Airworthiness Directives; Hartzell Propeller Inc. Model HC-E5N-3( ), HC-E5N-3( )(L), and HC-E5B-5( ) Propellers, 67564-67566 [E7-23119]

Download as PDF 67564 Federal Register / Vol. 72, No. 229 / Thursday, November 29, 2007 / Rules and Regulations 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 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. 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 AD and placed it in the AD docket. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: I 1. The authority citation for part 39 continues to read as follows: I Authority: 49 U.S.C. 106(g), 40113, 44701. 2. The FAA amends § 39.13 by adding the following new AD: I 2007–24–10 Turbomeca: Amendment 39– 15276.; Docket No. FAA–2007–28125, Directorate Identifier 2007–NE–17–AD. Effective Date (a) This airworthiness directive (AD) becomes effective December 14, 2007. Applicability (c) This AD applies to Turbomeca Arriel 2S1 and 2S2 turboshaft engines, all serial numbers that have a hydro mechanical unit (HMU) installed that was manufactured before December 8, 2006, or repaired/ overhauled before December 8, 2006. These engines are installed on, but not limited to, Sikorsky S–76C helicopters. rmajette on PROD1PC64 with RULES Reason (d) European Aviation Safety Agency (EASA) AD No. 2007–0063, dated March 3, 2007, states: During assembly of a new HP/LP fuel pump, the drain screw on the fuel filter unit failed when it was tightened to the torque value specified in the assembly schedule (12 Nm). Investigation of the screw showed that it was fully conforming to its specification, VerDate Aug<31>2005 DEPARTMENT OF TRANSPORTATION FAA AD Differences RIN 2120–AA64 (f) This AD differs from the EASA AD and/ or service information as follows: (1) EASA AD No. 2007–0063 requires compliance with the AD within 30 HMU operating hours, but not later than 15 April 2007, whichever occurs first after the effective date of that AD. (2) This AD, written later, requires compliance within 30 HMU operating hours or 45 days after the effective date of this AD, whichever occurs first. (g) The Manager, Engine Certification Office, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. (h) Refer to EASA AD 2007–0063, dated March 8, 2007, for related information. (i) Contact Christopher Spinney, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: Christopher.spinney@faa.gov; telephone (781) 238–7175; fax (781) 238– 7199, for more information about this AD. Material Incorporated by Reference Affected ADs (b) None. 14:40 Nov 28, 2007 Jkt 214001 BILLING CODE 4910–13–P (e) Unless already done, within 30 HMU operating hours or 45 days after the effective date of this AD, whichever occurs first, replace the fuel filter drain screw with a new one and tighten it to an effective torque of 6.5 Nm, using Turbomeca Mandatory Service Bulletin (MSB) No. 292 73 2824, dated February 1, 2007. Related Information [Amended] Issued in Burlington, Massachusetts, on November 20, 2007. Peter A. White, Assistant Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E7–23031 Filed 11–28–07; 8:45 am] Actions and Compliance Alternative Methods of Compliance (AMOCs) PART 39—AIRWORTHINESS DIRECTIVES § 39.13 in terms of both dimensions and material. The mechanical calculations show, however, that a torque value of 12 Nm is too high for this screw, exceeding the elastic limit of the material. Failure of the affected screw could cause a fuel leak, resulting in an engine flame-out or engine fire. (j) You must use Turbomeca Mandatory Service Bulletin No. 292 73 2824, dated February 1, 2007, to do the actions required by this AD. (k) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (l) For service information identified in this AD, contact: Turbomeca, 40220 Tarnos, France; telephone 33 05 59 74 40 00, fax 33 05 59 74 45 15. (m) You may review service information copies at the FAA, New England Region, 12 New England Executive Park, Burlington, MA; 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/ibrlocations.html. PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–28656; Directorate Identifier 2007–NE–31–AD; Amendment 39– 15280; AD 2007–24–14] Airworthiness Directives; Hartzell Propeller Inc. Model HC–E5N–3( ), HC– E5N–3( )(L), and HC–E5B–5( ) Propellers Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for Hartzell Propeller Inc. Model HC–E5N–3( ), HC– E5N–3( )(L), and HC–E5B–5( ) propellers. This AD requires a onetime eddy current inspection of the propeller hub mounting bolt holes and replacement of the propeller hub if cracked. This AD results from the discovery of a five-bladed propeller hub with a large crack on the mounting flange of the hub. We are issuing this AD to prevent propeller hub failure, blade separation, damage to the airplane, and possible loss of airplane control. DATES: This AD becomes effective December 14, 2007. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulations as of December 14, 2007. We must receive any comments on this AD by January 28, 2008. ADDRESSES: Use one of the following addresses to comment on this AD: • Federal eRulemaking Portal: Go to http://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: U.S. Docket Management Facility, 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. E:\FR\FM\29NOR1.SGM 29NOR1 Federal Register / Vol. 72, No. 229 / Thursday, November 29, 2007 / Rules and Regulations • Fax: (202) 493–2251. Contact Hartzell Propeller Inc., Technical Publications Department, One Propeller Place, Piqua, OH 45356; telephone (937) 778–4200; fax (937) 778–4391, for the service information identified in this AD. FOR FURTHER INFORMATION CONTACT: Tim Smyth, Aerospace Engineer, Chicago Aircraft Certification Office, FAA, Small Airplane Directorate, 2300 East Devon Avenue, Des Plaines, IL 60018; e-mail: timothy.smyth@faa.gov; telephone (847) 294–7132; fax (847) 294–7834. SUPPLEMENTARY INFORMATION: Recently, a Piaggio P–180 airplane experienced a significant vibration in flight, from one of the propellers. The Hartzell model HC–E5N–3( )(L) propeller assembly was removed and examined. Inspection of the propeller assembly revealed a significant crack in the propeller hub. Although the exact cause of the crack is unknown, a major factor appears to be a pre-existing defect in one of the propeller mounting bolt holes. This defect may cause a crack to grow to catastrophic failure. Operating the propeller in an rpm range restricted by the airplane operating limitations may accelerate the hub crack. Acceleration of the propeller hub crack may also be due to operation beyond the airplane’s operating limitations when in ground idle without the propellers feathered, or used in maximum reverse. We determined that the hubs at risk are in two populations. The first population is those hubs with unknown hours, or with between 1,800 and 4,500 hours time-in-service (TIS). The second population is all other hubs with fewer than 1,800 or more than 4,500 hours TIS. This condition, if not corrected, could result in propeller hub cracks, blade separation, damage to the airplane, and possible loss of airplane control. Relevant Service Information We have reviewed and approved the technical contents of Hartzell Propeller Inc. Service Bulletin (SB) No. HC–SB– 61–295, Revision 2, dated August 1, 2007, that describes procedures for a onetime eddy current inspection of the propeller hub mounting bolt holes and replacement of the propeller hub if cracked. rmajette on PROD1PC64 with RULES FAA’s Determination and Requirements of This AD The unsafe condition described previously is likely to exist or develop on other Hartzell Propeller Inc. Model HC–E5N–3( ), HC–E5N–3( )(L), and HC–E5B–5( ) propellers of the same type design. For that reason, we are VerDate Aug<31>2005 14:40 Nov 28, 2007 Jkt 214001 issuing this AD to prevent propeller hub failure, blade separation, damage to the airplane, and possible loss of airplane control. 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, and that good cause exists for making this amendment effective in less than 30 days. 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; however, we invite you 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–2007–28656; Directorate Identifier 2007–NE–31–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:// 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 AD. Using the search function of the Federal Docket Management System Web site, anyone can find and read the comments in any of our dockets, including 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 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 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. PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 67565 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 this 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. 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 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: I E:\FR\FM\29NOR1.SGM 29NOR1 67566 Federal Register / Vol. 72, No. 229 / Thursday, November 29, 2007 / Rules and Regulations PART 39—AIRWORTHINESS DIRECTIVES damage to the airplane, and possible loss of airplane control. DEPARTMENT OF TRANSPORTATION 1. The authority citation for part 39 continues to read as follows: Compliance Federal Aviation Administration (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. 14 CFR Part 39 I 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: I 2007–24–14 Hartzell Propeller Inc.: Amendment 39–15280. Docket No. FAA–2007–28656; Directorate Identifier 2007–NE–31–AD. Effective Date (a) This airworthiness directive (AD) becomes effective December 14, 2007. Affected ADs (b) None. Applicability (c) This AD applies to Hartzell Propeller Inc. model HC–E5N–3( ), HC–E5N–3( )(L), and HC–E5B–5( ) propellers. Hartzell Propeller Inc. model HC–E5N–3( )and HC– E5N–3( )(L) propellers are installed on, but not limited to, Piaggio P–180 Avanti airplanes with propeller serial numbers (SNs) up to and including HF229 or KU92, except those SNs listed in the following Table 1. Hartzell Propeller Inc. HC–E5B( ) propellers are installed on Grumman S–2 Tracker airplanes with propeller SNs up to and including HN14. TABLE 1.—PROPELLER SNS NOT AFFECTED BY THIS AD HC–E5N–3( )L: HF4, HF5, HF6, HF7, HF18, HF20, HF26, HF28, HF30, HF34, HF45, HF50, HF52, HF74, HF76, HF87, HF93, HF94, HF97, HF101, HF109, HF121, HF122, HF126, HF130, HF133, HF135, HF137, HF140, HF147, HF149, HF152, HF153, HF156, HF158, HF164, HF165, HF179, HF183, HF184, HF188, HF190, HF195, HF205, HF213, HF215, HF225, HF226, HF230, HF231, HF232, HF233, HF234, HF235. HC–E5N–3( ): KU1, KU3, KU14, KU15, KU16, KU19, KU34, KU41, KU45, KU51, KU57, KU69, KU74, KU79, KU84, KU86, KU87, KU89, KU93, KU94, KU95, KU96, KU103. rmajette on PROD1PC64 with RULES HC–E5B–5( ): HN15. Unsafe Condition (d) This AD results from the discovery of a five-bladed propeller hub with a large crack on the mounting flange of the hub. We determined that the hubs at risk are in two populations. The first population is those hubs with unknown hours, or with between 1,800 and 4,500 hours time-in-service (TIS). The second population is all other hubs with fewer than 1,800 or more than 4,500 hours TIS. We are issuing this AD to prevent propeller hub failure, blade separation, VerDate Aug<31>2005 14:40 Nov 28, 2007 Jkt 214001 Propeller Hub Inspection (f) Using Hartzell Service Bulletin (SB) HC–SB–61–295, Revision 2, dated August 1, 2007, do a onetime eddy current inspection of the propeller mounting holes and replace the propeller hub if any crack is found. Inspect as follows: (1) If propeller hub TIS is unknown, or more than 1,800 hours but fewer than 4,500 hours, inspect the mounting holes within 12 calendar months, or within the next 150 hours TIS, or at the next scheduled airframe ‘‘A’’ check inspection. (2) If the propeller hub TIS is 1,800 hours or fewer, or 4,500 hours or more, inspect the mounting holes within 12 calendar months, or within 600 hours TIS, or at the next scheduled airframe ‘‘B’’ check inspection, whichever comes first. Alternative Methods of Compliance (g) The Manager, Chicago 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 Tim Smyth, Aerospace Engineer, Chicago Aircraft Certification Office, FAA, Small Airplane Directorate, 2300 East Devon Avenue, Des Plaines, IL 60018; e-mail: timothy.smyth@faa.gov; telephone (847) 294–7132; fax (847) 294– 7834, for more information about this AD. Material Incorporated by Reference (i) You must use Hartzell Service Bulletin HC–SB–61–295, Revision 2, dated August 1, 2007, to perform the inspection required by this AD. The Director of the Federal Register approved the incorporation by reference of this service bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Hartzell Propeller Inc., Technical Publications Department, One Propeller Place, Piqua, OH 45356; telephone (937) 778– 4200; fax (937) 778–4391, for a copy of this service information. You may review copies at the FAA, New England Region, 12 New England Executive Park, Burlington, MA 01803; 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. Issued in Burlington, Massachusetts, on November 21, 2007. Peter A. White, Assistant Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E7–23119 Filed 11–28–07; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 [Docket No. FAA–2007–0250; Directorate Identifier 2007–CE–091–AD; Amendment 39–15279; AD 2007–24–13] RIN 2120–AA64 Airworthiness Directives; Cirrus Design Corporation Model SR22 Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for certain Cirrus Design Corporation (Cirrus) Model SR22 airplanes. This AD requires you to install a drain hole in the left and right outboard wing tips. This AD results from reports of pilots’ inability to move the aileron control without using excessive force when flying in freezing conditions. Moisture from a prior rain shower entered through a gap at the interface of the left and right outboard wing tips and wing structure. The moisture traveled along the aft wing shear web, accumulated below the aileron control pulley, and froze at an altitude with an outside air temperature below freezing. When this moisture is exposed to freezing conditions, operation of the aileron control pulley is impaired. We are issuing this AD to prevent moisture from accumulating along the wing shear web where it may freeze in certain conditions. This condition could result in operational failure of the aileron control pulley, which could lead to loss of control. DATES: This AD becomes effective on December 4, 2007. On December 4, 2007, the Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD. We must receive any comments on this AD by January 28, 2008. ADDRESSES: Use one of the following addresses to comment on this AD. • Federal eRulemaking Portal: Go to http://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 E:\FR\FM\29NOR1.SGM 29NOR1

Agencies

[Federal Register Volume 72, Number 229 (Thursday, November 29, 2007)]
[Rules and Regulations]
[Pages 67564-67566]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-23119]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-28656; Directorate Identifier 2007-NE-31-AD; 
Amendment 39-15280; AD 2007-24-14]
RIN 2120-AA64


Airworthiness Directives; Hartzell Propeller Inc. Model HC-E5N-3( 
), HC-E5N-3( )(L), and HC-E5B-5( ) Propellers

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

ACTION: Final rule; request for comments.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
Hartzell Propeller Inc. Model HC-E5N-3( ), HC-E5N-3( )(L), and HC-E5B-
5( ) propellers. This AD requires a onetime eddy current inspection of 
the propeller hub mounting bolt holes and replacement of the propeller 
hub if cracked. This AD results from the discovery of a five-bladed 
propeller hub with a large crack on the mounting flange of the hub. We 
are issuing this AD to prevent propeller hub failure, blade separation, 
damage to the airplane, and possible loss of airplane control.

DATES: This AD becomes effective December 14, 2007. The Director of the 
Federal Register approved the incorporation by reference of certain 
publications listed in the regulations as of December 14, 2007.
    We must receive any comments on this AD by January 28, 2008.

ADDRESSES: Use one of the following addresses to comment on this AD:
     Federal eRulemaking Portal: Go to http://
www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: U.S. Docket Management Facility, 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.

[[Page 67565]]

     Fax: (202) 493-2251.
    Contact Hartzell Propeller Inc., Technical Publications Department, 
One Propeller Place, Piqua, OH 45356; telephone (937) 778-4200; fax 
(937) 778-4391, for the service information identified in this AD.

FOR FURTHER INFORMATION CONTACT: Tim Smyth, Aerospace Engineer, Chicago 
Aircraft Certification Office, FAA, Small Airplane Directorate, 2300 
East Devon Avenue, Des Plaines, IL 60018; e-mail: 
timothy.smyth@faa.gov; telephone (847) 294-7132; fax (847) 294-7834.

SUPPLEMENTARY INFORMATION: Recently, a Piaggio P-180 airplane 
experienced a significant vibration in flight, from one of the 
propellers. The Hartzell model HC-E5N-3( )(L) propeller assembly was 
removed and examined. Inspection of the propeller assembly revealed a 
significant crack in the propeller hub. Although the exact cause of the 
crack is unknown, a major factor appears to be a pre-existing defect in 
one of the propeller mounting bolt holes. This defect may cause a crack 
to grow to catastrophic failure. Operating the propeller in an rpm 
range restricted by the airplane operating limitations may accelerate 
the hub crack. Acceleration of the propeller hub crack may also be due 
to operation beyond the airplane's operating limitations when in ground 
idle without the propellers feathered, or used in maximum reverse. We 
determined that the hubs at risk are in two populations. The first 
population is those hubs with unknown hours, or with between 1,800 and 
4,500 hours time-in-service (TIS). The second population is all other 
hubs with fewer than 1,800 or more than 4,500 hours TIS. This 
condition, if not corrected, could result in propeller hub cracks, 
blade separation, damage to the airplane, and possible loss of airplane 
control.

Relevant Service Information

    We have reviewed and approved the technical contents of Hartzell 
Propeller Inc. Service Bulletin (SB) No. HC-SB-61-295, Revision 2, 
dated August 1, 2007, that describes procedures for a onetime eddy 
current inspection of the propeller hub mounting bolt holes and 
replacement of the propeller hub if cracked.

FAA's Determination and Requirements of This AD

    The unsafe condition described previously is likely to exist or 
develop on other Hartzell Propeller Inc. Model HC-E5N-3( ), HC-E5N-3( 
)(L), and HC-E5B-5( ) propellers of the same type design. For that 
reason, we are issuing this AD to prevent propeller hub failure, blade 
separation, damage to the airplane, and possible loss of airplane 
control. 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, and that good 
cause exists for making this amendment effective in less than 30 days.

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; however, we invite you 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-2007-28656; 
Directorate Identifier 2007-NE-31-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://
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 AD. Using the search function of the 
Federal Docket Management System Web site, anyone can find and read the 
comments in any of our dockets, including 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 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 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.

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 this 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. 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:

[[Page 67566]]

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:

2007-24-14 Hartzell Propeller Inc.: Amendment 39-15280. Docket No. 
FAA-2007-28656; Directorate Identifier 2007-NE-31-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective December 
14, 2007.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Hartzell Propeller Inc. model HC-E5N-3( 
), HC-E5N-3( )(L), and HC-E5B-5( ) propellers. Hartzell Propeller 
Inc. model HC-E5N-3( )and HC-E5N-3( )(L) propellers are installed 
on, but not limited to, Piaggio P-180 Avanti airplanes with 
propeller serial numbers (SNs) up to and including HF229 or KU92, 
except those SNs listed in the following Table 1. Hartzell Propeller 
Inc. HC-E5B( ) propellers are installed on Grumman S-2 Tracker 
airplanes with propeller SNs up to and including HN14.

             Table 1.--Propeller SNs Not Affected by This AD
------------------------------------------------------------------------
 
-------------------------------------------------------------------------
HC-E5N-3( )L:
  HF4, HF5, HF6, HF7, HF18, HF20, HF26, HF28, HF30, HF34, HF45, HF50,
   HF52, HF74, HF76, HF87, HF93, HF94, HF97, HF101, HF109, HF121, HF122,
   HF126, HF130, HF133, HF135, HF137, HF140, HF147, HF149, HF152, HF153,
   HF156, HF158, HF164, HF165, HF179, HF183, HF184, HF188, HF190, HF195,
   HF205, HF213, HF215, HF225, HF226, HF230, HF231, HF232, HF233, HF234,
   HF235.
------------------------------------------------------------------------
HC-E5N-3( ):
  KU1, KU3, KU14, KU15, KU16, KU19, KU34, KU41, KU45, KU51, KU57, KU69,
   KU74, KU79, KU84, KU86, KU87, KU89, KU93, KU94, KU95, KU96, KU103.
------------------------------------------------------------------------
HC-E5B-5( ):
  HN15.
------------------------------------------------------------------------

Unsafe Condition

    (d) This AD results from the discovery of a five-bladed 
propeller hub with a large crack on the mounting flange of the hub. 
We determined that the hubs at risk are in two populations. The 
first population is those hubs with unknown hours, or with between 
1,800 and 4,500 hours time-in-service (TIS). The second population 
is all other hubs with fewer than 1,800 or more than 4,500 hours 
TIS. We are issuing this AD to prevent propeller hub failure, blade 
separation, damage to the airplane, 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.

Propeller Hub Inspection

    (f) Using Hartzell Service Bulletin (SB) HC-SB-61-295, Revision 
2, dated August 1, 2007, do a onetime eddy current inspection of the 
propeller mounting holes and replace the propeller hub if any crack 
is found. Inspect as follows:
    (1) If propeller hub TIS is unknown, or more than 1,800 hours 
but fewer than 4,500 hours, inspect the mounting holes within 12 
calendar months, or within the next 150 hours TIS, or at the next 
scheduled airframe ``A'' check inspection.
    (2) If the propeller hub TIS is 1,800 hours or fewer, or 4,500 
hours or more, inspect the mounting holes within 12 calendar months, 
or within 600 hours TIS, or at the next scheduled airframe ``B'' 
check inspection, whichever comes first.

Alternative Methods of Compliance

    (g) The Manager, Chicago 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 Tim Smyth, Aerospace Engineer, Chicago Aircraft 
Certification Office, FAA, Small Airplane Directorate, 2300 East 
Devon Avenue, Des Plaines, IL 60018; e-mail: timothy.smyth@faa.gov; 
telephone (847) 294-7132; fax (847) 294-7834, for more information 
about this AD.

Material Incorporated by Reference

    (i) You must use Hartzell Service Bulletin HC-SB-61-295, 
Revision 2, dated August 1, 2007, to perform the inspection required 
by this AD. The Director of the Federal Register approved the 
incorporation by reference of this service bulletin in accordance 
with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Hartzell Propeller 
Inc., Technical Publications Department, One Propeller Place, Piqua, 
OH 45356; telephone (937) 778-4200; fax (937) 778-4391, for a copy 
of this service information. You may review copies at the FAA, New 
England Region, 12 New England Executive Park, Burlington, MA 01803; 
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.

    Issued in Burlington, Massachusetts, on November 21, 2007.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
 [FR Doc. E7-23119 Filed 11-28-07; 8:45 am]
BILLING CODE 4910-13-P