Airworthiness Directives; Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747SR, and 747SP Series Airplanes, 53939-53942 [E7-18541]
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<![CDATA[
Federal Register / Vol. 72, No. 183 / Friday, September 21, 2007 / Rules and Regulations
(k) Turbomeca Mandatory Service Bulletin
No. 218 73 0802, Update No. 1, dated January
8, 2007, pertains to the subject of this AD.
TABLE 1.—AFFECTED FUEL PUMP
SNS—Continued
F112B
F131B
F176B
F220B
F243B
F253B
F262B
F293B
F317B
F320B
F357B
F368B
F420B
F464B
F466B
F477B
F47B
F957B
808
1725
1766
1770
1897
1941
2154
2155
2233
2512
2620
2729
2759
2763
2786
2787
3385
3397
3458
3515
3548
3660
3746
3756
3757
3783
3792
3826
3858
3888
3894
3979
4066
Issued in Burlington, Massachusetts, on
September 11, 2007.
Francis A. Favara,
Manager, Engine and Propeller Directorate,
Aircraft Certification Service.
[FR Doc. E7–18434 Filed 9–20–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
New Requirement
(g) Remove from service the fuel pumps
listed by SN in Table 2 of this AD, and install
a serviceable fuel pump, before accumulating
50 hours in service after the effective date of
this AD, but no later than 30 days from the
effective date of this AD.
TABLE 2.—ADDITIONAL AFFECTED
FUEL PUMP SNS
158B
1749
1750
2103
2577
2665
2728
2837
2882
2887
2894
2933
3045
3120
3200
3220
3277
3293
3323
3326
3395
3438
3581
3725
3729
3884
3923
4123
4129
4213
4241B
B52B
B82B
C01B
D14B
D2B
D71B
D93B
E67B
F129B
F151B
F164B
F335B
F350B
F472B
F48B
F551B
F620B
F652B
F66B
F776B
F801B
F817B
F833B
F944B
F971B
G58B
G61B
ebenthall on PROD1PC69 with RULES
Related Information
(j) European Aviation Safety Agency AD
No. 2007–0030, dated February 6, 2007, also
addresses the subject of this AD.
Jkt 211001
Airworthiness Directives; Boeing
Model 747–100, 747–100B, 747–100B
SUD, 747–200B, 747–200C, 747–200F,
747–300, 747SR, and 747SP Series
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
Alternative Methods of Compliance
(i) The Manager, Engine Certification
Office, has the authority to approve
alternative methods of compliance for this
AD if requested using the procedures found
in 14 CFR 39.19.
15:32 Sep 20, 2007
RIN 2120–AA64
AGENCY:
Definition
(h) For the purpose of this AD, a
serviceable fuel pump is:
(1) A fuel pump that is not listed in Table
1 or Table 2 of this AD; or
(2) A fuel pump that is listed in Table 1
or Table 2 of this AD that has been retested
to verify that it meets maximum fuel flow
requirements.
VerDate Aug<31>2005
[Docket No. FAA–2007–29263; Directorate
Identifier 2007–NM–198–AD; Amendment
39–15210; AD 2007–19–19]
SUMMARY: The FAA is superseding an
existing airworthiness directive (AD)
that applies to certain Boeing Model 747
series airplanes. The existing AD
currently requires repetitive inspections
and torque checks of the hanger fittings
and strut forward bulkhead of the
forward engine mount and adjacent
support structure, and corrective actions
if necessary. The existing AD also
currently requires a terminating action
for the repetitive inspections and
checks. This new AD requires, among
other actions, new repetitive inspections
in the existing area and new areas. This
new AD also provides for an optional
inspection and no longer allows the
existing fastener replacement to
terminate repetitive inspections. This
AD results from new reports of undertorqued or loose fasteners, a cracked
bulkhead chord, and a fractured back-up
angle after operators accomplished the
terminating action required by the
existing AD. We are issuing this AD to
detect and correct loose fasteners and/
or damaged or cracked hanger fittings,
back-up angles, and bulkhead of the
forward engine mount, which could
lead to failure of the hanger fitting and
bulkhead and consequent separation of
the engine from the airplane.
DATES: This AD becomes effective
October 9, 2007.
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53939
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of October 9, 2007.
On December 6, 2000 (65 FR 69862,
November 21, 2000), the Director of the
Federal Register approved the
incorporation by reference of Boeing
Alert Service Bulletin 747–54A2203,
dated August 31, 2000.
We must receive any comments on
this AD by November 20, 2007.
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: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
• Fax: (202) 493–2251.
• Hand Delivery: Room W12–140 on
the ground floor of the West Building,
1200 New Jersey Avenue, SE.,
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:
Tamara Anderson, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 917–6421; fax (425) 917–6590.
SUPPLEMENTARY INFORMATION:
Discussion
On July 13, 2001, we issued AD 2001–
15–02, amendment 39–12336 (66 FR
37884, July 20, 2001). That AD applies
to certain Boeing Model 747 series
airplanes. That AD requires repetitive
inspections and torque checks of the
hanger fittings and strut forward
bulkhead of the forward engine mount
and adjacent support structure, and
corrective actions if necessary. That AD
also requires a terminating action for the
repetitive inspections and checks. That
AD resulted from reports indicating the
detection of loose fasteners of the
hanger fittings and strut forward
bulkhead of the forward engine mount.
The actions specified in that AD are
intended to prevent loose fasteners and
associated damage to the hanger fittings
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Federal Register / Vol. 72, No. 183 / Friday, September 21, 2007 / Rules and Regulations
and bulkhead of the forward engine
mount, which could result in separation
of the engine from the airplane.
ebenthall on PROD1PC69 with RULES
Actions Since AD Was Issued
Since we issued that AD, we have
received new reports of under-torqued
or loose fasteners after operators
accomplished the terminating action
required by AD 2001–15–02 (i.e., Part 6
specified in Boeing Alert Service
Bulletin 747–54A2203, dated August 31,
2000). In addition, we have received a
report of a crack approximately 1.5-inch
in length in the bulkhead chord adjacent
to an upper fastener on a number 2 strut
with approximately 20,050 total flight
cycles and 110,000 total flight hours.
Further investigation revealed that the
back-up angle inside the strut adjacent
to the crack had fractured at its bend
radius. The fracture initiated as a result
of fatigue at multiple locations on the
inner diameter of the bend radius. The
cause of the loose fasteners of the
hanger fittings of the bulkhead of the
forward engine mount is their location
in an area of high vibration and the
design of the bulkhead. Loose fasteners
and/or damaged or cracked hanger
fittings, back-up angles, and bulkhead of
the forward engine mount, if not
corrected, could lead to failure of the
hanger fitting and bulkhead and
consequent separation of the engine
from the airplane.
Relevant Service Information
We have reviewed Boeing Alert
Service Bulletin 747–54A2203, Revision
1, dated August 9, 2007. The service
information describes the following new
procedures:
• Repetitive detailed inspections of
the torque stripes and bulkhead of the
forward engine mount and the adjacent
support structure on the inboard and
outboard struts and repetitive torque
inspections (checks) of the bulkhead for
cracks and/or fretting damage of the
hanger fittings and bulkhead and for
loose or under-torqued fasteners, as
applicable; and applicable related
investigative and corrective actions (i.e.,
Part 2 of the Accomplishment
Instructions).
• Repetitive high frequency eddy
current (HFEC), detailed, or fluorescent
penetrant inspections of the bulkhead of
the forward engine mount on the
inboard and outboard struts for cracks of
the bulkhead chords, evidence of a
fractured internal angle, or cracks/
fracture of the internal angles; as
applicable (i.e., Part 8 of the
Accomplishment Instructions); and
detailed and HFEC inspections to detect
cracks or fracture of the internal angle
and stiffener (i.e., Part 7 of the
VerDate Aug<31>2005
15:32 Sep 20, 2007
Jkt 211001
Accomplishment Instructions), and
applicable related investigative and
corrective actions.
The related investigative actions
involve doing applicable inspections
described previously. The corrective
actions include applying optional
torque stripes; reworking, repairing,
and/or replacing any discrepant part
with a new part; replacing all fasteners
with new fasteners; and contacting
Boeing for certain conditions; as
applicable.
For the inspections specified in Parts
2 and 8 of the Accomplishment
Instructions, the service information
specifies an initial compliance time of
90 days and repeat intervals of 6 and 18
months, depending on the inspection
type. For the inspections specified in
Part 7 of the Accomplishment
Instructions, the service information
specifies an initial compliance time of
18 months and repeat intervals of 36
months. The service bulletin specifies a
compliance time of before further flight
or 18 months for doing the related
investigative and corrective actions, as
applicable.
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. For this reason, we are issuing
this AD to supersede AD 2001–15–02.
This new AD retains the required
fastener replacement, except that action
no longer terminates any repetitive
inspections and torque inspections
(checks). This AD also requires
accomplishing the actions specified in
Parts 2 and 8 of the Accomplishment
Instructions of the service information
described previously, except as
discussed under ‘‘Differences Between
the AD and Service Information.’’ This
AD also provides, as an option, the
inspections specified in Part 7 of the
Accomplishment Instructions of the
service information described
previously.
Interim Action
This is considered to be interim
action. We are currently considering
requiring the inspections and applicable
related investigative and corrective
actions specified in Part 7 of the
Accomplishment Instructions of Boeing
Alert Service Bulletin 747–54A2203,
Revision 1. However, the planned
compliance time for the inspections is
sufficiently long so that notice and
opportunity for prior public comment
will be practicable.
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Fmt 4700
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Differences Between the AD and
Service Information
The service information specifies to
contact the manufacturer for
instructions on how to repair certain
conditions, but this AD requires
repairing those conditions in one of the
following ways:
• Using a method that we approve; or
• Using data that meet the
certification basis of the airplane, and
that have been approved by an
Authorized Representative for the
Boeing Commercial Airplanes
Delegation Option Authorization
Organization whom we have authorized
to make those findings.
Change to Existing AD
This AD will retain certain
requirements of AD 2001–15–02. Since
AD 2001–15–02 was issued, we have
revised the AD format and rearranged
certain paragraphs. As a result, we
reidentified paragraph (c) of AD 2001–
15–02 as paragraph (f) in this AD.
Boeing Commercial Airplanes has
received a Delegation Option
Authorization (DOA). We have revised
paragraph (f) of this AD to delegate the
authority to approve an alternative
method of compliance for any repair
required by this AD to an Authorized
Representative for the Boeing
Commercial Airplanes DOA rather than
a Designated Engineering Representative
(DER).
FAA’s Determination of the Effective
Date
An unsafe condition exists that
requires the immediate adoption of this
AD; therefore, providing notice and
opportunity for public comment before
the AD is issued is impracticable, and
good cause exists to make this AD
effective in less than 30 days.
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 in the
ADDRESSES section. Include ‘‘Docket No.
FAA–2007–29263; Directorate Identifier
2007–NM–198–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
E:\FR\FM\21SER1.SGM
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Federal Register / Vol. 72, No. 183 / Friday, September 21, 2007 / Rules and Regulations
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 Operations office
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The Docket Operations office (telephone
(800) 647–5527) is located on the
ground level of the West 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.
ebenthall on PROD1PC69 with RULES
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;
VerDate Aug<31>2005
15:32 Sep 20, 2007
Jkt 211001
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
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends part 39 of the Federal
Aviation Regulations (14 CFR part 39) as
follows:
I
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by removing amendment 39–12336 (66
FR 37884, July 20, 2001) and adding the
following new airworthiness directive
(AD):
I
2007–19–19 Boeing: Docket No. FAA–2007–
29263; Directorate Identifier 2007–NM–
198–AD; Amendment 39–15210.
Effective Date
(a) This AD becomes effective October 9,
2007.
Affected ADs
(b) This AD supersedes AD 2001–15–02.
Applicability
(c) This AD applies to Boeing Model 747–
100, 747–100B, 747–100B SUD, 747–200B,
747–200C, 747–200F, 747–300, 747SR, and
747SP series airplanes, certificated in any
category; as identified in Boeing Alert
Service Bulletin 747–54A2203, Revision 1,
dated August 9, 2007.
Unsafe Condition
(d) This AD results from new reports of
under-torqued or loose fasteners, a cracked
bulkhead chord, and a fractured back-up
angle after operators accomplished the
terminating action required by the existing
AD. We are issuing this AD to detect and
correct loose fasteners and/or damaged or
cracked hanger fittings, back-up angles, and
bulkhead of the forward engine mount,
which could lead to failure of the hanger
fitting and bulkhead and consequent
separation of the engine from the airplane.
PO 00000
Frm 00029
Fmt 4700
Sfmt 4700
53941
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.
Certain Requirement of AD 2001–15–02
(f) Within 60 months after August 24, 2001
(the effective date of AD 2001–15–02):
Accomplish all actions specified in Part 6 of
the Accomplishment Instructions of Boeing
Alert Service Bulletin 747–54A2203, dated
August 31, 2000. Where the alert service
bulletin specifies that the manufacturer may
be contacted for disposition of certain
corrective actions (rework or replacement of
fittings), this AD requires such rework and/
or replacement to be done in accordance with
a method approved by the Manager, Seattle
Aircraft Certification Office (ACO); or in
accordance with data meeting the type
certification basis of the airplane approved
by a Boeing Company Designated
Engineering Representative (DER) who has
been authorized by the Manager, Seattle
ACO, to make such findings. For a repair
method to be approved by the Manager,
Seattle ACO, as required by this paragraph,
the Manager’s approval letter must
specifically reference this AD. As of the
effective date of this AD, the rework and/or
replacement must be done using a method
approved in accordance with the procedures
specified in paragraph (k) of this AD.
Note 1: Installation of two
BACW10BP*APU washers on Group A
fasteners accomplished during modification
in accordance with Boeing Service Bulletin
747–54A2159, dated November 3, 1994,
Revision 1, dated June 1, 1995, or Revision
2, dated March 14, 1996; and pin or bolt
protrusion as specified in the 747 Structural
Repair Manual, Chapter 51–30–02 (both
referenced in Boeing Alert Service Bulletin
747–54A2203, dated August 31, 2000); is
considered acceptable for compliance with
the action required by paragraph (f) of this
AD.
New Actions Required by This AD
Inspections and Related Investigative and
Corrective Actions
(g) Except as provided by paragraphs (i)
and (j) of this AD: At the applicable
compliance times and repeat intervals listed
in Tables 1 and 2 of paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 747–54A2203, Revision 1, dated
August 9, 2007, do the inspections and
applicable related investigative and
corrective actions by accomplishing all the
actions specified in Parts 2 and 8 of the
Accomplishment Instructions of the service
bulletin.
Optional Initial and Repetitive Inspections
and Related Investigative and Corrective
Actions
(h) Do the initial and repetitive inspections
and related investigative and corrective
actions by accomplishing all the actions
specified in Part 7 of the Accomplishment
Instructions of Boeing Alert Service Bulletin
747–54A2203, Revision 1, dated August 9,
2007, except as provided by paragraph (j) of
this AD.
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53942
Federal Register / Vol. 72, No. 183 / Friday, September 21, 2007 / Rules and Regulations
Exceptions to Service Bulletin
(i) Where Boeing Alert Service Bulletin
747–54A2203, Revision 1, dated August 9,
2007, specifies a compliance time after the
date of the service bulletin, this AD requires
compliance within the specified compliance
time after the effective date of this AD.
(j) Where Boeing Alert Service Bulletin
747–54A2203, Revision 1, dated August 9,
2007, specifies to contact Boeing for
appropriate action, this AD requires, before
further flight, repair of the discrepancy or
replacement of the discrepant part using a
method approved in accordance with the
procedures specified in paragraph (k) of this
AD.
Alternative Methods of Compliance
(AMOCs)
ebenthall on PROD1PC69 with RULES
Material Incorporated by Reference
(l) You must use Boeing Alert Service
Bulletin 747–54A2203, dated August 31,
2000; and Boeing Alert Service Bulletin 747–
54A2203, Revision 1, dated August 9, 2007;
to perform the actions that are required by
this AD, unless the AD specifies otherwise.
(1) The Director of the Federal Register
approved the incorporation by reference of
Boeing Alert Service Bulletin 747–54A2203,
Revision 1, dated August 9, 2007, in
accordance with 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) On December 6, 2000 (65 FR 69862,
November 21, 2000), the Director of the
Federal Register approved the incorporation
by reference of Boeing Alert Service Bulletin
747–54A2203, dated August 31, 2000.
(3) Contact Boeing Commercial Airplanes,
P.O. Box 3707, Seattle, Washington 98124–
2207, for a copy of this service information.
You may review copies at the FAA,
Transport Airplane Directorate, 1601 Lind
Avenue, SW., Renton, Washington; or at 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/cfr/ibrlocations.html.
15:32 Sep 20, 2007
Jkt 211001
BILLING CODE 4910–13–P
DEPARTMENT OF COMMERCE
National Oceanic and Atmospheric
Administration
15 CFR Part 902
50 CFR Part 648
(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) To request a different method of
compliance or a different compliance time
for this AD, follow the procedures in 14 CFR
39.19. Before using any approved AMOC on
any airplane to which the AMOC applies,
notify your appropriate principal inspector
(PI) in the FAA Flight Standards District
Office (FSDO), or lacking a PI, your local
FSDO.
(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.
VerDate Aug<31>2005
Issued in Renton, Washington, on
September 14, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–18541 Filed 9–20–07; 8:45 am]
[Docket No. 0612243159–7456–03; I.D.
020507A]
RIN 0648–AU34
Magnuson-Stevens Fishery
Conservation and Management Act
Provisions; Fisheries of the
Northeastern United States; Monkfish
Fishery; Framework Adjustment 4
National Marine Fisheries
Service (NMFS), National Oceanic and
Atmospheric Administration (NOAA),
Commerce.
ACTION: Interim final rule; request for
comments.
AGENCY:
SUMMARY: NMFS implements new
management measures for the monkfish
fishery approved in Framework
Adjustment 4 to the Monkfish Fishery
Management Plan (FMP). This
framework eliminates the control rule
for determining management measures
established by Framework Adjustment 2
to the FMP, and establishes target total
allowable catch (TAC) levels, trip limits,
and days-at-sea (DAS) allocations for the
final 3 years of the monkfish rebuilding
plan. The intent of this action is to
replace the Framework 2 control rule
with measures consistent with the stock
rebuilding goals established in the
original FMP, and in accordance with
Magnuson-Stevens Fishery
Conservation and Management Act
(Magnuson-Stevens Act) requirements.
NMFS is publishing this action as an
interim final rule in order to provide the
opportunity for additional public
comment because the approval of
Framework 4 was based, in part, on the
consideration of the integrated monkfish
stock assessment, which was not
available during the original public
comment period. This action also
contains three changes to address
incorrect cross-references or duplicate
regulatory text.
DATES: The interim rule published on
April 27, 2007 (72 FR 20952), which is
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Frm 00030
Fmt 4700
Sfmt 4700
scheduled to expire on October 28,
2007, is superseded by this interim final
rule and expires at 12:01 a.m. on
October 22, 2007. The amendments in
this interim final rule become effective
at 12:02 a.m. on October 22, 2007.
Comments on the measures contained in
this interim final rule must be received
by 5 p.m. on October 22, 2007.
Copies of the
Environmental Assessment (EA),
including the Regulatory Impact Review
(RIR) and Initial Regulatory Flexibility
Analysis (IRFA), prepared for this action
are available upon request from Paul
Howard, Executive Director, New
England Fishery Management Council,
50 Water Street, Newburyport, MA,
01950. The document is also available
online at www.nefmc.org. NMFS
prepared a Final Regulatory Flexibility
Analysis (FRFA), which is contained in
the classification section of this interim
final rule. The small entity compliance
guide is available from Patricia A.
Kurkul, Regional Administrator,
Northeast Regional Office, National
Marine Fisheries Service, One
Blackburn Drive, Gloucester, MA 01930
2298, and on the Northeast Regional
Office’s website at www.nero.noaa.gov/
nero/nr/.
Written comments on this interim
final rule may be submitted by any of
the following methods:
• E-mail: E-mail comments may be
submitted to
monkfish.FW4interim@noaa.gov.
Include in the subject line the following
‘‘Comments on the Interim Final Rule
for Framework Adjustment 4.’’
• Mail: Comments submitted by mail
should be sent to Patricia A. Kurkul,
Administrator, Northeast Region, NMFS
(Regional Administrator), One
Blackburn Drive, Gloucester, MA
01930–2298. Mark the outside of the
envelope ‘‘Comments on the Interim
Final Rule for Framework Adjustment 4
to the Monkfish FMP.’’
• Facsimile (fax): Comments
submitted by fax should be faxed to
(978) 281–9135.
Written comments regarding the
burden-hour estimates or other aspects
of the collection-of-information
requirements contained in this interim
final rule may be submitted to the
Regional Administrator at the address
listed above and by e-mail to
DavidlRostker@omb.eop.gov, or fax to
(202) 395–7285.
FOR FURTHER INFORMATION CONTACT:
Allison McHale, Fishery Policy Analyst,
e-mail Allison.McHale@noaa.gov, phone
(978) 281–9103, fax (978) 281–9135.
SUPPLEMENTARY INFORMATION:
ADDRESSES:
E:\FR\FM\21SER1.SGM
21SER1
]]>Agencies
[Federal Register Volume 72, Number 183 (Friday, September 21, 2007)]
[Rules and Regulations]
[Pages 53939-53942]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-18541]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-29263; Directorate Identifier 2007-NM-198-AD;
Amendment 39-15210; AD 2007-19-19]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 747-100, 747-100B, 747-
100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747SR, and 747SP
Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: The FAA is superseding an existing airworthiness directive
(AD) that applies to certain Boeing Model 747 series airplanes. The
existing AD currently requires repetitive inspections and torque checks
of the hanger fittings and strut forward bulkhead of the forward engine
mount and adjacent support structure, and corrective actions if
necessary. The existing AD also currently requires a terminating action
for the repetitive inspections and checks. This new AD requires, among
other actions, new repetitive inspections in the existing area and new
areas. This new AD also provides for an optional inspection and no
longer allows the existing fastener replacement to terminate repetitive
inspections. This AD results from new reports of under-torqued or loose
fasteners, a cracked bulkhead chord, and a fractured back-up angle
after operators accomplished the terminating action required by the
existing AD. We are issuing this AD to detect and correct loose
fasteners and/or damaged or cracked hanger fittings, back-up angles,
and bulkhead of the forward engine mount, which could lead to failure
of the hanger fitting and bulkhead and consequent separation of the
engine from the airplane.
DATES: This AD becomes effective October 9, 2007.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of October 9,
2007.
On December 6, 2000 (65 FR 69862, November 21, 2000), the Director
of the Federal Register approved the incorporation by reference of
Boeing Alert Service Bulletin 747-54A2203, dated August 31, 2000.
We must receive any comments on this AD by November 20, 2007.
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: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
Fax: (202) 493-2251.
Hand Delivery: Room W12-140 on the ground floor of the
West Building, 1200 New Jersey Avenue, SE., 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: Tamara Anderson, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
917-6421; fax (425) 917-6590.
SUPPLEMENTARY INFORMATION:
Discussion
On July 13, 2001, we issued AD 2001-15-02, amendment 39-12336 (66
FR 37884, July 20, 2001). That AD applies to certain Boeing Model 747
series airplanes. That AD requires repetitive inspections and torque
checks of the hanger fittings and strut forward bulkhead of the forward
engine mount and adjacent support structure, and corrective actions if
necessary. That AD also requires a terminating action for the
repetitive inspections and checks. That AD resulted from reports
indicating the detection of loose fasteners of the hanger fittings and
strut forward bulkhead of the forward engine mount. The actions
specified in that AD are intended to prevent loose fasteners and
associated damage to the hanger fittings
[[Page 53940]]
and bulkhead of the forward engine mount, which could result in
separation of the engine from the airplane.
Actions Since AD Was Issued
Since we issued that AD, we have received new reports of under-
torqued or loose fasteners after operators accomplished the terminating
action required by AD 2001-15-02 (i.e., Part 6 specified in Boeing
Alert Service Bulletin 747-54A2203, dated August 31, 2000). In
addition, we have received a report of a crack approximately 1.5-inch
in length in the bulkhead chord adjacent to an upper fastener on a
number 2 strut with approximately 20,050 total flight cycles and
110,000 total flight hours. Further investigation revealed that the
back-up angle inside the strut adjacent to the crack had fractured at
its bend radius. The fracture initiated as a result of fatigue at
multiple locations on the inner diameter of the bend radius. The cause
of the loose fasteners of the hanger fittings of the bulkhead of the
forward engine mount is their location in an area of high vibration and
the design of the bulkhead. Loose fasteners and/or damaged or cracked
hanger fittings, back-up angles, and bulkhead of the forward engine
mount, if not corrected, could lead to failure of the hanger fitting
and bulkhead and consequent separation of the engine from the airplane.
Relevant Service Information
We have reviewed Boeing Alert Service Bulletin 747-54A2203,
Revision 1, dated August 9, 2007. The service information describes the
following new procedures:
Repetitive detailed inspections of the torque stripes and
bulkhead of the forward engine mount and the adjacent support structure
on the inboard and outboard struts and repetitive torque inspections
(checks) of the bulkhead for cracks and/or fretting damage of the
hanger fittings and bulkhead and for loose or under-torqued fasteners,
as applicable; and applicable related investigative and corrective
actions (i.e., Part 2 of the Accomplishment Instructions).
Repetitive high frequency eddy current (HFEC), detailed,
or fluorescent penetrant inspections of the bulkhead of the forward
engine mount on the inboard and outboard struts for cracks of the
bulkhead chords, evidence of a fractured internal angle, or cracks/
fracture of the internal angles; as applicable (i.e., Part 8 of the
Accomplishment Instructions); and detailed and HFEC inspections to
detect cracks or fracture of the internal angle and stiffener (i.e.,
Part 7 of the Accomplishment Instructions), and applicable related
investigative and corrective actions.
The related investigative actions involve doing applicable
inspections described previously. The corrective actions include
applying optional torque stripes; reworking, repairing, and/or
replacing any discrepant part with a new part; replacing all fasteners
with new fasteners; and contacting Boeing for certain conditions; as
applicable.
For the inspections specified in Parts 2 and 8 of the
Accomplishment Instructions, the service information specifies an
initial compliance time of 90 days and repeat intervals of 6 and 18
months, depending on the inspection type. For the inspections specified
in Part 7 of the Accomplishment Instructions, the service information
specifies an initial compliance time of 18 months and repeat intervals
of 36 months. The service bulletin specifies a compliance time of
before further flight or 18 months for doing the related investigative
and corrective actions, as applicable.
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. For this reason, we
are issuing this AD to supersede AD 2001-15-02. This new AD retains the
required fastener replacement, except that action no longer terminates
any repetitive inspections and torque inspections (checks). This AD
also requires accomplishing the actions specified in Parts 2 and 8 of
the Accomplishment Instructions of the service information described
previously, except as discussed under ``Differences Between the AD and
Service Information.'' This AD also provides, as an option, the
inspections specified in Part 7 of the Accomplishment Instructions of
the service information described previously.
Interim Action
This is considered to be interim action. We are currently
considering requiring the inspections and applicable related
investigative and corrective actions specified in Part 7 of the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
54A2203, Revision 1. However, the planned compliance time for the
inspections is sufficiently long so that notice and opportunity for
prior public comment will be practicable.
Differences Between the AD and Service Information
The service information specifies to contact the manufacturer for
instructions on how to repair certain conditions, but this AD requires
repairing those conditions in one of the following ways:
Using a method that we approve; or
Using data that meet the certification basis of the
airplane, and that have been approved by an Authorized Representative
for the Boeing Commercial Airplanes Delegation Option Authorization
Organization whom we have authorized to make those findings.
Change to Existing AD
This AD will retain certain requirements of AD 2001-15-02. Since AD
2001-15-02 was issued, we have revised the AD format and rearranged
certain paragraphs. As a result, we reidentified paragraph (c) of AD
2001-15-02 as paragraph (f) in this AD.
Boeing Commercial Airplanes has received a Delegation Option
Authorization (DOA). We have revised paragraph (f) of this AD to
delegate the authority to approve an alternative method of compliance
for any repair required by this AD to an Authorized Representative for
the Boeing Commercial Airplanes DOA rather than a Designated
Engineering Representative (DER).
FAA's Determination of the Effective Date
An unsafe condition exists that requires the immediate adoption of
this AD; therefore, providing notice and opportunity for public comment
before the AD is issued is impracticable, and good cause exists to make
this AD effective in less than 30 days.
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 in the ADDRESSES section. Include ``Docket No. FAA-2007-
29263; Directorate Identifier 2007-NM-198-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
[[Page 53941]]
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 Operations office between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays. The
Docket Operations office (telephone (800) 647-5527) is located on the
ground level of the West 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 part 39 of the Federal Aviation Regulations (14 CFR part
39) as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The Federal Aviation Administration (FAA) amends Sec. 39.13 by
removing amendment 39-12336 (66 FR 37884, July 20, 2001) and adding the
following new airworthiness directive (AD):
2007-19-19 Boeing: Docket No. FAA-2007-29263; Directorate Identifier
2007-NM-198-AD; Amendment 39-15210.
Effective Date
(a) This AD becomes effective October 9, 2007.
Affected ADs
(b) This AD supersedes AD 2001-15-02.
Applicability
(c) This AD applies to Boeing Model 747-100, 747-100B, 747-100B
SUD, 747-200B, 747-200C, 747-200F, 747-300, 747SR, and 747SP series
airplanes, certificated in any category; as identified in Boeing
Alert Service Bulletin 747-54A2203, Revision 1, dated August 9,
2007.
Unsafe Condition
(d) This AD results from new reports of under-torqued or loose
fasteners, a cracked bulkhead chord, and a fractured back-up angle
after operators accomplished the terminating action required by the
existing AD. We are issuing this AD to detect and correct loose
fasteners and/or damaged or cracked hanger fittings, back-up angles,
and bulkhead of the forward engine mount, which could lead to
failure of the hanger fitting and bulkhead and consequent 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.
Certain Requirement of AD 2001-15-02
(f) Within 60 months after August 24, 2001 (the effective date
of AD 2001-15-02): Accomplish all actions specified in Part 6 of the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
54A2203, dated August 31, 2000. Where the alert service bulletin
specifies that the manufacturer may be contacted for disposition of
certain corrective actions (rework or replacement of fittings), this
AD requires such rework and/or replacement to be done in accordance
with a method approved by the Manager, Seattle Aircraft
Certification Office (ACO); or in accordance with data meeting the
type certification basis of the airplane approved by a Boeing
Company Designated Engineering Representative (DER) who has been
authorized by the Manager, Seattle ACO, to make such findings. For a
repair method to be approved by the Manager, Seattle ACO, as
required by this paragraph, the Manager's approval letter must
specifically reference this AD. As of the effective date of this AD,
the rework and/or replacement must be done using a method approved
in accordance with the procedures specified in paragraph (k) of this
AD.
Note 1: Installation of two BACW10BP*APU washers on Group A
fasteners accomplished during modification in accordance with Boeing
Service Bulletin 747-54A2159, dated November 3, 1994, Revision 1,
dated June 1, 1995, or Revision 2, dated March 14, 1996; and pin or
bolt protrusion as specified in the 747 Structural Repair Manual,
Chapter 51-30-02 (both referenced in Boeing Alert Service Bulletin
747-54A2203, dated August 31, 2000); is considered acceptable for
compliance with the action required by paragraph (f) of this AD.
New Actions Required by This AD
Inspections and Related Investigative and Corrective Actions
(g) Except as provided by paragraphs (i) and (j) of this AD: At
the applicable compliance times and repeat intervals listed in
Tables 1 and 2 of paragraph 1.E., ``Compliance,'' of Boeing Alert
Service Bulletin 747-54A2203, Revision 1, dated August 9, 2007, do
the inspections and applicable related investigative and corrective
actions by accomplishing all the actions specified in Parts 2 and 8
of the Accomplishment Instructions of the service bulletin.
Optional Initial and Repetitive Inspections and Related Investigative
and Corrective Actions
(h) Do the initial and repetitive inspections and related
investigative and corrective actions by accomplishing all the
actions specified in Part 7 of the Accomplishment Instructions of
Boeing Alert Service Bulletin 747-54A2203, Revision 1, dated August
9, 2007, except as provided by paragraph (j) of this AD.
[[Page 53942]]
Exceptions to Service Bulletin
(i) Where Boeing Alert Service Bulletin 747-54A2203, Revision 1,
dated August 9, 2007, specifies a compliance time after the date of
the service bulletin, this AD requires compliance within the
specified compliance time after the effective date of this AD.
(j) Where Boeing Alert Service Bulletin 747-54A2203, Revision 1,
dated August 9, 2007, specifies to contact Boeing for appropriate
action, this AD requires, before further flight, repair of the
discrepancy or replacement of the discrepant part using a method
approved in accordance with the procedures specified in paragraph
(k) of this AD.
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) To request a different method of compliance or a different
compliance time for this AD, follow the procedures in 14 CFR 39.19.
Before using any approved AMOC on any airplane to which the AMOC
applies, notify your appropriate principal inspector (PI) in the FAA
Flight Standards District Office (FSDO), or lacking a PI, your local
FSDO.
(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
(l) You must use Boeing Alert Service Bulletin 747-54A2203,
dated August 31, 2000; and Boeing Alert Service Bulletin 747-
54A2203, Revision 1, dated August 9, 2007; to perform the actions
that are required by this AD, unless the AD specifies otherwise.
(1) The Director of the Federal Register approved the
incorporation by reference of Boeing Alert Service Bulletin 747-
54A2203, Revision 1, dated August 9, 2007, in accordance with 5
U.S.C. 552(a) and 1 CFR part 51.
(2) On December 6, 2000 (65 FR 69862, November 21, 2000), the
Director of the Federal Register approved the incorporation by
reference of Boeing Alert Service Bulletin 747-54A2203, dated August
31, 2000.
(3) Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle,
Washington 98124-2207, for a copy of this service information. You
may review copies at the FAA, Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington; or at 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/cfr/ibr-locations.html.
Issued in Renton, Washington, on September 14, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E7-18541 Filed 9-20-07; 8:45 am]
BILLING CODE 4910-13-P
