Airworthiness Directives; Twin Commander Aircraft LLC Models 690, 690A, and 690B Airplanes, 63565-63568 [E9-28548]

Download as PDF Federal Register / Vol. 74, No. 232 / Friday, December 4, 2009 / Rules and Regulations 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 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: jlentini on DSKJ8SOYB1PROD with RULES ■ PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. VerDate Nov<24>2008 17:09 Dec 03, 2009 Jkt 220001 § 39.13 [Amended] 2. Section 39.13 is amended by adding a new airworthiness directive to read as follows: ■ 2009–25–10 Sikorsky Aircraft Corp.: Amendment 39–16130. Docket No. FAA–2009–1130; Directorate Identifier 2009–SW–40–AD. Applicability: Model S–92A helicopters, serial numbers 920006 through 920109, certificated in any category. Compliance: Required as indicated, unless done previously. To prevent complete loss of oil from the main gearbox (MGB), failure of the MGB, and subsequent loss of control of the helicopter, do the following: (a) Within 7 days, inspect the MGB lube system filter assembly for damage to the primary and secondary oil filters by following the Accomplishment Instructions, paragraphs 3.A.(4) and through 3.A.(6) of Sikorsky Alert Service Bulletin (ASB) No. 92–63–018, dated July 1, 2009 (ASB No. 92– 63–018). For purposes of this AD, ‘‘damage’’ is the presence of those conditions described in paragraphs 3.A.(5) and 3.A.(8) of the Accomplishment Instructions of ASB No. 92– 63–018. (b) If you find damage in the primary oil filter element (part number (P/N) 70351– 38801–102) as follows: ‘‘wavy pleats’’ as depicted in Figure 1, internal buckling or a crack as depicted in Figure 2, or indented dimples as depicted in Figure 3 of ASB No. 92–63–018 or damage in the secondary oil filter element (P/N 70351–38801–103) as follows: ‘‘wavy pleats’’ as depicted in Figure 4 or an elongated cup as depicted in Figure 5 of ASB No. 92–63–018, replace both the primary and secondary filters, packings, and filter bowl mounting studs, service the transmission and perform a functional test before further flight by following the Accomplishment Instructions, paragraphs 3.C.(1) through 3.C.(23), of ASB No. 92–63– 018, except this AD does not require you to return removed studs to HSI nor does it require you to contact the manufacturer. If you find damage in the tapped holes or in the MGB housing lockring counterbore, contact the Boston Aircraft Certification Office for an approved repair. (c) If you find no damage in the primary or secondary oil filter element, before further flight, replace the packings, service the transmission, and perform a functional test by following the Accomplishment Instructions, paragraphs 3.B.(1) through 3.B.(4) of ASB No. 92–63–018. (d) For those helicopters on which the primary or secondary oil filter element and filter bowl mounting studs were replaced as required by paragraph (b) of this AD: (1) Before the first flight of each day until the oil filter bowl, P/N AAC367–16D2A, is replaced, inspect the MGB lube system filter assembly for any oil leak. (2) Before further flight after any oil leak is detected as required by paragraph (d)(1) of this AD or within 30 days, whichever is earlier, replace the oil filter bowl. Note: Sikorsky ASB No. 92–63–019, dated July 1, 2009, pertains to the subject of this AD. PO 00000 Frm 00035 Fmt 4700 Sfmt 4700 63565 (e) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Contact the Manager, Boston Aircraft Certification Office, FAA, ATTN: Kirk Gustafson, Aviation Safety Engineer, Engine and Propeller Directorate, FAA, 12 New England Executive Park, Burlington, MA 01803, telephone (781) 238–7190, fax (781) 238–7170, for information about previously approved alternative methods of compliance. (f) The Joint Aircraft System/Component (JASC) Code is 6300: Main Rotor System. (g) Inspecting and replacing the main gearbox lube system assembly parts shall be done by following the specified portions of Sikorsky Alert Service Bulletin (ASB) No. 92–63–018, dated July 1, 2009. The Director of the Federal Register approved this incorporation by reference under 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Sikorsky Aircraft Corporation, Attn: Manager, Commercial Technical Support, mailstop s581a, 6900 Main Street, Stratford, CT, telephone (203) 383–4866, email address tsslibrary@sikorsky.com, or at http://www.sikorsky.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. (h) This amendment becomes effective on December 21, 2009. Issued in Fort Worth, Texas, on November 25, 2009. Lance T. Gant, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. E9–28863 Filed 12–3–09; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2009–0778; Directorate Identifier 2009–CE–040–AD; Amendment 39–16119; AD 2009–25–02] RIN 2120–AA64 Airworthiness Directives; Twin Commander Aircraft LLC Models 690, 690A, and 690B Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. SUMMARY: We are adopting a new airworthiness directive (AD) for certain Twin Commander Aircraft LLC Models 690, 690A, and 690B airplanes. This AD requires you to inspect between the surface of the left-hand (LH) and right- E:\FR\FM\04DER1.SGM 04DER1 63566 Federal Register / Vol. 74, No. 232 / Friday, December 4, 2009 / Rules and Regulations hand (RH) upper wing skins and the engine mount beam support straps for any signs of corrosion, replace the upper steel straps with parts of improved design, and modify both wings. This AD results from reports that corrosion was found between the mating surfaces of the wing upper skin surface and the engine mount beam support straps. We are issuing this AD to detect and correct corrosion on the engine mount beam support straps and the upper wing skins, which could result in failure of the engine mount beam support straps. This failure could lead to loss of the engine and possible loss of control of the airplane. DATES: This AD becomes effective on January 8, 2010. On January 8, 2010, the Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD. ADDRESSES: To get the service information identified in this AD, contact Twin Commander Aircraft LLC, 18933–59th Avenue, NE., Suite 115, Arlington, WA 98223, telephone: (360) 435–9797; fax: (360) 435–1112; Internet: http://www.twincommander.com. 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–2009–0778; Directorate Identifier 2009–CE–040–AD. FOR FURTHER INFORMATION CONTACT: Vince Massey, Aerospace Engineer, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone: (425) 917–6475; fax: (425) 917–6590; email: vince.massey@faa.gov. SUPPLEMENTARY INFORMATION: Discussion On August 21, 2009, we issued a proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to include an AD that would apply to certain Twin Commander Aircraft LLC Models 690, 690A, and 690B airplanes. This proposal was published in the Federal Register as a notice of proposed rulemaking (NPRM) on August 28, 2009 (74 FR 44308). The NPRM proposed to require you to inspect between the surface of the LH and RH upper wing skins and the engine mount beam support straps for any signs of corrosion, replace the upper steel straps with parts of improved design, and modify both wings. Comments We provided the public the opportunity to participate in developing this AD. The following presents the comments received on the proposal and FAA’s response to each comment: Comment Issue: Extend Compliance Time Michael Curtis Pidek, William I. Smith, and Tom Bayer all state that with 275 airplanes affected by this AD and only 15 service centers available to do the actions required in this AD, there is not enough time to comply with the AD. All three commenters request an extension of the compliance time to allow enough time for the service centers to schedule the work without grounding airplanes until the work can be done. We do not agree with the commenters. Over 65 airplanes are already in compliance with this AD. We have consulted with Twin Commander Aircraft LLC and they have covered this issue with the service centers. The service centers know how much work is required since they have already done the work on over 65 of the affected airplanes. The service centers plan on using multiple teams to work on several airplanes at the same time. They have confirmed they can perform the actions required in this AD in the compliance time as proposed. Part of the alternative method of compliance (AMOC) provisions of 14 CFR 39.19 is an extension of the compliance time provided a level of safety acceptable to the FAA is met. The FAA will review any AMOCs of this nature on a case-by-case basis. If we determine the proposal presents an acceptable level of safety, we will approve it as an AMOC to the AD. We are not changing the final rule AD action based on these comments. Conclusion We have carefully reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed except for minor editorial corrections. We have determined that these minor corrections: • Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM. Costs of Compliance We estimate that this AD will affect 275 airplanes in the U.S. registry. We estimate the following costs to do the inspection: Labor cost Parts cost Total cost per airplane Total cost on U.S. operators 80 work-hours × $80 per hour = $6,400 ...................... Not applicable ............................................................... $6,400 $1,760,000 We estimate the following costs to do any necessary repairs/replacements that will be required based on the results of the inspection. We have no way of determining the number of airplanes that may need this repair/replacement: SHORT MODIFICATION—OPTION A * jlentini on DSKJ8SOYB1PROD with RULES Labor cost Parts cost Total cost per airplane per side 250 work-hours × $80 per hour = $20,000 per side .................. $9,170 per kit per side ............................................................... $29,170 VerDate Nov<24>2008 17:09 Dec 03, 2009 Jkt 220001 PO 00000 Frm 00036 Fmt 4700 Sfmt 4700 E:\FR\FM\04DER1.SGM 04DER1 63567 Federal Register / Vol. 74, No. 232 / Friday, December 4, 2009 / Rules and Regulations MIDDLE MODIFICATION—OPTION B * Labor cost Parts cost Total cost per airplane per side 280 work-hours × $80 per hour = $22,400 per side .................. $9,170 per kit per side ............................................................... $31,570 LONG MODIFICATION—OPTION C * Labor cost Parts cost Total cost per airplane per side 320 work-hours × $80 per hour = $25,600 per side .................. $9,170 per kit per side ............................................................... $34,770 Note: * Depending on airplane configuration, airplanes with rectangular plates will need the Plate and Hardware Kit (SB237–4) at $2,090 per side. Labor to install this kit is included in Options A, B, and C. STRAP ONLY REPLACEMENT—OPTION D Labor cost Parts cost Total cost per airplane per side 75 work-hours × $80 per hour = $6,000 per side ...................... $6,190 per strap per side ........................................................... $12,190 We estimate the following costs to do the installation of access holes: Labor cost Parts cost Total cost per airplane Total cost on U.S. operators 30 work-hours × $80 per hour = $2,400 ..................................................................................... $1,293 $3,693 $1,015,575 Labor cost Parts cost Total cost per airplane Total cost on U.S. operators 8.5 work-hours × $80 per hour = $680 ....................................................................................... $250 $930 $255,750 We estimate the following costs to do the wing fastener modification: jlentini on DSKJ8SOYB1PROD 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 VerDate Nov<24>2008 17:09 Dec 03, 2009 Jkt 220001 that is likely to exist or develop on products identified in this AD. 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 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, PO 00000 Frm 00037 Fmt 4700 Sfmt 4700 on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a summary of the costs to comply with this AD (and other information as included in the Regulatory Evaluation) and placed it in the AD Docket. You may get a copy of this summary by sending a request to us at the address listed under ADDRESSES. Include ‘‘Docket No. FAA–2009–0778; Directorate Identifier 2009–CE–040– AD’’ in your request. 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, ■ E:\FR\FM\04DER1.SGM 04DER1 63568 Federal Register / Vol. 74, No. 232 / Friday, December 4, 2009 / Rules and Regulations the Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows: Effective Date (a) This AD becomes effective on January 8, 2010. PART 39—AIRWORTHINESS DIRECTIVES Affected ADs (b) None. 1. The authority citation for part 39 continues to read as follows: Applicability (c) This AD applies to the following airplane models and serial numbers that are certificated in any category: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] Models 2. FAA amends § 39.13 by adding a new AD to read as follows: Serial Nos. (S/Ns) 690 ......... 690A ...... All S/Ns All S/Ns except 11195 and 11279. All S/Ns except 11361, 11383, 11527, and 11536. ■ 2009–25–02 Twin Commander Aircraft LLC: Amendment 39–16119; Docket No. FAA–2009–0778; Directorate Identifier 2009–CE–040–AD. 690B ...... Unsafe Condition (d) This AD results from reports that corrosion was found between the mating surfaces of the wing upper skin surface and the engine mount beam support straps. We are issuing this AD to detect and correct corrosion on the engine mount beam support straps and upper wing skins, which could result in failure of the engine mount beam support straps. This failure could lead to loss of the engine and possible loss of control of the airplane. Compliance (e) To address this problem, you must do the following, unless already done: Actions Compliance Procedures (1) Inspect between the surface of the left-hand (LH) and right-hand (RH) upper wing skins and the engine mount beam support straps for any signs of corrosion and determine the extent of any corrosion found. (2) Install modification access holes in the LH and RH lower wing skins. Within the next 150 hours time-in-service after January 8, 2010 (the effective date of this AD) or within the next 12 months after January 8, 2010 (the effective date of this AD), whichever occurs first. Before further flight after the inspection required in paragraph (e)(1) of this AD. Follow Twin Commander Aircraft LLC Alert Service Bulletin No. 237, dated May 13, 2005, pages 1 through 14. (3) If corrosion damage is found during the inspection required in paragraph (e)(1) of this AD, perform necessary modification. Before further flight after the inspection required in paragraph (e)(1) of this AD. (4) If corrosion damage is not found during the inspection required in paragraph (e)(1) of this AD, do the upper steel strap replacements. Before further flight after the inspection required in paragraph (e)(1) of this AD. (5) Install additional wing fasteners on the LH and RH wing. Before further flight after the inspection required in paragraph (e)(1) of the AD. Note: Although not required by this AD, we highly recommend compliance with Twin Commander Aircraft Corporation Service Bulletin No. 217, Revision No. 1, dated May 26, 1993, Engine Nacelle Firewall Reinforcement; and Twin Commander Aircraft LLC Alert Service Bulletin No. 239, dated February 13, 2006, Outboard Flap— Inboard Hinge Inspection & Reinforcement. jlentini on DSKJ8SOYB1PROD with RULES Alternative Methods of Compliance (AMOCs) (f) The Manager, Seattle Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Vince Massey, Aerospace Engineer, FAA, Seattle ACO, 1601 Lind Avenue, SW, Renton, Washington 98057–3356; telephone: (425) 917–6475; fax: (425) 917–6590; email: vince.massey@faa.gov. 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. VerDate Nov<24>2008 17:09 Dec 03, 2009 Jkt 220001 Material Incorporated by Reference (g) You must use Twin Commander Aircraft LLC Alert Service Bulletin No. 237, dated May 13, 2005; Twin Commander Aircraft Corporation Custom Kit No. 150, dated July 8, 1994; and Gulfstream American Corporation Service Bulletin No. 182, dated March 2, 1981, 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 this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact Twin Commander Aircraft LLC, 18933—59th Avenue, NE., Arlington, WA 98223, telephone: (360) 435–9797; fax: (360) 435–1112; Internet: http:// www.twincommander.com. (3) You may review copies of the service information incorporated by reference for this AD at the FAA, Central Region, Office of the Regional Counsel, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the Central Region, call (816) 329–3768. (4) You may also review copies of the service information incorporated by reference PO 00000 Frm 00038 Fmt 4700 Sfmt 4700 Follow the Accomplishment Instructions, steps 1 through 4 and 6 through 9, of Twin Commander Aircraft Corporation Custom Kit No. 150, dated July 8, 1994, as specified in Twin Commander Aircraft LLC Alert Service Bulletin No. 237, dated May 13, 2005. Follow Twin Commander Aircraft LLC Alert Service Bulletin No. 237, dated May 13, 2005, Part II, Options A, B, or C, on pages 15 through 29 and 31. Follow Twin Commander Aircraft LLC Alert Service Bulletin No. 237, dated May 13, 2005, Part II, Option D, on pages 30 and 31. Follow Gulfstream American Corporation Service Bulletin No. 182, dated March 2, 1981. for this AD 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. Issued in Kansas City, Missouri, on November 20, 2009. Margaret Kline, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E9–28548 Filed 12–3–09; 8:45 am] BILLING CODE 4910–13–P E:\FR\FM\04DER1.SGM 04DER1

Agencies

[Federal Register Volume 74, Number 232 (Friday, December 4, 2009)]
[Rules and Regulations]
[Pages 63565-63568]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-28548]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0778; Directorate Identifier 2009-CE-040-AD; 
Amendment 39-16119; AD 2009-25-02]
RIN 2120-AA64


Airworthiness Directives; Twin Commander Aircraft LLC Models 690, 
690A, and 690B Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
Twin Commander Aircraft LLC Models 690, 690A, and 690B airplanes. This 
AD requires you to inspect between the surface of the left-hand (LH) 
and right-

[[Page 63566]]

hand (RH) upper wing skins and the engine mount beam support straps for 
any signs of corrosion, replace the upper steel straps with parts of 
improved design, and modify both wings. This AD results from reports 
that corrosion was found between the mating surfaces of the wing upper 
skin surface and the engine mount beam support straps. We are issuing 
this AD to detect and correct corrosion on the engine mount beam 
support straps and the upper wing skins, which could result in failure 
of the engine mount beam support straps. This failure could lead to 
loss of the engine and possible loss of control of the airplane.

DATES: This AD becomes effective on January 8, 2010.
    On January 8, 2010, the Director of the Federal Register approved 
the incorporation by reference of certain publications listed in this 
AD.

ADDRESSES: To get the service information identified in this AD, 
contact Twin Commander Aircraft LLC, 18933-59th Avenue, NE., Suite 115, 
Arlington, WA 98223, telephone: (360) 435-9797; fax: (360) 435-1112; 
Internet: http://www.twincommander.com.
    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-2009-0778; 
Directorate Identifier 2009-CE-040-AD.

FOR FURTHER INFORMATION CONTACT: Vince Massey, Aerospace Engineer, FAA, 
Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, 
Washington 98057-3356; telephone: (425) 917-6475; fax: (425) 917-6590; 
e-mail: vince.massey@faa.gov.

SUPPLEMENTARY INFORMATION: 

Discussion

    On August 21, 2009, we issued a proposal to amend part 39 of the 
Federal Aviation Regulations (14 CFR part 39) to include an AD that 
would apply to certain Twin Commander Aircraft LLC Models 690, 690A, 
and 690B airplanes. This proposal was published in the Federal Register 
as a notice of proposed rulemaking (NPRM) on August 28, 2009 (74 FR 
44308). The NPRM proposed to require you to inspect between the surface 
of the LH and RH upper wing skins and the engine mount beam support 
straps for any signs of corrosion, replace the upper steel straps with 
parts of improved design, and modify both wings.

Comments

    We provided the public the opportunity to participate in developing 
this AD. The following presents the comments received on the proposal 
and FAA's response to each comment:

Comment Issue: Extend Compliance Time

    Michael Curtis Pidek, William I. Smith, and Tom Bayer all state 
that with 275 airplanes affected by this AD and only 15 service centers 
available to do the actions required in this AD, there is not enough 
time to comply with the AD.
    All three commenters request an extension of the compliance time to 
allow enough time for the service centers to schedule the work without 
grounding airplanes until the work can be done.
    We do not agree with the commenters. Over 65 airplanes are already 
in compliance with this AD. We have consulted with Twin Commander 
Aircraft LLC and they have covered this issue with the service centers. 
The service centers know how much work is required since they have 
already done the work on over 65 of the affected airplanes. The service 
centers plan on using multiple teams to work on several airplanes at 
the same time. They have confirmed they can perform the actions 
required in this AD in the compliance time as proposed.
    Part of the alternative method of compliance (AMOC) provisions of 
14 CFR 39.19 is an extension of the compliance time provided a level of 
safety acceptable to the FAA is met. The FAA will review any AMOCs of 
this nature on a case-by-case basis. If we determine the proposal 
presents an acceptable level of safety, we will approve it as an AMOC 
to the AD.
    We are not changing the final rule AD action based on these 
comments.

Conclusion

    We have carefully reviewed the available data and determined that 
air safety and the public interest require adopting the AD as proposed 
except for minor editorial corrections. We have determined that these 
minor corrections:
     Are consistent with the intent that was proposed in the 
NPRM for correcting the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM.

Costs of Compliance

    We estimate that this AD will affect 275 airplanes in the U.S. 
registry.
    We estimate the following costs to do the inspection:

----------------------------------------------------------------------------------------------------------------
                                                                                 Total cost per   Total cost on
                  Labor cost                              Parts cost                airplane      U.S. operators
----------------------------------------------------------------------------------------------------------------
80 work-hours x $80 per hour = $6,400........  Not applicable.................          $6,400       $1,760,000
----------------------------------------------------------------------------------------------------------------

     We estimate the following costs to do any necessary repairs/
replacements that will be required based on the results of the 
inspection. We have no way of determining the number of airplanes that 
may need this repair/replacement:

                     Short Modification--Option A *
------------------------------------------------------------------------
                                                          Total cost per
            Labor cost                  Parts cost         airplane per
                                                               side
------------------------------------------------------------------------
250 work-hours x $80 per hour =    $9,170 per kit per           $29,170
 $20,000 per side.                  side.
------------------------------------------------------------------------


[[Page 63567]]


                     Middle Modification--Option B *
------------------------------------------------------------------------
                                                          Total cost per
            Labor cost                  Parts cost         airplane per
                                                               side
------------------------------------------------------------------------
280 work-hours x $80 per hour =    $9,170 per kit per           $31,570
 $22,400 per side.                  side.
------------------------------------------------------------------------


                      Long Modification--Option C *
------------------------------------------------------------------------
                                                          Total cost per
            Labor cost                  Parts cost         airplane per
                                                               side
------------------------------------------------------------------------
320 work-hours x $80 per hour =    $9,170 per kit per           $34,770
 $25,600 per side.                  side.
------------------------------------------------------------------------


    Note: * Depending on airplane configuration, airplanes with 
rectangular plates will need the Plate and Hardware Kit (SB237-4) at 
$2,090 per side. Labor to install this kit is included in Options A, 
B, and C.


                    Strap Only Replacement--Option D
------------------------------------------------------------------------
                                                          Total cost per
            Labor cost                  Parts cost         airplane per
                                                               side
------------------------------------------------------------------------
75 work-hours x $80 per hour =     $6,190 per strap per         $12,190
 $6,000 per side.                   side.
------------------------------------------------------------------------

    We estimate the following costs to do the installation of access 
holes:

----------------------------------------------------------------------------------------------------------------
                                                                                 Total cost per   Total cost on
                          Labor cost                              Parts cost        airplane      U.S. operators
----------------------------------------------------------------------------------------------------------------
30 work-hours x $80 per hour = $2,400........................          $1,293           $3,693       $1,015,575
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do the wing fastener 
modification:

----------------------------------------------------------------------------------------------------------------
                                                                                 Total cost per   Total cost on
                          Labor cost                              Parts cost        airplane      U.S. operators
----------------------------------------------------------------------------------------------------------------
8.5 work-hours x $80 per hour = $680.........................            $250             $930         $255,750
----------------------------------------------------------------------------------------------------------------

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 AD.

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 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 a summary of the costs to comply with this AD (and 
other information as included in the Regulatory Evaluation) and placed 
it in the AD Docket. You may get a copy of this summary by sending a 
request to us at the address listed under ADDRESSES. Include ``Docket 
No. FAA-2009-0778; Directorate Identifier 2009-CE-040-AD'' in your 
request.

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,

[[Page 63568]]

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. FAA amends Sec.  39.13 by adding a new AD to read as follows:

2009-25-02 Twin Commander Aircraft LLC: Amendment 39-16119; Docket 
No. FAA-2009-0778; Directorate Identifier 2009-CE-040-AD.

Effective Date

    (a) This AD becomes effective on January 8, 2010.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to the following airplane models and serial 
numbers that are certificated in any category:

------------------------------------------------------------------------
              Models                         Serial Nos. (S/Ns)
------------------------------------------------------------------------
690...............................  All S/Ns
690A..............................  All S/Ns except 11195 and 11279.
690B..............................  All S/Ns except 11361, 11383, 11527,
                                     and 11536.
------------------------------------------------------------------------

Unsafe Condition

    (d) This AD results from reports that corrosion was found 
between the mating surfaces of the wing upper skin surface and the 
engine mount beam support straps. We are issuing this AD to detect 
and correct corrosion on the engine mount beam support straps and 
upper wing skins, which could result in failure of the engine mount 
beam support straps. This failure could lead to loss of the engine 
and possible loss of control of the airplane.

Compliance

    (e) To address this problem, you must do the following, unless 
already done:

------------------------------------------------------------------------
           Actions                 Compliance            Procedures
------------------------------------------------------------------------
(1) Inspect between the       Within the next 150   Follow Twin
 surface of the left-hand      hours time-in-        Commander Aircraft
 (LH) and right-hand (RH)      service after         LLC Alert Service
 upper wing skins and the      January 8, 2010       Bulletin No. 237,
 engine mount beam support     (the effective date   dated May 13, 2005,
 straps for any signs of       of this AD) or        pages 1 through 14.
 corrosion and determine the   within the next 12
 extent of any corrosion       months after
 found.                        January 8, 2010
                               (the effective date
                               of this AD),
                               whichever occurs
                               first.
(2) Install modification      Before further        Follow the
 access holes in the LH and    flight after the      Accomplishment
 RH lower wing skins.          inspection required   Instructions, steps
                               in paragraph (e)(1)   1 through 4 and 6
                               of this AD.           through 9, of Twin
                                                     Commander Aircraft
                                                     Corporation Custom
                                                     Kit No. 150, dated
                                                     July 8, 1994, as
                                                     specified in Twin
                                                     Commander Aircraft
                                                     LLC Alert Service
                                                     Bulletin No. 237,
                                                     dated May 13, 2005.
(3) If corrosion damage is    Before further        Follow Twin
 found during the inspection   flight after the      Commander Aircraft
 required in paragraph         inspection required   LLC Alert Service
 (e)(1) of this AD, perform    in paragraph (e)(1)   Bulletin No. 237,
 necessary modification.       of this AD.           dated May 13, 2005,
                                                     Part II, Options A,
                                                     B, or C, on pages
                                                     15 through 29 and
                                                     31.
(4) If corrosion damage is    Before further        Follow Twin
 not found during the          flight after the      Commander Aircraft
 inspection required in        inspection required   LLC Alert Service
 paragraph (e)(1) of this      in paragraph (e)(1)   Bulletin No. 237,
 AD, do the upper steel        of this AD.           dated May 13, 2005,
 strap replacements.                                 Part II, Option D,
                                                     on pages 30 and 31.
(5) Install additional wing   Before further        Follow Gulfstream
 fasteners on the LH and RH    flight after the      American
 wing.                         inspection required   Corporation Service
                               in paragraph (e)(1)   Bulletin No. 182,
                               of the AD.            dated March 2,
                                                     1981.
------------------------------------------------------------------------


    Note: Although not required by this AD, we highly recommend 
compliance with Twin Commander Aircraft Corporation Service Bulletin 
No. 217, Revision No. 1, dated May 26, 1993, Engine Nacelle Firewall 
Reinforcement; and Twin Commander Aircraft LLC Alert Service 
Bulletin No. 239, dated February 13, 2006, Outboard Flap--Inboard 
Hinge Inspection & Reinforcement.

Alternative Methods of Compliance (AMOCs)

    (f) The Manager, Seattle Aircraft Certification Office (ACO), 
FAA, has the authority to approve AMOCs for this AD, if requested 
using the procedures found in 14 CFR 39.19. Send information to 
ATTN: Vince Massey, Aerospace Engineer, FAA, Seattle ACO, 1601 Lind 
Avenue, SW, Renton, Washington 98057-3356; telephone: (425) 917-
6475; fax: (425) 917-6590; email: vince.massey@faa.gov. 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.

Material Incorporated by Reference

    (g) You must use Twin Commander Aircraft LLC Alert Service 
Bulletin No. 237, dated May 13, 2005; Twin Commander Aircraft 
Corporation Custom Kit No. 150, dated July 8, 1994; and Gulfstream 
American Corporation Service Bulletin No. 182, dated March 2, 1981, 
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 this service information under 5 
U.S.C. 552(a) and 1 CFR part 51.
    (2) For service information identified in this AD, contact Twin 
Commander Aircraft LLC, 18933--59th Avenue, NE., Arlington, WA 
98223, telephone: (360) 435-9797; fax: (360) 435-1112; Internet: 
http://www.twincommander.com.
    (3) You may review copies of the service information 
incorporated by reference for this AD at the FAA, Central Region, 
Office of the Regional Counsel, 901 Locust, Kansas City, Missouri 
64106. For information on the availability of this material at the 
Central Region, call (816) 329-3768.
    (4) You may also review copies of the service information 
incorporated by reference for this AD 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.

    Issued in Kansas City, Missouri, on November 20, 2009.
Margaret Kline,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E9-28548 Filed 12-3-09; 8:45 am]
BILLING CODE 4910-13-P