Airworthiness Directives; Hartzell Propeller Inc. Compact Series Propellers, 72915-72917 [E7-24855]

Download as PDF Federal Register / Vol. 72, No. 246 / Wednesday, December 26, 2007 / Rules and Regulations communications under paragraph (a) of this section aggregating in excess of $10,000 in a calendar year shall file statements as required by 11 CFR 104.20. Dated: December 17, 2007. Robert D. Lenhard, Chairman, Federal Election Commission. [FR Doc. E7–24797 Filed 12–21–07; 8:45 am] BILLING CODE 6715–01–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 23 Airworthiness Standards: Normal, Utility, Acrobatic, and Commuter Category Airplanes CFR Correction In Title 14 of the Code of Federal Regulations, Parts 1 to 59, revised as of January 1, 2007, on page 227, in § 23.561, remove the five paragraphs beginning with the second paragraph (d)(1)(i) through paragraph (d)(1)(v). [FR Doc. 07–55522 Filed 12–21–07; 8:45 am] BILLING CODE 1505–01–D DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–28876; Directorate Identifier 2000–NE–08–AD; Amendment 39– 15311; AD 2007–26–09] RIN 2120–AA64 Airworthiness Directives; Hartzell Propeller Inc. Compact Series Propellers Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. mstockstill on PROD1PC66 with RULES AGENCY: SUMMARY: The FAA is superseding an existing airworthiness directive (AD) for all Hartzell Propeller Inc. models ( ) HC–( )( )Y( )–( )( )( ) compact series, constant speed or feathering propellers with Hartzell manufactured ‘‘Y’’ shank aluminum blades. That AD currently requires initial blade inspections, with no repetitive inspections; rework of all ‘‘Y’’ shank aluminum blades including cold rolling of the blade shank retention radius, blade replacement and modification of pitch change mechanisms for certain propeller models; and changing the airplane operating limitations with VerDate Aug<31>2005 18:48 Dec 21, 2007 Jkt 214001 specific models of propellers installed. This AD requires the same actions but clarifies certain areas of the compliance, and updates a certain service bulletin (SB) reference to the most recent SB. This AD results from operators requesting clarification of certain portions of AD 2002–09–08. We are issuing this AD to prevent failure of the propeller blade from fatigue cracks in the blade shank radius, which can result in damage to the airplane and loss of airplane control. DATES: This AD becomes effective January 30, 2008. The Director of the Federal Register previously approved the incorporation by reference of certain publications listed in the regulations as of June 13, 2002 (67 FR 31113, May 9, 2002). The Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulations as of January 30, 2008. ADDRESSES: You can get the service information identified in this AD from Hartzell Propeller Inc. Technical Publications Department, One Propeller Place, Piqua, OH 45356; telephone (937) 778–4200; fax (937) 778–4391. The Docket Operations office is located at Docket Management Facility, U.S. Department of Transportation, 1200 New Jersey Avenue, SE., West Building Ground Floor, Room W12–140, Washington, DC 20590–0001. FOR FURTHER INFORMATION CONTACT: Tim Smyth, Senior Aerospace Engineer, Chicago Aircraft Certification Office, FAA, Small Airplane Directorate, 2300 East Devon Avenue, Des Plaines, IL 60018–4696; e-mail: timothy.smyth@faa.gov; telephone (847) 294–8110; fax (847) 294–7132. SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 by superseding AD 2002–09–08, Amendment 39–12741 (67 FR 31113, May 9, 2002) with a proposed AD. The proposed AD applies to Hartzell Propeller Inc. models ( )HC–( )( )Y ( )–( )( )( ) compact series, constant speed or feathering propellers with Hartzell manufactured ‘‘Y’’ shank aluminum blades. We published the proposed AD in the Federal Register on August 14, 2006 (71 FR 46413). That action proposed to require the same actions as AD 2002–09–08, but would clarify certain areas of the compliance and would update a certain SB reference to the most recent SB. 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, PO 00000 Frm 00017 Fmt 4700 Sfmt 4700 72915 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 provided in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. Comments We provided the public the opportunity to participate in the development of this AD. We have considered the comment received. Incorporate Service Documents by Reference and Publish Them in the Document Management System The Modification and Replacement Parts Association requests that all service documents deemed essential to the accomplishment of the AD be incorporated by reference into the regulatory instrument, and published in the Docket Management System. We partially agree. We have incorporated pertinent service material into the regulatory section of this AD. However, at this time, the FAA does not post service material on the Federal Docket Management System. We are in the process of reviewing issues surrounding the posting of service bulletins on the Federal Docket Management System as part of an AD docket. Once we have thoroughly examined all aspects of this issue and have made a final determination, we will consider whether our current practice needs to be revised. Format Changes We changed the propeller blade shank cold rolling information from being a note, to paragraphs. We also added paragraphs to the alternative methods of compliance, to make the information more readable. Conclusion We have carefully reviewed the available data, including the comment received, and determined that air safety and the public interest require adopting the AD with the changes described previously. Costs of Compliance We estimate that this AD will affect 35,750 propellers installed on airplanes of U.S. registry. We expect this AD will cost about $700 per propeller. Total cost to U.S. operators for this AD would be about $25.025 million. However, we also expect that all of the affected propellers should have already been inspected to comply with the existing AD’s requirements to inspect, and E:\FR\FM\26DER1.SGM 26DER1 72916 Federal Register / Vol. 72, No. 246 / Wednesday, December 26, 2007 / Rules and Regulations rework or replace the aluminum blades. Therefore, we expect that this AD will have no additional cost. Docket Number Change We are transferring the docket for this AD to the Federal Docket Management System as part of our on-going docket management consolidation efforts. The new Docket No. is FAA–2007–28876. The old Docket No. became the Directorate Identifier, which is 2000– NE–08–AD. 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 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 Accordingly, under the authority delegated to me by the Administrator, I the Federal Aviation Administration amends 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: I Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing Amendment 39–12741 (67 FR 31113, May 9, 2002), and by adding a new airworthiness directive, Amendment 39–15311, to read as follows: I 2007–26–09 Hartzell Propeller Inc.: Amendment 39–15311. Docket No. FAA–2007–28876; Directorate Identifier 2000–NE–08–AD. Effective Date (a) This airworthiness directive (AD) becomes effective January 30, 2008. Affected ADs (b) This AD supersedes AD 2002–09–08, Amendment 39–12741. Applicability (c) This AD applies to all Hartzell Propeller Inc. models ( )HC–( )( )Y( )–( )( )( ) compact series constant speed or feathering propellers with Hartzell manufactured ‘‘Y’’ shank aluminum blades. These propellers are used on, but not limited to, the following airplanes: Manufacturer Airplane Model Aermacchi S.pA. (formerly Siai–Marchetti) .............................................. Aero Commander ..................................................................................... Aerostar .................................................................................................... Beech ........................................................................................................ Bellanca .................................................................................................... Cessna ...................................................................................................... Embraer .................................................................................................... Maule ........................................................................................................ Mooney ..................................................................................................... Pilatus Britten Norman, or Britten Norman .............................................. Piper ......................................................................................................... S–208 200B and 200D 600 24, 35, 36, 45, 55, 56TC, 58, 60, and 95 14 and 17 series 182 and 188 EMB–200A M5 M20 and M22 BN–2, BN–2A, and BN–2A–6 PA–23, PA–24, PA–28, PA–30, PA–31, PA–32, PA–34, PA–36, and PA–39 S–1T and S–2A 112, 114, 200, 500, and 685 series Pitts ........................................................................................................... Rockwell ................................................................................................... mstockstill on PROD1PC66 with RULES (d) The parentheses appearing in the propeller model number indicates the presence or absence of an additional letter(s) that varies the basic propeller model. This AD applies regardless of whether these letters are present or absent in the propeller model designation. Unsafe Condition (e) This AD results from operators requesting clarification of certain portions of AD 2002–09–08. We are issuing this AD to prevent failure of the propeller blade from fatigue cracks in the aluminum blade shank VerDate Aug<31>2005 18:48 Dec 21, 2007 Jkt 214001 radius, which can result in damage to the airplane and loss of airplane control. Compliance (f) You are responsible for having the actions required by this AD performed within the compliance times specified unless the actions have already been done. (g) If the propeller maintenance records show compliance with AD 77–12–06R2, then compliance was previously done and no further action is required. (h) Propellers are considered in compliance with the one-time inspection and rework requirements only, of this AD if: PO 00000 Frm 00018 Fmt 4700 Sfmt 4700 (1) All blades are serial number D47534 and above, or (2) All blades are identified with the letters ‘‘PR’’ or ‘‘R’’ which are ink-stamped on the camber side, or the letters ‘‘RD’’ which are metal-stamped on the blade butt. Models ( )HC–( )( )Y( ‘‘Y’’ Shank Propellers ) Compact Series (i) If propeller models ( )HC–( )( )Y( ) have not been inspected and reworked in accordance with AD 77–12–06R2, then before further flight, do a one-time action to remove, inspect, rework, or replace blades if E:\FR\FM\26DER1.SGM 26DER1 Federal Register / Vol. 72, No. 246 / Wednesday, December 26, 2007 / Rules and Regulations necessary using Hartzell Service Bulletin (SB) No. 118A, dated February 15, 1977. Propeller Blade Shank Cold Rolling (j) One requirement in Hartzell SB No. 118A is the cold rolling of the propeller blade shank. (1) Cold rolling is a critical requirement in the prevention of cracks in the blade. Propeller repair shops must obtain and maintain proper certification to perform the cold rolling procedure. (2) For a current list of propeller overhaul facilities approved to perform the blade shank cold rolling procedure, contact Hartzell Product Support, telephone (937) 778–4200. (3) Not all propeller repair facilities have the equipment to properly perform a cold roll of the blade shanks. (4) In addition, any rework in the blade shank area will also necessitate the cold rolling of the blade shank area, apart from the one-time cold rolling requirement of this AD. Instrument Panel Modifications (k) If airplanes with propeller models ( ) HC–C2YK–( )( )( )/( )( )7666A–( ), installed on (undampered) 200 or more horsepower Lycoming IO–360 series engines, have not been modified using AD 77–12– 06R2, then modify the airplane instrument panel according to the following subparagraphs before further flight. Airplanes include, but are not limited to, Mooney M20E and M20F (normal category), Piper PA–28R– 200 (normal category), and Pitts S–1T and S– 2A (acrobatic category). (1) For normal category airplanes, before further flight, remove the present vibration placard and affix a new placard near the engine tachometer that states: ‘‘Avoid continuous operation: Between 2,000 and 2,350 rpm.’’ (n) Alternative methods of compliance for Hartzell SB No. 118A, dated February 15, 1977, are: Hartzell SB No. 118B, November 28, 1977; SB No. 118C, May 13, 1983; SB No. 118D, March 25, 1991; SB No. HC–SB–61– 118E, December 14, 2001; SB No. HC–SB– 61–118 revision F, dated August 15, 2002, and Hartzell Manual 133C. (o) An alternative method of compliance to Hartzell SB No. 101D, dated December 19, 1974, is Hartzell Manual 133C. (p) No adjustment in the compliance time is allowed. (2) For utility and acrobatic category airplanes, before further flight, remove the present vibration placard and affix a new placard near the engine tachometer that states: ‘‘Avoid continuous operation: Between 2,000 and 2,350 rpm. Above 2,600 rpm in acrobatic flight.’’ (3) For normal category airplanes, re-mark the engine tachometer face or bezel with a red arc for the restricted engine speed range, between 2,000 and 2,350 rpm. (4) For acrobatic and utility airplanes, remark the engine tachometer face or bezel with a red arc for each restricted engine speed range, i.e., between 2,000 and 2,350 rpm and between 2,600 and 2,700 rpm (red line). Models ( )HC–C2YK–( )( )( )/( )( 8475( )–( ) or ( )( )8477( )–( ) Propellers 72917 Related Information (q) Contact Tim Smyth, Senior Aerospace Engineer, Chicago Aircraft Certification Office, FAA, Small Airplane Directorate, 2300 East Devon Avenue, Des Plaines, IL 60018–4696; e-mail: timothy.smyth@faa.gov; telephone (847) 294–7132; fax (847) 294– 7834, for more information about this AD. ) (l) If propeller models ( )HC–C2YK–( )( ) Material Incorporated by Reference ( )/( )( )8475( )–( ) or ( )( )8477( )– (r) You must use the service information ( ) have not been inspected and reworked in specified in Table 1 of this AD to perform the accordance with AD 74–15–02, then do the actions required by this AD. The Director of following maintenance before further flight. the Federal Register previously approved the (1) Remove propeller from airplane. incorporation by reference of the documents (2) Modify pitch change mechanism, and listed in Table 1 of this AD in accordance replace blades with equivalent model blades with 5 U.S.C. 552(a) and 1 CFR part 51 on prefixed with letter ‘‘F’’ using Hartzell June 13, 2002. Contact Hartzell Propeller Inc. Service Letter No. 69, dated November 30, Technical Publications Department, One 1971 and Hartzell SB No. 101D, dated Propeller Place, Piqua, OH 45356; telephone December 19, 1974. (937) 778–4200; fax (937) 778–4391, for a (3) Inspect and repair or replace, if copy of this service information. You may necessary, using Hartzell SB No. 118A, dated review service information copies at the February 15, 1977. FAA, New England Region, 12 New England Executive Park, Burlington, MA; or at the Alternative Methods of Compliance National Archives and Records (m) The Manager, Chicago Aircraft Administration (NARA). For information on Certification Office, has the authority to the availability of this material at NARA, call approve alternative methods of compliance (202) 741–6030, or go to: http:// for this AD if requested using the procedures www.archives.gov/federal-register/cfr/ibrfound in 14 CFR 39.19. locations.html. TABLE 1.—INCORPORATION BY REFERENCE Hartzell service information Page SB No. 101D .................................................................................................................. SB No. 118A .................................................................................................................. SL No. 69 ....................................................................................................................... Issued in Burlington, Massachusetts, on December 17, 2007. Peter A. White, Assistant Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E7–24855 Filed 12–21–07; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF COMMERCE Bureau of Economic Analysis 15 CFR Part 806 [Docket No. 070301044–7814–02] RIN 0691–AA64 mstockstill on PROD1PC66 with RULES Direct Investment Surveys: BE–12, 2007 Benchmark Survey of Foreign Direct Investment in the United States Bureau of Economic Analysis, Commerce. ACTION: Final rule. AGENCY: SUMMARY: This final rule amends regulations concerning the reporting VerDate Aug<31>2005 18:48 Dec 21, 2007 Jkt 214001 PO 00000 Frm 00019 Fmt 4700 Sfmt 4700 Revision All All All Date D A 1 December 19, 1974. February 15, 1977. November 30, 1971. requirements for the BE–12, Benchmark Survey of Foreign Direct Investment in the United States. The BE–12 survey is conducted once every 5 years and covers virtually the entire universe of foreign direct investment in the United States in terms of value. The benchmark survey will be conducted for 2007. BEA is changing the reporting requirements on the BE–12 Benchmark survey to: Increase the exemption level for reporting on the BE–12(LF) (Long Form) from $125 million to $175 million; increase the exemption level for reporting on the BE–12(SF) (Short Form) from $10 million to $40 million; and increase the exemption level for reporting on the BE–12 Bank Form from E:\FR\FM\26DER1.SGM 26DER1

Agencies

[Federal Register Volume 72, Number 246 (Wednesday, December 26, 2007)]
[Rules and Regulations]
[Pages 72915-72917]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-24855]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-28876; Directorate Identifier 2000-NE-08-AD; 
Amendment 39-15311; AD 2007-26-09]
RIN 2120-AA64


Airworthiness Directives; Hartzell Propeller Inc. Compact Series 
Propellers

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

ACTION: Final rule.

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

SUMMARY: The FAA is superseding an existing airworthiness directive 
(AD) for all Hartzell Propeller Inc. models ( )HC-( )( )Y( )-( )( )( ) 
compact series, constant speed or feathering propellers with Hartzell 
manufactured ``Y'' shank aluminum blades. That AD currently requires 
initial blade inspections, with no repetitive inspections; rework of 
all ``Y'' shank aluminum blades including cold rolling of the blade 
shank retention radius, blade replacement and modification of pitch 
change mechanisms for certain propeller models; and changing the 
airplane operating limitations with specific models of propellers 
installed. This AD requires the same actions but clarifies certain 
areas of the compliance, and updates a certain service bulletin (SB) 
reference to the most recent SB. This AD results from operators 
requesting clarification of certain portions of AD 2002-09-08. We are 
issuing this AD to prevent failure of the propeller blade from fatigue 
cracks in the blade shank radius, which can result in damage to the 
airplane and loss of airplane control.

DATES: This AD becomes effective January 30, 2008. The Director of the 
Federal Register previously approved the incorporation by reference of 
certain publications listed in the regulations as of June 13, 2002 (67 
FR 31113, May 9, 2002). The Director of the Federal Register approved 
the incorporation by reference of certain publications listed in the 
regulations as of January 30, 2008.

ADDRESSES: You can get the service information identified in this AD 
from Hartzell Propeller Inc. Technical Publications Department, One 
Propeller Place, Piqua, OH 45356; telephone (937) 778-4200; fax (937) 
778-4391.
    The Docket Operations office is located at Docket Management 
Facility, U.S. Department of Transportation, 1200 New Jersey Avenue, 
SE., West Building Ground Floor, Room W12-140, Washington, DC 20590-
0001.

FOR FURTHER INFORMATION CONTACT: Tim Smyth, Senior Aerospace Engineer, 
Chicago Aircraft Certification Office, FAA, Small Airplane Directorate, 
2300 East Devon Avenue, Des Plaines, IL 60018-4696; e-mail: 
timothy.smyth@faa.gov; telephone (847) 294-8110; fax (847) 294-7132.

SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 by 
superseding AD 2002-09-08, Amendment 39-12741 (67 FR 31113, May 9, 
2002) with a proposed AD. The proposed AD applies to Hartzell Propeller 
Inc. models ( )HC-( )( )Y ( )-( )( )( ) compact series, constant speed 
or feathering propellers with Hartzell manufactured ``Y'' shank 
aluminum blades. We published the proposed AD in the Federal Register 
on August 14, 2006 (71 FR 46413). That action proposed to require the 
same actions as AD 2002-09-08, but would clarify certain areas of the 
compliance and would update a certain SB reference to the most recent 
SB.

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 provided in 
the ADDRESSES section. Comments will be available in the AD docket 
shortly after receipt.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the comment received.

Incorporate Service Documents by Reference and Publish Them in the 
Document Management System

    The Modification and Replacement Parts Association requests that 
all service documents deemed essential to the accomplishment of the AD 
be incorporated by reference into the regulatory instrument, and 
published in the Docket Management System. We partially agree. We have 
incorporated pertinent service material into the regulatory section of 
this AD. However, at this time, the FAA does not post service material 
on the Federal Docket Management System. We are in the process of 
reviewing issues surrounding the posting of service bulletins on the 
Federal Docket Management System as part of an AD docket. Once we have 
thoroughly examined all aspects of this issue and have made a final 
determination, we will consider whether our current practice needs to 
be revised.

Format Changes

    We changed the propeller blade shank cold rolling information from 
being a note, to paragraphs. We also added paragraphs to the 
alternative methods of compliance, to make the information more 
readable.

Conclusion

    We have carefully reviewed the available data, including the 
comment received, and determined that air safety and the public 
interest require adopting the AD with the changes described previously.

Costs of Compliance

    We estimate that this AD will affect 35,750 propellers installed on 
airplanes of U.S. registry. We expect this AD will cost about $700 per 
propeller. Total cost to U.S. operators for this AD would be about 
$25.025 million. However, we also expect that all of the affected 
propellers should have already been inspected to comply with the 
existing AD's requirements to inspect, and

[[Page 72916]]

rework or replace the aluminum blades. Therefore, we expect that this 
AD will have no additional cost.

Docket Number Change

    We are transferring the docket for this AD to the Federal Docket 
Management System as part of our on-going docket management 
consolidation efforts. The new Docket No. is FAA-2007-28876. The old 
Docket No. became the Directorate Identifier, which is 2000-NE-08-AD.

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 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
Accordingly, under the authority delegated to me by the Administrator, 
the Federal Aviation Administration amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:


    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by removing Amendment 39-12741 (67 FR 
31113, May 9, 2002), and by adding a new airworthiness directive, 
Amendment 39-15311, to read as follows:
2007-26-09 Hartzell Propeller Inc.: Amendment 39-15311. Docket No. 
FAA-2007-28876; Directorate Identifier 2000-NE-08-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective January 
30, 2008.

Affected ADs

    (b) This AD supersedes AD 2002-09-08, Amendment 39-12741.

Applicability

    (c) This AD applies to all Hartzell Propeller Inc. models ( )HC-
( )( )Y( )-( )( )( ) compact series constant speed or feathering 
propellers with Hartzell manufactured ``Y'' shank aluminum blades. 
These propellers are used on, but not limited to, the following 
airplanes:

------------------------------------------------------------------------
              Manufacturer                        Airplane Model
------------------------------------------------------------------------
Aermacchi S.pA. (formerly Siai-          S-208
 Marchetti).
Aero Commander.........................  200B and 200D
Aerostar...............................  600
Beech..................................  24, 35, 36, 45, 55, 56TC, 58,
                                          60, and 95
Bellanca...............................  14 and 17 series
Cessna.................................  182 and 188
Embraer................................  EMB-200A
Maule..................................  M5
Mooney.................................  M20 and M22
Pilatus Britten Norman, or Britten       BN-2, BN-2A, and BN-2A-6
 Norman.
Piper..................................  PA-23, PA-24, PA-28, PA-30, PA-
                                          31, PA-32, PA-34, PA-36, and
                                          PA-39
Pitts..................................  S-1T and S-2A
Rockwell...............................  112, 114, 200, 500, and 685
                                          series
------------------------------------------------------------------------

    (d) The parentheses appearing in the propeller model number 
indicates the presence or absence of an additional letter(s) that 
varies the basic propeller model. This AD applies regardless of 
whether these letters are present or absent in the propeller model 
designation.

Unsafe Condition

    (e) This AD results from operators requesting clarification of 
certain portions of AD 2002-09-08. We are issuing this AD to prevent 
failure of the propeller blade from fatigue cracks in the aluminum 
blade shank radius, which can result in damage to the airplane and 
loss of airplane control.

Compliance

    (f) You are responsible for having the actions required by this 
AD performed within the compliance times specified unless the 
actions have already been done.
    (g) If the propeller maintenance records show compliance with AD 
77-12-06R2, then compliance was previously done and no further 
action is required.
    (h) Propellers are considered in compliance with the one-time 
inspection and rework requirements only, of this AD if:
    (1) All blades are serial number D47534 and above, or
    (2) All blades are identified with the letters ``PR'' or ``R'' 
which are ink-stamped on the camber side, or the letters ``RD'' 
which are metal-stamped on the blade butt.

Models ( )HC-( )( )Y( ) Compact Series ``Y'' Shank Propellers

    (i) If propeller models ( )HC-( )( )Y( ) have not been inspected 
and reworked in accordance with AD 77-12-06R2, then before further 
flight, do a one-time action to remove, inspect, rework, or replace 
blades if

[[Page 72917]]

necessary using Hartzell Service Bulletin (SB) No. 118A, dated 
February 15, 1977.

Propeller Blade Shank Cold Rolling

    (j) One requirement in Hartzell SB No. 118A is the cold rolling 
of the propeller blade shank.
    (1) Cold rolling is a critical requirement in the prevention of 
cracks in the blade. Propeller repair shops must obtain and maintain 
proper certification to perform the cold rolling procedure.
    (2) For a current list of propeller overhaul facilities approved 
to perform the blade shank cold rolling procedure, contact Hartzell 
Product Support, telephone (937) 778-4200.
    (3) Not all propeller repair facilities have the equipment to 
properly perform a cold roll of the blade shanks.
    (4) In addition, any rework in the blade shank area will also 
necessitate the cold rolling of the blade shank area, apart from the 
one-time cold rolling requirement of this AD.

Instrument Panel Modifications

    (k) If airplanes with propeller models ( )HC-C2YK-( )( )( )/( )( 
)7666A-( ), installed on (undampered) 200 or more horsepower 
Lycoming IO-360 series engines, have not been modified using AD 77-
12-06R2, then modify the airplane instrument panel according to the 
following subparagraphs before further flight. Airplanes include, 
but are not limited to, Mooney M20E and M20F (normal category), 
Piper PA-28R-200 (normal category), and Pitts S-1T and S-2A 
(acrobatic category).
    (1) For normal category airplanes, before further flight, remove 
the present vibration placard and affix a new placard near the 
engine tachometer that states:
    ``Avoid continuous operation:
    Between 2,000 and 2,350 rpm.''
    (2) For utility and acrobatic category airplanes, before further 
flight, remove the present vibration placard and affix a new placard 
near the engine tachometer that states:
    ``Avoid continuous operation:
    Between 2,000 and 2,350 rpm.
    Above 2,600 rpm in acrobatic flight.''
    (3) For normal category airplanes, re-mark the engine tachometer 
face or bezel with a red arc for the restricted engine speed range, 
between 2,000 and 2,350 rpm.
    (4) For acrobatic and utility airplanes, re-mark the engine 
tachometer face or bezel with a red arc for each restricted engine 
speed range, i.e., between 2,000 and 2,350 rpm and between 2,600 and 
2,700 rpm (red line).

Models ( )HC-C2YK-( )( )( )/( )( )8475( )-( ) or ( )( )8477( )-( ) 
Propellers

    (l) If propeller models ( )HC-C2YK-( )( )( )/( )( )8475( )-( ) 
or ( )( )8477( )-( ) have not been inspected and reworked in 
accordance with AD 74-15-02, then do the following maintenance 
before further flight.
    (1) Remove propeller from airplane.
    (2) Modify pitch change mechanism, and replace blades with 
equivalent model blades prefixed with letter ``F'' using Hartzell 
Service Letter No. 69, dated November 30, 1971 and Hartzell SB No. 
101D, dated December 19, 1974.
    (3) Inspect and repair or replace, if necessary, using Hartzell 
SB No. 118A, dated February 15, 1977.

Alternative Methods of Compliance

    (m) 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.
    (n) Alternative methods of compliance for Hartzell SB No. 118A, 
dated February 15, 1977, are: Hartzell SB No. 118B, November 28, 
1977; SB No. 118C, May 13, 1983; SB No. 118D, March 25, 1991; SB No. 
HC-SB-61-118E, December 14, 2001; SB No. HC-SB-61-118 revision F, 
dated August 15, 2002, and Hartzell Manual 133C.
    (o) An alternative method of compliance to Hartzell SB No. 101D, 
dated December 19, 1974, is Hartzell Manual 133C.
    (p) No adjustment in the compliance time is allowed.

Related Information

    (q) Contact Tim Smyth, Senior Aerospace Engineer, Chicago 
Aircraft Certification Office, FAA, Small Airplane Directorate, 2300 
East Devon Avenue, Des Plaines, IL 60018-4696; e-mail: 
timothy.smyth@faa.gov; telephone (847) 294-7132; fax (847) 294-7834, 
for more information about this AD.

Material Incorporated by Reference

    (r) You must use the service information specified in Table 1 of 
this AD to perform the actions required by this AD. The Director of 
the Federal Register previously approved the incorporation by 
reference of the documents listed in Table 1 of this AD in 
accordance with 5 U.S.C. 552(a) and 1 CFR part 51 on June 13, 2002. 
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 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/ibr-locations.html.

                  Table 1.--Incorporation by Reference
------------------------------------------------------------------------
 Hartzell service information      Page       Revision         Date
------------------------------------------------------------------------
SB No. 101D..................          All            D  December 19,
                                                          1974.
SB No. 118A..................          All            A  February 15,
                                                          1977.
SL No. 69....................          All            1  November 30,
                                                          1971.
------------------------------------------------------------------------


    Issued in Burlington, Massachusetts, on December 17, 2007.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. E7-24855 Filed 12-21-07; 8:45 am]
BILLING CODE 4910-13-P