[Federal Register Volume 71, Number 206 (Wednesday, October 25, 2006)]
[Rules and Regulations]
[Pages 62380-62384]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 06-8731]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-21779; Directorate Identifier 2002-NM-349-AD; 
Amendment 39-14790; AD 2006-21-06]
RIN 2120-AA64


Airworthiness Directives; McDonnell Douglas Model DC-9-10 Series 
Airplanes; DC-9-20 Series Airplanes; DC-9-30 Series Airplanes; DC-9-40 
Series Airplanes; and DC-9-50 Series Airplanes

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

ACTION: Final rule.

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SUMMARY: The FAA is superseding an existing airworthiness directive 
(AD), which applies to certain McDonnell Douglas transport category 
airplanes. That AD currently requires, among other things, revision of 
an existing program of structural inspections. This new AD requires 
implementation of a program of structural inspections of baseline 
structure to detect and correct fatigue cracking in order to ensure the 
continued airworthiness of these airplanes as they approach the 
manufacturer's original fatigue design life goal. This AD results from 
a significant number of these airplanes approaching or exceeding the 
design service goal on which the initial type certification approval 
was predicated. We are issuing this AD to detect and correct fatigue 
cracking that could compromise the structural integrity of these 
airplanes.

DATES: This AD becomes effective November 29, 2006.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the AD as of November 29, 
2006.
    The incorporation of a certain other publication, as listed in the 
regulations, was approved previously by the Director of the Federal 
Register as of July 24, 1996 (61 FR 31009, June 19, 1996).

ADDRESSES: You may examine the AD docket on the Internet at http://dms.dot.gov or in person at the Docket Management Facility, U.S. 
Department of Transportation, 400 Seventh Street, SW., Nassif Building, 
Room PL-401, Washington, DC.
    Contact Boeing Commercial Airplanes, Long Beach Division, 3855 
Lakewood Boulevard, Long Beach, California 90846, Attention: Data and 
Service Management, Dept. C1-L5A (D800-0024), for service information 
identified in this AD.

FOR FURTHER INFORMATION CONTACT: Wahib Mina, Aerospace Engineer, 
Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification 
Office, 3960 Paramount Boulevard, Lakewood, California 90712-4137; 
telephone (562) 627-5324; fax (562) 627-5210.

SUPPLEMENTARY INFORMATION: 

Examining the Docket

    You may examine the airworthiness directive (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 street address stated in the ADDRESSES section.

Discussion

    The FAA issued a notice of supplemental notice of proposed 
rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that 
supersedes AD 96-13-03, amendment 39-9671 (61 FR 31009, June 19, 1996). 
The existing AD applies to all McDonnell Douglas Model DC-9-10, -20, -
30, -40, -50, and C-9 (military) series airplanes. (Since the issuance 
of that AD, the FAA has revised the applicability of the existing AD to 
identify model designations as published in the most recent type 
certificate data sheet for the affected models.) That supplemental NPRM 
was published in the Federal Register on March 7, 2006 (71 FR 11328). 
That supplemental NPRM proposed to require implementation of a program 
of structural inspections of baseline structure to detect and correct 
fatigue cracking in order to ensure the continued airworthiness of 
these airplanes as they approach the manufacturer's original fatigue 
design life goal.

[[Page 62381]]

Comments

    We provided the public the opportunity to participate in the 
development of this AD. No comments have been received on the 
supplemental NPRM or on the determination of the cost to the public.

Conclusion

    We have carefully reviewed the available data and determined that 
air safety and the public interest require adopting the AD as proposed.

Costs of Compliance

    There are about 710 McDonnell Douglas transport category airplanes 
worldwide of the affected design. This AD will affect about 477 
airplanes of U.S. registry, or 26 U.S. airline operators.
    The recurring inspection costs, as required by AD 96-13-03, take 
362 work hours per airplane, at an average labor rate of $65 per work 
hour. Based on these figures, the estimated cost of the currently 
required actions is $11,223,810, or $23,530 per airplane, per 
inspection cycle.
    The incorporation of the revised procedures in this AD action will 
require approximately 20 additional work hours per operator to 
accomplish, at an average labor rate of $65 per work hour. Based on 
these figures, the cost to the 26 affected U.S. operators to 
incorporate these revised procedures into the SID program is estimated 
to be $33,800, or $1,300 per operator.
    Additionally, the number of required work hours for each inspection 
(and the Supplemental Inspection Document (SID) program), as indicated 
above, is presented as if the accomplishment of those actions were to 
be conducted as ``stand alone'' actions. However, in actual practice, 
these actions for the most part will be accomplished coincidently or in 
combination with normally scheduled airplane inspections and other 
maintenance program tasks. Further, any costs associated with special 
airplane scheduling are expected to be minimal.

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 AD will not have federalism 
implications under Executive Order 13132. This AD will 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 this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866;
    (2) Is not a ``significant rule'' under 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 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, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
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]

0
2. The Federal Aviation Administration (FAA) amends Sec.  39.13 by 
removing amendment 39-9671 (61 FR 31009, June 19, 1996) and by adding 
the following new airworthiness directive (AD):

2006-21-06 McDonnell Douglas: Amendment 39-14790. Docket No. FAA-
2005-21779; Directorate Identifier 2002-NM-349-AD.

Effective Date

    (a) This AD becomes effective November 29, 2006.

Affected ADs

    (b) This AD supersedes AD 96-13-03.

Applicability

    (c) This AD applies to all McDonnell Douglas Model DC-9-11, DC-
9-12, DC-9-13, DC-9-14, DC-9-15, and DC-9-15F airplanes; DC-9-21 
airplanes; DC-9-31, DC-9-32, DC-9-32 (VC-9C), DC-9-32F, DC-9-33F, 
DC-9-34, DC-9-34F, and DC-9-32F (C-9A, C-9B) airplanes; DC-9-41 
airplanes; and DC-9-51 airplanes; certificated in any category.

Unsafe Condition

    (d) This AD was prompted by a significant number of these 
airplanes approaching or exceeding the design service goal on which 
the initial type certification approval was predicated. We are 
issuing this AD to detect and correct fatigue cracking that could 
compromise the structural integrity of these airplanes.

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 96-13-03

Revision of the FAA-Approved Maintenance Inspection Program

    (f) Within 6 months after July 24, 1996 (the effective date of 
AD 96-13-03), replace the FAA-approved maintenance inspection 
program with a revision that provides for inspection(s) of the 
principal structural elements (PSEs) defined in McDonnell Douglas 
Report No. L26-008, ``DC-9 Supplemental Inspection Document (SID),'' 
Section 2 of Volume I of McDonnell Douglas Report No. L26-008, ``DC-
9 Supplemental Inspection Document (SID),'' Revision 4, dated July 
1993, in accordance with Section 2 of Volume III-95, dated September 
1995, of the SID.


    Note 1: Operators should note that certain visual inspections of 
fleet leader operator sampling PSE's that were previously specified 
in earlier revisions of Volume III of the SID are no longer 
specified in Volume III-95 of the SID.

    (1) Prior to reaching the threshold (N<INF>th</INF>), but no 
earlier than one-half of the threshold (\1/2\N<INF>th</INF>), 
specified for all PSE's listed in Volume III-95, dated September 
1995, of the SID, inspect each PSE sample in accordance with the 
non-destructive inspection (NDI) procedures set forth in Section 2 
of Volume II, Revision 4, dated July 1993. Thereafter, repeat the 
inspection for that PSE at intervals not to exceed [Delta]NDI/2 of 
the NDI procedure that is specified in Volume III-95, dated 
September 1995, of the SID, until the requirements of paragraph (i) 
of this AD are accomplished.
    (2) The NDI techniques set forth in Section 2 of Volume II, 
Revision 4, dated July 1993, of the SID provide acceptable methods 
for accomplishing the inspections required by this paragraph.

[[Page 62382]]

    (3) All inspection results (negative or positive) must be 
reported to Boeing, in accordance with the instructions contained in 
Section 2 of Volume III-95, dated September 1995, of the SID. 
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.

    Note 2: Volume II of the SID, dated July 1993, is comprised of 
the following:


                                 Table 1
------------------------------------------------------------------------
                                                         Revision level
                  Volume designation                    shown on  volume
------------------------------------------------------------------------
Volume II--10/20......................................                 4
Volume II--20/30......................................                 5
Volume II--40.........................................                 4
Volume II--50.........................................                 4
------------------------------------------------------------------------


    Note 3: NDI inspections accomplished in accordance with the 
following Volume II of the SID provide acceptable methods for 
accomplishing the inspections required by this paragraph:


                                 Table 2
------------------------------------------------------------------------
     Volume designation          Revision level       Date of revision
------------------------------------------------------------------------
Volume II--10/20............  4...................  July 1993.
Volume II--10-20............  3...................  April 1991.
Volume II--10/20............  2...................  April 1990.
Volume II--10/20............  1...................  June 1989.
Volume II--20...............  Original............  November 1987.
Volume II--20/30............  5...................  July 1993.
Volume II--20/30............  4...................  April 1991.
Volume II--20/30............  3...................  April 1990.
Volume II--20/30............  2...................  June 1989.
Volume II--20/30............  1...................  November 1987.
Volume II--40...............  4...................  July 1993.
Volume II--40...............  3...................  April 1991.
Volume II--40...............  2...................  April 1990.
Volume II--40...............  1...................  June 1989.
Volume II--40...............  Original............  November 1987.
Volume II--50...............  4...................  July 1993.
Volume II--50...............  3...................  April 1991.
Volume II--50...............  2...................  April 1990.
Volume II--50...............  1...................  June 1989.
Volume II--50...............  Original............  November 1987.
------------------------------------------------------------------------

    (g) Any cracked structure detected during the inspections 
required by paragraph (f) of this AD must be repaired before further 
flight, in accordance with a method approved by the Manager, Los 
Angeles Aircraft Certification Office (ACO), Transport Airplane 
Directorate, FAA.

    Note 4: Requests for approval of any PSE repair that would 
affect the FAA-approved maintenance inspection program that is 
required by this AD should include a damage tolerance assessment for 
that PSE.

New Requirements of This AD

Revision of the Maintenance Inspection Program

    (h) Within 12 months after the effective date of this AD, 
incorporate a revision into the FAA-approved maintenance inspection 
program that provides for inspection(s) of the PSEs, in accordance 
with Boeing Report L26-008, ``DC-9 All Series, Supplemental 
Inspection Document (SID),'' Volume I, Revision 6, dated November 
2002. Unless otherwise specified, all further references in this AD 
to the ``SID'' are to Revision 6, dated November 2002.

Non-Destructive Inspections (NDIs)

    (i) For all PSEs listed in Section 2 of Volume I of the SID, 
perform an NDI for fatigue cracking of each PSE in accordance with 
the NDI procedures specified in Section 2 of Volume II, Revision 6, 
dated November 2004, of the SID, at the times specified in paragraph 
(i)(1), (i)(2), or (i)(3) of this AD, as applicable.
    (1) For airplanes that have less than three-quarters of the 
fatigue life threshold (\3/4\N<INF>th</INF>) as of the effective 
date of the AD: Perform an NDI for fatigue cracking no earlier than 
one-half of the threshold (\1/2\N<INF>th</INF>) but prior to 
reaching three-quarters of the threshold (\3/4\N<INF>th</INF>), or 
within 60 months after the effective date of this AD, whichever 
occurs later. Inspect again prior to reaching the threshold 
(N<INF>th</INF>) or [Delta]NDI/2, whichever occurs later, but no 
earlier than (\3/4\N<INF>th</INF>). Thereafter, after passing the 
threshold (N<INF>th</INF>), repeat the inspection for that PSE at 
intervals not to exceed [Delta]NDI/2.
    (2) For airplanes that have reached or exceeded three-quarters 
of the fatigue life threshold (\3/4\N<INF>th</INF>), but less than 
the threshold (N<INF>th</INF>), as of the effective date of the AD: 
Perform an NDI prior to reaching the threshold (N<INF>th</INF>), or 
within 18 months after the effective date of this AD, whichever 
occurs later. Thereafter, after passing the threshold 
(N<INF>th</INF>), repeat the inspection for that PSE at intervals 
not to exceed [Delta]NDI/2.
    (3) For airplanes that have reached or exceeded the fatigue life 
threshold (N<INF>th</INF>) as of the effective date of the AD: 
Perform an NDI within 18 months after the effective date of this AD. 
Thereafter, repeat the inspection for that PSE at intervals not to 
exceed [Delta]NDI/2.

    Note 5: Volume II of the SID, dated November 2004, comprises the 
following:


                                 Table 3
------------------------------------------------------------------------
                                                         Revision level
                  Volume designation                    shown on  volume
------------------------------------------------------------------------
Volume II--10/20......................................                 6
Volume II--20/30......................................                 7
Volume II--40.........................................                 6
Volume II--50.........................................                 6
------------------------------------------------------------------------

Discrepant Findings

    (j) If any discrepancy (e.g., a PSE cannot be inspected as 
specified in Volume II of the SID or does not match rework, repair, 
or modification description in Volume I of the SID) is detected 
during any inspection required by paragraph (i) of this AD, 
accomplish the action specified in paragraph (j)(1) or (j)(2) of 
this AD, as applicable.
    (1) If a discrepancy is detected during any inspection performed 
prior to \3/4\N<INF>th</INF> or N<INF>th</INF>: The area of the PSE 
affected by the discrepancy must be inspected prior to 
N<INF>th</INF> or within 18 months of the discovery of the 
discrepancy, whichever is later, in accordance with a method 
approved by the Manager, Los Angeles ACO, FAA.
    (2) If a discrepancy is detected during any inspection performed 
after N<INF>th</INF>: The area of the PSE affected by the 
discrepancy must be inspected prior to the accumulation of an 
additional [Delta]NDI/2, measured from the last non-discrepant 
inspection finding, or within 18 months of the discovery of the

[[Page 62383]]

discrepancy, whichever occurs later, in accordance with a method 
approved by the Manager of the Los Angeles ACO.

Reporting Requirements

    (k) All negative, positive, or discrepant (discrepant finding 
examples are described in paragraph (j) of this AD) findings of the 
inspections accomplished under paragraph (i) of this AD must be 
reported to Boeing, at the times specified in, and in accordance 
with the instructions contained in, Section 4 of Volume I, Revision 
6, of the SID. 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 (44 U.S.C. 
3501 et seq.) and have been assigned OMB Control Number 2120-0056.

Corrective Actions

    (l) Any cracked structure of a PSE detected during any 
inspection required by paragraph (i) of this AD must be repaired 
before further flight in accordance with a method approved by the 
Manager, Los Angles ACO, or by using a method approved in accordance 
with procedures specified in paragraph (p) of this AD. Accomplish 
follow-on actions described in paragraphs (l)(1), (l)(2), and (l)(3) 
of this AD, at the times specified.
    (1) Within 18 months after repair, perform a damage tolerance 
assessment (DTA) that defines the threshold for inspection of the 
repair and submit the assessment for approval.
    (2) Before reaching 75% of the repair threshold as determined in 
paragraph (l)(1) of this AD, submit the inspection methods and 
repetitive inspection intervals for the repair for approval.
    (3) Before the repair threshold, as determined in paragraph 
(l)(1) of this AD, incorporate the inspection method and repetitive 
inspection intervals into the FAA-approved structural maintenance or 
inspection program for the airplane.

    Note 6: For the purposes of this AD, we anticipate that 
submissions of the DTA of the repair, if acceptable, should be 
approved within six months after submission.


    Note 7: Advisory Circular AC 25.1529-1, ``Instructions for 
Continued Airworthiness of Structural Repairs on Transport 
Airplanes,'' dated August 1, 1991, is considered to be additional 
guidance concerning the approval of repairs to PSEs.

Inspection for Transferred Airplanes

    (m) Before any airplane that has exceeded the fatigue life 
threshold (N<INF>th</INF>) can be added to an air carrier's 
operations specifications, a program for the accomplishment of the 
inspections required by this AD must be established per paragraph 
(m)(1) or (m)(2) of this AD, as applicable.
    (1) For airplanes that have been inspected in accordance with 
this AD, the inspection of each PSE must be accomplished by the new 
operator in accordance with the previous operator's schedule and 
inspection method, or the new operator's schedule and inspection 
method, at whichever time would result in the earlier accomplishment 
date for that PSE inspection. The compliance time for accomplishment 
of this inspection must be measured from the last inspection 
accomplished by the previous operator. After each inspection has 
been performed once, each subsequent inspection must be performed in 
accordance with the new operator's schedule and inspection method.
    (2) For airplanes that have not been inspected in accordance 
with this AD, the inspection of each PSE required by this AD must be 
accomplished either prior to adding the airplane to the air 
carrier's operations specification, or in accordance with a schedule 
and an inspection method approved by the Manager, Los Angeles ACO. 
After each inspection has been performed once, each subsequent 
inspection must be performed per the new operator's schedule.

Inspections Accomplished Before the Effective Date of This AD

    (n) Inspections accomplished prior to the effective date of this 
AD in accordance with Boeing Report No. L26-008, ``DC-9 All Series 
Supplemental Inspection Document (SID),'' Volume I, Revision 6, 
dated November 2002, are acceptable for compliance with the 
requirements of paragraph (i) of this AD.

Acceptable for Compliance

    (o) Boeing Report MDC 91K0263, ``DC-9/MD-80 Aging Aircraft 
Repair Assessment Program Document,'' Revision 1, dated October 
2000, provides inspection/replacement programs for certain repairs 
to the fuselage pressure shell. These repairs and inspection/
replacement programs are considered acceptable for compliance with 
the requirements of paragraphs (i), (l), and (m) of this AD for 
repairs subject to that document.

Alternative Methods of Compliance (AMOCs)

    (p)(1) The Manager, Los Angles ACO, 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 CFR 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) An AMOC that provides an acceptable level of safety may be 
used for any repair required by this AD, if it is approved by an 
Authorized Representative for the Boeing Commercial Airplanes 
Delegation Option Authorization Organization who has been authorized 
by the Manager, Los Angeles ACO, to make those findings. For a 
repair method to be approved, the repair must meet the certification 
basis of the airplane and 14 CFR 25.571, Amendment 45, and the 
approval must specifically refer to this AD.
    (4) AMOCs approved previously for alternative inspection 
procedures per AD 87-14-07 R1, amendment 39-6019; AD 94-03-01, 
amendment 39-8807; and AD 96-13-03; are acceptable for compliance 
with the actions required by paragraph (f) of this AD for 
inspections performed before the requirements of paragraph (i) are 
accomplished.
    (5) AMOCs approved previously for repairs per AD 87-14-07 R1, AD 
94-03-01, and AD 96-13-03; are acceptable for compliance with the 
requirements of paragraph (l) of this AD.

Material Incorporated by Reference

    (q) You must use McDonnell Douglas Report No. L26-008, ``DC-9 
Supplemental Inspection Document (SID),'' Volume III-95, dated 
September 1995; and the volumes of Boeing Report L26-008, ``DC-9 All 
Series, Supplemental Inspection Document (SID),'' specified in Table 
4 of this AD; as applicable, to perform the actions that are 
required by this AD, unless the AD specifies otherwise.

                               Table 4.--Supplemental Inspection Document Volumes
----------------------------------------------------------------------------------------------------------------
                                                                        Revision
                Volume                        Effective pages            level                  Date
----------------------------------------------------------------------------------------------------------------
Volume I--All Series.................  List of Effective Pages:                 4  July 1993.
                                        Pages A-C.
Volume I--All Series.................  List of Effective Pages:                 6  November 2002.
                                        Pages A-D.
Volume II--10/20.....................  List of Effective Pages:                 4  July 1993.
                                        Pages A-K.
Volume II--10/20.....................  List of Effective Pages:                 6  November 2004.
                                        Pages A-M.
Volume II--20/30.....................  List of Effective Pages:                 5  July 1993.
                                        Pages A-T.
Volume II--20/30.....................  List of Effective Pages:                 7  November 2004.
                                        Pages A-X.
Volume II--40........................  List of Effective Pages:                 4  July 1993.
                                        Pages A-M.
Volume II--40........................  List of Effective Pages:                 6  November 2004.
                                        Pages A-O.
Volume II--50........................  List of Effective Pages:                 4  July 1993.
                                        Pages A-M.
Volume II--50........................  List of Effective Pages:                 6  November 2004.
                                        Pages A-O.
----------------------------------------------------------------------------------------------------------------


[[Page 62384]]

    (Where there are differences between the revision dates listed 
in the List of Effective Pages and the revision dates shown on the 
actual pages of these documents, the revision dates on the actual 
pages are correct, except for the following: Volume I-All Series, 
dated July 1993: The revision dates in the List of Effective Pages 
are correct for the Record of Revisions, page 13 of the 
Introduction, and page B of Section 2.)
    (1) The incorporation by reference of the volumes of Boeing 
Report L26-008, ``DC-9 All Series, Supplemental Inspection Document 
(SID),'' specified in Table 4 of this AD, is approved by the 
Director of the Federal Register in accordance with 5 U.S.C. 552(a) 
and CFR part 51.
    (2) The incorporation by reference of McDonnell Douglas Report 
No. L26-008, ``DC-9 Supplemental Inspection Document (SID),'' Volume 
III-95, dated September 1995, was approved previously by the 
Director of the Federal Register on July 24, 1996 (61 FR 31009, June 
19, 1996).
    (3) Contact Boeing Commercial Airplanes, Long Beach Division, 
3855 Lakewood Boulevard, Long Beach, California 90846, Attention: 
Data and Service Management, Dept. C1-L5A (D800-0024), for a copy of 
this service information. You may review copies at the Docket 
Management Facility, U.S. Department of Transportation, 400 Seventh 
Street, SW., Room PL-401, Nassif Building, Washington, DC; on the 
Internet at http://dms.dot.gov; or at the National Archives and 
Records Administration (NARA). For information on the availability 
of this material at the NARA, call (202) 741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Issued in Renton, Washington, on October 6, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 06-8731 Filed 10-24-06; 8:45 am]
BILLING CODE 4910-13-P