Airworthiness Directives; Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747SP, and 747SR Series Airplanes; Equipped With Pratt & Whitney Model JT9D-3 and -7 Series Engines, 47086-47090 [05-15882]
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47086
Federal Register / Vol. 70, No. 155 / Friday, August 12, 2005 / Rules and Regulations
these changes.4 The Federal Reserve
routing symbols assigned to all other
Federal Reserve branches and offices
will remain the same at this time. The
Board of Governors, however, intends to
issue similar notices at least sixty days
prior to the elimination of check
operations at some other Reserve Bank
offices, as described in the September
2004 Federal Register document.
Administrative Procedure Act
The Board has not followed the
provisions of 5 U.S.C. 553(b) relating to
notice and public participation in
connection with the adoption of this
final rule. The revisions to the appendix
are technical in nature, and the routing
symbol revisions are required by the
statutory and regulatory definitions of
‘‘check-processing region.’’ Because
there is no substantive change on which
to seek public input, the Board has
determined that the § 553(b) notice and
comment procedures are unnecessary.
Paperwork Reduction Act
In accordance with the Paperwork
Reduction Act of 1995 (44 U.S.C. 3506;
5 CFR 1320 Appendix A.1), the Board
has reviewed the final rule under
authority delegated to the Board by the
Office of Management and Budget.
These technical amendments to
appendix A of Regulation CC will delete
the reference to the Portland branch
office of the Federal Reserve Bank of
San Francisco and reassign the routing
symbols listed under that office to the
Seattle branch office of the Federal
Reserve Bank of San Francisco. The
depository institutions that are located
in the affected check processing regions
and that include the routing numbers in
their disclosure statements would be
required to notify customers of the
resulting change in availability under
§ 229.18(e). However, because all
paperwork collection procedures
associated with Regulation CC already
are in place, the Board anticipates that
no additional burden will be imposed as
a result of this rulemaking.
PART 229—AVAILABILITY OF FUNDS
AND COLLECTION OF CHECKS
(REGULATION CC)
DEPARTMENT OF TRANSPORTATION
I
1. The authority citation for part 229
continues to read as follows:
14 CFR Part 39
Authority: 12 U.S.C. 4001–4010, 12 U.S.C.
5001–5018.
[Docket No. FAA–2005–20325; Directorate
Identifier 2003–NM–129–AD; Amendment
39–14217; AD 2005–16–11]
2. The Twelfth Federal Reserve District
routing symbol list in appendix A is
revised to read as follows:
I
Appendix A To Part 229—Routing
Number Guide To Next-Day
Availability Checks and Local Checks
*
*
*
*
*
TWELFTH FEDERAL RESERVE DISTRICT
(Federal Reserve Bank of San Francisco)
Head Office
1210 ....................................................
1211 ....................................................
1212 ....................................................
1213 ....................................................
Los Angeles Branch
1220 ....................................................
1221 ....................................................
1222 ....................................................
1223 ....................................................
1224 ....................................................
Seattle Branch
1230 ....................................................
1231 ....................................................
1232 ....................................................
1233 ....................................................
1250 ....................................................
1251 ....................................................
1252 ....................................................
*
*
*
*
3230
3231
3232
3233
3250
3251
3252
*
BILLING CODE 6210–01–P
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 747–100, 747–100B, 747–100B
SUD, 747–200B, 747–200C, 747–200F,
747–300, 747SP, and 747SR Series
Airplanes; Equipped With Pratt &
Whitney Model JT9D–3 and –7 Series
Engines
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for certain
Boeing transport category airplanes
listed above. This AD requires repetitive
inspections for cracks of the upper
surface of the aft lower spar web of the
inboard and outboard struts, as
applicable; and repetitive inspections
for cracks of the upper surface of the
intermediate web bay of the aft lower
spar. This AD also requires repetitive
inspections and torque checks of the
bolts common to the aft lower spar
chords and the fitting of the rear engine
mount bulkhead for missing, loose, or
fractured bolts, as applicable; and
corrective action, if necessary. This AD
is prompted by reports of cracking in
the aft lower spar web and reports of
missing and fractured bolts. We are
issuing this AD to detect and correct
cracking of the aft lower spar web, and
to prevent missing, loose, or fractured
bolts common to the aft lower spar
chords and the fitting of the rear engine
mount bulkhead, which could result in
the loss of the aft lower spar load path
and reduced structural capability of the
pylon, which may result in the
separation of the engine from the
airplane.
This AD becomes effective
September 16, 2005.
The incorporation by reference of a
certain publication listed in the AD is
approved by the Director of the Federal
Register as of September 16, 2005.
ADDRESSES: For service information
identified in this AD, contact Boeing
Commercial Airplanes, P.O. Box 3707,
Seattle, Washington 98124–2207.
Docket: The AD docket contains the
proposed AD, comments, and any final
disposition. You can examine the AD
docket on the Internet at https://
DATES:
List of Subjects in 12 CFR Part 229
Banks, Banking, Reporting and
recordkeeping requirements.
Authority and Issuance
For the reasons set forth in the
preamble, the Board is amending 12 CFR
part 229 to read as follows:
I
4 Section 229.18(e) of Regulation CC requires that
banks notify account holders who are consumers
within 30 days after implementing a change that
improves the availability of funds.
12:47 Aug 11, 2005
3220
3221
3222
3223
3224
By order of the Board of Governors of the
Federal Reserve System, acting through the
Secretary of the Board under delegated
authority, August 8, 2005.
Jennifer J. Johnson,
Secretary of the Board.
[FR Doc. 05–15998 Filed 8–11–05; 8:45 am]
12 CFR Chapter II
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3211
3212
3213
Federal Aviation Administration
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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 U.S. Department of Transportation,
400 Seventh Street SW., room PL–401,
Washington, DC. This docket number is
FAA–2005–20325; the directorate
identifier for this docket is 2003–NM–
129–AD.
FOR FURTHER INFORMATION CONTACT:
Candice Gerretsen, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton,
Washington 98055–4056; telephone
(425) 917–6428; fax (425) 917–6590.
SUPPLEMENTARY INFORMATION: The FAA
proposed to amend 14 CFR part 39 with
an AD for certain Boeing transport
category airplanes. That action,
published in the Federal Register on
February 10, 2005 (70 FR 7052),
proposed to require repetitive
inspections for cracks of the upper
surface of the aft lower spar web of the
inboard and outboard struts, as
applicable; and repetitive inspections
for cracks of the upper surface of the
intermediate web bay of the aft lower
spar. That action also proposed to
require repetitive inspections and
torque checks of the bolts common to
the aft lower spar chords and the fitting
of the rear engine mount bulkhead for
missing, loose, or fractured bolts, as
applicable; and corrective action, if
necessary.
The commenter contends that retired
airplanes are not included in the
applicability of the proposed AD and
states that strut assemblies may be
interchanged between airplanes.
We do not agree to revise the
applicability. Retired airplanes are
included by variable number in Boeing
Alert Service Bulletin 747–54A2212,
dated May 1, 2003 (referenced as the
appropriate source of information for
the applicability of the proposed AD).
Also, it is our policy to not write the
applicability of ADs against a part of the
airframe, such as the strut. Section 39.3
(‘‘Definition of airworthiness
directives’’) of the Federal Aviation
Regulations (14 CFR 39.3) specifies that
airworthiness directives apply to the
following products: aircraft, aircraft
engine, propeller, or appliance (which is
not part of the airframe). We have not
changed the final rule in this regard.
Request To Revise Applicability
One commenter requests that the
applicability be revised to read:
Request To Advise Operators That Strut
Assemblies Are Interchangeable
The same commenter requests that a
clause be added to advise operators that
the strut assemblies are interchangeable
and that, if a strut assembly is installed
on another airplane, that airplane must
be evaluated to determine if it is
applicable to the proposed AD.
We agree that the strut assembly is an
interchangeable part. However, we do
not agree to revise the final rule to
advise operators that the strut
assemblies are interchangeable because
the strut is a serialized part that can be
tracked. Operators should note that they
are responsible for maintaining the
configuration of its airplanes, especially
in an area affected by an AD. As
required by section 39.17 of the Federal
Aviation Regulations (14 CFR 39.17), for
airplanes that have been modified,
altered, or repaired so that the
accomplishment of the requirements of
this final rule is affected, the operator
must request approval for an alternative
method of compliance according to
paragraph (q) of this AD.
This AD applies to engine strut assemblies
installed on Boeing Model 747–100, –100B,
–100B SUD, –200B, –200C, –200F, and –300
series airplanes, and Model 747–SP and 747
SR series airplanes; certificated in any
category; equipped with Pratt and Whitney
Model JT9D–3 and –7 series engines.
Request To Define Airplane Groups by
Pylon Web Thickness
One commenter requests that the
airplane groups be defined solely by
pylon web thickness. The commenter
states that the groups identified in the
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comments that have
been submitted on the proposed AD.
47087
service bulletin do not reflect its
airplane configuration. The commenter
notes that it has Group 1 airplanes with
0.032-inch pylon webs, Group 3
airplanes with 0.025-inch pylon webs,
and some airplanes with mixed 0.025inch pylon webs and 0.032-inch pylon
webs.
We acknowledge that the service
bulletin may not reflect an operator’s
current aircraft configuration because of
post-delivery modifications. Since the
groupings are not only defined by web
thickness but also by the location of web
stiffeners and the web material; we do
not agree to revise the final rule to
define airplane groups by pylon web
thickness. Operators are responsible for
maintaining the configuration of its
airplanes. If the configuration of an
airplane has been changed in an area
affected by this final rule and the
accomplishment of the requirements of
this final rule is affected, operators must
request approval for an alternative
method of compliance according to
paragraph (q) of this AD as required by
14 CFR 39.19.
Explanation of Change to Applicability
We have revised the applicability of
the proposed AD to identify model
designations as published in the most
recent type certificate data sheet for the
affected models.
Conclusion
We have carefully reviewed the
available data, including the comments
that have been submitted, and
determined that air safety and the
public interest require adopting the AD
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 244 airplanes of the
affected design in the worldwide fleet.
This AD will affect about 82 airplanes
of U.S. registry. The following table
provides the estimated costs for U.S.
operators to comply with this AD.
ESTIMATED COSTS
Applicable airplanes identified in Boeing Alert
Service Bulletin 747–54A2212 As—
Action
Groups 1–6 .......................................................
Groups 7–8 .......................................................
Groups 1–5 .......................................................
Web inspection .............................................
Web inspection .............................................
Web bay inspection ......................................
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Average labor
rate per hour
Work hours
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8
4
4
12AUR1
Cost per airplane, per inspection cycle
$65
65
65
$520
260
260
47088
Federal Register / Vol. 70, No. 155 / Friday, August 12, 2005 / Rules and Regulations
ESTIMATED COSTS—Continued
Applicable airplanes identified in Boeing Alert
Service Bulletin 747–54A2212 As—
Action
Groups 1–6 .......................................................
Bolt inspection ..............................................
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.
We prepared a regulatory evaluation
of the estimated costs to comply with
this AD. See the ADDRESSES section for
a location to examine the regulatory
evaluation.
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.
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
Average labor
rate per hour
Work hours
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
I
2005–16–11 Boeing: Amendment 39–14217.
Docket No. FAA–2005–20325;
Directorate Identifier 2003–NM–129–AD.
Effective Date
(a) This AD becomes effective September
16, 2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Boeing Model 747–
100, 747–100B, 747–100B SUD, 747–200B,
747–200C, 747–200F, 747–300, 747SP, and
747SR series airplanes; certificated in any
category; equipped with Pratt & Whitney
Model JT9D–3 and –7 series engines; as
identified in Boeing Alert Service Bulletin
747–54A2212, dated May 1, 2003.
Cost per airplane, per inspection cycle
65
260
4
Unsafe Condition
(d) This AD was prompted by reports of
cracking in the aft lower spar web and
reports of missing and fractured bolts. We are
issuing this AD to detect and correct cracking
of the aft lower spar web, and to prevent
missing, loose, or fractured bolts common to
the aft lower spar chords and the fitting of
the rear engine mount bulkhead, which could
result in the loss of the aft lower spar load
path and reduced structural capability of the
pylon, which may result in the separation of
the engine from 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.
Service Bulletin Reference
(f) The term ‘‘service bulletin,’’ as used in
this AD, means Boeing Alert Service Bulletin
747–54A2212, dated May 1, 2003.
Part 1—Web Inspections
(g) At the applicable times specified in
paragraph (g)(1), (g)(2), or (g)(3) of Table 1 of
this AD, do initial and repetitive detailed
inspections for cracks of the upper surface of
the aft lower spar web of the inboard and
outboard struts, as applicable; and before
further flight, do any applicable repair; by
doing all the actions specified in ‘‘Part 1—
Web Inspection’’ of the Work Instructions of
the service bulletin. For certain airplanes, the
repetitive inspections may be deferred or
ended provided that the optional stiffener
addition specified in paragraph (k) of this AD
is done.
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.’’
TABLE 1.—COMPLIANCE TIMES FOR WEB INSPECTION
For airplanes identified in the Service Bulletin
as—
Initial compliance time is—
Repetitive interval is—
(1) Group 1 airplanes on which the modification
specified in Boeing Service Bulletin 747–54–
2028, dated August 1, 1972, has been done;
and Group 2 airplanes.
(2) Group 1 airplanes on which the modification
specified in Boeing Service Bulletin 747–54–
2028, dated August 1, 1972, has not been
done; and Group 7 airplanes.
Within 12 months after the effective date of
this AD.
At intervals not to exceed 2,400 flight cycles.
Within 6 months after the effective date of this
AD.
At intervals not to exceed 350 flight cycles.
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Federal Register / Vol. 70, No. 155 / Friday, August 12, 2005 / Rules and Regulations
47089
TABLE 1.—COMPLIANCE TIMES FOR WEB INSPECTION—Continued
For airplanes identified in the Service Bulletin
as—
Initial compliance time is—
Repetitive interval is—
(3) Group 3, 4, 5, 6, and 8 airplanes .................
Within 12 months after the effective date of
this AD.
At intervals not to exceed 1,200 flight cycles.
Part 2—Intermediate Web Bay Inspection
(h) At the applicable times specified in
paragraph (h)(1) or (h)(2) of Table 2 of this
AD, do initial and repetitive detailed
inspections for cracks of the upper surface of
the intermediate web bay of the aft lower
spar; and before further flight do any
applicable repair; by doing all the actions
specified in ‘‘Part 2—Intermediate Web Bay
Inspection’’ of the Work Instructions of the
service bulletin. The repetitive inspections
may be ended provided that the optional
intermediate stiffener addition specified in
paragraph (l) of this AD is done.
TABLE 2.—COMPLIANCE TIMES FOR INTERMEDIATE WEB BAY INSPECTIONS
For airplanes identified in the Service Bulletin
as—
Initial compliance time is—
Repetitive interval is—
(1) Group 1 through 4 airplanes on which the
modification specified in Boeing Service Bulletin 747–71–2188, dated March 14, 1983,
has been done and on which the additional
work specified in Boeing Service Bulletin
747–71–2188, Revision 1, dated January
17, 1986; or Revision 2, dated March 26,
1987; has not been done.
(2) Group 5 airplanes on which the modification specified in Boeing Service Bulletin
747–54–2115, dated February 14, 1986; or
Revision 1, dated May 12, 1988; has not
been done.
Within 6 months after the effective date of this
AD.
At intervals not to exceed 350 flight cycles.
Within 6 months after the effective date of this
AD.
At intervals not to exceed 350 flight cycles.
Part 3—Maraging or H–11 Steel Bolt
Inspection
(i) For Group 1 through 6 airplanes
identified in the service bulletin: Within 12
months after the effective date of this AD, do
a detailed inspection and torque check of the
bolts common to the aft lower spar chords
and the fitting of the rear engine mount
bulkhead for missing, loose, or fractured
bolts, and do any applicable replacement
(including related investigative actions and
corrective action), by doing all the actions
specified in ‘‘Part 3—Maraging or H–11 Steel
Bolt Inspection’’ of the Work Instructions of
the service bulletin, except as provided by
paragraph (o) of this AD. Do any applicable
replacements (including related investigative
actions and corrective action) before further
flight, except as provided by paragraph (j) of
this AD. Repeat the actions thereafter at
intervals not to exceed 18 months. The
inspections and torque checks specified in
paragraph (i) of this AD may be ended
provided that the replacement specified in
paragraph (n) of this AD is done.
(j) If during any inspection required by
paragraph (i) of this AD, one of the
conditions specified in paragraphs (j)(1) and
(j)(2) of this AD is found, do the applicable
actions specified in paragraphs (j)(1) and
(j)(2) of this AD.
(1) If a missing or fractured bolt is found
on the inboard strut in any one bay, within
36 months after replacing the bolt with a new
bolt, do the replacement specified in
paragraph (n) of this AD.
(2) If two or more missing or fractured bolts
are found in any one bay, before further
flight, do the replacement specified in
paragraph (n) of this AD.
Part 4—Optional Stiffener Addition
(k) Except as provided by paragraph (o) of
this AD, accomplishing the optional stiffener
addition for the inboard and outboard struts,
doing the related investigation actions, and
doing any applicable repair, by doing all the
actions specified in ‘‘Part 4—Stiffener
Addition’’ of the Work Instructions of the
service bulletin before further flight after
accomplishing the actions specified in
paragraph (g) of this AD, defers or ends the
repetitive inspections required by paragraph
(g) of this AD as follows:
(1) For airplanes listed in paragraph (g)(2)
of Table 1 of this AD, accomplishing the
optional stiffener addition extends the
repetitive inspections required by paragraph
(g) of this AD to intervals not to exceed 2,400
flight cycles.
(2) For airplanes listed in paragraph (g)(3)
of Table 1 of this AD, accomplishing the
optional stiffener addition ends the repetitive
inspections required by paragraph (g) of this
AD.
(m) Where the service bulletin specifies to
install stiffeners as shown in ‘‘service
bulletin 747–71–2188 Revision 1 or later
releases (Group 1, 2, 3, and 4 Airplanes) or
747–54–2115 Original Issue or Revision 1
(Group 5 Airplanes),’’ this AD requires that
those actions be done in accordance with
Boeing Service Bulletin 747–71–2188,
Revision 1, dated January 17, 1986, or
Revision 2, dated March 26, 1987; or Boeing
Service Bulletin 747–54–2115, dated
February 14, 1986, or Revision 1, dated May
12, 1988; as applicable, except as provided
by paragraph (o) of this AD.
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Part 5—Optional Intermediate Stiffener
Addition
(l) For airplanes identified in paragraphs
(h)(1) and (h)(2) of Table 2 of this AD:
Accomplishing the optional intermediate
stiffener addition for the inboard and
outboard struts, by doing all the actions
specified in ‘‘Part 5—Intermediate Stiffener
Addition’’ of the Work Instructions of the
service bulletin before further flight after
accomplishing the actions specified in
paragraph (h) of this AD, except as provided
by paragraph (m) of this AD, ends the
repetitive inspections required by paragraph
(h) of this AD.
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Part 6—Maraging or H–11 Steel Bolt
Replacement
(n) For Group 1 through 6 airplanes
identified in the service bulletin: Except as
provided by paragraph (o) of this AD,
replacing all Maraging or H–11 steel bolts
with new inconel bolts, doing the related
investigation actions, and doing any
applicable corrective action, by doing all the
actions specified in ‘‘Part 6—Maraging or H–
11 Steel Bolt Replacement’’ of the Work
Instructions of the service bulletin ends the
inspections and torque checks required by
paragraph (i) of this AD.
Contact the FAA
(o) If during any action required by this AD
the service bulletin specifies to contact
Boeing for additional instructions; or if
Boeing Service Bulletin 747–71–2188,
Revision 1, dated January 17, 1986, or
Revision 2, dated March 26, 1987; or Boeing
Service Bulletin 747–54–2115, dated
February 14, 1986, or Revision 1, dated May
12, 1988; specifies to repair according to
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47090
Federal Register / Vol. 70, No. 155 / Friday, August 12, 2005 / Rules and Regulations
operators equivalent procedures: Before
further flight, repair according to a method
approved by the Manager, Seattle Aircraft
Certification Office (ACO), FAA; or according
to data meeting the certification basis of the
airplane approved by an Authorized
Representative for the Boeing 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 approval must
specifically reference this AD.
Parts Installation
(p) As of the effective date of this AD, no
person may install a Maraging or H–11 steel
bolt in the locations specified in this AD, on
any airplane.
Alternative Methods of Compliance
(AMOCs)
(q) 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.
Material Incorporated by Reference
(r) You must use Boeing Alert Service
Bulletin 747–54A2212, dated May 1, 2003, to
perform the actions that are required by this
AD, unless the AD specifies otherwise. The
Director of the Federal Register approves the
incorporation by reference of this document
in accordance with 5 U.S.C. 552(a) and 1 CFR
part 51. To get copies of the service
information, contact Boeing Commercial
Airplanes, P.O. Box 3707, Seattle,
Washington 98124–2207. To view the AD
docket, go to the Docket Management
Facility, U.S. Department of Transportation,
400 Seventh Street SW., room PL–401, Nassif
Building, Washington, DC. To review copies
of the service information, go to 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 August
4, 2005.
Kevin M. Mullin,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 05–15882 Filed 8–11–05; 8:45 am]
BILLING CODE 4910–13–U
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 97
[Docket No. 30452; Amdt. No. 3128]
Standard Instrument Approach
Procedures, Weather Takeoff
Minimums; Miscellaneous
Amendments
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
VerDate jul<14>2003
15:14 Aug 11, 2005
Jkt 205001
SUMMARY: This amendment establishes,
amends, suspends, or revokes Standard
Instrument Approach Procedures
(SIAPs) and/or Weather Takeoff
Minimums for operations at certain
airports. These regulatory actions are
needed because of the adoption of new
or revised criteria, or because of changes
occurring in the National Airspace
System, such as the commissioning of
new navigational facilities, addition of
new obstacles, or changes in air traffic
requirements. These changes are
designed to provide safe and efficient
use of the navigable airspace and to
promote safe flight operations under
instrument flight rules at the affected
airports.
This rule is effective August 12,
2005. The compliance date for each
SIAP and/or Weather Takeoff
Minimums is specified in the
amendatory provisions.
The incorporation by reference of
certain publications listed in the
regulations is approved by the Director
of the Federal Register as of August 12,
2005.
ADDRESSES: Availability of matters
incorporated by reference in the
amendment is as follows:
For Examination—
1. FAA Rules Docket, FAA
Headquarters Building, 800
Independence Avenue, SW.,
Washington, DC 20591;
2. The FAA Regional Office of the
region in which the affected airport is
located;
3. The National Flight Procedures
Office, 6500 South MacArthur Blvd.,
Oklahoma City, OK 73169 or,
4. The National Archives and Records
Administration (NARA). For
information on the availability of this
material at NARA, call 202–741–6030,
or go to: https://www.archives.gov/
federal_register/
code_of_federal_regulations/
ibr_locations.html.
For Purchase—Individual SIAP and
Weather Takeoff Minimums copies may
be obtained from:
1. FAA Public Inquiry Center (APA–
200), FAA Headquarters Building, 800
Independence Avenue, SW.,
Washington, DC 20591; or
2. The FAA Regional Office of the
region in which the affected airport is
located.
By Subscription—Copies of all SIAPs
and Weather Takeoff Minimums mailed
once every 2 weeks, are for sale by the
Superintendent of Documents, U.S.
Government Printing Office,
Washington, DC 20402.
FOR FURTHER INFORMATION CONTACT:
Donald P. Pate, Flight Procedure
DATES:
PO 00000
Frm 00014
Fmt 4700
Sfmt 4700
Standards Branch (AFS–420), Flight
Technologies and Programs Division,
Flight Standards Service, Federal
Aviation Administration, Mike
Monroney Aeronautical Center, 6500
South MacArthur Blvd. Oklahoma City,
OK 73169 (Mail Address: P.O. Box
25082 Oklahoma City, OK 73125)
telephone: (405) 954–4164.
SUPPLEMENTARY INFORMATION: This
amendment to Title 14 of the Code of
Federal Regulations, Part 97 (14 CFR
part 97), establishes, amends, suspends,
or revokes SIAPs and/or Weather
Takeoff Minimums. The complete
regulatory description of each SIAP
and/or Weather Takeoff Minimums is
contained in official FAA form
documents which are incorporated by
reference in this amendment under 5
U.S.C. 552(a), 1 CFR part 51, and 14
CFR part 97.20. The applicable FAA
Forms are identified as FAA Forms
8260–3, 8260–4, 8260–5 and 8260–15A.
Materials incorporated by reference are
available for examination or purchase as
stated above.
The large number of SIAPs and/or
Weather Takeoff Minimums, their
complex nature, and the need for a
special format make their verbatim
publication in the Federal Register
expensive and impractical. Further,
airmen do not use the regulatory text of
the SIAPs and/or Weather Takeoff
Minimums but refer to their depiction
on charts printed by publishers of
aeronautical materials. Thus, the
advantages of incorporation by reference
are realized and publication of the
complete description of each SIAP and/
or Weather Takeoff Minimums
contained in FAA form documents is
unnecessary. The provisions of this
amendment state the affected CFR
sections, with the types and effective
dates of the SIAPs and/or Weather
Takeoff Minimums. This amendment
also identifies the airport, its location,
the procedure identification and the
amendment number.
The Rule
This amendment to 14 CFR part 97 is
effective upon publication of each
separate SIAP and/or Weather Takeoff
Minimums as contained in the
transmittal. Some SIAP and/or Weather
Takeoff Minimums amendments may
have been previously issued by the FAA
in a Flight Data Center (FDC) Notice to
Airmen (NOTAM) as an emergency
action of immediate flight safety relating
directly to published aeronautical
charts. The circumstances which
created the need for some SIAP, and/or
Weather Takeoff Minimums
amendments may require making them
E:\FR\FM\12AUR1.SGM
12AUR1
]]>Agencies
[Federal Register Volume 70, Number 155 (Friday, August 12, 2005)]
[Rules and Regulations]
[Pages 47086-47090]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-15882]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-20325; Directorate Identifier 2003-NM-129-AD;
Amendment 39-14217; AD 2005-16-11]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 747-100, 747-100B, 747-
100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747SP, and 747SR
Series Airplanes; Equipped With Pratt & Whitney Model JT9D-3 and -7
Series Engines
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain Boeing transport category airplanes listed above. This AD
requires repetitive inspections for cracks of the upper surface of the
aft lower spar web of the inboard and outboard struts, as applicable;
and repetitive inspections for cracks of the upper surface of the
intermediate web bay of the aft lower spar. This AD also requires
repetitive inspections and torque checks of the bolts common to the aft
lower spar chords and the fitting of the rear engine mount bulkhead for
missing, loose, or fractured bolts, as applicable; and corrective
action, if necessary. This AD is prompted by reports of cracking in the
aft lower spar web and reports of missing and fractured bolts. We are
issuing this AD to detect and correct cracking of the aft lower spar
web, and to prevent missing, loose, or fractured bolts common to the
aft lower spar chords and the fitting of the rear engine mount
bulkhead, which could result in the loss of the aft lower spar load
path and reduced structural capability of the pylon, which may result
in the separation of the engine from the airplane.
DATES: This AD becomes effective September 16, 2005.
The incorporation by reference of a certain publication listed in
the AD is approved by the Director of the Federal Register as of
September 16, 2005.
ADDRESSES: For service information identified in this AD, contact
Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-
2207.
Docket: The AD docket contains the proposed AD, comments, and any
final disposition. You can examine the AD docket on the Internet at
https://
[[Page 47087]]
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 U.S.
Department of Transportation, 400 Seventh Street SW., room PL-401,
Washington, DC. This docket number is FAA-2005-20325; the directorate
identifier for this docket is 2003-NM-129-AD.
FOR FURTHER INFORMATION CONTACT: Candice Gerretsen, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
917-6428; fax (425) 917-6590.
SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39
with an AD for certain Boeing transport category airplanes. That
action, published in the Federal Register on February 10, 2005 (70 FR
7052), proposed to require repetitive inspections for cracks of the
upper surface of the aft lower spar web of the inboard and outboard
struts, as applicable; and repetitive inspections for cracks of the
upper surface of the intermediate web bay of the aft lower spar. That
action also proposed to require repetitive inspections and torque
checks of the bolts common to the aft lower spar chords and the fitting
of the rear engine mount bulkhead for missing, loose, or fractured
bolts, as applicable; and corrective action, if necessary.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comments that have been
submitted on the proposed AD.
Request To Revise Applicability
One commenter requests that the applicability be revised to read:
This AD applies to engine strut assemblies installed on Boeing
Model 747-100, -100B, -100B SUD, -200B, -200C, -200F, and -300
series airplanes, and Model 747-SP and 747 SR series airplanes;
certificated in any category; equipped with Pratt and Whitney Model
JT9D-3 and -7 series engines.
The commenter contends that retired airplanes are not included in
the applicability of the proposed AD and states that strut assemblies
may be interchanged between airplanes.
We do not agree to revise the applicability. Retired airplanes are
included by variable number in Boeing Alert Service Bulletin 747-
54A2212, dated May 1, 2003 (referenced as the appropriate source of
information for the applicability of the proposed AD). Also, it is our
policy to not write the applicability of ADs against a part of the
airframe, such as the strut. Section 39.3 (``Definition of
airworthiness directives'') of the Federal Aviation Regulations (14 CFR
39.3) specifies that airworthiness directives apply to the following
products: aircraft, aircraft engine, propeller, or appliance (which is
not part of the airframe). We have not changed the final rule in this
regard.
Request To Advise Operators That Strut Assemblies Are Interchangeable
The same commenter requests that a clause be added to advise
operators that the strut assemblies are interchangeable and that, if a
strut assembly is installed on another airplane, that airplane must be
evaluated to determine if it is applicable to the proposed AD.
We agree that the strut assembly is an interchangeable part.
However, we do not agree to revise the final rule to advise operators
that the strut assemblies are interchangeable because the strut is a
serialized part that can be tracked. Operators should note that they
are responsible for maintaining the configuration of its airplanes,
especially in an area affected by an AD. As required by section 39.17
of the Federal Aviation Regulations (14 CFR 39.17), for airplanes that
have been modified, altered, or repaired so that the accomplishment of
the requirements of this final rule is affected, the operator must
request approval for an alternative method of compliance according to
paragraph (q) of this AD.
Request To Define Airplane Groups by Pylon Web Thickness
One commenter requests that the airplane groups be defined solely
by pylon web thickness. The commenter states that the groups identified
in the service bulletin do not reflect its airplane configuration. The
commenter notes that it has Group 1 airplanes with 0.032-inch pylon
webs, Group 3 airplanes with 0.025-inch pylon webs, and some airplanes
with mixed 0.025-inch pylon webs and 0.032-inch pylon webs.
We acknowledge that the service bulletin may not reflect an
operator's current aircraft configuration because of post-delivery
modifications. Since the groupings are not only defined by web
thickness but also by the location of web stiffeners and the web
material; we do not agree to revise the final rule to define airplane
groups by pylon web thickness. Operators are responsible for
maintaining the configuration of its airplanes. If the configuration of
an airplane has been changed in an area affected by this final rule and
the accomplishment of the requirements of this final rule is affected,
operators must request approval for an alternative method of compliance
according to paragraph (q) of this AD as required by 14 CFR 39.19.
Explanation of Change to Applicability
We have revised the applicability of the proposed AD to identify
model designations as published in the most recent type certificate
data sheet for the affected models.
Conclusion
We have carefully reviewed the available data, including the
comments that have been submitted, and determined that air safety and
the public interest require adopting the AD 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 244 airplanes of the affected design in the
worldwide fleet. This AD will affect about 82 airplanes of U.S.
registry. The following table provides the estimated costs for U.S.
operators to comply with this AD.
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Applicable airplanes identified in Average labor airplane, per
Boeing Alert Service Bulletin 747- Action Work hours rate per hour inspection
54A2212 As-- cycle
----------------------------------------------------------------------------------------------------------------
Groups 1-6............................ Web inspection.......... 8 $65 $520
Groups 7-8............................ Web inspection.......... 4 65 260
Groups 1-5............................ Web bay inspection...... 4 65 260
[[Page 47088]]
Groups 1-6............................ Bolt inspection......... 4 65 260
----------------------------------------------------------------------------------------------------------------
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 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. 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 FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
2005-16-11 Boeing: Amendment 39-14217. Docket No. FAA-2005-20325;
Directorate Identifier 2003-NM-129-AD.
Effective Date
(a) This AD becomes effective September 16, 2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Boeing Model 747-100, 747-100B, 747-100B
SUD, 747-200B, 747-200C, 747-200F, 747-300, 747SP, and 747SR series
airplanes; certificated in any category; equipped with Pratt &
Whitney Model JT9D-3 and -7 series engines; as identified in Boeing
Alert Service Bulletin 747-54A2212, dated May 1, 2003.
Unsafe Condition
(d) This AD was prompted by reports of cracking in the aft lower
spar web and reports of missing and fractured bolts. We are issuing
this AD to detect and correct cracking of the aft lower spar web,
and to prevent missing, loose, or fractured bolts common to the aft
lower spar chords and the fitting of the rear engine mount bulkhead,
which could result in the loss of the aft lower spar load path and
reduced structural capability of the pylon, which may result in the
separation of the engine from 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.
Service Bulletin Reference
(f) The term ``service bulletin,'' as used in this AD, means
Boeing Alert Service Bulletin 747-54A2212, dated May 1, 2003.
Part 1--Web Inspections
(g) At the applicable times specified in paragraph (g)(1),
(g)(2), or (g)(3) of Table 1 of this AD, do initial and repetitive
detailed inspections for cracks of the upper surface of the aft
lower spar web of the inboard and outboard struts, as applicable;
and before further flight, do any applicable repair; by doing all
the actions specified in ``Part 1--Web Inspection'' of the Work
Instructions of the service bulletin. For certain airplanes, the
repetitive inspections may be deferred or ended provided that the
optional stiffener addition specified in paragraph (k) of this AD is
done.
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.''
Table 1.--Compliance Times for Web Inspection
------------------------------------------------------------------------
For airplanes identified in Initial compliance Repetitive interval
the Service Bulletin as-- time is-- is--
------------------------------------------------------------------------
(1) Group 1 airplanes on Within 12 months At intervals not to
which the modification after the effective exceed 2,400 flight
specified in Boeing Service date of this AD. cycles.
Bulletin 747-54-2028, dated
August 1, 1972, has been
done; and Group 2 airplanes.
(2) Group 1 airplanes on Within 6 months At intervals not to
which the modification after the effective exceed 350 flight
specified in Boeing Service date of this AD. cycles.
Bulletin 747-54-2028, dated
August 1, 1972, has not
been done; and Group 7
airplanes.
[[Page 47089]]
(3) Group 3, 4, 5, 6, and 8 Within 12 months At intervals not to
airplanes. after the effective exceed 1,200 flight
date of this AD. cycles.
------------------------------------------------------------------------
Part 2--Intermediate Web Bay Inspection
(h) At the applicable times specified in paragraph (h)(1) or
(h)(2) of Table 2 of this AD, do initial and repetitive detailed
inspections for cracks of the upper surface of the intermediate web
bay of the aft lower spar; and before further flight do any
applicable repair; by doing all the actions specified in ``Part 2--
Intermediate Web Bay Inspection'' of the Work Instructions of the
service bulletin. The repetitive inspections may be ended provided
that the optional intermediate stiffener addition specified in
paragraph (l) of this AD is done.
Table 2.--Compliance Times for Intermediate Web Bay Inspections
------------------------------------------------------------------------
For airplanes identified in Initial compliance Repetitive interval
the Service Bulletin as-- time is-- is--
------------------------------------------------------------------------
(1) Group 1 through 4 Within 6 months At intervals not to
airplanes on which the after the effective exceed 350 flight
modification specified in date of this AD. cycles.
Boeing Service Bulletin 747-
71-2188, dated March 14,
1983, has been done and on
which the additional work
specified in Boeing Service
Bulletin 747-71-2188,
Revision 1, dated January
17, 1986; or Revision 2,
dated March 26, 1987; has
not been done.
(2) Group 5 airplanes on Within 6 months At intervals not to
which the modification after the effective exceed 350 flight
specified in Boeing Service date of this AD. cycles.
Bulletin 747-54-2115, dated
February 14, 1986; or
Revision 1, dated May 12,
1988; has not been done.
------------------------------------------------------------------------
Part 3--Maraging or H-11 Steel Bolt Inspection
(i) For Group 1 through 6 airplanes identified in the service
bulletin: Within 12 months after the effective date of this AD, do a
detailed inspection and torque check of the bolts common to the aft
lower spar chords and the fitting of the rear engine mount bulkhead
for missing, loose, or fractured bolts, and do any applicable
replacement (including related investigative actions and corrective
action), by doing all the actions specified in ``Part 3--Maraging or
H-11 Steel Bolt Inspection'' of the Work Instructions of the service
bulletin, except as provided by paragraph (o) of this AD. Do any
applicable replacements (including related investigative actions and
corrective action) before further flight, except as provided by
paragraph (j) of this AD. Repeat the actions thereafter at intervals
not to exceed 18 months. The inspections and torque checks specified
in paragraph (i) of this AD may be ended provided that the
replacement specified in paragraph (n) of this AD is done.
(j) If during any inspection required by paragraph (i) of this
AD, one of the conditions specified in paragraphs (j)(1) and (j)(2)
of this AD is found, do the applicable actions specified in
paragraphs (j)(1) and (j)(2) of this AD.
(1) If a missing or fractured bolt is found on the inboard strut
in any one bay, within 36 months after replacing the bolt with a new
bolt, do the replacement specified in paragraph (n) of this AD.
(2) If two or more missing or fractured bolts are found in any
one bay, before further flight, do the replacement specified in
paragraph (n) of this AD.
Part 4--Optional Stiffener Addition
(k) Except as provided by paragraph (o) of this AD,
accomplishing the optional stiffener addition for the inboard and
outboard struts, doing the related investigation actions, and doing
any applicable repair, by doing all the actions specified in ``Part
4--Stiffener Addition'' of the Work Instructions of the service
bulletin before further flight after accomplishing the actions
specified in paragraph (g) of this AD, defers or ends the repetitive
inspections required by paragraph (g) of this AD as follows:
(1) For airplanes listed in paragraph (g)(2) of Table 1 of this
AD, accomplishing the optional stiffener addition extends the
repetitive inspections required by paragraph (g) of this AD to
intervals not to exceed 2,400 flight cycles.
(2) For airplanes listed in paragraph (g)(3) of Table 1 of this
AD, accomplishing the optional stiffener addition ends the
repetitive inspections required by paragraph (g) of this AD.
Part 5--Optional Intermediate Stiffener Addition
(l) For airplanes identified in paragraphs (h)(1) and (h)(2) of
Table 2 of this AD: Accomplishing the optional intermediate
stiffener addition for the inboard and outboard struts, by doing all
the actions specified in ``Part 5--Intermediate Stiffener Addition''
of the Work Instructions of the service bulletin before further
flight after accomplishing the actions specified in paragraph (h) of
this AD, except as provided by paragraph (m) of this AD, ends the
repetitive inspections required by paragraph (h) of this AD.
(m) Where the service bulletin specifies to install stiffeners
as shown in ``service bulletin 747-71-2188 Revision 1 or later
releases (Group 1, 2, 3, and 4 Airplanes) or 747-54-2115 Original
Issue or Revision 1 (Group 5 Airplanes),'' this AD requires that
those actions be done in accordance with Boeing Service Bulletin
747-71-2188, Revision 1, dated January 17, 1986, or Revision 2,
dated March 26, 1987; or Boeing Service Bulletin 747-54-2115, dated
February 14, 1986, or Revision 1, dated May 12, 1988; as applicable,
except as provided by paragraph (o) of this AD.
Part 6--Maraging or H-11 Steel Bolt Replacement
(n) For Group 1 through 6 airplanes identified in the service
bulletin: Except as provided by paragraph (o) of this AD, replacing
all Maraging or H-11 steel bolts with new inconel bolts, doing the
related investigation actions, and doing any applicable corrective
action, by doing all the actions specified in ``Part 6--Maraging or
H-11 Steel Bolt Replacement'' of the Work Instructions of the
service bulletin ends the inspections and torque checks required by
paragraph (i) of this AD.
Contact the FAA
(o) If during any action required by this AD the service
bulletin specifies to contact Boeing for additional instructions; or
if Boeing Service Bulletin 747-71-2188, Revision 1, dated January
17, 1986, or Revision 2, dated March 26, 1987; or Boeing Service
Bulletin 747-54-2115, dated February 14, 1986, or Revision 1, dated
May 12, 1988; specifies to repair according to
[[Page 47090]]
operators equivalent procedures: Before further flight, repair
according to a method approved by the Manager, Seattle Aircraft
Certification Office (ACO), FAA; or according to data meeting the
certification basis of the airplane approved by an Authorized
Representative for the Boeing 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
approval must specifically reference this AD.
Parts Installation
(p) As of the effective date of this AD, no person may install a
Maraging or H-11 steel bolt in the locations specified in this AD,
on any airplane.
Alternative Methods of Compliance (AMOCs)
(q) 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.
Material Incorporated by Reference
(r) You must use Boeing Alert Service Bulletin 747-54A2212,
dated May 1, 2003, to perform the actions that are required by this
AD, unless the AD specifies otherwise. The Director of the Federal
Register approves the incorporation by reference of this document in
accordance with 5 U.S.C. 552(a) and 1 CFR part 51. To get copies of
the service information, contact Boeing Commercial Airplanes, P.O.
Box 3707, Seattle, Washington 98124-2207. To view the AD docket, go
to the Docket Management Facility, U.S. Department of
Transportation, 400 Seventh Street SW., room PL-401, Nassif
Building, Washington, DC. To review copies of the service
information, go to 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 August 4, 2005.
Kevin M. Mullin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-15882 Filed 8-11-05; 8:45 am]
BILLING CODE 4910-13-U
