Airworthiness Directives; Boeing Model 747 Airplanes, 12125-12129 [06-2144]
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Federal Register / Vol. 71, No. 46 / Thursday, March 9, 2006 / Rules and Regulations
surface and the jam nut of the sump
drain valve assembly.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comment received. The
commenter, Boeing, supports the
NPRM.
Conclusion
We have carefully reviewed the
available data, including the comment
received, and determined that air safety
and the public interest require adopting
the AD as proposed.
Costs of Compliance
There are about 88 airplanes of the
affected design in the worldwide fleet.
This AD affects about 22 airplanes of
U.S. registry. The required actions will
take about 4 work hours per airplane, at
an average labor rate of $65 per work
hour. Required parts will cost about
$360 per airplane. Based on these
figures, the estimated cost of the AD for
U.S. operators is $13,640, or $620 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.
hsrobinson on PROD1PC70 with RULES
Regulatory Findings
We have determined that this AD will
not have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
the States, on the relationship between
the national government and the States,
or on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
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Jkt 208001
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
(2) Is not a ‘‘significant rule’’ under
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
(3) Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared a regulatory evaluation
of the estimated costs to comply with
this AD and placed it in the AD docket.
See the ADDRESSES section for a location
to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
I
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by adding the following new
airworthiness directive (AD):
I
2006–05–08 Boeing: Amendment 39–14505.
Docket No. FAA–2005–23357;
Directorate Identifier 2005–NM–207–AD.
Effective Date
(a) This AD becomes effective April 13,
2006.
Affected ADs
(b) None.
12125
Installation
(f) Within 60 months after the effective
date of this AD, install a new washer between
the lower wing surface and the jam nut of the
sump drain valve assembly in both wings, in
accordance with the Accomplishment
Instructions of Boeing Special Attention
Service Bulletin 777–28–0045, dated
September 1, 2005.
Alternative Methods of Compliance
(AMOCs)
(g)(1) The Manager, Seattle 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.
Material Incorporated by Reference
(h) You must use Boeing Special Attention
Service Bulletin 777–28–0045, dated
September 1, 2005, to perform the actions
that are required by this AD, unless the AD
specifies otherwise. The Director of the
Federal Register approved the incorporation
by reference of this document in accordance
with 5 U.S.C. 552(a) and 1 CFR part 51.
Contact Boeing Commercial Airplanes, P.O.
Box 3707, Seattle, Washington 98124–2207,
for a copy of this service information. You
may review copies at the Docket Management
Facility, U.S. Department of Transportation,
400 Seventh Street SW., room PL–401, Nassif
Building, Washington, DC; on the Internet at
https://dms.dot.gov; or at the National
Archives and Records Administration
(NARA). For information on the availability
of this material at the NARA, call (202) 741–
6030, or go to https://www.archives.gov/
federal_register/code_of_federal_regulations/
ibr_locations.html.
Issued in Renton, Washington, on February
27, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 06–2143 Filed 3–8–06; 8:45 am]
Applicability
(c) This AD applies to Boeing Model 777–
200 series airplanes, certificated in any
category; as identified in Boeing Special
Attention Service Bulletin 777–28–0045,
dated September 1, 2005.
BILLING CODE 4910–13–P
Unsafe Condition
(d) This AD results from fuel system
reviews conducted by the manufacturer. We
are issuing this AD to prevent energy from a
lightning strike on the bushing for the sump
drain valve from arcing to the inside of the
center fuel tank wall, which could create an
ignition source in the fuel tank and result in
a fuel tank explosion.
14 CFR Part 39
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.
AGENCY:
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
[Docket No. FAA–2005–22715; Directorate
Identifier 2005–NM–108–AD; Amendment
39–14503; AD 2006–05–06]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 747 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
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Federal Register / Vol. 71, No. 46 / Thursday, March 9, 2006 / Rules and Regulations
SUMMARY: The FAA is superseding three
existing airworthiness directives (ADs)
that apply to certain Boeing Model 747
airplanes. The existing ADs currently
require repetitive inspections of the
body station (BS) 2598 bulkhead, and
corrective action if necessary. This new
AD adds a requirement to modify the
bulkhead, including a one-time
inspection and corrective action if
necessary, which terminates certain
repetitive inspections. This AD also
requires a post-modification inspection
of the modified area. This AD results
from new reports of cracking in all three
areas that require inspection in
accordance with the existing ADs. We
are issuing this AD to prevent fatigue
cracking of the BS 2598 bulkhead
structure, which could result in
inability of the structure to carry
horizontal stabilizer flight loads, and
loss of controllability of the airplane.
DATES: This AD becomes effective April
13, 2006.
The Director of the Federal Register
approved the incorporation by reference
of certain publications as of April 13,
2006.
On October 27, 2003 (68 FR 54990,
September 22, 2003), the Director of the
Federal Register approved the
incorporation by reference of Boeing
Alert Service Bulletin 747–53A2467,
dated July 26, 2001.
On August 28, 2001 (66 FR 38365,
July 24, 2001), the Director of the
Federal Register approved the
incorporation by reference of Boeing
Alert Service Bulletin 747–53A2427,
Revision 2, dated October 5, 2000.
On August 16, 2001 (66 FR 36443,
July 12, 2001), the Director of the
Federal Register approved the
incorporation by reference of Boeing
Service Bulletin 747–53A2449, Revision
1, dated May 24, 2001.
ADDRESSES: You may examine the AD
docket on the Internet at https://
dms.dot.gov or in person at the Docket
Management Facility, U.S. Department
of Transportation, 400 Seventh Street
SW., Nassif Building, Room PL–401,
Washington, DC.
Contact Boeing Commercial
Airplanes, P.O. Box 3707, Seattle,
Washington 98124–2207, for service
information identified in this 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:
Examining the Docket
You may examine the airworthiness
directive (AD) docket on the Internet at
https://dms.dot.gov or in person at the
Docket Management Facility office
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The Docket Management Facility office
(telephone (800) 647–5227) is located on
the plaza level of the Nassif Building at
the street address stated in the
ADDRESSES section.
Discussion
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
supersede the ADs identified in the
following table:
EXISTING ADS
AD
Amendment
Federal Register reference
Requirements
Repetitive high-frequency eddy current (HFEC) inspections to detect
cracking of the bulkhead frame support at body station (BS) 2598
under the hinge support fittings of the horizontal stabilizer, and repair if necessary.
Repetitive HFEC inspections to detect cracking of the forward and
aft inner chords and the splice fitting of the forward inner chord of
the BS 2598 bulkhead, and repair if necessary.
Repetitive detailed inspections to detect discrepancies of certain
areas of the forward and aft sides of the BS 2598 bulkhead, and
repair if necessary.
2001–14–07 ...............
39–12318
66 FR 36443 (July 12, 2001) .......
2001–15–03 ...............
39–12337
66 FR 38365 (July 24, 2001) .......
2003–19–08 ...............
39–13311
68 FR 54990 (September 22,
2003).
hsrobinson on PROD1PC70 with RULES
The existing ADs apply to certain
Boeing Model 747 airplanes. That
NPRM was published in the Federal
Register on October 19, 2005 (70 FR
60744). That NPRM proposed to
continue to require repetitive
inspections of the BS 2598 bulkhead,
and corrective action if necessary. That
NPRM also proposed to add a
requirement to modify the bulkhead,
including a one-time inspection and
corrective action if necessary, which
would terminate certain repetitive
inspections. That NPRM also proposed
to require a post-modification
inspection of the modified area.
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Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comment that has been
received on the NPRM. The commenter
supports the NPRM.
Clarification of Alternative Method of
Compliance (AMOC) Paragraph
We have revised this action to clarify
the appropriate procedure for notifying
the principal inspector before using any
approved AMOC on any airplane to
which the AMOC applies.
Conclusion
We have carefully reviewed the
available data, including the comment
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that has been received, and determined
that air safety and the public interest
require adopting the AD with the
change described previously. We have
determined that this change will neither
increase the economic burden on any
operator nor increase the scope of the
AD.
Costs of Compliance
There are about 1,147 airplanes of the
affected design in the worldwide fleet
and 280 U.S.-registered airplanes. The
following table provides the estimated
costs for U.S. operators to comply with
this AD.
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Federal Register / Vol. 71, No. 46 / Thursday, March 9, 2006 / Rules and Regulations
12127
ESTIMATED COSTS
Actions
Inspection required by AD 2001–14–07 (per inspection
cycle) ................................................................................
HFEC inspection required by AD 2001–15–03 (per inspection cycle) .........................................................................
Detailed inspection required by AD 2001–15–03 (per inspection cycle) ..................................................................
Inspection required by AD 2003–19–08 (per inspection
cycle) ................................................................................
Modification ..........................................................................
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, dection 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.
hsrobinson on PROD1PC70 with RULES
Regulatory Findings
We have determined that this AD will
not have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
the States, on the relationship between
the national government and the States,
or on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
(2) Is not a ‘‘significant rule’’ under
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
(3) Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared a regulatory evaluation
of the estimated costs to comply with
this AD and placed it in the AD docket.
See the ADDRESSES section for a location
to examine the regulatory evaluation.
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Jkt 208001
Average
hourly labor
rate
Work hours
$65
$0
$1,170
$327,600
2
65
0
130
36,400
2
65
0
130
36,400
4
126
65
65
0
33,716
260
41,906
72,800
11,733,680
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
I
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by removing amendment 39–12318 (66
FR 36443, July 12, 2001), amendment
39–12337 (66 FR 38365, July 24, 2001),
and amendment 39–13311 (68 FR
54990, September 22, 2003), and by
adding the following new airworthiness
directive (AD):
I
2006–05–06 Boeing: Amendment 39–14503.
Docket No. FAA–2005–22715;
Directorate Identifier 2005–NM–108–AD.
Effective Date
(a) This AD becomes effective April 13,
2006.
Affected ADs
(b) This AD supersedes ADs 2001–14–07,
2001–15–03, and 2003–19–08.
Applicability
(c) This AD applies to 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;
line numbers 1 through 1307 inclusive.
Unsafe Condition
(d) This AD results from reports of cracking
in areas required to be inspected by the
superseded ADs identified in paragraph (b) of
this AD. We are issuing this AD to prevent
fatigue cracking of the body station (BS) 2598
bulkhead structure, which could result in
inability of the structure to carry horizontal
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Fleet cost
18
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
§ 39.13
Cost per
airplane
Parts cost
Fmt 4700
Sfmt 4700
stabilizer flight loads, and loss of
controllability 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 AD 2001–14–07
Repetitive High Frequency Eddy Current
(HFEC) Inspections
(f) Before the accumulation of 10,000 total
flight cycles, or within 1,000 flight cycles
after August 16, 2001 (the effective date of
AD 2001–14–07), whichever occurs later: Do
an open-hole HFEC inspection to find
cracking of the bulkhead frame support
under the hinge support fittings of the
horizontal stabilizer on the left and right
sides at BS 2598, in accordance with Figure
2 of the Accomplishment Instructions of
Boeing Service Bulletin 747–53A2449,
Revision 1, dated May 24, 2001; or Revision
2, dated March 14, 2002. Repeat the
inspection after that at intervals not to exceed
3,000 flight cycles. Inspections accomplished
before August 16, 2001, per Boeing Alert
Service Bulletin 747–53A2449, dated June 8,
2000, are considered acceptable for
compliance with the applicable inspection
specified in this paragraph.
Repair
(g) If any cracking is found during any
inspection required by paragraph (f) of this
AD, before further flight, repair in accordance
with a method approved by the Manager,
Seattle Aircraft Certification Office (ACO),
FAA, or using a method approved in
accordance with paragraph (n) of this AD.
Restatement of Certain Requirements of AD
2001–15–03
Repetitive Inspections
(h) Do a surface HFEC inspection of the
forward and aft inner chords, the frame
support, and the splice fitting of the forward
inner chord of the upper corner of the station
2598 bulkhead to find cracking, in
accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
747–53A2427, Revision 2, dated October 5,
2000; or Revision 3, dated September 27,
2001; at the latest of the times specified in
paragraphs (h)(1) and (h)(2) of this AD, as
applicable. Repeat the inspection after that at
intervals not to exceed 1,500 flight cycles.
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Federal Register / Vol. 71, No. 46 / Thursday, March 9, 2006 / Rules and Regulations
(1) For airplanes having line numbers 1
through 1241 inclusive:
(i) Before the accumulation of 6,000 total
flight cycles.
(ii) Within 500 flight cycles after August
28, 2001 (the effective date of AD 2001–15–
03).
(iii) For airplanes inspected before August
28, 2001, in accordance with Boeing Alert
Service Bulletin 747–53A2427, dated
December 17, 1998 (including inspections of
the splice fitting), or Revision 1, dated
October 28, 1999: Within 1,500 flight cycles
after accomplishment of the last inspection
done in accordance with the original service
bulletin or Revision 1, as applicable.
(2) For airplanes having line numbers 1242
through 1307 inclusive:
(i) Before the accumulation of 16,000 total
flight cycles.
(ii) Within 500 flight cycles after August
28, 2001.
(iii) For airplanes inspected before August
28, 2001, in accordance with Boeing Alert
Service Bulletin 747–53A2427, dated
December 17, 1998 (including inspections of
the splice fitting), or Revision 1, dated
October 28, 1999: Within 1,500 flight cycles
after accomplishment of the last inspection
done in accordance with the original service
bulletin or Revision 1, as applicable.
Repair
(i) If any cracking is found during the
inspections required by paragraph (h) of this
AD, before further flight, repair in accordance
with the Accomplishment Instructions of
Boeing Alert Service Bulletin 747–53A2427,
Revision 2, dated October 5, 2000; or
Revision 3, dated September 27, 2001; except
where the alert service bulletin specifies that
the manufacturer may be contacted for
disposition of certain repair conditions,
before further flight, repair in accordance
with a method approved by the Manager,
Seattle ACO, or using a method approved in
accordance with the procedures specified in
paragraph (n) of this AD.
Restatement of AD 2003–19–08
Repetitive Inspections
(j) Before the accumulation of 10,000 total
flight cycles, or within 1,000 flight cycles
after October 27, 2003 (the effective date of
AD 2003–19–08), whichever is later: Do a
detailed inspection of the body station 2598
bulkhead for discrepancies (cracking,
elongated fastener holes) of the areas
specified in paragraphs (j)(1) and (j)(2) of this
AD, in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
747–53A2467, dated July 26, 2001; or
Revision 1, dated April 28, 2005. Repeat the
inspections after that at intervals not to
exceed 3,000 flight cycles.
(1) The lower aft inner chords.
(2) The upper aft outer chords, and the
diagonal brace attachment fittings, flanges,
and rods.
Note 1: For the purposes of this AD, a
detailed inspection is ‘‘an intensive
examination of a specific item, installation,
or assembly to detect damage, failure, or
irregularity. Available lighting is normally
supplemented with a direct source of good
lighting at an intensity deemed appropriate.
Inspection aids such as mirrors magnifying
lenses, etc. may be necessary. Surface
cleaning and elaborate procedures may be
required.’’
Repair
(k) If any discrepancy is found during any
inspection required by paragraph (j) of this
AD: Before further flight, repair in
accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
747–53A2467, dated July 26, 2001; or
Revision 1, dated April 28, 2005. If the
service bulletin specifies to contact Boeing
for appropriate action: Before further flight,
repair in accordance with a method approved
by the Manager, Seattle ACO, or using a
method approved in accordance with the
procedures specified in paragraph (n) of this
AD.
New Requirements of This AD
Modification
(l) Before the accumulation of 20,000 total
flight cycles, or within 48 months after the
effective date of this AD, whichever occurs
later: Modify the bulkhead by doing all
applicable actions including surface and
open-hole HFEC inspections for cracking of
the upper forward inner chord, aft inner
chord, upper splice fitting, and frame support
fitting, as specified in the Accomplishment
Instructions of Boeing Service Bulletin 747–
53–2473, dated March 24, 2005. Repair any
cracks before further flight in accordance
with the service bulletin. Where the service
bulletin specifies that the manufacturer may
be contacted for disposition of certain repair
conditions: Before further flight, repair the
cracks using a method approved in
accordance with the procedures specified in
paragraph (n) of this AD. Accomplishment of
the modification terminates the repetitive
inspections required by paragraphs (f), (h),
and (j)(1) of this AD.
Inspection
(m) Within 20,000 flight cycles after the
modification required by paragraph (l) of this
AD, inspect the BS 2598 bulkhead for cracks,
and repair any cracks before further flight, in
accordance with a method approved by the
Manager, Seattle ACO.
Alternative Methods of Compliance (AMOCs)
(n)(1) The Manager, Seattle ACO, has the
authority to approve AMOCs for this AD, if
requested in accordance with the procedures
found in 14 CFR 39.19.
(2) AMOCs approved previously according
to AD 2000–08–21, amendment 39–11707,
and AD 2001–15–03 are approved as AMOCs
for the corresponding requirements of
paragraphs (h) and (i) of this AD. (AD 2000–
08–21 was superseded by AD 2001–15–03.)
(3) AMOCs approved previously according
to AD 2001–14–07 are approved as AMOCs
for the corresponding requirements of
paragraphs (f) and (g) of this AD.
(4) AMOCs approved previously according
to AD 2003–19–08 are approved as AMOCs
for the corresponding requirements of
paragraphs (j) and (k) of this AD.
(5) Before using any AMOC approved in
accordance with 14 CFR 39.19 on any
airplane to which the AMOC applies, notify
the appropriate principal inspector in the
FAA Flight Standards Certificate Holding
District Office.
(6) 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.
Material Incorporated by Reference
(o) You must use the service information
identified in Table 1 of this AD, as
applicable, to perform the actions that are
required by this AD, unless the AD specifies
otherwise.
TABLE 1.—ALL MATERIAL INCORPORATED BY REFERENCE
hsrobinson on PROD1PC70 with RULES
Boeing service bulletin
Revision
level
Date
Alert Service Bulletin 747–53A2427 ..................................................................................................................
Alert Service Bulletin 747–53A2427 ..................................................................................................................
Alert Service Bulletin 747–53A2467 ..................................................................................................................
Service Bulletin 747–53A2467 ..........................................................................................................................
Service Bulletin 747–53–2473 ...........................................................................................................................
Service Bulletin 747–53A2449 ..........................................................................................................................
Service Bulletin 747–53A2449 ..........................................................................................................................
2 ...............
3 ...............
Original ....
1 ...............
Original ....
1 ...............
2 ...............
October 5, 2000.
September 27, 2001.
July 26, 2001.
April 28, 2005.
March 24, 2005.
May 24, 2001.
March 14, 2002.
(1) The Director of the Federal Register
approved the incorporation by reference of
service bulletins identified in Table 2 of this
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Jkt 208001
AD, in accordance with 5 U.S.C. 552(a) and
1 CFR part 51.
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Federal Register / Vol. 71, No. 46 / Thursday, March 9, 2006 / Rules and Regulations
TABLE 2.—NEW MATERIAL INCORPORATED BY REFERENCE
Boeing service bulletin
Revision
level
Date
Alert Service Bulletin 747–53A2427 ..................................................................................................................
Service Bulletin 747–53A2467 ..........................................................................................................................
Service Bulletin 747–53–2473 ...........................................................................................................................
Service Bulletin 747–53A2449 ..........................................................................................................................
3 ...............
1 ...............
Original ....
2 ...............
September 27, 2001.
April 28, 2005.
March 24, 2005.
March 14, 2002.
(2) On October 27, 2003 (68 FR 54990,
September 22, 2003), the Director of the
Federal Register approved the incorporation
by reference of Boeing Alert Service Bulletin
747–53A2467, dated July 26, 2001.
(3) On August 28, 2001 (66 FR 38365, July
24, 2001), the Director of the Federal Register
approved the incorporation by reference of
Boeing Alert Service Bulletin 747–53A2427,
Revision 2, dated October 5, 2000.
(4) On August 16, 2001 (66 FR 36443, July
12, 2001), the Director of the Federal Register
approved the incorporation by reference of
Boeing Service Bulletin 747–53A2449,
Revision 1, dated May 24, 2001.
(5) Contact Boeing Commercial Airplanes,
P.O. Box 3707, Seattle, Washington 98124–
2207, for a copy of this service information.
You may review copies at the Docket
Management Facility, U.S. Department of
Transportation, 400 Seventh Street SW.,
Room PL–401, Nassif Building, Washington,
DC; on the Internet at https://dms.dot.gov; or
at the National Archives and Records
Administration (NARA). For information on
the availability of this material at the NARA,
call (202) 741–6030, or go to https://
www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html.
Issued in Renton, Washington, on February
22, 2006.
Michael J. Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 06–2144 Filed 3–8–06; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–20220; Directorate
Identifier 2004–NM–152–AD; Amendment
39–14504; AD 2006–05–07]
RIN 2120–AA64
Airworthiness Directives; Aerospatiale
Model ATR42–200, –300, and –320
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
hsrobinson on PROD1PC70 with RULES
AGENCY:
The FAA is adopting a new
airworthiness directive (AD) for certain
SUMMARY:
VerDate Aug<31>2005
15:06 Mar 08, 2006
Jkt 208001
Aerospatiale Model ATR42–200, –300,
and –320 airplanes. This AD requires
doing repetitive inspections of the
upper arms of the main landing gear
(MLG) side braces for missing or
inadequately bonded identification
plates; doing an ultrasonic inspection of
the upper arm of the MLG side brace for
any defects and related investigative/
corrective actions if necessary; and
replacing the side brace assembly with
a modified part. This AD results from an
operator who reported experiencing an
unlock warning for the MLG on the right
side of the airplane. We are issuing this
AD to prevent cracking of the upper
arms of the side braces of the MLG,
which could result in failure of the MLG
during landing and possible damage to
the airplane and injury to the flightcrew
and passengers.
DATES: This AD becomes effective April
13, 2006.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of April 13, 2006.
ADDRESSES: You may examine the AD
docket on the Internet at https://
dms.dot.gov or in person at the Docket
Management Facility, U.S. Department
of Transportation, 400 Seventh Street,
SW., Nassif Building, room PL–401,
Washington, DC.
Contact Aerospatiale, 316 Route de
Bayonne, 31060 Toulouse, Cedex 03,
France, for service information
identified in this AD.
FOR FURTHER INFORMATION CONTACT: Tom
Rodriguez, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton,
Washington 98055–4056; telephone
(425) 227–1137; fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
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
PO 00000
Frm 00009
Fmt 4700
Sfmt 4700
level of the Nassif Building at the street
address stated in the ADDRESSES section.
Discussion
The FAA issued a supplemental
notice of proposed rulemaking (NPRM)
to amend 14 CFR part 39 to include an
AD that would apply to certain
Aerospatiale Model ATR42–200, –300,
and –320 airplanes. That supplemental
NPRM was published in the Federal
Register on December 13, 2005 (70 FR
73671). That supplemental NPRM
proposed to require repetitive
inspections of the upper arms of the
main landing gear (MLG) side braces for
missing or inadequately bonded
identification plates; doing an ultrasonic
inspection of the upper arm of the MLG
side brace for any defects and related
investigative/corrective actions if
necessary; and replacing the side brace
assembly with a modified part.
Comments
We provided the public the
opportunity to participate in the
development of this AD. No comments
have been received on the supplemental
NPRM or on the determination of the
cost to the public.
Change Made to This AD
We have added a grace period of 25
flight hours to paragraph (i) of this AD
for operators who may inadvertently use
Revision 1 of Messier-Dowty Special
Inspection Service Bulletin 631–32–181,
dated March 16, 2005, after the effective
date of this AD.
Conclusion
We have carefully reviewed the
available data and determined that air
safety and the public interest require
adopting the AD with the change
described previously. We have
determined that this change will neither
increase the economic burden on any
operator nor increase the scope of the
AD.
Costs of Compliance
The following table provides the
estimated costs for U.S. operators to
comply with this AD.
E:\FR\FM\09MRR1.SGM
09MRR1
]]>Agencies
[Federal Register Volume 71, Number 46 (Thursday, March 9, 2006)]
[Rules and Regulations]
[Pages 12125-12129]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 06-2144]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-22715; Directorate Identifier 2005-NM-108-AD;
Amendment 39-14503; AD 2006-05-06]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 747 Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
[[Page 12126]]
SUMMARY: The FAA is superseding three existing airworthiness directives
(ADs) that apply to certain Boeing Model 747 airplanes. The existing
ADs currently require repetitive inspections of the body station (BS)
2598 bulkhead, and corrective action if necessary. This new AD adds a
requirement to modify the bulkhead, including a one-time inspection and
corrective action if necessary, which terminates certain repetitive
inspections. This AD also requires a post-modification inspection of
the modified area. This AD results from new reports of cracking in all
three areas that require inspection in accordance with the existing
ADs. We are issuing this AD to prevent fatigue cracking of the BS 2598
bulkhead structure, which could result in inability of the structure to
carry horizontal stabilizer flight loads, and loss of controllability
of the airplane.
DATES: This AD becomes effective April 13, 2006.
The Director of the Federal Register approved the incorporation by
reference of certain publications as of April 13, 2006.
On October 27, 2003 (68 FR 54990, September 22, 2003), the Director
of the Federal Register approved the incorporation by reference of
Boeing Alert Service Bulletin 747-53A2467, dated July 26, 2001.
On August 28, 2001 (66 FR 38365, July 24, 2001), the Director of
the Federal Register approved the incorporation by reference of Boeing
Alert Service Bulletin 747-53A2427, Revision 2, dated October 5, 2000.
On August 16, 2001 (66 FR 36443, July 12, 2001), the Director of
the Federal Register approved the incorporation by reference of Boeing
Service Bulletin 747-53A2449, Revision 1, dated May 24, 2001.
ADDRESSES: You may examine the AD docket on the Internet at https://
dms.dot.gov or in person at the Docket Management Facility, U.S.
Department of Transportation, 400 Seventh Street SW., Nassif Building,
Room PL-401, Washington, DC.
Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle,
Washington 98124-2207, for service information identified in this 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:
Examining the Docket
You may examine the airworthiness directive (AD) docket on the
Internet at https://dms.dot.gov or in person at the Docket Management
Facility office between 9 a.m. and 5 p.m., Monday through Friday,
except Federal holidays. The Docket Management Facility office
(telephone (800) 647-5227) is located on the plaza level of the Nassif
Building at the street address stated in the ADDRESSES section.
Discussion
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to include an AD that would supersede the ADs identified in
the following table:
Existing ADs
----------------------------------------------------------------------------------------------------------------
AD Amendment Federal Register reference Requirements
----------------------------------------------------------------------------------------------------------------
2001-14-07............................ 39-12318 66 FR 36443 (July 12, Repetitive high-frequency eddy
2001). current (HFEC) inspections to
detect cracking of the
bulkhead frame support at body
station (BS) 2598 under the
hinge support fittings of the
horizontal stabilizer, and
repair if necessary.
2001-15-03............................ 39-12337 66 FR 38365 (July 24, Repetitive HFEC inspections to
2001). detect cracking of the forward
and aft inner chords and the
splice fitting of the forward
inner chord of the BS 2598
bulkhead, and repair if
necessary.
2003-19-08............................ 39-13311 68 FR 54990 (September 22, Repetitive detailed inspections
2003). to detect discrepancies of
certain areas of the forward
and aft sides of the BS 2598
bulkhead, and repair if
necessary.
----------------------------------------------------------------------------------------------------------------
The existing ADs apply to certain Boeing Model 747 airplanes. That NPRM
was published in the Federal Register on October 19, 2005 (70 FR
60744). That NPRM proposed to continue to require repetitive
inspections of the BS 2598 bulkhead, and corrective action if
necessary. That NPRM also proposed to add a requirement to modify the
bulkhead, including a one-time inspection and corrective action if
necessary, which would terminate certain repetitive inspections. That
NPRM also proposed to require a post-modification inspection of the
modified area.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comment that has been
received on the NPRM. The commenter supports the NPRM.
Clarification of Alternative Method of Compliance (AMOC) Paragraph
We have revised this action to clarify the appropriate procedure
for notifying the principal inspector before using any approved AMOC on
any airplane to which the AMOC applies.
Conclusion
We have carefully reviewed the available data, including the
comment that has been received, and determined that air safety and the
public interest require adopting the AD with the change described
previously. We have determined that this change will neither increase
the economic burden on any operator nor increase the scope of the AD.
Costs of Compliance
There are about 1,147 airplanes of the affected design in the
worldwide fleet and 280 U.S.-registered airplanes. The following table
provides the estimated costs for U.S. operators to comply with this AD.
[[Page 12127]]
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Average hourly Cost per
Actions Work hours labor rate Parts cost airplane Fleet cost
----------------------------------------------------------------------------------------------------------------
Inspection required by AD 2001- 18 $65 $0 $1,170 $327,600
14-07 (per inspection cycle)...
HFEC inspection required by AD 2 65 0 130 36,400
2001-15-03 (per inspection
cycle).........................
Detailed inspection required by 2 65 0 130 36,400
AD 2001-15-03 (per inspection
cycle).........................
Inspection required by AD 2003- 4 65 0 260 72,800
19-08 (per inspection cycle)...
Modification.................... 126 65 33,716 41,906 11,733,680
----------------------------------------------------------------------------------------------------------------
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, dection 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We have determined that this AD will not have federalism
implications under Executive Order 13132. This AD will not have a
substantial direct effect on the States, on the relationship between
the national government and the States, or on the distribution of power
and responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866;
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979); and
(3) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this AD and placed it in the AD docket. See the ADDRESSES
section for a location to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The Federal Aviation Administration (FAA) amends Sec. 39.13 by
removing amendment 39-12318 (66 FR 36443, July 12, 2001), amendment 39-
12337 (66 FR 38365, July 24, 2001), and amendment 39-13311 (68 FR
54990, September 22, 2003), and by adding the following new
airworthiness directive (AD):
2006-05-06 Boeing: Amendment 39-14503. Docket No. FAA-2005-22715;
Directorate Identifier 2005-NM-108-AD.
Effective Date
(a) This AD becomes effective April 13, 2006.
Affected ADs
(b) This AD supersedes ADs 2001-14-07, 2001-15-03, and 2003-19-
08.
Applicability
(c) This AD applies to 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; line numbers 1 through 1307 inclusive.
Unsafe Condition
(d) This AD results from reports of cracking in areas required
to be inspected by the superseded ADs identified in paragraph (b) of
this AD. We are issuing this AD to prevent fatigue cracking of the
body station (BS) 2598 bulkhead structure, which could result in
inability of the structure to carry horizontal stabilizer flight
loads, and loss of controllability 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 AD 2001-14-07
Repetitive High Frequency Eddy Current (HFEC) Inspections
(f) Before the accumulation of 10,000 total flight cycles, or
within 1,000 flight cycles after August 16, 2001 (the effective date
of AD 2001-14-07), whichever occurs later: Do an open-hole HFEC
inspection to find cracking of the bulkhead frame support under the
hinge support fittings of the horizontal stabilizer on the left and
right sides at BS 2598, in accordance with Figure 2 of the
Accomplishment Instructions of Boeing Service Bulletin 747-53A2449,
Revision 1, dated May 24, 2001; or Revision 2, dated March 14, 2002.
Repeat the inspection after that at intervals not to exceed 3,000
flight cycles. Inspections accomplished before August 16, 2001, per
Boeing Alert Service Bulletin 747-53A2449, dated June 8, 2000, are
considered acceptable for compliance with the applicable inspection
specified in this paragraph.
Repair
(g) If any cracking is found during any inspection required by
paragraph (f) of this AD, before further flight, repair in
accordance with a method approved by the Manager, Seattle Aircraft
Certification Office (ACO), FAA, or using a method approved in
accordance with paragraph (n) of this AD.
Restatement of Certain Requirements of AD 2001-15-03
Repetitive Inspections
(h) Do a surface HFEC inspection of the forward and aft inner
chords, the frame support, and the splice fitting of the forward
inner chord of the upper corner of the station 2598 bulkhead to find
cracking, in accordance with the Accomplishment Instructions of
Boeing Alert Service Bulletin 747-53A2427, Revision 2, dated October
5, 2000; or Revision 3, dated September 27, 2001; at the latest of
the times specified in paragraphs (h)(1) and (h)(2) of this AD, as
applicable. Repeat the inspection after that at intervals not to
exceed 1,500 flight cycles.
[[Page 12128]]
(1) For airplanes having line numbers 1 through 1241 inclusive:
(i) Before the accumulation of 6,000 total flight cycles.
(ii) Within 500 flight cycles after August 28, 2001 (the
effective date of AD 2001-15-03).
(iii) For airplanes inspected before August 28, 2001, in
accordance with Boeing Alert Service Bulletin 747-53A2427, dated
December 17, 1998 (including inspections of the splice fitting), or
Revision 1, dated October 28, 1999: Within 1,500 flight cycles after
accomplishment of the last inspection done in accordance with the
original service bulletin or Revision 1, as applicable.
(2) For airplanes having line numbers 1242 through 1307
inclusive:
(i) Before the accumulation of 16,000 total flight cycles.
(ii) Within 500 flight cycles after August 28, 2001.
(iii) For airplanes inspected before August 28, 2001, in
accordance with Boeing Alert Service Bulletin 747-53A2427, dated
December 17, 1998 (including inspections of the splice fitting), or
Revision 1, dated October 28, 1999: Within 1,500 flight cycles after
accomplishment of the last inspection done in accordance with the
original service bulletin or Revision 1, as applicable.
Repair
(i) If any cracking is found during the inspections required by
paragraph (h) of this AD, before further flight, repair in
accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 747-53A2427, Revision 2, dated October 5, 2000; or
Revision 3, dated September 27, 2001; except where the alert service
bulletin specifies that the manufacturer may be contacted for
disposition of certain repair conditions, before further flight,
repair in accordance with a method approved by the Manager, Seattle
ACO, or using a method approved in accordance with the procedures
specified in paragraph (n) of this AD.
Restatement of AD 2003-19-08
Repetitive Inspections
(j) Before the accumulation of 10,000 total flight cycles, or
within 1,000 flight cycles after October 27, 2003 (the effective
date of AD 2003-19-08), whichever is later: Do a detailed inspection
of the body station 2598 bulkhead for discrepancies (cracking,
elongated fastener holes) of the areas specified in paragraphs
(j)(1) and (j)(2) of this AD, in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin 747-53A2467, dated
July 26, 2001; or Revision 1, dated April 28, 2005. Repeat the
inspections after that at intervals not to exceed 3,000 flight
cycles.
(1) The lower aft inner chords.
(2) The upper aft outer chords, and the diagonal brace
attachment fittings, flanges, and rods.
Note 1: For the purposes of this AD, a detailed inspection is
``an intensive examination of a specific item, installation, or
assembly to detect damage, failure, or irregularity. Available
lighting is normally supplemented with a direct source of good
lighting at an intensity deemed appropriate. Inspection aids such as
mirrors magnifying lenses, etc. may be necessary. Surface cleaning
and elaborate procedures may be required.''
Repair
(k) If any discrepancy is found during any inspection required
by paragraph (j) of this AD: Before further flight, repair in
accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 747-53A2467, dated July 26, 2001; or Revision 1,
dated April 28, 2005. If the service bulletin specifies to contact
Boeing for appropriate action: Before further flight, repair in
accordance with a method approved by the Manager, Seattle ACO, or
using a method approved in accordance with the procedures specified
in paragraph (n) of this AD.
New Requirements of This AD
Modification
(l) Before the accumulation of 20,000 total flight cycles, or
within 48 months after the effective date of this AD, whichever
occurs later: Modify the bulkhead by doing all applicable actions
including surface and open-hole HFEC inspections for cracking of the
upper forward inner chord, aft inner chord, upper splice fitting,
and frame support fitting, as specified in the Accomplishment
Instructions of Boeing Service Bulletin 747-53-2473, dated March 24,
2005. Repair any cracks before further flight in accordance with the
service bulletin. Where the service bulletin specifies that the
manufacturer may be contacted for disposition of certain repair
conditions: Before further flight, repair the cracks using a method
approved in accordance with the procedures specified in paragraph
(n) of this AD. Accomplishment of the modification terminates the
repetitive inspections required by paragraphs (f), (h), and (j)(1)
of this AD.
Inspection
(m) Within 20,000 flight cycles after the modification required
by paragraph (l) of this AD, inspect the BS 2598 bulkhead for
cracks, and repair any cracks before further flight, in accordance
with a method approved by the Manager, Seattle ACO.
Alternative Methods of Compliance (AMOCs)
(n)(1) The Manager, Seattle ACO, has the authority to approve
AMOCs for this AD, if requested in accordance with the procedures
found in 14 CFR 39.19.
(2) AMOCs approved previously according to AD 2000-08-21,
amendment 39-11707, and AD 2001-15-03 are approved as AMOCs for the
corresponding requirements of paragraphs (h) and (i) of this AD. (AD
2000-08-21 was superseded by AD 2001-15-03.)
(3) AMOCs approved previously according to AD 2001-14-07 are
approved as AMOCs for the corresponding requirements of paragraphs
(f) and (g) of this AD.
(4) AMOCs approved previously according to AD 2003-19-08 are
approved as AMOCs for the corresponding requirements of paragraphs
(j) and (k) of this AD.
(5) Before using any AMOC approved in accordance with 14 CFR
39.19 on any airplane to which the AMOC applies, notify the
appropriate principal inspector in the FAA Flight Standards
Certificate Holding District Office.
(6) 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.
Material Incorporated by Reference
(o) You must use the service information identified in Table 1
of this AD, as applicable, to perform the actions that are required
by this AD, unless the AD specifies otherwise.
Table 1.--All Material Incorporated by Reference
------------------------------------------------------------------------
Revision
Boeing service bulletin level Date
------------------------------------------------------------------------
Alert Service Bulletin 747- 2............ October 5, 2000.
53A2427.
Alert Service Bulletin 747- 3............ September 27, 2001.
53A2427.
Alert Service Bulletin 747- Original..... July 26, 2001.
53A2467.
Service Bulletin 747-53A2467. 1............ April 28, 2005.
Service Bulletin 747-53-2473. Original..... March 24, 2005.
Service Bulletin 747-53A2449. 1............ May 24, 2001.
Service Bulletin 747-53A2449. 2............ March 14, 2002.
------------------------------------------------------------------------
(1) The Director of the Federal Register approved the
incorporation by reference of service bulletins identified in Table
2 of this AD, in accordance with 5 U.S.C. 552(a) and 1 CFR part 51.
[[Page 12129]]
Table 2.--New Material Incorporated by Reference
------------------------------------------------------------------------
Revision
Boeing service bulletin level Date
------------------------------------------------------------------------
Alert Service Bulletin 747- 3............ September 27, 2001.
53A2427.
Service Bulletin 747-53A2467. 1............ April 28, 2005.
Service Bulletin 747-53-2473. Original..... March 24, 2005.
Service Bulletin 747-53A2449. 2............ March 14, 2002.
------------------------------------------------------------------------
(2) On October 27, 2003 (68 FR 54990, September 22, 2003), the
Director of the Federal Register approved the incorporation by
reference of Boeing Alert Service Bulletin 747-53A2467, dated July
26, 2001.
(3) On August 28, 2001 (66 FR 38365, July 24, 2001), the
Director of the Federal Register approved the incorporation by
reference of Boeing Alert Service Bulletin 747-53A2427, Revision 2,
dated October 5, 2000.
(4) On August 16, 2001 (66 FR 36443, July 12, 2001), the
Director of the Federal Register approved the incorporation by
reference of Boeing Service Bulletin 747-53A2449, Revision 1, dated
May 24, 2001.
(5) Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle,
Washington 98124-2207, for a copy of this service information. You
may review copies at the Docket Management Facility, U.S. Department
of Transportation, 400 Seventh Street SW., Room PL-401, Nassif
Building, Washington, DC; on the Internet at https://dms.dot.gov; or
at the National Archives and Records Administration (NARA). For
information on the availability of this material at the NARA, call
(202) 741-6030, or go to https://www.archives.gov/federal_register/
code_of_federal_regulations/ibr_locations.html.
Issued in Renton, Washington, on February 22, 2006.
Michael J. Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 06-2144 Filed 3-8-06; 8:45 am]
BILLING CODE 4910-13-P
