Airworthiness Directives; Fokker Services B.V. Model F.28 Mark 0100 Airplanes, 423-426 [2010-32990]

Download as PDF Federal Register / Vol. 76, No. 3 / Wednesday, January 5, 2011 / Rules and Regulations Service Bulletin A310–27–2099, Revision 01, dated March 21, 2008. (1) For airplanes on which the inspection required by paragraph (g) of this AD has been done before the effective date of this AD: Within 400 flight cycles after accomplishing the inspection. (2) For airplanes on which the inspection required by paragraph (g) of this AD has been done on or after the effective date of this AD: Within 400 flight hours after accomplishing the inspection required by paragraph (g) of this AD. New Requirements of This AD Actions (i) Accomplishment of the actions required by paragraph (h) do not terminate the repetitive inspections required by paragraph (g) of this AD. FAA AD Differences WReier-Aviles on DSKGBLS3C1PROD with RULES Note 2: This AD differs from the MCAI and/or service information as follows: No differences. Other FAA AD Provisions (j) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, Transport Airplane Directorate, 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: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057– 3356; telephone (425) 227–2125; fax (425) 227–1149. Before using any approved AMOC on any airplane to which the AMOC applies, notify your principal maintenance inspector (PMI) or principal avionics inspector (PAI), as appropriate, or lacking a principal inspector, your local Flight Standards District Office. The AMOC approval letter must specifically reference this AD. AMOCs approved previously in accordance with AD 2007–02–22, Amendment 39–14909, are approved as AMOCs for the corresponding provisions of paragraphs (g) and (h) of this AD. (2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAAapproved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. (3) Reporting Requirements: A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB Control Number. The OMB Control Number for this information collection is 2120–0056. Public reporting for this collection of information is estimated to be approximately 5 minutes per response, including the time for reviewing instructions, VerDate Mar<15>2010 15:20 Jan 04, 2011 Jkt 223001 completing and reviewing the collection of information. All responses to this collection of information are mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at: 800 Independence Ave. SW., Washington, DC 20591, Attn: Information Collection Clearance Officer, AES–200. (k) Refer to MCAI European Aviation Safety Agency Airworthiness Directive 2006– 0111R1, dated August 26, 2009; and Airbus Mandatory Service Bulletin A310–27–2099, Revision 01, dated March 21, 2008; for related information. Material Incorporated by Reference (l) You must use Airbus Mandatory Service Bulletin A310–27–2099, Revision 01, dated March 21, 2008, 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 Airbus Mandatory Service Bulletin A310–27– 2099, Revision 01, dated March 21, 2008, under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact Airbus SAS—EAW (Airworthiness Office), 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; e-mail: account.airwortheas@airbus.com; Internet https:// www.airbus.com. (3) You may review copies of the service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227–1221. (4) You may also review copies of the service information that is incorporated by reference 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: https://www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on December 17, 2010. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2010–32987 Filed 1–4–11; 8:45 am] Fmt 4700 Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2010–0701; Directorate Identifier 2010–NM–017–AD; Amendment 39–16561; AD 2011–01–08] Airworthiness Directives; Fokker Services B.V. Model F.28 Mark 0100 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are superseding an existing airworthiness directive (AD) that applies to the products listed above. 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 MCAI describes the unsafe condition as: SUMMARY: Two reports have been received where, during inspection of the vertical stabilizer of F28 Mark 0100 aeroplanes, one of the bolts that connect the horizontal stabilizer control unit actuator with the dog-links was found broken (one on the nut side & one on the head side). In both occasions, the bolt shaft was still present in the connection and therefore the horizontal stabilizer function was not affected. If a single dog-link connection fails, the complete stabilizer load is taken up by the remaining dog-link connection. * * * To address and correct this unsafe condition EASA [European Aviation Safety Agency] issued AD 2007–0287 [corresponding FAA AD 2008–22–14] that required a one-time inspection of the affected bolts, * * * and replacement of failed bolts with serviceable parts. EASA AD 2007–0287 also required the installation of a tie wrap through the lower bolts of the horizontal stabilizer control unit, to keep the bolt in place in the event of a bolt head failure. Recent examination revealed that the bolts failed due to stress corrosion, attributed to excessive bolt torque. Investigation of the recently failed bolts showed that the modification as required by AD 2007–0287 is not adequate. * * * * * Loss of horizontal stabilizer function could result in partial loss of control of the airplane. We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective February 9, 2011. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of February 9, 2011. BILLING CODE 4910–13–P Frm 00005 DEPARTMENT OF TRANSPORTATION RIN 2120–AA64 Related Information PO 00000 423 Sfmt 4700 E:\FR\FM\05JAR1.SGM 05JAR1 424 Federal Register / Vol. 76, No. 3 / Wednesday, January 5, 2011 / Rules and Regulations The Director of the Federal Register approved the incorporation by reference of a certain other publication listed in this AD as of December 26, 2008 (73 FR 70261, November 20, 2008). ADDRESSES: You may examine the AD docket on the Internet at https:// www.regulations.gov or in person at the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC. FOR FURTHER INFORMATION CONTACT: Tom Rodriguez, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1137; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: Discussion WReier-Aviles on DSKGBLS3C1PROD with RULES We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. That NPRM was published in the Federal Register on July 27, 2010 (75 FR 43876), and proposed to supersede AD 2008– 22–14, Amendment 39–15710 (73 FR 70261, November 20, 2008). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states: Two reports have been received where, during inspection of the vertical stabilizer of F28 Mark 0100 aeroplanes, one of the bolts that connect the horizontal stabilizer control unit actuator with the dog-links was found broken (one on the nut side & one on the head side). In both occasions, the bolt shaft was still present in the connection and therefore the horizontal stabilizer function was not affected. If a single dog-link connection fails, the complete stabilizer load is taken up by the remaining dog-link connection. Any failed connection should be detected and corrected at the next scheduled inspection. To address and correct this unsafe condition EASA [European Aviation Safety Agency] issued AD 2007–0287 [corresponding FAA AD 2008–22–14] that required a one-time inspection of the affected bolts, Part Number (P/N) 23233–1, and replacement of failed bolts with serviceable parts. EASA AD 2007–0287 also required the installation of a tie wrap through the lower bolts of the horizontal stabilizer control unit, to keep the bolt in place in the event of a bolt head failure. Recent examination revealed that the bolts failed due to stress corrosion, attributed to excessive bolt torque. Investigation of the recently failed bolts showed that the modification as required by AD 2007–0287 is not adequate. To address the stress corrosion, the manufacturer of the bolt, Goodrich, has introduced a bolt with an improved corrosion VerDate Mar<15>2010 15:20 Jan 04, 2011 Jkt 223001 protection, P/N 23233–3, through Service Bulletin 23100–27–29. For the reasons described above, this EASA AD retains the requirements of AD 2007– 0287, which is superseded, and adds the requirement to replace the affected P/N 23233–1 bolts with improved bolts. Concurrently, the tie-wrap must be removed. Loss of horizontal stabilizer function could result in partial loss of control of the airplane. You may obtain further information by examining the MCAI in the AD docket. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM or on the determination of the cost to the public. Conclusion We reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed. Differences Between This AD and the MCAI or Service Information We have reviewed the MCAI and related service information and, in general, agree with their substance. But we might have found it necessary to use different words from those in the MCAI to ensure the AD is clear for U.S. operators and is enforceable. In making these changes, we do not intend to differ substantively from the information provided in the MCAI and related service information. We might also have required different actions in this AD from those in the MCAI in order to follow our FAA policies. Any such differences are highlighted in a Note within the AD. Costs of Compliance We estimate that this AD will affect about 4 products of U.S. registry. The actions that are required by AD 2008–22–14 and retained in this AD take about 3 work-hours per product, at an average labor rate of $85 per workhour. Based on these figures, the estimated cost of the currently required actions is $255 per product. We estimate that it will take about 7 work-hours per product to comply with the new basic requirements of this AD. The average labor rate is $85 per workhour. Required parts will cost about $1,550 per product. Where the service information lists required parts costs that are covered under warranty, we have assumed that there will be no charge for these costs. As we do not control warranty coverage for affected parties, some parties may incur costs higher than estimated here. Based on PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 these figures, we estimate the cost of this AD to the U.S. operators to be $8,580, or $2,145 per product. 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. For the reasons discussed above, 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 a regulatory evaluation of the estimated costs to comply with this AD and placed it in the AD docket. Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains the NPRM, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. E:\FR\FM\05JAR1.SGM 05JAR1 Federal Register / Vol. 76, No. 3 / Wednesday, January 5, 2011 / Rules and Regulations 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: ■ * 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. [Amended] 2. The FAA amends § 39.13 by removing Amendment 39–15710 (73 FR 70261, November 20, 2008) and adding the following new AD: ■ 2011–01–08 Fokker Services B.V.: Amendment 39–16561. Docket No. FAA–2010–0701; Directorate Identifier 2010–NM–017–AD. Effective Date (a) This airworthiness directive (AD) becomes effective February 9, 2011. Affected ADs (b) This AD supersedes AD 2008–22–14, Amendment 39–15710. Applicability (c) This AD applies to Fokker Services B.V. Model F.28 Mark 0100 airplanes, certificated in any category, all serial numbers. WReier-Aviles on DSKGBLS3C1PROD with RULES Subject (d) Air Transport Association (ATA) of America Code 27: Flight Controls. Reason (e) The mandatory continuing airworthiness information (MCAI) states: Two reports have been received where, during inspection of the vertical stabilizer of F28 Mark 0100 aeroplanes, one of the bolts that connect the horizontal stabilizer control unit actuator with the dog-links was found broken (one on the nut side & one on the head side). In both occasions, the bolt shaft was still present in the connection and therefore the horizontal stabilizer function was not affected. If a single dog-link connection fails, the complete stabilizer load is taken up by the remaining dog-link connection. * * * To address and correct this unsafe condition EASA [European Aviation Safety Agency] issued AD 2007–0287 [corresponding FAA AD 2008–22–14] that required a one-time inspection of the affected bolts, * * * and replacement of failed bolts with serviceable parts. EASA AD 2007–0287 also required the installation of a tie wrap through the lower bolts of the horizontal VerDate Mar<15>2010 15:20 Jan 04, 2011 Jkt 223001 * * * * Loss of horizontal stabilizer function could result in partial loss of control of the airplane. PART 39—AIRWORTHINESS DIRECTIVES § 39.13 stabilizer control unit, to keep the bolt in place in the event of a bolt head failure. Recent examination revealed that the bolts failed due to stress corrosion, attributed to excessive bolt torque. Investigation of the recently failed bolts showed that the modification as required by AD 2007–0287 is not adequate. Compliance (f) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Restatement of Requirements of AD 2008– 22–14 Actions and Compliance (g) Unless already done, within 6 months after December 26, 2008 (the effective date of AD 2008–22–14), do the following actions. (1) Perform a one-time inspection (integrity check) for failure of the lower bolts of the stabilizer control unit dog-links, in accordance with the Accomplishment Instructions of Fokker Service Bulletin SBF100–27–091, dated August 31, 2007. If a failed bolt is found, before further flight, replace the bolt with a serviceable bolt in accordance with the Accomplishment Instructions of that service bulletin. (2) Install a tie-wrap through the lower bolts of the stabilizer control unit, in accordance with the Accomplishment Instructions of Fokker Service Bulletin SBF100–27–091, dated August 31, 2007. New Requirements of This AD Actions (h) Within 30 months after the effective date of this AD, do the actions specified in paragraphs (h)(1) and (h)(2) of this AD concurrently. Accomplishing the actions of both paragraphs (h)(1) and (h)(2) of this AD terminates the actions required by paragraph (g) of this AD. (1) Remove the tie-wrap, P/N MS3367–2– 9, from the lower bolts of the horizontal stabilizer control unit, in accordance with the Accomplishment Instructions of Fokker Service Bulletin SBF100–27–092, dated April 27, 2009. (2) Remove the lower bolts, P/N 23233–1, of the horizontal stabilizer control unit and install bolts, P/N 23233–3, in accordance with the Accomplishment Instructions of Goodrich Service Bulletin 23100–27–29, dated November 14, 2008. (i) After accomplishing the requirements of paragraph (h) of this AD, do not install a bolt having P/N 23233–1 or a tie-wrap having P/N MS3367–2–9. FAA AD Differences Note 1: This AD differs from the MCAI and/or service information as follows: No differences. PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 425 Other FAA AD Provisions (j) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, 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: Tom Rodriguez, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1137; fax (425) 227–1149. Before using any approved AMOC on any airplane to which the AMOC applies, notify your principal maintenance inspector (PMI) or principal avionics inspector (PAI), as appropriate, or lacking a principal inspector, your local Flight Standards District Office. The AMOC approval letter must specifically reference this AD. (2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAAapproved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. (3) Reporting Requirements: A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB Control Number. The OMB Control Number for this information collection is 2120–0056. Public reporting for this collection of information is estimated to be approximately 5 minutes per response, including the time for reviewing instructions, completing and reviewing the collection of information. All responses to this collection of information are mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at: 800 Independence Ave. SW., Washington, DC 20591, Attn: Information Collection Clearance Officer, AES–200. Related Information (k) Refer to MCAI EASA Airworthiness Directive 2009–0216, dated October 7, 2009; Fokker Service Bulletin SBF100–27–091, dated August 31, 2007; Fokker Service Bulletin SBF100–27–092, dated April 27, 2009; and Goodrich Service Bulletin 23100– 27–29, dated November 14, 2008; for related information. Material Incorporated by Reference (l) You must use the applicable service information contained in Table 1 of this AD to do the actions required by this AD, unless the AD specifies otherwise. E:\FR\FM\05JAR1.SGM 05JAR1 426 Federal Register / Vol. 76, No. 3 / Wednesday, January 5, 2011 / Rules and Regulations TABLE 1—ALL MATERIAL INCORPORATED BY REFERENCE Document Date Fokker Service Bulletin SBF100–27–091 ................................................................................................................................ Fokker Service Bulletin SBF100–27–092 ................................................................................................................................ Goodrich Service Bulletin 23100–27–29 ................................................................................................................................. (1) The Director of the Federal Register approved the incorporation by reference of Fokker Service Bulletin SBF100–27–092, dated April 27, 2009; and Goodrich Service Bulletin 23100–27–29, dated November 14, 2008; under 5 U.S.C. 552(a) and 1 CFR part 51. (2) The Director of the Federal Register previously approved the incorporation by reference of Fokker Service Bulletin SBF100– 27–091, dated August 31, 2007, on December 26, 2008 (73 FR 70261, November 20, 2008). (3) For Fokker service information identified in this AD, contact Fokker Services B.V., Technical Services Dept., P.O. Box 231, 2150 AE Nieuw-Vennep, the Netherlands; telephone +31 (0)252–627–350; fax +31 (0)252–627–211; e-mail technicalservices.fokkerservices@stork.com; Internet https://www.myfokkerfleet.com. For Goodrich service information identified in this AD, contact Goodrich Corporation, Landing Gear, 1400 South Service Road, West Oakville L6L 5Y7, Ontario, Canada; telephone 905–825–1568; e-mail jean.breed@goodrich.com; Internet https:// www.goodrich.com/TechPubs. (4) You may review copies of the service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227–1221. (5) You may also review copies of the service information that is incorporated by reference 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: https://www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on December 17, 2010. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2010–32990 Filed 1–4–11; 8:45 am] WReier-Aviles on DSKGBLS3C1PROD with RULES BILLING CODE 4910–13–P VerDate Mar<15>2010 15:20 Jan 04, 2011 Jkt 223001 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2010–0855; Directorate Identifier 2010–NM–066–AD; Amendment 39–16566; AD 2011–01–12] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Model 737–300, –400, and –500 Series Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are superseding an existing airworthiness directive (AD) for the products listed above. That AD currently requires repetitive inspections for discrepancies of the fuse pins of the inboard and outboard midspar fittings of the nacelle strut, and corrective actions if necessary. This new AD requires replacing the midspar fuse pins with new, improved fuse pins, which would terminate the repetitive inspections. This AD was prompted by a report of corrosion damage of the chrome runout on the head side found on all four midspar fuse pins of the nacelle strut. Additionally, a large portion of the chrome plate was missing from the corroded area of the shank. We are issuing this AD to prevent damage of the fuse pins of the inboard and outboard midspar fittings of the nacelle strut, which could result in reduced structural integrity of the fuse pins, and consequent loss of the strut and separation of the engine from the airplane. SUMMARY: This AD is effective February 9, 2011. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of February 9, 2011. The Director of the Federal Register approved the incorporation by reference of a certain other publication listed in this AD as of November 13, 2008 (73 FR 59493, October 9, 2008). ADDRESSES: For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, DATES: PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 August 31, 2007. April 27, 2009. November 14, 2008. MC 2H–65, Seattle, Washington 98124– 2207; telephone 206–544–5000, extension 1; fax 206–766–5680; e-mail me.boecom@boeing.com; Internet https://www.myboeingfleet.com. You may review copies of the referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227– 1221. Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (phone: 800–647–5527) is Document Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Alan Pohl, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 917–6450; fax (425) 917–6590; e-mail: alan.pohl@faa.gov. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede airworthiness directive (AD) 2008–21–03, Amendment 39–15687 (73 FR 59493, October 9, 2008). That AD applies to the specified products. The NPRM published in the Federal Register on September 23, 2010 (75 FR 57882). That NPRM proposed to continue to require repetitive inspections for discrepancies of the fuse pins of the inboard and outboard midspar fittings of the nacelle strut, and corrective actions if necessary. That NPRM also proposed to require replacing the midspar fuse pins with new, improved fuse pins, which would terminate the requirement for repetitive detailed inspections. E:\FR\FM\05JAR1.SGM 05JAR1

Agencies

[Federal Register Volume 76, Number 3 (Wednesday, January 5, 2011)]
[Rules and Regulations]
[Pages 423-426]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-32990]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-0701; Directorate Identifier 2010-NM-017-AD; 
Amendment 39-16561; AD 2011-01-08]
RIN 2120-AA64


Airworthiness Directives; Fokker Services B.V. Model F.28 Mark 
0100 Airplanes

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

ACTION: Final rule.

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

SUMMARY: We are superseding an existing airworthiness directive (AD) 
that applies to the products listed above. 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 MCAI describes the unsafe 
condition as:

    Two reports have been received where, during inspection of the 
vertical stabilizer of F28 Mark 0100 aeroplanes, one of the bolts 
that connect the horizontal stabilizer control unit actuator with 
the dog-links was found broken (one on the nut side & one on the 
head side). In both occasions, the bolt shaft was still present in 
the connection and therefore the horizontal stabilizer function was 
not affected. If a single dog-link connection fails, the complete 
stabilizer load is taken up by the remaining dog-link connection. * 
* *
    To address and correct this unsafe condition EASA [European 
Aviation Safety Agency] issued AD 2007-0287 [corresponding FAA AD 
2008-22-14] that required a one-time inspection of the affected 
bolts, * * * and replacement of failed bolts with serviceable parts. 
EASA AD 2007-0287 also required the installation of a tie wrap 
through the lower bolts of the horizontal stabilizer control unit, 
to keep the bolt in place in the event of a bolt head failure.
    Recent examination revealed that the bolts failed due to stress 
corrosion, attributed to excessive bolt torque. Investigation of the 
recently failed bolts showed that the modification as required by AD 
2007-0287 is not adequate.

* * * * *
Loss of horizontal stabilizer function could result in partial loss of 
control of the airplane. We are issuing this AD to require actions to 
correct the unsafe condition on these products.

DATES: This AD becomes effective February 9, 2011.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of February 9, 
2011.

[[Page 424]]

    The Director of the Federal Register approved the incorporation by 
reference of a certain other publication listed in this AD as of 
December 26, 2008 (73 FR 70261, November 20, 2008).

ADDRESSES: You may examine the AD docket on the Internet at https://www.regulations.gov or in person at the U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC.

FOR FURTHER INFORMATION CONTACT: Tom Rodriguez, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
227-1137; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to include an AD that would apply to the specified products. 
That NPRM was published in the Federal Register on July 27, 2010 (75 FR 
43876), and proposed to supersede AD 2008-22-14, Amendment 39-15710 (73 
FR 70261, November 20, 2008). That NPRM proposed to correct an unsafe 
condition for the specified products. The MCAI states:

    Two reports have been received where, during inspection of the 
vertical stabilizer of F28 Mark 0100 aeroplanes, one of the bolts 
that connect the horizontal stabilizer control unit actuator with 
the dog-links was found broken (one on the nut side & one on the 
head side). In both occasions, the bolt shaft was still present in 
the connection and therefore the horizontal stabilizer function was 
not affected. If a single dog-link connection fails, the complete 
stabilizer load is taken up by the remaining dog-link connection. 
Any failed connection should be detected and corrected at the next 
scheduled inspection.
    To address and correct this unsafe condition EASA [European 
Aviation Safety Agency] issued AD 2007-0287 [corresponding FAA AD 
2008-22-14] that required a one-time inspection of the affected 
bolts, Part Number (P/N) 23233-1, and replacement of failed bolts 
with serviceable parts. EASA AD 2007-0287 also required the 
installation of a tie wrap through the lower bolts of the horizontal 
stabilizer control unit, to keep the bolt in place in the event of a 
bolt head failure.
    Recent examination revealed that the bolts failed due to stress 
corrosion, attributed to excessive bolt torque. Investigation of the 
recently failed bolts showed that the modification as required by AD 
2007-0287 is not adequate.
    To address the stress corrosion, the manufacturer of the bolt, 
Goodrich, has introduced a bolt with an improved corrosion 
protection, P/N 23233-3, through Service Bulletin 23100-27-29.
    For the reasons described above, this EASA AD retains the 
requirements of AD 2007-0287, which is superseded, and adds the 
requirement to replace the affected P/N 23233-1 bolts with improved 
bolts. Concurrently, the tie-wrap must be removed.

Loss of horizontal stabilizer function could result in partial loss of 
control of the airplane. You may obtain further information by 
examining the MCAI in the AD docket.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM or on the determination of 
the cost to the public.

Conclusion

    We reviewed the available data and determined that air safety and 
the public interest require adopting the AD as proposed.

Differences Between This AD and the MCAI or Service Information

    We have reviewed the MCAI and related service information and, in 
general, agree with their substance. But we might have found it 
necessary to use different words from those in the MCAI to ensure the 
AD is clear for U.S. operators and is enforceable. In making these 
changes, we do not intend to differ substantively from the information 
provided in the MCAI and related service information.
    We might also have required different actions in this AD from those 
in the MCAI in order to follow our FAA policies. Any such differences 
are highlighted in a Note within the AD.

Costs of Compliance

    We estimate that this AD will affect about 4 products of U.S. 
registry.
    The actions that are required by AD 2008-22-14 and retained in this 
AD take about 3 work-hours per product, at an average labor rate of $85 
per work-hour. Based on these figures, the estimated cost of the 
currently required actions is $255 per product.
    We estimate that it will take about 7 work-hours per product to 
comply with the new basic requirements of this AD. The average labor 
rate is $85 per work-hour. Required parts will cost about $1,550 per 
product. Where the service information lists required parts costs that 
are covered under warranty, we have assumed that there will be no 
charge for these costs. As we do not control warranty coverage for 
affected parties, some parties may incur costs higher than estimated 
here. Based on these figures, we estimate the cost of this AD to the 
U.S. operators to be $8,580, or $2,145 per product.

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.
    For the reasons discussed above, 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 a regulatory evaluation of the estimated costs to 
comply with this AD and placed it in the AD docket.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://www.regulations.gov; or in person at the Docket Operations office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains the NPRM, the regulatory evaluation, 
any comments received, and other information. The street address for 
the Docket Operations office (telephone (800) 647-5527) is in the 
ADDRESSES section. Comments will be available in the AD docket shortly 
after receipt.

[[Page 425]]

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:

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


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by removing Amendment 39-15710 (73 FR 
70261, November 20, 2008) and adding the following new AD:

2011-01-08 Fokker Services B.V.: Amendment 39-16561. Docket No. FAA-
2010-0701; Directorate Identifier 2010-NM-017-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective February 
9, 2011.

Affected ADs

    (b) This AD supersedes AD 2008-22-14, Amendment 39-15710.

Applicability

    (c) This AD applies to Fokker Services B.V. Model F.28 Mark 0100 
airplanes, certificated in any category, all serial numbers.

Subject

    (d) Air Transport Association (ATA) of America Code 27: Flight 
Controls.

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:
    Two reports have been received where, during inspection of the 
vertical stabilizer of F28 Mark 0100 aeroplanes, one of the bolts 
that connect the horizontal stabilizer control unit actuator with 
the dog-links was found broken (one on the nut side & one on the 
head side). In both occasions, the bolt shaft was still present in 
the connection and therefore the horizontal stabilizer function was 
not affected. If a single dog-link connection fails, the complete 
stabilizer load is taken up by the remaining dog-link connection. * 
* *
    To address and correct this unsafe condition EASA [European 
Aviation Safety Agency] issued AD 2007-0287 [corresponding FAA AD 
2008-22-14] that required a one-time inspection of the affected 
bolts, * * * and replacement of failed bolts with serviceable parts. 
EASA AD 2007-0287 also required the installation of a tie wrap 
through the lower bolts of the horizontal stabilizer control unit, 
to keep the bolt in place in the event of a bolt head failure.
    Recent examination revealed that the bolts failed due to stress 
corrosion, attributed to excessive bolt torque. Investigation of the 
recently failed bolts showed that the modification as required by AD 
2007-0287 is not adequate.
* * * * *
Loss of horizontal stabilizer function could result in partial loss 
of control of the airplane.

Compliance

    (f) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

Restatement of Requirements of AD 2008-22-14

Actions and Compliance

    (g) Unless already done, within 6 months after December 26, 2008 
(the effective date of AD 2008-22-14), do the following actions.
    (1) Perform a one-time inspection (integrity check) for failure 
of the lower bolts of the stabilizer control unit dog-links, in 
accordance with the Accomplishment Instructions of Fokker Service 
Bulletin SBF100-27-091, dated August 31, 2007. If a failed bolt is 
found, before further flight, replace the bolt with a serviceable 
bolt in accordance with the Accomplishment Instructions of that 
service bulletin.
    (2) Install a tie-wrap through the lower bolts of the stabilizer 
control unit, in accordance with the Accomplishment Instructions of 
Fokker Service Bulletin SBF100-27-091, dated August 31, 2007.

New Requirements of This AD

Actions

    (h) Within 30 months after the effective date of this AD, do the 
actions specified in paragraphs (h)(1) and (h)(2) of this AD 
concurrently. Accomplishing the actions of both paragraphs (h)(1) 
and (h)(2) of this AD terminates the actions required by paragraph 
(g) of this AD.
    (1) Remove the tie-wrap, P/N MS3367-2-9, from the lower bolts of 
the horizontal stabilizer control unit, in accordance with the 
Accomplishment Instructions of Fokker Service Bulletin SBF100-27-
092, dated April 27, 2009.
    (2) Remove the lower bolts, P/N 23233-1, of the horizontal 
stabilizer control unit and install bolts, P/N 23233-3, in 
accordance with the Accomplishment Instructions of Goodrich Service 
Bulletin 23100-27-29, dated November 14, 2008.
    (i) After accomplishing the requirements of paragraph (h) of 
this AD, do not install a bolt having P/N 23233-1 or a tie-wrap 
having P/N MS3367-2-9.

FAA AD Differences

    Note 1: This AD differs from the MCAI and/or service information 
as follows: No differences.

Other FAA AD Provisions

    (j) The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, Transport Airplane Directorate, 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: Tom 
Rodriguez, Aerospace Engineer, International Branch, ANM-116, 
Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, 
Washington 98057-3356; telephone (425) 227-1137; fax (425) 227-1149. 
Before using any approved AMOC on any airplane to which the AMOC 
applies, notify your principal maintenance inspector (PMI) or 
principal avionics inspector (PAI), as appropriate, or lacking a 
principal inspector, your local Flight Standards District Office. 
The AMOC approval letter must specifically reference this AD.
    (2) Airworthy Product: For any requirement in this AD to obtain 
corrective actions from a manufacturer or other source, use these 
actions if they are FAA-approved. Corrective actions are considered 
FAA-approved if they are approved by the State of Design Authority 
(or their delegated agent). You are required to assure the product 
is airworthy before it is returned to service.
    (3) Reporting Requirements: A federal agency may not conduct or 
sponsor, and a person is not required to respond to, nor shall a 
person be subject to a penalty for failure to comply with a 
collection of information subject to the requirements of the 
Paperwork Reduction Act unless that collection of information 
displays a current valid OMB Control Number. The OMB Control Number 
for this information collection is 2120-0056. Public reporting for 
this collection of information is estimated to be approximately 5 
minutes per response, including the time for reviewing instructions, 
completing and reviewing the collection of information. All 
responses to this collection of information are mandatory. Comments 
concerning the accuracy of this burden and suggestions for reducing 
the burden should be directed to the FAA at: 800 Independence Ave. 
SW., Washington, DC 20591, Attn: Information Collection Clearance 
Officer, AES-200.

Related Information

    (k) Refer to MCAI EASA Airworthiness Directive 2009-0216, dated 
October 7, 2009; Fokker Service Bulletin SBF100-27-091, dated August 
31, 2007; Fokker Service Bulletin SBF100-27-092, dated April 27, 
2009; and Goodrich Service Bulletin 23100-27-29, dated November 14, 
2008; for related information.

Material Incorporated by Reference

    (l) You must use the applicable service information contained in 
Table 1 of this AD to do the actions required by this AD, unless the 
AD specifies otherwise.

[[Page 426]]



             Table 1--All Material Incorporated by Reference
------------------------------------------------------------------------
              Document                               Date
------------------------------------------------------------------------
Fokker Service Bulletin SBF100-27-    August 31, 2007.
 091.
Fokker Service Bulletin SBF100-27-    April 27, 2009.
 092.
Goodrich Service Bulletin 23100-27-   November 14, 2008.
 29.
------------------------------------------------------------------------

     (1) The Director of the Federal Register approved the 
incorporation by reference of Fokker Service Bulletin SBF100-27-092, 
dated April 27, 2009; and Goodrich Service Bulletin 23100-27-29, 
dated November 14, 2008; under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) The Director of the Federal Register previously approved the 
incorporation by reference of Fokker Service Bulletin SBF100-27-091, 
dated August 31, 2007, on December 26, 2008 (73 FR 70261, November 
20, 2008).
    (3) For Fokker service information identified in this AD, 
contact Fokker Services B.V., Technical Services Dept., P.O. Box 
231, 2150 AE Nieuw-Vennep, the Netherlands; telephone +31 (0)252-
627-350; fax +31 (0)252-627-211; e-mail 
technicalservices.fokkerservices@stork.com; Internet https://www.myfokkerfleet.com. For Goodrich service information identified 
in this AD, contact Goodrich Corporation, Landing Gear, 1400 South 
Service Road, West Oakville L6L 5Y7, Ontario, Canada; telephone 905-
825-1568; e-mail jean.breed@goodrich.com; Internet https://www.goodrich.com/TechPubs.
    (4) You may review copies of the service information at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington. For information on the availability of this material at 
the FAA, call 425-227-1221.
    (5) You may also review copies of the service information that 
is incorporated by reference 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: https://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Issued in Renton, Washington, on December 17, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2010-32990 Filed 1-4-11; 8:45 am]
BILLING CODE 4910-13-P
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