Airworthiness Directives; Boeing Model 757 Airplanes, 53554-53556 [05-17772]
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53554
Federal Register / Vol. 70, No. 174 / Friday, September 9, 2005 / Rules and Regulations
TABLE 1.—GOODRICH ‘‘FASTPROP’’ PROPELLER DE-ICERS—Continued
De-icer P/N
Installed on, but not limited to
Bombardier (deHavilland) DHC–2MK.III equipped with HC–B3TN–3, HC–B3TN–3B, or HC–B3TN–3BY props.
Bombardier (deHavilland) DHC–6–300 equipped with Hartzell HC–B3TN–3(D)(Y) props.
Embraer EMB–110P1/2 equipped with Hartzell HC–B3TN–3C or HC–B3TN–3D props.
The following models equipped with Hartzell HC–B3TN–5( ) props: M7 Aerospace (Fairchild) SA226–AT, and
SA226T.
M7 Aerospace (Fairchild) SA226–TC equipped with Hartzell HC–B4TN–5( ) props.
M7 Aerospace (Fairchild) SA226–TC with STC SA344GL equipped with Hartzell HC–B3TN–5( ) props.
M7 Aerospace (Fairchild) SA226–TC with STC SA344Gl.
The following models equipped with Hartzell HC–A3VF–7 or HC–3VH–7B props: AeroSpace Technologies of Australia
(Government Aircraft Factories) N22B and N24A.
The following models equipped with Hartzell HC–B3TN–3D props: IAI Arava 101 and 101B.
The following models equipped with Hartzell HC–B3TN–3DY props: McKinnon (Grumman) G–21E and G–21G.
The following models equipped with HC–B3TN–5( ) props: Mitsubishi Heavy Industries MU–2B, and MU–2B–10.
The following models equipped with Hartzell HC–B3TN–5 props: Mitsubishi Heavy Industries MU–2B–15, MU–2B–20,
MU–2B–25, MU–2B–26, MU–2B–30, MU–2B–35, and MU–2B–36.
The following models equipped with Hartzell HC–B3TN–3C props: Pilatus PC–6, PC–6/B–H2, PC–6/B1–H2, PC–6/C–
H2, PC–6/C1–H2.
The following models equipped with Hartzell HC–B3TN–3B props: Piper PA–31T and PA31T1.
The following models equipped with Hartzell HC–B3TN–3B or HC–B3TN–3K props: Piper PA42 and PA42–720.
The following model equipped with Hartzell HC–B3TN–5( ) props: Short Brothers SC–7 series 3 Variant 200.
With STC SA02059AK on the following model equipped with HC–B4TN–5 props: Short Brothers SC–7 series 3 Variant 200.
The following models equipped with Hartzell HC–B3TN–5( ) props: Twin Commander (Gulfstream) 690, 690A, and
690B.
Unsafe Condition
(d) This AD results from reports of
Goodrich ‘‘FASTprop’’ propeller de-icers
becoming loose or debonded, and detaching
from propeller blades during operation. We
are issuing this AD to prevent Goodrich
‘‘FASTprop’’ propeller de-icers from
detaching from the propeller blade, resulting
in damage to the airplane, and possible
injury to passengers and crewmembers.
repaired, or replaced as necessary before the
next flight. Terminating action is
accomplished when the ‘‘FASTprop’’
propeller de-icer is removed and replaced
with an approved propeller de-icer. Use
paragraph 2.A(2) of the Accomplishment
Instructions of Goodrich De-icing and
Specialty Systems Alert Service Bulletin
(ASB) No. 30–60–00–1, dated November 15,
2004 to do these actions.
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.
(f) Properly certificated maintenance
personnel must perform the initial inspection
required in this AD. Thereafter, the pilot or
properly certificated maintenance personnel
may perform the repetitive visual check.
Alternative Methods of Compliance
(i) The Manager, Chicago Aircraft
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.
Initial Visual Inspection of ‘‘FASTprop’’
Propeller De-Icers
(g) Within 10 hours after the effective date
of this AD, inspect the ‘‘FASTprop’’ propeller
de-icers. If any ‘‘FASTprop’’ propeller de-icer
fails the inspection, then the ‘‘FASTprop’’
de-icer must be repaired or replaced as
necessary before the next flight. Use
paragraphs 2.A(3) through (5) of the
Accomplishment Instructions of Goodrich
De-icing and Specialty Systems Alert Service
Bulletin (ASB) No. 30–60–00–1, dated
November 15, 2004 to do these actions.
Repetitive Visual Inspections of
‘‘FASTprop’’ Propeller De-Icers
(h) After the initial inspection, visually
check the ‘‘FASTprop’’ propeller de-icer once
per day either during the pilot’s first preflight
inspection of the day or when maintenance
personnel are available. If any ‘‘FASTprop’’
propeller de-icer fails the visual check, then
the ‘‘FASTprop’’ de-icer must be inspected,
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Special Flight Permits
(j) Under 14 CFR part 39.23, we are
limiting the special flight permits for this AD
by requiring that any propeller found with a
loose or debonded ‘‘FASTprop’’ de-icer must
have all propeller blade de-icers removed
before the flight, to maintain a balanced
propeller. Information on removing de-icers
can be found in paragraph 1.K.(1) of
Goodrich De-icing and Specialty Systems
ASB No. 30–60–00–1, dated November 15,
2004.
Related Information
(k) None.
Material Incorporated by Reference
(l) You must use Goodrich De-icing and
Specialty Systems Alert Service Bulletin No.
30–60–00–1, dated November 15, 2004, to
perform the inspections, repairs, and
replacements required by this AD. The
Director of the Federal Register approved the
incorporation by reference of this service
bulletin in accordance with 5 U.S.C. 552(a)
and 1 CFR part 51. Contact Goodrich De-icing
and Specialty Systems, 1555 Corporate
Woods Parkway, Uniontown, Ohio 44685,
PO 00000
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telephone (330) 374–3743, 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., Nassif Building, Room PL–401,
Washington, DC 20590–0001, 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 NARA, call (202) 741–
6030, or go to: https://www.archives.gov/
federal_register/code_of_federal_regulations/
ibr_locations.html.
Issued in Burlington, Massachusetts, on
September 1, 2005.
Peter A. White,
Acting Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. 05–17773 Filed 9–8–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2004–19540; Directorate
Identifier 2004–NM–110–AD; Amendment
39–14258; AD 2005–18–18]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 757 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for certain
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Federal Register / Vol. 70, No. 174 / Friday, September 9, 2005 / Rules and Regulations
Boeing Model 757 airplanes. This AD
requires inspections of certain wire
bundles in the left and right engine-towing aft fairings for discrepancies;
installation of back-to-back p-clamps
between the wire and hydraulic supply
tube at the aft end of the right-hand strut
only; and associated re-routing of the
wire bundles, if necessary. This AD
results from a report indicating that a
circuit breaker for the fuel shutoff valve
tripped due to a wire that chafed against
the structure in the flammable leakage
zone of the aft fairing, causing a short
circuit. We are issuing this AD to
prevent chafing between the wire
bundle and the structure of the aft
fairing, which could result in electrical
arcing and subsequent ignition of
flammable vapors and possible
uncontrollable fire.
DATES: This AD becomes effective
October 14, 2005.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of October 14, 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:
Thomas Thorson, Aerospace Engineer,
Propulsion Branch, ANM–140S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton,
Washington 98055–4056; telephone
(425) 917–6508; fax (425) 917–6590.
SUPPLEMENTARY INFORMATION:
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 street
address stated in the ADDRESSES section.
Discussion
The FAA issued a supplemental
notice of proposed rulemaking (NPRM)
to amend 14 CFR part 39 to include an
AD that would apply to certain Boeing
Model 757 airplanes. That supplemental
NPRM was published in the Federal
Register on July 6, 2005 (70 FR 38823).
That supplemental NPRM proposed to
VerDate Aug<18>2005
15:11 Sep 08, 2005
Jkt 205001
require inspections of certain wire
bundles in the left and right engine-towing aft fairings for discrepancies;
installation of back-to-back p-clamps
between the wire and hydraulic supply
tube at the aft end of the right-hand strut
only; and associated re-routing of the
wire bundles, if necessary.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comments received. The
commenters support the supplemental
NPRM.
Conclusion
We have carefully reviewed the
available data, including the comments
received, and determined that air safety
and the public interest require adopting
the AD as proposed in the supplemental
NPRM.
Costs of Compliance
There are about 618 airplanes of the
affected design in the worldwide fleet.
This AD will affect about 342 airplanes
of U.S. registry. The actions will take
between 16 and 44 work hours per
airplane, depending on airplane
configuration, at an average labor rate of
$65 per work hour. Required parts will
cost about $600 per airplane. Based on
these figures, the estimated cost of this
AD on U.S. operators is between
$560,880 and $1,183,320, or between
$1,640 and $3,460 per airplane.
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
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53555
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
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):
I
2005–18–18 Boeing: Amendment 39–14258.
Docket No. FAA–2004–19540;
Directorate Identifier 2004–NM–110–AD.
Effective Date
(a) This AD becomes effective October 14,
2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Model 757–200,
–200PF, –200CB, and –300 series airplanes;
certificated in any category; equipped with
Rolls-Royce engines; as identified in Boeing
Alert Service Bulletins 757–28A0073 and
757–28A0074, both Revision 1, both dated
February 24, 2005.
Unsafe Condition
(d) This AD was prompted by a report
indicating that a circuit breaker for the fuel
shutoff valve tripped due to a wire that
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09SER1
53556
Federal Register / Vol. 70, No. 174 / Friday, September 9, 2005 / Rules and Regulations
chafed against the structure in the flammable
leakage zone of the aft fairing, causing a short
circuit. The FAA is issuing this AD to
prevent chafing between the wire bundle and
the structure of the aft fairing, which could
result in electrical arcing and subsequent
ignition of flammable vapors and possible
uncontrollable fire.
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.
One-Time Inspections/Related Investigative
and Corrective Actions
(f) Within 60 months after the effective
date of this AD, do the actions required by
paragraphs (f)(1) and (f)(2) of this AD.
(1) Accomplish the detailed inspections for
discrepancies of the wire bundles in the left
and right engine-to-wing aft fairings, and
applicable and related investigative and
corrective actions if necessary, as applicable,
by doing all the actions specified in the
Accomplishment Instructions of the
applicable service bulletins listed in Table 1
of this AD. Accomplish any related
investigative and corrective actions before
further flight in accordance with the
applicable service bulletin.
TABLE 1.—AIRPLANE MODELS AND SERVICE BULLETINS
Boeing Alert
Service
Bulletin
Boeing airplanes
Model
Model
Model
Model
757–200, –200CB, 200PF series airplanes ............................................................
757–200, –200CB, 200PF series airplanes ............................................................
757–300 series airplanes ........................................................................................
757–300 series airplanes ........................................................................................
(2) Install back-to-back p-clamps between
the wire and hydraulic supply tube at the aft
end of the right-hand strut only; and re-route
the wire bundles, if necessary, by doing all
the applicable actions specified in the
Accomplishment Instructions of Boeing Alert
Service Bulletin 757–28A0073 or 757–
28A0074, both Revision 1, both dated
February 24, 2005; as applicable.
Note 1: For the purposes of this AD, a
detailed inspection is: ‘‘An intensive
examination of a specific item, installation,
or assembly to detect damage, failure, or
irregularity. Available lighting is normally
supplemented with a direct source of good
lighting at an intensity deemed appropriate.
Inspection aids such as mirror, magnifying
Revision
level
757–28A0073
757–28A0073
757–28A0074
757–28A0074
Original ......
1 .................
Original ......
1 .................
lenses, etc., may be necessary. Surface
cleaning and elaborate procedures may be
required.’’
Alternative Methods of Compliance
(AMOCs)
(g) The Manager, Seattle Aircraft
Certification Office, FAA, has the authority to
approve AMOCs for this AD, if requested in
accordance with the procedures found in 14
CFR 39.19.
Material Incorporated by Reference
(h) You must use the applicable service
bulletin listed in Table 2 of this AD to
perform the actions that are required by this
AD, unless the AD specifies otherwise. The
Director of the Federal Register approved the
Date
November 20, 2003.
February 24, 2005.
November 20, 2003.
February 24, 2005.
incorporation by reference of these
documents 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.
TABLE 2.—MATERIAL INCORPORATED BY REFERENCE
Revision
level
Boeing Alert Service Bulletin
757–28A0073
757–28A0073
757–28A0074
757–28A0074
................................................................................................................................................
................................................................................................................................................
................................................................................................................................................
................................................................................................................................................
Issued in Renton, Washington, on August
31, 2005.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 05–17772 Filed 9–8–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–21683; Directorate
Identifier 2005–NM–021–AD; Amendment
39–14259; AD 2005–18–19]
RIN 2120–AA64
Airworthiness Directives; Fokker
Model F27 Mark 200, 400, 500, and 600
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
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15:11 Sep 08, 2005
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Fmt 4700
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Original ......
1 .................
Original ......
1 .................
Date
November 20, 2003.
February 24, 2005.
November 20, 2003.
February 24, 2005.
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for certain
Fokker Model F27 Mark 200, 400, 500,
and 600 airplanes. This AD requires a
general visual inspection of the rotary
knobs for the fuel tank isolation valves
to determine if the seal wire has been
installed correctly, and corrective
actions if necessary. This AD results
from investigation of a recent accident,
which found that the rotary knobs
controlling the fuel tank isolating valves
had been in the shut position. We are
issuing this AD to ensure that the rotary
knobs are not inadvertently moved to
the shut position, which could result in
fuel starvation to both engines and
E:\FR\FM\09SER1.SGM
09SER1
]]>Agencies
[Federal Register Volume 70, Number 174 (Friday, September 9, 2005)]
[Rules and Regulations]
[Pages 53554-53556]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-17772]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2004-19540; Directorate Identifier 2004-NM-110-AD;
Amendment 39-14258; AD 2005-18-18]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 757 Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain
[[Page 53555]]
Boeing Model 757 airplanes. This AD requires inspections of certain
wire bundles in the left and right engine-to-wing aft fairings for
discrepancies; installation of back-to-back p-clamps between the wire
and hydraulic supply tube at the aft end of the right-hand strut only;
and associated re-routing of the wire bundles, if necessary. This AD
results from a report indicating that a circuit breaker for the fuel
shutoff valve tripped due to a wire that chafed against the structure
in the flammable leakage zone of the aft fairing, causing a short
circuit. We are issuing this AD to prevent chafing between the wire
bundle and the structure of the aft fairing, which could result in
electrical arcing and subsequent ignition of flammable vapors and
possible uncontrollable fire.
DATES: This AD becomes effective October 14, 2005.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of October 14,
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: Thomas Thorson, Aerospace Engineer,
Propulsion Branch, ANM-140S, FAA, Seattle Aircraft Certification
Office, 1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone
(425) 917-6508; fax (425) 917-6590.
SUPPLEMENTARY INFORMATION:
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 street address stated in the
ADDRESSES section.
Discussion
The FAA issued a supplemental notice of proposed rulemaking (NPRM)
to amend 14 CFR part 39 to include an AD that would apply to certain
Boeing Model 757 airplanes. That supplemental NPRM was published in the
Federal Register on July 6, 2005 (70 FR 38823). That supplemental NPRM
proposed to require inspections of certain wire bundles in the left and
right engine-to-wing aft fairings for discrepancies; installation of
back-to-back p-clamps between the wire and hydraulic supply tube at the
aft end of the right-hand strut only; and associated re-routing of the
wire bundles, if necessary.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comments received. The
commenters support the supplemental NPRM.
Conclusion
We have carefully reviewed the available data, including the
comments received, and determined that air safety and the public
interest require adopting the AD as proposed in the supplemental NPRM.
Costs of Compliance
There are about 618 airplanes of the affected design in the
worldwide fleet. This AD will affect about 342 airplanes of U.S.
registry. The actions will take between 16 and 44 work hours per
airplane, depending on airplane configuration, at an average labor rate
of $65 per work hour. Required parts will cost about $600 per airplane.
Based on these figures, the estimated cost of this AD on U.S. operators
is between $560,880 and $1,183,320, or between $1,640 and $3,460 per
airplane.
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]
0
2. The Federal Aviation Administration (FAA) amends Sec. 39.13 by
adding the following new airworthiness directive (AD):
2005-18-18 Boeing: Amendment 39-14258. Docket No. FAA-2004-19540;
Directorate Identifier 2004-NM-110-AD.
Effective Date
(a) This AD becomes effective October 14, 2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Model 757-200, -200PF, -200CB, and -300
series airplanes; certificated in any category; equipped with Rolls-
Royce engines; as identified in Boeing Alert Service Bulletins 757-
28A0073 and 757-28A0074, both Revision 1, both dated February 24,
2005.
Unsafe Condition
(d) This AD was prompted by a report indicating that a circuit
breaker for the fuel shutoff valve tripped due to a wire that
[[Page 53556]]
chafed against the structure in the flammable leakage zone of the
aft fairing, causing a short circuit. The FAA is issuing this AD to
prevent chafing between the wire bundle and the structure of the aft
fairing, which could result in electrical arcing and subsequent
ignition of flammable vapors and possible uncontrollable fire.
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.
One-Time Inspections/Related Investigative and Corrective Actions
(f) Within 60 months after the effective date of this AD, do the
actions required by paragraphs (f)(1) and (f)(2) of this AD.
(1) Accomplish the detailed inspections for discrepancies of the
wire bundles in the left and right engine-to-wing aft fairings, and
applicable and related investigative and corrective actions if
necessary, as applicable, by doing all the actions specified in the
Accomplishment Instructions of the applicable service bulletins
listed in Table 1 of this AD. Accomplish any related investigative
and corrective actions before further flight in accordance with the
applicable service bulletin.
Table 1.--Airplane Models and Service Bulletins
----------------------------------------------------------------------------------------------------------------
Boeing Alert Service
Boeing airplanes Bulletin Revision level Date
----------------------------------------------------------------------------------------------------------------
Model 757-200, -200CB, 200PF 757-28A0073......... Original............ November 20, 2003.
series airplanes.
Model 757-200, -200CB, 200PF 757-28A0073......... 1................... February 24, 2005.
series airplanes.
Model 757-300 series airplanes... 757-28A0074......... Original............ November 20, 2003.
Model 757-300 series airplanes... 757-28A0074......... 1................... February 24, 2005.
----------------------------------------------------------------------------------------------------------------
(2) Install back-to-back p-clamps between the wire and hydraulic
supply tube at the aft end of the right-hand strut only; and re-
route the wire bundles, if necessary, by doing all the applicable
actions specified in the Accomplishment Instructions of Boeing Alert
Service Bulletin 757-28A0073 or 757-28A0074, both Revision 1, both
dated February 24, 2005; as applicable.
Note 1: For the purposes of this AD, a detailed inspection is:
``An intensive examination of a specific item, installation, or
assembly to detect damage, failure, or irregularity. Available
lighting is normally supplemented with a direct source of good
lighting at an intensity deemed appropriate. Inspection aids such as
mirror, magnifying lenses, etc., may be necessary. Surface cleaning
and elaborate procedures may be required.''
Alternative Methods of Compliance (AMOCs)
(g) The Manager, Seattle Aircraft Certification Office, FAA, has
the authority to approve AMOCs for this AD, if requested in
accordance with the procedures found in 14 CFR 39.19.
Material Incorporated by Reference
(h) You must use the applicable service bulletin listed in Table
2 of this AD 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 these documents
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.
Table 2.--Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
Boeing Alert Service Bulletin Revision level Date
----------------------------------------------------------------------------------------------------------------
757-28A0073.............................. Original................... November 20, 2003.
757-28A0073.............................. 1.......................... February 24, 2005.
757-28A0074.............................. Original................... November 20, 2003.
757-28A0074.............................. 1.......................... February 24, 2005.
----------------------------------------------------------------------------------------------------------------
Issued in Renton, Washington, on August 31, 2005.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-17772 Filed 9-8-05; 8:45 am]
BILLING CODE 4910-13-P
