Airworthiness Directives; Boeing Model 747 Airplanes, 35581-35584 [E6-9721]
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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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Jkt 208001
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:
PO 00000
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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
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Federal Register / Vol. 71, No. 119 / Wednesday, June 21, 2006 / Proposed Rules
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.
rwilkins on PROD1PC63 with PROPOSAL
Discussion
On July 27, 2004, we issued AD 2004–
16–05, amendment 39–13761 (69 FR
48359, August 10, 2004), for all Boeing
Model 747 airplanes. That AD 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. That AD also requires
removal of the load evening system, if
such a system is installed. That AD
resulted from reports that the outer
cylinder of the wing landing gear was
found cracked or fractured on Model
747 airplanes. We issued that AD to
prevent fracture of the outer cylinder of
the wing landing gear, which could
result in collapse of the wing landing
gear.
Actions Since Existing AD Was Issued
Since we issued AD 2004–16–05,
Boeing has published Service Bulletin
747–32–2472, Revision 1, dated
February 23, 2006, to identify an outer
cylinder, P/N 65B01382–( ), which
was inadvertently omitted from the
original issue of the service bulletin,
dated November 30, 2000. We
referenced the original service bulletin
as the appropriate source of service
information for accomplishing the
inspection and replacement required by
the existing AD.
(The procedures in Revision 1 are
essentially the same as those in the
original service bulletin.) P/N
65B01382–( ) has chrome plating on its
inner surface, similar to the other unsafe
parts identified in the original service
bulletin and existing AD. Therefore, P/
N 65B01382–( ) is also subject to the
same unsafe condition addressed by the
existing AD.
Since P/N 65B01382–( ) was fitted
exclusively to Model 747–100, 747–
100B, 747–100B SUD, and 747SR series
airplanes, this NPRM proposes to
require an additional one-time
inspection to determine the P/Ns of the
outer cylinder of the wing landing only
on these airplanes. For any of these
airplanes equipped with a load evening
system, this NPRM would also require
removal of that system before replacing
P/N 65B01382–( ) with a reworked or
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16:40 Jun 20, 2006
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new, improved part if applicable. We
have added that requirement to
paragraphs (h) and (j) of this NPRM.
(Paragraph (h) of the NPRM corresponds
to paragraph (c) of the existing AD.)
Relevant Service Information
We have reviewed Revision 1 of
Boeing Service Bulletin 747–32–2472.
The service bulletin describes
procedures for doing a one-time
inspection to determine the P/N of the
outer cylinder of the wing landing gear.
The service bulletin also describes
procedures for replacing the outer
cylinder with a reworked or new part
and doing related investigative and
corrective actions, if an outer cylinder
having P/N 65B01212–( ), 65B01382–(
),
65B01430–3, or 65B01430–4 is installed
on an airplane. The related investigative
actions include the following:
• Doing a nital etch test of the upper
inner surface of the outer cylinder for
chrome plating.
• Doing a magnetic particle
inspection of the outer cylinder for any
cracking.
• Doing a nital etch inspection of
inner surface of the outer cylinder for
heat damage.
• Marking the outer cylinder to
indicate that part has been reworked.
The corrective actions include the
following:
• Removing any chrome plating
found on the upper inner surface of the
outer cylinder.
• Reworking the outer cylinder to
remove any cracking or heat damage.
Accomplishing the actions specified
in the service information is intended to
adequately address the unsafe
condition.
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 airplanes of the same type design.
For this reason, we are proposing this
AD, which would supersede AD 2004–
16–05 and would retain the
requirements of the existing AD. This
proposed AD would also require
accomplishing the actions specified in
the service bulletin described
previously, except as discussed under
‘‘Differences Between the Proposed AD
and Service Bulletin.’’
Differences Between the Proposed AD
and Service Bulletin
Service Bulletin 747–32–2472,
Revision 1, specifies that operators may
accomplish certain related investigative
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and corrective actions using an
‘‘approved equivalent procedure.’’
However, this proposed AD would
require operators to accomplish the
actions using the procedures specified
in a certain chapter(s) of the Boeing 747
SOPM or OHM, as applicable. An
‘‘approved equivalent procedure’’ may
be used only if approved as an
alternative method of compliance
according to paragraph (m) of this AD.
Changes to Existing AD
This proposed AD would retain
certain requirements of AD 2004–16–05.
Since AD 2004–16–05 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
Requirement in AD 2004–
16–05
Paragraph
Paragraph
Paragraph
Paragraph
(a)
(b)
(c)
(d)
......................
......................
......................
......................
Corresponding
requirement in
this proposed
AD
Paragraph
Paragraph
Paragraph
Paragraph
(f).
(g).
(h).
(i).
We have added reference to Revision
1 of Boeing Service Bulletin 747–32–
2472 in paragraphs (f) and (g) of this
proposed AD, since the procedures in
Revision 1 are essentially the same as
those in the original issue of the service
bulletin.
We have revised the ‘‘Alternative
Methods of Compliance (AMOCs)’’
paragraph in this proposed AD to clarify
the delegation authority for Authorized
Representatives for the Boeing
Commercial Airplanes Delegation
Option Authorization.
We have also revised this proposed
AD 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 1,106 Model 747
airplanes of the affected design in the
worldwide fleet. Of those airplanes,
there are about 66 Model 747–100, 747–
100B, 747–100B SUD, and 747SR series
airplanes of the affected design in the
worldwide fleet that would be subject to
the new proposed actions. The
following table provides the estimated
costs, at an average labor rate of $80 per
hour, for U.S. operators to comply with
this proposed AD.
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Federal Register / Vol. 71, No. 119 / Wednesday, June 21, 2006 / Proposed Rules
35583
ESTIMATED COSTS
Action
Work hours
Inspection for all airplanes (required by AD 2004–16–05) ..
Removal of the load evening system (required by AD
2004–16–05) ....................................................................
Inspection for certain airplanes (new proposed action) ......
If required, the chrome removal and
inspections for cracking or heat damage
would take about 12 work hours per
airplane, at an average labor rate of $80
per work hour. Based on these figures,
the estimated cost of these actions is
$960 per airplane.
rwilkins on PROD1PC63 with PROPOSAL
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
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19:42 Jun 20, 2006
Jkt 208001
Parts
$80
256
$20,480
240
1
$2,392
None
21,592
80
256
21
5,527,552
1,680
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.
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by removing amendment 39–13761 (69
FR 48359, August 10, 2004) and adding
the following new airworthiness
directive (AD):
Boeing: Docket No. FAA–2006–25087;
Directorate Identifier 2006–NM–053–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 2004–16–05.
Applicability
(c) This AD applies to all Boeing Model
747–100, 747–100B, 747–100B SUD, 747–
200B, 747–200C, 747–200F, 747–300, 747–
400, 747–400D, 747–400F, 747SR, and 747SP
series airplanes, certificated in any category.
Unsafe Condition
(d) This AD results from identification of
an additional unsafe outer cylinder of the
wing landing gear. We are issuing this AD to
prevent fracture of the outer cylinder of the
wing landing gear, which could result in
collapse of the wing landing gear.
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.
Frm 00023
Fleet cost
None
List of Subjects in 14 CFR Part 39
PO 00000
Number of
U.S.-registered
airplanes
1
this proposed AD and placed it in the
AD docket. See the ADDRESSES section
for a location to examine the regulatory
evaluation.
§ 39.13
Cost per airplane
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Restatement of Requirements of AD 2004–
16–05
Inspection to Determine Part Number
(f) Within 36 months after September 14,
2004 (the effective date of AD 2004–16–05),
perform a one-time inspection to determine
the part number (P/N) of the outer cylinder
of the wing landing gear on both sides of the
airplane, per the Accomplishment
Instructions of Boeing Service Bulletin 747–
32–2472, dated November 30, 2000, or
Revision 1, dated February 23, 2006. Instead
of inspecting the outer cylinder of the wing
landing gear, a review of airplane
maintenance records is acceptable if the
detailed P/N of the outer cylinder of the wing
landing gear (not just a higher-level
assembly) can be positively determined from
that review.
(1) If no outer cylinder having P/N
65B01212–( ) (where ‘‘( )’’ is any dash
number of that part number), 65B01430–3, or
65B01430–4 is found: No further action is
required by this paragraph.
(2) If any outer cylinder having P/N
65B01212–( ) (where ‘‘( )’’ is any dash
number of that part number), 65B01430–3, or
65B01430–4 is found: Accomplish paragraph
(g) of this AD.
Replacement of Outer Cylinder
(g) For any outer cylinder identified in
paragraph (f)(2) of this AD: Within 36 months
after September 14, 2004, replace the outer
cylinder on the wing landing gear with a
new, improved part or a part that has been
inspected and reworked per the
Accomplishment Instructions of Boeing
Service Bulletin 747–32–2472, dated
November 30, 2000; or Revision 1, dated
February 23, 2006, except as provided by
paragraph (k) of this AD. The rework
procedures described in the service bulletin,
if accomplished, include performing a onetime nital etch inspection of the upper inner
surface of the outer cylinder for chrome
plating; removing any chrome plating that is
present; performing a one-time magnetic
particle inspection for cracking of the outer
cylinder; performing a nital etch inspection
for heat damage of the outer cylinder;
reworking the outer cylinder, as applicable;
and marking the outer cylinder to indicate
that the service bulletin has been
accomplished.
Removal of the Load Evening System
(h) For airplanes identified in Boeing
Service Bulletin 747–32–2131, Revision 2,
dated March 15, 1974: Before performing the
requirements of paragraph (g) or (j) of this
AD, as applicable, remove the load evening
system installed on the wing landing gear,
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Federal Register / Vol. 71, No. 119 / Wednesday, June 21, 2006 / Proposed Rules
per the Accomplishment Instructions of the
service bulletin.
New Requirements of This AD
Inspection To Determine Outer Cylinder P/N
on Certain Airplanes
(i) For Model 747–100, 747–100B, 747–
100B SUD, and 747SR series airplanes:
Within 36 months after the effective date of
this AD, do a one-time inspection to
determine the P/N of the outer cylinder of the
wing landing gear on both sides of the
airplane, in accordance with the
Accomplishment Instructions of Boeing
Service Bulletin 747–32–2472, Revision 1,
dated February 23, 2006. Instead of
inspecting the outer cylinder of the wing
landing gear, a review of airplane
maintenance records is acceptable if the
detailed P/N of the outer cylinder of the wing
landing gear (not just a higher-level
assembly) can be positively determined from
that review.
(1) If no outer cylinder having P/N
65B01382–( ) is found: No further action is
required by this paragraph.
(2) If any outer cylinder having P/N
65B01382–( ) is found: Accomplish
paragraph (j) of this AD.
Replacement of a Certain Outer Cylinder
(j) For any outer cylinder identified in
paragraph (i)(2) of this AD: Within 36 months
after the effective date of this AD, replace the
outer cylinder on the wing landing gear with
a reworked or new, improved part, and do
the related investigative actions and all
applicable corrective actions before further
flight after the replacement, by
accomplishing all of the applicable actions
specified in 3.B.2 and 3.B.3 of the
Accomplishment Instructions of Boeing
Service Bulletin 747–32–2472, Revision 1,
dated February 23, 2006; except as provided
by paragraph (k) of this AD. If applicable, do
the actions specified in paragraph (h) of this
AD before accomplishing the actions
specified in this paragraph.
rwilkins on PROD1PC63 with PROPOSAL
Exception to Revision 1 of the Service
Bulletin
(k) Where Service Bulletin 747–32–2472,
Revision 1, dated February 23, 2006,
specifies that the related investigative and
corrective actions may be accomplished
using an operator’s ‘‘equivalent procedure:’’
The related investigative and corrective
actions must be accomplished in accordance
with the chapter(s) of the applicable Boeing
747 SOPM or OHM specified in the service
bulletin.
Parts Installation
(l) As of September 14, 2004, no person
may install, on any airplane, an outer
cylinder of the wing landing gear if the outer
cylinder has P/N 65B01212–( ), 65B01430–3,
or 65B01430–4, unless the outer cylinder has
been inspected, reworked, and marked to
indicate that Boeing Service Bulletin 747–
32–2472, dated November 30, 2000, or
Revision 1, dated February 23, 2006, has
been accomplished. As of the effective date
of this AD, no person may install an outer
cylinder, P/N 65B01382–( ), of the wing
landing gear on any airplane, unless the outer
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Jkt 208001
cylinder has been inspected, reworked, and
marked to indicate that Boeing Service
Bulletin 747–32–2472, Revision 1, dated
February 23, 2006, has been accomplished.
SUMMARY: The Energy Policy Act of 2005
directs the Commission to issue labeling
requirements for the electricity used by
ceiling fans to circulate air. The
Commission is seeking public comment
on proposed energy labeling
requirements for these products.
DATES: Written comments must be
received on or before September 8,
2006.
and on the envelope, and should be
mailed or delivered, with two complete
copies, to the following address: Federal
Trade Commission/Office of the
Secretary, Room H–135 (Annex L), 600
Pennsylvania Avenue, NW.,
Washington, DC 20580. Comments
containing confidential material must be
filed in paper form, and the first page of
the document must be clearly labeled
‘‘Confidential’’ and must comply with
Commission Rule 4.9(c).1 The FTC is
requesting that any comment filed in
paper form be sent by courier or
overnight service, if possible, because
postal mail in the Washington area and
at the Commission is subject to delay
due to heightened security precautions.
Comments filed in electronic form
should be submitted by following the
instructions on the web-based form at
https://secure.commentworks.com/ftcfan. To ensure that the Commission
considers an electronic comment, you
must file it on that web-based form. You
also may visit https://
www.regulations.gov to read this
proposed Rule, and may file an
electronic comment through that Web
site. The Commission will consider all
comments that regulations.gov forwards
to it.
Comments on any proposed filing,
recordkeeping, or disclosure
requirements that are subject to
paperwork burden review under the
Paperwork Reduction Act should
additionally be submitted to: Office of
Information and Regulatory Affairs,
Office of Management and Budget,
Attention: Desk Officer for Federal
Trade Commission. Comments should
be submitted via facsimile to (202) 395–
6974 because U.S. postal mail at the
Office of Management and Budget
(‘‘OMB’’) is subject to lengthy delays
due to heightened security precautions.
The FTC Act and other laws the
Commission administers permit the
collection of public comments to
consider and use in this proceeding as
appropriate. The Commission will
consider all timely and responsive
public comments that it receives,
whether filed in paper or electronic
form. Comments received will be
available to the public on the FTC Web
site, to the extent practicable, at https://
www.ftc.gov. As a matter of discretion,
the FTC makes every effort to remove
home contact information for
Interested parties are
invited to submit written comments.
Comments should refer to ‘‘Ceiling Fan
Labeling, Matter No. R611018’’ to
facilitate the organization of comments.
A comment filed in paper form should
include this reference both in the text
1 Any request for confidential treatment,
including the factual and legal basis for the request,
must accompany the comment and must identify
the specific portions of the comment to be withheld
from the public record. The request will be granted
or denied by the Commission’s General Counsel,
consistent with applicable law and the public
interest. See Commission Rule 4.9(c), 16 CFR 4.9(c).
Alternative Methods of Compliance (AMOCs)
(m)(1) The Manager, Seattle Aircraft
Certification Office (ACO), 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) 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, Seattle ACO, to
make those findings. For a repair method to
be approved, the repair must meet the
certification basis of the airplane, and the
approval must specifically refer to this AD.
(4) AMOCs approved previously in
accordance with AD 2004–16–05,
amendment 39–13761, are approved as
AMOCs for the corresponding provisions of
paragraphs (f), (g), and (h) of this AD.
Issued in Renton, Washington, on June 13,
2006.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E6–9721 Filed 6–20–06; 8:45 am]
BILLING CODE 4910–13–P
FEDERAL TRADE COMMISSION
16 CFR Part 305
RIN 3084–AA74
Appliance Labeling Rule
Federal Trade Commission
(‘‘FTC’’ or ‘‘Commission’’).
ACTION: Notice of proposed rulemaking;
request for public comment.
AGENCY:
ADDRESSES:
PO 00000
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]]>Agencies
[Federal Register Volume 71, Number 119 (Wednesday, June 21, 2006)]
[Proposed Rules]
[Pages 35581-35584]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-9721]
-----------------------------------------------------------------------
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
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 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.
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, 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
[[Page 35582]]
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 July 27, 2004, we issued AD 2004-16-05, amendment 39-13761 (69
FR 48359, August 10, 2004), for all Boeing Model 747 airplanes. That AD
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. That AD also requires removal
of the load evening system, if such a system is installed. That AD
resulted from reports that the outer cylinder of the wing landing gear
was found cracked or fractured on Model 747 airplanes. We issued that
AD to prevent fracture of the outer cylinder of the wing landing gear,
which could result in collapse of the wing landing gear.
Actions Since Existing AD Was Issued
Since we issued AD 2004-16-05, Boeing has published Service
Bulletin 747-32-2472, Revision 1, dated February 23, 2006, to identify
an outer cylinder, P/N 65B01382-( ), which was inadvertently omitted
from the original issue of the service bulletin, dated November 30,
2000. We referenced the original service bulletin as the appropriate
source of service information for accomplishing the inspection and
replacement required by the existing AD. (The procedures in Revision 1
are essentially the same as those in the original service bulletin.) P/
N 65B01382-( ) has chrome plating on its inner surface, similar to the
other unsafe parts identified in the original service bulletin and
existing AD. Therefore, P/N 65B01382-( ) is also subject to the same
unsafe condition addressed by the existing AD.
Since P/N 65B01382-( ) was fitted exclusively to Model 747-100,
747-100B, 747-100B SUD, and 747SR series airplanes, this NPRM proposes
to require an additional one-time inspection to determine the P/Ns of
the outer cylinder of the wing landing only on these airplanes. For any
of these airplanes equipped with a load evening system, this NPRM would
also require removal of that system before replacing P/N 65B01382-( )
with a reworked or new, improved part if applicable. We have added that
requirement to paragraphs (h) and (j) of this NPRM. (Paragraph (h) of
the NPRM corresponds to paragraph (c) of the existing AD.)
Relevant Service Information
We have reviewed Revision 1 of Boeing Service Bulletin 747-32-2472.
The service bulletin describes procedures for doing a one-time
inspection to determine the P/N of the outer cylinder of the wing
landing gear. The service bulletin also describes procedures for
replacing the outer cylinder with a reworked or new part and doing
related investigative and corrective actions, if an outer cylinder
having P/N 65B01212-( ), 65B01382-( ), 65B01430-3, or 65B01430-4 is
installed on an airplane. The related investigative actions include the
following:
Doing a nital etch test of the upper inner surface of the
outer cylinder for chrome plating.
Doing a magnetic particle inspection of the outer cylinder
for any cracking.
Doing a nital etch inspection of inner surface of the
outer cylinder for heat damage.
Marking the outer cylinder to indicate that part has been
reworked.
The corrective actions include the following:
Removing any chrome plating found on the upper inner
surface of the outer cylinder.
Reworking the outer cylinder to remove any cracking or
heat damage.
Accomplishing the actions specified in the service information is
intended to adequately address the unsafe condition.
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 airplanes of the
same type design. For this reason, we are proposing this AD, which
would supersede AD 2004-16-05 and would retain the requirements of the
existing AD. This proposed AD would also require accomplishing the
actions specified in the service bulletin described previously, except
as discussed under ``Differences Between the Proposed AD and Service
Bulletin.''
Differences Between the Proposed AD and Service Bulletin
Service Bulletin 747-32-2472, Revision 1, specifies that operators
may accomplish certain related investigative and corrective actions
using an ``approved equivalent procedure.'' However, this proposed AD
would require operators to accomplish the actions using the procedures
specified in a certain chapter(s) of the Boeing 747 SOPM or OHM, as
applicable. An ``approved equivalent procedure'' may be used only if
approved as an alternative method of compliance according to paragraph
(m) of this AD.
Changes to Existing AD
This proposed AD would retain certain requirements of AD 2004-16-
05. Since AD 2004-16-05 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 2004-16-05 this proposed AD
------------------------------------------------------------------------
Paragraph (a)........................... Paragraph (f).
Paragraph (b)........................... Paragraph (g).
Paragraph (c)........................... Paragraph (h).
Paragraph (d)........................... Paragraph (i).
------------------------------------------------------------------------
We have added reference to Revision 1 of Boeing Service Bulletin
747-32-2472 in paragraphs (f) and (g) of this proposed AD, since the
procedures in Revision 1 are essentially the same as those in the
original issue of the service bulletin.
We have revised the ``Alternative Methods of Compliance (AMOCs)''
paragraph in this proposed AD to clarify the delegation authority for
Authorized Representatives for the Boeing Commercial Airplanes
Delegation Option Authorization.
We have also revised this proposed AD 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 1,106 Model 747 airplanes of the affected design in
the worldwide fleet. Of those airplanes, there are about 66 Model 747-
100, 747-100B, 747-100B SUD, and 747SR series airplanes of the affected
design in the worldwide fleet that would be subject to the new proposed
actions. The following table provides the estimated costs, at an
average labor rate of $80 per hour, for U.S. operators to comply with
this proposed AD.
[[Page 35583]]
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Number of U.S.-
Action Work hours Parts Cost per registered Fleet cost
airplane airplanes
----------------------------------------------------------------------------------------------------------------
Inspection for all airplanes 1 None $80 256 $20,480
(required by AD 2004-16-05)....
Removal of the load evening 240 $2,392 21,592 256 5,527,552
system (required by AD 2004-16-
05)............................
Inspection for certain airplanes 1 None 80 21 1,680
(new proposed action)..........
----------------------------------------------------------------------------------------------------------------
If required, the chrome removal and inspections for cracking or
heat damage would take about 12 work hours per airplane, at an average
labor rate of $80 per work hour. Based on these figures, the estimated
cost of these actions is $960 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 39-13761 (69 FR 48359, August 10, 2004) and adding
the following new airworthiness directive (AD):
Boeing: Docket No. FAA-2006-25087; Directorate Identifier 2006-NM-
053-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 2004-16-05.
Applicability
(c) This AD applies to all Boeing Model 747-100, 747-100B, 747-
100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D,
747-400F, 747SR, and 747SP series airplanes, certificated in any
category.
Unsafe Condition
(d) This AD results from identification of an additional unsafe
outer cylinder of the wing landing gear. We are issuing this AD to
prevent fracture of the outer cylinder of the wing landing gear,
which could result in collapse of the wing landing gear.
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 2004-16-05
Inspection to Determine Part Number
(f) Within 36 months after September 14, 2004 (the effective
date of AD 2004-16-05), perform a one-time inspection to determine
the part number (P/N) of the outer cylinder of the wing landing gear
on both sides of the airplane, per the Accomplishment Instructions
of Boeing Service Bulletin 747-32-2472, dated November 30, 2000, or
Revision 1, dated February 23, 2006. Instead of inspecting the outer
cylinder of the wing landing gear, a review of airplane maintenance
records is acceptable if the detailed P/N of the outer cylinder of
the wing landing gear (not just a higher-level assembly) can be
positively determined from that review.
(1) If no outer cylinder having P/N 65B01212-( ) (where ``( )''
is any dash number of that part number), 65B01430-3, or 65B01430-4
is found: No further action is required by this paragraph.
(2) If any outer cylinder having P/N 65B01212-( ) (where ``( )''
is any dash number of that part number), 65B01430-3, or 65B01430-4
is found: Accomplish paragraph (g) of this AD.
Replacement of Outer Cylinder
(g) For any outer cylinder identified in paragraph (f)(2) of
this AD: Within 36 months after September 14, 2004, replace the
outer cylinder on the wing landing gear with a new, improved part or
a part that has been inspected and reworked per the Accomplishment
Instructions of Boeing Service Bulletin 747-32-2472, dated November
30, 2000; or Revision 1, dated February 23, 2006, except as provided
by paragraph (k) of this AD. The rework procedures described in the
service bulletin, if accomplished, include performing a one-time
nital etch inspection of the upper inner surface of the outer
cylinder for chrome plating; removing any chrome plating that is
present; performing a one-time magnetic particle inspection for
cracking of the outer cylinder; performing a nital etch inspection
for heat damage of the outer cylinder; reworking the outer cylinder,
as applicable; and marking the outer cylinder to indicate that the
service bulletin has been accomplished.
Removal of the Load Evening System
(h) For airplanes identified in Boeing Service Bulletin 747-32-
2131, Revision 2, dated March 15, 1974: Before performing the
requirements of paragraph (g) or (j) of this AD, as applicable,
remove the load evening system installed on the wing landing gear,
[[Page 35584]]
per the Accomplishment Instructions of the service bulletin.
New Requirements of This AD
Inspection To Determine Outer Cylinder P/N on Certain Airplanes
(i) For Model 747-100, 747-100B, 747-100B SUD, and 747SR series
airplanes: Within 36 months after the effective date of this AD, do
a one-time inspection to determine the P/N of the outer cylinder of
the wing landing gear on both sides of the airplane, in accordance
with the Accomplishment Instructions of Boeing Service Bulletin 747-
32-2472, Revision 1, dated February 23, 2006. Instead of inspecting
the outer cylinder of the wing landing gear, a review of airplane
maintenance records is acceptable if the detailed P/N of the outer
cylinder of the wing landing gear (not just a higher-level assembly)
can be positively determined from that review.
(1) If no outer cylinder having P/N 65B01382-( ) is found: No
further action is required by this paragraph.
(2) If any outer cylinder having P/N 65B01382-( ) is found:
Accomplish paragraph (j) of this AD.
Replacement of a Certain Outer Cylinder
(j) For any outer cylinder identified in paragraph (i)(2) of
this AD: Within 36 months after the effective date of this AD,
replace the outer cylinder on the wing landing gear with a reworked
or new, improved part, and do the related investigative actions and
all applicable corrective actions before further flight after the
replacement, by accomplishing all of the applicable actions
specified in 3.B.2 and 3.B.3 of the Accomplishment Instructions of
Boeing Service Bulletin 747-32-2472, Revision 1, dated February 23,
2006; except as provided by paragraph (k) of this AD. If applicable,
do the actions specified in paragraph (h) of this AD before
accomplishing the actions specified in this paragraph.
Exception to Revision 1 of the Service Bulletin
(k) Where Service Bulletin 747-32-2472, Revision 1, dated
February 23, 2006, specifies that the related investigative and
corrective actions may be accomplished using an operator's
``equivalent procedure:'' The related investigative and corrective
actions must be accomplished in accordance with the chapter(s) of
the applicable Boeing 747 SOPM or OHM specified in the service
bulletin.
Parts Installation
(l) As of September 14, 2004, no person may install, on any
airplane, an outer cylinder of the wing landing gear if the outer
cylinder has P/N 65B01212-( ), 65B01430-3, or 65B01430-4, unless the
outer cylinder has been inspected, reworked, and marked to indicate
that Boeing Service Bulletin 747-32-2472, dated November 30, 2000,
or Revision 1, dated February 23, 2006, has been accomplished. As of
the effective date of this AD, no person may install an outer
cylinder, P/N 65B01382-( ), of the wing landing gear on any
airplane, unless the outer cylinder has been inspected, reworked,
and marked to indicate that Boeing Service Bulletin 747-32-2472,
Revision 1, dated February 23, 2006, has been accomplished.
Alternative Methods of Compliance (AMOCs)
(m)(1) The Manager, Seattle Aircraft Certification Office (ACO),
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) 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, Seattle ACO, to make those findings. For a repair
method to be approved, the repair must meet the certification basis
of the airplane, and the approval must specifically refer to this
AD.
(4) AMOCs approved previously in accordance with AD 2004-16-05,
amendment 39-13761, are approved as AMOCs for the corresponding
provisions of paragraphs (f), (g), and (h) of this AD.
Issued in Renton, Washington, on June 13, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E6-9721 Filed 6-20-06; 8:45 am]
BILLING CODE 4910-13-P
