR 3.1''), of Issue 3 of the ALI. TR
3.1 contains changes and additions to Issue 3 of the ALI. The
applicability, limit of validity, program rules, program notes, and
definitions remain valid as stated in Issue 3 of the ALI.
Accomplishing the actions specified in Issue 3 of the ALI as
revised by TR 3.1 ends the supplemental structural inspections required
by AD 96-13-11.
Accomplishing the actions specified in the service information is
intended to adequately address the unsafe condition. The EASA mandated
the service information and issued airworthiness directive 2006-0071,
dated March 30, 2006, to ensure the continued airworthiness of these
airplanes in the European Union.

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. As described in FAA
Order 8100.14A, ``Interim Procedures for Working with the European
Community on Airworthiness Certification and Continued Airworthiness,''
dated August 12, 2005, the EASA has kept the FAA informed of the
situation described above. We have examined the EASA's findings,
evaluated all pertinent information, and determined that we need to
issue an AD for products of this type design that are certificated for
operation in the United States.
This proposed AD would supersede AD 96-13-11 and would retain all
the requirements of the existing AD. This proposed AD would also
require revising the FAA-approved maintenance program by incorporating
new and revised supplemental structural inspections, inspection
intervals, and repairs; and repair of any damaged, cracked, or corroded
structure; which would end the existing supplement structural
inspections.

Differences Between the Proposed AD, EASA Airworthiness Directive,
Issue 3 of the ALI, and TR 3.1

The EASA airworthiness directive specifies a compliance time of
within 90 days from the effective date of the airworthiness directive
for doing the actions specified in Issue 3 of the ALI, which replaces
the actions specified in Airbus A300 SSID, Revision 4. However, this
proposed AD would require, within 12 months after the effective date of
this AD, revising the

[[Page 56060]]

FAA-approved maintenance program by incorporating the new and revised
actions specified in Issue 3 of the ALI as revised by TR 3.1. In
developing an appropriate compliance time for this action, we
considered the safety implications and normal maintenance schedules for
the timely accomplishment of the proposed revision. We also consider
the proposed revision to be more complex than that required by the EASA
airworthiness directive. AD 96-13-11 did not mandate incorporation of
Revision 3 or Revision 4 of the Airbus A300 SSID and thus U.S.
operators would be required to incorporate more changes than those
specified in the EASA airworthiness directive. In consideration of
these items, we have determined that a compliance time of 12 months
will ensure an acceptable level of safety and allow the revision to be
done during scheduled maintenance intervals for most affected
operators.
Unlike the procedures described in Issue 3 of the ALI as revised by
TR 3.1, this proposed AD would not permit further flight if any cracked
structure is detected. We have determined that, because of the safety
implications and consequences associated with that cracking, any
cracked structure must be repaired before further flight. This
difference has been coordinated with the EASA.
Issue 3 of the ALI as revised by TR 3.1 specifies to contact the
manufacturer for instructions on how to repair certain conditions, but
this proposed AD would require repairing those conditions using a
method that we or the EASA (or its delegated agent) approve. In light
of the type of repair that would be required to address the unsafe
condition, and consistent with existing bilateral airworthiness
agreements, we have determined that, for this proposed AD, a repair we
or the EASA approve would be acceptable for compliance with this
proposed AD.
Although Issue 3 of the ALI as revised by TR 3.1 specifies a
``Sampling Concept'' in section B, this proposed AD does not include
that requirement. Since issuance of AD 98-16-06, we have determined
that such a sampling does not provide an adequate statistical sampling
size to provide confidence in the structural integrity of the fleet of
airplanes. Therefore, the proposed AD would prohibit the use of such a
sampling program and would require all affected airplanes of the fleet
to be inspected.

Change to Existing AD

This proposed AD would retain all requirements of AD 96-13-11.
Since AD 96-13-11 was issued, the AD format has been revised, and
certain paragraphs have been rearranged. As a result, the corresponding
paragraph identifiers have changed in this proposed AD, as listed in
the following table:

Revised Paragraph Identifiers
------------------------------------------------------------------------
Corresponding requirement in
Requirement in AD 96-13-11 this proposed AD
------------------------------------------------------------------------
paragraph (a)............................. paragraph (f).
paragraph (b)............................. paragraph (g).
paragraph (c)............................. paragraph (h).
paragraph (d)............................. paragraph (i).
paragraph (e)............................. paragraph (j).
paragraph (f)............................. paragraph (k).
paragraph (g)............................. paragraph (l).
paragraph (h)............................. paragraph (m).
paragraph (i)............................. paragraph (n).
paragraph (j)............................. paragraph (o).
paragraph (k)............................. paragraph (p).
paragraph (l)............................. paragraph (q).
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Costs of Compliance

The following table provides the estimated costs for U.S. operators
to comply with this proposed AD.

Estimated Costs
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Number of
Work Average Cost per U.S.-
Action hours labor rate Parts airplane registered Fleet cost
per hour airplanes
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Implementation of SSID (required 597 $80 None......... $47,760 29 $1,385,040
by AD 96-13-11).
Revision of the FAA-approved 10 80 None......... 800 29 23,200
maintenance program (new proposed
action).
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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;
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:

[[Page 56061]]

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 39-9679 (61 FR 35122, July 5, 1996) and adding the
following new airworthiness directive (AD):

Airbus: Docket No. FAA-2006-25890; Directorate Identifier 2006-NM-
115-AD.

Comments Due Date

(a) The FAA must receive comments on this AD action by October
26, 2006.

Affected ADs

(b) This AD supersedes AD 96-13-11.

Applicability

Note 1: This AD requires revisions to certain operator
maintenance documents to include new inspections. Compliance with
these inspections is required by 14 CFR 91.403(c). For airplanes
that have been previously modified, altered, or repaired in the
areas addressed by these inspections, the operator may not be able
to accomplish the inspections described in the revisions. In this
situation, to comply with 14 CFR 91.403(c), the operator must
request approval for an alternative method of compliance according
to paragraph (x) of this AD. The request should include a
description of changes to the required inspections that will ensure
the continued damage tolerance of the affected structure. The FAA
has provided guidance for this determination in Advisory Circular
(AC) 25-1529.

Unsafe Condition

(d) This AD results from a review of service history and reports
received from the current supplemental structural inspection
document program. We are issuing this AD to prevent reduced
structural integrity of these airplanes due to fatigue cracking.

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 96-13-11:
(f) Within one year after March 9, 1993 (the effective date of
AD 93-01-24, amendment 39-8478), incorporate a revision into the
FAA-approved maintenance inspection program that provides for
supplemental maintenance inspections, modifications, repair, or
replacement of the significant structural details (SSD) and
significant structural items (SSI) specified in ``Airbus Industrie
A300 Supplemental Structural Inspection Document'' (SSID), dated
September 1989 (hereafter referred to as ``the SSID'').
(g) Within one year after August 9, 1996 (the effective date of
AD 96-13-11), replace the revision of the FAA-approved maintenance
program required by paragraph (f) of this AD with the inspections,
inspection intervals, repairs, and replacements defined in ``Airbus
Industrie A300 Supplemental Structural Inspection Document'' (SSID),
Revision 2, dated June 1994 (hereafter referred to as ``Revision 2
of the SSID''). Accomplish the actions specified in the service
bulletins identified in Section 6, ``SB Reference List,'' Revision 2
of the SSID, at the times specified in those service bulletins. The
actions are to be accomplished in accordance with those service
bulletins.
(1) For airplanes that have exceeded the threshold specified in
any of the service bulletins identified in Section 6, ``SB Reference
List,'' Revision 2 of the SSID: Accomplish the actions specified in
those service bulletins within the grace period specified in that
service bulletin. The grace period is to be measured from August 9,
1996.
(2) For airplanes that have exceeded the threshold specified in
any of the service bulletins identified in Section 6, ``SB Reference
List,'' Revision 2 of the SSID, and a grace period is not specified
in that service bulletin: Accomplish the actions specified in that
service bulletin within 1,500 flight cycles after August 9, 1996.
(h) If any cracked structure is detected during the inspections
required by either paragraph (f) or (g) of this AD, prior to further
flight, permanently repair the cracked structure in accordance with
either paragraph (h)(1), (h)(2), or (h)(3) of this AD.

Note 2: A permanent repair is defined as a repair that meets the
certification basis of the airplane, and does not require additional
modification at a later date.

(1) The service bulletins listed in Section 6, ``SB Reference
List,'' of the SSID (for airplanes that are currently being
inspected in accordance with paragraph (f) of this AD); or in
accordance with a method approved by the Manager, International
Branch, ANM-116 (formerly the Standardization Branch, ANM-113), FAA,
Transport Airplane Directorate, if a permanent repair is not
specified in any of these service bulletins. Or
(2) The service bulletins listed in Section 6, ``SB Reference
List,'' of Revision 2 of the SSID (for airplanes that are currently
being inspected in accordance with paragraph (g) of this AD); or in
accordance with a method approved by the Manager, International
Branch, ANM-116 (formerly the Standardization Branch, ANM-113), if a
permanent repair is not specified in any of these service bulletins.
Or
(3) Other permanent repair data meeting the certification basis
of the airplane which is approved by the Manager, International
Branch, ANM-116 (formerly the Standardization Branch, ANM-113), or
by the Direction Ge[aacute]ne[aacute]rale de l'Aviation Civile
(DGAC) of France.
(i) For airplanes identified as Fleet Leader Program (FLP) in
Section 5, ``Fleet Leader Program,'' of the SSID or Revision 2 of
the SSID: Inspect according to the instructions and intervals
specified in paragraph 4.4, ``Adjustment of Inspection Requirements
and DSG,'' of Section 4, or Section 9, as applicable, of the SSID
(for airplanes inspected in accordance with paragraph (f) of this
AD), or Revision 2 of the SSID (for airplanes inspected in
accordance with paragraph (g) of this AD), for each SSD.
(j) For the purpose of accomplishing paragraphs (i), (k), (l),
and (n) of this AD, operators shall not use paragraph 6.2,
``Complete RR Method,'' of Section 9 of the SSID to calculate
inspection thresholds and intervals.
(k) For Model A300-B2 and B2K-3C series airplanes: For any SSD
that has exceeded the values of the threshold specified in paragraph
6, ``Inspection Threshold and Intervals,'' Section 9 of the SSID,
inspect at the time specified in either paragraph (k)(1) or (k)(2)
of this AD, as applicable.
(1) For airplanes inspected in accordance with paragraph (f) of
this AD: Inspect within 2,000 landings after March 9, 1993, in
accordance with the SSID. Or
(2) For airplanes inspected in accordance with paragraph (g) of
this AD: Inspect within 2,000 landings after August 9, 1996, in
accordance with Revision 2 of the SSID.
(l) For Model A300-B4 series airplanes: For any SSD that has
exceeded the values of the threshold specified in paragraph 6,
``Inspection Threshold and Intervals,'' Section 9 of the SSID,
inspect at the time specified in either paragraph (l)(1) or (l)(2)
of this AD, as applicable.
(1) For airplanes inspected in accordance with paragraph (f) of
this AD: Inspect within 1,500 landings after March 9, 1993 [the
effective date of AD 93-01-24, amendment 39-8478]. Or
(2) For airplanes inspected in accordance with paragraph (g) of
this AD: Inspect within 1,500 landings after August 9, 1996.
(m) For airplanes identified as FLP in Section 5, ``Fleet Leader
Program,'' of the SSID or Revision 2 of the SSID: Within one year
after August 9, 1996, apply the basic requirements given in Revision
2 of the SSID.
(n) For airplanes that are subject to the requirements of
paragraph (g) of this AD, and have exceeded the initial inspection
threshold specified in paragraph 4.4, ``Adjustment of Inspection
Requirements and DSG,'' of Section 4, or paragraph 6, ``Inspection
Threshold and Intervals,'' of Section 9, for each SSD: Perform the
initial inspection prior to the accumulation of the number of flight
cycles specified in paragraph 7, ``Additional Information,'' Section
9, of Revision 2 of the SSID.
Note 3: Fatigue ratings are not applicable to these allowances;
therefore, no adjustment is required.
Note 4: Paragraph (n) of this AD provides the ``grace'' periods
for those airplanes that are new to the FLP or that have newly added
or revised SSID requirements in accordance with paragraph (g) of
this AD.
(o) The grace period provided by paragraph (n) of this AD is
also applicable to the thresholds and/or repeat intervals for each
SSD for which the inspection interval or threshold was reduced in
accordance with the requirements of paragraph (g) of this AD.
(p) For FLP airplanes identified in Section 5, ``Fleet Leader
Program,'' of the SSID or Revision 2 of the SSID that are listed in
Section 7, ``SSI Limitation List,'' of the SSID (for airplanes that
are currently being inspected in accordance with paragraph (f) of
this AD) , or Revision 2 of the SSID (for airplanes that are
currently being inspected in accordance with paragraph (g) of this
AD):

[[Page 56062]]

Inspect at intervals not to exceed the interval specified for each
SSI, in accordance with the values given in Section 7, ``SSI
Limitation List,'' of the SSID or Revision 2 of the SSID, as
applicable.
(q) For all airplanes: All inspection results, positive or
negative, must be reported to Airbus in accordance with either
paragraph (q)(1) or (q)(2) of this AD, as applicable. Information
collection requirements contained in this regulation have been
approved by the Office of Management and Budget (OMB) under the
provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et
seq.) and have been assigned OMB Control Number 2120-0056.
(1) For FLP airplanes, identified in Section 5, ``Fleet Leader
Program,'' of the SSID or Revision 2 of the SSID: Submit reports in
accordance with the instructions in paragraph 5.2, ``SSIP Inspection
Reporting,'' of Section 5, and paragraph 7.1, ``General,'' of
Section 7 of the SSID (for airplanes that are currently being
inspected in accordance with paragraph (f) of this AD); or Revision
2 of the SSID (for airplanes inspected in accordance with paragraph
(g) of this AD).
(2) For all airplanes that are subject to Section 6, ``SB
Reference List,'' of the SSID: Submit reports in accordance with the
instructions in the applicable service bulletins identified in
Section 6 of the SSID (for airplanes that are currently being
inspected in accordance with paragraph (f) of this AD); or Revision
2 of the SSID (for airplanes that are currently being inspected in
accordance with paragraph (g) of this AD).

New Requirements of This AD

Revision of the FAA-Approved Maintenance Inspection Program

(r) Within 12 months after the effective date of this AD,
replace the revision of the FAA-approved maintenance program
required by paragraph (g) of this AD with the supplemental
structural inspections, inspection intervals, and repairs defined in
Airbus A300 Airworthiness Limitation Items (ALI) Document SEM2/
95A.1090/05, Issue 3, dated September 2005, as revised by Airbus
Temporary Revision (TR) 3.1, dated April 2006 (hereafter referred to
as ``Issue 3 of the ALI''). Accomplish the actions specified in
Issue 3 of the ALI at the times specified in that ALI, except as
provided by paragraph (s) of this AD. The actions must be
accomplished in accordance with Issue 3 of the ALI. Accomplishing
the applicable initial ALI tasks constitutes terminating action for
the requirements of paragraphs (f) through (q) of this AD.
(s) For airplanes that have exceeded the threshold or intervals
specified in Issue 3 of the ALI for the application tolerance on the
first interval for new and revised requirements and have exceeded 50
percent of the intervals specified in sections D and E of Issue 3 of
the ALI: Do the actions within 6 months after the effective date of
this AD.

Corrective Actions

(t) Damaged, cracked, or corroded structure detected during any
inspection done in accordance with Issue 3 of the ALI must be
repaired, before further flight, in accordance with Issue 3 of the
ALI, except as provided by paragraph (u) of this AD; or other data
meeting the certification basis of the airplane which is approved by
the Manager, International Branch, ANM-116; or by the European
Aviation Safety Agency (EASA) (or its delegated agent).
(u) Where Issue 3 of the ALI specifies contacting Airbus for
appropriate action: Before further flight, repair the damaged,
cracked, or corroded structure using a method approved by either the
Manager, International Branch, ANM-116; or the EASA (or its
delegated agent).

No Fleet Sampling

(v) Although Issue 3 of the ALI specifies to do a ``Sampling
Concept'' in section B, this AD prohibits the use of such a sampling
program and requires all affected airplanes of the fleet to be
inspected.

No Reporting

(w) Although Issue 3 of the ALI specifies to submit certain
information to the manufacturer, this AD does not include that
requirement.

Alternative Methods of Compliance (AMOCs)

(x)(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.
(3) AMOCs approved previously in accordance with AD 96-13-11 are
approved as AMOCs for the corresponding provisions of paragraphs (f)
through (q) of this AD.

Related Information

(y) The EASA airworthiness directive 2006-0071, dated March 30,
2006, also addresses the subject of this AD.

Issued in Renton, Washington, on September 14, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 06-8224 Filed 9-25-06; 8:45 am]

BILLING CODE 4910-13-P