Airworthiness Directives; Enstrom Helicopter Corporation Model F-28, F-28A, F-28C, F-28C-2, F-28C-2R, F-28F, F-28F-R, 280, 280C, 280F, 280FX, TH-28, 480, and 480B Helicopters, 41615-41618 [07-3711]

Download as PDF rmajette on PROD1PC64 with RULES Federal Register / Vol. 72, No. 146 / Tuesday, July 31, 2007 / Rules and Regulations has on the prices producers receive for their commodity. Without volume control, spearmint oil markets would likely be over-supplied, resulting in low producer prices and a large volume of oil stored and carried over to the next crop year. The model estimates how much lower producer prices would likely be in the absence of volume controls. The recommended allotment percentages, upon which 2006–2007 producer allotments were based, are 153 percent for Scotch (a 108-percentage point increase from the original allotment percentage of 45 percent) and 55 percent for Native (a 9 percentage point increase from the original allotment percentage of 46 percent). Without volume controls, producers would not be limited to these allotment levels, and could produce and sell additional spearmint oil. The econometric model estimated a $1.37 decline in the season average producer price per pound of Far West spearmint oil (combining the two classes of spearmint oil) resulting from the higher quantities that would be produced and marketed if volume controls were not used. A previous price decline estimate of $1.49 per pound was based on the original 2006–2007 allotment percentages (45 percent for Scotch and 46 percent for Native) published in the Federal Register on April 5, 2006 (71 FR 16986). The revised estimate reflects the impact of the additional quantities that have been made available by this rule compared to the original allotment percentages. In actuality, this rule made available 13,026 additional pounds of Scotch and 21,624 additional pounds of Native spearmint oil, since not all producers have reserve pool oil. Loosening the volume control restriction resulted in the smaller price decline estimate of $1.37 per pound. The use of volume controls allows the industry to fully supply spearmint oil markets while avoiding the negative consequences of over-supplying these markets. The use of volume controls is believed to have little or no effect on consumer prices of products containing spearmint oil and will not result in fewer retail sales of such products. Based on projections available at the meeting, the Committee considered alternatives to each of the increases. The Committee not only considered leaving the salable quantity and allotment percentage unchanged, but also looked at various increases. The Committee reached each of its recommendations to increase the salable quantity and allotment percentage for Scotch and Native spearmint oil after careful VerDate Aug<31>2005 13:44 Jul 30, 2007 Jkt 211001 consideration of all available information, and believes that the levels recommended will achieve the objectives sought. Without the increases, the Committee believes the industry would not have been able to meet market needs. This rule will not impose any additional reporting or recordkeeping requirements on either small or large spearmint oil handlers. As with all Federal marketing order programs, reports and forms are periodically reviewed to reduce information requirements and duplication by industry and public sector agencies. In addition, as noted in the initial regulatory flexibility analysis, USDA has not identified any relevant Federal rules that duplicate, overlap or conflict with this rule. The AMS is committed to complying with the E-Government Act, to promote the use of the Internet and other information technologies to provide increased opportunities for citizen access to Government information and services, and for other purposes. The Committee’s meeting was widely publicized throughout the spearmint oil industry and all interested persons were invited to attend the meeting and participate in Committee deliberations. Like all Committee meetings, the February 21, 2007, meeting was a public meeting and all entities, both large and small, were able to express their views on this issue. An interim final rule concerning this action was published in the Federal Register on April 12, 2007. A notice of the rule was mailed by the Committee’s staff to all committee members, producers, handlers, and other interested persons. In addition, the rule was made available through the Internet by USDA and the Office of the Federal Register. That rule provided for a 60-day comment period which ended June 11, 2007. No comments were received. A small business guide on complying with fruit, vegetable, and specialty crop marketing agreements and orders may be viewed at: http://www.ams.usda.gov/ fv/moab.html. Any questions about the compliance guide should be sent to Jay Guerber at the previously mentioned address in the FOR FURTHER INFORMATION CONTACT section. After consideration of all relevant material presented, including the Committee’s recommendation, and other information, it is found that finalizing the interim final rule, without change, as published in the Federal Register (72 FR 18345, April 12, 2007) will tend to effectuate the declared policy of the Act. PO 00000 Frm 00025 Fmt 4700 Sfmt 4700 41615 List of Subjects in 7 CFR Part 985 Marketing agreements, Oils and fats, Reporting and recordkeeping requirements, Spearmint oil. PART 985—MARKETING ORDER REGULATING THE HANDLING OF SPEARMINT OIL PRODUCED IN THE FAR WEST Accordingly, the interim final rule amending 7 CFR part 985, which was published at 71 FR 18345 on April, 12, 2007, is adopted as a final rule without change. I Dated: July 24, 2007. Lloyd C. Day, Administrator, Agricultural Marketing Service. [FR Doc. E7–14622 Filed 7–30–07; 8:45 am] BILLING CODE 3410–02–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–28813; Directorate Identifier 2007–SW–09–AD; Amendment 39– 15140; AD 2007–16–01] RIN 2120–AA64 Airworthiness Directives; Enstrom Helicopter Corporation Model F–28, F–28A, F–28C, F–28C–2, F–28C–2R, F– 28F, F–28F–R, 280, 280C, 280F, 280FX, TH–28, 480, and 480B Helicopters Federal Aviation Administration, DOT. ACTION: Final rule; request for comments. AGENCY: SUMMARY: This amendment adopts a new airworthiness directive (AD) for Enstrom Helicopter Corporation (Enstrom) Model F–28, F–28A, F–28C, F–28C–2, F–28C–2R, F–28F, F–28F–R, 280, 280C, 280F, 280FX, TH–28, 480, and 480B helicopters. This action requires a visual check to determine if a certain serial-numbered main rotor blade retention pin (retention pin) is installed, and removing and replacing any affected retention pin with an airworthy retention pin. This amendment is prompted by a report from the manufacturer that some retention pins were not manufactured in accordance with specifications cited on the engineering drawing. The actions specified in this AD are intended to prevent failure of a retention pin, separation of a main rotor blade from the helicopter, and subsequent loss of control of the helicopter. DATES: Effective August 15, 2007. E:\FR\FM\31JYR1.SGM 31JYR1 41616 Federal Register / Vol. 72, No. 146 / Tuesday, July 31, 2007 / Rules and Regulations rmajette on PROD1PC64 with RULES Comments for inclusion in the Rules Docket must be received on or before October 1, 2007. ADDRESSES: Use one of the following addresses to submit comments on this AD: • DOT Docket Web site: Go to http://dms.dot.gov and follow the instructions for sending your comments electronically; • Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your comments electronically; • Mail: 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: Deliver to the ‘‘Mail’’ address between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays; or • Fax: 202–493–2251. You may get the service information identified in this AD from Enstrom Helicopter Corporation, 2209 22nd Street, P.O. Box 490, Menominee, Michigan 49858–0490. EXAMINING THE DOCKET: You may examine the docket that contains the AD, any comments, and other information on the Internet at http:// dms.dot.gov, or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Operations office (telephone (800) 647– 5527) is located in Room W12–140 on the ground floor of the West Building at the street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after the DMS receives them. FOR FURTHER INFORMATION CONTACT: Gregory J. Michalik, Senior Aerospace Engineer, FAA, Small Airplane Directorate, Chicago Aircraft Certification Office, 2300 E. Devon Ave., Room 107, Des Plaines, Illinois 60018, telephone (847) 298–7135, fax (847) 294–7834. SUPPLEMENTARY INFORMATION: This amendment adopts a new AD for Enstrom Model F–28, F–28A, F–28C, F– 28C–2, F–28C–2R, F–28F, F–28F–R, 280, 280C, 280F, 280FX, TH–28, 480, and 480B helicopters with a retention pin, part number (P/N) 28–14007–3, installed, with a serial number (S/N) that is listed in the following table: RETENTION PIN S/N 04098–01 through 04098–56. 05018–01 through 05018–36. 05143–01 through 05143–56. 05341–1 through 05341–8. VerDate Aug<31>2005 13:44 Jul 30, 2007 Jkt 211001 This unsafe condition is likely to exist or develop on other helicopters of the 05341–10 through 05341–17. same type design. Therefore, this AD is 05341–19. being issued to prevent failure of a 05341–21 through 05341–33. retention pin, separation of a main rotor 05341–35 through 05341–42. blade from the helicopter, and 05341–44 through 05341–59. subsequent loss of control of the 05341–61. helicopter. This AD requires removing 05341–62. and replacing certain serial-numbered 05341–64 through 05341–71. 06214–3 through 06214–14. retention pins. The visual check 06214–16 through 06214–23. required by this AD may be performed 06214–25 through 06214–29. by an owner/operator (pilot), but must 06214–31. be entered into the aircraft records 06214–33 through 06214–35. showing compliance with paragraph (a) 06214–37 through 06214–57. of this AD in accordance with 14 CFR 06214–59 through 06214–68. 43.11 and 91.417(a)(2)(v). This AD allows a pilot to perform this check This action requires, before further because it involves only a visual check flight, visually checking each retention of the head of each retention pin to pin to determine if the S/N, which is marked on the head of the retention pin, determine the S/N. The short compliance time involved is listed in the Applicability section of is required because the previously this AD. If there is no serial number marked on the head of the retention pin described critical unsafe condition can (i.e., the retention pin head is blank), the adversely affect the controllability and structural integrity of the helicopter. retention pin does not need to be Therefore, removing and replacing each replaced and this visual check affected retention pin is required within constitutes a terminating action for the 5 hours TIS or within 30 days, requirements of this AD for that depending on the retention pin’s hours retention pin. If an affected retention TIS, which constitutes a very short time pin is installed, determining the retention pin’s number of hours time-in- period, and this AD must be issued immediately. service (TIS) and removing and Since a situation exists that requires replacing it with an airworthy retention the immediate adoption of this pin that has a S/N that is not listed in regulation, it is found that notice and the Applicability section of this AD is opportunity for prior public comment required: hereon are impracticable, and that good • Within the next 5 hours TIS or cause exists for making this amendment within 30 days, whichever occurs first, effective in less than 30 days. if the retention pin has 545 or more We estimate that this AD will affect hours TIS, or • On or before reaching 550 hours TIS 39 helicopters, and • Determining the S/N of all retention or within 30 days, whichever occurs pins (3 on each helicopter) will take first, if the retention pin has less than approximately 0.5 work hour; 545 hours TIS. • Determining the hours TIS of three This amendment is prompted by a affected retention pins will take report from the manufacturer that some approximately 1 work hour; and retention pins were manufactured from • Removing and replacing three steel that did not meet the specifications retention pins will take approximately 3 cited on the engineering drawing. The work hours at an average labor rate of actions specified in this AD are $80 per work hour. Required parts will intended to prevent failure of a cost approximately $680 per helicopter. retention pin, separation of a main rotor Based on these figures, we estimate the blade from the helicopter, and total cost impact of the AD on U.S. subsequent loss of control of the operators to be $1,040 per helicopter or helicopter. $40,560 if all retention pins get replaced We have reviewed Enstrom Helicopter on the entire fleet. Corporation Service Directive Bulletin (SDB) No. 0102 and Enstrom Helicopter Comments Invited Corporation SDB No. T–029, both dated This AD is a final rule that involves March 20, 2007, which specify visual requirements that affect flight safety and and magnetic particle inspections for was not preceded by notice and an cracks in certain serial-numbered opportunity for public comment; retention pins, and repairing or however, we invite you to submit any replacing retention pins in accordance written data, views, or arguments with certain inspection criteria. This AD regarding this AD. Send your comments does not require inspections for cracks to an address listed under ADDRESSES. but requires that each affected retention Include ‘‘Docket No. FAA–2007–28813; pin be replaced. Directorate Identifier 2007–SW–09–AD’’ PO 00000 RETENTION PIN S/N—Continued Frm 00026 Fmt 4700 Sfmt 4700 E:\FR\FM\31JYR1.SGM 31JYR1 Federal Register / Vol. 72, No. 146 / Tuesday, July 31, 2007 / Rules and Regulations at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the AD. We will consider all comments received by the closing date and may amend the AD in light of those comments. We will post all comments we receive, without change, to http:// dms.dot.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this AD. Using the search function of our docket Web site, you can find and read the comments to any of our dockets, including the name of the individual who sent the comment. You may review the DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78), or you may visit http://dms.dot.gov. rmajette on PROD1PC64 with RULES Regulatory Findings We have determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that the regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared an economic evaluation of the estimated costs to comply with VerDate Aug<31>2005 13:44 Jul 30, 2007 Jkt 211001 this AD. See the DMS to examine the economic evaluation. 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. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. Adoption of the Amendment Accordingly, pursuant to 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 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. Section 39.13 is amended by adding a new airworthiness directive to read as follows: I PO 00000 Frm 00027 Fmt 4700 Sfmt 4700 41617 2007–16–01 Enstrom Helicopter Corporation: Amendment 39–15140. Docket No. FAA–2007–28813; Directorate Identifier 2007–SW–09–AD. Applicability: Model F–28, F–28A, F–28C, F–28C–2, F–28C–2R, F–28F, F–28F–R, 280, 280C, 280F, 280FX, TH–28, 480, and 480B helicopters, with a main rotor blade retention pin (retention pin) having a serial number (S/ N) that is listed in the following table, installed, certificated in any category: RETENTION PIN S/N 04098–01 through 04098–56. 05018–01 through 05018–36. 05143–01 through 05143–56. 05341–1 through 05341–8. 05341–10 through 05341–17. 05341–19. 05341–21 through 05341–33. 05341–35 through 05341–42. 05341–44 through 05341–59. 05341–61. 05341–62. 05341–64 through 05341–71. 06214–3 through 06214–14. 06214–16 through 06214–23. 06214–25 through 06214–29. 06214–31. 06214–33 through 06214–35. 06214–37 through 06214–57. 06214–59 through 06214–68. Compliance: Required as indicated, unless accomplished previously. To prevent failure of a retention pin, separation of a main rotor blade from the helicopter, and subsequent loss of control of the helicopter, accomplish the following: (a) Before further flight, check the S/N that is marked on the head of each retention pin to see if it is a S/N that is listed in the Applicability section of this AD. See Figure 1 for the location of the S/N. If there is no serial number marked on the head of the retention pin (i.e., the retention pin head is blank), the retention pin does not need to be replaced and this determination constitutes a terminating action for the requirements of this AD for that retention pin. E:\FR\FM\31JYR1.SGM 31JYR1 Federal Register / Vol. 72, No. 146 / Tuesday, July 31, 2007 / Rules and Regulations (b) The visual check required by paragraph (a) of this AD may be performed by an owner/operator (pilot) holding at least a private pilot certificate, and must be entered into the aircraft records showing compliance with paragraph (a) of this AD in accordance with 14 CFR sections 43.11 and 91.417(a)(2)(v). (c) Determine the number of hours TIS for any affected retention pin and replace the retention pin with an airworthy retention pin as follows: (1) For a retention pin with 545 or more hours TIS, remove the retention pin and replace it with an airworthy retention pin with a S/N that is not listed in the Applicability section of this AD within the next 5 hours TIS or within 30 days, whichever occurs first. (2) For a retention pin with less than 545 hours TIS, remove the retention pin and replace it with an airworthy retention pin with a S/N that is not listed in the Applicability section of this AD on or before reaching 550 hours TIS or within 30 days, whichever occurs first. Note: Enstrom Service Directive Bulletin No. T–029 and Enstrom Service Directive Bulletin 0102, both dated March 20, 2007, pertain to the subject of this AD. (d) Removing any affected retention pin and replacing it with an airworthy retention pin that is not included in the Applicability section of this AD is considered a terminating action for the requirements of this AD for that retention pin. VerDate Aug<31>2005 13:44 Jul 30, 2007 Jkt 211001 (e) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Contact the Manager, Chicago Aircraft Certification Office, FAA, ATTN: Gregory J. Michalik, Senior Aerospace Engineer, 2300 E. Devon Ave., Room 107, Des Plaines, Illinois, 60018, telephone (847) 298–7135, fax (847) 294–7834, for information about previously approved alternative methods of compliance. (f) This amendment becomes effective on August 15, 2007. Issued in Fort Worth, Texas, on July 24, 2007. David A. Downey, Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 07–3711 Filed 7–30–07; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF HEALTH AND HUMAN SERVICES Food and Drug Administration 21 CFR Part 558 New Animal Drugs For Use in Animal Feeds; Ractopamine and Tylosin AGENCY: Food and Drug Administration, HHS. PO 00000 Frm 00028 Fmt 4700 Sfmt 4700 ACTION: Final rule. SUMMARY: The Food and Drug Administration (FDA) is amending the animal drug regulations to reflect approval of a supplemental new animal drug application (NADA) filed by Elanco Animal Health. The supplemental NADA revises the indications for use of two-way combination Type B and Type C medicated swine feeds formulated with ractopamine hydrochloride and tylosin phosphate. DATES: This rule is effective July 31, 2007. FOR FURTHER INFORMATION CONTACT: Harlan J. Howard, Center for Veterinary Medicine (HFV–120), Food and Drug Administration, 7500 Standish Pl., Rockville, MD 20855, 301–827–0231, email: harlan.howard@fda.hhs.gov. SUPPLEMENTARY INFORMATION: Elanco Animal Health, a Division of Eli Lilly & Co., Lilly Corporate Center, Indianapolis, IN 46285, filed a supplement to NADA 141–172 that provides for use of two-way combination Type B and Type C medicated swine feeds formulated with PAYLEAN (ractopamine hydrochloride) and TYLAN (tylosin phosphate) single- E:\FR\FM\31JYR1.SGM 31JYR1 ER31JY07.016</GPH> rmajette on PROD1PC64 with RULES 41618

Agencies

[Federal Register Volume 72, Number 146 (Tuesday, July 31, 2007)]
[Rules and Regulations]
[Pages 41615-41618]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 07-3711]


=======================================================================
-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-28813; Directorate Identifier 2007-SW-09-AD; 
Amendment 39-15140; AD 2007-16-01]
RIN 2120-AA64


Airworthiness Directives; Enstrom Helicopter Corporation Model F-
28, F-28A, F-28C, F-28C-2, F-28C-2R, F-28F, F-28F-R, 280, 280C, 280F, 
280FX, TH-28, 480, and 480B Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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

SUMMARY: This amendment adopts a new airworthiness directive (AD) for 
Enstrom Helicopter Corporation (Enstrom) Model F-28, F-28A, F-28C, F-
28C-2, F-28C-2R, F-28F, F-28F-R, 280, 280C, 280F, 280FX, TH-28, 480, 
and 480B helicopters. This action requires a visual check to determine 
if a certain serial-numbered main rotor blade retention pin (retention 
pin) is installed, and removing and replacing any affected retention 
pin with an airworthy retention pin. This amendment is prompted by a 
report from the manufacturer that some retention pins were not 
manufactured in accordance with specifications cited on the engineering 
drawing. The actions specified in this AD are intended to prevent 
failure of a retention pin, separation of a main rotor blade from the 
helicopter, and subsequent loss of control of the helicopter.

DATES: Effective August 15, 2007.

[[Page 41616]]

    Comments for inclusion in the Rules Docket must be received on or 
before October 1, 2007.

ADDRESSES: Use one of the following addresses to submit comments on 
this AD:
     DOT Docket Web site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically;
     Government-wide rulemaking Web site: Go to http://
www.regulations.gov and follow the instructions for sending your 
comments electronically;
     Mail: 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: Deliver to the ``Mail'' address between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays; or
     Fax: 202-493-2251.
    You may get the service information identified in this AD from 
Enstrom Helicopter Corporation, 2209 22nd Street, P.O. Box 490, 
Menominee, Michigan 49858-0490.

Examining the Docket: You may examine the docket that contains the AD, 
any comments, and other information on the Internet at http://
dms.dot.gov, or in person at the Docket Operations office between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays. The 
Docket Operations office (telephone (800) 647-5527) is located in Room 
W12-140 on the ground floor of the West Building at the street address 
stated in the ADDRESSES section. Comments will be available in the AD 
docket shortly after the DMS receives them.

FOR FURTHER INFORMATION CONTACT: Gregory J. Michalik, Senior Aerospace 
Engineer, FAA, Small Airplane Directorate, Chicago Aircraft 
Certification Office, 2300 E. Devon Ave., Room 107, Des Plaines, 
Illinois 60018, telephone (847) 298-7135, fax (847) 294-7834.

SUPPLEMENTARY INFORMATION: This amendment adopts a new AD for Enstrom 
Model F-28, F-28A, F-28C, F-28C-2, F-28C-2R, F-28F, F-28F-R, 280, 280C, 
280F, 280FX, TH-28, 480, and 480B helicopters with a retention pin, 
part number (P/N) 28-14007-3, installed, with a serial number (S/N) 
that is listed in the following table:

                            Retention Pin S/N
------------------------------------------------------------------------
 
-------------------------------------------------------------------------
04098-01 through 04098-56.
05018-01 through 05018-36.
05143-01 through 05143-56.
05341-1 through 05341-8.
05341-10 through 05341-17.
05341-19.
05341-21 through 05341-33.
05341-35 through 05341-42.
05341-44 through 05341-59.
05341-61.
05341-62.
05341-64 through 05341-71.
06214-3 through 06214-14.
06214-16 through 06214-23.
06214-25 through 06214-29.
06214-31.
06214-33 through 06214-35.
06214-37 through 06214-57.
06214-59 through 06214-68.
------------------------------------------------------------------------

This action requires, before further flight, visually checking each 
retention pin to determine if the S/N, which is marked on the head of 
the retention pin, is listed in the Applicability section of this AD. 
If there is no serial number marked on the head of the retention pin 
(i.e., the retention pin head is blank), the retention pin does not 
need to be replaced and this visual check constitutes a terminating 
action for the requirements of this AD for that retention pin. If an 
affected retention pin is installed, determining the retention pin's 
number of hours time-in-service (TIS) and removing and replacing it 
with an airworthy retention pin that has a S/N that is not listed in 
the Applicability section of this AD is required:
     Within the next 5 hours TIS or within 30 days, whichever 
occurs first, if the retention pin has 545 or more hours TIS, or
     On or before reaching 550 hours TIS or within 30 days, 
whichever occurs first, if the retention pin has less than 545 hours 
TIS.

This amendment is prompted by a report from the manufacturer that some 
retention pins were manufactured from steel that did not meet the 
specifications cited on the engineering drawing. The actions specified 
in this AD are intended to prevent failure of a retention pin, 
separation of a main rotor blade from the helicopter, and subsequent 
loss of control of the helicopter.
    We have reviewed Enstrom Helicopter Corporation Service Directive 
Bulletin (SDB) No. 0102 and Enstrom Helicopter Corporation SDB No. T-
029, both dated March 20, 2007, which specify visual and magnetic 
particle inspections for cracks in certain serial-numbered retention 
pins, and repairing or replacing retention pins in accordance with 
certain inspection criteria. This AD does not require inspections for 
cracks but requires that each affected retention pin be replaced.
    This unsafe condition is likely to exist or develop on other 
helicopters of the same type design. Therefore, this AD is being issued 
to prevent failure of a retention pin, separation of a main rotor blade 
from the helicopter, and subsequent loss of control of the helicopter. 
This AD requires removing and replacing certain serial-numbered 
retention pins. The visual check required by this AD may be performed 
by an owner/operator (pilot), but must be entered into the aircraft 
records showing compliance with paragraph (a) of this AD in accordance 
with 14 CFR 43.11 and 91.417(a)(2)(v). This AD allows a pilot to 
perform this check because it involves only a visual check of the head 
of each retention pin to determine the S/N.
    The short compliance time involved is required because the 
previously described critical unsafe condition can adversely affect the 
controllability and structural integrity of the helicopter. Therefore, 
removing and replacing each affected retention pin is required within 5 
hours TIS or within 30 days, depending on the retention pin's hours 
TIS, which constitutes a very short time period, and this AD must be 
issued immediately.
    Since a situation exists that requires the immediate adoption of 
this regulation, it is found that notice and opportunity for prior 
public comment hereon are impracticable, and that good cause exists for 
making this amendment effective in less than 30 days.
    We estimate that this AD will affect 39 helicopters, and
     Determining the S/N of all retention pins (3 on each 
helicopter) will take approximately 0.5 work hour;
     Determining the hours TIS of three affected retention pins 
will take approximately 1 work hour; and
     Removing and replacing three retention pins will take 
approximately 3 work hours at an average labor rate of $80 per work 
hour. Required parts will cost approximately $680 per helicopter. Based 
on these figures, we estimate the total cost impact of the AD on U.S. 
operators to be $1,040 per helicopter or $40,560 if all retention pins 
get replaced on the entire fleet.

Comments Invited

    This AD is a final rule that involves requirements that affect 
flight safety and was not preceded by notice and an opportunity for 
public comment; however, we invite you to submit any written data, 
views, or arguments regarding this AD. Send your comments to an address 
listed under ADDRESSES. Include ``Docket No. FAA-2007-28813; 
Directorate Identifier 2007-SW-09-AD''

[[Page 41617]]

at the beginning of your comments. We specifically invite comments on 
the overall regulatory, economic, environmental, and energy aspects of 
the AD. We will consider all comments received by the closing date and 
may amend the AD in light of those comments.
    We will post all comments we receive, without change, to http://
dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact with FAA 
personnel concerning this AD. Using the search function of our docket 
Web site, you can find and read the comments to any of our dockets, 
including the name of the individual who sent the comment. You may 
review the DOT's complete Privacy Act Statement in the Federal Register 
published on April 11, 2000 (65 FR 19477-78), or you may visit http://
dms.dot.gov.

Regulatory Findings

    We have determined that this AD will not have federalism 
implications under Executive Order 13132. This AD will not have a 
substantial direct effect on the States, on the relationship between 
the national Government and the States, or on the distribution of power 
and responsibilities among the various levels of government.
    For the reasons discussed above, I certify that the regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979); and
    3. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared an economic evaluation of the estimated costs to comply 
with this AD. See the DMS to examine the economic evaluation.

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.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

Adoption of the Amendment

0
Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends part 39 of 
the Federal Aviation Regulations (14 CFR part 39) as follows:

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13  [Amended]

0
2. Section 39.13 is amended by adding a new airworthiness directive to 
read as follows:

2007-16-01 Enstrom Helicopter Corporation: Amendment 39-15140. 
Docket No. FAA-2007-28813; Directorate Identifier 2007-SW-09-AD.

    Applicability: Model F-28, F-28A, F-28C, F-28C-2, F-28C-2R, F-
28F, F-28F-R, 280, 280C, 280F, 280FX, TH-28, 480, and 480B 
helicopters, with a main rotor blade retention pin (retention pin) 
having a serial number (S/N) that is listed in the following table, 
installed, certificated in any category:

                            Retention Pin S/N
------------------------------------------------------------------------
 
-------------------------------------------------------------------------
04098-01 through 04098-56.
05018-01 through 05018-36.
05143-01 through 05143-56.
05341-1 through 05341-8.
05341-10 through 05341-17.
05341-19.
05341-21 through 05341-33.
05341-35 through 05341-42.
05341-44 through 05341-59.
05341-61.
05341-62.
05341-64 through 05341-71.
06214-3 through 06214-14.
06214-16 through 06214-23.
06214-25 through 06214-29.
06214-31.
06214-33 through 06214-35.
06214-37 through 06214-57.
06214-59 through 06214-68.
------------------------------------------------------------------------

    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent failure of a retention pin, separation of a main 
rotor blade from the helicopter, and subsequent loss of control of 
the helicopter, accomplish the following:
    (a) Before further flight, check the S/N that is marked on the 
head of each retention pin to see if it is a S/N that is listed in 
the Applicability section of this AD. See Figure 1 for the location 
of the S/N. If there is no serial number marked on the head of the 
retention pin (i.e., the retention pin head is blank), the retention 
pin does not need to be replaced and this determination constitutes 
a terminating action for the requirements of this AD for that 
retention pin.

[[Page 41618]]

[GRAPHIC] [TIFF OMITTED] TR31JY07.016

    (b) The visual check required by paragraph (a) of this AD may be 
performed by an owner/operator (pilot) holding at least a private 
pilot certificate, and must be entered into the aircraft records 
showing compliance with paragraph (a) of this AD in accordance with 
14 CFR sections 43.11 and 91.417(a)(2)(v).
    (c) Determine the number of hours TIS for any affected retention 
pin and replace the retention pin with an airworthy retention pin as 
follows:
    (1) For a retention pin with 545 or more hours TIS, remove the 
retention pin and replace it with an airworthy retention pin with a 
S/N that is not listed in the Applicability section of this AD 
within the next 5 hours TIS or within 30 days, whichever occurs 
first.
    (2) For a retention pin with less than 545 hours TIS, remove the 
retention pin and replace it with an airworthy retention pin with a 
S/N that is not listed in the Applicability section of this AD on or 
before reaching 550 hours TIS or within 30 days, whichever occurs 
first.

    Note: Enstrom Service Directive Bulletin No. T-029 and Enstrom 
Service Directive Bulletin 0102, both dated March 20, 2007, pertain 
to the subject of this AD.

    (d) Removing any affected retention pin and replacing it with an 
airworthy retention pin that is not included in the Applicability 
section of this AD is considered a terminating action for the 
requirements of this AD for that retention pin.
    (e) To request a different method of compliance or a different 
compliance time for this AD, follow the procedures in 14 CFR 39.19. 
Contact the Manager, Chicago Aircraft Certification Office, FAA, 
ATTN: Gregory J. Michalik, Senior Aerospace Engineer, 2300 E. Devon 
Ave., Room 107, Des Plaines, Illinois, 60018, telephone (847) 298-
7135, fax (847) 294-7834, for information about previously approved 
alternative methods of compliance.
    (f) This amendment becomes effective on August 15, 2007.

    Issued in Fort Worth, Texas, on July 24, 2007.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 07-3711 Filed 7-30-07; 8:45 am]
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