Airworthiness Directives; Fokker Services B.V. Airplanes, 51172-51175 [2017-22558]

Download as PDF 51172 Federal Register / Vol. 82, No. 212 / Friday, November 3, 2017 / Proposed Rules 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. This AD is issued in accordance with authority delegated by the Executive Director, Aircraft Certification Service, as authorized by FAA Order 8000.51C. In accordance with that order, issuance of ADs is normally a function of the Compliance and Airworthiness Division, but during this transition period, the Executive Director has delegated the authority to issue ADs applicable to engines, propellers, and associated appliances to the Manager, Engine and Propeller Standards Branch, Policy and Innovation Division. Regulatory Findings We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 proposed regulation: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation in Alaska, and (4) 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. Safran Helicopter Engines, S.A. (Type Certificate previously held by Turbomeca, S.A): Docket No. FAA– 2017–0838; Product Identifier 2017–NE– 33–AD. (a) Comments Due Date We must receive comments by December 18, 2017. (b) Affected ADs None. (c) Applicability This AD applies to all Safran Helicopter Engines S.A. Arriel 2E turboshaft engines with front support, part number 0 292 11 715 0, installed (pre-mod TU 197 configuration). (d) Subject Joint Aircraft System Component (JASC) Code 8300, Accessory Gearboxes. (e) Reason This AD was prompted by reports of ruptured front support pins on the accessory gearbox front support. We are issuing this AD to prevent failure of a front support, loss of engine thrust control and reduced control of the helicopter. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Required Actions Before the accessory gearbox and transmission shaft module (Module 01) accumulates 1,600 engine operating hours since new, or within 80 engine operating hours after the effective date of this AD, whichever occurs later, replace the front support with a part eligible for installation. (h) Definition For the purpose of this AD, a part eligible for installation is a Module 01 with a premod TU 197 front support, that has not accumulated more than 1,680 engine operating hours since new; or a Module 01 with a post-mod TU 197 front support. (i) Installation Prohibition As of the effective date of this AD, you may not install a pre-mod TU 197 front support on any engine with a post-mod TU 197 front support installed. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: jstallworth on DSKBBY8HB2PROD with PROPOSALS List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. (j) Alternative Methods of Compliance (AMOCs) (1) The Manager, FAA, ECO Branch, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the ECO Branch, send it to the attention of the person identified in paragraph (k)(1) of this AD. You may email your request to: ANE-AD-AMOC@faa.gov. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. 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 airworthiness directive (AD): ■ VerDate Sep<11>2014 15:06 Nov 02, 2017 Jkt 244001 PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 (k) Related Information (1) For more information about this AD, contact Robert Green, Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781–238– 7754; fax: 781–238–7199; email: robert.green@faa.gov. (2) Refer to MCAI EASA AD 2016–0235, dated November 24, 2016, for more information. You may examine the MCAI in the AD docket on the Internet at http:// www.regulations.gov by searching for and locating it in Docket No. FAA–2017–0838. Issued in Burlington, Massachusetts, on October 24, 2017. Robert J. Ganley, Manager, Engine and Propeller Standards Branch, Aircraft Certification Service. [FR Doc. 2017–23606 Filed 11–2–17; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2017–0906; Product Identifier 2017–NM–039–AD] RIN 2120–AA64 Airworthiness Directives; Fokker Services B.V. Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to supersede Airworthiness Directive (AD) 2005–12– 16, for all Fokker Services B.V. Model F28 Mark 0100 airplanes. AD 2005–12– 16 requires an inspection to determine the part number of the passenger service unit (PSU) panels for the PSU modification status, and corrective actions if applicable. Since we issued AD 2005–12–16, we have determined that the required modification actions might not have been implemented correctly. This proposed AD would require an inspection of the PSU panels and the PSU panel/airplane interface connectors for discrepancies, and corrective actions if necessary. This proposed AD would also remove airplanes from the applicability. We are proposing this AD to address the unsafe condition on these products. DATES: We must receive comments on this proposed AD by December 18, 2017. SUMMARY: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: ADDRESSES: E:\FR\FM\03NOP1.SGM 03NOP1 Federal Register / Vol. 82, No. 212 / Friday, November 3, 2017 / Proposed Rules • Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this NPRM, contact Fokker Services B.V., Technical Services Dept., P.O. Box 1357, 2130 EL Hoofddorp, the Netherlands; telephone +31 (0)88–6280– 350; fax +31 (0)88–6280–111; email technicalservices@fokker.com; Internet http://www.myfokkerfleet.com. You may view this referenced service information at the FAA, Transport Standards Branch, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425– 227–1221. jstallworth on DSKBBY8HB2PROD with PROPOSALS Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2017– 0906; 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 proposed AD, 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. FOR FURTHER INFORMATION CONTACT: Tom Rodriguez, Aerospace Engineer, International Section, Transport Standards Branch, 1601 Lind Avenue SW., Renton, WA 98055–4056; telephone 425–227–1137; fax 425–227– 1149. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA– 2017–0906; Product Identifier 2017– NM–039–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments. VerDate Sep<11>2014 15:06 Nov 02, 2017 Jkt 244001 We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion We issued AD 2005–12–16, Amendment 39–14132 (70 FR 34642, June 15, 2005) (‘‘AD 2005–12–16’’), for all Fokker Services B.V. Model F28 Mark 0100 airplanes. AD 2005–12–16 was prompted by reports of smoke in the passenger compartment during flight. One of those incidents also included a burning smell and consequently led to emergency evacuation of the airplane. AD 2005– 12–16 requires an inspection to determine the part number of the PSU panels for the PSU modification status, and corrective actions if applicable. We issued AD 2005–12–16 to detect and correct overheating of the PSU panel due to moisture ingress, which could result in smoke or fire in the passenger cabin. Since we issued AD 2005–12–16, we have determined that the modification actions required by AD 2005–12–16 might not have been implemented correctly. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2017–0043, dated March 15, 2017 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Fokker Services B.V. Model F28 Mark 0100 airplanes. The MCAI states: Reports were received of burning smell and smoke in the passenger compartment during flight as a result of overheating of passenger service units (PSU). These were attributed to moisture ingress into the interface electrical connectors of an unsealed PSU panel. This condition, if not detected and corrected, could lead to further incidents of smoke in the passenger compartment, possibly resulting in injury to occupants. To address this potential unsafe condition, Grimes Aerospace Company, the PSU manufacturer (currently Honeywell) issued SB 10–1178–33–0040 and SB 10–1571–33– 0041, and Fokker Services issued SBF100– 25–097, to provide instructions for installation of improved sealing of the PSU and its interface electrical connectors. Subsequently, CAA–NL [Civil Aviation Authority—The Netherlands] issued AD (BLA) 2004–022 [which corresponds to FAA AD 2005–12–16] to require modification, cleaning and sealing of the affected PSU. Since that [CAA–NL] AD was issued, following a new occurrence of burning smell and smoke in the passenger compartment PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 51173 during disembarking of the passengers, the investigation revealed that, on several aeroplanes, the modification instructions of Honeywell and Fokker Services (SB listed above) were not, or not correctly, implemented. Prompted by these findings, Fokker Services published SBF100–25–128, providing inspection instructions to detect non-accomplishment and any discrepancy with the original modification instructions. For the reasons described above, this [EASA] AD retains the requirement of CAA– NL AD (BLA) 2004–022, which is superseded, and requires a one-time inspection [for discrepancies] of the PSU panels and their interface with the aeroplane, and, depending on findings, the accomplishment of applicable corrective action(s). Discrepancies include incorrect application of the sealant on the PSU panels, uninstalled gaskets, inability to properly lock the connectors, and incorrectly applied sealant on the connectors. Corrective actions include restoring the sealing of the affected PSU panel, repairing the PSU panel, or installing a new PSU panel with a replaced receptacle, and installing gaskets; making sure the connecter can properly lock; and applying sealant on the connector. The MCAI also revised the applicability by specifying specific line numbers and excluding airplanes on which certain modifications were done. You may examine the MCAI in the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2017– 0906. Related Service Information Under 1 CFR Part 51 Fokker Services B.V. has issued Fokker Service Bulletin SBF100–25– 128, dated July 21, 2016. This service information describes procedures for inspection of the PSU panels and the PSU panel/airplane interface connectors for discrepancies, and for incorrectly applied sealant on the connectors, and corrective actions. Grimes Aerospace has issued Service Bulletin 10–1178–33–0040, dated October 15, 1993; Service Bulletin 10– 1178–33–0040, Revision 1, dated March 25, 1996; and Service Bulletin 10–1571– 33–0041, dated October 15, 1993. This service information describes procedures for inspection of the PSU panels and the PSU panel/airplane interface connectors for discrepancies, and corrective actions. This service information is distinct since it applies to different part numbers. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. E:\FR\FM\03NOP1.SGM 03NOP1 51174 Federal Register / Vol. 82, No. 212 / Friday, November 3, 2017 / Proposed Rules FAA’s Determination and Requirements of This Proposed AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of the same type design. Costs of Compliance We estimate that this proposed AD affects 8 airplanes of U.S. registry. The actions required by AD 2005–12– 16, and retained in this proposed AD take about 5 work-hours per product, at an average labor rate of $85 per workhour. Required parts cost about $6 per product. Based on these figures, the estimated cost of the actions that are required by AD 2005–12–16 is $431 per product. We also estimate that it would take about 13 work-hours per product to comply with the basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this proposed AD on U.S. operators to be $8,840, or $1,105 per product. We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in this proposed AD. jstallworth on DSKBBY8HB2PROD with PROPOSALS 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. This AD is issued in accordance with authority delegated by the Executive VerDate Sep<11>2014 15:06 Nov 02, 2017 Jkt 244001 Director, Aircraft Certification Service, as authorized by FAA Order 8000.51C. In accordance with that order, issuance of ADs is normally a function of the Compliance and Airworthiness Division, but during this transition period, the Executive Director has delegated the authority to issue ADs applicable to transport category airplanes to the Director of the System Oversight Division. Regulatory Findings We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 proposed regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska; and 4. 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. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 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 removing Airworthiness Directive (AD) 2005–12–16, Amendment 39–14132 (70 FR 34642, June 15, 2005), and adding the following new AD: ■ Fokker Services B.V.: Docket No. FAA– 2017–0906; Product Identifier 2017– NM–039–AD. (a) Comments Due Date We must receive comments by December 18, 2017. PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 (b) Affected ADs This AD replaces 2005–12–16, Amendment 39–14132 (70 FR 34642, June 15, 2005) (‘‘AD 2005–12–16’’). (c) Applicability This AD applies to Fokker Services B.V. Model F28 Mark 0100 airplanes, certificated in any category, serial numbers 11244 through 11527 inclusive, except those airplanes modified in service as specified in Fokker Service Bulletin SBF100–25–070, or Fokker Service Bulletin SBF100–25–109, or Fokker Modification Report FS–N545 or FS– N571. (d) Subject Air Transport Association (ATA) of America Code 25, Equipment/furnishings. (e) Reason This AD was prompted by reports of smoke in the passenger compartment during ground operations and in-flight. We are issuing this AD to detect and correct overheating of the passenger service unit (PSU) panel due to moisture ingress, which could result in smoke or fire in the passenger cabin. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Inspection and Corrective Actions, With No Changes This paragraph restates the requirements of paragraph (f) of AD 2005–12–16, with no changes. Within 36 months after July 20, 2005 (the effective date of AD 2005–12–16), inspect to determine if Grimes Aerospace PSU panels having part number (P/N) 10– 1178–( ) or P/N 10–1571–( ) are installed and the PSU modification status if applicable, and do any corrective actions if applicable, by doing all of the actions specified in the Accomplishment Instructions of Fokker Service Bulletin SBF100–25–097, dated December 30, 2003. Note 1 to paragraph (g) of this AD: Fokker Service Bulletin SBF100–25–097, dated December 30, 2003, refers to Grimes Aerospace Service Bulletin 10–1178–33– 0040, Revision 1, dated March 25, 1996 (for PSU panels having P/N 10–1178–( )); and Service Bulletin 10–1571–33–0041, dated October 15, 1993 (for PSU panels having P/ N 10–1571–( )), as additional guidance for modifying the PSU panel. (h) Retained Parts Installation Limitation, With No Changes This paragraph restates the requirements of paragraph (g) of AD 2005–12–16, with no changes. As of July 20, 2005 (the effective date of AD 2005–12–16), no person may install a PSU panel having P/N 10–1178–( ) or P/N 10–1571–( ) on any airplane, unless it has been inspected and any applicable corrective actions have been done in accordance with paragraph (g) of this AD. (i) New Affected PSU Identification For the purpose of this AD, Grimes (Honeywell) PSUs having P/N 10–1178– (series) with a serial number below 4000, and E:\FR\FM\03NOP1.SGM 03NOP1 Federal Register / Vol. 82, No. 212 / Friday, November 3, 2017 / Proposed Rules PSUs having P/N 10–1571–(series) with a serial number below 1000, are referred to as affected PSUs in paragraphs (j) through (l) of this AD. (j) New Inspections Within 24 months after the effective date of this AD: Do the actions required by paragraphs (j)(1) and (j)(2) of this AD. (1) Do a general visual inspection of the panel of each affected PSU for incorrect application of the sealant, in accordance with the Accomplishment Instructions of Fokker Service Bulletin SBF100–25–097, dated December 30, 2003; and, as applicable, Grimes Aerospace Service Bulletin 10–1178– 33–0040, dated October 15, 1993 (for PSUs having P/N 10–1178–(series)); Revision 1, dated March 25, 1996 (for PSUs having P/N 10–1178–(series)); and Grimes Aerospace Service Bulletin 10–1571–33–0041, dated October 15, 1993 (for PSUs having P/N 10– 1571–(series)). (2) Do a general visual inspection of the electrical connectors of each affected PSU panel for discrepancies; i.e., uninstalled gaskets, inability to properly lock the connectors, and incorrectly applied sealant on the connectors; in accordance with the Accomplishment Instructions of Fokker Service Bulletin SBF100–25–128, dated July 21, 2016. (k) Corrective Actions If, during any inspection required by paragraph (j) of this AD, any discrepancy is found, before further flight, restore the sealing of the affected PSU panels and accomplish all applicable corrective actions to correct the PSU panel interface, in accordance with the Accomplishment Instructions of Fokker Service Bulletin SBF100–25–128, dated July 21, 2016. Do all applicable corrective actions before further flight. of the local flight standards district office/ certificate holding district office. (ii) AMOCs approved previously for AD 2005–12–16 are approved as AMOCs for the corresponding provisions of this AD. (2) Contacting the Manufacturer: As of the effective date of this AD, for any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or the European Aviation Safety Agency (EASA); or Fokker Services B.V.’s Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. (n) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2017–0043, dated March 6, 2017, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA– 2017–0906. (2) For more information about this AD, contact Tom Rodriguez, Aerospace Engineer, International Section, Transport Standards Branch, 1601 Lind Avenue SW., Renton, WA 98055–4056; telephone 425–227–1137; fax 425–227–1149. (3) For service information identified in this AD, contact Fokker Services B.V., Technical Services Dept., P.O. Box 1357, 2130 EL Hoofddorp, the Netherlands; telephone +31 (0)88–6280–350; fax +31 (0)88–6280–111; email technicalservices@ fokker.com; Internet http:// www.myfokkerfleet.com. You may view this service information at the FAA, Transport Standards Branch, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. jstallworth on DSKBBY8HB2PROD with PROPOSALS (l) Parts Installation Limitation As of the effective date of this AD, an affected PSU panel may be installed on any airplane, provided that, before further flight after installation, it has been inspected in accordance with paragraph (j) of this AD and all applicable corrective actions have been done in accordance with paragraph (k) of this AD. Issued in Renton, Washington, on October 11, 2017. Dionne Palermo, Acting Director, System Oversight Division, Aircraft Certification Service. (m) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Section, Transport Standards Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Section, send it to the attention of the person identified in paragraph (n)(2) of this AD. Information may be emailed to: 9-ANM-116-AMOCREQUESTS@faa.gov. (i) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager DEPARTMENT OF TRANSPORTATION VerDate Sep<11>2014 15:06 Nov 02, 2017 Jkt 244001 [FR Doc. 2017–22558 Filed 11–2–17; 8:45 am] BILLING CODE 4910–13–P Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2017–1011; Product Identifier 2017–SW–004–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Helicopters Deutschland GmbH (Type Certificate Previously Held by Eurocopter Deutschland GmbH) Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 51175 We propose to supersede Airworthiness Directive (AD) 2013–16– 14 for Eurocopter Deutschland GmbH (now Airbus Helicopters Deutschland GmbH) Model EC 135 P1, P2, P2+, T1, T2, and T2+ helicopters. AD 2013–16– 14 currently requires installing a washer in and modifying the main transmission filter housing upper part. Since we issued AD 2013–16–14, Airbus Helicopters Deutschland GmbH has extended the overhaul interval for the main transmission and determined that other models may have the same unsafe condition. This proposed AD would retain the requirements of AD 2013–16– 14, add models to the applicability, and revise the required compliance time for the modification. The actions of this proposed AD are intended to correct an unsafe condition on these products. DATES: We must receive comments on this proposed AD by January 2, 2018. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Docket: Go to http://www.regulations.gov. Follow the online instructions for sending your comments electronically. • Fax: 202–493–2251. • Mail: Send comments to the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590–0001. • Hand Delivery: Deliver to the ‘‘Mail’’ address between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. SUMMARY: Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2017– 1011; 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 this proposed AD, the European Aviation Safety Agency (EASA) AD, the economic 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. For service information identified in this proposed rule, contact Airbus Helicopters, 2701 N. Forum Drive, Grand Prairie, TX 75052; telephone (972) 641–0000 or (800) 232–0323; fax (972) 641–3775; or at http:// www.airbushelicopters.com/website/ technical-expert/. You may review service information at the FAA, Office of the Regional E:\FR\FM\03NOP1.SGM 03NOP1

Agencies

[Federal Register Volume 82, Number 212 (Friday, November 3, 2017)]
[Proposed Rules]
[Pages 51172-51175]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-22558]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0906; Product Identifier 2017-NM-039-AD]
RIN 2120-AA64


Airworthiness Directives; Fokker Services B.V. Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to supersede Airworthiness Directive (AD) 2005-12-
16, for all Fokker Services B.V. Model F28 Mark 0100 airplanes. AD 
2005-12-16 requires an inspection to determine the part number of the 
passenger service unit (PSU) panels for the PSU modification status, 
and corrective actions if applicable. Since we issued AD 2005-12-16, we 
have determined that the required modification actions might not have 
been implemented correctly. This proposed AD would require an 
inspection of the PSU panels and the PSU panel/airplane interface 
connectors for discrepancies, and corrective actions if necessary. This 
proposed AD would also remove airplanes from the applicability. We are 
proposing this AD to address the unsafe condition on these products.

DATES: We must receive comments on this proposed AD by December 18, 
2017.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:

[[Page 51173]]

     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this NPRM, contact Fokker 
Services B.V., Technical Services Dept., P.O. Box 1357, 2130 EL 
Hoofddorp, the Netherlands; telephone +31 (0)88-6280-350; fax +31 
(0)88-6280-111; email technicalservices@fokker.com; Internet http://www.myfokkerfleet.com. You may view this referenced service information 
at the FAA, Transport Standards Branch, 1601 Lind Avenue SW., Renton, 
WA. 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 http://www.regulations.gov by searching for and locating Docket No. FAA-2017-
0906; 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 proposed AD, 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.

FOR FURTHER INFORMATION CONTACT: Tom Rodriguez, Aerospace Engineer, 
International Section, Transport Standards Branch, 1601 Lind Avenue 
SW., Renton, WA 98055-4056; telephone 425-227-1137; fax 425-227-1149.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2017-0906; 
Product Identifier 2017-NM-039-AD'' at the beginning of your comments. 
We specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this proposed AD. We will consider 
all comments received by the closing date and may amend this proposed 
AD based on those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    We issued AD 2005-12-16, Amendment 39-14132 (70 FR 34642, June 15, 
2005) (``AD 2005-12-16''), for all Fokker Services B.V. Model F28 Mark 
0100 airplanes. AD 2005-12-16 was prompted by reports of smoke in the 
passenger compartment during flight. One of those incidents also 
included a burning smell and consequently led to emergency evacuation 
of the airplane. AD 2005-12-16 requires an inspection to determine the 
part number of the PSU panels for the PSU modification status, and 
corrective actions if applicable. We issued AD 2005-12-16 to detect and 
correct overheating of the PSU panel due to moisture ingress, which 
could result in smoke or fire in the passenger cabin.
    Since we issued AD 2005-12-16, we have determined that the 
modification actions required by AD 2005-12-16 might not have been 
implemented correctly.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2017-0043, dated March 15, 2017 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for certain Fokker 
Services B.V. Model F28 Mark 0100 airplanes. The MCAI states:

    Reports were received of burning smell and smoke in the 
passenger compartment during flight as a result of overheating of 
passenger service units (PSU). These were attributed to moisture 
ingress into the interface electrical connectors of an unsealed PSU 
panel.
    This condition, if not detected and corrected, could lead to 
further incidents of smoke in the passenger compartment, possibly 
resulting in injury to occupants.
    To address this potential unsafe condition, Grimes Aerospace 
Company, the PSU manufacturer (currently Honeywell) issued SB 10-
1178-33-0040 and SB 10-1571-33-0041, and Fokker Services issued 
SBF100-25-097, to provide instructions for installation of improved 
sealing of the PSU and its interface electrical connectors. 
Subsequently, CAA-NL [Civil Aviation Authority--The Netherlands] 
issued AD (BLA) 2004-022 [which corresponds to FAA AD 2005-12-16] to 
require modification, cleaning and sealing of the affected PSU.
    Since that [CAA-NL] AD was issued, following a new occurrence of 
burning smell and smoke in the passenger compartment during 
disembarking of the passengers, the investigation revealed that, on 
several aeroplanes, the modification instructions of Honeywell and 
Fokker Services (SB listed above) were not, or not correctly, 
implemented. Prompted by these findings, Fokker Services published 
SBF100-25-128, providing inspection instructions to detect non-
accomplishment and any discrepancy with the original modification 
instructions.
    For the reasons described above, this [EASA] AD retains the 
requirement of CAA-NL AD (BLA) 2004-022, which is superseded, and 
requires a one-time inspection [for discrepancies] of the PSU panels 
and their interface with the aeroplane, and, depending on findings, 
the accomplishment of applicable corrective action(s).

    Discrepancies include incorrect application of the sealant on the 
PSU panels, uninstalled gaskets, inability to properly lock the 
connectors, and incorrectly applied sealant on the connectors. 
Corrective actions include restoring the sealing of the affected PSU 
panel, repairing the PSU panel, or installing a new PSU panel with a 
replaced receptacle, and installing gaskets; making sure the connecter 
can properly lock; and applying sealant on the connector.
    The MCAI also revised the applicability by specifying specific line 
numbers and excluding airplanes on which certain modifications were 
done. You may examine the MCAI in the AD docket on the Internet at 
http://www.regulations.gov by searching for and locating Docket No. 
FAA-2017-0906.

Related Service Information Under 1 CFR Part 51

    Fokker Services B.V. has issued Fokker Service Bulletin SBF100-25-
128, dated July 21, 2016. This service information describes procedures 
for inspection of the PSU panels and the PSU panel/airplane interface 
connectors for discrepancies, and for incorrectly applied sealant on 
the connectors, and corrective actions.
    Grimes Aerospace has issued Service Bulletin 10-1178-33-0040, dated 
October 15, 1993; Service Bulletin 10-1178-33-0040, Revision 1, dated 
March 25, 1996; and Service Bulletin 10-1571-33-0041, dated October 15, 
1993. This service information describes procedures for inspection of 
the PSU panels and the PSU panel/airplane interface connectors for 
discrepancies, and corrective actions. This service information is 
distinct since it applies to different part numbers.
    This service information is reasonably available because the 
interested parties have access to it through their normal course of 
business or by the means identified in the ADDRESSES section.

[[Page 51174]]

FAA's Determination and Requirements of This Proposed AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI and service 
information referenced above. We are proposing this AD because we 
evaluated all pertinent information and determined an unsafe condition 
exists and is likely to exist or develop on other products of the same 
type design.

Costs of Compliance

    We estimate that this proposed AD affects 8 airplanes of U.S. 
registry.
    The actions required by AD 2005-12-16, and retained in this 
proposed AD take about 5 work-hours per product, at an average labor 
rate of $85 per work-hour. Required parts cost about $6 per product. 
Based on these figures, the estimated cost of the actions that are 
required by AD 2005-12-16 is $431 per product.
    We also estimate that it would take about 13 work-hours per product 
to comply with the basic requirements of this proposed AD. The average 
labor rate is $85 per work-hour. Based on these figures, we estimate 
the cost of this proposed AD on U.S. operators to be $8,840, or $1,105 
per product.
    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this proposed 
AD.

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.
    This AD is issued in accordance with authority delegated by the 
Executive Director, Aircraft Certification Service, as authorized by 
FAA Order 8000.51C. In accordance with that order, issuance of ADs is 
normally a function of the Compliance and Airworthiness Division, but 
during this transition period, the Executive Director has delegated the 
authority to issue ADs applicable to transport category airplanes to 
the Director of the System Oversight Division.

Regulatory Findings

    We determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979);
    3. Will not affect intrastate aviation in Alaska; and
    4. 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.

List of Subjects in 14 CFR Part 39

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

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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 Airworthiness Directive (AD) 
2005-12-16, Amendment 39-14132 (70 FR 34642, June 15, 2005), and adding 
the following new AD:

Fokker Services B.V.: Docket No. FAA-2017-0906; Product Identifier 
2017-NM-039-AD.

(a) Comments Due Date

    We must receive comments by December 18, 2017.

(b) Affected ADs

    This AD replaces 2005-12-16, Amendment 39-14132 (70 FR 34642, 
June 15, 2005) (``AD 2005-12-16'').

(c) Applicability

    This AD applies to Fokker Services B.V. Model F28 Mark 0100 
airplanes, certificated in any category, serial numbers 11244 
through 11527 inclusive, except those airplanes modified in service 
as specified in Fokker Service Bulletin SBF100-25-070, or Fokker 
Service Bulletin SBF100-25-109, or Fokker Modification Report FS-
N545 or FS-N571.

(d) Subject

    Air Transport Association (ATA) of America Code 25, Equipment/
furnishings.

(e) Reason

    This AD was prompted by reports of smoke in the passenger 
compartment during ground operations and in-flight. We are issuing 
this AD to detect and correct overheating of the passenger service 
unit (PSU) panel due to moisture ingress, which could result in 
smoke or fire in the passenger cabin.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Retained Inspection and Corrective Actions, With No Changes

    This paragraph restates the requirements of paragraph (f) of AD 
2005-12-16, with no changes. Within 36 months after July 20, 2005 
(the effective date of AD 2005-12-16), inspect to determine if 
Grimes Aerospace PSU panels having part number (P/N) 10-1178-( ) or 
P/N 10-1571-( ) are installed and the PSU modification status if 
applicable, and do any corrective actions if applicable, by doing 
all of the actions specified in the Accomplishment Instructions of 
Fokker Service Bulletin SBF100-25-097, dated December 30, 2003.

    Note 1 to paragraph (g) of this AD: Fokker Service Bulletin 
SBF100-25-097, dated December 30, 2003, refers to Grimes Aerospace 
Service Bulletin 10-1178-33-0040, Revision 1, dated March 25, 1996 
(for PSU panels having P/N 10-1178-( )); and Service Bulletin 10-
1571-33-0041, dated October 15, 1993 (for PSU panels having P/N 10-
1571-( )), as additional guidance for modifying the PSU panel.

(h) Retained Parts Installation Limitation, With No Changes

    This paragraph restates the requirements of paragraph (g) of AD 
2005-12-16, with no changes. As of July 20, 2005 (the effective date 
of AD 2005-12-16), no person may install a PSU panel having P/N 10-
1178-( ) or P/N 10-1571-( ) on any airplane, unless it has been 
inspected and any applicable corrective actions have been done in 
accordance with paragraph (g) of this AD.

(i) New Affected PSU Identification

    For the purpose of this AD, Grimes (Honeywell) PSUs having P/N 
10-1178-(series) with a serial number below 4000, and

[[Page 51175]]

PSUs having P/N 10-1571-(series) with a serial number below 1000, 
are referred to as affected PSUs in paragraphs (j) through (l) of 
this AD.

(j) New Inspections

    Within 24 months after the effective date of this AD: Do the 
actions required by paragraphs (j)(1) and (j)(2) of this AD.
    (1) Do a general visual inspection of the panel of each affected 
PSU for incorrect application of the sealant, in accordance with the 
Accomplishment Instructions of Fokker Service Bulletin SBF100-25-
097, dated December 30, 2003; and, as applicable, Grimes Aerospace 
Service Bulletin 10-1178-33-0040, dated October 15, 1993 (for PSUs 
having P/N 10-1178-(series)); Revision 1, dated March 25, 1996 (for 
PSUs having P/N 10-1178-(series)); and Grimes Aerospace Service 
Bulletin 10-1571-33-0041, dated October 15, 1993 (for PSUs having P/
N 10-1571-(series)).
    (2) Do a general visual inspection of the electrical connectors 
of each affected PSU panel for discrepancies; i.e., uninstalled 
gaskets, inability to properly lock the connectors, and incorrectly 
applied sealant on the connectors; in accordance with the 
Accomplishment Instructions of Fokker Service Bulletin SBF100-25-
128, dated July 21, 2016.

(k) Corrective Actions

    If, during any inspection required by paragraph (j) of this AD, 
any discrepancy is found, before further flight, restore the sealing 
of the affected PSU panels and accomplish all applicable corrective 
actions to correct the PSU panel interface, in accordance with the 
Accomplishment Instructions of Fokker Service Bulletin SBF100-25-
128, dated July 21, 2016. Do all applicable corrective actions 
before further flight.

(l) Parts Installation Limitation

    As of the effective date of this AD, an affected PSU panel may 
be installed on any airplane, provided that, before further flight 
after installation, it has been inspected in accordance with 
paragraph (j) of this AD and all applicable corrective actions have 
been done in accordance with paragraph (k) of this AD.

(m) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Section, Transport Standards Branch, FAA, has the 
authority to approve AMOCs for this AD, if requested using the 
procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, 
send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the International Section, send it to the attention of 
the person identified in paragraph (n)(2) of this AD. Information 
may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov.
    (i) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.
    (ii) AMOCs approved previously for AD 2005-12-16 are approved as 
AMOCs for the corresponding provisions of this AD.
    (2) Contacting the Manufacturer: As of the effective date of 
this AD, for any requirement in this AD to obtain corrective actions 
from a manufacturer, the action must be accomplished using a method 
approved by the Manager, International Section, Transport Standards 
Branch, FAA; or the European Aviation Safety Agency (EASA); or 
Fokker Services B.V.'s Design Organization Approval (DOA). If 
approved by the DOA, the approval must include the DOA-authorized 
signature.

(n) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2017-0043, dated March 6, 2017, 
for related information. This MCAI may be found in the AD docket on 
the Internet at http://www.regulations.gov by searching for and 
locating Docket No. FAA-2017-0906.
    (2) For more information about this AD, contact Tom Rodriguez, 
Aerospace Engineer, International Section, Transport Standards 
Branch, 1601 Lind Avenue SW., Renton, WA 98055-4056; telephone 425-
227-1137; fax 425-227-1149.
    (3) For service information identified in this AD, contact 
Fokker Services B.V., Technical Services Dept., P.O. Box 1357, 2130 
EL Hoofddorp, the Netherlands; telephone +31 (0)88-6280-350; fax +31 
(0)88-6280-111; email technicalservices@fokker.com; Internet http://www.myfokkerfleet.com. You may view this service information at the 
FAA, Transport Standards Branch, 1601 Lind Avenue SW., Renton, WA. 
For information on the availability of this material at the FAA, 
call 425-227-1221.

    Issued in Renton, Washington, on October 11, 2017.
Dionne Palermo,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2017-22558 Filed 11-2-17; 8:45 am]
BILLING CODE 4910-13-P