Airworthiness Directives; McDonnell Douglas Model MD-11 and -11F Airplanes, 35578-35581 [E6-9718]
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35578
Federal Register / Vol. 71, No. 119 / Wednesday, June 21, 2006 / Proposed Rules
appropriate principal inspector in the FAA
Flight Standards Certificate Holding District
Office.
(3) AMOCs approved previously in
accordance with AD 2005–15–05 are
approved as AMOCs for the corresponding
provisions of this AD.
Related Information
(i) French airworthiness directive F–2006–
035, dated February 1, 2006, also addresses
the subject of this AD.
Issued in Renton, Washington, on June 14,
2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. E6–9715 Filed 6–20–06; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–25089; Directorate
Identifier 2006–NM–091–AD]
RIN 2120–AA64
Airworthiness Directives; McDonnell
Douglas Model MD–11 and –11F
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
rwilkins on PROD1PC63 with PROPOSAL
AGENCY:
SUMMARY: The FAA proposes to
supersede an existing airworthiness
directive (AD) that applies to certain
McDonnell Douglas Model MD–11 and
–11F airplanes. The existing 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 proposed AD would
continue to require the existing actions,
and for certain airplanes, this proposed
AD would require installation of new
clamps on the power feeder cables of
the IDG of engine pylons No. 1 and No.
3. This proposed 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
proposing 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.
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We must receive comments on
this proposed AD by August 7, 2006.
ADDRESSES: Use one of the following
addresses to submit comments on this
proposed AD.
• DOT Docket Web site: Go to https://
dms.dot.gov and follow the instructions
for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://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 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 proposed 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:
DATES:
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–2006–25089;
Directorate Identifier 2006–NM–091–
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 https://
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
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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 may can visit https://
dms.dot.gov.
Examining the Docket
You may examine the 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 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 January 2, 2004, we issued AD
2004–01–17, amendment 39–13431 (69
FR 2657, January 20, 2004), for certain
McDonnell Douglas Model MD–11 and
–11F airplanes. That AD 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. That AD resulted
from the FAA’s practice of re-examining
all aspects of the service experience of
a particular aircraft whenever an
accident occurs. We became aware of
reports indicating that the power feeder
cables of the integrated drive generator
(IDG) are riding against structure and
fuel lines in engine pylons No. 1 and
No. 3 on the wings of certain McDonnell
Douglas Model MD–11 and –11F
airplanes. We issued that 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 of the fuel lines in
the engine pylons and possible fuel fire.
Actions Since Existing AD Was Issued
Since we issued AD 2004–01–17, the
manufacturer has notified us that
certain airplanes with 4/0 size cables
installed have clamps too small to
install over the 4/0 size cables. Those
airplanes need to have larger clamps
installed. The larger clamps are needed
to prevent chafing of the larger power
feeder cables of the IDG.
Relevant Service Information
We have reviewed Boeing Alert
Service Bulletin (ASB) MD11–54A011,
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Revision 3, dated November 9, 2005.
Revision 3 of the ASB is essentially the
same as Revision 02, dated May 31,
2002, which is the appropriate source of
service information for AD 2004–01–17.
In addition to the actions specified in
Revision 02 of the ASB, Revision 3 of
the ASB describes general visual
inspections 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 for
certain airplanes, and installing larger
clamps on the power feeder cables of
the IDG of engine pylons No. 1 and No.
3 for airplanes with 4/0 size cables.
Accomplishment of the actions
specified in the service bulletin is
intended to adequately address the
identified unsafe condition.
For certain airplanes, the ASB also
specifies concurrent or prior
accomplishment of BFGoodrich
Aerospace Service Bulletin MD–11 54–
174, dated May 27, 1993, which
describes installation of the IDG harness
support brackets.
FAA’s Determination and Requirements
of the Proposed AD
We have evaluated all pertinent
information and identified an unsafe
condition that is likely to develop on
other McDonnell Douglas Model MD–11
and –11F airplanes of the same type
design. For this reason, we are
proposing this AD, which would
supersede AD 2004–01–17 and would
retain the requirements of the existing
AD. For airplanes having 4/0 size
cables, this proposed AD also would
require installation of a larger clamp on
the power feeder cables of the IDG.
Change to Existing AD
This proposed AD would retain the
requirements of AD 2004–01–17. Since
AD 2004–01–17 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
rwilkins on PROD1PC63 with PROPOSAL
Requirement in AD 2004–
01–17
Paragraph
Paragraph
Paragraph
Paragraph
(a)
(b)
(c)
(d)
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......................
......................
......................
......................
16:40 Jun 20, 2006
Corresponding
requirement in
this proposed
AD
Paragraph
Paragraph
Paragraph
Paragraph
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(f)
(g)
(h)
(i)
Clarification of Alternative Method of
Compliance (AMOC) Paragraph
We have revised this action to clarify
the appropriate procedure for notifying
the principal inspector before using any
approved AMOC on any airplane to
which the AMOC applies.
Costs of Compliance
There are about 195 airplanes of the
affected design in the worldwide fleet.
This proposed AD would 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
proposed 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 proposed inspection would
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
specified in this proposed AD for U.S.
operators is $7,840, or $80 per airplane,
per inspection cycle.
The new proposed terminating action
would 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 proposed terminating action
specified in this proposed 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
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.
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35579
Regulatory Findings
We have determined that this
proposed AD would not have federalism
implications under Executive Order
13132. This proposed AD would not
have a substantial direct effect on the
States, on the relationship between the
national Government and the States, or
on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that the proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
3. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared a regulatory evaluation
of the estimated costs to comply with
this proposed AD and placed it in the
AD docket. See the ADDRESSES section
for a location to examine the regulatory
evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by removing amendment 39–13431 (69
FR 2657, January 20, 2004) and adding
the following new airworthiness
directive (AD):
McDonnell Douglas: Docket No. FAA–2006–
25089; Directorate Identifier 2006–NM–
091–AD.
Comments Due Date
(a) The FAA must receive comments on
this AD action by August 7, 2006.
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.
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Federal Register / Vol. 71, No. 119 / Wednesday, June 21, 2006 / Proposed Rules
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.
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.
rwilkins on PROD1PC63 with PROPOSAL
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
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16:40 Jun 20, 2006
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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.
(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.
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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 paragraph (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 paragraphs (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 (l)(2) or (l)(3) of this AD, as
applicable, are accomplished.
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Federal Register / Vol. 71, No. 119 / Wednesday, June 21, 2006 / Proposed Rules
(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.
rwilkins on PROD1PC63 with PROPOSAL
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 paragraphs (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, is 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,
amendment 39–13431, 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.
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Issued in Renton, Washington, on June 13,
2006.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E6–9718 Filed 6–20–06; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–25087; Directorate
Identifier 2006–NM–053–AD]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 747 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: The FAA proposes to
supersede an existing airworthiness
directive (AD) that applies to all Boeing
Model 747 airplanes. The existing AD
currently requires a one-time inspection
to determine whether the outer cylinder
of the wing landing gear has certain part
numbers (P/Ns), and replacement of the
outer cylinder of the wing landing gear
with a new, improved, or reworked part
if necessary. The existing AD also
requires removal of the load evening
system, if such a system is installed. For
certain airplanes, this proposed AD
would require an additional one-time
inspection to determine whether the
outer cylinder has a certain other P/N.
For those certain airplanes, this
proposed AD would also require
replacement of the outer cylinder with
a reworked or new, improved part and
related investigative/corrective actions,
if necessary. This proposed AD results
from identification of an additional
unsafe part. We are proposing this AD
to prevent fracture of the outer cylinder
of the wing landing gear, which could
result in collapse of the wing landing
gear.
We must receive comments on
this proposed AD by August 7, 2006.
ADDRESSES: Use one of the following
addresses to submit comments on this
proposed AD.
• DOT Docket Web site: Go to https://
dms.dot.gov and follow the instructions
for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
DATES:
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35581
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 Boeing Commercial
Airplanes, P.O. Box 3707, Seattle,
Washington 98124–2207, for service
information identified in this proposed
AD.
FOR FURTHER INFORMATION CONTACT:
Nicholas Kusz, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton,
Washington 98055–4056; telephone
(425) 917–6432; fax (425) 917–6590.
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–2006–25087;
Directorate Identifier 2006–NM–053–
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 https://
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 may can visit https://
dms.dot.gov.
Examining the Docket
You may examine the 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
E:\FR\FM\21JNP1.SGM
21JNP1
Agencies
[Federal Register Volume 71, Number 119 (Wednesday, June 21, 2006)]
[Proposed Rules]
[Pages 35578-35581]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-9718]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-25089; Directorate Identifier 2006-NM-091-AD]
RIN 2120-AA64
Airworthiness Directives; McDonnell Douglas Model MD-11 and -11F
Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to supersede an existing airworthiness
directive (AD) that applies to certain McDonnell Douglas Model MD-11
and -11F airplanes. The existing 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 proposed AD
would continue to require the existing actions, and for certain
airplanes, this proposed AD would require installation of new clamps on
the power feeder cables of the IDG of engine pylons No. 1 and No. 3.
This proposed 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
proposing 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: We must receive comments on this proposed AD by August 7, 2006.
ADDRESSES: Use one of the following addresses to submit comments on
this proposed AD.
DOT Docket Web site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to https://
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 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 proposed 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:
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-2006-25089; Directorate Identifier 2006-NM-091-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 https://
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 may
can visit https://dms.dot.gov.
Examining the Docket
You may examine the 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 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 January 2, 2004, we issued AD 2004-01-17, amendment 39-13431 (69
FR 2657, January 20, 2004), for certain McDonnell Douglas Model MD-11
and -11F airplanes. That AD 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. That AD resulted from the FAA's practice of
re-examining all aspects of the service experience of a particular
aircraft whenever an accident occurs. We became aware of reports
indicating that the power feeder cables of the integrated drive
generator (IDG) are riding against structure and fuel lines in engine
pylons No. 1 and No. 3 on the wings of certain McDonnell Douglas Model
MD-11 and -11F airplanes. We issued that 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 of the fuel lines in the
engine pylons and possible fuel fire.
Actions Since Existing AD Was Issued
Since we issued AD 2004-01-17, the manufacturer has notified us
that certain airplanes with 4/0 size cables installed have clamps too
small to install over the 4/0 size cables. Those airplanes need to have
larger clamps installed. The larger clamps are needed to prevent
chafing of the larger power feeder cables of the IDG.
Relevant Service Information
We have reviewed Boeing Alert Service Bulletin (ASB) MD11-54A011,
[[Page 35579]]
Revision 3, dated November 9, 2005. Revision 3 of the ASB is
essentially the same as Revision 02, dated May 31, 2002, which is the
appropriate source of service information for AD 2004-01-17. In
addition to the actions specified in Revision 02 of the ASB, Revision 3
of the ASB describes general visual inspections 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 for certain
airplanes, and installing larger clamps on the power feeder cables of
the IDG of engine pylons No. 1 and No. 3 for airplanes with 4/0 size
cables.
Accomplishment of the actions specified in the service bulletin is
intended to adequately address the identified unsafe condition.
For certain airplanes, the ASB also specifies concurrent or prior
accomplishment of BFGoodrich Aerospace Service Bulletin MD-11 54-174,
dated May 27, 1993, which describes installation of the IDG harness
support brackets.
FAA's Determination and Requirements of the Proposed AD
We have evaluated all pertinent information and identified an
unsafe condition that is likely to develop on other McDonnell Douglas
Model MD-11 and -11F airplanes of the same type design. For this
reason, we are proposing this AD, which would supersede AD 2004-01-17
and would retain the requirements of the existing AD. For airplanes
having 4/0 size cables, this proposed AD also would require
installation of a larger clamp on the power feeder cables of the IDG.
Change to Existing AD
This proposed AD would retain the requirements of AD 2004-01-17.
Since AD 2004-01-17 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 2004-01-17 this proposed AD
------------------------------------------------------------------------
Paragraph (a)........................... Paragraph (f)
Paragraph (b)........................... Paragraph (g)
Paragraph (c)........................... Paragraph (h)
Paragraph (d)........................... Paragraph (i)
------------------------------------------------------------------------
Clarification of Alternative Method of Compliance (AMOC) Paragraph
We have revised this action to clarify the appropriate procedure
for notifying the principal inspector before using any approved AMOC on
any airplane to which the AMOC applies.
Costs of Compliance
There are about 195 airplanes of the affected design in the
worldwide fleet. This proposed AD would 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 proposed 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 proposed inspection would 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 specified in this
proposed AD for U.S. operators is $7,840, or $80 per airplane, per
inspection cycle.
The new proposed terminating action would 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
proposed terminating action specified in this proposed 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 is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We have determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify that the proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this proposed AD and placed it in the AD docket. See the
ADDRESSES section for a location to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. The Federal Aviation Administration (FAA) amends Sec. 39.13 by
removing amendment 39-13431 (69 FR 2657, January 20, 2004) and adding
the following new airworthiness directive (AD):
McDonnell Douglas: Docket No. FAA-2006-25089; Directorate Identifier
2006-NM-091-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by August 7,
2006.
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.
[[Page 35580]]
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.
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.
(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 paragraph (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 paragraphs
(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
(l)(2) or (l)(3) of this AD, as applicable, are accomplished.
[[Page 35581]]
(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 paragraphs
(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, is 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,
amendment 39-13431, 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.
Issued in Renton, Washington, on June 13, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E6-9718 Filed 6-20-06; 8:45 am]
BILLING CODE 4910-13-P