Airworthiness Directives; McDonnell Douglas Model MD-11 and -11F Airplanes, 1143-1146 [E6-22536]
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Federal Register / Vol. 72, No. 6 / Wednesday, January 10, 2007 / Rules and Regulations
For the reasons discussed above, I
certify this AD:
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 AD and placed it in the AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
I
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
I
2007–01–04 Turbomeca: Amendment 39–
14875. Docket No. FAA–2006–26128;
Directorate Identifier 2006–NE–34–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective January 25, 2007.
Affected ADs
(b) None.
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Applicability
(c) This AD applies to Artouste III B and
III B1 turboshaft engines fitted with a fuel
pipe, part number 0 202 12 800 0. These
engines are installed on SA 315 B LAMA and
SA 316 B Alouette III helicopters.
Reason
(d) European Aviation Safety Agency,
(EASA), Airworthiness Directive No. 2006–
0154, dated June 1, 2006, states:
3 cases of cracking due to exfoliation
corrosion on the unions of fuel pipes P/N 0
202 12 800 0, connecting the Fuel Control
Unit to the start electrovalve, were reported.
These cases of cracking, if they had not
previously been detected, could have caused
a loss of integrity of the union conveying fuel
under pressure. A fuel leakage could then
have happened and would have led to an
uncommanded loss of power and to a fire
hazard. This AD requires the fuel pipe to be
inspected for cracking.
FAA AD Differences
(e) None.
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Actions and Compliance
1143
Issued in Burlington, Massachusetts, on
December 27, 2006.
Ann C. Mollica,
Acting Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. E6–22533 Filed 1–9–07; 8:45 am]
(f) At the next maintenance action on the
engine or airframe, but no later than 30 days
after the effective date of this AD, unless
already done, do the following action.
(1) Inspect for cracks in the lower union of
the flexible fuel pipe between the electric
fuel cock and the start valve.
(2) Use the instructions contained in
paragraph 2 of Turbomeca Mandatory Service
Bulletin No. A218 73 0803, dated May 2,
2006, to do the inspection.
BILLING CODE 4910–13–P
Other FAA AD Provisions
14 CFR Part 39
(g) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, Engine Certification
Office, has the authority to approve AMOCs
for this AD, if requested using the procedures
found in 14 CFR 39.19.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
(3) Reporting Requirements: For any
reporting requirement in this AD, under the
provisions of the Paperwork Reduction Act,
the Office of Management and Budget (OMB)
has approved the information collection
requirements and has assigned OMB Control
Number 2120–0056.
Related Information
(h) Refer to the EASA Airworthiness
Directive 2006–0154, dated June 1, 2006, and
Turbomeca Mandatory Service Bulletin A218
73 0803, dated May 2, 2006, for related
information.
(i) Contact Christopher Spinney, Aerospace
Engineer, Engine Certification Office, FAA,
Engine & Propeller Directorate, 12 New
England Executive Park, Burlington, MA
01803; telephone (781) 238–7175; fax (781)
238–7199, for more information about this
AD.
Material Incorporated by Reference
(j) You must use Turbomeca Mandatory
Service Bulletin No. A218 73 0803, dated
May 2, 2006, to do the actions required by
this AD, unless the AD specifies otherwise.
(1) The Director of the Federal Register
approved the incorporation by reference of
this service information under 5 U.S.C.
552(a) and 1 CFR part 51.
(2) For service information identified in
this AD, contact Turbomeca, 40220 Tarnos,
France; telephone (33) 05 59 74 40 00; fax
(33) 05 59 74 45 15.
(3) You may review copies at the National
Archives and Records Administration
(NARA). For information on the availability
of this material at NARA, call (202) 741–
6030, or go to: https://www.archives.gov/
federal-register/cfr/ibr-locations.html.
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
[Docket No. FAA–2006–25089; Directorate
Identifier 2006–NM–091–AD; Amendment
39–14873; AD 2007–01–02]
RIN 2120–AA64
Airworthiness Directives; McDonnell
Douglas Model MD–11 and –11F
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: The FAA is superseding an
existing airworthiness directive (AD),
which applies to certain McDonnell
Douglas Model MD–11 and –11F
airplanes. That AD currently requires an
initial general visual inspection of the
power feeder cables of the integrated
drive generator (IDG) and the fuel feed
lines of engine pylons No. 1 and No. 3
on the wings for proper clearance and
damage; corrective actions if necessary;
and repetitive general visual inspections
and a terminating action for the
repetitive inspections. This new AD
requires the existing actions, and for
certain airplanes, this AD requires
installation of new clamps on the power
feeder cables of the IDG of engine
pylons No. 1 and No. 3. This AD results
from reports of IDG power feeder cables
riding against structure and fuel lines in
the No. 1 and No. 3 pylons. We are
issuing this AD to prevent potential
chafing of the power feeder cables of the
IDG in engine pylons No. 1 and No. 3
on the wings, and consequent arcing on
the fuel lines in the engine pylons and
possible fuel fire.
DATES: This AD becomes effective
February 14, 2007.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of February 14, 2007.
On February 24, 2004 (69 FR 2657,
January 20, 2004), the Director of the
Federal Register approved the
incorporation by reference of Boeing
Alert Service Bulletin MD11–54A011,
Revision 02, dated May 31, 2002.
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You may examine the AD
docket on the Internet at https://
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:
Brett Portwood, Aerospace Engineer,
Systems and Equipment Branch, ANM–
130L, FAA, Los Angeles Aircraft
Certification Office, 3960 Paramount
Boulevard, Lakewood, California 90712;
telephone (562) 627–5350; fax (562)
627–5210.
SUPPLEMENTARY INFORMATION:
element of compliance it should not
simply be referenced, but should be
incorporated into the regulatory
document.
We understand MARPA’s comment
concerning incorporation by reference.
The Office of the Federal Register (OFR)
requires that documents that are
necessary to accomplish the
requirements of the AD be incorporated
by reference during the final rule phase
of rulemaking. This final rule
incorporates by reference the document
necessary for the accomplishment of the
requirements mandated by this AD.
Further, we point out that while
documents that are incorporated by
reference do become public information,
they do not lose their copyright
protection. For that reason, we advise
the public to contact the manufacturer
to obtain copies of the referenced
service information.
Examining the Docket
You may examine the airworthiness
directive (AD) docket on the Internet at
https://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.
Request To Publish Service Information
This same commenter, MARPA, also
requests that service documents
referenced in ADs be made available to
the public by publishing the service
documents in either the Federal
Register or the Docket Management
System (DMS). MARPA states that
incorporation by reference was
authorized to reduce the volume of
material published in the Federal
Register. MARPA contends that, with
service information readily available in
electronic formats, it is no longer
necessary to have the high concern for
brevity.
In regard to the commenter’s request
that service documents be made
available to the public by publication in
the Federal Register, we acknowledge
that incorporation by reference was
authorized to reduce the volume of
material published in the Federal
Register and the Code of Federal
Regulations. However, as specified in
the Federal Register Document Drafting
Handbook, the Director of the OFR
decides when an agency may
incorporate material by reference. As
the commenter is aware, the OFR files
documents for public inspection on the
workday before the date of publication
of the rule at its office in Washington,
DC. As stated in the Federal Register
Document Drafting Handbook, when
documents are filed for public
inspection, anyone may inspect or copy
file documents during the OFR’s hours
of business. Further questions regarding
publication of documents in the Federal
Register or incorporation by reference
should be directed to the OFR.
In regards to the commenter’s request
to post service bulletins on the
Department of Transportation’s DMS,
ADDRESSES:
Discussion
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that
supersedes AD 2004–01–17, amendment
39–13431 (69 FR 2657, January 20,
2004). The existing AD applies to
certain McDonnell Douglas Model MD–
11 and –11F airplanes. That NPRM was
published in the Federal Register on
June 21, 2006 (71 FR 35578). That
NPRM proposed to continue to require
the existing actions, and for certain
airplanes, the NPRM proposed to
require installation of new clamps on
the power feeder cables of the integrated
drive generator (IDG) of engine pylons
No. 1 and No. 3.
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Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comments that have
been received on the NPRM.
Request to Incorporate by Reference
Certain Service Information
One commenter, the Modification and
Replacement Parts Association
(MARPA), states that if a service
document is used as a mandatory
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we are currently in the process of
reviewing issues surrounding the
posting of service bulletins on the DMS
as part of an AD docket. Once we have
thoroughly examined all aspects of this
issue and have made a final
determination, we will consider
whether our current practice needs to be
revised. No change to the final rule is
necessary in response to this comment.
Conclusion
We have carefully reviewed the
available data, including the comments
that have been submitted, and
determined that air safety and the
public interest require adopting the AD
as proposed.
Costs of Compliance
There are about 195 airplanes of the
affected design in the worldwide fleet.
This AD will affect about 98 Model MD–
11 and –11F airplanes of U.S. registry.
The inspections that are required by
AD 2004–01–17 and retained in this AD
take about 1 work hour per airplane, at
an average labor rate of $80 per work
hour. Based on these figures, the
estimated cost of the currently required
actions is $80 per airplane, per
inspection cycle.
The new required inspection will take
about 1 work hour per airplane, at an
average labor rate of $80 per work hour.
Based on these figures, the estimated
cost of the new inspections required in
this AD for U.S. operators is $7,840, or
$80 per airplane, per inspection cycle.
The new required terminating action
will take approximately 4 work hours
per airplane to accomplish, at an
average labor rate of $80 per work hour.
The vendor states that it will supply the
parts at no cost to the operator. Based
on these figures, the estimated cost of
the terminating action specified in this
AD for U.S. operators is $31,360, or
$320 per airplane.
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
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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
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
I
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by removing amendment 39–13431 (69
FR 2657, January 20, 2004) and by
adding the following new airworthiness
directive (AD):
I
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2007–01–02 McDonnell Douglas:
Amendment 39–14873. Docket No. FAA
2006–25089; Directorate Identifier 2006–
NM–091–AD.
Effective Date
(a) This AD becomes effective February 14,
2007.
Affected ADs
(b) This AD supersedes AD 2004–01–17.
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Applicability
(c) This AD applies to McDonnell Douglas
Model MD–11 and –11F airplanes, as
identified in Boeing Alert Service Bulletin
MD11–54A011, Revision 3, dated November
9, 2005; certificated in any category.
Unsafe Condition
(d) This AD results from reports of
integrated drive generator (IDG) power feeder
cables riding against structure and fuel lines
in the No. 1 and No. 3 pylons. We are issuing
this AD to prevent potential chafing of the
power feeder cables of the IDG in engine
pylons No. 1 and No. 3 on the wings, and
consequent arcing on the fuel lines in the
engine pylons and possible fuel fire.
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 2004–
01–17
Note 1: Boeing has issued Information
Notice MD11–54A011 R02 IN 02, dated July
11, 2002. The information notice informs
operators of a typographical error for the
string tie part number (P/N) specified in
Boeing Alert Service Bulletin MD11–54A011,
Revision 02, dated May 31, 2002. The service
bulletin specifies string tie P/N 190L0F21G/
A; the correct P/N is 109 LOF 21G/A.
Initial Inspection
(f) Within 30 days after February 24, 2004
(the effective date of AD 2004–01–17), do a
general visual inspection of the power feeder
cables of the IDG and the fuel feed lines of
engine pylons No. 1 and No. 3 on the wings
for proper clearance and damage, per Boeing
Alert Service Bulletin MD11–54A011,
Revision 02, dated May 31, 2002; or Boeing
Alert Service Bulletin MD11–54A011,
Revision 3, dated November 9, 2005.
Note 2: For the purposes of this AD, a
general visual inspection is defined as: ‘‘A
visual examination of an interior or exterior
area, installation, or assembly to detect
obvious damage, failure, or irregularity. This
level of inspection is made from within
touching distance unless otherwise specified.
A mirror may be necessary to enhance visual
access to all exposed surfaces in the
inspection area. This level of inspection is
made under normally available lighting
conditions such as daylight, hangar lighting,
flashlight, or droplight and may require
removal or opening of access panels or doors.
Stands, ladders, or platforms may be required
to gain proximity to the area being checked.’’
Condition 1: Proper Clearance and No
Damage
(g) If proper clearance exists and no
damage is detected during any inspection
required by paragraph (f) of this AD, do the
action(s) specified in paragraphs (g)(1), (g)(2),
and (g)(3) of this AD, as applicable, per
Boeing Alert Service Bulletin MD11–54A011,
Revision 02, dated May 31, 2002; or Boeing
Alert Service Bulletin MD11–54A011,
Revision 3, dated November 9, 2005.
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(1) For Group 1 and Group 2 airplanes
identified in the service bulletin: Repeat the
inspection required by paragraph (f) of this
AD every 6 months until the modification
required by paragraph (g)(2) or (g)(3) of this
AD, as applicable, has been done.
(2) For Group 1 airplanes identified in the
service bulletin: Within 18 months after
February 24, 2004, install the brackets to
support the IDG harness, and install new
clamps on the power feeder cables of the IDG
of the No. 1 and No. 3 pylons.
(3) For Group 2 airplanes identified in the
service bulletin: Within 18 months after
February 24, 2004, replace the existing
fairlead with a new clamp, and install new
tape.
Condition 2: Improper Clearance and No
Damage
(h) If improper clearance exists and no
damage is detected during any inspection
required by paragraph (f) of this AD, do the
action(s) specified in paragraphs (h)(1),
(h)(2), and (h)(3) of this AD, as applicable,
per Boeing Alert Service Bulletin MD11–
54A011, Revision 02, dated May 31, 2002; or
Boeing Alert Service Bulletin MD11–54A011,
Revision 3, dated November 9, 2005.
(1) For Group 1 and Group 2 airplanes
identified in the service bulletin: Before
further flight, reposition cables, and repeat
the inspection required by paragraph (f) of
this AD every 6 months until the
modification required by paragraph (h)(2) or
(h)(3) of this AD, as applicable, has been
done.
(2) For Group 1 airplanes identified in the
service bulletin: Within 18 months after
February 24, 2004, install the brackets to
support the IDG harness, and install new
clamps on the power feeder cables of the IDG
of engine pylons No. 1 and No. 3.
(3) For Group 2 airplanes identified in the
service bulletin: Within 18 months after
February 24, 2004, replace the existing
fairlead with a new clamp, and install new
tape.
Condition 3: Improper Clearance and
Damage Detected
(i) If improper clearance exists and any
damage is detected during any inspection
required by paragraph (f) of this AD, do the
action(s) specified in paragraphs (i)(1), (i)(2),
and (i)(3) of this AD, as applicable, per
Boeing Alert Service Bulletin MD11–54A011,
Revision 02, dated May 31, 2002; or Boeing
Alert Service Bulletin MD11–54A011,
Revision 3, dated November 9, 2005.
(1) For Group 1 and Group 2 airplanes
identified in the service bulletin: Before
further flight, reposition cables; repair
damage or replace damaged cables or fuel
feed lines with new or serviceable cables or
fuel feed lines; and repeat the inspection
required by paragraph (f) of this AD every 6
months until the modification required by
paragraph (i)(2) or (i)(3) of this AD, as
applicable, has been done.
(2) For Group 1 airplanes identified in the
service bulletin: Within 18 months after
February 24, 2004, install the brackets to
support the IDG harness, and install new
clamps on the power feeder cables of the IDG
of engine pylons No. 1 and No. 3.
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(3) For Group 2 airplanes identified in the
service bulletin: Within 18 months after
February 24, 2004, replace the existing
fairlead with a new clamp, and install new
tape.
New Requirements of This AD
General Visual Inspection
(j) For airplanes identified as Group 1,
configurations 3 and 4, and Group 2,
configuration 2, in Boeing Alert Service
Bulletin (ASB) MD11–54A011, Revision 3,
dated November 9, 2005: Within 30 days
after the effective date of this AD, do a
general visual inspection for proper clearance
and damage of the power feeder cables of the
IDG and the fuel feed lines of engine pylons
No. 1 and No. 3 on the wings, in accordance
with the Accomplishment Instructions of
Boeing ASB MD11–54A011, Revision 3,
dated November 9, 2005.
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Condition 1: Proper Clearance and No
Damage
(k) For airplanes identified as Group 1,
configurations 3 and 4, and Group 2,
configuration 2, in Boeing ASB MD11–
54A011, Revision 3, dated November 9, 2005:
If proper clearance exists and no damage is
detected during any inspection required by
paragraph (j) of this AD, do the actions
specified in paragraphs (k)(1), (k)(2), and
(k)(3) of this AD, as applicable, in accordance
with the Accomplishment Instructions of
Boeing ASB MD11–54A011, Revision 3,
dated November 9, 2005. Accomplishment of
the actions specified in paragraph (k)(2) or
(k)(3) of this AD, as applicable, terminates
the inspection requirements of paragraph
(k)(1) of this AD.
(1) For Group 1 airplanes, configurations 3
and 4, and Group 2, configuration 2: Repeat
the inspection required by paragraph (j) of
this AD thereafter at intervals not to exceed
6 months, until the actions specified in
paragraph (k)(2) or (k)(3) of this AD, as
applicable, are accomplished.
(2) For Group 1 airplanes, configuration 3:
Within 18 months after the effective date of
this AD, install IDG harness support brackets
and modify the IDG power feeder cable
installations.
(3) For Group 1 airplanes, configuration 4,
and Group 2, configuration 2: Within 18
months after the effective date of this AD,
modify the IDG power feeder cable
installations.
Condition 2: Improper Clearance and No
Damage
(l) For airplanes identified as Group 1,
configurations 3 and 4, and Group 2,
configuration 2, in Boeing ASB MD11–
54A011, Revision 3, dated November 9, 2005:
If improper clearance exists and no damage
is detected during any inspection required by
paragraph (j) of this AD, do the actions
specified in paragraphs (l)(1), (l)(2), and (l)(3)
of this AD, as applicable, in accordance with
the Accomplishment Instructions of Boeing
ASB MD11–54A011, Revision 3, dated
November 9, 2005. Accomplishment of the
actions specified in paragraph (l)(2) or (l)(3)
of this AD, as applicable, terminates the
repetitive inspections required in paragraph
(l)(1) of this AD.
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(1) Before further flight, reposition the
cables. Repeat the inspection required by
paragraph (j) of this AD thereafter at intervals
not to exceed 6 months, until the actions
specified by paragraph (l)(2) or (l)(3) of this
AD, as applicable, are accomplished.
(2) For Group 1 airplanes, configuration 3:
Within 18 months after the effective date of
this AD, install IDG harness support brackets
and modify the IDG power feeder cable
installations.
(3) For Group 1 airplanes, configuration 4,
and Group 2 airplanes, configuration 2:
Within 18 months after the effective date of
this AD, modify the IDG power feeder cable
installations.
Condition 3: Improper Clearance and
Damage Detected
(m) For airplanes identified as Group 1,
configurations 3 and 4, and Group 2,
configuration 2, in Boeing ASB MD11–
54A011, Revision 3, dated November 9, 2005:
If improper clearance exists and there is any
damage to the cables, structure, or fuel feed
line, do the actions specified in paragraphs
(m)(1), (m)(2), and (m)(3) of this AD, as
applicable, in accordance with the
Accomplishment Instructions of Boeing ASB
MD11–54A011, Revision 3, dated November
9, 2005. Accomplishment of the actions
specified in paragraph (m)(2) or (m)(3) of this
AD, as applicable, terminates the repetitive
inspection requirements of paragraph (m)(1)
of this AD.
(1) Before further flight, reposition cables
and repair damage or replace damaged cables
or fuel feed lines with new or serviceable
cables or fuel feed lines. Repeat the
inspection required by paragraph (j) of this
AD thereafter at intervals not to exceed 6
months, until the actions specified by
paragraph (m)(2) or (m)(3) of this AD, as
applicable, are accomplished.
(2) For Group 1 airplanes, configuration 3:
Within 18 months after the effective date of
this AD, install IDG harness support brackets,
and modify the IDG power feeder cable
installations.
(3) For Group 1 airplanes, configuration 4,
and Group 2 airplanes, configuration 2:
Within 18 months after the effective date of
this AD: Modify the IDG power feeder cable
installations.
Alternative Methods of Compliance
(AMOCs)
(n)(1) The Manager, Los Angeles Aircraft
Certification Office, Transport Airplane
Directorate, FAA, has the authority to
approve AMOCs for this AD, if requested in
accordance with the procedures found in 14
CFR 39.19.
(2) Before using any AMOC approved in
accordance with § 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 2004–01–17, are not
approved as AMOCs with this AD.
(4) 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
PO 00000
Frm 00012
Fmt 4700
Sfmt 4700
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, and the approval
must specifically refer to this AD.
Material Incorporated by Reference
(o) You must use Boeing Alert Service
Bulletin MD11–54A011, Revision 02, dated
May 31, 2002, or Boeing Alert Service
Bulletin MD11–54A011, Revision 3, dated
November 9, 2005, to perform the actions
that are required by this AD, unless the AD
specifies otherwise.
(1) The Director of the Federal Register
approved the incorporation by reference of
Boeing Alert Service Bulletin MD11–54A011,
Revision 3, dated November 9, 2005, in
accordance with 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) On February 24, 2004 (69 FR 2657,
January 20, 2004), the Director of the Federal
Register approved the incorporation by
reference of Boeing Alert Service Bulletin
MD11–54A011, Revision 02, dated May 31,
2002.
(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 https://
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 https://www.archives.gov/
federal_register/code_of_federal_regulations/
ibr_locations.html.
Issued in Renton, Washington, on
December 21, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E6–22536 Filed 1–9–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–26797; Directorate
Identifier 2006–NM–195–AD; Amendment
39–14878; AD 2006–20–14]
RIN 2120–AA64
Airworthiness Directives; Empresa
Brasileira de Aeronautica S.A.
(EMBRAER) Model ERJ 170 and ERJ
190 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
AGENCY:
E:\FR\FM\10JAR1.SGM
10JAR1
]]>Agencies
[Federal Register Volume 72, Number 6 (Wednesday, January 10, 2007)]
[Rules and Regulations]
[Pages 1143-1146]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-22536]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-25089; Directorate Identifier 2006-NM-091-AD;
Amendment 39-14873; AD 2007-01-02]
RIN 2120-AA64
Airworthiness Directives; McDonnell Douglas Model MD-11 and -11F
Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is superseding an existing airworthiness directive
(AD), which applies to certain McDonnell Douglas Model MD-11 and -11F
airplanes. That AD currently requires an initial general visual
inspection of the power feeder cables of the integrated drive generator
(IDG) and the fuel feed lines of engine pylons No. 1 and No. 3 on the
wings for proper clearance and damage; corrective actions if necessary;
and repetitive general visual inspections and a terminating action for
the repetitive inspections. This new AD requires the existing actions,
and for certain airplanes, this AD requires installation of new clamps
on the power feeder cables of the IDG of engine pylons No. 1 and No. 3.
This AD results from reports of IDG power feeder cables riding against
structure and fuel lines in the No. 1 and No. 3 pylons. We are issuing
this AD to prevent potential chafing of the power feeder cables of the
IDG in engine pylons No. 1 and No. 3 on the wings, and consequent
arcing on the fuel lines in the engine pylons and possible fuel fire.
DATES: This AD becomes effective February 14, 2007.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of February 14,
2007.
On February 24, 2004 (69 FR 2657, January 20, 2004), the Director
of the Federal Register approved the incorporation by reference of
Boeing Alert Service Bulletin MD11-54A011, Revision 02, dated May 31,
2002.
[[Page 1144]]
ADDRESSES: You may examine the AD docket on the Internet at https://
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: Brett Portwood, Aerospace Engineer,
Systems and Equipment Branch, ANM-130L, FAA, Los Angeles Aircraft
Certification Office, 3960 Paramount Boulevard, Lakewood, California
90712; telephone (562) 627-5350; fax (562) 627-5210.
SUPPLEMENTARY INFORMATION:
Examining the Docket
You may examine the airworthiness directive (AD) docket on the
Internet at https://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 proposed rulemaking (NPRM) to amend 14
CFR part 39 to include an AD that supersedes AD 2004-01-17, amendment
39-13431 (69 FR 2657, January 20, 2004). The existing AD applies to
certain McDonnell Douglas Model MD-11 and -11F airplanes. That NPRM was
published in the Federal Register on June 21, 2006 (71 FR 35578). That
NPRM proposed to continue to require the existing actions, and for
certain airplanes, the NPRM proposed to require installation of new
clamps on the power feeder cables of the integrated drive generator
(IDG) of engine pylons No. 1 and No. 3.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comments that have been
received on the NPRM.
Request to Incorporate by Reference Certain Service Information
One commenter, the Modification and Replacement Parts Association
(MARPA), states that if a service document is used as a mandatory
element of compliance it should not simply be referenced, but should be
incorporated into the regulatory document.
We understand MARPA's comment concerning incorporation by
reference. The Office of the Federal Register (OFR) requires that
documents that are necessary to accomplish the requirements of the AD
be incorporated by reference during the final rule phase of rulemaking.
This final rule incorporates by reference the document necessary for
the accomplishment of the requirements mandated by this AD. Further, we
point out that while documents that are incorporated by reference do
become public information, they do not lose their copyright protection.
For that reason, we advise the public to contact the manufacturer to
obtain copies of the referenced service information.
Request To Publish Service Information
This same commenter, MARPA, also requests that service documents
referenced in ADs be made available to the public by publishing the
service documents in either the Federal Register or the Docket
Management System (DMS). MARPA states that incorporation by reference
was authorized to reduce the volume of material published in the
Federal Register. MARPA contends that, with service information readily
available in electronic formats, it is no longer necessary to have the
high concern for brevity.
In regard to the commenter's request that service documents be made
available to the public by publication in the Federal Register, we
acknowledge that incorporation by reference was authorized to reduce
the volume of material published in the Federal Register and the Code
of Federal Regulations. However, as specified in the Federal Register
Document Drafting Handbook, the Director of the OFR decides when an
agency may incorporate material by reference. As the commenter is
aware, the OFR files documents for public inspection on the workday
before the date of publication of the rule at its office in Washington,
DC. As stated in the Federal Register Document Drafting Handbook, when
documents are filed for public inspection, anyone may inspect or copy
file documents during the OFR's hours of business. Further questions
regarding publication of documents in the Federal Register or
incorporation by reference should be directed to the OFR.
In regards to the commenter's request to post service bulletins on
the Department of Transportation's DMS, we are currently in the process
of reviewing issues surrounding the posting of service bulletins on the
DMS as part of an AD docket. Once we have thoroughly examined all
aspects of this issue and have made a final determination, we will
consider whether our current practice needs to be revised. No change to
the final rule is necessary in response to this comment.
Conclusion
We have carefully reviewed the available data, including the
comments that have been submitted, and determined that air safety and
the public interest require adopting the AD as proposed.
Costs of Compliance
There are about 195 airplanes of the affected design in the
worldwide fleet. This AD will affect about 98 Model MD-11 and -11F
airplanes of U.S. registry.
The inspections that are required by AD 2004-01-17 and retained in
this AD take about 1 work hour per airplane, at an average labor rate
of $80 per work hour. Based on these figures, the estimated cost of the
currently required actions is $80 per airplane, per inspection cycle.
The new required inspection will take about 1 work hour per
airplane, at an average labor rate of $80 per work hour. Based on these
figures, the estimated cost of the new inspections required in this AD
for U.S. operators is $7,840, or $80 per airplane, per inspection
cycle.
The new required terminating action will take approximately 4 work
hours per airplane to accomplish, at an average labor rate of $80 per
work hour. The vendor states that it will supply the parts at no cost
to the operator. Based on these figures, the estimated cost of the
terminating action specified in this AD for U.S. operators is $31,360,
or $320 per airplane.
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
[[Page 1145]]
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 39-13431 (69 FR 2657, January 20, 2004) and by
adding the following new airworthiness directive (AD):
2007-01-02 McDonnell Douglas: Amendment 39-14873. Docket No. FAA
2006-25089; Directorate Identifier 2006-NM-091-AD.
Effective Date
(a) This AD becomes effective February 14, 2007.
Affected ADs
(b) This AD supersedes AD 2004-01-17.
Applicability
(c) This AD applies to McDonnell Douglas Model MD-11 and -11F
airplanes, as identified in Boeing Alert Service Bulletin MD11-
54A011, Revision 3, dated November 9, 2005; certificated in any
category.
Unsafe Condition
(d) This AD results from reports of integrated drive generator
(IDG) power feeder cables riding against structure and fuel lines in
the No. 1 and No. 3 pylons. We are issuing this AD to prevent
potential chafing of the power feeder cables of the IDG in engine
pylons No. 1 and No. 3 on the wings, and consequent arcing on the
fuel lines in the engine pylons and possible fuel fire.
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 2004-01-17
Note 1: Boeing has issued Information Notice MD11-54A011 R02 IN
02, dated July 11, 2002. The information notice informs operators of
a typographical error for the string tie part number (P/N) specified
in Boeing Alert Service Bulletin MD11-54A011, Revision 02, dated May
31, 2002. The service bulletin specifies string tie P/N 190L0F21G/A;
the correct P/N is 109 LOF 21G/A.
Initial Inspection
(f) Within 30 days after February 24, 2004 (the effective date
of AD 2004-01-17), do a general visual inspection of the power
feeder cables of the IDG and the fuel feed lines of engine pylons
No. 1 and No. 3 on the wings for proper clearance and damage, per
Boeing Alert Service Bulletin MD11-54A011, Revision 02, dated May
31, 2002; or Boeing Alert Service Bulletin MD11-54A011, Revision 3,
dated November 9, 2005.
Note 2: For the purposes of this AD, a general visual inspection
is defined as: ``A visual examination of an interior or exterior
area, installation, or assembly to detect obvious damage, failure,
or irregularity. This level of inspection is made from within
touching distance unless otherwise specified. A mirror may be
necessary to enhance visual access to all exposed surfaces in the
inspection area. This level of inspection is made under normally
available lighting conditions such as daylight, hangar lighting,
flashlight, or droplight and may require removal or opening of
access panels or doors. Stands, ladders, or platforms may be
required to gain proximity to the area being checked.''
Condition 1: Proper Clearance and No Damage
(g) If proper clearance exists and no damage is detected during
any inspection required by paragraph (f) of this AD, do the
action(s) specified in paragraphs (g)(1), (g)(2), and (g)(3) of this
AD, as applicable, per Boeing Alert Service Bulletin MD11-54A011,
Revision 02, dated May 31, 2002; or Boeing Alert Service Bulletin
MD11-54A011, Revision 3, dated November 9, 2005.
(1) For Group 1 and Group 2 airplanes identified in the service
bulletin: Repeat the inspection required by paragraph (f) of this AD
every 6 months until the modification required by paragraph (g)(2)
or (g)(3) of this AD, as applicable, has been done.
(2) For Group 1 airplanes identified in the service bulletin:
Within 18 months after February 24, 2004, install the brackets to
support the IDG harness, and install new clamps on the power feeder
cables of the IDG of the No. 1 and No. 3 pylons.
(3) For Group 2 airplanes identified in the service bulletin:
Within 18 months after February 24, 2004, replace the existing
fairlead with a new clamp, and install new tape.
Condition 2: Improper Clearance and No Damage
(h) If improper clearance exists and no damage is detected
during any inspection required by paragraph (f) of this AD, do the
action(s) specified in paragraphs (h)(1), (h)(2), and (h)(3) of this
AD, as applicable, per Boeing Alert Service Bulletin MD11-54A011,
Revision 02, dated May 31, 2002; or Boeing Alert Service Bulletin
MD11-54A011, Revision 3, dated November 9, 2005.
(1) For Group 1 and Group 2 airplanes identified in the service
bulletin: Before further flight, reposition cables, and repeat the
inspection required by paragraph (f) of this AD every 6 months until
the modification required by paragraph (h)(2) or (h)(3) of this AD,
as applicable, has been done.
(2) For Group 1 airplanes identified in the service bulletin:
Within 18 months after February 24, 2004, install the brackets to
support the IDG harness, and install new clamps on the power feeder
cables of the IDG of engine pylons No. 1 and No. 3.
(3) For Group 2 airplanes identified in the service bulletin:
Within 18 months after February 24, 2004, replace the existing
fairlead with a new clamp, and install new tape.
Condition 3: Improper Clearance and Damage Detected
(i) If improper clearance exists and any damage is detected
during any inspection required by paragraph (f) of this AD, do the
action(s) specified in paragraphs (i)(1), (i)(2), and (i)(3) of this
AD, as applicable, per Boeing Alert Service Bulletin MD11-54A011,
Revision 02, dated May 31, 2002; or Boeing Alert Service Bulletin
MD11-54A011, Revision 3, dated November 9, 2005.
(1) For Group 1 and Group 2 airplanes identified in the service
bulletin: Before further flight, reposition cables; repair damage or
replace damaged cables or fuel feed lines with new or serviceable
cables or fuel feed lines; and repeat the inspection required by
paragraph (f) of this AD every 6 months until the modification
required by paragraph (i)(2) or (i)(3) of this AD, as applicable,
has been done.
(2) For Group 1 airplanes identified in the service bulletin:
Within 18 months after February 24, 2004, install the brackets to
support the IDG harness, and install new clamps on the power feeder
cables of the IDG of engine pylons No. 1 and No. 3.
[[Page 1146]]
(3) For Group 2 airplanes identified in the service bulletin:
Within 18 months after February 24, 2004, replace the existing
fairlead with a new clamp, and install new tape.
New Requirements of This AD
General Visual Inspection
(j) For airplanes identified as Group 1, configurations 3 and 4,
and Group 2, configuration 2, in Boeing Alert Service Bulletin (ASB)
MD11-54A011, Revision 3, dated November 9, 2005: Within 30 days
after the effective date of this AD, do a general visual inspection
for proper clearance and damage of the power feeder cables of the
IDG and the fuel feed lines of engine pylons No. 1 and No. 3 on the
wings, in accordance with the Accomplishment Instructions of Boeing
ASB MD11-54A011, Revision 3, dated November 9, 2005.
Condition 1: Proper Clearance and No Damage
(k) For airplanes identified as Group 1, configurations 3 and 4,
and Group 2, configuration 2, in Boeing ASB MD11-54A011, Revision 3,
dated November 9, 2005: If proper clearance exists and no damage is
detected during any inspection required by paragraph (j) of this AD,
do the actions specified in paragraphs (k)(1), (k)(2), and (k)(3) of
this AD, as applicable, in accordance with the Accomplishment
Instructions of Boeing ASB MD11-54A011, Revision 3, dated November
9, 2005. Accomplishment of the actions specified in paragraph (k)(2)
or (k)(3) of this AD, as applicable, terminates the inspection
requirements of paragraph (k)(1) of this AD.
(1) For Group 1 airplanes, configurations 3 and 4, and Group 2,
configuration 2: Repeat the inspection required by paragraph (j) of
this AD thereafter at intervals not to exceed 6 months, until the
actions specified in paragraph (k)(2) or (k)(3) of this AD, as
applicable, are accomplished.
(2) For Group 1 airplanes, configuration 3: Within 18 months
after the effective date of this AD, install IDG harness support
brackets and modify the IDG power feeder cable installations.
(3) For Group 1 airplanes, configuration 4, and Group 2,
configuration 2: Within 18 months after the effective date of this
AD, modify the IDG power feeder cable installations.
Condition 2: Improper Clearance and No Damage
(l) For airplanes identified as Group 1, configurations 3 and 4,
and Group 2, configuration 2, in Boeing ASB MD11-54A011, Revision 3,
dated November 9, 2005: If improper clearance exists and no damage
is detected during any inspection required by paragraph (j) of this
AD, do the actions specified in paragraphs (l)(1), (l)(2), and
(l)(3) of this AD, as applicable, in accordance with the
Accomplishment Instructions of Boeing ASB MD11-54A011, Revision 3,
dated November 9, 2005. Accomplishment of the actions specified in
paragraph (l)(2) or (l)(3) of this AD, as applicable, terminates the
repetitive inspections required in paragraph (l)(1) of this AD.
(1) Before further flight, reposition the cables. Repeat the
inspection required by paragraph (j) of this AD thereafter at
intervals not to exceed 6 months, until the actions specified by
paragraph (l)(2) or (l)(3) of this AD, as applicable, are
accomplished.
(2) For Group 1 airplanes, configuration 3: Within 18 months
after the effective date of this AD, install IDG harness support
brackets and modify the IDG power feeder cable installations.
(3) For Group 1 airplanes, configuration 4, and Group 2
airplanes, configuration 2: Within 18 months after the effective
date of this AD, modify the IDG power feeder cable installations.
Condition 3: Improper Clearance and Damage Detected
(m) For airplanes identified as Group 1, configurations 3 and 4,
and Group 2, configuration 2, in Boeing ASB MD11-54A011, Revision 3,
dated November 9, 2005: If improper clearance exists and there is
any damage to the cables, structure, or fuel feed line, do the
actions specified in paragraphs (m)(1), (m)(2), and (m)(3) of this
AD, as applicable, in accordance with the Accomplishment
Instructions of Boeing ASB MD11-54A011, Revision 3, dated November
9, 2005. Accomplishment of the actions specified in paragraph (m)(2)
or (m)(3) of this AD, as applicable, terminates the repetitive
inspection requirements of paragraph (m)(1) of this AD.
(1) Before further flight, reposition cables and repair damage
or replace damaged cables or fuel feed lines with new or serviceable
cables or fuel feed lines. Repeat the inspection required by
paragraph (j) of this AD thereafter at intervals not to exceed 6
months, until the actions specified by paragraph (m)(2) or (m)(3) of
this AD, as applicable, are accomplished.
(2) For Group 1 airplanes, configuration 3: Within 18 months
after the effective date of this AD, install IDG harness support
brackets, and modify the IDG power feeder cable installations.
(3) For Group 1 airplanes, configuration 4, and Group 2
airplanes, configuration 2: Within 18 months after the effective
date of this AD: Modify the IDG power feeder cable installations.
Alternative Methods of Compliance (AMOCs)
(n)(1) The Manager, Los Angeles Aircraft Certification Office,
Transport Airplane Directorate, FAA, has the authority to approve
AMOCs for this AD, if requested in accordance with the procedures
found in 14 CFR 39.19.
(2) Before using any AMOC approved in accordance with Sec.
39.19 on any airplane to which the AMOC applies, notify the
appropriate principal inspector in the FAA Flight Standards
Certificate Holding District Office.
(3) AMOCs approved previously in accordance with AD 2004-01-17,
are not approved as AMOCs with this AD.
(4) 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, and the approval must specifically
refer to this AD.
Material Incorporated by Reference
(o) You must use Boeing Alert Service Bulletin MD11-54A011,
Revision 02, dated May 31, 2002, or Boeing Alert Service Bulletin
MD11-54A011, Revision 3, dated November 9, 2005, to perform the
actions that are required by this AD, unless the AD specifies
otherwise.
(1) The Director of the Federal Register approved the
incorporation by reference of Boeing Alert Service Bulletin MD11-
54A011, Revision 3, dated November 9, 2005, in accordance with 5
U.S.C. 552(a) and 1 CFR part 51.
(2) On February 24, 2004 (69 FR 2657, January 20, 2004), the
Director of the Federal Register approved the incorporation by
reference of Boeing Alert Service Bulletin MD11-54A011, Revision 02,
dated May 31, 2002.
(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 https://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 https://
www.archives.gov/federal_register/code_of_federal_
regulations/ibr_locations.html.
Issued in Renton, Washington, on December 21, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E6-22536 Filed 1-9-07; 8:45 am]
BILLING CODE 4910-13-P
