Airworthiness Directives; Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747SR, and 747SP Series Airplanes, 20528-20530 [06-3796]
Download as PDF
<![CDATA[
20528
Federal Register / Vol. 71, No. 77 / Friday, April 21, 2006 / Rules and Regulations
Bank Insurance Fund (BIF), the former
Savings Association Insurance Fund
(SAIF) or the Deposit Insurance Fund’’.
I B. Paragraph (s)(3) is amended by
removing ‘‘or the BIF, the SAIF’’ and
adding in its place ‘‘or the former BIF,
the former SAIF, the Deposit Insurance
Fund’’.
§ 367.6
[Amended]
39. Section 367.6(d) is amended by
removing ‘‘Federal deposit insurance
funds’’ and adding in its place ‘‘Deposit
Insurance Fund (or any predecessor
deposit insurance fund)’’.
I
By order of the Board of Directors.
Dated at Washington DC, this 4th day of
April, 2006.
Federal Deposit Insurance Corporation.
Valerie J. Best,
Assistant Executive Secretary.
[FR Doc. 06–3721 Filed 4–20–06; 8:45 am]
BILLING CODE 6714–01–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–23441; Directorate
Identifier 2005–NM–199–AD; Amendment
39–14571; AD 2006–09–01]
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
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
wwhite on PROD1PC61 with RULES
AGENCY:
SUMMARY: The FAA is superseding an
existing airworthiness directive (AD),
which applies to certain Boeing Model
747–100, 747–100B, 747–100B SUD,
747–200B, 747–200C, 747–200F, 747–
300, 747SR, and 747SP series airplanes.
That AD currently requires repetitive
detailed and ultrasonic inspections of
the thrust links of the rear engine
mounts for any crack or fracture and
corrective actions if necessary. This new
AD requires repetitive replacement of
the thrust links with new or overhauled
thrust links, which ends the repetitive
detailed and ultrasonic inspections.
This AD results from the finding of
fractured and cracked forward lugs of
the rear engine mount thrust link on the
VerDate Aug<31>2005
16:06 Apr 20, 2006
Jkt 208001
number one strut on two airplanes. We
are issuing this AD to prevent cracked
or fractured thrust links that could lead
to the loss of the load path for the rear
engine mount bulkhead and damage to
other primary engine mount structure,
which could result in the in-flight
separation of the engine from the
airplane and consequent loss of control
of the airplane.
DATES: This AD becomes effective May
26, 2006.
On September 30, 2005 (70 FR 54474,
September 15, 2005), the Director of the
Federal Register approved the
incorporation by reference of Boeing
Alert Service Bulletin 747–71A2309,
dated August 18, 2005.
ADDRESSES: You may examine the AD
docket on the Internet at https://
dms.dot.gov or in person at the Docket
Management Facility, U.S. Department
of Transportation, 400 Seventh Street,
SW., Nassif Building, room PL–401,
Washington, DC.
Contact Boeing Commercial
Airplanes, P.O. Box 3707, Seattle,
Washington 98124–2207, for service
information identified in this AD.
FOR FURTHER INFORMATION CONTACT: 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:
Examining the Docket
You may examine the airworthiness
directive (AD) docket on the Internet at
https://dms.dot.gov or in person at the
Docket Management Facility office
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The Docket Management Facility office
(telephone (800) 647–5227) is located on
the plaza level of the Nassif Building at
the street address stated in the
ADDRESSES section.
Discussion
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that
supersedes AD 2005–19–06, amendment
39–14271 (70 FR 54474, September 15,
2005). The existing AD applies to
certain Boeing Model 747–100, 747–
100B, 747–100B SUD, 747–200B, 747–
200C, 747–200F, 747–300, 747SR, and
747SP series airplanes. That NPRM was
published in the Federal Register on
January 11, 2006 (71 FR 1718). That
NPRM proposed to continue to require
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Fmt 4700
Sfmt 4700
repetitive detailed and ultrasonic
inspections of the thrust links of the rear
engine mounts for any crack or fracture
and corrective actions if necessary. That
NPRM also proposed to require
repetitive replacement of the thrust
links with new or overhauled thrust
links, which ends the repetitive detailed
and ultrasonic inspections.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comments that have
been received on the NPRM.
Support for the NPRM
Boeing and Northwest Airlines
(NWA) support the NPRM.
Request for Clarification
NWA states that, as a result of the
inspections required by AD 2005–19–
06, some thrust links may have already
been replaced with new or overhauled
thrust links (prior to the initial
compliance time specified in Table 1 of
the NPRM). According to NWA’s
interpretation of paragraph (e) of the
NPRM, replacements done previously in
accordance with AD 2005–19–06
comply with the initial replacement
specified in the NPRM. We infer that the
commenter would like us to clarify
whether this interpretation is correct.
We agree that, under paragraph (e) of
this AD, the actions required by this AD
must be accomplished within the
specified compliance times, unless the
actions have been previously
accomplished. Therefore, replacement
of a cracked or fractured thrust link in
accordance with paragraph (h) of AD
2005–19–06 constitutes compliance
with the initial replacement required by
paragraph (k) of this AD, for that thrust
link only. No change to this AD is
necessary.
Conclusion
We have carefully reviewed the
available data, including the comments
that have been submitted, and
determined that air safety and the
public interest require adopting the AD
as proposed.
Costs of Compliance
There are about 274 airplanes of the
affected design in the worldwide fleet.
The following table provides the
estimated costs, at an average labor rate
of $65 per hour, for U.S. operators to
comply with this AD.
E:\FR\FM\21APR1.SGM
21APR1
Federal Register / Vol. 71, No. 77 / Friday, April 21, 2006 / Rules and Regulations
20529
ESTIMATED COSTS
Number of
U.S.registered
airplanes
Action
Work hours
Parts
Cost per airplane
Inspection (required by AD
2005–19–06).
Replacement (new action) .....
8 (2 per engine) .....
None ........
$520, per inspection cycle ....
100
4 (1 per engine) .....
$41,424 ...
$41,684, per replacement
cycle.
100
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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 this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
(2) Is not a ‘‘significant rule’’ under
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
(3) Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared a regulatory evaluation
of the estimated costs to comply with
this AD and placed it in the AD docket.
See the ADDRESSES section for a location
to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
VerDate Aug<31>2005
16:06 Apr 20, 2006
Jkt 208001
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
Authority: 49 U.S.C. 106(g), 40113, 44701.
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by removing amendment 39–14271 (70
FR 54474, September 15, 2005) and by
adding the following new airworthiness
directive (AD):
I
2006–09–01 Boeing: Amendment 39–14571.
Docket No. FAA–2005–23441;
Directorate Identifier 2005–NM–199–AD.
Effective Date
(a) This AD becomes effective May 26,
2006.
Affected ADs
(b) This AD supersedes AD 2005–19–06.
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; equipped with Pratt & Whitney
JT9D–3 and –7 series engines, except JT9D–
70 engines; as identified in Boeing Alert
Service Bulletin 747–71A2309, dated August
18, 2005.
Unsafe Condition
(d) This AD results from the finding of
fractured and cracked forward lugs of the rear
engine mount thrust link on the number one
strut on two airplanes. We are issuing this
AD to prevent cracked or fractured thrust
links that could lead to the loss of the load
path for the rear engine mount bulkhead and
damage to other primary engine mount
structure, which could result in the in-flight
separation of the engine from the airplane
and consequent loss of control of the
airplane.
Compliance
(e) You are responsible for having the
actions required by this AD performed within
the compliance times specified, unless the
actions have already been done.
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Frm 00007
Fmt 4700
Sfmt 4700
$52,000, per inspection
cycle.
$4,168,400, per replacement
cycle.
Restatement of Requirements of AD 2005–
19–06
Service Bulletin References
(f) The term ‘‘service bulletin,’’ as used in
this AD, means the Accomplishment
Instructions of Boeing Alert Service Bulletin
747–71A2309, dated August 18, 2005.
Repetitive Inspections of Thrust Links
1. The authority citation for part 39
continues to read as follows:
I
§ 39.13
Fleet cost
(g) Within 90 days after September 30,
2005 (the effective date of AD 2005–19–06),
do a detailed inspection and ultrasonic
inspection of thrust link lugs having part
number (P/N) 65B90360–1 or –4 of the rear
engine mount of struts 1, 2, 3, and 4 for any
crack or fracture, in accordance with Part 1
of the service bulletin. If the thrust link is not
found cracked or fractured: Repeat the
inspections thereafter at intervals not to
exceed 1,200 flight cycles or 18 months,
whichever is first, until the repetitive
replacement or overhaul of the thrust link
required by paragraph (k) of this AD is
accomplished. Accomplishing the repetitive
replacement or overhaul of a thrust link as
specified in paragraph (h) or (k) of this AD
terminates the repetitive inspections for that
thrust link only.
Corrective Actions
(h) If a cracked thrust link is found during
any inspection required by paragraph (g) of
this AD or during any replacement or
overhaul done in accordance with the service
bulletin: Before further flight, do the actions
specified in paragraph (h)(1) of this AD. If a
fractured thrust link is found during any
inspection required by paragraph (g) of this
AD or during any replacement or overhaul
done in accordance with the service bulletin:
Before further flight, do the actions specified
in paragraphs (h)(1) and (h)(2) of this AD.
(1) Replace the thrust link with a new or
overhauled thrust link in accordance with
Part 2 of the service bulletin; except as
provided by paragraph (i) of this AD. Repeat
the replacement at the applicable compliance
time specified in paragraph (h)(1)(i) or
(h)(1)(ii) of this AD.
(i) For replacement with a thrust link
assembly having P/N 65B90360–1 or –4:
Thereafter at intervals not to exceed 6,000
flight cycles.
(ii) For replacement with a thrust link
assembly having P/N 65B90360–7: Thereafter
at intervals not to exceed 12,000 flight cycles.
(2) Do the corrective actions in accordance
with Parts 3, 4, and 5 of the service bulletin;
except as provided by paragraph (i) of this
AD.
E:\FR\FM\21APR1.SGM
21APR1
20530
Federal Register / Vol. 71, No. 77 / Friday, April 21, 2006 / Rules and Regulations
Exception to Service Bulletin
(i) Where the service bulletin specifies to
contact Boeing for appropriate action, do the
corrective action using a method approved in
accordance with paragraph (l) of this AD.
Credit for Certain Corrective Actions
(j) Reworking the lugs on the bulkhead
fitting of the rear engine mount as specified
in paragraphs (b)(2), (e), and (f) of AD 2001–
15–15, amendment 39–12349, is acceptable
for compliance with accomplishing the
corrective action specified in ‘‘Part 3—Rear
Engine Mount Bulkhead Inspection and Lug
Overhaul and Upper Fitting Overhaul and
Bolt Replacement’’ of the service bulletin.
New Requirements of This AD
Terminating Action—Repetitive Replacement
or Overhaul of All Thrust Links
(k) At the applicable compliance times
specified in Table 1 of this AD: Repetitively
replace the thrust link of the rear engine
mount of struts 1, 2, 3, and 4 with a new or
overhauled thrust link, in accordance with
Part 2 of the service bulletin; except as
provided by paragraph (i) of this AD. During
any replacement required by this paragraph,
an existing thrust link may be replaced with
a new or overhauled thrust link having P/N
65B90360–1, –4 or –7, provided that the
applicable repetitive interval specified in
Table 1 of this AD is complied with. If a
fractured thrust link is found during any
replacement or overhaul done in accordance
with this paragraph: Before further flight, do
the corrective actions specified in paragraph
(h)(2) of this AD. Repetitive replacement of
all thrust links having P/N 65B90360–1 or –4
terminates the repetitive inspections required
by paragraph (g) of this AD. Accomplishing
the repetitive replacement or overhaul of a
thrust link required by paragraph (h) of this
AD constitutes compliance with the
requirements of this paragraph for that thrust
link only.
TABLE 1.—COMPLIANCE TIMES
For thrust link P/N—
Initial replacement—
Repetitive interval—
65B90360–1 or –4 .............................................
Within 36 months after the effective date of
this AD.
Within 12,000 flight cycles after the new thrust
link has been installed.
Thereafter at intervals not to exceed 6,000
flight cycles.
Thereafter at intervals not to exceed 12,000
flight cycles.
otherwise. On September 30, 2005 (70 FR
54474, September 15, 2005), the Director of
the Federal Register approved the
incorporation by reference of Boeing Alert
Service Bulletin 747–71A2309, dated August
18, 2005. Contact Boeing Commercial
Airplanes, P.O. Box 3707, Seattle,
Washington 98124–2207, for a copy of this
service information. You may review copies
at the Docket Management Facility, U.S.
Department of Transportation, 400 Seventh
Street, SW., room PL–401, Nassif Building,
Washington, DC; on the Internet at https://
dms.dot.gov; or at the National Archives and
Records Administration (NARA). For
information on the availability of this
material at the NARA, call (202) 741–6030,
or go to https://www.archives.gov/
federal_register/code_of_federal_regulations/
ibr_locations.html.
DEPARTMENT OF TRANSPORTATION
65B90360–7 ......................................................
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Alternative Methods of Compliance
(AMOCs)
(l)(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
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.
(4) The actions identified in paragraphs (g)
and (k) of this AD are approved as an AMOC
to paragraphs (c) and (d) of AD 2004–07–22,
amendment 39–13566, for the inspections of
structural significant item S–2, for the thrust
links only, of Boeing Supplemental
Structural Inspection Document D6–35022,
Revision G, dated December 2000. All
provisions of AD 2004–07–22 that are not
specifically referenced in this paragraph,
including the initial inspection threshold
required by paragraph (d) of AD 2004–07–22,
remain fully applicable and must be
complied with.
(5) AMOCs approved previously in
accordance with AD 2005–19–06,
amendment 39–14271, are approved as
AMOCs for the corresponding provisions of
this AD.
Issued in Renton, Washington, on April 13,
2006.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 06–3796 Filed 4–20–06; 8:45 am]
BILLING CODE 4910–13–P
Material Incorporated by Reference
(m) You must use Boeing Alert Service
Bulletin 747–71A2309, dated August 18,
2005, to perform the actions that are required
by this AD, unless the AD specifies
VerDate Aug<31>2005
16:06 Apr 20, 2006
Jkt 208001
PO 00000
Frm 00008
Fmt 4700
Sfmt 4700
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–24364; Directorate
Identifier 2004–NM–272–AD; Amendment
39–14534; AD 2006–07–07]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A300 B4–600, B4–600R, and F4–600R
Series Airplanes, and Model C4–605R
Variant F Airplanes (Collectively Called
A300–600 Series Airplanes)
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; correction.
AGENCY:
SUMMARY: The FAA is correcting a
typographical error in an existing
airworthiness directive (AD) that was
published in the Federal Register on
March 31, 2006 (71 FR 16206). The error
resulted in an incorrect Docket No. This
AD applies to certain Airbus Model
A300–600 series airplanes. This AD
requires modifying nine bolt holes in
the vertical flange to prevent cracking
before the inspection threshold of AD
98–18–02.
DATES: Effective April 17, 2006.
ADDRESSES: The AD docket contains the
proposed AD, comments, and any final
disposition. 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
E:\FR\FM\21APR1.SGM
21APR1
]]>Agencies
[Federal Register Volume 71, Number 77 (Friday, April 21, 2006)]
[Rules and Regulations]
[Pages 20528-20530]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 06-3796]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-23441; Directorate Identifier 2005-NM-199-AD;
Amendment 39-14571; AD 2006-09-01]
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.
-----------------------------------------------------------------------
SUMMARY: The FAA is superseding an existing airworthiness directive
(AD), which applies to certain Boeing Model 747-100, 747-100B, 747-100B
SUD, 747-200B, 747-200C, 747-200F, 747-300, 747SR, and 747SP series
airplanes. That AD currently requires repetitive detailed and
ultrasonic inspections of the thrust links of the rear engine mounts
for any crack or fracture and corrective actions if necessary. This new
AD requires repetitive replacement of the thrust links with new or
overhauled thrust links, which ends the repetitive detailed and
ultrasonic inspections. This AD results from the finding of fractured
and cracked forward lugs of the rear engine mount thrust link on the
number one strut on two airplanes. We are issuing this AD to prevent
cracked or fractured thrust links that could lead to the loss of the
load path for the rear engine mount bulkhead and damage to other
primary engine mount structure, which could result in the in-flight
separation of the engine from the airplane and consequent loss of
control of the airplane.
DATES: This AD becomes effective May 26, 2006.
On September 30, 2005 (70 FR 54474, September 15, 2005), the
Director of the Federal Register approved the incorporation by
reference of Boeing Alert Service Bulletin 747-71A2309, dated August
18, 2005.
ADDRESSES: You may examine the AD docket on the Internet at https://
dms.dot.gov or in person at the Docket Management Facility, U.S.
Department of Transportation, 400 Seventh Street, SW., Nassif Building,
room PL-401, Washington, DC.
Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle,
Washington 98124-2207, for service information identified in this AD.
FOR FURTHER INFORMATION CONTACT: 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:
Examining the Docket
You may examine the airworthiness directive (AD) docket on the
Internet at https://dms.dot.gov or in person at the Docket Management
Facility office between 9 a.m. and 5 p.m., Monday through Friday,
except Federal holidays. The Docket Management Facility office
(telephone (800) 647-5227) is located on the plaza level of the Nassif
Building at the street address stated in the ADDRESSES section.
Discussion
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to include an AD that supersedes AD 2005-19-06, amendment
39-14271 (70 FR 54474, September 15, 2005). The existing AD applies to
certain Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-
200C, 747-200F, 747-300, 747SR, and 747SP series airplanes. That NPRM
was published in the Federal Register on January 11, 2006 (71 FR 1718).
That NPRM proposed to continue to require repetitive detailed and
ultrasonic inspections of the thrust links of the rear engine mounts
for any crack or fracture and corrective actions if necessary. That
NPRM also proposed to require repetitive replacement of the thrust
links with new or overhauled thrust links, which ends the repetitive
detailed and ultrasonic inspections.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comments that have been
received on the NPRM.
Support for the NPRM
Boeing and Northwest Airlines (NWA) support the NPRM.
Request for Clarification
NWA states that, as a result of the inspections required by AD
2005-19-06, some thrust links may have already been replaced with new
or overhauled thrust links (prior to the initial compliance time
specified in Table 1 of the NPRM). According to NWA's interpretation of
paragraph (e) of the NPRM, replacements done previously in accordance
with AD 2005-19-06 comply with the initial replacement specified in the
NPRM. We infer that the commenter would like us to clarify whether this
interpretation is correct.
We agree that, under paragraph (e) of this AD, the actions required
by this AD must be accomplished within the specified compliance times,
unless the actions have been previously accomplished. Therefore,
replacement of a cracked or fractured thrust link in accordance with
paragraph (h) of AD 2005-19-06 constitutes compliance with the initial
replacement required by paragraph (k) of this AD, for that thrust link
only. No change to this AD is necessary.
Conclusion
We have carefully reviewed the available data, including the
comments that have been submitted, and determined that air safety and
the public interest require adopting the AD as proposed.
Costs of Compliance
There are about 274 airplanes of the affected design in the
worldwide fleet. The following table provides the estimated costs, at
an average labor rate of $65 per hour, for U.S. operators to comply
with this AD.
[[Page 20529]]
Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Number of
U.S.-
Action Work hours Parts Cost per airplane registered Fleet cost
airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Inspection (required by AD 2005-19- 8 (2 per engine)............... None................ $520, per inspection 100 $52,000, per
06). cycle. inspection cycle.
Replacement (new action)............ 4 (1 per engine)............... $41,424............. $41,684, per 100 $4,168,400, per
replacement cycle. replacement cycle.
--------------------------------------------------------------------------------------------------------------------------------------------------------
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
subtitle VII, part A, subpart III, section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We have determined that this AD will not have federalism
implications under Executive Order 13132. This AD will not have a
substantial direct effect on the States, on the relationship between
the National Government and the States, or on the distribution of power
and responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866;
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979); and
(3) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this AD and placed it in the AD docket. See the ADDRESSES
section for a location to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
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2. The Federal Aviation Administration (FAA) amends Sec. 39.13 by
removing amendment 39-14271 (70 FR 54474, September 15, 2005) and by
adding the following new airworthiness directive (AD):
2006-09-01 Boeing: Amendment 39-14571. Docket No. FAA-2005-23441;
Directorate Identifier 2005-NM-199-AD.
Effective Date
(a) This AD becomes effective May 26, 2006.
Affected ADs
(b) This AD supersedes AD 2005-19-06.
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; equipped with Pratt &
Whitney JT9D-3 and -7 series engines, except JT9D-70 engines; as
identified in Boeing Alert Service Bulletin 747-71A2309, dated
August 18, 2005.
Unsafe Condition
(d) This AD results from the finding of fractured and cracked
forward lugs of the rear engine mount thrust link on the number one
strut on two airplanes. We are issuing this AD to prevent cracked or
fractured thrust links that could lead to the loss of the load path
for the rear engine mount bulkhead and damage to other primary
engine mount structure, which could result in the in-flight
separation of the engine from the airplane and consequent loss of
control of the airplane.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Restatement of Requirements of AD 2005-19-06
Service Bulletin References
(f) The term ``service bulletin,'' as used in this AD, means the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
71A2309, dated August 18, 2005.
Repetitive Inspections of Thrust Links
(g) Within 90 days after September 30, 2005 (the effective date
of AD 2005-19-06), do a detailed inspection and ultrasonic
inspection of thrust link lugs having part number (P/N) 65B90360-1
or -4 of the rear engine mount of struts 1, 2, 3, and 4 for any
crack or fracture, in accordance with Part 1 of the service
bulletin. If the thrust link is not found cracked or fractured:
Repeat the inspections thereafter at intervals not to exceed 1,200
flight cycles or 18 months, whichever is first, until the repetitive
replacement or overhaul of the thrust link required by paragraph (k)
of this AD is accomplished. Accomplishing the repetitive replacement
or overhaul of a thrust link as specified in paragraph (h) or (k) of
this AD terminates the repetitive inspections for that thrust link
only.
Corrective Actions
(h) If a cracked thrust link is found during any inspection
required by paragraph (g) of this AD or during any replacement or
overhaul done in accordance with the service bulletin: Before
further flight, do the actions specified in paragraph (h)(1) of this
AD. If a fractured thrust link is found during any inspection
required by paragraph (g) of this AD or during any replacement or
overhaul done in accordance with the service bulletin: Before
further flight, do the actions specified in paragraphs (h)(1) and
(h)(2) of this AD.
(1) Replace the thrust link with a new or overhauled thrust link
in accordance with Part 2 of the service bulletin; except as
provided by paragraph (i) of this AD. Repeat the replacement at the
applicable compliance time specified in paragraph (h)(1)(i) or
(h)(1)(ii) of this AD.
(i) For replacement with a thrust link assembly having P/N
65B90360-1 or -4: Thereafter at intervals not to exceed 6,000 flight
cycles.
(ii) For replacement with a thrust link assembly having P/N
65B90360-7: Thereafter at intervals not to exceed 12,000 flight
cycles.
(2) Do the corrective actions in accordance with Parts 3, 4, and
5 of the service bulletin; except as provided by paragraph (i) of
this AD.
[[Page 20530]]
Exception to Service Bulletin
(i) Where the service bulletin specifies to contact Boeing for
appropriate action, do the corrective action using a method approved
in accordance with paragraph (l) of this AD.
Credit for Certain Corrective Actions
(j) Reworking the lugs on the bulkhead fitting of the rear
engine mount as specified in paragraphs (b)(2), (e), and (f) of AD
2001-15-15, amendment 39-12349, is acceptable for compliance with
accomplishing the corrective action specified in ``Part 3--Rear
Engine Mount Bulkhead Inspection and Lug Overhaul and Upper Fitting
Overhaul and Bolt Replacement'' of the service bulletin.
New Requirements of This AD
Terminating Action--Repetitive Replacement or Overhaul of All
Thrust Links
(k) At the applicable compliance times specified in Table 1 of
this AD: Repetitively replace the thrust link of the rear engine
mount of struts 1, 2, 3, and 4 with a new or overhauled thrust link,
in accordance with Part 2 of the service bulletin; except as
provided by paragraph (i) of this AD. During any replacement
required by this paragraph, an existing thrust link may be replaced
with a new or overhauled thrust link having P/N 65B90360-1, -4 or -
7, provided that the applicable repetitive interval specified in
Table 1 of this AD is complied with. If a fractured thrust link is
found during any replacement or overhaul done in accordance with
this paragraph: Before further flight, do the corrective actions
specified in paragraph (h)(2) of this AD. Repetitive replacement of
all thrust links having P/N 65B90360-1 or -4 terminates the
repetitive inspections required by paragraph (g) of this AD.
Accomplishing the repetitive replacement or overhaul of a thrust
link required by paragraph (h) of this AD constitutes compliance
with the requirements of this paragraph for that thrust link only.
Table 1.--Compliance Times
------------------------------------------------------------------------
Initial Repetitive
For thrust link P/N-- replacement-- interval--
------------------------------------------------------------------------
65B90360-1 or -4................ Within 36 months Thereafter at
after the intervals not to
effective date of exceed 6,000
this AD. flight cycles.
65B90360-7...................... Within 12,000 Thereafter at
flight cycles intervals not to
after the new exceed 12,000
thrust link has flight cycles.
been installed.
------------------------------------------------------------------------
Alternative Methods of Compliance (AMOCs)
(l)(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.
(4) The actions identified in paragraphs (g) and (k) of this AD
are approved as an AMOC to paragraphs (c) and (d) of AD 2004-07-22,
amendment 39-13566, for the inspections of structural significant
item S-2, for the thrust links only, of Boeing Supplemental
Structural Inspection Document D6-35022, Revision G, dated December
2000. All provisions of AD 2004-07-22 that are not specifically
referenced in this paragraph, including the initial inspection
threshold required by paragraph (d) of AD 2004-07-22, remain fully
applicable and must be complied with.
(5) AMOCs approved previously in accordance with AD 2005-19-06,
amendment 39-14271, are approved as AMOCs for the corresponding
provisions of this AD.
Material Incorporated by Reference
(m) You must use Boeing Alert Service Bulletin 747-71A2309,
dated August 18, 2005, to perform the actions that are required by
this AD, unless the AD specifies otherwise. On September 30, 2005
(70 FR 54474, September 15, 2005), the Director of the Federal
Register approved the incorporation by reference of Boeing Alert
Service Bulletin 747-71A2309, dated August 18, 2005. Contact Boeing
Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-2207,
for a copy of this service information. You may review copies at the
Docket Management Facility, U.S. Department of Transportation, 400
Seventh Street, SW., room PL-401, Nassif Building, Washington, DC;
on the Internet at https://dms.dot.gov; or at the National Archives
and Records Administration (NARA). For information on the
availability of this material at the NARA, call (202) 741-6030, or
go to https://www.archives.gov/federal_register/code_of_
federal_regulations/ibr_locations.html.
Issued in Renton, Washington, on April 13, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 06-3796 Filed 4-20-06; 8:45 am]
BILLING CODE 4910-13-P
