Airworthiness Directives; Hamilton Sundstrand Propellers Model 247F Propellers, 7833-7834 [E9-3608]

Download as PDF Federal Register / Vol. 74, No. 33 / Friday, February 20, 2009 / Proposed Rules Issued in Burlington, Massachusetts, on February 12, 2009. Francis A. Favara, Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E9–3609 Filed 2–19–09; 8:45 am] FOR FURTHER INFORMATION CONTACT: Terry Fahr, Aerospace Engineer, Boston Aircraft Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: terry.fahr@faa.gov; telephone (781) 238–7155; fax (781) 238–7170. SUPPLEMENTARY INFORMATION: BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2009–0113; Directorate Identifier 2008–NE–25–AD] RIN 2120–AA64 Airworthiness Directives; Hamilton Sundstrand Propellers Model 247F Propellers AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) for Hamilton Sundstrand Propellers model 247F propeller assemblies with certain part number (P/N) and serial number (SN) blades. This proposed AD would require removing affected propeller blades from service. This proposed AD results from reports of blades with corrosion pits in the tulip area of the blades. We are proposing this AD to prevent cracks from developing in the tulip area of the blade, which could result in separation of the blade and possible loss of airplane control. DATES: We must receive any comments on this proposed AD by April 21, 2009. ADDRESSES: Use one of the following addresses to comment on this proposed AD. • Federal eRulemaking Portal: Go to https://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. You can get the service information identified in this proposed AD from Hamilton Sundstrand Propeller Technical Team, One Hamilton Road, Mail Stop 1–3–AB43, Windsor Locks, CT 06096–1010; fax (860) 654–5107. VerDate Nov<24>2008 17:28 Feb 19, 2009 Jkt 217001 7833 R817370–1, could result in corrosion pits developing in the tulip area of the propeller blade. This condition, if not corrected, could cause cracks in the tulip area, which could result in separation of the propeller blade and possible loss of airplane control. Comments Invited We invite you to send us any written relevant data, views, or arguments regarding this proposal. Send your comments to an address listed under ADDRESSES. Include ‘‘Docket No. FAA– 2009–0113; Directorate Identifier 2008– NE–25–AD’’ in the subject line of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date and may amend the proposed AD in light of those comments. We will post all comments we receive, without change, to https:// 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). We have reviewed and approved the technical contents of Hamilton Sundstrand Service Bulletin 247F–61– 54, Revision 1, dated January 12, 2004, that describes procedures for reworking and re-marking the blade with a new P/N. Examining the AD Docket You may examine the AD docket on the Internet at https:// 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. Discussion We have received reports of corrosion on 6 propeller blades. A lack of adhesive and primer beyond the end of the compression wrap during manufacturing of certain serialnumbered propeller blades, P/N PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 Relevant Service Information 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. We are proposing this AD, which would require removing propeller blades, P/N R817370–1, with a SN listed in this proposed AD, within 30 days after the effective date of this proposed AD. Costs of Compliance We estimate that this proposed AD would affect 25 propellers installed on airplanes of U.S. registry. We also estimate that it would take about 128 work-hours per propeller to perform the proposed actions, and that the average labor rate is $80 per work-hour. Required parts would cost about $50 per propeller. Based on these figures, we estimate the total cost of the proposed AD to U.S. operators to be $257,250. 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. E:\FR\FM\20FEP1.SGM 20FEP1 7834 Federal Register / Vol. 74, No. 33 / Friday, February 20, 2009 / Proposed Rules 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 AD: 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 regulatory evaluation of the estimated costs to comply with this proposed AD. You may get a copy of this summary at the address listed under ADDRESSES. installed. These propellers are installed on, but not limited to, ATR–GIE Avions de Transport Regional ATR72–210 and ATR72– 210E airplanes. ACTION: Supplemental notice of proposed rulemaking (NPRM); reopening of comment period. Unsafe Condition (d) This AD results from reports of blades with corrosion pits in the tulip area of the blades. We are issuing this AD to prevent cracks from developing in the tulip area of the blade, which could result in separation of the blade and possible loss of airplane control. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. Related Information (h) Contact Terry Fahr, Aerospace Engineer, Boston Aircraft Certification Office, FAA, Engine 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. (i) Hamilton Sundstrand Service Bulletin 247F–61–54, Revision 1, dated January 12, 2004, pertains to the subject of this AD. Contact Hamilton Sundstrand Propeller Technical Team, One Hamilton Road, Mail Stop 1–3–AB43, Windsor Locks, CT 06096– 1010; fax (860) 654–5107, for a copy of this service information. SUMMARY: We are revising an earlier proposed airworthiness directive (AD) for all Boeing Model 747 airplanes. The original NPRM would have required inspecting for cracks in the left- and right-side Stringer 11 longeron adjacent to the horizontal stabilizer pivot bulkhead, and related investigative and corrective actions if necessary. The original NPRM resulted from a report of a crack found in the right-side Stringer 11 longeron horizontal flange, adjacent to the horizontal stabilizer pivot bulkhead, during a routine maintenance inspection. This action revises the original NPRM by reducing the compliance times for certain airplanes. We are proposing this supplemental NPRM to detect and correct fatigue cracking of the longeron, which can propagate and cause damage to the adjacent horizontal stabilizer pivot bulkhead. This damage could result in loss of structural integrity and consequent inability of the bulkhead to carry flight loads, which could adversely affect controllability of the airplane. The Proposed Amendment 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. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive: Hamilton Sundstrand Corporation: Docket No. FAA–2009–0113; Directorate Identifier 2008–NE–25–AD. Comments Due Date (a) The Federal Aviation Administration (FAA) must receive comments on this airworthiness directive (AD) action by April 21, 2009. Affected ADs (b) None. Removing Blades P/N R817370–1 (f) Remove blades P/N 817370–1, SNs FR2018, FR2083, FR2103, FR2108, FR2109, FR2111, FR2123, FR2178, FR2183, FR2187, FR2262, FR2276 through FR2279, FR2303, and FR2389. Alternative Methods of Compliance (g) 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. Issued in Burlington, Massachusetts, on February 11, 2009. Peter A. White, Assistant Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E9–3608 Filed 2–19–09; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2008–0612; Directorate Identifier 2008–NM–059–AD] Applicability (c) This AD applies to Hamilton Sundstrand model 247F series propellers with blades part number (P/N) 817370–1, serial numbers (SNs) FR2018, FR2083, FR2103, FR2108, FR2109, FR2111, FR2123, FR2178, FR2183, FR2187, FR2262, FR2276 through FR2279, FR2303, and FR2389, VerDate Nov<24>2008 Compliance (e) You are responsible for having the actions required by this AD performed within 30 days after the effective date of this AD. 17:28 Feb 19, 2009 Jkt 217001 RIN 2120–AA64 Airworthiness Directives; Boeing Model 747 Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 DATES: We must receive comments on this supplemental NPRM by March 17, 2009. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://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; telephone 206–544–9990; fax 206–766–5682; e-mail DDCS@boeing.com; Internet https://www.myboeingfleet.com. You may review copies of the referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227– 1221 or 425–227–1152. E:\FR\FM\20FEP1.SGM 20FEP1

Agencies

[Federal Register Volume 74, Number 33 (Friday, February 20, 2009)]
[Proposed Rules]
[Pages 7833-7834]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-3608]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0113; Directorate Identifier 2008-NE-25-AD]
RIN 2120-AA64


Airworthiness Directives; Hamilton Sundstrand Propellers Model 
247F Propellers

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

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for Hamilton Sundstrand Propellers model 247F propeller assemblies with 
certain part number (P/N) and serial number (SN) blades. This proposed 
AD would require removing affected propeller blades from service. This 
proposed AD results from reports of blades with corrosion pits in the 
tulip area of the blades. We are proposing this AD to prevent cracks 
from developing in the tulip area of the blade, which could result in 
separation of the blade and possible loss of airplane control.

DATES: We must receive any comments on this proposed AD by April 21, 
2009.

ADDRESSES: Use one of the following addresses to comment on this 
proposed AD.
     Federal eRulemaking Portal: Go to https://
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.
    You can get the service information identified in this proposed AD 
from Hamilton Sundstrand Propeller Technical Team, One Hamilton Road, 
Mail Stop 1-3-AB43, Windsor Locks, CT 06096-1010; fax (860) 654-5107.

FOR FURTHER INFORMATION CONTACT: Terry Fahr, Aerospace Engineer, Boston 
Aircraft Certification Office, FAA, Engine & Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803; e-mail: 
terry.fahr@faa.gov; telephone (781) 238-7155; fax (781) 238-7170.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send us any written relevant data, views, or 
arguments regarding this proposal. Send your comments to an address 
listed under ADDRESSES. Include ``Docket No. FAA-2009-0113; Directorate 
Identifier 2008-NE-25-AD'' in the subject line of your comments. We 
specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of the proposed AD. We will consider 
all comments received by the closing date and may amend the proposed AD 
in light of those comments.
    We will post all comments we receive, without change, to https://
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).

Examining the AD Docket

    You may examine the AD docket on the Internet at https://
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.

Discussion

    We have received reports of corrosion on 6 propeller blades. A lack 
of adhesive and primer beyond the end of the compression wrap during 
manufacturing of certain serial-numbered propeller blades, P/N R817370-
1, could result in corrosion pits developing in the tulip area of the 
propeller blade. This condition, if not corrected, could cause cracks 
in the tulip area, which could result in separation of the propeller 
blade and possible loss of airplane control.

Relevant Service Information

    We have reviewed and approved the technical contents of Hamilton 
Sundstrand Service Bulletin 247F-61-54, Revision 1, dated January 12, 
2004, that describes procedures for reworking and re-marking the blade 
with a new P/N.

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. We are proposing this AD, which would require 
removing propeller blades, P/N R817370-1, with a SN listed in this 
proposed AD, within 30 days after the effective date of this proposed 
AD.

Costs of Compliance

    We estimate that this proposed AD would affect 25 propellers 
installed on airplanes of U.S. registry. We also estimate that it would 
take about 128 work-hours per propeller to perform the proposed 
actions, and that the average labor rate is $80 per work-hour. Required 
parts would cost about $50 per propeller. Based on these figures, we 
estimate the total cost of the proposed AD to U.S. operators to be 
$257,250.

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.

[[Page 7834]]

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 AD:
    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 regulatory evaluation of the estimated costs to 
comply with this proposed AD. 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, Safety.

The Proposed Amendment

    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: Docket No. FAA-2009-0113; 
Directorate Identifier 2008-NE-25-AD.

Comments Due Date

    (a) The Federal Aviation Administration (FAA) must receive 
comments on this airworthiness directive (AD) action by April 21, 
2009.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Hamilton Sundstrand model 247F series 
propellers with blades part number (P/N) 817370-1, serial numbers 
(SNs) FR2018, FR2083, FR2103, FR2108, FR2109, FR2111, FR2123, 
FR2178, FR2183, FR2187, FR2262, FR2276 through FR2279, FR2303, and 
FR2389, installed. These propellers are installed on, but not 
limited to, ATR-GIE Avions de Transport Regional ATR72-210 and 
ATR72-210E airplanes.

Unsafe Condition

    (d) This AD results from reports of blades with corrosion pits 
in the tulip area of the blades. We are issuing this AD to prevent 
cracks from developing in the tulip area of the blade, which could 
result in separation of the blade and possible loss of airplane 
control.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within 30 days after the effective date of this AD.

Removing Blades P/N R817370-1

    (f) Remove blades P/N 817370-1, SNs FR2018, FR2083, FR2103, 
FR2108, FR2109, FR2111, FR2123, FR2178, FR2183, FR2187, FR2262, 
FR2276 through FR2279, FR2303, and FR2389.

Alternative Methods of Compliance

    (g) 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

    (h) Contact Terry Fahr, Aerospace Engineer, Boston Aircraft 
Certification Office, FAA, Engine 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.
    (i) Hamilton Sundstrand Service Bulletin 247F-61-54, Revision 1, 
dated January 12, 2004, pertains to the subject of this AD. Contact 
Hamilton Sundstrand Propeller Technical Team, One Hamilton Road, 
Mail Stop 1-3-AB43, Windsor Locks, CT 06096-1010; fax (860) 654-
5107, for a copy of this service information.

    Issued in Burlington, Massachusetts, on February 11, 2009.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
 [FR Doc. E9-3608 Filed 2-19-09; 8:45 am]
BILLING CODE 4910-13-P
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