Airworthiness Directives; Boeing Model 747 Airplanes, 7883-7887 [E6-2170]
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Federal Register / Vol. 71, No. 31 / Wednesday, February 15, 2006 / Proposed Rules
installation and reidentification requirements
of paragraphs (h)(2) and (i)(2) of this AD.
Condition 2 (Modification ‘‘AS’’ Is Not
Installed)
(i) If modification ‘‘AS’’ is NOT found
installed during the inspection required by
paragraph (g) of this AD, before further flight,
do the actions specified in paragraphs (i)(1),
(i)(2), and (i)(3) of this AD, per McDonnell
Douglas Service Bulletin MD11–34–085,
Revision 01, dated September 20, 1999.
(1) Remove FMC–1 and FMC–2.
(2) Install modification ‘‘AS’’ and new
software, and reidentify FMC–1 and FMC–2
as P/N 4059050–912.
(3) Install modified and reidentified FMC–
1 and FMC–2.
New Requirements of This AD
Upgrade Software/Hardware—Model MD–11
and MD–11F Airplanes
(j) For Model MD–11 and MD–11F
airplanes: Within 18 months after the
effective date of this AD, upgrade the FMC
software, and hardware as applicable, by
doing the applicable actions specified in
paragraph (j)(1), (j)(2), (j)(3), or (j)(4) of this
AD. Doing this upgrade terminates the
requirements of paragraphs (f) through (i) of
this AD.
(1) For airplanes on which FMC P/N
4059050–906 through –912 is installed:
Install new software in the main avionics
rack, and reidentify FMC–1 and FMC–2 as
P/N 4059050–913, in accordance with the
Accomplishment Instructions of Boeing
Service Bulletin MD11–34–130, dated March
16, 2005.
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Note 2: Boeing Service Bulletin MD11–34–
130 refers to Honeywell Alert Service
Bulletin 4059050–34–A6024, dated March 9,
2005, as an additional source of service
information for doing the actions specified in
paragraph (j)(1) of this AD.
(2) For airplanes on which FMC P/N
4059050–920 is installed: Install new
software in the main avionics rack, and
reidentify FMC–1 and FMC–2 as P/N
4059050–921, in accordance with the
Accomplishment Instructions of Boeing
Service Bulletin MD11–34–129, dated
September 22, 2004.
Note 3: Boeing Service Bulletin MD11–34–
129 refers to Honeywell Alert Service
Bulletin 4059050–34–A6023, dated
September 22, 2004, as an additional source
of service information for doing the actions
specified in paragraph (j)(2) of this AD.
(3) For airplanes on which FMC P/N
4059050–906 through –911 is installed: In
lieu of doing the software upgrade specified
in paragraph (j)(1) of this AD, install new
hardware and software and reidentify FMC–
1 and FMC–2 as P/N 4059050–921, by doing
all the applicable actions specified in the
Accomplishment Instructions of McDonnell
Douglas Service Bulletin MD11–34–085,
Revision 01, dated September 20, 1999;
Boeing Service Bulletin MD11–34–068,
Revision 3, dated April 6, 2004; and Boeing
Service Bulletin MD11–34–129, dated
September 22, 2004.
Note 4: McDonnell Douglas Service
Bulletin MD11–34–085 references Honeywell
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Service Bulletin 4059050–34–6020, Revision
1, dated April 30, 1999; Boeing Service
Bulletin MD11–34–068 references Honeywell
Service Bulletin 4059050–34–0010, dated
March 19, 2003; and Boeing Service Bulletin
MD11–34–129 refers to Honeywell Alert
Service Bulletin 4059050–34–A6023, dated
September 22, 2004; as additional sources of
service information for the doing the actions
specified in paragraph (j)(3) of this AD.
(4) For airplanes on which FMC P/N
4059050–912 is installed: In lieu of doing the
software upgrade specified in paragraph (j)(1)
of this AD, install new hardware and
software and reidentify FMC–1 and FMC–2
as P/N 4059050–921, by doing all the
applicable actions specified in the
Accomplishment Instructions of Boeing
Service Bulletin MD11–34–068, Revision 3,
dated April 6, 2004; and Boeing Service
Bulletin MD11–34–129, dated September 22,
2004.
Note 5: Boeing Service Bulletin MD11–34–
068 references Honeywell Service Bulletin
4059050–34–0010, dated March 19, 2003;
and Boeing Service Bulletin MD11–34–129
refers to Honeywell Alert Service Bulletin
4059050–34–A6023, dated September 22,
2004; as additional sources of service
information for the doing the actions
specified in paragraph (j)(4) of this AD.
Upgrade Software—Model MD–10–10F and
MD–10–30F Airplanes
(k) For Model MD–10–10F and MD–10–
30F airplanes: Within 18 months after the
effective date of this AD, install new software
in the main avionics rack and reidentify the
versatile integrated avionics (VIA) digital
computer as P/N 4081580–903, in accordance
with the Accomplishment Instructions of
Boeing Service Bulletin MD10–31–053,
Revision 1, dated June 14, 2005.
Note 6: Boeing Service Bulletin MD10–31–
053 refers to Honeywell Alert Service
Bulletin 4081580–31–A6002, dated January
14, 2005, as an additional source of service
information for doing the actions specified in
paragraph (k) of this AD.
Parts Installation
(l) For Model MD–11 and MD–11F
airplanes: As of the effective date of this AD,
no person may install an FMC, P/N 4059050–
906 through –912, or –920, on any airplane;
except as required by the actions specified in
paragraphs (h), (i), and (j) of this AD.
(m) For MD–10–10F and MD–10–30F
airplanes: As of the effective date of this AD,
no person may install a VIA digital computer,
P/N 4081580–901 or 4081580–902, on any
airplane.
Alternative Methods of Compliance (AMOCs)
(n)(1) The Manager, Los Angeles Aircraft
Certification Office, 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.
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7883
(3) AMOCs approved previously in
accordance with AD 2001–21–05 are
approved as AMOCs for the corresponding
provisions of paragraphs (f) through (i) of this
AD.
(4) Doing the actions required by paragraph
(j) or (k) of this AD, as applicable, is
approved as an AMOC for the actions
required by AD 2004–18–04, amendment 39–
13782.
Issued in Renton, Washington, on February
1, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E6–2176 Filed 2–14–06; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–23921; Directorate
Identifier 2005–NM–205–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 series airplanes. The existing
AD currently requires repetitive
inspections for cracking of the top and
side panel webs and panel stiffeners of
the nose wheel well (NWW), and
corrective actions if necessary. This
proposed AD would reduce the interval
for certain repetitive inspections and
remove a certain optional inspection.
This proposed AD would also require
replacing the NWW side and top panels
with new panels. The replacement
would terminate the repetitive
inspections. This proposed AD results
from the development of a new
modification. We are proposing this AD
to prevent fatigue cracks in the top and
side panel webs and stiffeners of the
NWW, which could compromise the
structural integrity of the NWW and
could lead to the rapid decompression
of the airplane.
DATES: We must receive comments on
this proposed AD by April 3, 2006.
ADDRESSES: Use one of the following
addresses to submit comments on this
proposed AD.
• DOT Docket Web site: Go to
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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: Nick
Kusz, 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–2006–23921;
Directorate Identifier 2005–NM–205–
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
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15:04 Feb 14, 2006
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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 April 13, 2005, we issued AD
2005–09–02, amendment 39–14070 (70
FR 29940, May 25, 2005), for all Boeing
Model 747 series airplanes. That AD
requires repetitive inspections for
cracking of the top and side panel webs
and panel stiffeners of the nose wheel
well (NWW), and corrective actions if
necessary. That AD resulted from a
report of an in-flight decompression of
a Model 747–100 series airplane that
had accumulated 27,241 total flight
cycles. We issued that AD to detect and
correct fatigue cracks in the top and side
panel webs and stiffeners of the NWW,
which could compromise the structural
integrity of the NWW and could lead to
the rapid decompression of the airplane.
Actions Since Existing AD Was Issued
In the preamble to AD 2005–09–02,
we stated that we considered the
requirements ‘‘interim action’’ and were
considering further rulemaking to
reduce certain repetitive inspection
intervals. In addition, we explained that
the manufacturer was developing a
modification and that we would
consider additional rulemaking once the
modification was developed, approved,
and available. We now have determined
that further rulemaking is indeed
necessary, and this proposed AD
follows from that determination.
Relevant Service Information
We have reviewed Boeing Service
Bulletin 747–53A2562, Revision 1,
dated July 28, 2005. The service bulletin
describes procedures for replacing the
NWW side and top panels with new
panels. 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 2005–
09–02 and would continue to require
repetitive inspections for cracking of the
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top and side panel webs and panel
stiffeners of the NWW, and corrective
actions if necessary. This proposed AD
would also reduce the interval for
certain repetitive inspections and would
require replacing the NWW side and top
panels with new panels. The
replacement would terminate the
repetitive inspections. The replacement
would be accomplished in accordance
with the actions specified in the service
information described previously,
except as discussed under ‘‘Differences
Between the Proposed AD and Boeing
Service Bulletin 747–53A2562.’’
Differences Between the Proposed AD
and Boeing Service Bulletin 747–
53A2562
Boeing Service Bulletin 747–
53A2562, Revision 1, dated July 28,
2005, specifies an effectivity of Model
747–100, 747–100B, 747–100B SUD,
747–200B, 747–300, 747–400, 747–
400D, 747SR, and 747SP series
airplanes, line numbers 1 through 1307.
The service bulletin notes that a future
revision will add airplanes with a nose
cargo door, and airplanes after line
number 1307. This proposed AD is
applicable to all Model 747 airplanes.
This proposed AD would require that,
for Model 747 airplanes identified as
Group 1 and 3 in the service bulletin
(Model 747–100, 747–100B, 747–100B
SUD, 747–200B, 747–300, 747–400,
747–400D, 747SR, and 747SP series
airplanes, line numbers 1 through 1307,
except those airplanes modified to the
Special Freighter configuration), the
replacement of the NWW side and top
panels must be done according to the
service bulletin. For all Model 747
airplanes identified as Group 2 in the
service bulletin and airplanes not
identified in the service bulletin, the
replacement must be done according to
a method approved by the FAA.
Explanation of Change to Applicability
We have revised the applicability of
the existing AD to identify model
designations as published in the most
recent type certificate data sheet for the
affected models.
Explanation of Changes Made to
Paragraph (f) of This Proposed AD
We have reduced the repetitive
inspection intervals for Area 3 from
6,000 flight cycles to 1,500 flight cycles
for airplanes on which the inspections
have been done in accordance with
Boeing Alert Service Bulletin (ASB)
747–53A2465, Revision 2, dated
November 11, 2004 (referenced as the
appropriate source of service
information for doing the inspection
specified in paragraph (f)(2)(ii) of the
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existing AD). In addition, we have
removed the optional inspection
specified in paragraph (f)(1)(ii) of the
existing AD; however, we have given
credit for airplanes on which the
inspections have been done in
accordance with Boeing Service Bulletin
747–53A2465, Revision 1, dated
October 16, 2003, for the Area 3
inspections. (Revision 1 was referenced
as the appropriate source of service
information for doing the inspection
specified in paragraph (f)(1)(ii) of the
existing AD with a repetitive inspection
interval of 1,000 flight cycles.)
Since issuance of Boeing ASB 747–
53A2465, Revision 2, Boeing has
received additional reports of cracking
and has done additional analysis to
determine the flight-cycle interval. The
1,500 flight-cycle interval for Area 3
specified in the proposed AD matches
the interval specified in Boeing ASB
747–53A2465, Revision 4, dated
February 24, 2005 (referenced as the
appropriate source of service
information for doing the new
requirements of the existing AD). We
have determined that the 1,500 flightcycle interval will ensure an acceptable
level of safety.
We also removed paragraphs (f)(1)(i)
and (f)(2)(i) of the existing AD because
all operators will be doing the
inspections of the top and sidewall
panel webs specified in paragraph (g) of
the existing AD. The inspections
specified in paragraph (g) of the existing
AD terminate the inspections of the top
and side panel webs specified in
paragraphs (f)(1)(i) and (f)(2)(i) of the
existing AD. Therefore we do not need
to restate paragraphs (f)(1)(i) and (f)(2)(i)
in the proposed AD.
Explanation of Change Made to This
Proposed AD
We have simplified paragraph (l) of
this proposed AD by referring to the
‘‘Alternative Methods of Compliance
7885
(AMOCs)’’ paragraph of this proposed
AD for repair methods and we have
revised the AMOCs paragraph in this
proposed AD to clarify the delegation
authority for Authorized
Representatives for the Boeing
Commercial Airplanes Delegation
Option Authorization.
Clarification of 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 1,127 airplanes of the
affected design in the worldwide fleet.
The following table provides the
estimated costs for U.S. operators to
comply with this proposed AD. Work
hours are estimated at an average labor
rate of $65 per work hour.
ESTIMATED COSTS
Action
Work hours
Area 1 and 3 inspections (required by AD 2005–09–02).
Area 2 inspections (required
by AD 2005–09–02).
Replacement (new proposed
action).
$0
$5,135, per inspection cycle ..
255
8–18
0
255
800
115,765
$520–$1,170, per inspection
cycle.
$167,765 ................................
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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
15:04 Feb 14, 2006
Number of
U.S.-registered
airplanes
79
Authority for This Rulemaking
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Cost per
airplane
Parts
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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.
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255
Fleet cost
$1,309,425, per inspection
cycle.
Up to $298,350, per inspection cycle.
$42,780,075.
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 39–14070 (70
FR 29940, May 25, 2005) and adding the
following new airworthiness directive
(AD):
Boeing: Docket No. FAA–2006–23921;
Directorate Identifier 2005–NM–205–AD.
Comments Due Date
(a) The FAA must receive comments on
this AD action by April 3, 2006.
Affected ADs
(b) This AD supersedes AD 2005–09–02.
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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 the development
of a new modification. We are issuing this
AD to prevent fatigue cracks in the top and
side panel webs and stiffeners of the nose
wheel well (NWW), which could
compromise the structural integrity of the
NWW and lead to the rapid decompression
of the airplane.
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 2005–
09–02 With New Repetitive Interval and
Service Information
Initial and Repetitive Inspections of the Top
and Side Panel Stiffeners
(f) Prior to the accumulation of 16,000 total
flight cycles, or within 1,000 flight cycles
after January 27, 2005 (the effective date of
AD 2004–25–23, amendment 39–13911),
whichever is later, do internal detailed and
surface high frequency eddy current (HFEC)
inspections of the top and side panel
stiffeners of the NWW (specified as Area 3 in
the service bulletin) for cracks in accordance
with the Accomplishment Instructions of
Boeing Alert Service Bulletin (ASB) 747–
53A2465, Revision 4, dated February 25,
2005. Repeat the inspections thereafter at the
compliance times specified in paragraph
(f)(1) or (f)(2) of this AD, as applicable.
(1) For airplanes on which an inspection
has not been done before the effective date
of this AD in accordance with any service
bulletin listed in Table 1 of this AD: Within
1,500 flight cycles after doing the inspection
specified in paragraph (f) of this AD, repeat
the inspection. Repeat the inspection
thereafter at intervals not to exceed 1,500
flight cycles.
(2) For airplanes on which an inspection
has been done before the effective date of this
AD in accordance with any service bulletin
listed in Table 1 of this AD: Within 6,000
flight cycles after doing the inspection
specified in paragraph (f) of this AD or
within 1,500 flight cycles after the effective
date of this AD, whichever occurs first,
repeat the inspection. Repeat the inspection
thereafter at intervals not to exceed 1,500
flight cycles.
TABLE 1.—BOEING SERVICE BULLETINS
Service bulletin
Boeing
Boeing
Boeing
Boeing
Boeing
Revision level
(1)
1
2
3
4
ASB 747–53A2465 .................................................................................................................
Service Bulletin 747–53A2465 ...............................................................................................
ASB 747–53A2465 .................................................................................................................
ASB 747–53A2465 .................................................................................................................
ASB 747–53A2465 .................................................................................................................
Date
April 5, 2001.
October 16, 2003.
November 11, 2004.
December 23, 2004.
February 25, 2005.
1 Original.
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Note 1: For the purposes of this AD, a
detailed inspection is defined as: ‘‘An
intensive visual examination of a specific
structural area, system, installation, or
assembly to detect damage, failure, or
irregularity. Available lighting is normally
supplemented with a direct source of good
lighting at intensity deemed appropriate by
the inspector. Inspection aids such as
mirrors, magnifying lenses, etc., may be used.
Surface cleaning and elaborate access
procedures may be required.’’
Initial Inspections of the Top and Sidewall
Panel Webs
(g) Do an external detailed inspection of
the top and sidewall panel webs of the NWW
(specified as Area 1 and Area 2 in the service
bulletin) for cracks, in accordance with the
Accomplishment Instructions of Boeing ASB
747–53A2465, Revision 4, dated February 24,
2005, at the earlier of the times specified in
paragraphs (g)(1) and (g)(2) of this AD.
(1) At the later of the times specified in
paragraph (g)(1)(i) and (g)(1)(ii) of this AD:
(i) Before accumulating 20,000 total flight
cycles.
(ii) Within 100 flight cycles or 90 days after
May 10, 2005 (the effective date of AD 2005–
09–02), whichever occurs first.
(2) At the later of the times specified in
paragraphs (g)(2)(i) and (g)(2)(ii) of this AD:
(i) Before accumulating 16,000 total flight
cycles.
(ii) Within 1,000 flight cycles after May 10,
2005.
Repetitive Inspections of the Top and
Sidewall Panel Webs
(h) Repeat the inspection required by
paragraph (g) of this AD at the intervals
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specified in paragraphs (h)(1) and (h)(2) of
this AD, as applicable.
(1) For airplanes with fewer than 20,000
total flight cycles as of May 10, 2005, repeat
at intervals not to exceed 1,000 flight cycles
until the first inspection after the airplane
reaches 20,000 total flight cycles.
(2) For airplanes with 20,000 total flight
cycles or more, repeat at intervals not to
exceed 500 flight cycles.
Ultrasonic Inspections (UT)
(i) Do a UT inspection of the top and
sidewall panel webs for cracks, in accordance
with Boeing ASB 747–53A2465, Revision 4,
dated February 24, 2005, at the later of the
times specified in paragraphs (i)(1) and (i)(2)
of this AD. Repeat the inspections thereafter
at intervals not to exceed 500 flight cycles.
(1) Prior to the accumulation of 20,000
total flight cycles.
(2) Within 100 flight cycles or 90 days after
May 10, 2005, whichever occurs first.
Additional Inspections and Corrective
Actions
(j) Except as specified in paragraph (l) of
this AD, if any crack is found during any
inspection required by this AD, prior to
further flight, do any applicable additional
detailed inspections of stiffeners and beams
and make repairs, in accordance with the
Accomplishment Instructions of Boeing ASB
747–53A2465, Revision 4, dated February 24,
2005.
Actions Accomplished Per Previous Issues of
Service Bulletin
(k) The actions specified in paragraphs
(k)(1), (k)(2), and (k)(3) of this AD are
acceptable for compliance with the
PO 00000
Frm 00013
Fmt 4702
Sfmt 4702
corresponding action specified in the
applicable paragraph.
(1) Inspections and corrective actions
accomplished before January 27, 2005, in
accordance with Boeing ASB 747–53A2465,
dated April 5, 2001, are considered
acceptable for compliance with the
corresponding inspections specified in
paragraph (f) of this AD.
(2) Inspections accomplished before the
effective date of this AD, in accordance with
Boeing Service Bulletin 747–53A2465,
Revision 1, dated October 16, 2003; Boeing
ASB 747–53A2465, Revision 2, dated
November 11, 2004; and Boeing ASB 747–
53A2465, Revision 3, dated December 23,
2004; are considered acceptable for
compliance with the corresponding
inspections specified in paragraph (f) of this
AD.
Note 2: The detailed and surface HFEC
inspections of the top and side panel
stiffeners of the NWW specified in Boeing
ASB 747–53A2465, dated April 5, 2001; and
Boeing Service Bulletin 747–53A2465,
Revision 1, dated October 16, 2003; are
acceptable for compliance with the internal
detailed and surface HFEC inspections
specified in paragraph (f) of this AD.
(3) Inspections and corrective actions
accomplished before May 10, 2005, in
accordance with Boeing Service Bulletin
747–53A2465, Revision 1, dated October 16,
2003; Boeing ASB 747–53A2465, Revision 2,
dated November 11, 2004; and Boeing ASB
747–53A2465, Revision 3, dated December
23, 2004; are considered acceptable for
compliance with the corresponding
inspections specified in paragraphs (g) and
(h) of this AD.
E:\FR\FM\15FEP1.SGM
15FEP1
Federal Register / Vol. 71, No. 31 / Wednesday, February 15, 2006 / Proposed Rules
Certain Other Corrective Actions
(l) Where Boeing ASB 747–53A2465
specifies contacting the manufacturer if
certain cracking is found, this AD requires,
before further flight, repairing the cracking
using a method approved in accordance with
the procedures specified in paragraph (p) of
this AD.
Issued in Renton, Washington, on January
26, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E6–2170 Filed 2–14–06; 8:45 am]
BILLING CODE 4910–13–P
No Reporting Requirement
(m) Although Boeing ASB 747–53A2465
specifies that operators should report
inspection results to the manufacturer, this
AD does not require those inspection results
to be reported.
DEPARTMENT OF TRANSPORTATION
New Requirements of This AD
[Docket No. FAA–2005–22857; Airspace
Docket No. 05–AAL–37]
Terminating Action
(n) For Group 1 and 3 airplanes identified
in Boeing Service Bulletin 747–53A2562,
Revision 1, dated July 28, 2005: Before
accumulating 22,000 total flight cycles or
within 48 months after the effective date of
this AD, whichever occurs later, replace the
NWW side and top panels with new panels
in accordance with the Accomplishment
Instructions of Boeing Service Bulletin 747–
53A2562, Revision 1, dated July 28, 2005.
Doing the replacement terminates the
requirements of this AD.
(o) For Group 2 airplanes identified in
Boeing Service Bulletin 747–53A2562,
Revision 1, dated July 28, 2005, and Model
747 airplanes not identified in the service
bulletin: Before accumulating 22,000 total
flight cycles or within 48 months after the
effective date of this AD, whichever occurs
later, replace the NWW side and top panels
using a method approved by the Manager,
Seattle Aircraft Certification Office (ACO),
FAA. Doing the replacement terminates the
requirements of this AD.
cprice-sewell on PROD1PC66 with PROPOSALS
Alternative Methods of Compliance (AMOCs)
(p)(1) The Manager, Seattle 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.
(4) AMOCs approved previously according
to AD 2005–09–02, amendment 39–14070,
are approved as AMOCs for the
corresponding provisions of paragraphs (f)
through (j) and (l) of this AD.
(5) AMOCs approved previously according
to AD 2004–25–23, amendment 39–13911,
are approved as AMOCs for the
corresponding provisions of paragraph (f) of
this AD.
VerDate Aug<31>2005
15:04 Feb 14, 2006
Jkt 208001
Federal Aviation Administration
14 CFR Part 71
Proposed Establishment of Class E
Airspace; Galbraith Lake, AK
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking.
AGENCY:
SUMMARY: This action proposes to
establish Class E airspace at Galbraith
Lake, AK. Two Standard Instrument
Approach Procedures (SIAPs) are being
published for the Galbraith Lake
Airport. Adoption of this proposal
would result in establishment of Class E
airspace upward from 700 feet (ft.)
above the surface at Galbraith Lake, AK.
DATES: Comments must be received on
or before April 3, 2006.
ADDRESSES: Send comments on the
proposal to the Docket Management
System, U.S. Department of
Transportation, Room Plaza 401, 400
Seventh Street, SW., Washington, DC
20590–0001. You must identify the
docket number FAA–2005–22857/
Airspace Docket No. 05–AAL–37, at the
beginning of your comments. You may
also submit comments on the Internet at
https://dms.dot.gov. You may review the
public docket containing the proposal,
any comments received, and any final
disposition in person in the Dockets
Office between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal
holidays. The Docket Office (telephone
1–800–647–5527) is on the plaza level
of the Department of Transportation
NASSIF Building at the above address.
An informal docket may also be
examined during normal business hours
at the office of the Manager, Safety,
Alaska Flight Service Operations,
Federal Aviation Administration, 222
West 7th Avenue, Box 14, Anchorage,
AK 99513–7587.
FOR FURTHER INFORMATION CONTACT: Gary
Rolf, Federal Aviation Administration,
222 West 7th Avenue, Box 14,
Anchorage, AK 99513–7587; telephone
number (907) 271–5898; fax: (907) 271–
2850; e-mail: gary.ctr.rolf@faa.gov.
PO 00000
Frm 00014
Fmt 4702
Sfmt 4702
7887
Internet address: https://
www.alaska.faa.gov/at.
SUPPLEMENTARY INFORMATION:
Comments Invited
Interested parties are invited to
participate in this proposed rulemaking
by submitting such written data, views,
or arguments as they may desire.
Comments that provide the factual basis
supporting the views and suggestions
presented are particularly helpful in
developing reasoned regulatory
decisions on the proposal. Comments
are specifically invited on the overall
regulatory, aeronautical, economic,
environmental, and energy-related
aspects of the proposal.
Communications should identify both
docket numbers and be submitted in
triplicate to the address listed above.
Commenters wishing the FAA to
acknowledge receipt of their comments
on this notice must submit with those
comments a self-addressed, stamped
postcard on which the following
statement is made: ‘‘Comments to
Docket No. FAA–2005–22857/Airspace
Docket No. 05–AAL–37.’’ The postcard
will be date/time stamped and returned
to the commenter.
All communications received on or
before the specified closing date for
comments will be considered before
taking action on the proposed rule. The
proposal contained in this notice may
be changed in light of comments
received. All comments submitted will
be available for examination in the
public docket both before and after the
closing date for comments. A report
summarizing each substantive public
contact with FAA personnel concerned
with this rulemaking will be filed in the
docket.
Availability of Notice of Proposed
Rulemakings (NPRMs)
An electronic copy of this document
may be downloaded through the
Internet at https://dms.dot.gov. Recently
published rulemaking documents can
also be accessed through the FAA’s Web
page at https://www.faa.gov or the
Superintendent of Document’s Web
page at https://www.access.gpo.gov/nara.
Additionally, any person may obtain
a copy of this notice by submitting a
request to the Federal Aviation
Administration, Office of Air Traffic
Airspace Management, ATA–400, 800
Independence Avenue, SW.,
Washington, DC 20591 or by calling
(202) 267–8783. Communications must
identify both docket numbers for this
notice. Persons interested in being
placed on a mailing list for future
NPRM’s should contact the FAA’s
Office of Rulemaking, (202) 267–9677,
E:\FR\FM\15FEP1.SGM
15FEP1
]]>Agencies
[Federal Register Volume 71, Number 31 (Wednesday, February 15, 2006)]
[Proposed Rules]
[Pages 7883-7887]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-2170]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-23921; Directorate Identifier 2005-NM-205-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 series airplanes.
The existing AD currently requires repetitive inspections for cracking
of the top and side panel webs and panel stiffeners of the nose wheel
well (NWW), and corrective actions if necessary. This proposed AD would
reduce the interval for certain repetitive inspections and remove a
certain optional inspection. This proposed AD would also require
replacing the NWW side and top panels with new panels. The replacement
would terminate the repetitive inspections. This proposed AD results
from the development of a new modification. We are proposing this AD to
prevent fatigue cracks in the top and side panel webs and stiffeners of
the NWW, which could compromise the structural integrity of the NWW and
could lead to the rapid decompression of the airplane.
DATES: We must receive comments on this proposed AD by April 3, 2006.
ADDRESSES: Use one of the following addresses to submit comments on
this proposed AD.
DOT Docket Web site: Go to
[[Page 7884]]
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: Nick Kusz, 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-2006-23921; Directorate Identifier 2005-NM-205-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 April 13, 2005, we issued AD 2005-09-02, amendment 39-14070 (70
FR 29940, May 25, 2005), for all Boeing Model 747 series airplanes.
That AD requires repetitive inspections for cracking of the top and
side panel webs and panel stiffeners of the nose wheel well (NWW), and
corrective actions if necessary. That AD resulted from a report of an
in-flight decompression of a Model 747-100 series airplane that had
accumulated 27,241 total flight cycles. We issued that AD to detect and
correct fatigue cracks in the top and side panel webs and stiffeners of
the NWW, which could compromise the structural integrity of the NWW and
could lead to the rapid decompression of the airplane.
Actions Since Existing AD Was Issued
In the preamble to AD 2005-09-02, we stated that we considered the
requirements ``interim action'' and were considering further rulemaking
to reduce certain repetitive inspection intervals. In addition, we
explained that the manufacturer was developing a modification and that
we would consider additional rulemaking once the modification was
developed, approved, and available. We now have determined that further
rulemaking is indeed necessary, and this proposed AD follows from that
determination.
Relevant Service Information
We have reviewed Boeing Service Bulletin 747-53A2562, Revision 1,
dated July 28, 2005. The service bulletin describes procedures for
replacing the NWW side and top panels with new panels. 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 2005-09-02 and would continue to require repetitive
inspections for cracking of the top and side panel webs and panel
stiffeners of the NWW, and corrective actions if necessary. This
proposed AD would also reduce the interval for certain repetitive
inspections and would require replacing the NWW side and top panels
with new panels. The replacement would terminate the repetitive
inspections. The replacement would be accomplished in accordance with
the actions specified in the service information described previously,
except as discussed under ``Differences Between the Proposed AD and
Boeing Service Bulletin 747-53A2562.''
Differences Between the Proposed AD and Boeing Service Bulletin 747-
53A2562
Boeing Service Bulletin 747-53A2562, Revision 1, dated July 28,
2005, specifies an effectivity of Model 747-100, 747-100B, 747-100B
SUD, 747-200B, 747-300, 747-400, 747-400D, 747SR, and 747SP series
airplanes, line numbers 1 through 1307. The service bulletin notes that
a future revision will add airplanes with a nose cargo door, and
airplanes after line number 1307. This proposed AD is applicable to all
Model 747 airplanes. This proposed AD would require that, for Model 747
airplanes identified as Group 1 and 3 in the service bulletin (Model
747-100, 747-100B, 747-100B SUD, 747-200B, 747-300, 747-400, 747-400D,
747SR, and 747SP series airplanes, line numbers 1 through 1307, except
those airplanes modified to the Special Freighter configuration), the
replacement of the NWW side and top panels must be done according to
the service bulletin. For all Model 747 airplanes identified as Group 2
in the service bulletin and airplanes not identified in the service
bulletin, the replacement must be done according to a method approved
by the FAA.
Explanation of Change to Applicability
We have revised the applicability of the existing AD to identify
model designations as published in the most recent type certificate
data sheet for the affected models.
Explanation of Changes Made to Paragraph (f) of This Proposed AD
We have reduced the repetitive inspection intervals for Area 3 from
6,000 flight cycles to 1,500 flight cycles for airplanes on which the
inspections have been done in accordance with Boeing Alert Service
Bulletin (ASB) 747-53A2465, Revision 2, dated November 11, 2004
(referenced as the appropriate source of service information for doing
the inspection specified in paragraph (f)(2)(ii) of the
[[Page 7885]]
existing AD). In addition, we have removed the optional inspection
specified in paragraph (f)(1)(ii) of the existing AD; however, we have
given credit for airplanes on which the inspections have been done in
accordance with Boeing Service Bulletin 747-53A2465, Revision 1, dated
October 16, 2003, for the Area 3 inspections. (Revision 1 was
referenced as the appropriate source of service information for doing
the inspection specified in paragraph (f)(1)(ii) of the existing AD
with a repetitive inspection interval of 1,000 flight cycles.)
Since issuance of Boeing ASB 747-53A2465, Revision 2, Boeing has
received additional reports of cracking and has done additional
analysis to determine the flight-cycle interval. The 1,500 flight-cycle
interval for Area 3 specified in the proposed AD matches the interval
specified in Boeing ASB 747-53A2465, Revision 4, dated February 24,
2005 (referenced as the appropriate source of service information for
doing the new requirements of the existing AD). We have determined that
the 1,500 flight-cycle interval will ensure an acceptable level of
safety.
We also removed paragraphs (f)(1)(i) and (f)(2)(i) of the existing
AD because all operators will be doing the inspections of the top and
sidewall panel webs specified in paragraph (g) of the existing AD. The
inspections specified in paragraph (g) of the existing AD terminate the
inspections of the top and side panel webs specified in paragraphs
(f)(1)(i) and (f)(2)(i) of the existing AD. Therefore we do not need to
restate paragraphs (f)(1)(i) and (f)(2)(i) in the proposed AD.
Explanation of Change Made to This Proposed AD
We have simplified paragraph (l) of this proposed AD by referring
to the ``Alternative Methods of Compliance (AMOCs)'' paragraph of this
proposed AD for repair methods and we have revised the AMOCs paragraph
in this proposed AD to clarify the delegation authority for Authorized
Representatives for the Boeing Commercial Airplanes Delegation Option
Authorization.
Clarification of 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 1,127 airplanes of the affected design in the
worldwide fleet. The following table provides the estimated costs for
U.S. operators to comply with this proposed AD. Work hours are
estimated at an average labor rate of $65 per work hour.
Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Number of U.S.-
Action Work hours Parts Cost per airplane registered Fleet cost
airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Area 1 and 3 inspections (required 79 $0 $5,135, per inspection 255 $1,309,425, per inspection cycle.
by AD 2005-09-02). cycle.
Area 2 inspections (required by AD 8-18 0 $520-$1,170, per 255 Up to $298,350, per inspection cycle.
2005-09-02). inspection cycle.
Replacement (new proposed action).. 800 115,765 $167,765.................. 255 $42,780,075.
--------------------------------------------------------------------------------------------------------------------------------------------------------
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 39-14070 (70 FR 29940, May 25, 2005) and adding the
following new airworthiness directive (AD):
Boeing: Docket No. FAA-2006-23921; Directorate Identifier 2005-NM-
205-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by April 3,
2006.
Affected ADs
(b) This AD supersedes AD 2005-09-02.
[[Page 7886]]
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 the development of a new modification.
We are issuing this AD to prevent fatigue cracks in the top and side
panel webs and stiffeners of the nose wheel well (NWW), which could
compromise the structural integrity of the NWW and lead to the rapid
decompression of the airplane.
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 2005-09-02 With New Repetitive
Interval and Service Information
Initial and Repetitive Inspections of the Top and Side Panel
Stiffeners
(f) Prior to the accumulation of 16,000 total flight cycles, or
within 1,000 flight cycles after January 27, 2005 (the effective
date of AD 2004-25-23, amendment 39-13911), whichever is later, do
internal detailed and surface high frequency eddy current (HFEC)
inspections of the top and side panel stiffeners of the NWW
(specified as Area 3 in the service bulletin) for cracks in
accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin (ASB) 747-53A2465, Revision 4, dated February 25,
2005. Repeat the inspections thereafter at the compliance times
specified in paragraph (f)(1) or (f)(2) of this AD, as applicable.
(1) For airplanes on which an inspection has not been done
before the effective date of this AD in accordance with any service
bulletin listed in Table 1 of this AD: Within 1,500 flight cycles
after doing the inspection specified in paragraph (f) of this AD,
repeat the inspection. Repeat the inspection thereafter at intervals
not to exceed 1,500 flight cycles.
(2) For airplanes on which an inspection has been done before
the effective date of this AD in accordance with any service
bulletin listed in Table 1 of this AD: Within 6,000 flight cycles
after doing the inspection specified in paragraph (f) of this AD or
within 1,500 flight cycles after the effective date of this AD,
whichever occurs first, repeat the inspection. Repeat the inspection
thereafter at intervals not to exceed 1,500 flight cycles.
Table 1.--Boeing Service Bulletins
----------------------------------------------------------------------------------------------------------------
Service bulletin Revision level Date
----------------------------------------------------------------------------------------------------------------
Boeing ASB 747-53A2465....................... (\1\) April 5, 2001.
Boeing Service Bulletin 747-53A2465.......... 1 October 16, 2003.
Boeing ASB 747-53A2465....................... 2 November 11, 2004.
Boeing ASB 747-53A2465....................... 3 December 23, 2004.
Boeing ASB 747-53A2465....................... 4 February 25, 2005.
----------------------------------------------------------------------------------------------------------------
\1\ Original.
Note 1: For the purposes of this AD, a detailed inspection is
defined as: ``An intensive visual examination of a specific
structural area, system, installation, or assembly to detect damage,
failure, or irregularity. Available lighting is normally
supplemented with a direct source of good lighting at intensity
deemed appropriate by the inspector. Inspection aids such as
mirrors, magnifying lenses, etc., may be used. Surface cleaning and
elaborate access procedures may be required.''
Initial Inspections of the Top and Sidewall Panel Webs
(g) Do an external detailed inspection of the top and sidewall
panel webs of the NWW (specified as Area 1 and Area 2 in the service
bulletin) for cracks, in accordance with the Accomplishment
Instructions of Boeing ASB 747-53A2465, Revision 4, dated February
24, 2005, at the earlier of the times specified in paragraphs (g)(1)
and (g)(2) of this AD.
(1) At the later of the times specified in paragraph (g)(1)(i)
and (g)(1)(ii) of this AD:
(i) Before accumulating 20,000 total flight cycles.
(ii) Within 100 flight cycles or 90 days after May 10, 2005 (the
effective date of AD 2005-09-02), whichever occurs first.
(2) At the later of the times specified in paragraphs (g)(2)(i)
and (g)(2)(ii) of this AD:
(i) Before accumulating 16,000 total flight cycles.
(ii) Within 1,000 flight cycles after May 10, 2005.
Repetitive Inspections of the Top and Sidewall Panel Webs
(h) Repeat the inspection required by paragraph (g) of this AD
at the intervals specified in paragraphs (h)(1) and (h)(2) of this
AD, as applicable.
(1) For airplanes with fewer than 20,000 total flight cycles as
of May 10, 2005, repeat at intervals not to exceed 1,000 flight
cycles until the first inspection after the airplane reaches 20,000
total flight cycles.
(2) For airplanes with 20,000 total flight cycles or more,
repeat at intervals not to exceed 500 flight cycles.
Ultrasonic Inspections (UT)
(i) Do a UT inspection of the top and sidewall panel webs for
cracks, in accordance with Boeing ASB 747-53A2465, Revision 4, dated
February 24, 2005, at the later of the times specified in paragraphs
(i)(1) and (i)(2) of this AD. Repeat the inspections thereafter at
intervals not to exceed 500 flight cycles.
(1) Prior to the accumulation of 20,000 total flight cycles.
(2) Within 100 flight cycles or 90 days after May 10, 2005,
whichever occurs first.
Additional Inspections and Corrective Actions
(j) Except as specified in paragraph (l) of this AD, if any
crack is found during any inspection required by this AD, prior to
further flight, do any applicable additional detailed inspections of
stiffeners and beams and make repairs, in accordance with the
Accomplishment Instructions of Boeing ASB 747-53A2465, Revision 4,
dated February 24, 2005.
Actions Accomplished Per Previous Issues of Service Bulletin
(k) The actions specified in paragraphs (k)(1), (k)(2), and
(k)(3) of this AD are acceptable for compliance with the
corresponding action specified in the applicable paragraph.
(1) Inspections and corrective actions accomplished before
January 27, 2005, in accordance with Boeing ASB 747-53A2465, dated
April 5, 2001, are considered acceptable for compliance with the
corresponding inspections specified in paragraph (f) of this AD.
(2) Inspections accomplished before the effective date of this
AD, in accordance with Boeing Service Bulletin 747-53A2465, Revision
1, dated October 16, 2003; Boeing ASB 747-53A2465, Revision 2, dated
November 11, 2004; and Boeing ASB 747-53A2465, Revision 3, dated
December 23, 2004; are considered acceptable for compliance with the
corresponding inspections specified in paragraph (f) of this AD.
Note 2: The detailed and surface HFEC inspections of the top and
side panel stiffeners of the NWW specified in Boeing ASB 747-
53A2465, dated April 5, 2001; and Boeing Service Bulletin 747-
53A2465, Revision 1, dated October 16, 2003; are acceptable for
compliance with the internal detailed and surface HFEC inspections
specified in paragraph (f) of this AD.
(3) Inspections and corrective actions accomplished before May
10, 2005, in accordance with Boeing Service Bulletin 747-53A2465,
Revision 1, dated October 16, 2003; Boeing ASB 747-53A2465, Revision
2, dated November 11, 2004; and Boeing ASB 747-53A2465, Revision 3,
dated December 23, 2004; are considered acceptable for compliance
with the corresponding inspections specified in paragraphs (g) and
(h) of this AD.
[[Page 7887]]
Certain Other Corrective Actions
(l) Where Boeing ASB 747-53A2465 specifies contacting the
manufacturer if certain cracking is found, this AD requires, before
further flight, repairing the cracking using a method approved in
accordance with the procedures specified in paragraph (p) of this
AD.
No Reporting Requirement
(m) Although Boeing ASB 747-53A2465 specifies that operators
should report inspection results to the manufacturer, this AD does
not require those inspection results to be reported.
New Requirements of This AD
Terminating Action
(n) For Group 1 and 3 airplanes identified in Boeing Service
Bulletin 747-53A2562, Revision 1, dated July 28, 2005: Before
accumulating 22,000 total flight cycles or within 48 months after
the effective date of this AD, whichever occurs later, replace the
NWW side and top panels with new panels in accordance with the
Accomplishment Instructions of Boeing Service Bulletin 747-53A2562,
Revision 1, dated July 28, 2005. Doing the replacement terminates
the requirements of this AD.
(o) For Group 2 airplanes identified in Boeing Service Bulletin
747-53A2562, Revision 1, dated July 28, 2005, and Model 747
airplanes not identified in the service bulletin: Before
accumulating 22,000 total flight cycles or within 48 months after
the effective date of this AD, whichever occurs later, replace the
NWW side and top panels using a method approved by the Manager,
Seattle Aircraft Certification Office (ACO), FAA. Doing the
replacement terminates the requirements of this AD.
Alternative Methods of Compliance (AMOCs)
(p)(1) The Manager, Seattle 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.
(4) AMOCs approved previously according to AD 2005-09-02,
amendment 39-14070, are approved as AMOCs for the corresponding
provisions of paragraphs (f) through (j) and (l) of this AD.
(5) AMOCs approved previously according to AD 2004-25-23,
amendment 39-13911, are approved as AMOCs for the corresponding
provisions of paragraph (f) of this AD.
Issued in Renton, Washington, on January 26, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E6-2170 Filed 2-14-06; 8:45 am]
BILLING CODE 4910-13-P
