Airworthiness Directives; Schempp-Hirth Flugzeugbau GmbH Sailplanes, 61722-61725 [2015-25710]

Download as PDF 61722 Federal Register / Vol. 80, No. 198 / Wednesday, October 14, 2015 / Rules and Regulations 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: a. Removing airworthiness directives (AD) 2001–18–06, Amendment 39– 12432 (66 FR 47575, September 13, 2001) (‘‘AD 2001–18–06’’); and AD 2008–22–16, Amendment 39–15712 (73 FR 63629, October 27, 2008) (‘‘AD 2008–22–16’’), and ■ b. Adding the following new AD: ■ ■ 2015–20–09 General Electric Company: Amendment 39–18288; Docket No. FAA–2008–0808; Directorate Identifier 2008–NE–18–AD. (a) Effective Date This AD is effective November 18, 2015. (b) Affected ADs This AD replaces AD 2001–18–06 and AD 2008–22–16. (c) Applicability This AD applies to all General Electric Company (GE) CT58–100–2, CT58–110–1, CT58–110–2, CT58–140–1, and CT58–140–2 turboshaft engines. (d) Unsafe Condition This AD was prompted by recalculation of life for parts installed on engines used in Utility operations, and a reduced life for compressor spools in all operations. We are issuing this AD to prevent failure of lifelimited rotating parts, uncontained part release, damage to the engine, and damage to the aircraft. (e) Compliance Do the actions required by this AD, unless already done. tkelley on DSK3SPTVN1PROD with RULES (1) Calculating Cyclic Life Consumption Re-calculate the cycles-since-new for all compressor spools, and for life-limited rotating parts other than compressor spools used in Utility operations. Use paragraphs 3.A.(1) and 3.B.(1) in the Accomplishment Instructions of GE CT58 Alert Service Bulletin (ASB) No. SB 72–A0162, Revision 16, dated January 7, 2015, to perform the calculations. (2) Removal of Compressor Spools After the effective date of this AD, remove compressor spools, part numbers (P/Ns) 5124T94G02, 6010T57G04, 6010T57G07, and 6010T57G08 from service, before reaching the life limits specified in paragraph 4.A., Appendix A, in GE CT58 ASB No. SB 72– A0162, Revision 16, dated January 7, 2015, as re-calculated per paragraph (e)(1) of this AD. VerDate Sep<11>2014 16:10 Oct 13, 2015 Jkt 238001 (3) Removal of Rotating Parts Used in Utility Operations Other Than Compressor Spools After the effective date of this AD, remove from service any life-limited rotating part used in Utility operations, other than the compressor spools with P/Ns listed in paragraph (e)(2) of this AD, that exceeds its life limit as re-calculated per paragraph (e)(1) of this AD. Use Tables I, II, III, and IV in paragraphs 3.D. through 3.G. in the Accomplishment Instructions in GE CT58 ASB No. SB 72–A0162, Revision 16, dated January 7, 2015, and paragraph 4.D., Appendix A of this GE CT58 ASB, to determine when to remove these parts. 202–741–6030, or go to: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. (4) Removal of Rotating Parts Not Used in Utility Operations Other Than Compressor Spools After the effective date of this AD, remove from service any life-limited rotating part not used in Utility operations, other than the compressor spools with P/Ns listed in paragraph (e)(2) of this AD, that exceeds its life limit. Use Tables I, II, III, and IV in paragraphs 3.D. through 3.G. in the Accomplishment Instructions in GE CT58 ASB No. SB 72–A0162, Revision 16, dated January 7, 2015, and paragraph 4.C., Appendix A of this GE CT58 ASB, to determine when to remove these parts. Federal Aviation Administration (f) Alternative Methods of Compliance (AMOCs) The Manager, Engine Certification Office, FAA, may approve AMOCs for this AD. Use the procedures found in 14 CFR 39.19 to make your request. You may email your request to: ANE-AD-AMOC@faa.gov. (g) Related Information For more information about this AD, contact Christopher McGuire, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; phone: 781–238–7120; fax: 781–238– 7199; email: chris.mcguire@faa.gov. (h) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) General Electric Company (GE) CT58 Alert Service Bulletin No. SB 72–A0162, Revision 16, dated January 7, 2015. (ii) Reserved. (3) For GE service information identified in this AD, contact General Electric Company, GE Aviation, Room 285, One Neumann Way, Cincinnati, OH 45215; phone: 513–552–3272; email: aviation.fleetsupport@ge.com. (4) You may view this service information at FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA. For information on the availability of this material at the FAA, call 781–238–7125. (5) You may view this service information at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 Issued in Burlington, Massachusetts, on September 30, 2015. Colleen M. D’Alessandro, Directorate Manager, Engine & Propeller Directorate, Aircraft Certification Service. [FR Doc. 2015–25719 Filed 10–13–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION 14 CFR Part 39 [Docket No. FAA–2015–3224; Directorate Identifier 2015–CE–026–AD; Amendment 39–18290; AD 2015–20–11] RIN 2120–AA64 Airworthiness Directives; SchemppHirth Flugzeugbau GmbH Sailplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for Schempp-Hirth Flugzeugbau GmbH Models Duo Discus and Duo Discus T powered sailplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued 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 excessive load on the air brake system. We are issuing this AD to require actions to address the unsafe condition on these products. DATES: This AD is effective November 18, 2015. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of November 18, 2015. ADDRESSES: You may examine the AD docket on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 3224; or in person at Document Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. For service information identified in this AD, contact Schempp-Hirth Flugzeugbau GmbH, Krebenstrasse 25, 73230 Kirchheim/Teck, Germany; telephone: +49 7021 7298–0; fax: +49 7021 7298–199; email: info@schempphirth.com; Internet: https:// SUMMARY: E:\FR\FM\14OCR1.SGM 14OCR1 Federal Register / Vol. 80, No. 198 / Wednesday, October 14, 2015 / Rules and Regulations www.schempp-hirth.com. You may view this referenced service information at the FAA, Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329–4148. It is also available on the Internet at https:// www.regulations.gov by searching for Docket No. FAA–2015–3224. FOR FURTHER INFORMATION CONTACT: Jim Rutherford, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4165; fax: (816) 329–4090; email: jim.rutherford@ faa.gov. SUPPLEMENTARY INFORMATION: tkelley on DSK3SPTVN1PROD with RULES Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to add an AD that would apply to Schempp-Hirth Flugzeugbau GmbH Models Duo Discus and Duo Discus T powered sailplanes. The NPRM was published in the Federal Register on August 4, 2015 (80 FR 46206). The NPRM proposed to correct an unsafe condition for the specified products and was based on mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country. The MCAI states: Operational experience shows that application of an excessive load on the air brake system may induce damage to the drive funnels in the fuselage and to the air brake bellcrank at the root rips of the wing. This condition, if not detected and corrected, could lead to an uncontrolled actuation of the air brakes (symmetric and asymmetric), possibly resulting in reduced control of the (powered) sailplane. To address this potential unsafe condition, Schempp-Hirth Flugzeugbau GmbH issued Technical Note (TN) 380–2, 396–17, 868–22 and 890–14 (published as a single document) to provide inspection instructions. Consequently EASA issued AD 2015–0139 to require to repetitive inspections of the air brake bellcrank, the air brake drive funnels and the airbrake control system, and replacement of damaged parts. Since that AD was issued, it was found that the drawing number of the reinforced air brake drive funnel was incorrectly stated in the original issue of the Schempp-Hirth TN. The wrongly referred drawing S14FB703 refers to an existing part, different from air brake drive funnel and cannot be installed as a replacement part for air brake drive funnel. Consequently, Schempp-Hirth Flugzeugbau GmbH issued Revision 1 of TN 380–2, 396– 17, 868–22 and 890–14, hearafter referenced to as ‘the revised TN’ in this AD. For the reasons described above, this AD is revised to require using the revised TN. The MCAI can be found in the AD docket on the Internet at https:// www.regulations.gov/ VerDate Sep<11>2014 16:10 Oct 13, 2015 Jkt 238001 #!documentDetail;D=FAA-2015-32240002. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM (80 FR 46206, August 4, 2015) or on the determination of the cost to the public. Conclusion We reviewed the relevant data and determined that air safety and the public interest require adopting the AD as proposed except for minor editorial changes. We have determined that these minor changes: • Are consistent with the intent that was proposed in the NPRM (80 FR 46206, August 4, 2015) for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM (80 FR 46206, August 4, 2015). Related Service Information Under 1 CFR Part 51 We reviewed Schempp-Hirth Flugzeugbau GmbH Technical Note No. 380–2/396–17/868–22/890–14, Revision 1, issued July 13, 2015 (published as a single document), and Working instruction for Technical Note No. 380– 2/396–17/868–22/890–14, Ausgabe (English translation: issue) 1, Datum (English translation: dated) May 11, 2015. The service information describes procedures for inspecting and replacing the airbrake bell crank and the airbrake drive funnels and inspecting the airbrake control system for proper clearance and making necessary adjustments. 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 of the AD. Costs of Compliance We estimate that this AD will affect 31 products of U.S. registry. We also estimate that it will take about 2 workhours per product to comply with the basic inspection requirements of this AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this portion of the AD on U.S. operators to be $5,270, or $170 per product. We estimate that it will take about 4 work-hours per product to comply with the airbrake bell crank replacement requirement of this AD. The average labor rate is $85 per work-hour. Required parts will cost about $500 per product. PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 61723 Based on these figures, we estimate the cost of this portion of the AD on U.S. operators to be $26,040, or $840 per product. We estimate that it will take about 4 work-hours per product to comply with the airbrake drive funnel replacement requirement of this AD. The average labor rate is $85 per work-hour. Required parts will cost about $500 per product. Based on these figures, we estimate the cost of this portion of the AD on U.S. operators to be $26,040, or $840 per product. In addition, we estimate that any necessary follow-on actions to make any necessary adjustments to the airbrake control system will take about 2 workhours for a cost of $170 per product. We have no way of determining the number of products that may need these actions. 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), (3) Will not affect intrastate aviation in Alaska, and E:\FR\FM\14OCR1.SGM 14OCR1 61724 Federal Register / Vol. 80, No. 198 / Wednesday, October 14, 2015 / Rules and Regulations (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. Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 3224; 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 the NPRM, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (telephone (800) 647– 5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. 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: ■ 2015–20–11 Schempp-Hirth Flugzeugbau GmbH: Amendment 39–18290; Docket No. FAA–2015–3224; Directorate Identifier 2015–CE–026–AD. (a) Effective Date This airworthiness directive (AD) becomes effective November 18, 2015. (b) Affected ADs None. tkelley on DSK3SPTVN1PROD with RULES (c) Applicability This AD applies to Schempp-Hirth Flugzeugbau GmbH Model Duo Discus powered sailplanes, serial numbers 1 through 639, and Model Duo Discus T powered sailplanes, serial numbers 1 through 110 and 112 through 247, certificated in any category. (d) Subject Air Transport Association of America (ATA) Code 27: Flight Controls. (e) Reason This AD was prompted by mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another VerDate Sep<11>2014 16:10 Oct 13, 2015 Jkt 238001 country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as excessive load on the air brake system. We are issuing this AD to prevent uncontrolled actuation of the air brakes (symmetric or asymmetric), which could result in reduced control. (f) Actions and Compliance Unless already done, do the actions in paragraph (f)(1) through (f)(5) of this AD. (1) Within 40 days after November 17, 2015 (the effective date of this AD) and repetitively thereafter at intervals not to exceed 100 hours time-in-service until the terminating replacement action required in paragraphs (f)(2) and (f)(3) of this AD (as applicable) is done, inspect the airbrake bell crank, the airbrake drive funnels, and the airbrake control system. (i) Inspect the airbrake bell crank and the airbrake drive funnels for cracks and damage following Action 1 in Schempp-Hirth Flugzeugbau GmbH Technical Note No. 380– 2/396–17/868–22/890–14, Revision 1, issued July 13, 2015 (published as a single document). (ii) Inspect the airbrake control system for proper clearance following Paragraph 2.d. of Schempp-Hirth Flugzeugbau GmbH Working instruction for Technical Note No. 380–2/ 396–17/868–22/890–14, Ausgabe (English translation: issue) 1, Datum (English translation: dated) May 11, 2015. (2) If cracks or damage is found on the airbrake bell cranks or the airbrake drive funnels during any inspection required in paragraph (f)(1) of this AD, before further flight, replace each cracked or damaged part with a reinforced part. Installing a reinforced part terminates the repetitive inspections required in paragraph (f)(1) of this AD for that part. (i) For replacement of the airbrake bell cranks, follow Picture 2: Reinforced version of airbrake bell crank according to HS 11– 50.016, Revision a or later, in Schempp-Hirth Flugzeugbau GmbH Working instruction for Technical Note No. 380–2/396–17/868–22/ 890–14, Ausgabe (English translation: issue) 1, Datum (English translation: dated) May 11, 2015. (ii) For replacement of the airbrake drive funnels, follow Picture 5: Airbrake drive funnel in fuselage ‘‘Reinforcement of airbrake drive funnel according to drawing S14RB703, Revision a, in Schempp-Hirth Flugzeugbau GmbH Working instruction for Technical Note No. 380–2/396–17/868–22/890–14, Ausgabe (English translation: issue) 1, Datum (English translation: dated) May 11, 2015. (3) If no cracks or damage were found on the airbrake bell cranks or the airbrake drive funnels during any inspection required in paragraph (f)(1) of this AD, within 12 months after November 17, 2015 (the effective date of this AD), replace each of the airbrake bell cranks and airbrake drive funnels with a reinforced part. These replacements terminate the repetitive inspections required in paragraph (f)(1) of this AD. (i) For replacement of the airbrake bell cranks, follow Picture 2: Reinforced version of airbrake bell crank according to HS 11– 50.016, Revision a or later, in Schempp-Hirth Flugzeugbau GmbH Working instruction for PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 Technical Note No. 380–2/396–17/868–22/ 890–14, Ausgabe (English translation: issue) 1, Datum (English translation: dated) May 11, 2015. (ii) For replacement of the airbrake drive funnels, follow Picture 5: Airbrake drive funnel in fuselage, ‘‘Reinforcement of airbrake drive funnel according to drawing S14RB703, Revision a,’’ in Schempp-Hirth Flugzeugbau GmbH Working instruction for Technical Note No. 380–2/396–17/868–22/ 890–14, Ausgabe (English translation: issue) 1, Datum (English translation: dated) May 11, 2015. (4) If the airbrake control system is found to not have proper clearance during the inspection required in paragraph (f)(1) of this AD, before further flight, make all necessary corrective adjustments following Paragraph 2.d. of Schempp-Hirth Flugzeugbau GmbH Working instruction for Technical Note No. 380–2/396–17/868–22/890–14, Ausgabe (English translation: issue) 1, Datum (English translation: dated) May 11, 2015. (5) As of November 17, 2015 (the effective date of this AD), only install an airbrake bell crank or an airbrake drive funnel that corresponds to Picture 2: Reinforced version of airbrake bell crank according to HS 11– 50.016, Revision a or later, and Picture 5: Airbrake drive funnel in fuselage, ‘‘Reinforcement of airbrake drive funnel according to drawing S14RB703, Revision a,’’ in Schempp-Hirth Flugzeugbau GmbH Working instruction for Technical Note No. 380–2/396–17/868–22/890–14, Ausgabe (English translation: issue) 1, Datum (English translation: dated) May 11, 2015, as applicable. (g) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, Standards 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: Jim Rutherford, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4165; fax: (816) 329– 4090; email: jim.rutherford@faa.gov. Before using any approved AMOC on any sailplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. (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. (h) Related Information Refer to MCAI European Aviation Safety Agency (EASA) AD No. 2015–0139R1, dated July 15, 2015, for related information. You may examine the MCAI on the Internet at https://www.regulations.gov/ #!documentDetail;D=FAA-2015-3224-0002. E:\FR\FM\14OCR1.SGM 14OCR1 Federal Register / Vol. 80, No. 198 / Wednesday, October 14, 2015 / Rules and Regulations (i) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) Schempp-Hirth Flugzeugbau GmbH Technical Note No. 380–2/396–17/868–22/ 890–14, Revision 1, issued July 13, 2015 (published as a single document). (ii) Schempp-Hirth Flugzeugbau GmbH Working instruction for Technical Note No. 380–2/396–17/868–22/890–14, Ausgabe (English translation: issue) 1, Datum (English translation: dated) May 11, 2015. (3) For Schempp-Hirth Flugzeugbau GmbH service information identified in this AD, contact Schempp-Hirth Flugzeugbau GmbH, Krebenstrasse 25, 73230 Kirchheim/Teck, Germany; telephone: +49 7021 7298–0; fax: +49 7021 7298–199; email: info@schempphirth.com; Internet: https://www.schempphirth.com. (4) You may view this service information at the FAA, Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329–4148. In addition, you can access this service information on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2015–3224. (5) You may view this 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/cfr/ibrlocations.html. Issued in Kansas City, Missouri, on October 1, 2015. Melvin Johnson, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–25710 Filed 10–13–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–4085; Directorate Identifier 2015–CE–033–AD; Amendment 39–18292; AD 2015–20–13] tkelley on DSK3SPTVN1PROD with RULES Airworthiness Directives; Piper Aircraft, Inc. Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: We are adopting a new airworthiness directive (AD) for certain VerDate Sep<11>2014 16:10 Oct 13, 2015 Jkt 238001 This AD is effective October 29, 2015. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of October 29, 2015. We must receive comments on this AD by November 30, 2015. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to https://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: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this AD, contact Piper Aircraft, Inc., Customer Service, 2926 Piper Drive, Vero Beach, Florida 32960; telephone: (877) 879–0275; fax: none; email: customer.service@piper.com; Internet: www.piper.com. You may review the referenced service information at the FAA, Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329– 4148. It is also available on the Internet at https://www.regulations.gov by searching for locating Docket No. FAA– 2015–4085. DATES: Examining the AD Docket RIN 2120–AA64 SUMMARY: Piper Aircraft, Inc. Models PA–28–161, PA–28–181, and PA–28R–201 airplanes. This AD requires inspecting the right wing rib at wing station 140.09 for cracks and taking necessary corrective action. This AD was prompted by a report of cracks found in the wing rib bead radius that were formed during production. We are issuing this AD to correct the unsafe condition on these products. You may examine the AD docket on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 4085; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The street address for PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 61725 the Docket Office (phone: 800–647– 5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Gregory ‘‘Keith’’ Noles, Aerospace Engineer, FAA, Atlanta Aircraft Certification Office, 1701 Columbia Avenue, College Park, Georgia 30337; phone: (404) 474–5551; fax: (404) 474– 5606; email: gregory.noles@faa.gov. SUPPLEMENTARY INFORMATION: Discussion We received a report from Piper Aircraft, Inc. of a production quality control problem on certain Models PA– 28–161, PA–28–181, and PA–28R–201 airplanes. A change in production tooling and processes caused cracks to form along the edge of rib stiffening beads during manufacture. These cracks cause reduced structural integrity of the wing, which results in the inability of the wing rib to carry ultimate load. This condition, if not corrected, could result in reduced structural integrity of the wing with consequent loss of control. We are issuing this AD to correct the unsafe condition on these products. Related Service Information Under 1 CFR Part 51 We reviewed Piper Aircraft, Inc. Service Bulletin No. 1279, dated August 26, 2015. The service bulletin describes procedures for inspecting the right wing rib at wing station 140.09 for cracks and for obtaining an FAA-approved repair if cracks are found. 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 of this AD. FAA’s Determination We are issuing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. AD Requirements This AD requires accomplishing the actions specified in the service information described previously. FAA’s Justification and Determination of the Effective Date An unsafe condition exists that requires the immediate adoption of this AD. The FAA has found that the risk to the flying public justifies waiving notice and comment prior to adoption of this rule because cracks in the wing rib, if not detected and corrected immediately, E:\FR\FM\14OCR1.SGM 14OCR1

Agencies

[Federal Register Volume 80, Number 198 (Wednesday, October 14, 2015)]
[Rules and Regulations]
[Pages 61722-61725]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-25710]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-3224; Directorate Identifier 2015-CE-026-AD; 
Amendment 39-18290; AD 2015-20-11]
RIN 2120-AA64


Airworthiness Directives; Schempp-Hirth Flugzeugbau GmbH 
Sailplanes

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

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for 
Schempp-Hirth Flugzeugbau GmbH Models Duo Discus and Duo Discus T 
powered sailplanes. This AD results from mandatory continuing 
airworthiness information (MCAI) issued 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 excessive 
load on the air brake system. We are issuing this AD to require actions 
to address the unsafe condition on these products.

DATES: This AD is effective November 18, 2015.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of November 18, 
2015.

ADDRESSES: You may examine the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2015-
3224; or in person at Document Management Facility, U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590.
    For service information identified in this AD, contact Schempp-
Hirth Flugzeugbau GmbH, Krebenstrasse 25, 73230 Kirchheim/Teck, 
Germany; telephone: +49 7021 7298-0; fax: +49 7021 7298-199; email: 
hirth.com">info@schempp-hirth.com; Internet: https://

[[Page 61723]]

www.schempp-hirth.com. You may view this referenced service information 
at the FAA, Small Airplane Directorate, 901 Locust, Kansas City, 
Missouri 64106. For information on the availability of this material at 
the FAA, call (816) 329-4148. It is also available on the Internet at 
https://www.regulations.gov by searching for Docket No. FAA-2015-3224.

FOR FURTHER INFORMATION CONTACT: Jim Rutherford, Aerospace Engineer, 
FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, 
Missouri 64106; telephone: (816) 329-4165; fax: (816) 329-4090; email: 
jim.rutherford@faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to add an AD that would apply to Schempp-Hirth Flugzeugbau GmbH 
Models Duo Discus and Duo Discus T powered sailplanes. The NPRM was 
published in the Federal Register on August 4, 2015 (80 FR 46206). The 
NPRM proposed to correct an unsafe condition for the specified products 
and was based on mandatory continuing airworthiness information (MCAI) 
originated by an aviation authority of another country. The MCAI 
states:

    Operational experience shows that application of an excessive 
load on the air brake system may induce damage to the drive funnels 
in the fuselage and to the air brake bellcrank at the root rips of 
the wing.
    This condition, if not detected and corrected, could lead to an 
uncontrolled actuation of the air brakes (symmetric and asymmetric), 
possibly resulting in reduced control of the (powered) sailplane.
    To address this potential unsafe condition, Schempp-Hirth 
Flugzeugbau GmbH issued Technical Note (TN) 380-2, 396-17, 868-22 
and 890-14 (published as a single document) to provide inspection 
instructions.
    Consequently EASA issued AD 2015-0139 to require to repetitive 
inspections of the air brake bellcrank, the air brake drive funnels 
and the airbrake control system, and replacement of damaged parts.
    Since that AD was issued, it was found that the drawing number 
of the reinforced air brake drive funnel was incorrectly stated in 
the original issue of the Schempp-Hirth TN. The wrongly referred 
drawing S14FB703 refers to an existing part, different from air 
brake drive funnel and cannot be installed as a replacement part for 
air brake drive funnel. Consequently, Schempp-Hirth Flugzeugbau GmbH 
issued Revision 1 of TN 380-2, 396-17, 868-22 and 890-14, hearafter 
referenced to as `the revised TN' in this AD.
    For the reasons described above, this AD is revised to require 
using the revised TN.

The MCAI can be found in the AD docket on the Internet at https://www.regulations.gov/#!documentDetail;D=FAA-2015-3224-0002.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM (80 FR 46206, August 4, 
2015) or on the determination of the cost to the public.

Conclusion

    We reviewed the relevant data and determined that air safety and 
the public interest require adopting the AD as proposed except for 
minor editorial changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM (80 FR 46206, August 4, 2015) for correcting the unsafe condition; 
and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (80 FR 46206, August 4, 2015).

Related Service Information Under 1 CFR Part 51

    We reviewed Schempp-Hirth Flugzeugbau GmbH Technical Note No. 380-
2/396-17/868-22/890-14, Revision 1, issued July 13, 2015 (published as 
a single document), and Working instruction for Technical Note No. 380-
2/396-17/868-22/890-14, Ausgabe (English translation: issue) 1, Datum 
(English translation: dated) May 11, 2015. The service information 
describes procedures for inspecting and replacing the airbrake bell 
crank and the airbrake drive funnels and inspecting the airbrake 
control system for proper clearance and making necessary adjustments. 
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 of the AD.

Costs of Compliance

    We estimate that this AD will affect 31 products of U.S. registry. 
We also estimate that it will take about 2 work-hours per product to 
comply with the basic inspection requirements of this AD. The average 
labor rate is $85 per work-hour.
    Based on these figures, we estimate the cost of this portion of the 
AD on U.S. operators to be $5,270, or $170 per product.
    We estimate that it will take about 4 work-hours per product to 
comply with the airbrake bell crank replacement requirement of this AD. 
The average labor rate is $85 per work-hour. Required parts will cost 
about $500 per product.
    Based on these figures, we estimate the cost of this portion of the 
AD on U.S. operators to be $26,040, or $840 per product.
    We estimate that it will take about 4 work-hours per product to 
comply with the airbrake drive funnel replacement requirement of this 
AD. The average labor rate is $85 per work-hour. Required parts will 
cost about $500 per product.
    Based on these figures, we estimate the cost of this portion of the 
AD on U.S. operators to be $26,040, or $840 per product.
    In addition, we estimate that any necessary follow-on actions to 
make any necessary adjustments to the airbrake control system will take 
about 2 work-hours for a cost of $170 per product. We have no way of 
determining the number of products that may need these actions.

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),
    (3) Will not affect intrastate aviation in Alaska, and

[[Page 61724]]

    (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.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2015-
3224; 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 the NPRM, the regulatory evaluation, any comments received, 
and other information. The street address for the Docket Office 
(telephone (800) 647-5527) is in the ADDRESSES section. Comments will 
be available in the AD docket shortly after receipt.

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

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:

2015-20-11 Schempp-Hirth Flugzeugbau GmbH: Amendment 39-18290; 
Docket No. FAA-2015-3224; Directorate Identifier 2015-CE-026-AD.

(a) Effective Date

    This airworthiness directive (AD) becomes effective November 18, 
2015.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Schempp-Hirth Flugzeugbau GmbH Model Duo 
Discus powered sailplanes, serial numbers 1 through 639, and Model 
Duo Discus T powered sailplanes, serial numbers 1 through 110 and 
112 through 247, certificated in any category.

(d) Subject

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

(e) Reason

    This AD was prompted by 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 excessive load 
on the air brake system. We are issuing this AD to prevent 
uncontrolled actuation of the air brakes (symmetric or asymmetric), 
which could result in reduced control.

(f) Actions and Compliance

    Unless already done, do the actions in paragraph (f)(1) through 
(f)(5) of this AD.
    (1) Within 40 days after November 17, 2015 (the effective date 
of this AD) and repetitively thereafter at intervals not to exceed 
100 hours time-in-service until the terminating replacement action 
required in paragraphs (f)(2) and (f)(3) of this AD (as applicable) 
is done, inspect the airbrake bell crank, the airbrake drive 
funnels, and the airbrake control system.
    (i) Inspect the airbrake bell crank and the airbrake drive 
funnels for cracks and damage following Action 1 in Schempp-Hirth 
Flugzeugbau GmbH Technical Note No. 380-2/396-17/868-22/890-14, 
Revision 1, issued July 13, 2015 (published as a single document).
    (ii) Inspect the airbrake control system for proper clearance 
following Paragraph 2.d. of Schempp-Hirth Flugzeugbau GmbH Working 
instruction for Technical Note No. 380-2/396-17/868-22/890-14, 
Ausgabe (English translation: issue) 1, Datum (English translation: 
dated) May 11, 2015.
    (2) If cracks or damage is found on the airbrake bell cranks or 
the airbrake drive funnels during any inspection required in 
paragraph (f)(1) of this AD, before further flight, replace each 
cracked or damaged part with a reinforced part. Installing a 
reinforced part terminates the repetitive inspections required in 
paragraph (f)(1) of this AD for that part.
    (i) For replacement of the airbrake bell cranks, follow Picture 
2: Reinforced version of airbrake bell crank according to HS 11-
50.016, Revision a or later, in Schempp-Hirth Flugzeugbau GmbH 
Working instruction for Technical Note No. 380-2/396-17/868-22/890-
14, Ausgabe (English translation: issue) 1, Datum (English 
translation: dated) May 11, 2015.
    (ii) For replacement of the airbrake drive funnels, follow 
Picture 5: Airbrake drive funnel in fuselage ``Reinforcement of 
airbrake drive funnel according to drawing S14RB703, Revision a, in 
Schempp-Hirth Flugzeugbau GmbH Working instruction for Technical 
Note No. 380-2/396-17/868-22/890-14, Ausgabe (English translation: 
issue) 1, Datum (English translation: dated) May 11, 2015.
    (3) If no cracks or damage were found on the airbrake bell 
cranks or the airbrake drive funnels during any inspection required 
in paragraph (f)(1) of this AD, within 12 months after November 17, 
2015 (the effective date of this AD), replace each of the airbrake 
bell cranks and airbrake drive funnels with a reinforced part. These 
replacements terminate the repetitive inspections required in 
paragraph (f)(1) of this AD.
    (i) For replacement of the airbrake bell cranks, follow Picture 
2: Reinforced version of airbrake bell crank according to HS 11-
50.016, Revision a or later, in Schempp-Hirth Flugzeugbau GmbH 
Working instruction for Technical Note No. 380-2/396-17/868-22/890-
14, Ausgabe (English translation: issue) 1, Datum (English 
translation: dated) May 11, 2015.
    (ii) For replacement of the airbrake drive funnels, follow 
Picture 5: Airbrake drive funnel in fuselage, ``Reinforcement of 
airbrake drive funnel according to drawing S14RB703, Revision a,'' 
in Schempp-Hirth Flugzeugbau GmbH Working instruction for Technical 
Note No. 380-2/396-17/868-22/890-14, Ausgabe (English translation: 
issue) 1, Datum (English translation: dated) May 11, 2015.
    (4) If the airbrake control system is found to not have proper 
clearance during the inspection required in paragraph (f)(1) of this 
AD, before further flight, make all necessary corrective adjustments 
following Paragraph 2.d. of Schempp-Hirth Flugzeugbau GmbH Working 
instruction for Technical Note No. 380-2/396-17/868-22/890-14, 
Ausgabe (English translation: issue) 1, Datum (English translation: 
dated) May 11, 2015.
    (5) As of November 17, 2015 (the effective date of this AD), 
only install an airbrake bell crank or an airbrake drive funnel that 
corresponds to Picture 2: Reinforced version of airbrake bell crank 
according to HS 11-50.016, Revision a or later, and Picture 5: 
Airbrake drive funnel in fuselage, ``Reinforcement of airbrake drive 
funnel according to drawing S14RB703, Revision a,'' in Schempp-Hirth 
Flugzeugbau GmbH Working instruction for Technical Note No. 380-2/
396-17/868-22/890-14, Ausgabe (English translation: issue) 1, Datum 
(English translation: dated) May 11, 2015, as applicable.

(g) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
Standards 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: Jim Rutherford, Aerospace Engineer, FAA, Small 
Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 
64106; telephone: (816) 329-4165; fax: (816) 329-4090; email: 
jim.rutherford@faa.gov. Before using any approved AMOC on any 
sailplane to which the AMOC applies, notify your appropriate 
principal inspector (PI) in the FAA Flight Standards District Office 
(FSDO), or lacking a PI, your local FSDO.
    (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.

(h) Related Information

    Refer to MCAI European Aviation Safety Agency (EASA) AD No. 
2015-0139R1, dated July 15, 2015, for related information. You may 
examine the MCAI on the Internet at https://www.regulations.gov/#!documentDetail;D=FAA-2015-3224-0002.

[[Page 61725]]

(i) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (i) Schempp-Hirth Flugzeugbau GmbH Technical Note No. 380-2/396-
17/868-22/890-14, Revision 1, issued July 13, 2015 (published as a 
single document).
    (ii) Schempp-Hirth Flugzeugbau GmbH Working instruction for 
Technical Note No. 380-2/396-17/868-22/890-14, Ausgabe (English 
translation: issue) 1, Datum (English translation: dated) May 11, 
2015.
    (3) For Schempp-Hirth Flugzeugbau GmbH service information 
identified in this AD, contact Schempp-Hirth Flugzeugbau GmbH, 
Krebenstrasse 25, 73230 Kirchheim/Teck, Germany; telephone: +49 7021 
7298-0; fax: +49 7021 7298-199; email: hirth.com">info@schempp-hirth.com; 
Internet: https://www.schempp-hirth.com.
    (4) You may view this service information at the FAA, Small 
Airplane Directorate, 901 Locust, Kansas City, Missouri 64106. For 
information on the availability of this material at the FAA, call 
(816) 329-4148. In addition, you can access this service information 
on the Internet at https://www.regulations.gov by searching for and 
locating Docket No. FAA-2015-3224.
    (5) You may view this 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/cfr/ibr-locations.html.

    Issued in Kansas City, Missouri, on October 1, 2015.
Melvin Johnson,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.

[FR Doc. 2015-25710 Filed 10-13-15; 8:45 am]
BILLING CODE 4910-13-P
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