Airworthiness Directives; MD Helicopters, Inc. Model 369A, OH-6A, 369D, 369E, 369F, 369FF, 369H, 369HE, 369HM, and 369HS Helicopters, 44139-44140 [E8-17274]

Download as PDF Federal Register / Vol. 73, No. 147 / Wednesday, July 30, 2008 / Rules and Regulations Prairie, Texas 75053–4005, telephone (972) 641–3460, fax (972) 641–3527. (l) You may review copies of the service information 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/ cfr/ibr-locations.html. Issued in Fort Worth, Texas, on May 5, 2008. David A. Downey, Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. E8–17265 Filed 7–29–08; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2008–0287; Directorate Identifier 2006–SW–15–AD; Amendment 39– 15615; AD 2008–15–03] RIN 2120–AA64 Airworthiness Directives; MD Helicopters, Inc. Model 369A, OH–6A, 369D, 369E, 369F, 369FF, 369H, 369HE, 369HM, and 369HS Helicopters Federal Aviation Administration, DOT. ACTION: Final rule. rwilkins on PROD1PC63 with RULES AGENCY: SUMMARY: This amendment adopts a new airworthiness directive (AD) for MD Helicopters, Inc. (MDHI) Model 369A, OH–6A, 369D, 369E, 369F, 369FF, 369H, 369HE, 369HM, and 369HS helicopters that requires repetitive tap inspections of each tail rotor (T/R) blade abrasion strip. This amendment is prompted by an incident in which an abrasion strip separated from a T/R blade. The actions specified by this AD are intended to prevent disbonding and subsequent separation of an abrasion strip from a T/R blade, which could result in vibration, loss of the T/R, and subsequent loss of control of the helicopter. DATES: Effective September 3, 2008. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of September 3, 2008. ADDRESSES: You may get the Helicopter Technology Company, LLC (HTC) service information identified in this AD from HTC, 12902 South Broadway, Los Angeles, California, 90061, telephone (310) 523–2750, fax (310) VerDate Aug<31>2005 16:51 Jul 29, 2008 Jkt 214001 523–2745, or on the Internet at http:// www.helicoptertech.com. The service information referenced in Note 2 of this AD may be obtained from MD Helicopters Inc., Attn: Customer Support Division, 4555 E. McDowell Rd., Mail Stop M615, Mesa, Arizona 85215–9734, telephone (800) 388–3378, fax (480) 346–6813, or on the Internet at http://www.mdhelicopters.com. Examining the Docket: You may examine the docket that contains this AD, any comments, and other information on the Internet at http:// www.regulations.gov or at the Docket Operations office, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC. 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: A proposal to amend 14 CFR part 39 to include an AD for the specified model helicopters was published in the Federal Register on March 13, 2008 (73 FR 13515). That action proposed to require, within 25 hours time-in-service (TIS), and thereafter at intervals not to exceed 25 hours TIS, tap inspections of the upper and lower surfaces of each T/ R blade abrasion strip using a coin (United States 25-cent piece or equivalent), or a small brass, mild steel, or aluminum hammer, to detect bonding voids that exceed 0.2 square inch in size with a minimum of 1.0 inch between voids, at least 75 percent of the bonded area of the abrasion strip being free from voids, and no voids at the edge of the abrasion strip. Also proposed was a terminating action of modifying each T/ R blade in accordance with FAAapproved data by installing a titanium rivet in the tip of the outboard end of each T/R blade and painting a ‘‘T’’ on the root-end of the T/R blade. We have reviewed the following service information: • HTC Mandatory Service Bulletin Notice No. 3100–4R4, dated May 10, 2006, which describes procedures for periodic inspection of the abrasion strip-to-skin bond integrity on each T/R blade, and modifying each T/R blade by installing a titanium rivet, P/N 500P3124–13, in the tip of the T/R blade, and painting a ‘‘T’’ on the rootend of the T/R blade in accordance with applicable engineering drawings or standard repair instructions; and • MD Helicopters Service Bulletin SB369D–203R1, SB369E–097R1, PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 44139 SB369F–082R1, and SB369H–246R1, dated January 23, 2006, which describes procedures for periodic inspections of the T/R abrasion strip-to-skin bond integrity and modification of the T/R blade by HTC to install a titanium rivet in the tip of the T/R blade. Interested persons have been afforded an opportunity to participate in the making of this amendment. No comments were received on the proposal or the FAA’s determination of the cost to the public. The FAA has determined that air safety and the public interest require the adoption of the rule as proposed. The FAA estimates that this AD will affect 718 helicopters of U.S. registry. • If operators conduct the repetitive inspections required by this AD instead of modifying their T/R blades by installing a titanium rivet, the estimated costs per year is $229,760 per year, assuming: • 24 inspections per year per helicopter (600 hours TIS per 25 hour TIS inspection), • Labor of 5 minutes per T/R blade (10 minutes (1⁄6 hour) per helicopter), and • An average labor rate of $80 per work hour. • If operators elect to implement the terminating action by installing a titanium rivet in each T/R blade, the estimated total cost is $244,120, assuming: • The cost of removing, reinstalling, and balancing the 2–T/R blade set for the entire fleet is $114,880, assuming that it takes 2 work hours per helicopter to perform these actions at an average labor rate of $80 per work hour, and • The cost of installing the rivet in each T/R blade in the fleet is $129,240, which includes the cost of $10 per rivet ($20 per helicopter), 1 work hour per T/ R blade (2 work hours per helicopter) to install a rivet, at an average labor rate of $80 per work hour. 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 E:\FR\FM\30JYR1.SGM 30JYR1 44140 Federal Register / Vol. 73, No. 147 / Wednesday, July 30, 2008 / Rules and Regulations 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 AD docket 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 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 rwilkins on PROD1PC63 with RULES 2008–15–03 MD Helicopters, Inc. (MDHI): Amendment 39–15615. Docket No. FAA–2008–0287; Directorate Identifier 2006–SW–15–AD. Applicability: Model 369A, OH–6A, 369D, 369E, 369F, 369FF, 369H, 369HE, 369HM, and 369HS, certificated in any category, with a tail rotor (T/R) blade installed as follows including all serial numbers and those T/R blades with an ‘‘M’’ or an ‘‘I’’ painted on the T/R blade root: VerDate Aug<31>2005 16:51 Jul 29, 2008 Jkt 214001 • Helicopter Technology Company, LLC (HTC) part number (P/N) 500P3100–101 and –103, or MDHI P/N 369D21640–501, –503, and –505. • HTC P/N 500P3100–301 and –303, or MDHI P/N 369D21641–501, –503, and –505. • HTC P/N 500P3300–501 and –503, or MDHI P/N 369D21643–501, –503, and –505. • HTC P/N 500P3500–701 and –703, or MDHI P/N 369D21642–501, –503, and –505. Note 1: An ‘‘M’’ or an ‘‘I’’ painted on the root of the T/R blade indicates compliance to an Alternate Method of Compliance (AMOC) to Emergency AD 2003–08–51 (Docket No. 2003–SW–17–AD, Amendment 39–13215, April 15, 2003), issued by the FAA, Los Angeles Aircraft Certification Office (LAACO) on June 13, 2003 to HTC. The AMOC addressed shot peening of the pitch horn of the T/R assembly. Compliance: Required as indicated. To prevent disbonding and subsequent separation of an abrasion strip from a T/R blade, which could result in vibration, loss of the T/R, and subsequent loss of control of the helicopter, accomplish the following: (a) Within 25 hours time-in-service (TIS), unless accomplished previously, and thereafter at intervals not to exceed 25 hours TIS, inspect the abrasion strip-to-skin bond integrity on each T/R blade using a tap test method in accordance with Part 1— Inspection, in Helicopter Technology Company, LLC (HTC) Mandatory Service Bulletin Notice No. 3100–4R4, dated May 10, 2006 (SB). Note 2: MD Helicopters Service Bulletin SB369D–203R1, SB369E–097R1, SB369F– 082R1, and SB369H–246R1, dated January 23, 2006, pertain to the subject of this AD. (b) Modifying each T/R blade in accordance with FAA-approved data by installing a titanium rivet at the outboard end and painting the letter ‘‘T’’ on the root-end of the T/R blade to indicate the modification has been accomplished is considered a terminating action for the requirements of this AD. (c) 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, 3960 Paramount Blvd., Lakewood, California 90712–4137, telephone (562) 627–5228, fax (562) 627–5210, for information about previously approved alternative methods of compliance. (d) Special flight permits will not be issued. (e) The inspection shall be done in accordance with the specified portions of Helicopter Technology Company, LLC (HTC) Mandatory Service Bulletin Notice No. 3100– 4R4, dated May 10, 2006. 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 HTC, 12902 South Broadway, Los Angeles, California, 90061, telephone (310) 523–2750, fax (310) 523–2745, or on the Internet at http://www.helicoptertech.com. Copies may be inspected at the FAA, Office of the Regional Counsel, Southwest Region, PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 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. (f) This amendment becomes effective on September 3, 2008. Issued in Fort Worth, Texas, on June 25, 2008. David A. Downey, Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. E8–17274 Filed 7–29–08; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–0177; Directorate Identifier 2007–SW–19–AD; Amendment 39–15616; AD 2008–15–04] RIN 2120–AA64 Airworthiness Directives; Bell Helicopter Textron Canada (BHTC) Model 430 Helicopters Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: We are adopting a new airworthiness directive (AD) for BHTC Model 430 helicopters. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The aviation authority of Canada, with which we have a bilateral agreement, states in the MCAI: ‘‘It has been determined that the existing rigging procedures for the tail rotor pitch change mechanism have to be changed due to possibility of parts interference.’’ The cumulative effect of individual part tolerances resulting in the total assemblage of those parts being out of tolerance could result in the tail rotor yoke striking another part other than the flapping stop (parts interference) cited in the MCAI. Also, the misalignment of the tail rotor counterweight bellcrank may result in higher tail rotor pedal forces and a higher pilot workload after failure of the #1 hydraulic system. Both parts interference and the misaligned counterweight bellcrank create an unsafe condition. This AD require actions that are intended to address these unsafe conditions. E:\FR\FM\30JYR1.SGM 30JYR1

Agencies

[Federal Register Volume 73, Number 147 (Wednesday, July 30, 2008)]
[Rules and Regulations]
[Pages 44139-44140]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-17274]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-0287; Directorate Identifier 2006-SW-15-AD; 
Amendment 39-15615; AD 2008-15-03]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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

SUMMARY: This amendment adopts a new airworthiness directive (AD) for 
MD Helicopters, Inc. (MDHI) Model 369A, OH-6A, 369D, 369E, 369F, 369FF, 
369H, 369HE, 369HM, and 369HS helicopters that requires repetitive tap 
inspections of each tail rotor (T/R) blade abrasion strip. This 
amendment is prompted by an incident in which an abrasion strip 
separated from a T/R blade. The actions specified by this AD are 
intended to prevent disbonding and subsequent separation of an abrasion 
strip from a T/R blade, which could result in vibration, loss of the T/
R, and subsequent loss of control of the helicopter.

DATES: Effective September 3, 2008.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of September 3, 2008.

ADDRESSES: You may get the Helicopter Technology Company, LLC (HTC) 
service information identified in this AD from HTC, 12902 South 
Broadway, Los Angeles, California, 90061, telephone (310) 523-2750, fax 
(310) 523-2745, or on the Internet at http://www.helicoptertech.com. 
The service information referenced in Note 2 of this AD may be obtained 
from MD Helicopters Inc., Attn: Customer Support Division, 4555 E. 
McDowell Rd., Mail Stop M615, Mesa, Arizona 85215-9734, telephone (800) 
388-3378, fax (480) 346-6813, or on the Internet at http://
www.mdhelicopters.com.
    Examining the Docket: You may examine the docket that contains this 
AD, any comments, and other information on the Internet at http://
www.regulations.gov or at the Docket Operations office, West Building 
Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE., Washington, 
DC.

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: A proposal to amend 14 CFR part 39 to 
include an AD for the specified model helicopters was published in the 
Federal Register on March 13, 2008 (73 FR 13515). That action proposed 
to require, within 25 hours time-in-service (TIS), and thereafter at 
intervals not to exceed 25 hours TIS, tap inspections of the upper and 
lower surfaces of each T/R blade abrasion strip using a coin (United 
States 25-cent piece or equivalent), or a small brass, mild steel, or 
aluminum hammer, to detect bonding voids that exceed 0.2 square inch in 
size with a minimum of 1.0 inch between voids, at least 75 percent of 
the bonded area of the abrasion strip being free from voids, and no 
voids at the edge of the abrasion strip. Also proposed was a 
terminating action of modifying each T/R blade in accordance with FAA-
approved data by installing a titanium rivet in the tip of the outboard 
end of each T/R blade and painting a ``T'' on the root-end of the T/R 
blade.
    We have reviewed the following service information:
     HTC Mandatory Service Bulletin Notice No. 3100-4R4, dated 
May 10, 2006, which describes procedures for periodic inspection of the 
abrasion strip-to-skin bond integrity on each T/R blade, and modifying 
each T/R blade by installing a titanium rivet, P/N 500P3124-13, in the 
tip of the T/R blade, and painting a ``T'' on the root-end of the T/R 
blade in accordance with applicable engineering drawings or standard 
repair instructions; and
     MD Helicopters Service Bulletin SB369D-203R1, SB369E-
097R1, SB369F-082R1, and SB369H-246R1, dated January 23, 2006, which 
describes procedures for periodic inspections of the T/R abrasion 
strip-to-skin bond integrity and modification of the T/R blade by HTC 
to install a titanium rivet in the tip of the T/R blade.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were received on the 
proposal or the FAA's determination of the cost to the public. The FAA 
has determined that air safety and the public interest require the 
adoption of the rule as proposed.
    The FAA estimates that this AD will affect 718 helicopters of U.S. 
registry.
     If operators conduct the repetitive inspections required 
by this AD instead of modifying their T/R blades by installing a 
titanium rivet, the estimated costs per year is $229,760 per year, 
assuming:
     24 inspections per year per helicopter (600 hours TIS per 
25 hour TIS inspection),
     Labor of 5 minutes per T/R blade (10 minutes (\1/6\ hour) 
per helicopter), and
     An average labor rate of $80 per work hour.
     If operators elect to implement the terminating action by 
installing a titanium rivet in each T/R blade, the estimated total cost 
is $244,120, assuming:
     The cost of removing, reinstalling, and balancing the 2-T/
R blade set for the entire fleet is $114,880, assuming that it takes 2 
work hours per helicopter to perform these actions at an average labor 
rate of $80 per work hour, and
     The cost of installing the rivet in each T/R blade in the 
fleet is $129,240, which includes the cost of $10 per rivet ($20 per 
helicopter), 1 work hour per T/R blade (2 work hours per helicopter) to 
install a rivet, at an average labor rate of $80 per work hour.

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

[[Page 44140]]

    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 AD docket 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:

2008-15-03 MD Helicopters, Inc. (MDHI): Amendment 39-15615. Docket 
No. FAA-2008-0287; Directorate Identifier 2006-SW-15-AD.

    Applicability: Model 369A, OH-6A, 369D, 369E, 369F, 369FF, 369H, 
369HE, 369HM, and 369HS, certificated in any category, with a tail 
rotor (T/R) blade installed as follows including all serial numbers 
and those T/R blades with an ``M'' or an ``I'' painted on the T/R 
blade root:
     Helicopter Technology Company, LLC (HTC) part number 
(P/N) 500P3100-101 and -103, or MDHI P/N 369D21640-501, -503, and -
505.
     HTC P/N 500P3100-301 and -303, or MDHI P/N 369D21641-
501, -503, and -505.
     HTC P/N 500P3300-501 and -503, or MDHI P/N 369D21643-
501, -503, and -505.
     HTC P/N 500P3500-701 and -703, or MDHI P/N 369D21642-
501, -503, and -505.

    Note 1: An ``M'' or an ``I'' painted on the root of the T/R 
blade indicates compliance to an Alternate Method of Compliance 
(AMOC) to Emergency AD 2003-08-51 (Docket No. 2003-SW-17-AD, 
Amendment 39-13215, April 15, 2003), issued by the FAA, Los Angeles 
Aircraft Certification Office (LAACO) on June 13, 2003 to HTC. The 
AMOC addressed shot peening of the pitch horn of the T/R assembly.

    Compliance: Required as indicated.
    To prevent disbonding and subsequent separation of an abrasion 
strip from a T/R blade, which could result in vibration, loss of the 
T/R, and subsequent loss of control of the helicopter, accomplish 
the following:
    (a) Within 25 hours time-in-service (TIS), unless accomplished 
previously, and thereafter at intervals not to exceed 25 hours TIS, 
inspect the abrasion strip-to-skin bond integrity on each T/R blade 
using a tap test method in accordance with Part 1--Inspection, in 
Helicopter Technology Company, LLC (HTC) Mandatory Service Bulletin 
Notice No. 3100-4R4, dated May 10, 2006 (SB).

    Note 2: MD Helicopters Service Bulletin SB369D-203R1, SB369E-
097R1, SB369F-082R1, and SB369H-246R1, dated January 23, 2006, 
pertain to the subject of this AD.

    (b) Modifying each T/R blade in accordance with FAA-approved 
data by installing a titanium rivet at the outboard end and painting 
the letter ``T'' on the root-end of the T/R blade to indicate the 
modification has been accomplished is considered a terminating 
action for the requirements of this AD.
    (c) 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, 3960 Paramount Blvd., 
Lakewood, California 90712-4137, telephone (562) 627-5228, fax (562) 
627-5210, for information about previously approved alternative 
methods of compliance.
    (d) Special flight permits will not be issued.
    (e) The inspection shall be done in accordance with the 
specified portions of Helicopter Technology Company, LLC (HTC) 
Mandatory Service Bulletin Notice No. 3100-4R4, dated May 10, 2006. 
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 HTC, 12902 South Broadway, Los Angeles, 
California, 90061, telephone (310) 523-2750, fax (310) 523-2745, or 
on the Internet at http://www.helicoptertech.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.
    (f) This amendment becomes effective on September 3, 2008.

    Issued in Fort Worth, Texas, on June 25, 2008.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. E8-17274 Filed 7-29-08; 8:45 am]
BILLING CODE 4910-13-P