Airworthiness Directives; Arrow Falcon Exporters, Inc. (previously Utah State University) et al. Model HH-1K, TH-1F, TH-1L, UH-1A, UH-1B, UH-1E, UH-1F, UH-1H, UH-1L, and UH-1P Helicopters; and Southwest Florida Aviation Model UH-1B (SW204 and SW204HP) and UH-1H (SW205) Helicopters, 26889-26891 [2010-11419]

Download as PDF Federal Register / Vol. 75, No. 92 / Thursday, May 13, 2010 / Proposed Rules Regulatory Findings We have determined that this proposed AD would not have federalism implications under Executive Order 13132. Additionally, this proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that the proposed regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a draft economic evaluation of the estimated costs to comply with this proposed AD. See the AD docket to examine the draft 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. cprice-sewell on DSKHWCL6B1PROD with PROPOSALS List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. PART 39—AIRWORTHINESS DIRECTIVES [Amended] Jkt 220001 Sikorsky Aircraft Corp.: Docket No. FAA– 2010–0490; Directorate Identifier 2010– SW–037–AD. Applicability Model S–70A and S–70C helicopters, tail gearbox output bevel gear (gear), part number 70358–06620, certificated in any category. Compliance Required as indicated. To prevent a tail rotor separating, loss of tail rotor control, and subsequent loss of control of the helicopter, do the following: (a) Within 500 hours time-in-service (TIS), unless accomplished previously, and thereafter at intervals not to exceed 500 hours TIS, remove the tail rotor servo control and pitch beam shaft, and using a Level II Ultrasonic Testing Technician or equivalent, ultransonic inspect the gear for a crack. Ultrasonic inspect the gear by following paragraphs A.(5)a. through A(5)n., Note 7, Special Service Instructions (SSI) No. 70– 121A, Revision A, dated May 21, 2009. If you find a crack, before further flight, replace the gear with an airworthy gear. (b) 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, Boston Aircraft Certification Office, FAA, ATTN: Terry Fahr, Aviation Safety Engineer, Boston Aircraft Certification Office, 12 New England Executive Park, Burlington, MA 01803, telephone (781) 238–7155, fax (781) 238– 7170, for information about previously approved alternative methods of compliance. (c) The Joint Aircraft System/Component (JASC) Code is: 6520: Tail rotor gearbox. Issued in Fort Worth, Texas, on May 3, 2010. Mark R. Schilling, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2010–11423 Filed 5–12–10; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00002 Fmt 4702 14 CFR Part 39 [Docket No. FAA–2010–0488; Directorate Identifier 2008–SW–20–AD] RIN 2120–AA64 2. Section 39.13 is amended by adding a new airworthiness directive to read as follows: Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration proposes to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows: 14:29 May 12, 2010 Federal Aviation Administration Authority: 49 U.S.C. 106(g), 40113, 44701. The Proposed Amendment VerDate Mar<15>2010 DEPARTMENT OF TRANSPORTATION 1. The authority citation for part 39 continues to read as follows: § 39.13 26889 Sfmt 4702 Airworthiness Directives; Arrow Falcon Exporters, Inc. (previously Utah State University) et al. Model HH–1K, TH–1F, TH–1L, UH–1A, UH–1B, UH–1E, UH–1F, UH–1H, UH–1L, and UH–1P Helicopters; and Southwest Florida Aviation Model UH–1B (SW204 and SW204HP) and UH–1H (SW205) Helicopters AGENCY: Federal Aviation Administration, DOT. ACTION: Notice of proposed rulemaking (NPRM). SUMMARY: This document proposes adopting a new airworthiness directive (AD) for the specified model helicopters. The AD would require inspecting each affected tail rotor blade (blade) forward tip weight retention block (tip block) and the aft tip closure (tip closure) for adhesive bond voids and removing any blade with an excessive void from service. This AD would also require modifying certain blades by installing shear pins and tip closure rivets. This proposal is prompted by five occurrences of missing tip blocks or tip closures resulting in minor to substantial damage to blades installed on Bell Model 212 and 412 helicopters. The actions specified by the proposed AD are intended to prevent loss of a tip block or tip closure, loss of a blade, and subsequent loss of control of the helicopter. DATES: Comments must be received on or before July 12, 2010. ADDRESSES: Use one of the following addresses to submit comments on this proposed AD: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. You may get the service information identified in this proposed AD from Bell E:\FR\FM\13MYP1.SGM 13MYP1 26890 Federal Register / Vol. 75, No. 92 / Thursday, May 13, 2010 / Proposed Rules Helicopter Textron, Inc., P.O. Box 482, Fort Worth, Texas 76101, telephone (817) 280–3391, fax (817) 280–6466. You may examine the comments to this proposed AD in the AD docket on the Internet at https:// www.regulations.gov. FOR FURTHER INFORMATION CONTACT: DOT/FAA Southwest Region, Michael Kohner, ASW–170, Aviation Safety Engineer, Rotorcraft Directorate, Rotorcraft Certification Office, 2601 Meacham Blvd., Fort Worth, Texas 76137, telephone (817) 222–5170, fax (817) 222–5783. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to submit any written data, views, or arguments regarding this proposed AD. Send your comments to the address listed under the caption ADDRESSES. Include the docket number ‘‘FAA–2010–0488, Directorate Identifier 2008–SW–20–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date and may amend the proposed AD in light of those comments. We will post all comments we receive, without change, to https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this proposed rulemaking. Using the search function of the docket Web site, you can find and read the comments to any of our dockets, including the name of the individual who sent or signed the comment. You may review the DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 15477). cprice-sewell on DSKHWCL6B1PROD with PROPOSALS Examining the Docket You may examine the docket that contains the proposed AD, any comments, and other information 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 receipt. Discussion This document proposes adopting a new AD for the specified model VerDate Mar<15>2010 14:29 May 12, 2010 Jkt 220001 helicopters. The AD would require inspecting each affected blade tip block and the tip closure for adhesive bond voids and removing from service any blade with an excessive void. This AD would also require modifying certain blades by installing shear pins and tip closure rivets. This proposal is prompted by five occurrences of missing tip blocks or tip closures resulting in minor to substantial damage to blades installed on Bell 212 and 412 helicopters. This condition, if not corrected, could result in loss of a tip block or tip closure, loss of a blade, and subsequent loss of control of the helicopter. AD 2002–09–04, Amendment 39– 12737 (67 FR 22349, May 3, 2002) was issued for the Bell Model 205A, 205A– 1, 205B, 212, 412, 412CF, and 412EP helicopters and contained the same requirements proposed in this AD. AD 2007–22–02, Amendment 39–15238 (72 FR 60760, October 26, 2007), superseded AD 2002–09–04 to expand the applicability to include other part and serial-numbered blades. Some of the blades in the applicability of AD 2007–22–02 are eligible for installation on helicopters included in this proposed AD. The helicopters included in this proposal may have an FAAapproved modification that increases the helicopter’s power rating to the equivalent of the twin-engine Bell Model 205B or 212 helicopter power rating. The Bell Model 205B and 212 helicopters are addressed in AD 2007– 22–02. Consequently, the inspections and modifications required by AD 2007–22–02 also need to be mandated for the helicopters included in this proposal. We have reviewed Bell Helicopter Textron Alert Service Bulletin No. 212– 00–111, Revision D, dated March 18, 2005 (ASB), which describes procedures for inspecting and modifying certain blades. The ASB was issued as a result of an investigation of an in-flight loss of a tail rotor blade tip block, part number (P/N) 212–010–750–105. The investigation revealed the countersunk screws retaining the tip block were installed incorrectly, resulting in inadequate tip block retention. Reports have also been submitted about loss of the tip closures from other blades possibly due to inadequate adhesive bonding in this area. We have identified an unsafe condition that is likely to exist or develop on other helicopters of these same type designs. Therefore, the proposed AD would require the following: • Inspecting the affected blades’ tip block and tip closure for voids. PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 • Removing any blade that has a void in excess of specified limitations. • Modifying certain blades by installing shear pins. • Modifying all affected blades by installing tip closure rivets and reidentifying the modified blades by adding an ‘‘FM’’ after the P/N. The actions would be required to be done by following specified portions of the ASB described previously. We estimate that this proposed AD would affect 716 helicopters of U.S. registry, but only 25 of those helicopters will have the increased power rating. It would take about 1 work hour to review the helicopter records. Also, it would take about 3 work hours to inspect the affected blades, install the shear pins and tip closure rivets, reidentify, and dynamically balance the blade set at an average labor rate of $85 per work hour. Required supplies would cost about $45 per helicopter. Based on these figures, the total cost impact of the proposed AD on U.S. operators would be $68,360. These costs are assuming that the records review to determine the applicability would be accomplished on the entire fleet of 716 helicopters. These costs also assume that the blade sets are installed on 25 helicopters with the FAA-approved modification and that those helicopters would need to be inspected and repaired. Regulatory Findings We have determined that this proposed AD would not have federalism implications under Executive Order 13132. Additionally, this proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that the proposed regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a draft economic evaluation of the estimated costs to comply with this proposed AD. See the AD docket to examine the draft 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, E:\FR\FM\13MYP1.SGM 13MYP1 Federal Register / Vol. 75, No. 92 / Thursday, May 13, 2010 / Proposed Rules 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, Incorporation by reference, Safety. The Proposed Amendment Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration proposes to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] cprice-sewell on DSKHWCL6B1PROD with PROPOSALS 2. Section 39.13 is amended by adding a new airworthiness directive to read as follows: Arrow Falcon Exporters, Inc. (previously Utah State University); Firefly Aviation Helicopter Services (previously Erickson Air-Crane Co.); California Department of Forestry; Garlick Helicopters, Inc.; Global Helicopter Technology, Inc.; Hagglund Helicopters, LLC (previously Western International Aviation, Inc.); International Helicopters, Inc.; Precision Helicopters, LLC; Robinson Air Crane, Inc.; San Joaquin Helicopters (previously Hawkins and Powers Aviation, Inc.); S.M.&T. Aircraft (previously US Helicopters, Inc., UNC Helicopter, Inc., Southern Aero Corporation, and Wilco Aviation); Smith Helicopters; Southern Helicopter, Inc.; Southwest Florida Aviation International, Inc. (previously Jamie R. Hill and Southwest Florida Aviation); Tamarack Helicopters, Inc. (previously Ranger Helicopter Services, Inc.); US Helicopter, Inc. (previously UNC Helicopter, Inc.); West Coast Fabrication; and Williams Helicopter Corporation (previously Scott Paper Co.) Model HH–1K, TH–1F, TH–1L, UH–1A, VerDate Mar<15>2010 14:29 May 12, 2010 Jkt 220001 UH–1B, UH–1E, UH–1F, UH–1H, UH–1L, and UH–1P Helicopters; and Southwest Florida Aviation Model UH–1B (SW204 and SW204HP) and UH–1H (SW205) Helicopters: Docket No. FAA–2010– 0488; Directorate Identifier 2008–SW– 20–AD. Applicability: Model HH–1K, TH–1F, TH– 1L, UH–1A, UH–1B, UH–1E, UH–1F, UH–1H, UH–1L, and UH–1P helicopters, and Southwest Florida Aviation Model UH–1B series (SW204 series and SW204HP) and UH–1H series (SW205 series) helicopters, with a tail rotor blade (blade), part number (P/N) 212–010–750–009 through –129, all serial numbers except serial numbers with a prefix of ‘‘A’’ or ‘‘AFS,’’ and the number 11926, 13351, 13367, 13393, 13400, 13402, 13515, 13540, 13568, 13595 through 13602, 13619, and subsequent larger numbers, installed, certificated in any category. Compliance: Within 100 hours time-inservice, unless accomplished previously. To prevent loss of the forward tip weight retention block (tip block) or aft tip closure (tip closure), loss of the blade, and subsequent loss of control of the helicopter, do the following: Note 1: A blade inspected and modified by following either AD 2002–09–04 or 2007–22– 02, for the Bell Helicopter Textron (Bell) Model 205A, 205A–1, 205B, 212, 412, 412CF, and 412EP helicopters satisfies the requirements of this AD. (a) Inspect the tip block and tip closure of each blade for voids. Remove from service any blade with a void in excess of that allowed by the applicable maintenance or Component Repair and Overhaul Manual limitations. (b) Inspect the tip block attachment countersink screws in the four locations to determine if the head of each countersunk screw is flush with the surface of the abrasion strip. The locations of these four screws are depicted on Figure 1 of Bell Alert Service Bulletin 212–00–111, Revision D, dated March 18, 2005 (ASB). If any of these screws are set below the surface of the abrasion strip or are covered with filler material, install shear pins by following the Accomplishment Instructions, Part A, Shear Pin Installation paragraphs, of the ASB. (c) Install the tip closure rivets on each blade, re-identify the modified blade by adding an ‘‘FM’’ after the P/N, and dynamically balance the tail rotor hub assembly by following the Accomplishment Instructions, Part B, Aft Tip Closure Rivet Installation paragraphs, of the ASB. (d) 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, Rotorcraft Certification Office, Rotorcraft Directorate, ATTN: DOT/FAA Southwest Region, Michael Kohner, ASW–170, Aviation Safety Engineer, 2601 Meacham Blvd., Fort Worth, Texas 76137, telephone (817) 222–5170, fax (817) 222–5783, for information about previously approved alternative methods of compliance. PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 26891 Issued in Fort Worth, Texas, on May 3, 2010. Mark R. Schilling, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2010–11419 Filed 5–12–10; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 71 Proposed Modification of the Detroit, MI, Class B Airspace Area; Public Meetings AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of public meetings. SUMMARY: This notice announces three fact-finding informal airspace meetings to solicit information from airspace users and others concerning a proposal to revise the Class B airspace area at Detroit, MI. The purpose of these meetings is to provide interested parties an opportunity to present views, recommendations, and comments on the proposal. All comments received during these meetings will be considered prior to any revision or issuance of a notice of proposed rulemaking. DATES: The informal airspace meetings will be held on Tuesday, July 20, 2010, at 1:30 p.m.; Wednesday, July 21, 2010, at 5 p.m.; and Thursday, July 22, 2010, at 7:30 p.m. Comments must be received on or before September 6, 2010. ADDRESSES: (1) The meeting on Tuesday, July 20, 2010, will be held at Troy Holiday Inn, 2537 Rochester Court, Troy, MI 48083. (2) The meeting on Wednesday, July 21, 2010, will be held at Eastern Michigan University, Student Event Center, Ballroom B, 2nd Floor, 900 Oakwood Street, Ypsilanti, MI 48197. (3) The meeting on Thursday, July 22, 2010, will be held at Monroe Holiday Inn Express, 1225 North Dixie Highway, Monroe, MI 48162. Comments: Send comments on the proposal, in triplicate, to: Anthony D. Roetzel, Manager, Operations Support Group, Central Service Center, Air Traffic Organization, Federal Aviation Administration, 2601 Meacham Boulevard, Fort Worth, Texas 76137, or by fax to (817) 321–7649. FOR FURTHER INFORMATION CONTACT: Tim Funari, FAA Detroit Metro (DTW) ATCT, Building 801, Detroit Metro Airport, Detroit, MI 48242; (734) 955– 5000. SUPPLEMENTARY INFORMATION: E:\FR\FM\13MYP1.SGM 13MYP1

Agencies

[Federal Register Volume 75, Number 92 (Thursday, May 13, 2010)]
[Proposed Rules]
[Pages 26889-26891]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-11419]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-0488; Directorate Identifier 2008-SW-20-AD]
RIN 2120-AA64


Airworthiness Directives; Arrow Falcon Exporters, Inc. 
(previously Utah State University) et al. Model HH-1K, TH-1F, TH-1L, 
UH-1A, UH-1B, UH-1E, UH-1F, UH-1H, UH-1L, and UH-1P Helicopters; and 
Southwest Florida Aviation Model UH-1B (SW204 and SW204HP) and UH-1H 
(SW205) Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: This document proposes adopting a new airworthiness directive 
(AD) for the specified model helicopters. The AD would require 
inspecting each affected tail rotor blade (blade) forward tip weight 
retention block (tip block) and the aft tip closure (tip closure) for 
adhesive bond voids and removing any blade with an excessive void from 
service. This AD would also require modifying certain blades by 
installing shear pins and tip closure rivets. This proposal is prompted 
by five occurrences of missing tip blocks or tip closures resulting in 
minor to substantial damage to blades installed on Bell Model 212 and 
412 helicopters. The actions specified by the proposed AD are intended 
to prevent loss of a tip block or tip closure, loss of a blade, and 
subsequent loss of control of the helicopter.

DATES: Comments must be received on or before July 12, 2010.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD:
     Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    You may get the service information identified in this proposed AD 
from Bell

[[Page 26890]]

Helicopter Textron, Inc., P.O. Box 482, Fort Worth, Texas 76101, 
telephone (817) 280-3391, fax (817) 280-6466.
    You may examine the comments to this proposed AD in the AD docket 
on the Internet at https://www.regulations.gov.

FOR FURTHER INFORMATION CONTACT: DOT/FAA Southwest Region, Michael 
Kohner, ASW-170, Aviation Safety Engineer, Rotorcraft Directorate, 
Rotorcraft Certification Office, 2601 Meacham Blvd., Fort Worth, Texas 
76137, telephone (817) 222-5170, fax (817) 222-5783.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to submit any written data, views, or arguments 
regarding this proposed AD. Send your comments to the address listed 
under the caption ADDRESSES. Include the docket number ``FAA-2010-0488, 
Directorate Identifier 2008-SW-20-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the proposed AD. We will 
consider all comments received by the closing date and may amend the 
proposed AD in light of those comments.
    We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact 
with FAA personnel concerning this proposed rulemaking. Using the 
search function of the docket Web site, you can find and read the 
comments to any of our dockets, including the name of the individual 
who sent or signed the comment. You may review the DOT's complete 
Privacy Act Statement in the Federal Register published on April 11, 
2000 (65 FR 15477).

Examining the Docket

    You may examine the docket that contains the proposed AD, any 
comments, and other information 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 receipt.

Discussion

    This document proposes adopting a new AD for the specified model 
helicopters. The AD would require inspecting each affected blade tip 
block and the tip closure for adhesive bond voids and removing from 
service any blade with an excessive void. This AD would also require 
modifying certain blades by installing shear pins and tip closure 
rivets. This proposal is prompted by five occurrences of missing tip 
blocks or tip closures resulting in minor to substantial damage to 
blades installed on Bell 212 and 412 helicopters. This condition, if 
not corrected, could result in loss of a tip block or tip closure, loss 
of a blade, and subsequent loss of control of the helicopter.
    AD 2002-09-04, Amendment 39-12737 (67 FR 22349, May 3, 2002) was 
issued for the Bell Model 205A, 205A-1, 205B, 212, 412, 412CF, and 
412EP helicopters and contained the same requirements proposed in this 
AD. AD 2007-22-02, Amendment 39-15238 (72 FR 60760, October 26, 2007), 
superseded AD 2002-09-04 to expand the applicability to include other 
part and serial-numbered blades. Some of the blades in the 
applicability of AD 2007-22-02 are eligible for installation on 
helicopters included in this proposed AD. The helicopters included in 
this proposal may have an FAA-approved modification that increases the 
helicopter's power rating to the equivalent of the twin-engine Bell 
Model 205B or 212 helicopter power rating. The Bell Model 205B and 212 
helicopters are addressed in AD 2007-22-02. Consequently, the 
inspections and modifications required by AD 2007-22-02 also need to be 
mandated for the helicopters included in this proposal.
    We have reviewed Bell Helicopter Textron Alert Service Bulletin No. 
212-00-111, Revision D, dated March 18, 2005 (ASB), which describes 
procedures for inspecting and modifying certain blades. The ASB was 
issued as a result of an investigation of an in-flight loss of a tail 
rotor blade tip block, part number (P/N) 212-010-750-105. The 
investigation revealed the countersunk screws retaining the tip block 
were installed incorrectly, resulting in inadequate tip block 
retention. Reports have also been submitted about loss of the tip 
closures from other blades possibly due to inadequate adhesive bonding 
in this area.
    We have identified an unsafe condition that is likely to exist or 
develop on other helicopters of these same type designs. Therefore, the 
proposed AD would require the following:
     Inspecting the affected blades' tip block and tip closure 
for voids.
     Removing any blade that has a void in excess of specified 
limitations.
     Modifying certain blades by installing shear pins.
     Modifying all affected blades by installing tip closure 
rivets and reidentifying the modified blades by adding an ``FM'' after 
the P/N.
    The actions would be required to be done by following specified 
portions of the ASB described previously.
    We estimate that this proposed AD would affect 716 helicopters of 
U.S. registry, but only 25 of those helicopters will have the increased 
power rating. It would take about 1 work hour to review the helicopter 
records. Also, it would take about 3 work hours to inspect the affected 
blades, install the shear pins and tip closure rivets, reidentify, and 
dynamically balance the blade set at an average labor rate of $85 per 
work hour. Required supplies would cost about $45 per helicopter. Based 
on these figures, the total cost impact of the proposed AD on U.S. 
operators would be $68,360. These costs are assuming that the records 
review to determine the applicability would be accomplished on the 
entire fleet of 716 helicopters. These costs also assume that the blade 
sets are installed on 25 helicopters with the FAA-approved modification 
and that those helicopters would need to be inspected and repaired.

Regulatory Findings

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

[[Page 26891]]

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, Incorporation by 
reference, Safety.

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13  [Amended]

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

Arrow Falcon Exporters, Inc. (previously Utah State University); 
Firefly Aviation Helicopter Services (previously Erickson Air-Crane 
Co.); California Department of Forestry; Garlick Helicopters, Inc.; 
Global Helicopter Technology, Inc.; Hagglund Helicopters, LLC 
(previously Western International Aviation, Inc.); International 
Helicopters, Inc.; Precision Helicopters, LLC; Robinson Air Crane, 
Inc.; San Joaquin Helicopters (previously Hawkins and Powers 
Aviation, Inc.); S.M.&T. Aircraft (previously US Helicopters, Inc., 
UNC Helicopter, Inc., Southern Aero Corporation, and Wilco 
Aviation); Smith Helicopters; Southern Helicopter, Inc.; Southwest 
Florida Aviation International, Inc. (previously Jamie R. Hill and 
Southwest Florida Aviation); Tamarack Helicopters, Inc. (previously 
Ranger Helicopter Services, Inc.); US Helicopter, Inc. (previously 
UNC Helicopter, Inc.); West Coast Fabrication; and Williams 
Helicopter Corporation (previously Scott Paper Co.) Model HH-1K, TH-
1F, TH-1L, UH-1A, UH-1B, UH-1E, UH-1F, UH-1H, UH-1L, and UH-1P 
Helicopters; and Southwest Florida Aviation Model UH-1B (SW204 and 
SW204HP) and UH-1H (SW205) Helicopters: Docket No. FAA-2010-0488; 
Directorate Identifier 2008-SW-20-AD.

    Applicability: Model HH-1K, TH-1F, TH-1L, UH-1A, UH-1B, UH-1E, 
UH-1F, UH-1H, UH-1L, and UH-1P helicopters, and Southwest Florida 
Aviation Model UH-1B series (SW204 series and SW204HP) and UH-1H 
series (SW205 series) helicopters, with a tail rotor blade (blade), 
part number (P/N) 212-010-750-009 through -129, all serial numbers 
except serial numbers with a prefix of ``A'' or ``AFS,'' and the 
number 11926, 13351, 13367, 13393, 13400, 13402, 13515, 13540, 
13568, 13595 through 13602, 13619, and subsequent larger numbers, 
installed, certificated in any category.
    Compliance: Within 100 hours time-in-service, unless 
accomplished previously.
    To prevent loss of the forward tip weight retention block (tip 
block) or aft tip closure (tip closure), loss of the blade, and 
subsequent loss of control of the helicopter, do the following:

    Note 1: A blade inspected and modified by following either AD 
2002-09-04 or 2007-22-02, for the Bell Helicopter Textron (Bell) 
Model 205A, 205A-1, 205B, 212, 412, 412CF, and 412EP helicopters 
satisfies the requirements of this AD.

    (a) Inspect the tip block and tip closure of each blade for 
voids. Remove from service any blade with a void in excess of that 
allowed by the applicable maintenance or Component Repair and 
Overhaul Manual limitations.
    (b) Inspect the tip block attachment countersink screws in the 
four locations to determine if the head of each countersunk screw is 
flush with the surface of the abrasion strip. The locations of these 
four screws are depicted on Figure 1 of Bell Alert Service Bulletin 
212-00-111, Revision D, dated March 18, 2005 (ASB). If any of these 
screws are set below the surface of the abrasion strip or are 
covered with filler material, install shear pins by following the 
Accomplishment Instructions, Part A, Shear Pin Installation 
paragraphs, of the ASB.
    (c) Install the tip closure rivets on each blade, re-identify 
the modified blade by adding an ``FM'' after the P/N, and 
dynamically balance the tail rotor hub assembly by following the 
Accomplishment Instructions, Part B, Aft Tip Closure Rivet 
Installation paragraphs, of the ASB.
    (d) 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, Rotorcraft Certification Office, Rotorcraft 
Directorate, ATTN: DOT/FAA Southwest Region, Michael Kohner, ASW-
170, Aviation Safety Engineer, 2601 Meacham Blvd., Fort Worth, Texas 
76137, telephone (817) 222-5170, fax (817) 222-5783, for information 
about previously approved alternative methods of compliance.

    Issued in Fort Worth, Texas, on May 3, 2010.
Mark R. Schilling,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2010-11419 Filed 5-12-10; 8:45 am]
BILLING CODE 4910-13-P
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