[Federal Register Volume 68, Number 231 (Tuesday, December 2, 2003)]
[Proposed Rules]
[Pages 67385-67388]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-29904]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2003-NE-48-AD]
RIN 2120-AA64


Airworthiness Directives; Hamilton Sundstrand Corporation 
(Formerly Hamilton Standard Division) Model 568F Propellers

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for certain serial numbered (SN) propeller blades installed in Hamilton 
Sundstrand Corporation (formerly Hamilton Standard Division) 568F 
propellers. This proposed AD would require replacement of propeller 
blades, part numbers (P/N's) R815505-3 and R815505-4 that have a serial 
number (SN) of FR1699 to FR20021010, with serviceable blades. This 
proposed AD is prompted by reports of these composite 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 proposing 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: We must receive any comments on this proposed AD by February 2, 
2004.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD:
    [sbull] By mail: Federal Aviation Administration (FAA), New England 
Region, Office of the Regional Counsel, Attention: Rules Docket No. 
2003-NE-48-AD, 12 New England Executive Park, Burlington, MA 01803-
5299.
    [sbull] By fax: (781) 238-7055.
    [sbull] By e-mail: [email protected].
    You can get the service information identified in this proposed 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, by appointment, at the FAA, New 
England Region, Office of the Regional Counsel, 12 New England 
Executive Park, Burlington, MA.

[[Page 67386]]


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:

Comments Invited

    We invite you to submit any written relevant data, views, or 
arguments regarding this proposal. Send your comments to an address 
listed under ADDRESSES. Include ``AD Docket No. 2003-NE-48-AD'' in the 
subject line of your comments. If you want us to acknowledge receipt of 
your mailed comments, send us a self-addressed, stamped postcard with 
the docket number written on it; we will date-stamp your postcard and 
mail it back to you. We specifically invite comments on the overall 
regulatory, economic, environmental, and energy aspects of the proposed 
AD. If a person contacts us verbally, and that contact relates to a 
substantive part of this proposed AD, we will summarize the contact and 
place the summary in the docket. We will consider all comments received 
by the closing date and may amend the proposed AD in light of those 
comments.
    We are reviewing the writing style we currently use in regulatory 
documents. We are interested in your comments on whether the style of 
this document is clear, and your suggestions to improve the clarity of 
our communications that affect you. You can get more information about 
plain language at http://www.faa.gov/language and http://www.plainlanguage.gov.

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.

Discussion

    The manufacturer has recently notified us that while investigating 
corrosion indications on some blade tulip counterweight areas of 568F 
composite propeller blades, random areas of missing adhesive under the 
compression wrap were discovered, exposing the steel tulip part of the 
blade. This missing adhesive is determined to be the result of a 
manufacturing operation designed to remove resin flashing from this 
area of the blade interface, during original manufacture. The 
manufacturer has implemented a corrective action in the manufacturing 
process for new blades, beginning with blade SN 20021011, and higher. 
Upon further investigation, the manufacturer has identified two serial 
number groups of blades that are suspect for missing adhesive. They are 
568F propeller blades, P/Ns R815505-3 and R815505-4, SNs FR1699 through 
FR2625 inclusive (877 blades), and SNs FR20010610 through FR20021010 
inclusive (713 blades).

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 products 
of this same type design. Therefore, we are proposing this AD, which 
would require replacement of propeller blades, P/Ns R815505-3 and 
R815505-4, that have a SN of FR1699 to FR20021010, with serviceable 
blades. A calendar-based schedule has been established for the removal 
of blades based on a safety evaluation of the blade population. The 
schedule takes into consideration the age of the blade, availability of 
spare blades and the repair capabilities necessary to restore removed 
blades to a serviceable condition. Since corrosion is an age-related 
process, the oldest blades are to be replaced first. In addition, the 
specialized tooling necessary to remove and replace the composite 
material on the blade during repair is only available at one repair 
facility. The calendar-based schedule provides airplane owners and 
operators with compliance dates to accommodate scheduling for blade 
removal within the safety evaluation.

Changes to 14 CFR Part 39--Effect on the Proposed AD

    On July 10, 2002, we issued a new version of 14 CFR part 39 (67 FR 
47998, July 22, 2002), which governs the FAA's AD system. This 
regulation now includes material that relates to altered products, 
special flight permits, and alternative methods of compliance. This 
material previously was included in each individual AD. Since this 
material is included in 14 CFR part 39, we will not include it in 
future AD actions.

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 proposed AD. We also estimate that it would take 
approximately 8 work hours per airplane 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 proposed AD to 
U.S. operators to be $6,240.

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. Would 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 proposal 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.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the Federal Aviation Administration 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 
airworthiness directive:

    Hamilton Sundstrand Corporation (formerly Hamilton Standard 
Division): Docket No. 2003-NE-48-AD.

Comments Due Date

    (a) The Federal Aviation Administration (FAA) must receive 
comments on this airworthiness directive (AD) action by February 2, 
2004.

Affected ADs

    (b) None.

[[Page 67387]]

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 is prompted by 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 omitted when specifying 
affected serial numbers.

               Table 1.--Propeller Blade Removal Schedule
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                                    Remove propeller blades from service
     For propeller blades SNs:           for rework, no later than:
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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.
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                Table 2.--Blade SNs Excluded From Table 1
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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
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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

    (h) The Manager, Boston Aircraft Certification Office, has the 
authority to approve alternative methods of compliance

[[Page 67388]]

for this AD if requested using the procedures found in 14 CFR 39.19.

Related Information

    (i) 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 November 24, 2003.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 03-29904 Filed 12-1-03; 8:45 am]
BILLING CODE 4910-13-P