[Federal Register Volume 71, Number 92 (Friday, May 12, 2006)]
[Rules and Regulations]
[Pages 27600-27602]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 06-4390]



[[Page 27600]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-24517; Directorate Identifier 2006-NE-18-AD; 
Amendment 39-14591; AD 2006-10-07]
RIN 2120-AA64


Airworthiness Directives; Hamilton Sundstrand Model 14RF-9 
Propellers

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule; request for comments.

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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
Hamilton Sundstrand model 14RF-9 propellers. This AD requires visual, 
feeler gage, and tap test inspections of certain serial number (SN) 
propeller blades of the ``+E'' repair configuration for blade 
delamination, and removing the blade from service if the blade fails 
inspection. This AD also requires removing those serial-numbered 
propeller blades from service by March 1, 2007. This AD results from 
reports of delaminated blade fiberglass repair patches that allowed 
corrosion to form on the aluminum blade spar under the patch. We are 
issuing this AD to prevent blade failure that could result in 
separation of a propeller blade and loss of control of the airplane.

DATES: This AD becomes effective May 22, 2006. The Director of the 
Federal Register approved the incorporation by reference of certain 
publications listed in the regulations as of May 22, 2006.
    We must receive any comments on this AD by July 11, 2006.

ADDRESSES: Use one of the following addresses to comment on this AD:
     DOT Docket Web site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility; U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, 
Washington, DC 20590-0001.
     Fax: (202) 493-2251.
     Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For the service information identified in this AD, contact the 
Hamilton Sundstrand Propeller Technical Team, One Hamilton Road, Mail 
Stop 1-3-AB43, Windsor Locks, CT 06096-1010; fax 1-860-654-5107.

FOR FURTHER INFORMATION CONTACT: Frank Walsh, Aerospace Engineer, 
Boston Aircraft Certification Office, FAA, Engine & Propeller 
Directorate, 12 New England Executive Park, Burlington, MA 01803; 
telephone (781) 238-7158; fax (781) 238-7170.

SUPPLEMENTARY INFORMATION: In March 2006, we became aware of reports of 
263 Hamilton Sundstrand model 14RF-9 ``+E'' repair configuration 
propeller blades with delaminated blade fiberglass repair patches. The 
delamination allows corrosion to form on the aluminum blade spar under 
the patch. The repairs were done using Hamilton Sundstrand Alert 
Service Bulletin (ASB) No. 14RF-9-61-A92 and marked with the ``+E'' 
repair configuration. The repairs done using Hamilton Sundstrand ASB 
No. 14RF-9-61-A92 were limited to blades with SNs below SN 885751. 
Blades of the ``+E'' repair configuration with SNs below 885751, are 
susceptible to delamination and corrosion.
    Hamilton Sundstrand issued the following ASBs:
     ASB No. 14RF-9-61-A143, dated November 21, 2005.
     ASB No. 14RF-9-61-A143, Revision 1, dated December 5, 
2005.
     ASB No. 14RF-9-61-A144, dated February 27, 2006.
     ASB No. 14RF-9-61-A145, dated April 13, 2006.
     ASB No. 14RF-9-61-A146, dated April 3, 2006.
    Those ASBs define the affected blade population, describe 
procedures for inspecting the blades, and define requirements for 
removing the blade. Hamilton Sundstrand recently reported to us that 
not all operators have complied with the accomplishment instructions in 
the first three listed ASBs. Based on a continuing operational safety 
assessment, Hamilton Sundstrand determined that two visual, feeler 
gage, and tap test inspections must be performed on the affected 
blades. The affected blades that pass the two visual, feeler gage, and 
tap test inspections may remain in service until March 1, 2007.
    Also, Hamilton Sundstrand issued ASB No. 14RF-9-61-A 147, dated 
April 19, 2006, to introduce a blade repair upgrade to a ``+E2'' repair 
configuration for return to service. The ``+E2'' repair configuration 
is not affected by this AD.
    Continued operation with a delaminated blade and corrosion on the 
aluminum blade spar can lead to blade fracture. This condition, if not 
corrected, could result in blade failure that could result in 
separation of a propeller blade and loss of control of the airplane.

Relevant Service Information

    We have reviewed and approved the technical contents of Hamilton 
Sundstrand ASB No. 14RF-9-61-A145, dated April 13, 2006. That ASB 
defines the affected blade population, describes procedures for 
inspecting blades for delamination, and defines blade removal 
requirements.
    We have also reviewed and approved ASB No. 14RF-9-61-A146, dated 
April 3, 2006. That ASB describes procedures for inspecting blades for 
delamination that were not in service during the initial compliance 
period of ASBs No. 14RF-9-61-A143, dated November 21, 2005, and ASB No. 
14RF-9-61-A143, Revision 1, dated December 5, 2005.
    We have also reviewed and approved the technical contents of 
Hamilton Sundstrand ASB No. 14RF-9-61-A147, dated April 19, 2006. That 
ASB defines procedures for removing the ``+E'' repair configuration 
blades having SNs below 885751, by March 1, 2007, and references a 
procedure for upgrading the blades to the ``+E2'' repair configuration.

FAA's Determination and Requirements of this AD

    The unsafe condition described previously is likely to exist or 
develop on other Hamilton Sundstrand model 14RF-9 propellers with 
``+E'' repair configuration propeller blades. For that reason, we are 
issuing this AD to prevent blade failure that could result in 
separation of a propeller blade and loss of control of the airplane. 
This AD requires inspections of propeller blades of the ``+E'' repair 
configuration having SNs below 885751, for blade delamination within 10 
flight cycles or 5 days after the effective date of this AD. This AD 
also requires removal from service if the blade fails inspection, and 
removal from service by March 1, 2007. You must use the service 
information described previously to perform the actions required by 
this AD.

FAA's Determination of the Effective Date

    Since an unsafe condition exists that requires the immediate 
adoption of this AD, we have found that notice and opportunity for 
public comment before issuing this AD are impracticable. Good cause 
exists for making this amendment effective in less than 30 days.

[[Page 27601]]

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety and was not preceded by notice and an opportunity for public 
comment. We invite you however, to send us any written relevant data, 
views, or arguments regarding this AD. Send your comments to an address 
listed under ADDRESSES. Include ``AD Docket No. FAA-2006-24517; 
Directorate Identifier 2006-NE-18-AD'' in the subject line of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the rule that might 
suggest a need to modify it.
    We will post all comments we receive, without change, to http://dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact with FAA 
personnel concerning this AD. Using the search function of the DMS web 
site, anyone can find and read the comments in any of our dockets. This 
includes 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) or you may visit 
http://dms.dot.gov.

Examining the AD Docket

    You may examine the docket that contains the AD, any comments 
received, and any final disposition in person at the Docket Management 
Facility Docket Office between 9 a.m. and 5 p.m., Monday through 
Friday, except Federal holidays. The Docket Office (telephone (800) 
647-5227) is located on the plaza level of the Department of 
Transportation Nassif Building at the street address stated in 
ADDRESSES. Comments will be available in the AD docket shortly after 
the DMS receives them.

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 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 the 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 summary of the costs to comply with this AD and 
placed it in the AD Docket. You may get a copy of this summary at the 
address listed under ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Under the authority delegated to me by the Administrator, the Federal 
Aviation Administration amends part 39 of the Federal Aviation 
Regulations (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:

2006-10-07 Hamilton Sundstrand (formerly Hamilton Standard 
Division): Amendment 39-14591. Docket No. FAA-2006-24517; 
Directorate Identifier 2006-NE-18-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective May 22, 
2006.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Hamilton Sundstrand (formerly Hamilton 
Standard Division) model 14RF-9 propellers with propeller blades of 
the ``+E'' repair configuration (excludes ``+E2'' repair 
configuration) having serial numbers (SNs) below 885751. These 
propellers are installed on, but not limited to, Embraer 120 
airplanes.

Unsafe Condition

    (d) This AD results from reports of delaminated blade fiberglass 
repair patches that allowed corrosion to form on the aluminum blade 
spar under the patch. We are issuing this AD to prevent blade 
failure that could result in separation of a propeller blade and 
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.

Identifying the Blade Repair Configuration

    (f) The ``+E'' blade marking can be found on the blade airfoil 
or stamped on the blade shank, adjacent to the blade and pin 
assembly part number.
    (g) If the blade is stamped with ``+E2'' no further action is 
required.

Initial Inspection of Installed Blades Not Previously Inspected

    (h) For installed blades not previously inspected using Hamilton 
Sundstrand Alert Service Bulletin (ASB) No. 14RF-9-61-A143, dated 
November 21, 2005; or Revision 1, dated December 5, 2005; or ASB No. 
14RF-9-61-A144, dated February 27, 2006; or ASB No. 14RF-9-61-A145, 
dated April 13, 2006; or ASB No. 14RF-9-61-146, dated April 3, 2006, 
do the following:
    (1) Perform initial visual, feeler gage, and tap test 
inspections for delamination within 10 flight cycles or 5 days after 
the effective date of this AD, whichever occurs first.
    (2) Use paragraph 3 of the Accomplishment Instructions of 
Hamilton Sundstrand ASB No. 14RF-9-61-A145, dated April 13, 2006, to 
do the inspection.

2nd Inspection of Installed Blades

    (i) For installed blades that have not been reinspected using 
Hamilton Sundstrand ASB No. 14RF-9-61-A143, dated November 21, 2005; 
or Revision 1, dated December 5, 2005; or ASB No. 14RF-9-61-A144, 
dated February 27, 2006; or ASB No. 14RF-9-61-A145, dated April 13, 
2006; or ASB No. 14RF-9-61-A146, dated April 3, 2006, do the 
following:
    (1) Perform a 2nd inspection of installed blades for 
delamination after accumulating an additional 500 flight cycles or 
by July 1, 2006, whichever occurs first.
    (2) Use paragraph 3 of the Accomplishment Instructions of 
Hamilton Sundstrand ASB No. 14RF-9-61-A145, dated April 13, 2006, to 
do the inspection.

[[Page 27602]]

Blades Placed in Service After the Effective Date of This AD

    (j) For blades being installed after the effective date of this 
AD that were not previously inspected using Hamilton Sundstrand ASB 
No. 14RF-9-61-A143, dated November 21, 2005; or Revision 1, dated 
December 5, 2005; or ASB No. 14RF-9-61-A144, dated February 27, 
2006; or ASB No. 14RF-9-61-A145, dated April 13, 2006, do the 
following:
    (1) Before installing the blade, perform initial visual, feeler 
gage, and tap test inspections for delamination. Use paragraph 3. of 
the Accomplishment Instructions of Hamilton Sundstrand ASB No. 14RF-
9-61-A146, dated April 3, 2006, to do the inspection.
    (2) Perform a 2nd inspection for delamination at least 7 days 
after installing the blade, but no later than 60 days after the 
initial inspection. Use paragraph 3. of the Accomplishment 
Instructions of Hamilton Sundstrand ASB No. 14RF-9-61-A146, dated 
April 3, 2006, to do the inspection.

Blades That Fail Inspection

    (k) Before further flight, remove propeller blades from service 
that fail inspection.

Blade Removal From Service

    (l) By March 1, 2007, remove from service all blades of the 
``+E'' repair configuration having SNs below 885751.
    (m) After March 1, 2007, do not install any blades of the ``+E'' 
repair configuration having SNs below 885751, onto any propeller.
    (n) Hamilton Sundstrand ASB No. 14RF-9-61-A147, dated April 19, 
2006, contains information on upgrading the removed blades to the 
``+E2'' repair configuration.

Inspection Reporting Requirement

    (o) Within 10 days after each blade inspection, record the 
inspection data on a copy of the data sheet. The data sheet is on 
page 10 of ASB No. 14RF-9-61-A145, dated April 13, 2006, and ASB No. 
14RF-9-61-A146, dated April 3, 2006. Report the inspection data to 
Hamilton Sundstrand, fax (800) 654-5107, and Boston Aircraft 
Certification Office, fax (781) 238-7170. The Office of Management 
and Budget (OMB) approved the reporting requirements and assigned 
OMB control number 2120-0056.

Alternative Methods of Compliance

    (p) 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.

Related Information

    (q) Hamilton Sundstrand ASB No. 14RF-9-61--A143, dated November 
21, 2005; ASB No. 14RF-9-61-A143, Revision 1, dated December 5, 
2005; and ASB No. 14RF-9-61-A144, dated February 27, 2006, pertain 
to the subject of this AD.

Material Incorporated by Reference

    (r) You must use the Hamilton Sundstrand service information 
specified in Table 1 of this AD to perform the inspections and blade 
removals required by this AD. The Director of the Federal Register 
approved the incorporation by reference of this service information 
in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact the 
Hamilton Sundstrand Propeller Technical Team, One Hamilton Road, 
Mail Stop 1-3-AB43, Windsor Locks, CT 06096-1010, USA.; fax 1-860-
654-5107, for a copy of this service information. You may review 
copies at the Docket Management Facility; U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-
401, Washington, DC 20590-0001, on the internet at http://dms.dot.gov, or at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

                                      Table 1.--Incorporation by Reference
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     Alert service bulletin No.               Page                  Revision                    Date
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14RF-9-61-A145; Total Pages: 10....  All...................  Original.............  April 13, 2006.
14RF-9-61-A146; Total Pages: 10....  All...................  Original.............  April 3, 2006.
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    Issued in Burlington, Massachusetts, on May 5, 2006.
Thomas A. Boudraeu,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 06-4390 Filed 5-11-06; 8:45am]
BILLING CODE 4910-13-P