Airworthiness Directives; Boeing Model 747-100B, 747-200B, 747-200F, 747-300, 747-400, 747-400F, and 747SP Series Airplanes, 32818-32822 [06-5125]
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Federal Register / Vol. 71, No. 109 / Wednesday, June 7, 2006 / Rules and Regulations
Credit for Previous Service Bulletin
(m) For Model A300 B4–601, B4–603, B4–
620, and B4–622 airplanes and Model A300
C4–605R Variant F airplanes: Actions done
before the effective date of this AD in
accordance with Airbus Service Bulletin
A300–28–6089, dated July 18, 2005, are
acceptable for compliance with the
requirements of paragraph (l) of this AD.
Alternative Methods of Compliance
(AMOCs)
(n)(1) The Manager, International Branch,
ANM–116, Transport Airplane Directorate,
FAA, has the authority to approve AMOCs
for this AD, if requested in accordance with
the procedures found in 14 CFR 39.19.
(2) Before using any AMOC approved in
accordance with § 39.19 on any airplane to
which the AMOC applies, notify the
appropriate principal inspector in the FAA
Flight Standards Certificate Holding District
Office.
Related Information
(o) French airworthiness directive F–2005–
199, dated December 7, 2005, also addresses
the subject of this AD.
Material Incorporated by Reference
(p) You must use the Airbus service
information identified in Table 1 of this AD
to perform the actions that are required by
this AD, as applicable, unless the AD
specifies otherwise.
TABLE 1.—MATERIAL INCORPORATED BY REFERENCE
Airbus service information
Revision level
Date
All Operators Telex A300–600–28A6075 ......................................................................................................
All Operators Telex A300–28A6075 ..............................................................................................................
Service Bulletin A300–28–0084, excluding Appendix 01 ..............................................................................
Service Bulletin A300–28–0085 ....................................................................................................................
Service Bulletin A300–28–6089 ....................................................................................................................
Service Bulletin A310–28–2159, excluding Appendix 01 ..............................................................................
Service Bulletin A310–28–2160 ....................................................................................................................
Original ..........
01 ...................
Original ..........
Original ..........
01 ...................
Original ..........
Original ..........
February 20, 2003.
October 24, 2005.
June 28, 2005.
July 18, 2005.
November 28, 2005.
June 28, 2005.
July 18, 2005.
(1) The Director of the Federal Register
approved the incorporation by reference of
the Airbus service information identified in
Table 2 of this AD in accordance with 5
U.S.C. 552(a) and 1 CFR part 51.
TABLE 2.—NEW MATERIAL INCORPORATED BY REFERENCE
Revision level
Date
All Operators Telex A300–28A6075 ..............................................................................................................
Service Bulletin A300–28–0084, excluding Appendix 01 ..............................................................................
Service Bulletin A300–28–0085 ....................................................................................................................
Service Bulletin A300–28–6089 ....................................................................................................................
Service Bulletin A310–28–2159, excluding Appendix 01 ..............................................................................
Service Bulletin A310–28–2160 ....................................................................................................................
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Airbus service information
01 ...................
Original ..........
Original ..........
01 ...................
Original ..........
Original ..........
October 24, 2005.
June 28, 2005.
July 18, 2005.
November 28, 2005.
June 28, 2005.
July 18, 2005.
(Only the first page of Airbus All Operators
Telex A300–28A6075, Revision 01, dated
October 24, 2005, contains the document
number and issue date; no other page of this
document contains this information.)
(2) On May 19, 2004 (69 FR 19756, April
14, 2004), the Director of the Federal Register
approved the incorporation by reference of
Airbus All Operators Telex A300–600–
28A6075, dated February 20, 2003.
(3) Contact Airbus, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France, 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 May 30,
2006.
Jeffrey E. Duven,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 06–5122 Filed 6–6–06; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–24950; Directorate
Identifier 2006–NM–036–AD; Amendment
39–14627; AD 2006–12–03]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 747–100B, 747–200B, 747–200F,
747–300, 747–400, 747–400F, and
747SP Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
AGENCY:
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Final rule; request for
comments.
ACTION:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for certain
747–100B, 747–200B, 747–200F, 747–
300, 747–400, 747–400F, and 747SP
series airplanes. This AD requires doing
inspections of the midpivot bolt and
midpivot bolt access door of the spring
beam of the inboard side of the outboard
struts for discrepancies, installing a
placard on the midpivot bolt access
door, and applicable corrective actions
if necessary. This AD results from
reports indicating that the midpivot bolt
and midpivot bolt access door of the
spring beam of the inboard side of the
outboard struts were installed in the
incorrect position. We are issuing this
AD to ensure that the subject midpivot
bolts and midpivot bolt access doors are
installed in the correct position. If not
installed in the correct position, a
midpivot bolt could be overloaded and
crack or fracture, which could result in
the loss of the spring load path and
consequent separation of the associated
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Federal Register / Vol. 71, No. 109 / Wednesday, June 7, 2006 / Rules and Regulations
outboard strut and engine from the
airplane.
DATES: This AD becomes effective June
22, 2006.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of June 22, 2006.
We must receive comments on this
AD by August 7, 2006.
ADDRESSES: Use one of the following
addresses to submit comments on this
AD.
• DOT Docket Web site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically.
• Mail: Docket Management Facility;
U.S. Department of Transportation, 400
Seventh Street, SW., Nassif Building,
Room PL–401, Washington, DC 20590.
• Fax: (202) 493–2251.
• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
400 Seventh Street, SW., Washington,
DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
Contact Boeing Commercial
Airplanes, P.O. Box 3707, Seattle,
Washington 98124–2207, for service
information identified in this AD.
FOR FURTHER INFORMATION CONTACT: Ivan
Li, Aerospace Engineer, Airframe
Branch, ANM–120S, FAA, Seattle
Aircraft Certification Office, 1601 Lind
Avenue, SW., Renton, Washington
98055–4056; telephone (425) 917–6437;
fax (425) 917–6590.
SUPPLEMENTARY INFORMATION:
Discussion
We have received reports indicating
that the midpivot bolt and midpivot bolt
access door of the spring beam of the
inboard side of the outboard struts were
installed in the incorrect position on
two airplanes. On one of the airplanes,
the midpivot bolts and midpivot bolt
access doors had been installed during
accomplishment of the modification of
the nacelle strut and wing structure in
accordance with Boeing Service Bulletin
747–54A2157 (required by AD 95–13–
05, amendment 39–9285 (60 FR 33333,
June 28, 1995)). Investigation revealed
that the service bulletin specified
incorrect part numbers for the midpivot
bolt access doors. In addition, the
production installation drawings did
not provide clear instructions for
installing the midpivot bolts and
midpivot bolt access doors, which
resulted in the discrepancies on the
other airplane.
The midpivot bolt access door is
attached to the skin of the inboard side
of the outboard struts. A midpivot bolt
access door has anti-rotation tabs that fit
the slots of the midpivot bolt’s head. If
any midpivot bolt access door is not
installed correctly or if its anti-rotation
tabs are not properly aligned with the
slots of the midpivot bolt’s head, the
midpivot bolt and its internal
lubrication channel will not be in
correct position. When the lubrication
32819
channel is not in the correct position, a
midpivot bolt could be overloaded and
crack or fracture. These conditions, if
not corrected, could result in the loss of
a spring beam load path and consequent
separation of the associated outboard
strut and engine from the airplane.
Relevant Service Information
We have reviewed Boeing Alert
Service Bulletin 747–54A2225, dated
February 16, 2006. The service bulletin
describes the inspection procedures
specified in the table below. The service
bulletin also describes procedures for
installing a placard on the midpivot bolt
access doors, and doing applicable
corrective actions if necessary. The
applicable corrective actions include
changing or replacing any midpivot bolt
access door that is damaged or installed
in the incorrect position with a new or
serviceable midpivot bolt access door,
and under certain conditions, replacing
the midpivot bolt with a new bolt. The
service bulletin specifies the following
compliance time depending on the
airplane configuration and accumulated
flight cycles:
• ‘‘Within 24 months from the release
date on this service bulletin or within
90 days from accumulating 8,000 flight
cycles from the accomplishment of SB
747–54A2157, whichever occurs first;’’
• ‘‘Within 24 months from the release
on this service bulletin or within 90
days from accumulating 8,000 total
flight cycles, whichever occurs first;’’ or
• ‘‘Within 90 days from the release
date on this service bulletin.’’
INSPECTIONS
Doing—
Of—
For—
(1) A general visual inspection ...........................
The midpivot bolt access doors .......................
(2) A general visual inspection ...........................
(3) A general visual inspection ...........................
The anti-rotation tabs of the midpivot bolt access doors.
The midpivot bolts ............................................
(4) An ultrasonic inspection ................................
The midpivot bolts ............................................
The correct part number, damage (i.e., wear,
nicks, gouges, elongated fastener holes, or
cracks), or the correct position of its anti-rotation tabs.
Damage (i.e., wear, nicks, gouges, or cracks)
or any missing tab.
Correct position or damage (i.e., nicks, gouges, or cracks).
Cracks.
Accomplishing the actions specified in
the service information is intended to
adequately address the unsafe
condition.
sroberts on PROD1PC70 with RULES
FAA’s Determination and Requirements
of This AD
The unsafe condition described
previously is likely to exist or develop
on other airplanes of the same type
design that may be registered in the U.S.
at some time in the future. Therefore,
we are issuing this AD to ensure that the
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subject midpivot bolts and midpivot
bolt access doors are installed in the
correct position. If not installed in the
correct position, a midpivot bolt could
be overloaded and crack or fracture,
which could result in the loss of the
spring load path and consequent
separation of the associated outboard
strut and engine from the airplane. This
AD requires accomplishing the actions
specified in the service information
described previously, except as
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described under ‘‘Difference Between
the Proposed AD and Service Bulletin.’’
Difference Between the Proposed Rule
and Service Bulletin
Operators should note that, although
the Accomplishment Instructions of the
referenced service bulletin describe
procedures for submitting a report of
inspection findings to Boeing, this AD
will not require that action.
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Federal Register / Vol. 71, No. 109 / Wednesday, June 7, 2006 / Rules and Regulations
Costs of Compliance
Examining the Docket
None of the airplanes affected by this
action are on the U.S. Register. All
airplanes affected by this AD are
currently operated by non-U.S.
operators under foreign registry;
therefore, they are not directly affected
by this AD action. However, we
consider this AD necessary to ensure
that the unsafe condition is addressed if
any affected airplane is imported and
placed on the U.S. Register in the future.
If an affected airplane is imported and
placed on the U.S. Register in the future,
the required inspection and installation
of a placard would take about 6 work
hours per airplane, at an average labor
rate of $80 per work hour. Based on
these figures, the estimated cost of the
AD would be $480 per airplane.
You may examine the AD docket on
the Internet at https://dms.dot.gov, or in
person at the Docket Management
Facility office between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays. The Docket
Management Facility office (telephone
(800) 647–5227) is located on the plaza
level of the Nassif Building at the DOT
street address stated in the ADDRESSES
section. Comments will be available in
the AD docket shortly after the Docket
Management System receives them.
FAA’s Determination of the Effective
Date
No airplane affected by this AD is
currently on the U.S. Register.
Therefore, providing notice and
opportunity for public comment is
unnecessary before this AD is issued,
and this AD may be made effective in
less than 30 days after it is published in
the Federal Register.
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Comments Invited
This AD is a final rule that involves
requirements that affect flight safety and
was not preceded by notice and an
opportunity for public comment;
however, we invite you to submit any
relevant written data, views, or
arguments regarding this AD. Send your
comments to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2006–24950; Directorate Identifier
2006–NM–036–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of the AD that might suggest a
need to modify it.
We will post all comments we
receive, without change, to https://
dms.dot.gov, including any personal
information you provide. We will also
post a report summarizing each
substantive verbal contact with FAA
personnel concerning this AD. Using the
search function of that Web site, anyone
can find and read the comments in any
of our dockets, including the name of
the individual who sent the comment
(or signed the comment on behalf of an
association, business, labor union, etc.).
You may review the DOT’s complete
Privacy Act Statement in the Federal
Register published on April 11, 2000
(65 FR 19477–78), or you may visit
https://dms.dot.gov.
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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 the regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
3. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared a regulatory evaluation
of the estimated costs to comply with
this AD and placed it in the AD docket.
See the ADDRESSES section for a location
to examine the regulatory evaluation.
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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:
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
2006–12–03 Boeing: Amendment 39–14627.
Docket No. FAA–2006–24950;
Directorate Identifier 2006–NM–036–AD.
Effective Date
(a) This AD becomes effective June 22,
2006.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Boeing Model 747–
100B, 747–200B, 747–200F, 747–300, 747–
400, 747–400F, and 747SP series airplanes,
certificated in any category; as identified in
Boeing Alert Service Bulletin 747–54A2225,
dated February 16, 2006.
Unsafe Condition
(d) This AD results from reports indicating
that the midpivot bolt and midpivot bolt
access door of the spring beam of the inboard
side of the outboard struts were installed in
the incorrect position. We are issuing this AD
to ensure that the subject midpivot bolts and
midpivot bolt access doors are installed in
the correct position. If not installed in the
correct position, a midpivot bolt could be
overloaded and crack or fracture, which
could result in the loss of the spring load
path and consequent separation of the
associated outboard strut and 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.
Inspections
(f) Do the inspections specified in Table 1
of this AD at the applicable compliance time
listed in paragraph 1.E., ‘‘Compliance,’’ of
Boeing Alert Service Bulletin 747–54A2225,
dated February 16, 2006; except, where the
service bulletin specifies a compliance time
from the release date of the service bulletin,
this AD requires compliance within the
specified compliance time after the effective
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date of this AD. Do the inspections in
32821
accordance with the Accomplishment
Instructions of the service bulletin.
TABLE 1.—INSPECTIONS
Do—
Of—
For—
(1) A general visual inspection ...........................
The midpivot bolt access doors .......................
(2) A general visual inspection ...........................
(3) A general visual inspection ...........................
The anti-rotation tabs of the midpivot bolt access doors.
The midpivot bolts ............................................
(4) An ultrasonic inspection ................................
The midpivot bolts ............................................
The correct part number, damage (i.e., wear,
nicks, gouges, elongated fastener holes, or
cracks), or the correct position of its anti-rotation tabs.
Damage (i.e., wear, nicks, gouges, or cracks)
or any missing tab.
Correct position or damage (i.e., nicks, gouges, or cracks).
Cracks.
Note 1: There is a discrepancy in Step 2
of Figure 13, Sheet 2, of Boeing Alert Service
Bulletin 747–54A2225, dated February 16,
2006. The ‘‘MORE DATA’’ column of the
table incorrectly describes the anti-rotation
slot installation as being ‘‘horizontal and are
perpendicular to the strut skin aft edge.’’ The
correct description is ‘‘vertical and are
parallel to the strut skin aft edge.’’
Installation of a Placard and Corrective
Actions
(g) Before further flight after doing the
inspections required by paragraph (f) of this
AD, do the applicable actions specified in
Table 2 of this AD in accordance with the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–54A2225, dated
February 16, 2006.
TABLE 2.—INSTALLATION OF A PLACARD AND CORRECTIVE ACTIONS
If—
And if—
Then—
(1) Any midpivot bolt access door has the correct part number and no damage.
(2) Any midpivot bolt access door has the incorrect part number and no damage.
Its anti-rotation tabs are present, are in the
correct position, and have no damage.
Its anti-rotation tabs are present, are in the incorrect position, and have no damage.
Install a placard on the midpivot access door.
(3) Any midpivot bolt access door has the incorrect part number, any damage, or any
damaged or missing anti-rotation tab.
(4) Any midpivot bolt is in the correct position ...
None .................................................................
(5) Any midpivot bolt is in the incorrect position
Any midpivot bolt has any damage ....................
It has no damage .............................................
None .................................................................
It has no damage .............................................
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Replacement of Midpivot Bolt
Parts Installation
(h) If any condition in paragraph (h)(1) or
(h)(2) of this AD is found on any outboard
strut, within 24 months after doing the
inspections required by paragraph (f) of this
AD, replace the midpivot bolt of the spring
beam of the inboard side of that outboard
strut with a new midpivot bolt, in accordance
with the Accomplishment Instructions of
Boeing Alert Service Bulletin 747–54A2225,
dated February 16, 2006.
(1) If any midpivot bolt access door of the
spring beam of the inboard side of the
outboard struts is found in the incorrect
position (i.e., the midpivot bolt access door
has the incorrect part number or its antirotation tabs are in the incorrect position)
and if no damage is found on that bolt during
any inspection required by paragraph (f) of
this AD.
(2) If any midpivot bolt of the spring beam
of the inboard side of the outboard struts is
found in the incorrect position and if no
damage is found on that bolt during any
inspection required by paragraph (f) of this
AD.
(i) As of the effective date of this AD, no
person may install, on any airplane, a
midpivot access door, part number
65B89670–339, 65B89670–340, 654U6624–
356, or 654U6624–357, unless it has been
inspected in accordance with paragraphs
(f)(1) and (f)(2) of this AD and found to have
the correct part number for the door location,
no damage, and no damaged or missing antirotation tab.
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No Reporting
(j) Although the service bulletin referenced
in this AD specifies to submit certain
information to the manufacturer, this AD
does not include that requirement.
Alternative Methods of Compliance
(AMOCs)
(k)(1) The Manager, Seattle Aircraft
Certification Office (ACO), FAA, has the
authority to approve AMOCs for this AD, if
requested in accordance with the procedures
found in 14 CFR 39.19.
(2) Before using any AMOC approved in
accordance with § 39.19 on any airplane to
which the AMOC applies, notify the
appropriate principal inspector in the FAA
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Change the midpivot access door or replace it
with a new or serviceable access door, and
install a placard on the midpivot access
door.
Replace the midpivot access door with a new
or serviceable door and install a placard on
the door.
No further action is required by this paragraph.
Correct the midpivot bolt position.
Replace the midpivot bolt with a new bolt.
Flight Standards Certificate Holding District
Office.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair
required by this AD, if it is approved by an
Authorized Representative for the Boeing
Commercial Airplanes Delegation Option
Authorization Organization who has been
authorized by the Manager, Seattle ACO, to
make those findings. For a repair method to
be approved, the repair must meet the
certification basis of the airplane, and the
approval must specifically refer to this AD.
Material Incorporated by Reference
(1) You must use Boeing Alert Service
Bulletin 747–54A2225, dated February 16,
2006, 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, WA 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
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Federal Register / Vol. 71, No. 109 / Wednesday, June 7, 2006 / Rules and Regulations
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 May 26,
2006.
Jeffrey E. Duven,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 06–5125 Filed 6–6–06; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 71
[Docket No. FAA–2006–24424; Airspace
Docket No. 06–ASO–6]
Amendment of Class D Airspace
Pompano Beach; FL, Amendment of
Class D Airspace, Fort Lauderdale
Executive Airport, FL
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
SUMMARY: This action will amend Class
D airspace at Pompano Beach, FL and
Fort Lauderdale Executive Airport, FL.
As a result of the decommissioning of
the Pompano Beach VHF
Omnidirectional Range (VOR), the legal
description for the Class D airspace at
Pompano Beach, FL, and Fort
Lauderdale Executive Airport, FL, must
be changed.
DATES: Effective Date: 0901 UTC, August
3, 2006.
FOR FURTHER INFORMATION CONTACT:
Mark D. Ward, Manager, Airspace and
Procedures Branch, Air Traffic Division,
Federal Aviation Administration, P.O.
Box 20636, Atlanta, Georgia 30320;
telephone (404) 305–5586.
SUPPLEMENTARY INFORMATION:
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History
An internal evaluation determined
that the legal description for the Class
D airspace at Pompano Beach, FL and
Fort Lauderdale Executive Airport, FL
contains reference to a line made up of
radials off the Pompano Beach VOR,
which has been decommissioned. This
action will amend the legal description
by replacing the reference to a line made
up of a VOR radial, with a line now
made up of geographic coordinates.
Designations for Class D airspace areas
extending upward from the surface of
the earth are published in Paragraphs
VerDate Aug<31>2005
19:09 Jun 06, 2006
Jkt 208001
5000 of FAA Order 7400.9N, dated
September 1, 2005, and effective
September 16, 2005, which is
incorporated by reference in 14 CFR
part 71.1. The Class D designations
listed in this document will be
published subsequently in the Order.
Since this action has no impact on the
users of the airspace in the vicinity of
the Pompano Beach Airpark or Fort
Lauderdale Executive Airport, notice
and public procedure under 5 U.S.C.
553(b) are not necessary.
The Rule
This amendment to part 71 of the
Federal Aviation Regulations (14 CFR
part 71) amends Class D airspace at
Pompano Beach, FL and Fort
Lauderdale Executive Airport, FL.
The FAA has determined that this
proposed regulation only involves an
established body of technical
regulations for which frequent and
routine amendments are necessary to
keep them operationally current. It,
therefore, (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) does not warrant
preparation of a Regulatory Evaluation
as the anticipated impact is so minimal.
Since this is a routine matter that will
only affect air traffic procedures and air
navigation, it is certified that this rule,
when promulgated, will not have a
significant economic impact on a
substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
List of Subjects in 14 CFR Part 71
Airspace, Incorporation by reference,
Navigation (Air).
Adoption of the Amendment
In consideration of the foregoing, the
Federal Aviation Administration
amends 14 CFR part 71 as follows:
I
PART 71—DESGINATION OF CLASS A,
CLASS B, CLASS C, CLASS D, AND
CLASS E AIRSPACE AREAS;
AIRWAYS; ROUTES; AND REPORTING
POINTS
1. The authority citation for part 71
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40103, 40113,
40120; E.O. 10854, 24 FR 9565, 3 CFR, 1959–
1963 Comp., p. 389.
§ 71.1
Points, dated September 1, 2006, and
effective September 16, 2006, is
amended as follows:
Paragraph 5000
Class D airspace.
*
*
*
ASO FL D
*
Pompano Beach, FL [REVISED]
Pompano Beach, Airpark, FL
(Lat. 26°14′50″ N, long. 80°06′40″ W)
Fort Lauderdale Executive Airport, FL
(Lat. 26°11′50″ N, long. 80°10′15″ W)
That airspace extending upward from the
surface to and including 2,500 feet MSL
within a 4-mile radius of Pompano Beach
Airpark; excluding that portion southwest of
a line between lat. 26°15′48″ N., long.
80°10′59″ W; and lat. 26°13′05″ N.; long.
80°08′36″ W and that portion south of a line
1 mile north of and parallel to the extended
runway centerline of Runway 8/26 at Fort
Lauderdale Executive Airport. This Class D
airspace area is effective during the specific
days and times established in advance by a
Notice to Airmen. The effective days and
times will thereafter be continuously
published in the Airport/Facility Directory.
*
*
*
*
*
*
Sfmt 4700
*
*
Issued in College Park, Georgia on May 31,
2006.
Mark D. Ward,
Acting Area Director, Air Traffic Division,
Southern Region.
[FR Doc. 06–5185 Filed 6–6–06; 8:45 am]
BILLING CODE 4910–13–M
2. The incorporation by reference in
14 CFR 71.1 of Federal Aviation
Administration Order 7400.9N,
Airspace Designations and Reporting
Fmt 4700
*
Fort Lauderdale Executive Airport, FL
(Lat. 26°11′50″ N, long. 80°10′15″ W)
Fort Lauderdale-Hollywood International
Airport, FL
(Lat. 26°04′21″ N, long. 80°09′10″ W)
That airspace extending upward from the
surface to and including 2,500 feet MSL
within a 4-mile radius of Fort Lauderdale
Executive Airport; excluding that portion
within the Fort Lauderdale-Hollywood
International Airport, FL, Class C airspace
area and that portion northeast of a line
between lat. 26°15′48″ N; long. 80°10′59″ W;
and lat. 26°13′05″ N; long. 80°08′36″ W and
that portion north of a line 1 mile north of
and parallel to the extended runway
centerline of Runway 8/26 at Fort Lauderdale
Executive Airport. This Class D airspace area
is effective during the specific days and times
established in advance by a Notice to
Airmen. The effective days and times will
thereafter be continuously published in the
Airport/Facility Directory.
[Amended]
Frm 00020
*
ASO FL D Fort Lauderdale Executive
Airport, FL [REVISED]
I
PO 00000
*
E:\FR\FM\07JNR1.SGM
07JNR1
]]>Agencies
[Federal Register Volume 71, Number 109 (Wednesday, June 7, 2006)]
[Rules and Regulations]
[Pages 32818-32822]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 06-5125]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-24950; Directorate Identifier 2006-NM-036-AD;
Amendment 39-14627; AD 2006-12-03]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 747-100B, 747-200B, 747-
200F, 747-300, 747-400, 747-400F, and 747SP Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain 747-100B, 747-200B, 747-200F, 747-300, 747-400, 747-400F, and
747SP series airplanes. This AD requires doing inspections of the
midpivot bolt and midpivot bolt access door of the spring beam of the
inboard side of the outboard struts for discrepancies, installing a
placard on the midpivot bolt access door, and applicable corrective
actions if necessary. This AD results from reports indicating that the
midpivot bolt and midpivot bolt access door of the spring beam of the
inboard side of the outboard struts were installed in the incorrect
position. We are issuing this AD to ensure that the subject midpivot
bolts and midpivot bolt access doors are installed in the correct
position. If not installed in the correct position, a midpivot bolt
could be overloaded and crack or fracture, which could result in the
loss of the spring load path and consequent separation of the
associated
[[Page 32819]]
outboard strut and engine from the airplane.
DATES: This AD becomes effective June 22, 2006.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in the AD as of June 22,
2006.
We must receive comments on this AD by August 7, 2006.
ADDRESSES: Use one of the following addresses to submit comments on
this AD.
DOT Docket Web site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to https://
www.regulations.gov and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility; U.S. Department of
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401,
Washington, DC 20590.
Fax: (202) 493-2251.
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle,
Washington 98124-2207, for service information identified in this AD.
FOR FURTHER INFORMATION CONTACT: Ivan Li, Aerospace Engineer, Airframe
Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind
Avenue, SW., Renton, Washington 98055-4056; telephone (425) 917-6437;
fax (425) 917-6590.
SUPPLEMENTARY INFORMATION:
Discussion
We have received reports indicating that the midpivot bolt and
midpivot bolt access door of the spring beam of the inboard side of the
outboard struts were installed in the incorrect position on two
airplanes. On one of the airplanes, the midpivot bolts and midpivot
bolt access doors had been installed during accomplishment of the
modification of the nacelle strut and wing structure in accordance with
Boeing Service Bulletin 747-54A2157 (required by AD 95-13-05, amendment
39-9285 (60 FR 33333, June 28, 1995)). Investigation revealed that the
service bulletin specified incorrect part numbers for the midpivot bolt
access doors. In addition, the production installation drawings did not
provide clear instructions for installing the midpivot bolts and
midpivot bolt access doors, which resulted in the discrepancies on the
other airplane.
The midpivot bolt access door is attached to the skin of the
inboard side of the outboard struts. A midpivot bolt access door has
anti-rotation tabs that fit the slots of the midpivot bolt's head. If
any midpivot bolt access door is not installed correctly or if its
anti-rotation tabs are not properly aligned with the slots of the
midpivot bolt's head, the midpivot bolt and its internal lubrication
channel will not be in correct position. When the lubrication channel
is not in the correct position, a midpivot bolt could be overloaded and
crack or fracture. These conditions, if not corrected, could result in
the loss of a spring beam load path and consequent separation of the
associated outboard strut and engine from the airplane.
Relevant Service Information
We have reviewed Boeing Alert Service Bulletin 747-54A2225, dated
February 16, 2006. The service bulletin describes the inspection
procedures specified in the table below. The service bulletin also
describes procedures for installing a placard on the midpivot bolt
access doors, and doing applicable corrective actions if necessary. The
applicable corrective actions include changing or replacing any
midpivot bolt access door that is damaged or installed in the incorrect
position with a new or serviceable midpivot bolt access door, and under
certain conditions, replacing the midpivot bolt with a new bolt. The
service bulletin specifies the following compliance time depending on
the airplane configuration and accumulated flight cycles:
``Within 24 months from the release date on this service
bulletin or within 90 days from accumulating 8,000 flight cycles from
the accomplishment of SB 747-54A2157, whichever occurs first;''
``Within 24 months from the release on this service
bulletin or within 90 days from accumulating 8,000 total flight cycles,
whichever occurs first;'' or
``Within 90 days from the release date on this service
bulletin.''
Inspections
------------------------------------------------------------------------
Doing-- Of-- For--
------------------------------------------------------------------------
(1) A general visual The midpivot bolt The correct part
inspection. access doors. number, damage
(i.e., wear, nicks,
gouges, elongated
fastener holes, or
cracks), or the
correct position of
its anti-rotation
tabs.
(2) A general visual The anti-rotation Damage (i.e., wear,
inspection. tabs of the nicks, gouges, or
midpivot bolt cracks) or any
access doors. missing tab.
(3) A general visual The midpivot bolts.. Correct position or
inspection. damage (i.e.,
nicks, gouges, or
cracks).
(4) An ultrasonic inspection The midpivot bolts.. Cracks.
------------------------------------------------------------------------
Accomplishing the actions specified in the service information is
intended to adequately address the unsafe condition.
FAA's Determination and Requirements of This AD
The unsafe condition described previously is likely to exist or
develop on other airplanes of the same type design that may be
registered in the U.S. at some time in the future. Therefore, we are
issuing this AD to ensure that the subject midpivot bolts and midpivot
bolt access doors are installed in the correct position. If not
installed in the correct position, a midpivot bolt could be overloaded
and crack or fracture, which could result in the loss of the spring
load path and consequent separation of the associated outboard strut
and engine from the airplane. This AD requires accomplishing the
actions specified in the service information described previously,
except as described under ``Difference Between the Proposed AD and
Service Bulletin.''
Difference Between the Proposed Rule and Service Bulletin
Operators should note that, although the Accomplishment
Instructions of the referenced service bulletin describe procedures for
submitting a report of inspection findings to Boeing, this AD will not
require that action.
[[Page 32820]]
Costs of Compliance
None of the airplanes affected by this action are on the U.S.
Register. All airplanes affected by this AD are currently operated by
non-U.S. operators under foreign registry; therefore, they are not
directly affected by this AD action. However, we consider this AD
necessary to ensure that the unsafe condition is addressed if any
affected airplane is imported and placed on the U.S. Register in the
future.
If an affected airplane is imported and placed on the U.S. Register
in the future, the required inspection and installation of a placard
would take about 6 work hours per airplane, at an average labor rate of
$80 per work hour. Based on these figures, the estimated cost of the AD
would be $480 per airplane.
FAA's Determination of the Effective Date
No airplane affected by this AD is currently on the U.S. Register.
Therefore, providing notice and opportunity for public comment is
unnecessary before this AD is issued, and this AD may be made effective
in less than 30 days after it is published in the Federal Register.
Comments Invited
This AD is a final rule that involves requirements that affect
flight safety and was not preceded by notice and an opportunity for
public comment; however, we invite you to submit any relevant written
data, views, or arguments regarding this AD. Send your comments to an
address listed under the ADDRESSES section. Include ``Docket No. FAA-
2006-24950; Directorate Identifier 2006-NM-036-AD'' at the beginning of
your comments. We specifically invite comments on the overall
regulatory, economic, environmental, and energy aspects of the AD that
might suggest a need to modify it.
We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact with FAA
personnel concerning this AD. Using the search function of that Web
site, anyone can find and read the comments in any of our dockets,
including the name of the individual who sent the comment (or signed
the comment on behalf of an association, business, labor union, etc.).
You may review the DOT's complete Privacy Act Statement in the Federal
Register published on April 11, 2000 (65 FR 19477-78), or you may visit
https://dms.dot.gov.
Examining the Docket
You may examine the AD docket on the Internet at https://
dms.dot.gov, or in person at the Docket Management Facility office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the DOT
street address stated in the ADDRESSES section. Comments will be
available in the AD docket shortly after the Docket Management System
receives them.
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 the regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this 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
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
adding the following new airworthiness directive (AD):
2006-12-03 Boeing: Amendment 39-14627. Docket No. FAA-2006-24950;
Directorate Identifier 2006-NM-036-AD.
Effective Date
(a) This AD becomes effective June 22, 2006.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Boeing Model 747-100B, 747-200B, 747-
200F, 747-300, 747-400, 747-400F, and 747SP series airplanes,
certificated in any category; as identified in Boeing Alert Service
Bulletin 747-54A2225, dated February 16, 2006.
Unsafe Condition
(d) This AD results from reports indicating that the midpivot
bolt and midpivot bolt access door of the spring beam of the inboard
side of the outboard struts were installed in the incorrect
position. We are issuing this AD to ensure that the subject midpivot
bolts and midpivot bolt access doors are installed in the correct
position. If not installed in the correct position, a midpivot bolt
could be overloaded and crack or fracture, which could result in the
loss of the spring load path and consequent separation of the
associated outboard strut and 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.
Inspections
(f) Do the inspections specified in Table 1 of this AD at the
applicable compliance time listed in paragraph 1.E., ``Compliance,''
of Boeing Alert Service Bulletin 747-54A2225, dated February 16,
2006; except, where the service bulletin specifies a compliance time
from the release date of the service bulletin, this AD requires
compliance within the specified compliance time after the effective
[[Page 32821]]
date of this AD. Do the inspections in accordance with the
Accomplishment Instructions of the service bulletin.
Table 1.--Inspections
------------------------------------------------------------------------
Do-- Of-- For--
------------------------------------------------------------------------
(1) A general visual The midpivot bolt The correct part
inspection. access doors. number, damage
(i.e., wear, nicks,
gouges, elongated
fastener holes, or
cracks), or the
correct position of
its anti-rotation
tabs.
(2) A general visual The anti-rotation Damage (i.e., wear,
inspection. tabs of the nicks, gouges, or
midpivot bolt cracks) or any
access doors. missing tab.
(3) A general visual The midpivot bolts.. Correct position or
inspection. damage (i.e.,
nicks, gouges, or
cracks).
(4) An ultrasonic inspection The midpivot bolts.. Cracks.
------------------------------------------------------------------------
Note 1: There is a discrepancy in Step 2 of Figure 13, Sheet 2,
of Boeing Alert Service Bulletin 747-54A2225, dated February 16,
2006. The ``MORE DATA'' column of the table incorrectly describes
the anti-rotation slot installation as being ``horizontal and are
perpendicular to the strut skin aft edge.'' The correct description
is ``vertical and are parallel to the strut skin aft edge.''
Installation of a Placard and Corrective Actions
(g) Before further flight after doing the inspections required
by paragraph (f) of this AD, do the applicable actions specified in
Table 2 of this AD in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin 747-54A2225, dated
February 16, 2006.
Table 2.--Installation of A Placard and Corrective Actions
------------------------------------------------------------------------
If-- And if-- Then--
------------------------------------------------------------------------
(1) Any midpivot bolt access Its anti-rotation Install a placard on
door has the correct part tabs are present, the midpivot access
number and no damage. are in the correct door.
position, and have
no damage.
(2) Any midpivot bolt access Its anti-rotation Change the midpivot
door has the incorrect part tabs are present, access door or
number and no damage. are in the replace it with a
incorrect position, new or serviceable
and have no damage. access door, and
install a placard
on the midpivot
access door.
(3) Any midpivot bolt access None................ Replace the midpivot
door has the incorrect part access door with a
number, any damage, or any new or serviceable
damaged or missing anti- door and install a
rotation tab. placard on the
door.
(4) Any midpivot bolt is in It has no damage.... No further action is
the correct position. required by this
paragraph.
(5) Any midpivot bolt is in It has no damage.... Correct the midpivot
the incorrect position. bolt position.
Any midpivot bolt has any None................ Replace the midpivot
damage. bolt with a new
bolt.
------------------------------------------------------------------------
Replacement of Midpivot Bolt
(h) If any condition in paragraph (h)(1) or (h)(2) of this AD is
found on any outboard strut, within 24 months after doing the
inspections required by paragraph (f) of this AD, replace the
midpivot bolt of the spring beam of the inboard side of that
outboard strut with a new midpivot bolt, in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
54A2225, dated February 16, 2006.
(1) If any midpivot bolt access door of the spring beam of the
inboard side of the outboard struts is found in the incorrect
position (i.e., the midpivot bolt access door has the incorrect part
number or its anti-rotation tabs are in the incorrect position) and
if no damage is found on that bolt during any inspection required by
paragraph (f) of this AD.
(2) If any midpivot bolt of the spring beam of the inboard side
of the outboard struts is found in the incorrect position and if no
damage is found on that bolt during any inspection required by
paragraph (f) of this AD.
Parts Installation
(i) As of the effective date of this AD, no person may install,
on any airplane, a midpivot access door, part number 65B89670-339,
65B89670-340, 654U6624-356, or 654U6624-357, unless it has been
inspected in accordance with paragraphs (f)(1) and (f)(2) of this AD
and found to have the correct part number for the door location, no
damage, and no damaged or missing anti-rotation tab.
No Reporting
(j) Although the service bulletin referenced in this AD
specifies to submit certain information to the manufacturer, this AD
does not include that requirement.
Alternative Methods of Compliance (AMOCs)
(k)(1) The Manager, Seattle Aircraft Certification Office (ACO),
FAA, has the authority to approve AMOCs for this AD, if requested in
accordance with the procedures found in 14 CFR 39.19.
(2) Before using any AMOC approved in accordance with Sec.
39.19 on any airplane to which the AMOC applies, notify the
appropriate principal inspector in the FAA Flight Standards
Certificate Holding District Office.
(3) An AMOC that provides an acceptable level of safety may be
used for any repair required by this AD, if it is approved by an
Authorized Representative for the Boeing Commercial Airplanes
Delegation Option Authorization Organization who has been authorized
by the Manager, Seattle ACO, to make those findings. For a repair
method to be approved, the repair must meet the certification basis
of the airplane, and the approval must specifically refer to this
AD.
Material Incorporated by Reference
(1) You must use Boeing Alert Service Bulletin 747-54A2225,
dated February 16, 2006, 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, WA
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
[[Page 32822]]
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 May 26, 2006.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 06-5125 Filed 6-6-06; 8:45 am]
BILLING CODE 4910-13-P
