Airworthiness Directives; MD Helicopters, Inc., Model 369, YOH-6A, 369A, OH-6A, 369H, 369HM, 369HS, 369HE, 369D, 369E, 369F, and 369FF Helicopters, 33642-33644 [E7-11409]

Download as PDF 33642 Federal Register / Vol. 72, No. 117 / Tuesday, June 19, 2007 / Rules and Regulations Actions Compliance Procedures (2) Replace the hydraulic pump outlet tube, part number (P/N) 390–580035 (or FAA-approved equivalent) for the LH engine or P/N 390–580037 (or FAA-approved equivalent) for the RH engine. Each and every time any of the following occurs until the kits required in paragraph (e)(4) of this AD are incorporated (i) Prior to further flight after any inspection required in paragraph (e)(1) of this AD where evidence of chafing, excessive vibration, wear, deterioration, or hydraulic fluid leakage is found; and (ii) Within 1 hour TIS following identification of an intended or unintended engine operation with the hydraulic shutoff valve closed. Within 5 days after December 28, 2006 (the effective date of AD 2006–26–08). Raytheon Aircraft Premier 1 Model 390 Maintenance Manual, P/N 390–590001–0015. (3) Incorporate Raytheon Aircraft Company Part Number 390–590001–0003C3TC6, dated September 16, 2006 into the airplane flight manual (AFM). (4) Incorporate Kits No. 390–5804–0001 and 390–5805–0001. At whichever of the following that occurs first: (i) Within the next 25 hours TIS after June 20, 2007 (the effective date of this AD); or (ii) Within the next 45 days after June 20, 2007 (the effective date of this AD. (f) After the actions required in paragraph (e)(4) of this AD are done: (1) the repetitive inspections and replacement of paragraphs (e)(1) and (e)(2) of this AD are no longer required. (2) the requirement in paragraph (e)(3) of this AD to incorporate Raytheon Aircraft Company Part Number 390–590001– 0003C3TC6, dated September 16, 2006, into the AFM remains valid. 5805 (Kit 390–5805–0001 Field Service Kit), as referenced in Hawker Beechcraft Mandatory Service Bulletin 29–3800, Issued May, 2007, to do the actions required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of Raytheon Aircraft Company Kit—Dampener Support Improvement, Drawing No. 390– 5804 (Kit 390–5804–0001 Field Service Kit) and Raytheon Aircraft Company Kit— Hydraulic Pump Pressure Hose Installation No. 390–5805 (Kit 390–5805–0001 Field Service Kit), as referenced in Hawker Beechcraft Mandatory Service Bulletin 29– 3800, Issued May, 2007, under 5 U.S.C. 552(a) and 1 CFR part 51. (2) On February 2, 2006 (71 FR 5581, February 2, 2006), the Director of the Federal Register approved the incorporation by reference of Raytheon Mandatory Service Bulletin No. SB 29–3771, dated January, 2006; and Raytheon Safety Communique No. 267, dated January 2006. (3) For service information identified in this AD, contact Hawker Beechcraft Corporation, 9709 East Central, Wichita, Kansas 67291; telephone: (800) 429–5372 or (316) 676–3140. (4) You may review copies at the FAA, Central Region, Office of the Regional Counsel, 901 Locust, Kansas City, Missouri 64106; 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/ code_of_federal_regulations/ ibr_locations.html. pwalker on PROD1PC71 with RULES Alternative Methods of Compliance (AMOCs) (g) The Manager, Wichita Aircraft Certification Office, FAA, ATTN: James P. Galstad, Propulsion Aerospace Engineer, ACE 116W, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Wichita, Kansas 67209; telephone: (316) 946– 4135; fax: (316) 946–4107, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. (h) AMOCs approved for AD 2006–26–08 are approved for this AD. Material Incorporated by Reference (i) You must use Raytheon Mandatory Service Bulletin No. SB 29–3771, dated January, 2006; Raytheon Safety Communique No. 267, dated January 2006; and Raytheon Aircraft Company Kit—Dampener Support Improvement, Drawing No. 390–5804 (Kit 390–5804–0001 Field Service Kit) and Raytheon Aircraft Company Kit—Hydraulic Pump Pressure Hose Installation No. 390– VerDate Aug<31>2005 17:54 Jun 18, 2007 Jkt 211001 PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 The owner/operator holding at least a private pilot certificate as authorized by section 43.7 of the Federal Aviation Regulations (14 CFR 43.7) may do the AFM change requirement of this AD. Make an entry into the aircraft records showing compliance with this portion of the AD in accordance with section 43.9 of the Federal Aviation Regulations (14 CFR 43.9). Follow the instructions in the documents presented below as referenced in Hawker Beechcraft Mandatory Service Bulletin 29– 3800, Issued May, 2007: (i) Raytheon Aircraft Company Kit— Dampener Support Improvement, Drawing No. 390–5804 (Kit 390–5804– 0001 Field Service Kit). (ii) Raytheon Aircraft Company Kit—Hydraulic Pump Pressure Hose Installation No. 390–5805 (Kit 390–5805–0001 Field Service Kit). Issued in Kansas City, Missouri, on June 4, 2007. David R. Showers, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–11241 Filed 6–18–07; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–28449; Directorate Identifier 2007–SW–18–AD; Amendment 39– 15103; AD 2007–09–51] RIN 2120–AA64 Airworthiness Directives; MD Helicopters, Inc., Model 369, YOH–6A, 369A, OH–6A, 369H, 369HM, 369HS, 369HE, 369D, 369E, 369F, and 369FF Helicopters Federal Aviation Administration, DOT. ACTION: Final rule; request for comments. AGENCY: SUMMARY: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 2007–09–51, sent previously to all known U.S. owners and operators of the E:\FR\FM\19JNR1.SGM 19JNR1 pwalker on PROD1PC71 with RULES Federal Register / Vol. 72, No. 117 / Tuesday, June 19, 2007 / Rules and Regulations specified MD Helicopters, Inc. (MDHI), model helicopters by individual letters. This AD requires, before further flight, removing each affected tail rotor blade assembly and inspecting the bore of the tail rotor blade root fitting. If the blade assembly does not have a smooth radius, the AD requires replacing it. The AD also requires identifying each airworthy tail rotor blade assembly with the applicable helicopter model. This amendment is prompted by a report of an accident after the loss of a tail rotor blade. The actions specified by this AD are intended to prevent the failure of a tail rotor blade and subsequent loss of control of the helicopter. DATES: Effective July 5, 2007, to all persons except those persons to whom it was made immediately effective by Emergency AD 2007–09–51, issued on April 27, 2007, which contained the requirements of this amendment. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of July 5, 2007. Comments for inclusion in the Rules Docket must be received on or before August 20, 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 Mail address above 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 MD Helicopters Inc., Attn: Customer Support Division, 4555 E. McDowell Rd., Mail Stop M615, Mesa, Arizona 85215–9734, telephone 1–800–388– 3378, fax 480–346–6813, or on the web at http://www.mdhelicopters.com. 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 Management System (DMS) Docket Offices between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Office (telephone VerDate Aug<31>2005 17:54 Jun 18, 2007 Jkt 211001 (800) 647–5527) is located on the plaza level of the Department of Transportation Nassif 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: John Cecil, Aviation Safety Engineer, FAA, Los Angeles Aircraft Certification Office, Airframe Branch, 3960 Paramount Blvd., Lakewood, California 90712–4137, telephone (562) 627–5228, fax (562) 627–5210. SUPPLEMENTARY INFORMATION: On April 27, 2007, the FAA issued Emergency AD 2007–09–51 (EAD) for the specified MDHI model helicopters. The EAD requires, before further flight, removing each affected tail rotor blade assembly and, using a bright light, inspecting the bore of the tail rotor blade root fitting. If the blade assembly does not have a smooth radius, the AD requires replacing it. The AD also requires identifying each airworthy tail rotor blade assembly with the applicable model of helicopter. That action was prompted by a report of an accident after the loss of a tail rotor blade. This condition, if not corrected, could result in the failure of a tail rotor blade and subsequent loss of control of the helicopter. MDHI has issued Service Bulletin No. SB369H–247, SB369D–204, SB369E– 099, and SB369F–084, dated April 26, 2007 (SB), which describes procedures for inspecting the tail rotor blade assembly. The SB states that reports from the field have shown that there are tail rotor blades in operation with a machining defect. The SB further states that these blades have a sharp transition in the tapered end of the root fitting bore that can cause the tail rotor blade root fitting to fail. Since the unsafe condition described is likely to exist or develop on other MDHI model helicopters of these same type designs, the FAA issued EAD 2007–09–51 to prevent the failure of a tail rotor blade and subsequent loss of control of the helicopter. This AD requires the following, before further flight: • Remove each affected tail rotor blade assembly. Using a bright light, inspect the bore of the tail rotor blade root fitting. • Replace each blade assembly that does not have a smooth radius. • Identify the airworthy tail rotor blade assembly with the applicable model of helicopter. The actions must be done by following specified portions of the ASB described previously. The short compliance time PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 33643 involved is required because the previously described critical unsafe condition can adversely affect the controllability and structural integrity of the helicopter. Therefore, removing each affected blade assembly, inspecting the bore of the tail rotor blade root fitting, and replacing each blade assembly that does not have a smooth radius are required before further flight, and this AD must be issued immediately. Since it was found that immediate corrective action was required, notice and opportunity for prior public comment thereon were impracticable and contrary to the public interest. Good cause existed to make the AD effective immediately by individual letters issued on April 27, 2007, to all known U.S. owners and operators of MD Helicopters, Inc., Model 369 (Army YOH–6A), 369A (Army OH–6A), 369H, 369HM, 369HS, 369HE, 369D, 369E, 369F, and 369FF helicopters. These conditions still exist, and the AD is hereby published in the Federal Register as an amendment to 14 CFR 39.13 to make it effective to all persons. The FAA estimates that this AD will affect 980 helicopters of U.S. registry and will require about: • 0.1 work hour to identify a blade, • 2 work hours to remove, inspect, install and balance the tail rotor blade assemblies on each helicopter, • $80 per work hour labor rate, and • $8,862 for each replacement blade plus hardware. Based on these figures, we estimate the total cost impact of the AD on U.S. operators to be $1,901,592, assuming 1 out of 10 blades are found defective for an estimated 196 blades that need replacing. 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–2007–28449; Directorate Identifier 2007–SW–18–AD’’ 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 E:\FR\FM\19JNR1.SGM 19JNR1 33644 Federal Register / Vol. 72, No. 117 / Tuesday, June 19, 2007 / Rules and Regulations 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. pwalker on PROD1PC71 with RULES 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, Incorporation by reference, Safety. VerDate Aug<31>2005 18:22 Jun 18, 2007 Jkt 211001 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 2007–09–51 MD Helicopters, Inc.: Amendment 39–15103. Docket No. FAA–2007–28449; Directorate Identifier 2007–SW–28–AD. Applicability Model 369, YOH–6A, 369A, OH–6A, 369H, 369HM, 369HS, 369HE, 369D, 369E, 369F, and 369FF helicopters, with a tail rotor blade, part number (P/N) 369A1613, 369D21606, 369D21613, 369D21615, or 421– 088, all dash numbers, installed, certificated in any category. Compliance Before further flight, unless accomplished previously. To prevent the loss of a tail rotor blade and subsequent loss of control of the helicopter, do the following: (a) Inspect each affected tail rotor blade for a smooth radius as follows: (1) Remove the tail rotor blade assembly by following the Accomplishment Instructions, paragraphs 2.B.(1) through 2.B.(3), Part 2., of MD Helicopters, Inc., Service Bulletin SB369H–247, SB369D–204, SB369E–099, and SB369F–084 dated April 26, 2007 (SB). (2) Using a bright light, inspect the bore of the tail rotor blade root fitting by following the Accomplishment Instructions, paragraphs 2.B.(4) and 2.B.(5), Part 2, and Figures 1 and 2 of the SB. (b) Replace each blade assembly that does not have a smooth radius by following the Accomplishment Instructions, paragraphs 2.B.(6) and (7), Part 2, and Figure 2 of the SB. (c) Identify the airworthy tail rotor blade assembly with the applicable model of helicopter by following the Identification, paragraphs 3.(1) through 3.(4) of the SB. (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, Los Angeles Aircraft Certification Office, FAA; Attn: John Cecil, Aviation Safety Engineer, Airframe Branch, 3960 Paramount Blvd., Lakewood, California 90712–4137, telephone (562) 627– 5228, fax (562) 627–5210, for information about previously approved alternative methods of compliance. (e) Special flight permits will not be issued. (f) Inspecting, replacing, and identifying the tail rotor blade assembly shall be done by PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 following the specified portions of MD Helicopters, Inc., Service Bulletin SB369H– 247, SB369D–204, SB369E–099, and SB369F–084, dated April 26, 2007. The Director of the Federal Register approved this incorporation by reference in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from MD Helicopters, Inc., Attn: Customer Support Division, 4555 E. McDowell Rd., Mail Stop M615, Mesa, Arizona 85215–9734, telephone 1–800–388–3378, fax 480–346–6813, or on the Web at http://www.mdhelicopters.com. Copies may be inspected at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 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/ code_of_federal_regulations/ ibr_locations.html. (g) This amendment becomes effective on July 5, 2007, to all persons except those persons to whom it was made immediately effective by Emergency AD 2007–09–51, issued April 27, 2007, which contained the requirements of this amendment. Issued in Fort Worth, Texas, on June 5, 2007. Mark R. Schilling, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. E7–11409 Filed 6–18–07; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 71 [Docket No. FAA–2007–27678; Airspace Docket No. 07–ACE–3] Modification of Class E Airspace; Monticello, IA Federal Aviation Administration (FAA), DOT. ACTION: Direct final rule; confirmation of effective date. AGENCY: SUMMARY: This document confirms the effective date of the direct final rule which revises Class E airspace at Monticello, IA. DATE: Effective Date: 0901 UTC, July 5, 2007. FOR FURTHER INFORMATION CONTACT: Grant Nichols, System Support, DOT Regional Headquarters Building, Federal Aviation Administration, 901 Locust, Kansas City, MO 64106; telephone: (816) 329–2522. SUPPLEMENTARY INFORMATION: The FAA published this direct final rule with a request for comments in the Federal Register on May 16, 2007 (72 FR 27415). The FAA uses the direct final E:\FR\FM\19JNR1.SGM 19JNR1

Agencies

[Federal Register Volume 72, Number 117 (Tuesday, June 19, 2007)]
[Rules and Regulations]
[Pages 33642-33644]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-11409]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-28449; Directorate Identifier 2007-SW-18-AD; 
Amendment 39-15103; AD 2007-09-51]
RIN 2120-AA64


Airworthiness Directives; MD Helicopters, Inc., Model 369, YOH-
6A, 369A, OH-6A, 369H, 369HM, 369HS, 369HE, 369D, 369E, 369F, and 369FF 
Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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

SUMMARY: This document publishes in the Federal Register an amendment 
adopting Airworthiness Directive (AD) 2007-09-51, sent previously to 
all known U.S. owners and operators of the

[[Page 33643]]

specified MD Helicopters, Inc. (MDHI), model helicopters by individual 
letters. This AD requires, before further flight, removing each 
affected tail rotor blade assembly and inspecting the bore of the tail 
rotor blade root fitting. If the blade assembly does not have a smooth 
radius, the AD requires replacing it. The AD also requires identifying 
each airworthy tail rotor blade assembly with the applicable helicopter 
model. This amendment is prompted by a report of an accident after the 
loss of a tail rotor blade. The actions specified by this AD are 
intended to prevent the failure of a tail rotor blade and subsequent 
loss of control of the helicopter.

DATES: Effective July 5, 2007, to all persons except those persons to 
whom it was made immediately effective by Emergency AD 2007-09-51, 
issued on April 27, 2007, which contained the requirements of this 
amendment.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of July 5, 2007.
    Comments for inclusion in the Rules Docket must be received on or 
before August 20, 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 Mail address above 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 MD 
Helicopters Inc., Attn: Customer Support Division, 4555 E. McDowell 
Rd., Mail Stop M615, Mesa, Arizona 85215-9734, telephone 1-800-388-
3378, fax 480-346-6813, or on the web at http://www.mdhelicopters.com.
    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 Management System (DMS) Docket 
Offices between 9 a.m. and 5 p.m., Monday through Friday, except 
Federal holidays. The Docket Office (telephone (800) 647-5527) is 
located on the plaza level of the Department of Transportation Nassif 
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: John Cecil, Aviation Safety Engineer, 
FAA, Los Angeles Aircraft Certification Office, Airframe Branch, 3960 
Paramount Blvd., Lakewood, California 90712-4137, telephone (562) 627-
5228, fax (562) 627-5210.

SUPPLEMENTARY INFORMATION: On April 27, 2007, the FAA issued Emergency 
AD 2007-09-51 (EAD) for the specified MDHI model helicopters. The EAD 
requires, before further flight, removing each affected tail rotor 
blade assembly and, using a bright light, inspecting the bore of the 
tail rotor blade root fitting. If the blade assembly does not have a 
smooth radius, the AD requires replacing it. The AD also requires 
identifying each airworthy tail rotor blade assembly with the 
applicable model of helicopter. That action was prompted by a report of 
an accident after the loss of a tail rotor blade. This condition, if 
not corrected, could result in the failure of a tail rotor blade and 
subsequent loss of control of the helicopter.
    MDHI has issued Service Bulletin No. SB369H-247, SB369D-204, 
SB369E-099, and SB369F-084, dated April 26, 2007 (SB), which describes 
procedures for inspecting the tail rotor blade assembly. The SB states 
that reports from the field have shown that there are tail rotor blades 
in operation with a machining defect. The SB further states that these 
blades have a sharp transition in the tapered end of the root fitting 
bore that can cause the tail rotor blade root fitting to fail.
    Since the unsafe condition described is likely to exist or develop 
on other MDHI model helicopters of these same type designs, the FAA 
issued EAD 2007-09-51 to prevent the failure of a tail rotor blade and 
subsequent loss of control of the helicopter. This AD requires the 
following, before further flight:
     Remove each affected tail rotor blade assembly. Using a 
bright light, inspect the bore of the tail rotor blade root fitting.
     Replace each blade assembly that does not have a smooth 
radius.
     Identify the airworthy tail rotor blade assembly with the 
applicable model of helicopter.

The actions must be done by following specified portions of the ASB 
described previously. 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 each affected blade assembly, 
inspecting the bore of the tail rotor blade root fitting, and replacing 
each blade assembly that does not have a smooth radius are required 
before further flight, and this AD must be issued immediately.
    Since it was found that immediate corrective action was required, 
notice and opportunity for prior public comment thereon were 
impracticable and contrary to the public interest. Good cause existed 
to make the AD effective immediately by individual letters issued on 
April 27, 2007, to all known U.S. owners and operators of MD 
Helicopters, Inc., Model 369 (Army YOH-6A), 369A (Army OH-6A), 369H, 
369HM, 369HS, 369HE, 369D, 369E, 369F, and 369FF helicopters. These 
conditions still exist, and the AD is hereby published in the Federal 
Register as an amendment to 14 CFR 39.13 to make it effective to all 
persons.
    The FAA estimates that this AD will affect 980 helicopters of U.S. 
registry and will require about:
     0.1 work hour to identify a blade,
     2 work hours to remove, inspect, install and balance the 
tail rotor blade assemblies on each helicopter,
     $80 per work hour labor rate, and
     $8,862 for each replacement blade plus hardware.

Based on these figures, we estimate the total cost impact of the AD on 
U.S. operators to be $1,901,592, assuming 1 out of 10 blades are found 
defective for an estimated 196 blades that need replacing.

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-2007-28449; 
Directorate Identifier 2007-SW-18-AD'' 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

[[Page 33644]]

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, Incorporation by 
reference, 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:

2007-09-51 MD Helicopters, Inc.: Amendment 39-15103. Docket No. FAA-
2007-28449; Directorate Identifier 2007-SW-28-AD.

Applicability

    Model 369, YOH-6A, 369A, OH-6A, 369H, 369HM, 369HS, 369HE, 369D, 
369E, 369F, and 369FF helicopters, with a tail rotor blade, part 
number (P/N) 369A1613, 369D21606, 369D21613, 369D21615, or 421-088, 
all dash numbers, installed, certificated in any category.

Compliance

    Before further flight, unless accomplished previously.
    To prevent the loss of a tail rotor blade and subsequent loss of 
control of the helicopter, do the following:
    (a) Inspect each affected tail rotor blade for a smooth radius 
as follows:
    (1) Remove the tail rotor blade assembly by following the 
Accomplishment Instructions, paragraphs 2.B.(1) through 2.B.(3), 
Part 2., of MD Helicopters, Inc., Service Bulletin SB369H-247, 
SB369D-204, SB369E-099, and SB369F-084 dated April 26, 2007 (SB).
    (2) Using a bright light, inspect the bore of the tail rotor 
blade root fitting by following the Accomplishment Instructions, 
paragraphs 2.B.(4) and 2.B.(5), Part 2, and Figures 1 and 2 of the 
SB.
    (b) Replace each blade assembly that does not have a smooth 
radius by following the Accomplishment Instructions, paragraphs 
2.B.(6) and (7), Part 2, and Figure 2 of the SB.
    (c) Identify the airworthy tail rotor blade assembly with the 
applicable model of helicopter by following the Identification, 
paragraphs 3.(1) through 3.(4) of the SB.
    (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, Los Angeles Aircraft Certification Office, FAA; 
Attn: John Cecil, Aviation Safety Engineer, Airframe Branch, 3960 
Paramount Blvd., Lakewood, California 90712-4137, telephone (562) 
627-5228, fax (562) 627-5210, for information about previously 
approved alternative methods of compliance.
    (e) Special flight permits will not be issued.
    (f) Inspecting, replacing, and identifying the tail rotor blade 
assembly shall be done by following the specified portions of MD 
Helicopters, Inc., Service Bulletin SB369H-247, SB369D-204, SB369E-
099, and SB369F-084, dated April 26, 2007. The Director of the 
Federal Register approved this incorporation by reference in 
accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be 
obtained from MD Helicopters, Inc., Attn: Customer Support Division, 
4555 E. McDowell Rd., Mail Stop M615, Mesa, Arizona 85215-9734, 
telephone 1-800-388-3378, fax 480-346-6813, or on the Web at http://
www.mdhelicopters.com. Copies may be inspected at the FAA, Office of 
the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 
663, Fort Worth, Texas 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/code_of_federal_regulations/
ibr_locations.html.
    (g) This amendment becomes effective on July 5, 2007, to all 
persons except those persons to whom it was made immediately 
effective by Emergency AD 2007-09-51, issued April 27, 2007, which 
contained the requirements of this amendment.

    Issued in Fort Worth, Texas, on June 5, 2007.
Mark R. Schilling,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. E7-11409 Filed 6-18-07; 8:45 am]
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