[Federal Register: June 14, 2004 (Volume 69, Number 113)]
[Rules and Regulations]
[Page 32855-32857]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr14jn04-6]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2003-NE-48-AD; Amendment 39-13669; AD 2004-12-10]
RIN 2120-AA64
Airworthiness Directives; Hamilton Sundstrand Corporation
(Formerly Hamilton Standard Division) Model 568F Propellers
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain serial-numbered propeller blades installed in Hamilton
Sundstrand Corporation (formerly Hamilton Standard Division) 568F
propellers. This AD requires replacement of propeller blades, part
numbers (P/Ns) R815505-3 and R815505-4 that have a serial number (SN)
of FR1699 to FR20021010, with serviceable blades. This AD results from
reports of these composite propeller blades found at inspection, with
random areas of
[[Page 32856]]
missing adhesive under the compression wrap, which exposed the steel
tulip part of the blade. We are issuing this AD to prevent propeller
blade failure due to corrosion-induced fatigue, which could result in
blade separation and possible loss of airplane control.
DATES: This AD becomes effective July 19, 2004.
ADDRESSES: You can get the service information identified in this AD
from Hamilton Sundstrand, A United Technologies Company, Publications
Manager, Mail Stop 2AM-EE50, One Hamilton Road, Windsor Locks, CT
06096.
You may examine the AD docket, at the FAA, New England Region,
Office of the Regional Counsel, 12 New England Executive Park,
Burlington, MA.
FOR FURTHER INFORMATION CONTACT: Frank Walsh, Aerospace Engineer,
Boston Aircraft Certification Office, FAA, Engine and Propeller
Directorate, 12 New England Executive Park, Burlington, MA 01803-5299;
telephone (781) 238-7158; fax (781) 238-7170.
SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR Part 39
with a proposed airworthiness directive (AD). The proposed AD applies
to certain serial-numbered propeller blades installed in Hamilton
Sundstrand Corporation (formerly Hamilton Standard Division) 568F
propellers. We published the proposed AD in the Federal Register on
December 2, 2003 (68 FR 67385). That action proposed to require
replacement of propeller blades, P/Ns R815505-3 and R815505-4 that have
a SN of FR1699 to FR20021010, with serviceable blades.
Examining the AD Docket
You may examine the AD Docket (including any comments and service
information), by appointment, between 8 a.m. and 4:30 p.m. Monday
through Friday, except Federal holidays. See ADDRESSES for the
location.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comment received.
One commenter requests that the Cost of Compliance statement be
clarified to indicate that the blade removal cost is for AD compliance
only. The commenter has concerns regarding potential liabilities for
the worldwide fleet if the AD does not distinguish between the removals
for normally scheduled maintenance and unscheduled removals for AD
compliance.
The FAA agrees in part. We have clarified the Cost of Compliance
statement in the AD to reflect removals for this AD. We do not agree
with including worldwide costs in this AD because worldwide costs are
not within the scope of the FAA authority.
Conclusion
We have carefully reviewed the available data, including the
comment received, and determined that air safety and the public
interest require adopting the AD with the changes described previously.
We have determined that these changes will neither increase the
economic burden on any operator nor increase the scope of the AD.
Costs of Compliance
We estimate that 24 Hamilton Sundstrand Corporation 568F propellers
with suspect blades installed on airplanes of U.S. registry would be
affected by this AD. We estimate it will take about 4 work hours per
propeller to remove and replace suspect blades, and that the average
labor rate is $65 per work hour. Based on these figures, we estimate
the total labor cost of the AD to U.S. operators to be $6,240.
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 summary of the costs to comply with this AD and
placed it in the AD Docket. You may get a copy of this summary by
sending a request to us at the address listed under ADDRESSES. Include
``AD Docket No. 2003-NE-48-AD'' in your request.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the Federal Aviation Administration 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 FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
2004-12-10 Hamilton Sundstrand Corporation (formerly Hamilton
Standard Division): Amendment 39-13669. Docket No. 2003-NE-48-AD.
Effective Date
(a) This AD becomes effective July 19, 2004.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Hamilton Sundstrand Corporation (formerly
Hamilton Standard Division) 568F propellers with propeller blades,
part numbers (P/Ns) R815505-3 and R815505-4, serial numbers (SNs)
FR1699 through FR2625 inclusive (877 blades), and SNs FR20010610
through FR20021010 inclusive (713 blades), installed. These
composite propeller blades are installed on, but not limited to,
Aerospatiale ATR42-400, ATR42-500, ATR72-212, and ATR72-500
airplanes.
Unsafe Condition
(d) This AD results from reports of propeller blades found at
inspection, with random areas of missing adhesive under the
compression wrap, which exposed the steel tulip part of the blade.
We are issuing this AD to prevent propeller blade failure due to
corrosion-induced fatigue, which could result in blade separation
and possible loss of airplane control.
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.
Removal From Service of Affected Propeller Blades
(f) Remove propeller blades, P/Ns R815505-3 and R815505-4 from
service as follows:
(1) Blades listed by SN in the following Table 1 of this AD must
be removed no later than the date listed in Table 1 of this AD. See
Table 2 of this AD for blade SNs that are excluded from the
compliance times specified in Table 1 of this AD.
(2) Remove the blades that are listed by SN in Table 2 of this
AD no later than December 31, 2007.
(3) In some instances, an ``RT'' reference immediately follows
the numeric portion of the serial number on the blade. For purposes
of this AD, the ``RT'' reference has been
[[Page 32857]]
omitted when specifying affected serial numbers.
Table 1.--Propeller Blade Removal Schedule
------------------------------------------------------------------------
Remove propeller blades from
For propeller blades SNs: service for rework, no later
than:
------------------------------------------------------------------------
FR1699 through FR1765..................... December 31, 2003.
FR1766 through FR1776..................... March 31, 2004.
FR1777 through FR1855..................... June 30, 2004.
FR1856 through FR1956..................... September 30, 2004.
FR1957 through FR2132..................... December 31, 2004.
FR2133 through FR2230..................... March 31, 2005.
FR2231 through FR2315..................... June 30, 2005.
FR2316 through FR2390..................... September 30, 2005.
FR2391 through FR2433..................... December 31, 2005.
FR2434 through FR2553..................... March 31, 2006.
FR2554 through FR2625..................... June 30, 2006.
FR20010610 through FR20010729............. June 30, 2006
FR20010730 through FR20011018............. September 30, 2006.
FR20011019 through FR20011218............. December 31, 2006.
FR20011219 through FR20020511............. March 31, 2007.
FR20020512 through FR20020757............. June 30, 2007.
FR20020758 through FR20020842............. September 30, 2007.
FR20020843 through FR20021010............. December 31, 2007.
------------------------------------------------------------------------
Table 2.--Blade SNs Excluded From Table 1
----------------------------------------------------------------------------------------------------------------
----------------------------------------------------------------------------------------------------------------
FR1720 FR1887 FR1962 FR2163
FR1740 FR1888 FR1963 FR2164
FR1742 FR1889 FR2013 FR2165
FR1752 FR1892 FR2022 FR2166
FR1777 FR1893 FR2032 FR2167
FR1791 FR1927 FR2037 FR2168
FR1796 FR1928 FR2038 FR2173
FR1841 FR1929 FR2039 FR2177
FR1843 FR1930 FR2047 FR2179
FR1858 FR1931 FR2058 FR2180
FR1860 FR1932 FR2059 FR2183
FR1865 FR1933 FR2060 FR2204
FR1869 FR1934 FR2063 FR2205
FR1871 FR1935 FR2064 FR2206
FR1872 FR1936 FR2067 FR2207
FR1873 FR1937 FR2068 FR2208
FR1874 FR1938 FR2099 FR2233
FR1875 FR1942 FR2108 FR2234
FR1877 FR1943 FR2134 FR2467
FR1878 FR1957 FR2135 FR20010626
FR1879 FR1960 FR2136 FR20010936
FR1880 FR1961 FR2137 FR20011218
----------------------------------------------------------------------------------------------------------------
Installation of Propeller Blades that have a SN Listed in Table 1 or
Table 2 of this AD
(g) After the effective date of this AD, do not install any
blade that has P/N R815505-3 or R815505-4 and SN listed in Table 1
or Table 2 of this AD, and that has exceeded the date for
replacement.
Alternative Methods of Compliance (AMOCs)
(h) The Manager, Boston 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.
Material Incorporated by Reference
(i) None.
Related Information
(j) Hamilton Sundstrand Service Bulletin No. 568F-61-A45,
Revision 1, dated October 7, 2003, provides information to rework
and remark the affected blades for return to service.
Issued in Burlington, Massachusetts, on June 1, 2004.
Francis A. Favara,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 04-13145 Filed 6-10-04; 8:45 am]
BILLING CODE 4910-13-P