[Federal Register: May 20, 2008 (Volume 73, Number 98)]
[Proposed Rules]
[Page 29087-29089]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr20my08-14]
[[Page 29087]]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-0561; Directorate Identifier 2007-NM-223-AD]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 757-200 and -200PF Series
Airplanes, and Model 767-200 and -300 Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for certain Boeing Model 757-200 and -200PF series airplanes; and Model
767-200 and -300 series airplanes. This proposed AD would require doing
an inspection to determine the part number and serial number of the hub
assembly of the ram air turbine (RAT), and replacing the hub assembly
of the RAT with a new, serviceable, or reworked and re-identified hub
assembly if necessary. This proposed AD results from reports indicating
that the counterweights in some hub assemblies of the RATs could be
under strength and fracture when they are extended in flight. We are
proposing this AD to prevent a fractured counterweight on the hub
assembly of the RAT, which will cause an overspeed condition, and
consequent turbine blade separation, possible injury to passengers,
possible airplane structural damage, and an inoperative RAT. An
inoperative RAT will cause the loss of hydraulic power to the primary
flight controls in cases where both engines are shut down in flight,
resulting in subsequent loss of control of the airplane.
DATES: We must receive comments on this proposed AD by July 7, 2008.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to http://
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 AD, contact Boeing
Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-2207.
Examining the AD Docket
You may examine the AD docket on the Internet at http://
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: Kenneth Frey, Aerospace Engineer,
Systems and Equipment Branch, ANM-130S, FAA, Seattle Aircraft
Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057-
3356; telephone (425) 917-6468; 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-2008-0561;
Directorate Identifier 2007-NM-223-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 http://
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 indicating that the counterweights in some
hub assemblies of the ram air turbine (RAT) could be under strength and
fracture when they are extended in flight, on certain Boeing Model 757-
200 and -200PF series airplanes and Model 767-200 and -300 series
airplanes. The cause of the fractures has been attributed to a
manufacturing process error. A fractured counterweight on the hub
assembly of the RAT, if not corrected, will cause an overspeed
condition, and consequent turbine blade separation, possible injury to
passengers, possible airplane structural damage, and an inoperative
RAT. An inoperative RAT will cause the loss of hydraulic power to the
primary flight controls in cases where both engines are shut down in
flight, resulting in subsequent loss of control of the airplane.
Relevant Service Information
We have reviewed Boeing Alert Service Bulletin 757-29A0066, dated
January 2, 2007 (for Model 757-200 and -200PF series airplanes); and
Boeing Alert Service Bulletin 767-29A0110, dated January 2, 2007 (for
Model 767-200 and -300 series airplanes). The service bulletins
describe procedures for doing an inspection to determine the part
number and serial number on the hub assembly of the RAT, replacing the
hub assembly of the RAT with a new, serviceable, or reworked and re-
identified hub assembly if necessary, and submitting a report to the
manufacturer. Accomplishing the actions specified in the service
information is intended to adequately address the unsafe condition.
Boeing Alert Service Bulletin 757-29A0066, refers to the Hamilton
Sundstrand Service Bulletin 730814-29-12, dated November 30, 2005; and
Boeing Alert Service Bulletin 767-29A0110, refers to the Hamilton
Sundstrand Service Bulletin 729548-29-15, dated November 30, 2005; as
additional sources of service information for accomplishing the
inspection and replacement of the hub assembly of the RAT.
FAA's Determination and Requirements of the Proposed AD
We have evaluated all pertinent information and identified an
unsafe condition that is likely to exist or develop on other airplanes
of this same type design. For this reason, we are proposing this AD,
which would require accomplishing the actions specified in the Boeing
service information described previously, except as discussed under
``Difference between the Proposed Rule and Referenced Service
Bulletin.''
Difference Between Proposed Rule and Referenced Service Bulletin
Operators should note that, although the Accomplishment
Instructions of the referenced Boeing service bulletins describe
procedures for submitting a feedback form related to the service
bulletins, this proposed AD would not require those actions.
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Costs of Compliance
There are about 60 airplanes of the affected design in the
worldwide fleet. This proposed AD would affect about 43 airplanes of
U.S. registry. The proposed inspection would take about 1 work hour per
airplane, at an average labor rate of $80 per work hour. Based on these
figures, the estimated cost of the proposed AD for U.S. operators is
$3,440, or $80 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 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 that the 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.
We prepared a regulatory evaluation of the estimated costs to
comply with this proposed 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, 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 Federal Aviation Administration (FAA) amends Sec. 39.13 by
adding the following new airworthiness directive (AD):
Boeing: Docket No. FAA-2008-0561; Directorate Identifier 2007-NM-
223-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by July 7,
2008.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Boeing airplanes identified in Table 1 of
this AD, certified in any category.
Table 1.--Applicability
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For model-- As identified in--
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(1) 757-200 and -200PF series airplanes Boeing Alert Service Bulletin
757-29A0066, dated January 2,
2007.
(2) 767-200 and -300 series airplanes.. Boeing Alert Service Bulletin
767-29A0110, dated January 2,
2007.
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Unsafe Condition
(d) This AD results from reports indicating that the
counterweights in some hub assemblies of the ram air turbines (RAT)
could be under strength and fracture when they are extended in
flight. We are issuing this AD to prevent a fractured counterweight
on the hub assembly of the RAT, which will cause an overspeed
condition, and consequent turbine blade separation, possible injury
to passengers, possible airplane structural damage, and an
inoperative RAT. An inoperative RAT will cause the loss of hydraulic
power to the primary flight controls in cases where both engines are
shut down in flight, resulting in 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.
Inspection and Replacement
(f) Within 24 months after the effective date of this AD, do an
inspection to determine the part number and serial number on the hub
assembly of the RAT in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin 757-29A0066, dated
January 2, 2007 (for Model 757-200 and -200PF series airplanes); or
Boeing Alert Service Bulletin 767-29A0110, dated January 2, 2007
(for Model 767-200 and -300 series airplanes); as applicable. If the
part number and serial number on the hub assembly of the RAT are
listed in Table 2 of this AD, within 24 months after the effective
date of this AD, replace the hub assembly of the RAT with a new,
serviceable, or reworked and re-identified hub assembly, in
accordance with the Accomplishment Instructions of the service
bulletin.
Parts Installation
(g) As of the effective date of this AD, no person may install a
hub assembly of the RAT having any applicable part number and serial
number listed in Table 2 of this AD, on any airplane, unless it has
been reworked and re-identified in accordance with paragraph (f) of
this AD.
Table 2.--RAT Hub Assembly Part Numbers
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For model-- Part No.-- Serial No.--
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(1) 757-200 and -200PF series 733785A or 733785B 0410 through 0413
airplanes. inclusive, 0415,
0417 through
0430, 0432, or
0434.
(2) 767-200 and -300 series 734350A, 734350B, 0666, 0673 through
airplanes. 734350C, or 0684 inclusive,
734350D. 0686, 0687, or
0689.
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No Information Submission
(h) Although Boeing Alert Service Bulletin 757-29A0066, dated
January 2, 2007 (for Model 757-200 and -200PF series airplanes); and
Boeing Alert Service Bulletin 767-29A0110, dated January 2, 2007
(for Model 767-200 and -300 series airplanes); specify to submit
information to the manufacturer, this AD does not include that
requirement.
Alternative Methods of Compliance (AMOCs)
(i)(1) 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.
(2) To request a different method of compliance or a different
compliance time for this AD, follow the procedures in 14 CFR 39.19.
Before using any approved AMOC on any airplane to which the AMOC
applies, notify your appropriate principal inspector (PI) in the FAA
Flight Standards District Office (FSDO), or lacking a PI, your local
FSDO.
Issued in Renton, Washington, on May 7, 2008.
Michael J. Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E8-11286 Filed 5-19-08; 8:45 am]
BILLING CODE 4910-13-P