Airworthiness Directives; Fokker Services B.V. Model F.28 Mark 0070 and 0100 Airplanes, 63042-63045 [2010-25449]

Download as PDF 63042 Federal Register / Vol. 75, No. 198 / Thursday, October 14, 2010 / Rules and Regulations accordance with the Accomplishment Instructions of Boeing Service Bulletin DC10–28–262, dated January 6, 2010. PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Alternative Methods of Compliance (AMOCs) Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ 2010–21–13 McDonnell Douglas Corporation: Amendment 39–16473; Docket No. FAA–2010–0672; Directorate Identifier 2010–NM–047–AD. Effective Date (a) This AD is effective November 18, 2010. Affected ADs (b) None. Applicability (c) This AD applies to McDonnell Douglas Corporation Model DC–10–10, DC–10–10F, DC–10–30, DC–10–30F (KDC–10), DC–10–40, and DC–10–40F airplanes, certificated in any category, as identified in Boeing Service Bulletin DC10–28–262, Revision 1, dated June 9, 2010. Subject (d) Air Transport Association (ATA) of America Code 28: Fuel. Unsafe Condition (e) This AD results from fuel system reviews conducted by the manufacturer. The Federal Aviation Administration is issuing this AD to prevent lightning-induced transients to the fuel quantity indication system, which could cause voltage levels to go beyond original design levels between fuel tank probes and structure and become a potential ignition source at the fuel tank, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss 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. emcdonald on DSK2BSOYB1PROD with RULES Installation (g) Within 60 months after the effective date of this AD, install a support bracket and coupler on the left and right wing-to-fuselage transition, and metallic overbraid on the left and right leading edge wire assembly, in accordance with the Accomplishment Instructions of Boeing Service Bulletin DC10–28–262, Revision 1, dated June 9, 2010. Installation According to Previous Issue of Service Bulletin (h) Installing a support bracket and coupler on the left and right wing-to-fuselage transition, and metallic overbraid on the left and right leading edge wire assembly, is also acceptable for compliance with the requirements of paragraph (g) of this AD if done before the effective date of this AD in VerDate Mar<15>2010 16:06 Oct 13, 2010 Jkt 223001 (i)(1) The Manager, Los Angeles Aircraft Certification Office, 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: Samuel Lee, Aerospace Engineer, Propulsion Branch, ANM–140L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, California 90712– 4137; telephone (562) 627–5262; fax (562) 627–5210. (2) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. 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. Related Information (j) For more information about this AD, contact Samuel Lee, Aerospace Engineer, Propulsion Branch, ANM–140L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, California 90712–4137; telephone (562) 627– 5262; fax (562) 627–5210; e-mail samuel.lee@faa.gov. Material Incorporated by Reference (k) You must use Boeing Service Bulletin DC10–28–262, Revision 1, dated June 9, 2010, 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 Boeing Service Bulletin DC10–28–262, Revision 1, dated June 9, 2010, under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, 3855 Lakewood Boulevard, MC D800–0019, Long Beach, California 90846– 0001; telephone 206–544–5000, extension 2; fax 206–766–5683; e-mail dse.boecom@boeing.com; Internet https:// www.myboeingfleet.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 an NARA facility, call 202–741– 6030, or go to https://www.archives.gov/ federal_register/code_of_federal_regulations/ ibr_locations.html. PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 Issued in Renton, Washington, on September 30, 2010. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2010–25442 Filed 10–13–10; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2010–0479; Directorate Identifier 2009–NM–220–AD; Amendment 39–16472; AD 2010–21–12] RIN 2120–AA64 Airworthiness Directives; Fokker Services B.V. Model F.28 Mark 0070 and 0100 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for 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: Recently, a brake fire was reported which was caused by a ruptured brake piston. The fire was quickly extinguished but caused damage to the paint and hydraulic/electrical harness and its components. Detailed investigation showed that a hydraulic lock must have been present close to the affected brake creating enough internal pressure to rupture the piston. The most probable scenario for the hydraulic lock is a loosened (not necessarily disconnected) brake QD [quick-disconnect] coupling. Further investigation of the service experience files at Fokker Services showed that more brake fires have occurred on aeroplanes in a pre-mod SBF100–32–127 configuration. * * * * * The unsafe condition is loss of braking capability and possible brake fires, which could reduce the ability of the flightcrew to safely land the airplane. We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective November 18, 2010. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of November 18, 2010. E:\FR\FM\14OCR1.SGM 14OCR1 Federal Register / Vol. 75, No. 198 / Thursday, October 14, 2010 / Rules and Regulations 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: ADDRESSES: Discussion emcdonald on DSK2BSOYB1PROD 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 May 19, 2010 (75 FR 27961). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states: During 1995, several reports were received of brake QD [quick-disconnect] couplings loosened and/or disconnected during operation. In a few cases, residual brake pressure was trapped in the affected brake, causing asymmetric braking and/or resulting in hot brakes. Loosened couplings may cause a hydraulic leak with the risk of a brake fire. Investigation revealed that the installation of the brake QD couplings must be done with care and that the locking teeth on the light alloy sleeve are prone to wear. The Fokker 70/100 Aircraft Maintenance Manual (AMM) has been revised to include additional information to ensure correct removal and installation of the couplings. In 1997, Fokker Services issued SBF100– 32–106, recommending the introduction of QD couplings with corrosion resistant steel (CRES) sleeves that would prevent excessive wear of the locking teeth on the light alloy sleeve. In response to more reported cases of loosened QD couplings resulting in brake problems, further improved QD couplings were introduced in 2001 through SBF100– 32–127. These couplings increase the reliability of the brake system. Recently, a brake fire was reported which was caused by a ruptured brake piston. The fire was quickly extinguished but caused damage to the paint and hydraulic/electrical harness and its components. Detailed investigation showed that a hydraulic lock must have been present close to the affected brake creating enough internal pressure to rupture the piston. The most probable scenario for the hydraulic lock is a loosened (not necessarily disconnected) brake QD coupling. Further investigation of the service experience files at Fokker Services showed that more brake fires have occurred on aeroplanes in a pre-mod SBF100–32–127 configuration. In order to reduce the probability of a fluid fire as described in CS (certification VerDate Mar<15>2010 16:06 Oct 13, 2010 Jkt 223001 specification) 25.863, additional action is deemed necessary. For the reasons described above, this [European Aviation Safety Agency] AD requires repetitive [detailed] inspections [for wear] of the affected brake QD couplings and replacement of the QD couplings with improved units. Installation of the improved QD couplings terminates the repetitive inspections requirements. The unsafe condition is loss of braking capability and possible brake fires, which could reduce the ability of the flightcrew to safely land 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 16 products of U.S. registry. We also estimate that it will take about 4 workhours per product to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour. Required parts will cost about $4,814 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 parts. 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 $82,464, or $5,154 per product. PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 63043 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\14OCR1.SGM 14OCR1 63044 Federal Register / Vol. 75, No. 198 / Thursday, October 14, 2010 / Rules and Regulations Subject (d) Air Transport Association (ATA) of America Code 32: Landing Gear. 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: ■ 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. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new AD: ■ 2010–21–12 Fokker Services B.V.: Amendment 39–16472. Docket No. FAA–2010–0479; Directorate Identifier 2009–NM–220–AD. Effective Date (a) This airworthiness directive (AD) becomes effective November 18, 2010. Affected ADs (b) None. Applicability (c) This AD applies to Fokker Services B.V. Model F.28 Mark 0070 and 0100 airplanes, certificated in any category, all serial numbers, with any brake quick-disconnect (QD) coupling having part number (P/N) AE70690E, AE70691E, AE99111E, or AE99119E installed. Reason (e) The mandatory continuing airworthiness information (MCAI) states: During 1995, several reports were received of brake QD couplings loosened and/or disconnected during operation. In a few cases, residual brake pressure was trapped in the affected brake, causing asymmetric braking and/or resulting in hot brakes. Loosened couplings may cause a hydraulic leak with the risk of a brake fire. Investigation revealed that the installation of the brake QD couplings must be done with care and that the locking teeth on the light alloy sleeve are prone to wear. The Fokker 70/100 Aircraft Maintenance Manual (AMM) has been revised to include additional information to ensure correct removal and installation of the couplings. In 1997, Fokker Services issued SBF100– 32–106, recommending the introduction of QD couplings with corrosion resistant steel (CRES) sleeves that would prevent excessive wear of the locking teeth on the light alloy sleeve. In response to more reported cases of loosened QD couplings resulting in brake problems, further improved QD couplings were introduced in 2001 through SBF100– 32–127. These couplings increase the reliability of the brake system. Recently, a brake fire was reported which was caused by a ruptured brake piston. The fire was quickly extinguished but caused damage to the paint and hydraulic/electrical harness and its components. Detailed investigation showed that a hydraulic lock must have been present close to the affected brake creating enough internal pressure to rupture the piston. The most probable scenario for the hydraulic lock is a loosened (not necessarily disconnected) brake QD coupling. Further investigation of the service experience files at Fokker Services showed that more brake fires have occurred on aeroplanes in a pre-mod SBF100–32–127 configuration. In order to reduce the probability of a fluid fire as described in CS (certification specification) 25.863, additional action is deemed necessary. For the reasons described above, this [European Aviation Safety Agency] AD requires repetitive [detailed] inspections [for wear] of the affected brake QD couplings and replacement of the QD couplings with improved units. Installation of the improved QD couplings terminates the repetitive inspections requirements. The unsafe condition is loss of braking capability and possible brake fires, which could reduce the ability of the flightcrew to safely land 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. Actions (g) Do the following actions. (1) Within 6 months after the effective date of this AD, do a detailed inspection for wear of the brake QD couplings by measuring dimension ‘‘A,’’ in accordance with Part 1 of the Accomplishment Instructions of Fokker Service Bulletin SBF100–32–156, Revision 1, dated June 29, 2009. Repeat the inspection thereafter at the applicable intervals specified in Table 1 of this AD, except as required by paragraph (g)(2) of this AD. TABLE 1—REPETITIVE INSPECTION INTERVALS Repeat the inspection at intervals not to exceed— Greater than or equal to 0.76 mm .................................................................................................................................................... Less than 0.76 mm but greater than or equal to 0.72 mm .............................................................................................................. Less than 0.72 mm but greater than or equal to 0.68 mm .............................................................................................................. Less than 0.68 mm but greater than or equal to 0.61 mm .............................................................................................................. Less than 0.61 mm but greater than 0.53 mm ................................................................................................................................ emcdonald on DSK2BSOYB1PROD with RULES If dimension ‘‘A’’ is— 6 months. 3 months. 30 days. 7 days. 24 hours. (2) If, during any inspection required by paragraph (g)(1) of this AD, dimension ‘‘A’’ on any brake QD coupling is less than or equal to 0.53 mm, before further flight, replace the affected brake QD coupling with an improved unit having P/N AE73059E or P/N AE73091E, as applicable, in accordance with Part 2 of the Accomplishment Instructions of Fokker Service Bulletin SBF100–32–156, Revision 1, dated June 29, 2009. VerDate Mar<15>2010 16:06 Oct 13, 2010 Jkt 223001 (3) Within 24 months after the effective date of this AD, replace all remaining brake QD couplings having P/N AE70690E, P/N AE70691E, P/N AE99111E, and P/N AE99119E with improved units, in accordance with Part 2 of the Accomplishment Instructions of Fokker Service Bulletin SBF100–32–156, Revision 1, dated June 29, 2009. (4) Installation of brake QD couplings with an improved unit having P/N AE73059E or PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 P/N AE73091E at all locations terminates the repetitive inspections required by paragraph (g)(1) of this AD. (5) Replacing the brake QD couplings is also acceptable for compliance with the corresponding requirements of paragraphs (g)(1), (g)(2), and (g)(3) of this AD if done before the effective date of this AD, in accordance with any of the service bulletins specified in Table 2 of this AD: E:\FR\FM\14OCR1.SGM 14OCR1 Federal Register / Vol. 75, No. 198 / Thursday, October 14, 2010 / Rules and Regulations 63045 TABLE 2—FOKKER CREDIT SERVICE BULLETINS Fokker Service Bulletins Revision Fokker Performa Service Bulletin SBF100–32–127, including Appendix XIV, dated February 1, 2006. Fokker Performa Service Bulletin SBF100–32–127, including Appendix XIV, dated February 1, 2006. Fokker Service Bulletin SBF100–32–156 ........................................................................................... Original ......................... July 20, 2001. 1 .................................... March 6, 2009. Original ......................... March 6, 2009. FAA AD Differences Note 1: This AD differs from the MCAI and/or service information as follows: No differences. Other FAA AD Provisions (h) 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: For any reporting requirement in this AD, under the provisions of the Paperwork Reduction Act (44 U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120–0056. emcdonald on DSK2BSOYB1PROD with RULES Related Information (i) Refer to MCAI European Aviation Safety Agency Airworthiness Directive 2009–0176, dated August 6, 2009; and Fokker Service Bulletin SBF100–32–156, Revision 1, dated June 29, 2009; for related information. Material Incorporated by Reference (j) You must use Fokker Service Bulletin SBF100–32–156, Revision 1, dated June 29, 2009, 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 Fokker Services B.V., VerDate Mar<15>2010 16:06 Oct 13, 2010 Jkt 223001 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.myfokkerfleetcom. (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. Date * * * [F]uel leaks and failed fasteners [have been reported] in the region of the rear spar root joint attachment fitting at wing rib 2. * * * [Docket No. FAA–2010–0642; Directorate Identifier 2007–NM–332–AD; Amendment 39–16470; AD 2010–21–10] * * * * * The unsafe condition is stress corrosion failures in the region of the rear spar root joint attachment fitting at wing rib 2, which could lead to reduced structural integrity of the wing, and consequent reduced controllability of the airplane. We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective November 18, 2010. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of November 18, 2010. 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: Todd Thompson, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1175; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: RIN 2120–AA64 Discussion Airworthiness Directives; BAE SYSTEMS (OPERATIONS) LIMITED Model BAe 146 and Avro 146–RJ Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. 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 1, 2010 (75 FR 38058). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states: We are adopting a new airworthiness directive (AD) for 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: British Aerospace originally issued Service Bulletin (SB) 57–033 in 1989 to detect fuel leaks and failed fasteners in the region of the rear spar root joint attachment fitting at wing rib 2. Accomplishment of this SB was mandated by the [Civil Aviation Authority] CAA United Kingdom AD 044–09–89. Revisions 1 through 7 of this SB were introduced to inspect pre mod HCM01447A standard installations for fuel leaks and loose or broken bolts. Modification HCM01447A Issued in Renton, Washington, on September 29, 2010. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2010–25449 Filed 10–13–10; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 AGENCY: SUMMARY: PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 E:\FR\FM\14OCR1.SGM 14OCR1

Agencies

[Federal Register Volume 75, Number 198 (Thursday, October 14, 2010)]
[Rules and Regulations]
[Pages 63042-63045]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-25449]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-0479; Directorate Identifier 2009-NM-220-AD; 
Amendment 39-16472; AD 2010-21-12]
RIN 2120-AA64


Airworthiness Directives; Fokker Services B.V. Model F.28 Mark 
0070 and 0100 Airplanes

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

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for 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:
* * * * *
    Recently, a brake fire was reported which was caused by a 
ruptured brake piston. The fire was quickly extinguished but caused 
damage to the paint and hydraulic/electrical harness and its 
components. Detailed investigation showed that a hydraulic lock must 
have been present close to the affected brake creating enough 
internal pressure to rupture the piston. The most probable scenario 
for the hydraulic lock is a loosened (not necessarily disconnected) 
brake QD [quick-disconnect] coupling. Further investigation of the 
service experience files at Fokker Services showed that more brake 
fires have occurred on aeroplanes in a pre-mod SBF100-32-127 
configuration.
* * * * *
The unsafe condition is loss of braking capability and possible brake 
fires, which could reduce the ability of the flightcrew to safely land 
the airplane. We are issuing this AD to require actions to correct the 
unsafe condition on these products.

DATES: This AD becomes effective November 18, 2010.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of November 18, 
2010.

[[Page 63043]]


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 May 19, 2010 (75 FR 
27961). That NPRM proposed to correct an unsafe condition for the 
specified products. The MCAI states:

    During 1995, several reports were received of brake QD [quick-
disconnect] couplings loosened and/or disconnected during operation. 
In a few cases, residual brake pressure was trapped in the affected 
brake, causing asymmetric braking and/or resulting in hot brakes. 
Loosened couplings may cause a hydraulic leak with the risk of a 
brake fire. Investigation revealed that the installation of the 
brake QD couplings must be done with care and that the locking teeth 
on the light alloy sleeve are prone to wear. The Fokker 70/100 
Aircraft Maintenance Manual (AMM) has been revised to include 
additional information to ensure correct removal and installation of 
the couplings.
    In 1997, Fokker Services issued SBF100-32-106, recommending the 
introduction of QD couplings with corrosion resistant steel (CRES) 
sleeves that would prevent excessive wear of the locking teeth on 
the light alloy sleeve. In response to more reported cases of 
loosened QD couplings resulting in brake problems, further improved 
QD couplings were introduced in 2001 through SBF100-32-127. These 
couplings increase the reliability of the brake system.
    Recently, a brake fire was reported which was caused by a 
ruptured brake piston. The fire was quickly extinguished but caused 
damage to the paint and hydraulic/electrical harness and its 
components. Detailed investigation showed that a hydraulic lock must 
have been present close to the affected brake creating enough 
internal pressure to rupture the piston. The most probable scenario 
for the hydraulic lock is a loosened (not necessarily disconnected) 
brake QD coupling. Further investigation of the service experience 
files at Fokker Services showed that more brake fires have occurred 
on aeroplanes in a pre-mod SBF100-32-127 configuration.
    In order to reduce the probability of a fluid fire as described 
in CS (certification specification) 25.863, additional action is 
deemed necessary.
    For the reasons described above, this [European Aviation Safety 
Agency] AD requires repetitive [detailed] inspections [for wear] of 
the affected brake QD couplings and replacement of the QD couplings 
with improved units. Installation of the improved QD couplings 
terminates the repetitive inspections requirements.

The unsafe condition is loss of braking capability and possible brake 
fires, which could reduce the ability of the flightcrew to safely land 
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 16 products of U.S. registry. 
We also estimate that it will take about 4 work-hours per product to 
comply with the basic requirements of this AD. The average labor rate 
is $85 per work-hour. Required parts will cost about $4,814 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 parts. 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 $82,464, or $5,154 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 63044]]

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 adding the following new AD:

2010-21-12 Fokker Services B.V.: Amendment 39-16472. Docket No. FAA-
2010-0479; Directorate Identifier 2009-NM-220-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective November 
18, 2010.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Fokker Services B.V. Model F.28 Mark 0070 
and 0100 airplanes, certificated in any category, all serial 
numbers, with any brake quick-disconnect (QD) coupling having part 
number (P/N) AE70690E, AE70691E, AE99111E, or AE99119E installed.

Subject

    (d) Air Transport Association (ATA) of America Code 32: Landing 
Gear.

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:

    During 1995, several reports were received of brake QD couplings 
loosened and/or disconnected during operation. In a few cases, 
residual brake pressure was trapped in the affected brake, causing 
asymmetric braking and/or resulting in hot brakes. Loosened 
couplings may cause a hydraulic leak with the risk of a brake fire. 
Investigation revealed that the installation of the brake QD 
couplings must be done with care and that the locking teeth on the 
light alloy sleeve are prone to wear. The Fokker 70/100 Aircraft 
Maintenance Manual (AMM) has been revised to include additional 
information to ensure correct removal and installation of the 
couplings.
    In 1997, Fokker Services issued SBF100-32-106, recommending the 
introduction of QD couplings with corrosion resistant steel (CRES) 
sleeves that would prevent excessive wear of the locking teeth on 
the light alloy sleeve. In response to more reported cases of 
loosened QD couplings resulting in brake problems, further improved 
QD couplings were introduced in 2001 through SBF100-32-127. These 
couplings increase the reliability of the brake system.
    Recently, a brake fire was reported which was caused by a 
ruptured brake piston. The fire was quickly extinguished but caused 
damage to the paint and hydraulic/electrical harness and its 
components. Detailed investigation showed that a hydraulic lock must 
have been present close to the affected brake creating enough 
internal pressure to rupture the piston. The most probable scenario 
for the hydraulic lock is a loosened (not necessarily disconnected) 
brake QD coupling. Further investigation of the service experience 
files at Fokker Services showed that more brake fires have occurred 
on aeroplanes in a pre-mod SBF100-32-127 configuration.
    In order to reduce the probability of a fluid fire as described 
in CS (certification specification) 25.863, additional action is 
deemed necessary.
    For the reasons described above, this [European Aviation Safety 
Agency] AD requires repetitive [detailed] inspections [for wear] of 
the affected brake QD couplings and replacement of the QD couplings 
with improved units. Installation of the improved QD couplings 
terminates the repetitive inspections requirements.

The unsafe condition is loss of braking capability and possible 
brake fires, which could reduce the ability of the flightcrew to 
safely land 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.

Actions

    (g) Do the following actions.
    (1) Within 6 months after the effective date of this AD, do a 
detailed inspection for wear of the brake QD couplings by measuring 
dimension ``A,'' in accordance with Part 1 of the Accomplishment 
Instructions of Fokker Service Bulletin SBF100-32-156, Revision 1, 
dated June 29, 2009. Repeat the inspection thereafter at the 
applicable intervals specified in Table 1 of this AD, except as 
required by paragraph (g)(2) of this AD.

                Table 1--Repetitive Inspection Intervals
------------------------------------------------------------------------
                                               Repeat the  inspection at
           If dimension ``A'' is--              intervals not to exceed--
 
------------------------------------------------------------------------
Greater than or equal to 0.76 mm.............  6 months.
Less than 0.76 mm but greater than or equal    3 months.
 to 0.72 mm.
Less than 0.72 mm but greater than or equal    30 days.
 to 0.68 mm.
Less than 0.68 mm but greater than or equal    7 days.
 to 0.61 mm.
Less than 0.61 mm but greater than 0.53 mm...  24 hours.
------------------------------------------------------------------------

     (2) If, during any inspection required by paragraph (g)(1) of 
this AD, dimension ``A'' on any brake QD coupling is less than or 
equal to 0.53 mm, before further flight, replace the affected brake 
QD coupling with an improved unit having P/N AE73059E or P/N 
AE73091E, as applicable, in accordance with Part 2 of the 
Accomplishment Instructions of Fokker Service Bulletin SBF100-32-
156, Revision 1, dated June 29, 2009.
    (3) Within 24 months after the effective date of this AD, 
replace all remaining brake QD couplings having P/N AE70690E, P/N 
AE70691E, P/N AE99111E, and P/N AE99119E with improved units, in 
accordance with Part 2 of the Accomplishment Instructions of Fokker 
Service Bulletin SBF100-32-156, Revision 1, dated June 29, 2009.
    (4) Installation of brake QD couplings with an improved unit 
having P/N AE73059E or P/N AE73091E at all locations terminates the 
repetitive inspections required by paragraph (g)(1) of this AD.
    (5) Replacing the brake QD couplings is also acceptable for 
compliance with the corresponding requirements of paragraphs (g)(1), 
(g)(2), and (g)(3) of this AD if done before the effective date of 
this AD, in accordance with any of the service bulletins specified 
in Table 2 of this AD:

[[Page 63045]]



                Table 2--Fokker Credit Service Bulletins
------------------------------------------------------------------------
   Fokker Service Bulletins         Revision               Date
------------------------------------------------------------------------
Fokker Performa Service         Original........  July 20, 2001.
 Bulletin SBF100-32-127,
 including Appendix XIV, dated
 February 1, 2006.
Fokker Performa Service         1...............  March 6, 2009.
 Bulletin SBF100-32-127,
 including Appendix XIV, dated
 February 1, 2006.
Fokker Service Bulletin SBF100- Original........  March 6, 2009.
 32-156.
------------------------------------------------------------------------

FAA AD Differences

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

Other FAA AD Provisions

    (h) 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: For any reporting requirement in 
this AD, under the provisions of the Paperwork Reduction Act (44 
U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has 
approved the information collection requirements and has assigned 
OMB Control Number 2120-0056.

Related Information

    (i) Refer to MCAI European Aviation Safety Agency Airworthiness 
Directive 2009-0176, dated August 6, 2009; and Fokker Service 
Bulletin SBF100-32-156, Revision 1, dated June 29, 2009; for related 
information.

Material Incorporated by Reference

    (j) You must use Fokker Service Bulletin SBF100-32-156, Revision 
1, dated June 29, 2009, 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 
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.myfokkerfleetcom.
    (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 September 29, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2010-25449 Filed 10-13-10; 8:45 am]
BILLING CODE 4910-13-P
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