Airworthiness Directives; Bell Helicopter Textron Canada (BHTC) Model 430 Helicopters, 44140-44142 [E8-17275]

Download as PDF 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 Federal Register / Vol. 73, No. 147 / Wednesday, July 30, 2008 / Rules and Regulations This AD becomes effective on September 3, 2008. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of September 3, 2008. ADDRESSES: You may examine the AD docket on the Internet at http:// www.regulations.gov or in person at the Docket Operations office, U.S. Department of Transportation, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC between 9 a.m. and 5 p.m. Monday through Friday, except Federal holidays. You may get the service information identified in this AD from Bell Helicopter Textron Canada, 12,800 Rue de l’Avenir, Mirabel, Quebec J7J1R4, telephone (450) 437–2862 or (800) 363– 8023, fax (450) 433–0272. Examining the AD Docket: The AD docket contains the Notice of Proposed Rulemaking (NPRM), the economic evaluation, any comments received, and other information. The street address and operating hours for the Docket Operations office (telephone (800) 647– 5227) are in the ADDRESSES section of this AD. Comments will be available in the AD docket shortly after they are received. FOR FURTHER INFORMATION CONTACT: Tyrone Millard, Aviation Safety Engineer, FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, Fort Worth, Texas 76193–0111, telephone (817) 222–5439, fax (817) 222–5961. SUPPLEMENTARY INFORMATION: rwilkins on PROD1PC63 with RULES DATES: Discussion We issued an NPRM to amend 14 CFR part 39 to include an AD that would apply to BHTC Model 430 helicopters, serial numbers 49001 through 49122, on November 2, 2007. That NPRM was published in the Federal Register on November 16, 2007 (72 FR 64540). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states: ‘‘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.’’ Because the cumulative effect of the tolerances on the various parts may result in the total assemblage outboard of the counterweight bellcrank being out of tolerance, the tail rotor yoke may contact the nut, part number (P/N) 222–012–731–001, before contacting the flapping stop, resulting in less tail rotor travel. Additionally, the manufacturer has indicated that the tail rotor counterweight bellcranks may be misaligned, resulting in higher tail rotor VerDate Aug<31>2005 16:51 Jul 29, 2008 Jkt 214001 pedal forces and higher pilot workload after failure of the #1 hydraulic system. Both the parts interference and the higher pedal forces constitute unsafe conditions. You may obtain further information by examining the MCAI and any related service information in the AD docket. Comments By publishing the NPRM, we gave the public an opportunity to participate in developing this AD. However, we received no comment on the NPRM or on our determination of the cost to the public. Therefore, based on our review and evaluation of the available data, we have determined that air safety and the public interest require adopting the AD as proposed. Relevant Service Information Bell Helicopter Textron has issued Alert Service Bulletin No. 430–07–39, dated January 9, 2007, that describes revised rigging procedures for the tail rotor pitch change mechanism. The actions described in the MCAI are intended to correct the same unsafe condition as that identified in the service information. Differences Between This AD and the MCAI We have reviewed the MCAI and related service information and, in general, agree with their substance. However, this AD requires compliance within the next 150 hours time-inservice or at the next annual inspection, whichever occurs first, instead of ‘‘at the next 150 hour or annual inspection, but no later than 31 December 2007.’’ In making this change, we do not intend to differ substantively from the information provided in the MCAI. This difference is highlighted in the ‘‘Differences Between this AD and the MCAI’’ section in the AD. Costs of Compliance We estimate that this AD will affect 58 helicopters of U.S. registry. We also estimate that it will take about 2 workhours per helicopter to comply with the basic requirements of this AD. The average labor rate is $80 per work-hour. A replacement yoke will cost about $21,218, assuming the part is no longer under warranty. However, because the service information lists this part as covered under warranty, we have assumed that there will be no charge for this part. Therefore, as we do not control warranty coverage for affected parties, some parties may incur costs higher than estimated here. Based on these assumptions and figures, we estimate the cost of this AD on U.S. PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 44141 operators to be $9,280, or $160 per helicopter. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ‘‘Subtitle VII: Aviation Programs,’’ describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in ‘‘Subtitle VII, Part A, Subpart III, section 44701: General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We 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. Therefore, I certify this AD: 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 and placed it in the AD docket. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: I PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: I E:\FR\FM\30JYR1.SGM 30JYR1 44142 Federal Register / Vol. 73, No. 147 / Wednesday, July 30, 2008 / Rules and Regulations Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new AD: I 2008–15–04 Bell Helicopter Textron Canada: Amendment 39–15616. Docket No. FAA–2007–0177; Directorate Identifier 2007–SW–19–AD. Effective Date (a) This airworthiness directive (AD) becomes effective on September 3, 2008. Other Affected ADs (b) None. Applicability (c) This AD applies to Model 430 helicopters, serial numbers 49001 through 49122, certificated in any category. rwilkins on PROD1PC63 with RULES Reason (d) The mandatory continuing airworthiness information (MCAI) states: ‘‘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.’’ This ‘‘possibility of parts interference’’ occurs because the cumulative effect of the tolerances on the various parts may result in the total assemblage outboard of the counterweight bellcrank being out of tolerance and the tail rotor yoke may contact the nut, part number (P/N ) 222–012–731– 001, before contacting the flapping stop. Further, the manufacturer has indicated that the tail rotor counterweight bellcranks may be misaligned, resulting in higher tail rotor pedal forces and higher pilot workload after failure of the #1 hydraulic system. Both the parts interference and the higher pedal forces constitute unsafe conditions. This AD requires actions that are intended to address these unsafe conditions. Actions and Compliance (e) Within the next 150 hours time-inservice (TIS) or at the next annual inspection, whichever occurs first, unless already accomplished, do the following: (1) Adjust the rigging of the tail rotor pitch change mechanism in accordance with the Accomplishment Instructions, paragraphs 1 and 2, in Bell Helicopter Textron Alert Service Bulletin 430–07–39, dated January 9, 2007 (ASB). (2) If either at full left pedal position or full right pedal position a gap exists between the tail rotor yoke and the flapping stop, replace the tail rotor yoke with an airworthy tail rotor yoke. (3) If no gap exists between the tail rotor yoke and the flapping stop at either full right or full left pedal position, measure the gap between the tail rotor yoke and nut, P/N 222– 012–731–001, adjust the tail rotor pitch change mechanism, and adjust the tail rotor pedal forces in accordance with the Accomplishment Instruction, paragraphs 4 through 6 of the ASB. hours TIS or at the next annual inspection, whichever occurs first, instead of ‘‘at the next 150 hour or annual inspection, but no later than 31 December 2007.’’ DEPARTMENT OF TRANSPORTATION Other Information 14 CFR Part 39 (g) Alternative Methods of Compliance (AMOCs): The Manager, Safety Management Group, FAA, ATTN: Tyrone Millard, Aviation Safety Engineer, FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, Fort Worth, Texas 76193–0111, telephone (817) 222–5439, fax (817) 222–5961 has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. [Docket No. FAA–2008–0353; Directorate Identifier 2007–CE–101–AD; Amendment 39–15620; AD 2008–16–02] Related Information (h) MCAI Transport Canada Airworthiness Directive No. CF–2007–04, dated April 5, 2007, contains related information. Air Transport Association of America (ATA) Tracking Code (i) ATA Code JASC 6720: Tail Rotor Control System, Tail Rotor Pitch Change. Material Incorporated by Reference (j) You must use the specified portions of Bell Helicopter Textron Alert Service Bulletin No. 430–07–39, dated January 9, 2007, to do the actions required. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact Bell Helicopter Textron Canada, 12,800 Rue de l’Avenir, Mirabel, Quebec J7J1R4, telephone (450) 437–2862 or (800) 363–8023, fax (450) 433–0272. (3) You may review copies at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Fort Worth, Texas, 76193; 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 July 9, 2008. Mark R. Schilling, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. E8–17275 Filed 7–29–08; 8:45 am] BILLING CODE 4910–13–P Differences Between This AD and the MCAI (f) This AD differs from the MCAI in that it requires compliance within the next 150 VerDate Aug<31>2005 16:51 Jul 29, 2008 Jkt 214001 PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 Federal Aviation Administration RIN 2120–AA64 Airworthiness Directives; Hawker Beechcraft Corporation Model 390 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: We are adopting a new airworthiness directive (AD) for certain Hawker Beechcraft Corporation Model 390 airplanes. This AD requires you to repetitively do a post-flight check (owner/operator holding at least a private pilot certificate checking for residual heat in the angle-of-attack (AOA) probes or an appropriately-rated mechanic doing a maintenance manual operational test of the heat of the AOA probes) after every flight and replace or modify (upload software) the stall warning AOA transmitters. This AD results from reports of the potential for unannunciated loss of the heating function in the left-hand (LH) and righthand (RH) stall warning AOA transmitters of Model 390 airplanes. We are issuing this AD to correct potentially inadequate stall warning with loss of stick pusher function. DATES: This AD becomes effective on September 3, 2008. On September 3, 2008, the Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD. ADDRESSES: 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. To view the AD docket, go to U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590, or on the Internet at http:// www.regulations.gov. The docket number is FAA–2008–0353; Directorate Identifier 2007–CE–101–AD. FOR FURTHER INFORMATION CONTACT: Philip Petty, Aerospace Engineer, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Wichita, Kansas 67209; telephone: (316) 946– 4139; fax: (316) 946–4107. E:\FR\FM\30JYR1.SGM 30JYR1

Agencies

[Federal Register Volume 73, Number 147 (Wednesday, July 30, 2008)]
[Rules and Regulations]
[Pages 44140-44142]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-17275]


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

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

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

ACTION: Final rule.

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

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.

[[Page 44141]]


DATES: This AD becomes effective on September 3, 2008.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of September 3, 
2008.

ADDRESSES: You may examine the AD docket on the Internet at http://
www.regulations.gov or in person at the Docket Operations office, U.S. 
Department of Transportation, M-30, West Building Ground Floor, Room 
W12-140, 1200 New Jersey Avenue, SE., Washington, DC between 9 a.m. and 
5 p.m. Monday through Friday, except Federal holidays.
    You may get the service information identified in this AD from Bell 
Helicopter Textron Canada, 12,800 Rue de l'Avenir, Mirabel, Quebec 
J7J1R4, telephone (450) 437-2862 or (800) 363-8023, fax (450) 433-0272.
    Examining the AD Docket: The AD docket contains the Notice of 
Proposed Rulemaking (NPRM), the economic evaluation, any comments 
received, and other information. The street address and operating hours 
for the Docket Operations office (telephone (800) 647-5227) are in the 
ADDRESSES section of this AD. Comments will be available in the AD 
docket shortly after they are received.

FOR FURTHER INFORMATION CONTACT: Tyrone Millard, Aviation Safety 
Engineer, FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, Fort 
Worth, Texas 76193-0111, telephone (817) 222-5439, fax (817) 222-5961.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued an NPRM to amend 14 CFR part 39 to include an AD that 
would apply to BHTC Model 430 helicopters, serial numbers 49001 through 
49122, on November 2, 2007. That NPRM was published in the Federal 
Register on November 16, 2007 (72 FR 64540). That NPRM proposed to 
correct an unsafe condition for the specified products. The MCAI 
states: ``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.'' Because the cumulative effect of 
the tolerances on the various parts may result in the total assemblage 
outboard of the counterweight bellcrank being out of tolerance, the 
tail rotor yoke may contact the nut, part number (P/N) 222-012-731-001, 
before contacting the flapping stop, resulting in less tail rotor 
travel. Additionally, the manufacturer has indicated that the tail 
rotor counterweight bellcranks may be misaligned, resulting in higher 
tail rotor pedal forces and higher pilot workload after failure of the 
1 hydraulic system. Both the parts interference and the higher 
pedal forces constitute unsafe conditions. You may obtain further 
information by examining the MCAI and any related service information 
in the AD docket.

Comments

    By publishing the NPRM, we gave the public an opportunity to 
participate in developing this AD. However, we received no comment on 
the NPRM or on our determination of the cost to the public. Therefore, 
based on our review and evaluation of the available data, we have 
determined that air safety and the public interest require adopting the 
AD as proposed.

Relevant Service Information

    Bell Helicopter Textron has issued Alert Service Bulletin No. 430-
07-39, dated January 9, 2007, that describes revised rigging procedures 
for the tail rotor pitch change mechanism. The actions described in the 
MCAI are intended to correct the same unsafe condition as that 
identified in the service information.

Differences Between This AD and the MCAI

    We have reviewed the MCAI and related service information and, in 
general, agree with their substance. However, this AD requires 
compliance within the next 150 hours time-in-service or at the next 
annual inspection, whichever occurs first, instead of ``at the next 150 
hour or annual inspection, but no later than 31 December 2007.'' In 
making this change, we do not intend to differ substantively from the 
information provided in the MCAI. This difference is highlighted in the 
``Differences Between this AD and the MCAI'' section in the AD.

Costs of Compliance

    We estimate that this AD will affect 58 helicopters of U.S. 
registry. We also estimate that it will take about 2 work-hours per 
helicopter to comply with the basic requirements of this AD. The 
average labor rate is $80 per work-hour. A replacement yoke will cost 
about $21,218, assuming the part is no longer under warranty. However, 
because the service information lists this part as covered under 
warranty, we have assumed that there will be no charge for this part. 
Therefore, as we do not control warranty coverage for affected parties, 
some parties may incur costs higher than estimated here. Based on these 
assumptions and figures, we estimate the cost of this AD on U.S. 
operators to be $9,280, or $160 per helicopter.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation 
Programs,'' describes in more detail the scope of the Agency's 
authority.
    We are issuing this rulemaking under the authority described in 
``Subtitle VII, Part A, Subpart III, section 44701: General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We 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.
    Therefore, I certify this AD:
    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 and placed it in the AD docket.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

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


[[Page 44142]]


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


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new AD:

2008-15-04 Bell Helicopter Textron Canada: Amendment 39-15616. 
Docket No. FAA-2007-0177; Directorate Identifier 2007-SW-19-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective on 
September 3, 2008.

Other Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Model 430 helicopters, serial numbers 
49001 through 49122, certificated in any category.

Reason

    (d) The mandatory continuing airworthiness information (MCAI) 
states: ``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.''
    This ``possibility of parts interference'' occurs because the 
cumulative effect of the tolerances on the various parts may result 
in the total assemblage outboard of the counterweight bellcrank 
being out of tolerance and the tail rotor yoke may contact the nut, 
part number (P/N ) 222-012-731-001, before contacting the flapping 
stop. Further, the manufacturer has indicated that the tail rotor 
counterweight bellcranks may be misaligned, resulting in higher tail 
rotor pedal forces and higher pilot workload after failure of the 
1 hydraulic system. Both the parts interference and the 
higher pedal forces constitute unsafe conditions. This AD requires 
actions that are intended to address these unsafe conditions.

Actions and Compliance

    (e) Within the next 150 hours time-in-service (TIS) or at the 
next annual inspection, whichever occurs first, unless already 
accomplished, do the following:
    (1) Adjust the rigging of the tail rotor pitch change mechanism 
in accordance with the Accomplishment Instructions, paragraphs 1 and 
2, in Bell Helicopter Textron Alert Service Bulletin 430-07-39, 
dated January 9, 2007 (ASB).
    (2) If either at full left pedal position or full right pedal 
position a gap exists between the tail rotor yoke and the flapping 
stop, replace the tail rotor yoke with an airworthy tail rotor yoke.
    (3) If no gap exists between the tail rotor yoke and the 
flapping stop at either full right or full left pedal position, 
measure the gap between the tail rotor yoke and nut, P/N 222-012-
731-001, adjust the tail rotor pitch change mechanism, and adjust 
the tail rotor pedal forces in accordance with the Accomplishment 
Instruction, paragraphs 4 through 6 of the ASB.

Differences Between This AD and the MCAI

    (f) This AD differs from the MCAI in that it requires compliance 
within the next 150 hours TIS or at the next annual inspection, 
whichever occurs first, instead of ``at the next 150 hour or annual 
inspection, but no later than 31 December 2007.''

Other Information

    (g) Alternative Methods of Compliance (AMOCs): The Manager, 
Safety Management Group, FAA, ATTN: Tyrone Millard, Aviation Safety 
Engineer, FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, 
Fort Worth, Texas 76193-0111, telephone (817) 222-5439, fax (817) 
222-5961 has the authority to approve AMOCs for this AD, if 
requested using the procedures found in 14 CFR 39.19.

Related Information

    (h) MCAI Transport Canada Airworthiness Directive No. CF-2007-
04, dated April 5, 2007, contains related information.

Air Transport Association of America (ATA) Tracking Code

    (i) ATA Code JASC 6720: Tail Rotor Control System, Tail Rotor 
Pitch Change.

Material Incorporated by Reference

    (j) You must use the specified portions of Bell Helicopter 
Textron Alert Service Bulletin No. 430-07-39, dated January 9, 2007, 
to do the actions required.
    (1) The Director of the Federal Register approved the 
incorporation by reference of this service information under 5 
U.S.C. 552(a) and 1 CFR part 51.
    (2) For service information identified in this AD, contact Bell 
Helicopter Textron Canada, 12,800 Rue de l'Avenir, Mirabel, Quebec 
J7J1R4, telephone (450) 437-2862 or (800) 363-8023, fax (450) 433-
0272.
    (3) You may review copies at the FAA, Office of the Regional 
Counsel, Southwest Region, 2601 Meacham Blvd., Fort Worth, Texas, 
76193; 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 July 9, 2008.
Mark R. Schilling,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. E8-17275 Filed 7-29-08; 8:45 am]
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