Airworthiness Directives; The Boeing Company Model 777-200 and -300 Series Airplanes Equipped With Pratt and Whitney Engines, 3566-3569 [2011-1119]
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Federal Register / Vol. 76, No. 13 / Thursday, January 20, 2011 / Proposed Rules
under the criteria of the Regulatory
Flexibility Act.
You can find our regulatory
evaluation and the estimated costs of
compliance in the AD Docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
Saab AB, Saab Aerosystems: Docket No.
FAA–2010–0042; Directorate Identifier
2009–NM–010–AD.
Comments Due Date
(a) We must receive comments by March 7,
2011.
Affected ADs
(b) None.
Applicability
(c) This AD applies to the Saab AB, Saab
Aerosystems airplanes, certificated in any
category, identified in paragraphs (c)(1) and
(c)(2) of this AD, that have been modified in
accordance with Supplemental Type
Certificate (STC) ST00224WI–D,
ST00146WI–D, or SA984GL–D.
(1) Model SAAB 340A (SAAB/SF340A)
airplanes, serial numbers 004 through 159
inclusive.
(2) Model SAAB 340B airplanes, serial
numbers 160 through 459 inclusive.
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Subject
(d) Joint Aircraft System Component
(JASC)/Air Transport Association (ATA) of
America Code 53: Fuselage.
Unsafe Condition
(e) This AD results from a report of a crack
found behind the external adapter plate of
the antennae during inspection. Similar
cracking was found on two additional
airplanes, and extensive corrosion was found
on one airplane. The Federal Aviation
Administration is issuing this AD to detect
and correct corrosion and cracking behind
the external adapter plate of the antennae of
certain damage-tolerant structure, which
could result in reduced structural integrity
and consequent rapid depressurization of the
airplane.
Compliance
(f) You are responsible for having the
actions required by this AD performed within
the compliance times specified.
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Jkt 223001
Inspection/Corrective Actions
(g) Within 600 flight cycles after the
effective date of this AD: Remove the external
adapter plate of the antennae installation and
do a general visual inspection of the fuselage
surface for corrosion and cracking behind the
external adapter plate of the antennae
installation. If any corrosion or cracking is
found, repair before further flight. If no
corrosion or cracking is found, before further
flight, ensure that proper corrosion
protection has been applied before
reinstalling the adapter plate. Do all the
actions required by this paragraph in
accordance with a method approved by the
Manager, Wichita Aircraft Certification Office
(ACO), FAA.
Note 1: For the purposes of this AD, a
general visual inspection is: ‘‘A visual
examination of an interior or exterior area,
installation, or assembly to detect obvious
damage, failure, or irregularity. This level of
inspection is made from within touching
distance unless otherwise specified. A mirror
may be necessary to ensure visual access to
all surfaces in the inspection area. This level
of inspection is made under normally
available lighting conditions such as
daylight, hangar lighting, flashlight, or
droplight and may require removal or
opening of access panels or doors. Stands,
ladders, or platforms may be required to gain
proximity to the area being checked.’’
Reporting Requirement
(h) At the applicable time specified in
paragraph (h)(1) or (h)(2) of this AD: Submit
a report of the positive findings of the
inspections required by paragraph (g) of this
AD. Send the report to the Manager, Wichita
ACO. The report must contain, at a
minimum, the inspection results, a
description of any discrepancies found, the
airplane serial number, and the number of
flight cycles and flight hours on the airplane
since installation of the STC. Under the
provisions of the Paperwork Reduction Act
(44 U.S.C. 3501 et seq.), the Office of
Management and Budget (OMB) has
approved the information collection
requirements contained in this AD and has
assigned OMB Control Number 2120–0056.
(1) If the inspection was done on or after
the effective date of this AD: Submit the
report within 30 days after the inspection.
(2) If the inspection was done before the
effective date of this AD: Submit the report
within 30 days after the effective date of this
AD.
(3) A Federal agency may not conduct or
sponsor, and a person is not required to
respond to, nor shall a person be subject to
a penalty for failure to comply with a
collection of information subject to the
requirements of the Paperwork Reduction
Act unless that collection of information
displays a current valid OMB Control
Number. The OMB Control Number for this
information collection is 2120–0056. Public
reporting for this collection of information is
estimated to be approximately 5 minutes per
response, including the time for reviewing
instructions, completing and reviewing the
collection of information. All responses to
this collection of information are mandatory.
Comments concerning the accuracy of this
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burden and suggestions for reducing the
burden should be directed to the FAA at: 800
Independence Ave., SW, Washington, DC
20591, Attn: Information Collection
Clearance Officer, AES–200.
Special Flight Permit
(i) Special flight permits, as described in
Section 21.197 and Section 21.199 of the
Federal Aviation Regulations (14 CFR 21.197
and 21.199), may be issued to operate the
airplane to a location where the requirements
of this AD can be accomplished, but
concurrence by the Manager, Wichita ACO,
FAA, is required prior to issuance of the
special flight permit.
Alternative Methods of Compliance
(AMOCs)
(j)(1) The Manager, Wichita ACO, FAA, has
the authority to approve AMOCs for this AD,
if requested using the procedures found in 14
CFR 39.19. Send information to ATTN:
William Griffith, Aerospace Engineer,
Airframe Branch, ACE–118W, FAA, Wichita
ACO, 1801 Airport Road, Room 100, MidContinent Airport, Wichita, Kansas 67209;
telephone (316) 946–4116; fax (316) 946–
4107.
(2) To request a different method of
compliance or a different compliance time
for this AD, follow the procedures in 14 CFR
39.19. Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office. The AMOC
approval letter must specifically reference
this AD.
Issued in Renton, Washington on January
12, 2011.
Jeffrey E. Duven,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2011–1118 Filed 1–19–11; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2011–0026; Directorate
Identifier 2010–NM–104–AD]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Model 777–200 and –300
Series Airplanes Equipped With Pratt
and Whitney Engines
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for certain
Model 777–200 and –300 series
airplanes. This proposed AD would
require repetitive inspections for
SUMMARY:
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Federal Register / Vol. 76, No. 13 / Thursday, January 20, 2011 / Proposed Rules
hydraulic fluid contamination of the
interior of the strut disconnect
assembly; repetitive inspections for
discrepancies of the interior of the strut
disconnect assembly, if necessary;
repetitive inspections of the exterior of
the strut disconnect assembly for cracks,
if necessary; and corrective action if
necessary. This proposed AD also
provides an optional terminating action
for the inspections. This proposed AD
results from reports of system
disconnect boxes that have been
contaminated with hydraulic fluid and,
in one incident, led to subsequent
cracking of titanium parts in the system
disconnect assembly. We are proposing
this AD to detect and correct hydraulic
fluid contamination, which can cause
cracking of titanium parts in the system
disconnect assembly, resulting in
compromise of the engine firewall. A
cracked firewall can allow fire in the
engine area to enter the strut and can
lead to an uncontained engine strut fire
if flammable fluid is present. Cracking
of the disconnect box may also reduce
the effectiveness of the fire
extinguishing system in the engine
compartment and could contribute to an
uncontained engine fire. In addition, a
cracked disconnect box can leak
flammable fluids into the engine core,
which can initiate an engine fire, and
lead to one or both fire conditions
discussed above.
DATES: We must receive comments on
this proposed AD by March 7, 2011.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590, between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays.
For service information identified in
this proposed AD, contact Boeing
Commercial Airplanes, Attention: Data
& Services Management, P.O. Box 3707,
MC 2H–65, Seattle, Washington 98124–
2207; telephone 206–544–5000,
extension 1; fax 206–766–5680; e-mail
me.boecom@boeing.com; Internet
https://www.myboeingfleet.com. You
may review copies of the referenced
service information at the FAA,
Transport Airplane Directorate, 1601
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18:20 Jan 19, 2011
Jkt 223001
Lind Avenue, SW., Renton, Washington.
For information on the availability of
this material at the FAA, call 425–227–
1221.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Management Facility between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Office
(telephone 800–647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT:
Kevin Nguyen, Propulsion Branch,
ANM–140S, FAA, Seattle Aircraft
Certification Office (ACO), 1601 Lind
Avenue, SW., Renton, Washington
98057–3356; telephone (425) 917–6501;
fax (425) 917–6590.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2011–0026; Directorate Identifier
2010–NM–104–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD because of those
comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
We have received reports of system
disconnect boxes that have been
contaminated with hydraulic fluid. One
operator has found cracks in the system
disconnect assembly bulkheads and
lower skin panel. Subsequent analysis at
Boeing found hydrogen enbrittlement of
the system disconnect assembly
bulkheads and lower skin panel. The
system disconnect assembly is made
from titanium and is located near the
hot engine core of the engine where
temperatures can exceed 270 degrees
Fahrenheit. The presence of hydraulic
fluid and temperature above 270 degrees
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Fahrenheit can result in hydrogen
embrittlement of the titanium system
disconnect assembly. Hydrogen
embrittlement combined with a high
sonic vibration environment can result
in cracking of the system disconnect
assembly. The system disconnect
assembly is a box where hydraulic, fuel,
and electrical connections are made
between the engine and the strut. This
box acts as a firewall between the
engine compartment and the strut. The
engine compartment has a fire
extinguishing system while the strut
does not. The strut is considered a
flammable leakage zone where
flammable fluids may be present. These
fluids are subsequently drained from the
strut and system disconnect box. A
cracked firewall can allow fire in the
engine area to enter the strut and can
lead to an uncontained engine strut fire
if flammable fluid is present. Cracking
of the disconnect box may also reduce
the effectiveness of the fire
extinguishing system in the engine
compartment and could contribute to an
uncontained engine fire. In addition, a
cracked disconnect box can leak
flammable fluids into the engine core,
which can initiate an engine fire, and
lead to one or both fire conditions
discussed above.
Relevant Service Information
We have reviewed Boeing Alert
Service Bulletin 777–54A0024, Revision
1, dated November 4, 2010. This service
bulletin describes procedures for doing
repetitive general visual inspections for
hydraulic fluid contamination of the
interior of the strut disconnect
assembly; repetitive detailed
inspections for discrepancies (e.g.,
hydraulic fluid coking, heat
discoloration, cracks, and etching or
pitting) of the interior of the strut
disconnect assembly, if certain
conditions are found; repetitive detailed
inspections of the exterior of the strut
disconnect assembly for cracks; and
corrective action, if certain conditions
are found. The corrective action is
replacing the titanium system
disconnect assembly with an Inconel
system disconnect assembly. If
accomplished, the replacement will
eliminate the potential for hydrogen
embrittlement and subsequent cracking,
and would eliminate the need for the
inspections of the titanium strut
disconnect assembly.
FAA’s Determination and Requirements
of This Proposed AD
We are proposing this AD because we
evaluated all relevant information and
determined the unsafe condition
described previously is likely to exist or
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Federal Register / Vol. 76, No. 13 / Thursday, January 20, 2011 / Proposed Rules
develop in other products of these same
type designs. This proposed AD would
require accomplishing the actions
specified in the service information
described previously.
Costs of Compliance
We estimate that this proposed AD
would affect 53 airplanes of U.S.
registry. We also estimate that it would
take about 48 work-hours per product to
comply with this proposed AD. The
average labor rate is $85 per work-hour.
Required parts would cost about
$122,617 per product. Based on these
figures, we estimate the cost of this
proposed AD to the U.S. operators to be
$6,714,941, or $122,697 per product.
Authority for This Rulemaking
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Regulatory Findings
We determined that this proposed AD
would not have federalism implications
under Executive Order 13132. This
proposed AD would 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 this proposed 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.
18:20 Jan 19, 2011
Jkt 223001
the compliance times specified, unless the
actions have already been done.
Unsafe Condition
(e) This AD results from reports of system
disconnect boxes that have been
contaminated with hydraulic fluid, in which
one case a crack was found. The Federal
Aviation Administration is issuing this AD to
detect and correct hydraulic fluid
contamination, which can cause cracking of
titanium parts in the system disconnect
assembly, resulting in compromise of the
engine firewall. A cracked firewall can allow
fire in the engine area to enter the strut and
can lead to an uncontained engine strut fire
if flammable fluid is present. Cracking of the
disconnect box may also reduce the
effectiveness of the fire extinguishing system
in the engine compartment and could
contribute to an uncontained engine fire. In
addition, a cracked disconnect box can leak
flammable fluids into the engine core, which
can initiate an engine fire and lead to one or
both fire conditions discussed above.
Inspections and Corrective Actions
(g) Within 12 months after the effective
date of this AD: Do a general visual
inspection for hydraulic fluid contamination
of the interior of the strut disconnect
assembly, in accordance with Part 1 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 777–54A0024, Revision 1,
dated November 4, 2010.
(1) For airplanes on which no hydraulic
fluid contamination is found (Condition 1):
Repeat the general visual inspection required
by paragraph (g) of this AD thereafter at
intervals not to exceed 6,000 flight cycles or
750 days, whichever occurs first.
(2) For airplanes on which hydraulic fluid
contamination is found (Condition 2): Before
further flight, do a detailed inspection for
discrepancies (e.g., hydraulic fluid coking,
heat discoloration, cracks, and etching or
pitting) of the interior of the strut disconnect
assembly, in accordance with Part 2 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 777–54A0024, Revision 1,
dated November 4, 2010.
(i) For airplanes on which no discrepancy
is found during the inspection required by
paragraph (g)(2) of this AD (Condition 2A):
Repeat the detailed inspection required by
paragraph (g)(2) of this AD thereafter at
intervals not to exceed 6,000 flight cycles or
750 days, whichever occurs first.
(ii) For airplanes on which hydraulic fluid
coking or heat discoloration is found but no
cracking, etching, or pitting is found during
the inspection required by paragraph (g)(2) of
this AD (Condition 2B): Do the actions
required by paragraph (g)(2)(ii)(A) and
(g)(2)(ii)(B) of this AD.
(A) Within 300 flight cycles after doing the
inspection required by paragraph (g)(2) of
this AD: Do a detailed inspection of the
exterior of the strut disconnect assembly for
cracks, in accordance with Part 3 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 777–54A0024, Revision 1,
dated November 4, 2010; and repeat the
detailed inspection thereafter at intervals not
to exceed 300 flight cycles.
(B) Within 6,000 flight cycles or 750 days
after hydraulic fluid coking and/or heat
discoloration was found during the
inspection required by paragraph (g)(2) of
this AD, whichever occurs first: Replace the
titanium system disconnect assembly with an
Inconel system, in accordance with Part 4 of
the Accomplishment Instructions of Boeing
Alert Service Bulletin 777–54A0024,
Revision 1, dated November 4, 2010.
(h) For airplanes on which any crack,
etching, or pitting is found during any
inspection required by paragraph (g)(2) or
(g)(2)(ii)(A) of this AD (Condition 3): Before
further flight, replace the titanium system
disconnect assembly with an Inconel system,
in accordance with Part 4 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 777–54A0024, Revision 1,
dated November 4, 2010.
Compliance
(f) You are responsible for having the
actions required by this AD performed within
Optional Terminating Action
(i) Replacing the titanium system
disconnect assembly with an Inconel system
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
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.
VerDate Mar<15>2010
You can find our regulatory
evaluation and the estimated costs of
compliance in the AD Docket.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
The Boeing Company: Docket No. FAA–
2011–0026; Directorate Identifier 2010–
NM–104–AD.
Comments Due Date
(a) We must receive comments by March 7,
2011.
Affected ADs
(b) None.
Applicability
(c) This AD applies to The Boeing
Company Model 777–200 and –300 series
airplanes, certificated in any category;
equipped with Pratt and Whitney engines; as
identified in Boeing Alert Service Bulletin
777–54A0024, Revision 1, dated November 4,
2010.
Subject
(d) Air Transport Association (ATA) of
America Code 54: Nacelles/Pylons.
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Federal Register / Vol. 76, No. 13 / Thursday, January 20, 2011 / Proposed Rules
disconnect assembly in accordance with Part
4 of the Accomplishment Instructions of
Boeing Alert Service Bulletin 777–54A0024,
Revision 1, dated November 4, 2010,
terminates the actions required by this AD.
Credit for Actions Accomplished in
Accordance With Previous Service
Information
(j) Actions accomplished before the
effective date of this AD according to Boeing
Alert Service Bulletin 777–54A0024, dated
April 1, 2010, are considered acceptable for
compliance with the corresponding actions
specified in this AD.
Alternative Methods of Compliance
(AMOCs)
(k)(1) The Manager, Seattle Aircraft
Certification Office (ACO), FAA, has the
authority to approve AMOCs for this AD, if
requested using the procedures found in 14
CFR 39.19. Send information to ATTN: Kevin
Nguyen, Propulsion Branch, ANM–140S,
FAA, Seattle Aircraft Certification Office
(ACO), 1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone (425)
917–6501; fax (425) 917–6590. Information
may be e-mailed to: 9–ANM–Seattle-ACO–
AMOC–Requests@faa.gov.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
Issued in Renton, Washington, on January
12, 2011.
Jeffrey E. Duven,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2011–1119 Filed 1–19–11; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 71
[Docket No. FAA–2010–1209; Airspace
Docket No. 10–ANM–10]
Proposed Amendment of Class E
Airspace; West Yellowstone, MT
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
This action proposes to
modify Class E airspace at Yellowstone
Airport, West Yellowstone, MT, to
accommodate aircraft using the
Instrument Landing System (ILS)
Localizer (LOC) standard instrument
approach procedures at Yellowstone
Airport, West Yellowstone, MT. The
FAA is proposing this action to enhance
the safety and management of aircraft
operations at Yellowstone Airport.
DATES: Comments must be received on
or before March 7, 2011.
emcdonald on DSK2BSOYB1PROD with PROPOSALS
SUMMARY:
VerDate Mar<15>2010
18:20 Jan 19, 2011
Jkt 223001
Send comments on this
proposal to the U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590; telephone (202)
366–9826. You must identify FAA
Docket No. FAA–2010–1209; Airspace
Docket No. 10–ANM–10, at the
beginning of your comments. You may
also submit comments through the
Internet at https://www.regulations.gov.
ADDRESSES:
FOR FURTHER INFORMATION CONTACT:
Eldon Taylor, Federal Aviation
Administration, Operations Support
Group, Western Service Center, 1601
Lind Avenue, SW., Renton, WA 98057;
telephone (425) 203–4537.
SUPPLEMENTARY INFORMATION:
Comments Invited
Interested parties are invited to
participate in this proposed rulemaking
by submitting such written data, views,
or arguments, as they may desire.
Comments that provide the factual basis
supporting the views and suggestions
presented are particularly helpful in
developing reasoned regulatory
decisions on the proposal. Comments
are specifically invited on the overall
regulatory, aeronautical, economic,
environmental, and energy-related
aspects of the proposal.
Communications should identify both
docket numbers (FAA Docket No. FAA
2010–1209 and Airspace Docket No. 10–
ANM–10) and be submitted in triplicate
to the Docket Management System (see
ADDRESSES section for address and
phone number). You may also submit
comments through the Internet at
https://www.regulations.gov.
Commenters wishing the FAA to
acknowledge receipt of their comments
on this action must submit with those
comments a self-addressed stamped
postcard on which the following
statement is made: ‘‘Comments to FAA
Docket No. FAA–2010–1209 and
Airspace Docket No. 10–ANM–10’’. The
postcard will be date/time stamped and
returned to the commenter.
All communications received on or
before the specified closing date for
comments will be considered before
taking action on the proposed rule. The
proposal contained in this action may
be changed in light of comments
received. All comments submitted will
be available for examination in the
public docket both before and after the
closing date for comments. A report
summarizing each substantive public
contact with FAA personnel concerned
with this rulemaking will be filed in the
docket.
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3569
Availability of NPRMs
An electronic copy of this document
may be downloaded through the
Internet at https://www.regulations.gov.
Recently published rulemaking
documents can also be accessed through
the FAA’s web page at https://
www.faa.gov/airports_airtraffic/
air_traffic/publications/
airspace_amendments/.
You may review the public docket
containing the proposal, any comments
received, and any final disposition in
person in the Dockets Office (see the
ADDRESSES section for the address and
phone number) between 9 a.m. and 5
p.m., Monday through Friday, except
federal holidays. An informal docket
may also be examined during normal
business hours at the Northwest
Mountain Regional Office of the Federal
Aviation Administration, Air Traffic
Organization, Western Service Center,
Operations Support Group, 1601 Lind
Avenue, SW., Renton, WA 98057.
Persons interested in being placed on
a mailing list for future NPRMs should
contact the FAA’s Office of Rulemaking,
(202) 267–9677, for a copy of Advisory
Circular No. 11–2A, Notice of Proposed
Rulemaking Distribution System, which
describes the application procedure.
The Proposal
The FAA is proposing an amendment
to Title 14 Code of Federal Regulations
(14 CFR) Part 71 by modifying Class E
airspace extending upward from 700
feet above the surface at Yellowstone
Airport, West Yellowstone, MT, to
accommodate new ILS LOC standard
instrument approach procedures at
Yellowstone Airport, West Yellowstone,
MT. This action would enhance the
safety and management of aircraft
operations at Yellowstone Airport.
Class E airspace designations are
published in paragraph 6005, of FAA
Order 7400.9U, dated August 18, 2010,
and effective September 15, 2010, which
is incorporated by reference in 14 CFR
71.1. The Class E airspace designation
listed in this document will be
published subsequently in this Order.
The FAA has determined this
proposed regulation only involves an
established body of technical
regulations for which frequent and
routine amendments are necessary to
keep them operationally current.
Therefore, this proposed regulation; (1)
is not a ‘‘significant regulatory action’’
under Executive Order 12866; (2) is not
a ‘‘significant rule’’ under DOT
Regulatory Policies and Procedures (44
FR 11034; February 26, 1979); and (3)
does not warrant preparation of a
regulatory evaluation as the anticipated
E:\FR\FM\20JAP1.SGM
20JAP1
]]>Agencies
[Federal Register Volume 76, Number 13 (Thursday, January 20, 2011)]
[Proposed Rules]
[Pages 3566-3569]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-1119]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2011-0026; Directorate Identifier 2010-NM-104-AD]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Model 777-200 and -
300 Series Airplanes Equipped With Pratt and Whitney Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: We propose to adopt a new airworthiness directive (AD) for
certain Model 777-200 and -300 series airplanes. This proposed AD would
require repetitive inspections for
[[Page 3567]]
hydraulic fluid contamination of the interior of the strut disconnect
assembly; repetitive inspections for discrepancies of the interior of
the strut disconnect assembly, if necessary; repetitive inspections of
the exterior of the strut disconnect assembly for cracks, if necessary;
and corrective action if necessary. This proposed AD also provides an
optional terminating action for the inspections. This proposed AD
results from reports of system disconnect boxes that have been
contaminated with hydraulic fluid and, in one incident, led to
subsequent cracking of titanium parts in the system disconnect
assembly. We are proposing this AD to detect and correct hydraulic
fluid contamination, which can cause cracking of titanium parts in the
system disconnect assembly, resulting in compromise of the engine
firewall. A cracked firewall can allow fire in the engine area to enter
the strut and can lead to an uncontained engine strut fire if flammable
fluid is present. Cracking of the disconnect box may also reduce the
effectiveness of the fire extinguishing system in the engine
compartment and could contribute to an uncontained engine fire. In
addition, a cracked disconnect box can leak flammable fluids into the
engine core, which can initiate an engine fire, and lead to one or both
fire conditions discussed above.
DATES: We must receive comments on this proposed AD by March 7, 2011.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
For service information identified in this proposed AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone 206-
544-5000, extension 1; fax 206-766-5680; e-mail me.boecom@boeing.com;
Internet https://www.myboeingfleet.com. You may review copies of the
referenced service information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information
on the availability of this material at the FAA, call 425-227-1221.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov; or in person at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this proposed AD, the regulatory
evaluation, any comments received, and other information. The street
address for the Docket Office (telephone 800-647-5527) is in the
ADDRESSES section. Comments will be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT: Kevin Nguyen, Propulsion Branch, ANM-
140S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind
Avenue, SW., Renton, Washington 98057-3356; telephone (425) 917-6501;
fax (425) 917-6590.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2011-0026;
Directorate Identifier 2010-NM-104-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD because of those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
We have received reports of system disconnect boxes that have been
contaminated with hydraulic fluid. One operator has found cracks in the
system disconnect assembly bulkheads and lower skin panel. Subsequent
analysis at Boeing found hydrogen enbrittlement of the system
disconnect assembly bulkheads and lower skin panel. The system
disconnect assembly is made from titanium and is located near the hot
engine core of the engine where temperatures can exceed 270 degrees
Fahrenheit. The presence of hydraulic fluid and temperature above 270
degrees Fahrenheit can result in hydrogen embrittlement of the titanium
system disconnect assembly. Hydrogen embrittlement combined with a high
sonic vibration environment can result in cracking of the system
disconnect assembly. The system disconnect assembly is a box where
hydraulic, fuel, and electrical connections are made between the engine
and the strut. This box acts as a firewall between the engine
compartment and the strut. The engine compartment has a fire
extinguishing system while the strut does not. The strut is considered
a flammable leakage zone where flammable fluids may be present. These
fluids are subsequently drained from the strut and system disconnect
box. A cracked firewall can allow fire in the engine area to enter the
strut and can lead to an uncontained engine strut fire if flammable
fluid is present. Cracking of the disconnect box may also reduce the
effectiveness of the fire extinguishing system in the engine
compartment and could contribute to an uncontained engine fire. In
addition, a cracked disconnect box can leak flammable fluids into the
engine core, which can initiate an engine fire, and lead to one or both
fire conditions discussed above.
Relevant Service Information
We have reviewed Boeing Alert Service Bulletin 777-54A0024,
Revision 1, dated November 4, 2010. This service bulletin describes
procedures for doing repetitive general visual inspections for
hydraulic fluid contamination of the interior of the strut disconnect
assembly; repetitive detailed inspections for discrepancies (e.g.,
hydraulic fluid coking, heat discoloration, cracks, and etching or
pitting) of the interior of the strut disconnect assembly, if certain
conditions are found; repetitive detailed inspections of the exterior
of the strut disconnect assembly for cracks; and corrective action, if
certain conditions are found. The corrective action is replacing the
titanium system disconnect assembly with an Inconel system disconnect
assembly. If accomplished, the replacement will eliminate the potential
for hydrogen embrittlement and subsequent cracking, and would eliminate
the need for the inspections of the titanium strut disconnect assembly.
FAA's Determination and Requirements of This Proposed AD
We are proposing this AD because we evaluated all relevant
information and determined the unsafe condition described previously is
likely to exist or
[[Page 3568]]
develop in other products of these same type designs. This proposed AD
would require accomplishing the actions specified in the service
information described previously.
Costs of Compliance
We estimate that this proposed AD would affect 53 airplanes of U.S.
registry. We also estimate that it would take about 48 work-hours per
product to comply with this proposed AD. The average labor rate is $85
per work-hour. Required parts would cost about $122,617 per product.
Based on these figures, we estimate the cost of this proposed AD to the
U.S. operators to be $6,714,941, or $122,697 per product.
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 determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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 this proposed
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.
You can find our regulatory evaluation and the estimated costs of
compliance in the AD Docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. The FAA amends Sec. 39.13 by adding the following new AD:
The Boeing Company: Docket No. FAA-2011-0026; Directorate Identifier
2010-NM-104-AD.
Comments Due Date
(a) We must receive comments by March 7, 2011.
Affected ADs
(b) None.
Applicability
(c) This AD applies to The Boeing Company Model 777-200 and -300
series airplanes, certificated in any category; equipped with Pratt
and Whitney engines; as identified in Boeing Alert Service Bulletin
777-54A0024, Revision 1, dated November 4, 2010.
Subject
(d) Air Transport Association (ATA) of America Code 54:
Nacelles/Pylons.
Unsafe Condition
(e) This AD results from reports of system disconnect boxes that
have been contaminated with hydraulic fluid, in which one case a
crack was found. The Federal Aviation Administration is issuing this
AD to detect and correct hydraulic fluid contamination, which can
cause cracking of titanium parts in the system disconnect assembly,
resulting in compromise of the engine firewall. A cracked firewall
can allow fire in the engine area to enter the strut and can lead to
an uncontained engine strut fire if flammable fluid is present.
Cracking of the disconnect box may also reduce the effectiveness of
the fire extinguishing system in the engine compartment and could
contribute to an uncontained engine fire. In addition, a cracked
disconnect box can leak flammable fluids into the engine core, which
can initiate an engine fire and lead to one or both fire conditions
discussed above.
Compliance
(f) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Inspections and Corrective Actions
(g) Within 12 months after the effective date of this AD: Do a
general visual inspection for hydraulic fluid contamination of the
interior of the strut disconnect assembly, in accordance with Part 1
of the Accomplishment Instructions of Boeing Alert Service Bulletin
777-54A0024, Revision 1, dated November 4, 2010.
(1) For airplanes on which no hydraulic fluid contamination is
found (Condition 1): Repeat the general visual inspection required
by paragraph (g) of this AD thereafter at intervals not to exceed
6,000 flight cycles or 750 days, whichever occurs first.
(2) For airplanes on which hydraulic fluid contamination is
found (Condition 2): Before further flight, do a detailed inspection
for discrepancies (e.g., hydraulic fluid coking, heat discoloration,
cracks, and etching or pitting) of the interior of the strut
disconnect assembly, in accordance with Part 2 of the Accomplishment
Instructions of Boeing Alert Service Bulletin 777-54A0024, Revision
1, dated November 4, 2010.
(i) For airplanes on which no discrepancy is found during the
inspection required by paragraph (g)(2) of this AD (Condition 2A):
Repeat the detailed inspection required by paragraph (g)(2) of this
AD thereafter at intervals not to exceed 6,000 flight cycles or 750
days, whichever occurs first.
(ii) For airplanes on which hydraulic fluid coking or heat
discoloration is found but no cracking, etching, or pitting is found
during the inspection required by paragraph (g)(2) of this AD
(Condition 2B): Do the actions required by paragraph (g)(2)(ii)(A)
and (g)(2)(ii)(B) of this AD.
(A) Within 300 flight cycles after doing the inspection required
by paragraph (g)(2) of this AD: Do a detailed inspection of the
exterior of the strut disconnect assembly for cracks, in accordance
with Part 3 of the Accomplishment Instructions of Boeing Alert
Service Bulletin 777-54A0024, Revision 1, dated November 4, 2010;
and repeat the detailed inspection thereafter at intervals not to
exceed 300 flight cycles.
(B) Within 6,000 flight cycles or 750 days after hydraulic fluid
coking and/or heat discoloration was found during the inspection
required by paragraph (g)(2) of this AD, whichever occurs first:
Replace the titanium system disconnect assembly with an Inconel
system, in accordance with Part 4 of the Accomplishment Instructions
of Boeing Alert Service Bulletin 777-54A0024, Revision 1, dated
November 4, 2010.
(h) For airplanes on which any crack, etching, or pitting is
found during any inspection required by paragraph (g)(2) or
(g)(2)(ii)(A) of this AD (Condition 3): Before further flight,
replace the titanium system disconnect assembly with an Inconel
system, in accordance with Part 4 of the Accomplishment Instructions
of Boeing Alert Service Bulletin 777-54A0024, Revision 1, dated
November 4, 2010.
Optional Terminating Action
(i) Replacing the titanium system disconnect assembly with an
Inconel system
[[Page 3569]]
disconnect assembly in accordance with Part 4 of the Accomplishment
Instructions of Boeing Alert Service Bulletin 777-54A0024, Revision
1, dated November 4, 2010, terminates the actions required by this
AD.
Credit for Actions Accomplished in Accordance With Previous Service
Information
(j) Actions accomplished before the effective date of this AD
according to Boeing Alert Service Bulletin 777-54A0024, dated April
1, 2010, are considered acceptable for compliance with the
corresponding actions specified in this AD.
Alternative Methods of Compliance (AMOCs)
(k)(1) The Manager, Seattle Aircraft Certification Office (ACO),
FAA, has the authority to approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19. Send information to
ATTN: Kevin Nguyen, Propulsion Branch, ANM-140S, FAA, Seattle
Aircraft Certification Office (ACO), 1601 Lind Avenue, SW., Renton,
Washington 98057-3356; telephone (425) 917-6501; fax (425) 917-6590.
Information may be e-mailed to: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
Issued in Renton, Washington, on January 12, 2011.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2011-1119 Filed 1-19-11; 8:45 am]
BILLING CODE 4910-13-P
