Airworthiness Directives; Boeing Model 757-200 and -200PF Series Airplanes Equipped With Pratt & Whitney Engines, 24571-24573 [06-3891]
Download as PDF
Federal Register / Vol. 71, No. 80 / Wednesday, April 26, 2006 / Rules and Regulations
practices are prohibited, and additional
disclosures on advertisements of
courtesy overdraft services are required.
The Board solicited comment on how
the burden of disclosures on credit
unions could be minimized, but
received no suggestions. Therefore,
NCUA is issuing a final rule with only
clarifying modifications and no
substantive changes.
hsrobinson on PROD1PC68 with RULES
Paperwork Reduction Act
In accordance with the Paperwork
Reduction Act of 1995, 44 U.S.C. 3501
et seq., the Board submitted the
information collection requirements
contained in this final rule to the Office
of Management and Budget (OMB).
OMB approved the information
collection on December 28, 2005, under
control number 3133–0134.
NCUA estimated the total, continuing
annual burden for the Truth in Savings
program to be 12,076,057 hours for
9,128 credit unions. Two credit unions
commented that the rule was overly
burdensome, but provided no estimated
costs, burden hours, or suggestions to
minimize the burden.
NCUA has a continuing interest in the
public’s opinions of our information
collections. Interested parties may send
comments regarding the burden
estimate or any other aspect of the
collection, including suggestions for
reducing the burden, at any time, to
Secretary of the Board, National Credit
Union Administration, 1775 Duke
Street, Alexandria, Virginia 22314–
3428, E-mail: regcomments@ncua.gov,
or Fax: (703) 518–6319. Send a copy of
comments on the information collection
to NCUA Desk Officer, Office of
Management and Budget, New
Executive Office Building, Washington,
DC 20503, or fax (202) 395–6974 also.
Include ‘‘Comments on Part 707 Truth
in Savings’’ in the comments header.
Executive Order 13132
Executive Order 13132 encourages
independent regulatory agencies to
consider the impact of their actions on
state and local interests. In adherence to
fundamental federalism principles,
NCUA, an independent regulatory
agency as defined in 44 U.S.C. 3502(5),
voluntarily complies with the executive
order. The final rule will not have
substantial direct effects on the states,
on the connection between the national
government and the states, or on the
distribution of power and
responsibilities among the various
levels of government. NCUA has
determined that this rule does not
constitute a policy that has federalism
implications for purposes of the
executive order.
VerDate Aug<31>2005
14:58 Apr 25, 2006
Jkt 208001
The Treasury and General Government
Appropriations Act, 1999—Assessment
of Federal Regulations and Policies on
Families
The NCUA has determined that this
final rule would not affect family wellbeing within the meaning of section 654
of the Treasury and General
Government Appropriations Act, 1999,
Pub. L. 105–277, 112 Stat. 2681 (1998).
Small Business Regulatory Enforcement
Fairness Act
The Small Business Regulatory
Enforcement Fairness Act of 1996, Pub.
L. 104–121, (SBREFA) provides
generally for congressional review of
agency rules. A reporting requirement is
triggered in instances where NCUA
issues a final rule as defined by Section
551 of the Administrative Procedure
Act. 5 U.S.C. 551. The Office of
Management and Budget has
determined that this rule is not a major
rule for purposes of SBREFA. As
required by SBREFA, NCUA will file the
appropriate reports with Congress and
the General Accounting Office so that
the rule may be reviewed.
List of Subjects in 12 CFR Part 707
Advertising, Consumer protection,
Credit unions, Reporting and
recordkeeping requirements, Truth in
savings.
For the reasons set forth in the
preamble, the Board amends 12 CFR
part 707 as set forth below:
I
PART 707—TRUTH IN SAVINGS
Accordingly, the interim rule
amending 12 CFR part 707, which was
published at 70 FR 72898 on December
8, 2005, is adopted as a final rule
without change.
I
By the National Credit Union
Administration Board on April 20, 2006.
Mary F. Rupp,
Secretary of the Board.
[FR Doc. 06–3916 Filed 4–25–06; 8:45 am]
BILLING CODE 7535–01–P
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24571
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–24557; Directorate
Identifier 2006–NM–082–AD; Amendment
39–14572; AD 2006–09–02]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 757–200 and –200PF Series
Airplanes Equipped With Pratt &
Whitney Engines
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for certain
Boeing Model 757–200 and –200PF
series airplanes equipped with Pratt &
Whitney engines. This AD requires
repetitive detailed inspections to detect
and correct any gap between the strut
fitting and the forward engine mount
assembly and applicable related
investigative actions, corrective actions,
and other specified actions. This AD
results from a report indicating that gaps
had been found between the strut fitting
and the forward engine mount
assembly. We are issuing this AD to
detect and correct any gaps between the
strut fitting and the forward engine
mount assembly of both engines, which
could result in separation of the engine
from the wing and subsequent loss of
control of the airplane.
DATES: This AD becomes effective May
11, 2006.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of May 11, 2006.
We must receive comments on this
AD by June 26, 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,
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26APR1
24572
Federal Register / Vol. 71, No. 80 / Wednesday, April 26, 2006 / Rules and Regulations
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:
Dennis Stremick, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton,
Washington 98055–4056; telephone
(425) 917–6450; fax (425) 917–6590.
SUPPLEMENTARY INFORMATION:
Discussion
We have received a report indicating
that gaps have been found between the
strut fitting and the forward engine
mount assembly above the Number 1
engine on Boeing Model 757–200 and
–200PF series airplanes. The gap was
caused by the loosening of vertical
tension bolts that were installed on the
forward engine mount installation. The
gap at the two forward engine mount
bolts was 3⁄16 of an inch and the gap at
the aft two engine mount bolts was 1⁄8
of an inch. In addition, wear damage
was also found on the surfaces of the
forward engine mount assembly and the
strut fitting. This condition, if not
corrected, could result in separation of
the engine from the wing and
subsequent loss of control of the
airplane.
hsrobinson on PROD1PC68 with RULES
Relevant Service Information
We have reviewed Boeing Alert
Service Bulletin (ASB) 757–71A0085,
dated March 2, 2006.
Part 1 of the Accomplishment
Instructions of the ASB describes
procedures for an initial detailed
inspection to detect gaps between the
strut fitting and the forward engine
mount assembly of both engines. Part 1
also describes the following related
investigative actions, corrective actions,
and other specified actions. If there is
no gap found, Part 1 specifies applying
inspection torque to each engine mount
bolt and applying torque stripe between
each bolt and forward engine mount
surface. Part 1 also specifies, for certain
limits, applying installation torque to all
the bolts. If there is a gap between the
strut fitting and forward engine mount
assembly at a bolt location, Part 1
specifies a detailed inspection to detect
damage of the parts and repairing or
replacing parts. In addition, Part 1
advises operators to write to Boeing if
necessary for repair information.
Part 2 of the Accomplishment
Instructions of the ASB describes
similar procedures for repetitive
VerDate Aug<31>2005
14:58 Apr 25, 2006
Jkt 208001
detailed inspections to detect gaps
between the strut fitting and the forward
engine mount assembly of both engines.
Part 2 also describes the following
related investigative actions, corrective
actions, and other special actions. If
there is no gap found but the torque
stripe on one or more bolts is cracked,
broken or missing, Part 2 specifies
applying an inspection torque to each
forward engine mount bolt and applying
a new torque stripe between each bolt
and forward engine mount surface. Part
2 also specifies, if there is a gap found
between the strut fitting and forward
engine mount assembly at a bolt
location, performing a detailed
inspection for damage of the forward
engine mount and strut fitting and
repairing or replacing any damaged
parts. In addition, Part 2 advises
operators to write to Boeing if necessary
for repair information.
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 detect and correct any gaps
between the strut fitting and the forward
engine mount assembly. This AD
requires accomplishing the actions
specified in the service information
described previously, except as
discussed under ‘‘Differences Between
the AD and the ASB.’’
Differences Between the AD and the
ASB
Although the ASB specifies repairing
or replacing, if damage is found on parts
before subsequent flights, it also advises
operators to write to the manufacturer if
necessary for repair information. We
have clarified in Note 1 of this AD that
any deviation from the Accomplishment
Instructions provided in the ASB must
be approved as an alternative method of
compliance under paragraph (h) of this
AD.
Interim Action
This is considered to be interim
action. The manufacturer has advised
that it currently is developing a
modification that will address the
unsafe condition identified in this AD.
Once this modification is developed,
approved, and available, the FAA may
consider additional rulemaking.
FAA’s Determination of the Effective
Date
Since an unsafe condition exists that
requires the immediate adoption of this
AD, we have found that notice and
opportunity for public comment before
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Fmt 4700
Sfmt 4700
issuing this AD are impracticable, and
that 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–2006–24557; Directorate Identifier
2006–NM–082–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
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Federal Register / Vol. 71, No. 80 / Wednesday, April 26, 2006 / Rules and Regulations
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
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
I
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by adding the following new
airworthiness directive (AD):
hsrobinson on PROD1PC68 with RULES
I
2006–09–02 Boeing: Amendment 39–
14572. Docket No. FAA–2006–24557;
Directorate Identifier 2006–NM–082–AD.
Effective Date
(a) This AD becomes effective May 11,
2006.
VerDate Aug<31>2005
14:58 Apr 25, 2006
Jkt 208001
Affected ADs
(b) None.
Applicability
(c) This AD applies to Boeing Model 757–
200 and –200PF series airplanes, certificated
in any category, equipped with Pratt &
Whitney engines, as identified in Boeing
Alert Service Bulletin (ASB) 757–71A0085,
dated March 2, 2006.
Unsafe Condition
(d) This AD results from a report indicating
that gaps had been found between the strut
fitting and the forward engine mount
assembly. We are issuing this AD to detect
and correct any gaps found between the strut
fitting and the forward engine mount
assembly of both engines, which could result
in separation of the engine from the wing and
subsequent 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.
Initial Inspection
(f) Within 90 days after the effective date
of this AD or within 3,000 flight cycles since
the most recent installation of each engine,
whichever occurs later: For each engine,
perform a detailed inspection to detect any
gap between the strut fitting and the forward
engine mount assembly of the engine, and
before further flight, do all applicable related
investigative actions, corrective actions, and
other specified actions; in accordance with
Part 1 of the Accomplishment Instructions of
Boeing ASB 757–71A0085, dated March 2,
2006.
Note 1: In the Accomplishment
Instructions of the ASB, the manufacturer
provides instructions to repair or replace
parts before ‘‘subsequent’’ flight if damage is
found on parts. However, the manufacturer
also specifies to write to the manufacturer if
necessary for repair information. This AD
requires that any deviation from the
instructions provided in the ASB must be
approved as an alternative method of
compliance under paragraph (h) of this AD.
Repetitive Inspections
(g) Within 3,000 flight cycles after
accomplishing the requirements of paragraph
(f) of this AD: Perform a detailed inspection
to detect any gap between the strut fitting
and the forward mount assembly of both
engines, and before further flight, do all
applicable related investigative actions,
corrective actions, and other specified
actions; in accordance with Part 2 of the
Accomplishment Instructions of Boeing ASB
757–71A0085, dated March 2, 2006.
Thereafter, repeat the actions specified in
Part 2 of the Accomplishment Instructions of
the ASB at intervals not to exceed 3,000
flight cycles.
Alternative Methods of Compliance
(AMOCs)
(h)(1) The Manager, Seattle Aircraft
Certification Office (ACO), FAA, has the
authority to approve AMOCs for this AD, if
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Fmt 4700
Sfmt 4700
24573
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.
Material Incorporated by Reference
(i) You must use Boeing Alert Service
Bulletin 757–71A0085, dated March 2, 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, 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 17,
2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 06–3891 Filed 4–25–06; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–23313; Directorate
Identifier 2005–NM–111–AD; Amendment
39–14573; AD 2006–09–03]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 727, 727C, 727–100, and 727–
100C Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for all
E:\FR\FM\26APR1.SGM
26APR1
Agencies
[Federal Register Volume 71, Number 80 (Wednesday, April 26, 2006)]
[Rules and Regulations]
[Pages 24571-24573]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 06-3891]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-24557; Directorate Identifier 2006-NM-082-AD;
Amendment 39-14572; AD 2006-09-02]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 757-200 and -200PF Series
Airplanes Equipped With Pratt & Whitney Engines
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 Boeing Model 757-200 and -200PF series airplanes equipped with
Pratt & Whitney engines. This AD requires repetitive detailed
inspections to detect and correct any gap between the strut fitting and
the forward engine mount assembly and applicable related investigative
actions, corrective actions, and other specified actions. This AD
results from a report indicating that gaps had been found between the
strut fitting and the forward engine mount assembly. We are issuing
this AD to detect and correct any gaps between the strut fitting and
the forward engine mount assembly of both engines, which could result
in separation of the engine from the wing and subsequent loss of
control of the airplane.
DATES: This AD becomes effective May 11, 2006.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in the AD as of May 11, 2006.
We must receive comments on this AD by June 26, 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,
[[Page 24572]]
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: Dennis Stremick, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
917-6450; fax (425) 917-6590.
SUPPLEMENTARY INFORMATION:
Discussion
We have received a report indicating that gaps have been found
between the strut fitting and the forward engine mount assembly above
the Number 1 engine on Boeing Model 757-200 and -200PF series
airplanes. The gap was caused by the loosening of vertical tension
bolts that were installed on the forward engine mount installation. The
gap at the two forward engine mount bolts was \3/16\ of an inch and the
gap at the aft two engine mount bolts was \1/8\ of an inch. In
addition, wear damage was also found on the surfaces of the forward
engine mount assembly and the strut fitting. This condition, if not
corrected, could result in separation of the engine from the wing and
subsequent loss of control of the airplane.
Relevant Service Information
We have reviewed Boeing Alert Service Bulletin (ASB) 757-71A0085,
dated March 2, 2006.
Part 1 of the Accomplishment Instructions of the ASB describes
procedures for an initial detailed inspection to detect gaps between
the strut fitting and the forward engine mount assembly of both
engines. Part 1 also describes the following related investigative
actions, corrective actions, and other specified actions. If there is
no gap found, Part 1 specifies applying inspection torque to each
engine mount bolt and applying torque stripe between each bolt and
forward engine mount surface. Part 1 also specifies, for certain
limits, applying installation torque to all the bolts. If there is a
gap between the strut fitting and forward engine mount assembly at a
bolt location, Part 1 specifies a detailed inspection to detect damage
of the parts and repairing or replacing parts. In addition, Part 1
advises operators to write to Boeing if necessary for repair
information.
Part 2 of the Accomplishment Instructions of the ASB describes
similar procedures for repetitive detailed inspections to detect gaps
between the strut fitting and the forward engine mount assembly of both
engines. Part 2 also describes the following related investigative
actions, corrective actions, and other special actions. If there is no
gap found but the torque stripe on one or more bolts is cracked, broken
or missing, Part 2 specifies applying an inspection torque to each
forward engine mount bolt and applying a new torque stripe between each
bolt and forward engine mount surface. Part 2 also specifies, if there
is a gap found between the strut fitting and forward engine mount
assembly at a bolt location, performing a detailed inspection for
damage of the forward engine mount and strut fitting and repairing or
replacing any damaged parts. In addition, Part 2 advises operators to
write to Boeing if necessary for repair information.
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 detect and correct any gaps between the strut
fitting and the forward engine mount assembly. This AD requires
accomplishing the actions specified in the service information
described previously, except as discussed under ``Differences Between
the AD and the ASB.''
Differences Between the AD and the ASB
Although the ASB specifies repairing or replacing, if damage is
found on parts before subsequent flights, it also advises operators to
write to the manufacturer if necessary for repair information. We have
clarified in Note 1 of this AD that any deviation from the
Accomplishment Instructions provided in the ASB must be approved as an
alternative method of compliance under paragraph (h) of this AD.
Interim Action
This is considered to be interim action. The manufacturer has
advised that it currently is developing a modification that will
address the unsafe condition identified in this AD. Once this
modification is developed, approved, and available, the FAA may
consider additional rulemaking.
FAA's Determination of the Effective Date
Since an unsafe condition exists that requires the immediate
adoption of this AD, we have found that notice and opportunity for
public comment before issuing this AD are impracticable, and that 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-2006-
24557; Directorate Identifier 2006-NM-082-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
[[Page 24573]]
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
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
adding the following new airworthiness directive (AD):
2006-09-02 Boeing: Amendment 39-14572. Docket No. FAA-2006-24557;
Directorate Identifier 2006-NM-082-AD.
Effective Date
(a) This AD becomes effective May 11, 2006.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Boeing Model 757-200 and -200PF series
airplanes, certificated in any category, equipped with Pratt &
Whitney engines, as identified in Boeing Alert Service Bulletin
(ASB) 757-71A0085, dated March 2, 2006.
Unsafe Condition
(d) This AD results from a report indicating that gaps had been
found between the strut fitting and the forward engine mount
assembly. We are issuing this AD to detect and correct any gaps
found between the strut fitting and the forward engine mount
assembly of both engines, which could result in separation of the
engine from the wing and subsequent 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.
Initial Inspection
(f) Within 90 days after the effective date of this AD or within
3,000 flight cycles since the most recent installation of each
engine, whichever occurs later: For each engine, perform a detailed
inspection to detect any gap between the strut fitting and the
forward engine mount assembly of the engine, and before further
flight, do all applicable related investigative actions, corrective
actions, and other specified actions; in accordance with Part 1 of
the Accomplishment Instructions of Boeing ASB 757-71A0085, dated
March 2, 2006.
Note 1: In the Accomplishment Instructions of the ASB, the
manufacturer provides instructions to repair or replace parts before
``subsequent'' flight if damage is found on parts. However, the
manufacturer also specifies to write to the manufacturer if
necessary for repair information. This AD requires that any
deviation from the instructions provided in the ASB must be approved
as an alternative method of compliance under paragraph (h) of this
AD.
Repetitive Inspections
(g) Within 3,000 flight cycles after accomplishing the
requirements of paragraph (f) of this AD: Perform a detailed
inspection to detect any gap between the strut fitting and the
forward mount assembly of both engines, and before further flight,
do all applicable related investigative actions, corrective actions,
and other specified actions; in accordance with Part 2 of the
Accomplishment Instructions of Boeing ASB 757-71A0085, dated March
2, 2006. Thereafter, repeat the actions specified in Part 2 of the
Accomplishment Instructions of the ASB at intervals not to exceed
3,000 flight cycles.
Alternative Methods of Compliance (AMOCs)
(h)(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
(i) You must use Boeing Alert Service Bulletin 757-71A0085,
dated March 2, 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,
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 17, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 06-3891 Filed 4-25-06; 8:45 am]
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