[Federal Register: May 18, 2009 (Volume 74, Number 94)]
[Proposed Rules]
[Page 23131-23133]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr18my09-15]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-0545; Directorate Identifier 2008-NE-16-AD]
RIN 2120-AA64
Airworthiness Directives; Dowty Propellers Models R354/4-123-F/
13, R354/4-123-F/20, R375/4-123-F/21, R389/4-123-F/25, R389/4-123-F/26,
and R390/4-123-F/27 Propellers
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Supplemental notice of proposed rulemaking (NPRM); reopening of
the comment period.
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SUMMARY: This supplemental NPRM revises an earlier proposed
airworthiness directive (AD), applicable to Dowty Propellers Models
R354/4-123-F/13, R354/4-123-F/20, R375/4-123-F/21, R389/4-123-F/25,
R389/4-123-F/26, and R390/4-123-F/27 propellers. That proposed AD would
have required initial and repetitive visual inspections of propeller
blade root outer sleeves for cracks, and removal before further flight
of propeller blades with cracked blade root outer sleeves. That
proposed AD resulted from mandatory continuing airworthiness
information (MCAI) issued by the European Aviation Safety Agency (EASA)
to identify and correct an unsafe condition on certain Dowty
propellers. This supplemental NPRM revises the proposed AD to correct
the listing of propeller models affected. This supplemental NPRM
results from the discovery that we need to correct one of the propeller
model numbers affected, and to remove an erroneous propeller model
number. We are proposing this AD to prevent blade counterweight
release, which could result in injury or damage to the airplane. The
MCAI describes the unsafe condition as:
A number of propeller blade outer sleeves have been found with
cracks since 1996. Testing has shown that blade retention integrity
is not affected by this cracking. However, this condition, if not
detected and corrected, can lead to blade counterweight release,
possibly resulting in damage to the aircraft and injury to occupants
or persons on the ground.
We are proposing this AD to prevent blade counterweight release,
which could result in injury or damage to the airplane.
DATES: We must receive comments on this proposed AD by June 17, 2009.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to http://
www.regulations.gov and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility, U.S. Department of
Transportation, 1200 New Jersey Avenue, SE., West Building Ground
Floor, Room W12-140, Washington, DC 20590-0001.
Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Fax: (202) 493-2251.
Examining the AD Docket
You may examine the AD docket on the Internet at http://
www.regulations.gov; or in person at the Docket Operations office
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 Operations office (telephone (800) 647-5527) is
the same as the Mail address provided in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Terry Fahr, Aerospace Engineer, Boston
Aircraft Certification Office, FAA, Engine and Propeller Directorate,
12 New England Executive Park, Burlington, MA 01803; e-mail:
terrance.fahr@faa.gov; telephone (781) 238-7155; fax (781) 238-7170.
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-2008-0545;
Directorate Identifier 2008-NE-16-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 based on 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
with FAA personnel concerning this proposed AD. Using the search
function of the Web site, anyone can find and read the comments in any
of our dockets, including, if provided, the name of the individual who
sent the comment (or signed the comment on behalf of an association,
business, labor union, etc.). You may review the DOT's complete Privacy
Act Statement in the Federal Register published on April 11, 2000 (65
FR 19477-78).
Discussion
EASA, which is the Technical Agent for the Member States of the
European Community, has issued EASA AD 2008-0033, dated February 19,
2008, to correct an unsafe condition for the specified products. The
EASA AD states:
A number of propeller blade outer sleeves have been found with
cracks since 1996. Testing has shown that blade retention integrity
is not affected by this cracking. However, this condition, if not
detected and corrected, can lead to blade counterweight release,
possibly resulting in damage to the
[[Page 23132]]
aircraft and injury to occupants or persons on the ground.
You may obtain further information by examining the MCAI in the AD
docket.
Relevant Service Information
Dowty Propellers has issued Alert Service Bulletin No. SF340-61-
A106, Revision 1, dated March 20, 2008. The actions described in this
service information are intended to correct the unsafe condition
identified in the MCAI.
FAA's Determination and Requirements of This Proposed AD
This product has been approved by the aviation authority of the
United Kingdom, and is approved for operation in the United States.
Pursuant to our bilateral agreement with the United Kingdom, they have
notified us of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all information provided by EASA and determined the unsafe
condition exists and is likely to exist or develop on other products of
the same type design. This Supplemental NPRM requires initial and
repetitive visual inspections of propeller blade root outer sleeves for
cracks, and removal before further flight of propeller blades with
cracked blade root outer sleeves.
Comments
We gave the public the opportunity to participate in developing
this AD. We considered the comments received on the original NPRM.
Request To Reference the Latest Service Bulletin
One commenter, Colgan Air, requests that we reference the latest
service bulletin, which is Dowty Propellers Alert Service Bulletin No.
SF340-61-A106, Revision 1, dated March 20, 2008.
We agree and changed that reference in this Supplemental NPRM.
Request To Clarify Airplane Manufacturer
One commenter, SAAB AB, SAAB Aerosystems, requests that we clarify
that ``340B airplanes'' should be referred to as ``SAAB 340B
airplanes''.
We agree and clarified that reference in this Supplemental NPRM.
Need To Correct the Listing of Propeller Models Affected
We discovered the need to correct the listing of the propeller
models affected that was included in the original NPRM published in the
Federal Register on June 30, 2008 (73 FR 36819). That listing, which is
Dowty Propellers models R354/4-123-F/13, R354/4-123-F/20, R354/4-123-F/
21, R375/4-123-F/21, R389/4-123-F/25, R354/4-123-F/26, and R390/4-123-
F/27 propellers, is changed in this Supplemental NPRM to Dowty
Propellers Models R354/4-123-F/13, R354/4-123-F/20, R375/4-123-F/21,
R389/4-123-F/25, R389/4-123-F/26, and R390/4-123-F/27 propellers.
Conclusion
We reviewed the available data, including the comments received,
and determined that air safety and the public interest require making
the changes described previously. We determined that these changes will
not increase the economic burden on any operator or increase the scope
of the Supplemental NPRM.
Costs of Compliance
Based on the service information, we estimate that this proposed AD
would affect about 292 propellers installed on airplanes of U.S.
registry. We also estimate that it would take 0.5 work-hour per
propeller to visually inspect for cracks. The average labor rate is $80
per work hour. Based on these figures, we estimate the cost of the
proposed AD on U.S. operators to be $11,680.
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.
We prepared a regulatory evaluation of the estimated costs to
comply with this proposed AD and placed it 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.
Sec. 39.13 [Amended]
2. The FAA amends Sec. 39.13 by adding the following new AD:
Dowty Propellers: Docket No. FAA-2008-0545; Directorate Identifier
2008-NE-16-AD.
Comments Due Date
(a) We must receive comments by June 17, 2009.
Affected Airworthiness Directives (ADs)
(b) None.
Applicability
(c) This AD applies to Dowty Propellers Models R354/4-123-F/13,
R354/4-123-F/20, R375/4-123-F/21, R389/4-123-F/25, R389/4-123-F/26,
and R390/4-123-F/27 propellers. These propellers are installed on,
but not limited to, Saab AB, Saab Aerosystems SF340A and SAAB SF340B
airplanes.
Reason
(d) European Aviation Safety Agency (EASA) AD No. 2008-0033,
dated February 19, 2008, states:
A number of propeller blade outer sleeves have been found with
cracks since 1996. Testing has shown that blade retention integrity
is not affected by this cracking. However, this condition, if not
detected and corrected, can lead to blade counterweight release,
possibly resulting in damage to the aircraft and injury to occupants
or persons on the ground.
[[Page 23133]]
This AD requires initial and repetitive visual inspections of
propeller blade root outer sleeves for cracks, and removal before
further flight of propeller blades with cracked blade root outer
sleeves. We are issuing this AD to prevent blade counterweight
release, which could result in injury or damage to the airplane.
Actions and Compliance
(e) Unless already done, do the following actions.
Propeller Blade Root Outer Sleeve Visual Inspections
(1) At the next 1,600 flight hours (FH) aircraft check after the
effective date of this AD, or, after any blade accumulates 15,000 FH
time-in-service, whichever occurs later, visually inspect all
propeller blade root outer sleeves for cracks.
(2) Thereafter, at intervals not to exceed 1,600 FH, visually
inspect all propeller blade root outer sleeves for cracks.
(3) Before further flight, remove any propeller blades found
with cracked root outer sleeves during the visual inspections in
paragraphs (e)(1) and (e)(2) of this AD.
FAA AD Differences
(f) None.
Alternative Methods of Compliance (AMOCs)
(g) The Manager, Boston Aircraft Certification Office, FAA,
Engine and Propeller Directorate, has the authority to approve AMOCs
for this AD, if requested using the procedures found in 14 CFR
39.19.
Related Information
(h) Refer to European Aviation Safety Agency AD 2008-0033, dated
February 19, 2008, and Dowty Propellers Alert Service Bulletin No.
SF340-61-A106, Revision 1, dated March 20, 2008, for related
information.
(i) Contact Terry Fahr, Aerospace Engineer, Boston Aircraft
Certification Office, FAA, Engine and Propeller Directorate, 12 New
England Executive Park, Burlington, MA 01803; e-mail:
terry.fahr@faa.gov; telephone (781) 238-7155; fax (781) 238-7170,
for more information about this AD.
Issued in Burlington, Massachusetts, on May 8, 2009.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. E9-11478 Filed 5-15-09; 8:45 am]
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