80 FR 61722 - Airworthiness Directives; Schempp-Hirth Flugzeugbau GmbH Sailplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 80, Issue 198 (October 14, 2015)
Federal Aviation Administration
Federal Register Volume 80, Issue 198 (October 14, 2015)
| Page Range | 61722-61725 | |
| FR Document | 2015-25710 |
[Federal Register Volume 80, Number 198 (Wednesday, October 14, 2015)] [Rules and Regulations] [Pages 61722-61725] From the Federal Register Online [www.thefederalregister.org] [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 http://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: http:// [[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 http://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 http://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 http://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 http://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: http://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 http://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: http://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
![61722 Federal Register / Vol. 80, No. 198 / Wednesday, October 14, 2015 / Rules and Regulations
the FAA amends 14 CFR part 39 as (3) Removal of Rotating Parts Used in Utility 202–741–6030, or go to: http://
follows: Operations Other Than Compressor Spools www.archives.gov/federal-register/cfr/ibr-
After the effective date of this AD, remove locations.html.
PART 39—AIRWORTHINESS from service any life-limited rotating part Issued in Burlington, Massachusetts, on
DIRECTIVES used in Utility operations, other than the September 30, 2015.
compressor spools with P/Ns listed in Colleen M. D’Alessandro,
■ 1. The authority citation for part 39 paragraph (e)(2) of this AD, that exceeds its
life limit as re-calculated per paragraph (e)(1) Directorate Manager, Engine & Propeller
continues to read as follows: Directorate, Aircraft Certification Service.
of this AD. Use Tables I, II, III, and IV in
Authority: 49 U.S.C. 106(g), 40113, 44701. paragraphs 3.D. through 3.G. in the [FR Doc. 2015–25719 Filed 10–13–15; 8:45 am]
Accomplishment Instructions in GE CT58 BILLING CODE 4910–13–P
§ 39.13 [Amended] ASB No. SB 72–A0162, Revision 16, dated
January 7, 2015, and paragraph 4.D.,
■ 2. The FAA amends § 39.13 by: Appendix A of this GE CT58 ASB, to DEPARTMENT OF TRANSPORTATION
■ a. Removing airworthiness directives determine when to remove these parts.
(AD) 2001–18–06, Amendment 39– Federal Aviation Administration
(4) Removal of Rotating Parts Not Used in
12432 (66 FR 47575, September 13, Utility Operations Other Than Compressor
2001) (‘‘AD 2001–18–06’’); and AD Spools 14 CFR Part 39
2008–22–16, Amendment 39–15712 (73
After the effective date of this AD, remove [Docket No. FAA–2015–3224; Directorate
FR 63629, October 27, 2008) (‘‘AD from service any life-limited rotating part not Identifier 2015–CE–026–AD; Amendment
2008–22–16’’), and used in Utility operations, other than the 39–18290; AD 2015–20–11]
■ b. Adding the following new AD: compressor spools with P/Ns listed in
paragraph (e)(2) of this AD, that exceeds its RIN 2120–AA64
2015–20–09 General Electric Company:
life limit. Use Tables I, II, III, and IV in
Amendment 39–18288; Docket No. Airworthiness Directives; Schempp-
paragraphs 3.D. through 3.G. in the
FAA–2008–0808; Directorate Identifier
Accomplishment Instructions in GE CT58 Hirth Flugzeugbau GmbH Sailplanes
2008–NE–18–AD.
ASB No. SB 72–A0162, Revision 16, dated
(a) Effective Date January 7, 2015, and paragraph 4.C., AGENCY: Federal Aviation
Appendix A of this GE CT58 ASB, to Administration (FAA), Department of
This AD is effective November 18, 2015.
determine when to remove these parts. Transportation (DOT).
(b) Affected ADs ACTION: Final rule.
(f) Alternative Methods of Compliance
This AD replaces AD 2001–18–06 and AD (AMOCs)
2008–22–16. SUMMARY: We are adopting a new
The Manager, Engine Certification Office, airworthiness directive (AD) for
(c) Applicability FAA, may approve AMOCs for this AD. Use
Schempp-Hirth Flugzeugbau GmbH
This AD applies to all General Electric the procedures found in 14 CFR 39.19 to
make your request. You may email your Models Duo Discus and Duo Discus T
Company (GE) CT58–100–2, CT58–110–1,
request to: ANE-AD-AMOC@faa.gov. powered sailplanes. This AD results
CT58–110–2, CT58–140–1, and CT58–140–2
turboshaft engines. from mandatory continuing
(g) Related Information airworthiness information (MCAI)
(d) Unsafe Condition For more information about this AD, issued by an aviation authority of
This AD was prompted by recalculation of contact Christopher McGuire, Aerospace another country to identify and correct
life for parts installed on engines used in Engineer, Engine Certification Office, FAA, an unsafe condition on an aviation
Utility operations, and a reduced life for Engine & Propeller Directorate, 12 New
product. The MCAI describes the unsafe
compressor spools in all operations. We are England Executive Park, Burlington, MA
01803; phone: 781–238–7120; fax: 781–238– condition as excessive load on the air
issuing this AD to prevent failure of life-
7199; email: chris.mcguire@faa.gov. brake system. We are issuing this AD to
limited rotating parts, uncontained part
release, damage to the engine, and damage to require actions to address the unsafe
(h) Material Incorporated by Reference condition on these products.
the aircraft.
(1) The Director of the Federal Register DATES: This AD is effective November
(e) Compliance approved the incorporation by reference
18, 2015.
Do the actions required by this AD, unless (IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR The Director of the Federal Register
already done. approved the incorporation by reference
part 51.
(1) Calculating Cyclic Life Consumption (2) You must use this service information of a certain publication listed in the AD
Re-calculate the cycles-since-new for all as applicable to do the actions required by as of November 18, 2015.
compressor spools, and for life-limited this AD, unless the AD specifies otherwise. ADDRESSES: You may examine the AD
rotating parts other than compressor spools (i) General Electric Company (GE) CT58 docket on the Internet at http://
used in Utility operations. Use paragraphs Alert Service Bulletin No. SB 72–A0162,
www.regulations.gov by searching for
3.A.(1) and 3.B.(1) in the Accomplishment Revision 16, dated January 7, 2015.
(ii) Reserved. and locating Docket No. FAA–2015–
Instructions of GE CT58 Alert Service
Bulletin (ASB) No. SB 72–A0162, Revision (3) For GE service information identified in 3224; or in person at Document
16, dated January 7, 2015, to perform the this AD, contact General Electric Company, Management Facility, U.S. Department
calculations. GE Aviation, Room 285, One Neumann Way, of Transportation, Docket Operations,
Cincinnati, OH 45215; phone: 513–552–3272; M–30, West Building Ground Floor,
(2) Removal of Compressor Spools email: aviation.fleetsupport@ge.com. Room W12–140, 1200 New Jersey
After the effective date of this AD, remove (4) You may view this service information Avenue SE., Washington, DC 20590.
compressor spools, part numbers (P/Ns) at FAA, Engine & Propeller Directorate, 12 For service information identified in
tkelley on DSK3SPTVN1PROD with RULES
5124T94G02, 6010T57G04, 6010T57G07, and New England Executive Park, Burlington,
this AD, contact Schempp-Hirth
6010T57G08 from service, before reaching MA. For information on the availability of
the life limits specified in paragraph 4.A., this material at the FAA, call 781–238–7125. Flugzeugbau GmbH, Krebenstrasse 25,
Appendix A, in GE CT58 ASB No. SB 72– (5) You may view this service information 73230 Kirchheim/Teck, Germany;
A0162, Revision 16, dated January 7, 2015, at the National Archives and Records telephone: +49 7021 7298–0; fax: +49
as re-calculated per paragraph (e)(1) of this Administration (NARA). For information on 7021 7298–199; email: info@schempp-
AD. the availability of this material at NARA, call hirth.com; Internet: http://
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![61724 Federal Register / Vol. 80, No. 198 / Wednesday, October 14, 2015 / Rules and Regulations
(4) Will not have a significant country to identify and correct an unsafe Technical Note No. 380–2/396–17/868–22/
economic impact, positive or negative, condition on an aviation product. The MCAI 890–14, Ausgabe (English translation: issue)
on a substantial number of small entities describes the unsafe condition as excessive 1, Datum (English translation: dated) May 11,
load on the air brake system. We are issuing 2015.
under the criteria of the Regulatory
this AD to prevent uncontrolled actuation of (ii) For replacement of the airbrake drive
Flexibility Act. the air brakes (symmetric or asymmetric), funnels, follow Picture 5: Airbrake drive
Examining the AD Docket which could result in reduced control. funnel in fuselage, ‘‘Reinforcement of
(f) Actions and Compliance airbrake drive funnel according to drawing
You may examine the AD docket on S14RB703, Revision a,’’ in Schempp-Hirth
the Internet at http:// Unless already done, do the actions in Flugzeugbau GmbH Working instruction for
www.regulations.gov by searching for paragraph (f)(1) through (f)(5) of this AD. Technical Note No. 380–2/396–17/868–22/
and locating Docket No. FAA–2015– (1) Within 40 days after November 17, 2015
890–14, Ausgabe (English translation: issue)
3224; or in person at the Docket (the effective date of this AD) and repetitively
1, Datum (English translation: dated) May 11,
thereafter at intervals not to exceed 100 hours
Management Facility between 9 a.m. 2015.
time-in-service until the terminating
and 5 p.m., Monday through Friday, replacement action required in paragraphs
(4) If the airbrake control system is found
except Federal holidays. The AD docket to not have proper clearance during the
(f)(2) and (f)(3) of this AD (as applicable) is
contains the NPRM, the regulatory done, inspect the airbrake bell crank, the inspection required in paragraph (f)(1) of this
evaluation, any comments received, and airbrake drive funnels, and the airbrake AD, before further flight, make all necessary
other information. The street address for control system. corrective adjustments following Paragraph
(i) Inspect the airbrake bell crank and the 2.d. of Schempp-Hirth Flugzeugbau GmbH
the Docket Office (telephone (800) 647–
airbrake drive funnels for cracks and damage Working instruction for Technical Note No.
5527) is in the ADDRESSES section. 380–2/396–17/868–22/890–14, Ausgabe
Comments will be available in the AD following Action 1 in Schempp-Hirth
Flugzeugbau GmbH Technical Note No. 380– (English translation: issue) 1, Datum (English
docket shortly after receipt. translation: dated) May 11, 2015.
2/396–17/868–22/890–14, Revision 1, issued
List of Subjects in 14 CFR Part 39 July 13, 2015 (published as a single (5) As of November 17, 2015 (the effective
document). date of this AD), only install an airbrake bell
Air transportation, Aircraft, Aviation (ii) Inspect the airbrake control system for crank or an airbrake drive funnel that
safety, Incorporation by reference, proper clearance following Paragraph 2.d. of corresponds to Picture 2: Reinforced version
Safety. Schempp-Hirth Flugzeugbau GmbH Working of airbrake bell crank according to HS 11–
instruction for Technical Note No. 380–2/ 50.016, Revision a or later, and Picture 5:
Adoption of the Amendment Airbrake drive funnel in fuselage,
396–17/868–22/890–14, Ausgabe (English
Accordingly, under the authority translation: issue) 1, Datum (English ‘‘Reinforcement of airbrake drive funnel
delegated to me by the Administrator, translation: dated) May 11, 2015. according to drawing S14RB703, Revision a,’’
the FAA amends 14 CFR part 39 as (2) If cracks or damage is found on the in Schempp-Hirth Flugzeugbau GmbH
airbrake bell cranks or the airbrake drive Working instruction for Technical Note No.
follows:
funnels during any inspection required in 380–2/396–17/868–22/890–14, Ausgabe
PART 39—AIRWORTHINESS paragraph (f)(1) of this AD, before further (English translation: issue) 1, Datum (English
flight, replace each cracked or damaged part translation: dated) May 11, 2015, as
DIRECTIVES applicable.
with a reinforced part. Installing a reinforced
■ 1. The authority citation for part 39 part terminates the repetitive inspections (g) Other FAA AD Provisions
continues to read as follows: required in paragraph (f)(1) of this AD for
that part. The following provisions also apply to this
Authority: 49 U.S.C. 106(g), 40113, 44701. (i) For replacement of the airbrake bell AD:
cranks, follow Picture 2: Reinforced version (1) Alternative Methods of Compliance
§ 39.13 [Amended] of airbrake bell crank according to HS 11– (AMOCs): The Manager, Standards Office,
■ 2. The FAA amends § 39.13 by adding 50.016, Revision a or later, in Schempp-Hirth FAA, has the authority to approve AMOCs
the following new AD: Flugzeugbau GmbH Working instruction for for this AD, if requested using the procedures
Technical Note No. 380–2/396–17/868–22/ found in 14 CFR 39.19. Send information to
2015–20–11 Schempp-Hirth Flugzeugbau 890–14, Ausgabe (English translation: issue) ATTN: Jim Rutherford, Aerospace Engineer,
GmbH: Amendment 39–18290; Docket 1, Datum (English translation: dated) May 11, FAA, Small Airplane Directorate, 901 Locust,
No. FAA–2015–3224; Directorate 2015. Room 301, Kansas City, Missouri 64106;
Identifier 2015–CE–026–AD. (ii) For replacement of the airbrake drive telephone: (816) 329–4165; fax: (816) 329–
(a) Effective Date funnels, follow Picture 5: Airbrake drive 4090; email: jim.rutherford@faa.gov. Before
funnel in fuselage ‘‘Reinforcement of airbrake using any approved AMOC on any sailplane
This airworthiness directive (AD) becomes to which the AMOC applies, notify your
drive funnel according to drawing S14RB703,
effective November 18, 2015.
Revision a, in Schempp-Hirth Flugzeugbau appropriate principal inspector (PI) in the
(b) Affected ADs GmbH Working instruction for Technical FAA Flight Standards District Office (FSDO),
None. Note No. 380–2/396–17/868–22/890–14, or lacking a PI, your local FSDO.
Ausgabe (English translation: issue) 1, Datum (2) Airworthy Product: For any requirement
(c) Applicability (English translation: dated) May 11, 2015. in this AD to obtain corrective actions from
This AD applies to Schempp-Hirth (3) If no cracks or damage were found on a manufacturer or other source, use these
Flugzeugbau GmbH Model Duo Discus the airbrake bell cranks or the airbrake drive actions if they are FAA-approved. Corrective
powered sailplanes, serial numbers 1 through funnels during any inspection required in actions are considered FAA-approved if they
639, and Model Duo Discus T powered paragraph (f)(1) of this AD, within 12 months are approved by the State of Design Authority
sailplanes, serial numbers 1 through 110 and after November 17, 2015 (the effective date of (or their delegated agent). You are required
112 through 247, certificated in any category. this AD), replace each of the airbrake bell to assure the product is airworthy before it
cranks and airbrake drive funnels with a is returned to service.
(d) Subject reinforced part. These replacements
(h) Related Information
tkelley on DSK3SPTVN1PROD with RULES
Air Transport Association of America terminate the repetitive inspections required
(ATA) Code 27: Flight Controls. in paragraph (f)(1) of this AD. Refer to MCAI European Aviation Safety
(i) For replacement of the airbrake bell Agency (EASA) AD No. 2015–0139R1, dated
(e) Reason cranks, follow Picture 2: Reinforced version July 15, 2015, for related information. You
This AD was prompted by mandatory of airbrake bell crank according to HS 11– may examine the MCAI on the Internet at
continuing airworthiness information (MCAI) 50.016, Revision a or later, in Schempp-Hirth http://www.regulations.gov/
originated by an aviation authority of another Flugzeugbau GmbH Working instruction for #!documentDetail;D=FAA-2015-3224-0002.
VerDate Sep<11>2014 16:10 Oct 13, 2015 Jkt 238001 PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 E:\FR\FM\14OCR1.SGM 14OCR1](https://thefederalregister.org/doc/80_FR_61920/page/3.svg)
![Federal Register / Vol. 80, No. 198 / Wednesday, October 14, 2015 / Rules and Regulations 61725
(i) Material Incorporated by Reference Piper Aircraft, Inc. Models PA–28–161, the Docket Office (phone: 800–647–
(1) The Director of the Federal Register PA–28–181, and PA–28R–201 airplanes. 5527) is in the ADDRESSES section.
approved the incorporation by reference This AD requires inspecting the right Comments will be available in the AD
(IBR) of the service information listed in this wing rib at wing station 140.09 for docket shortly after receipt.
paragraph under 5 U.S.C. 552(a) and 1 CFR cracks and taking necessary corrective FOR FURTHER INFORMATION CONTACT:
part 51. action. This AD was prompted by a Gregory ‘‘Keith’’ Noles, Aerospace
(2) You must use this service information report of cracks found in the wing rib
as applicable to do the actions required by Engineer, FAA, Atlanta Aircraft
this AD, unless the AD specifies otherwise.
bead radius that were formed during Certification Office, 1701 Columbia
(i) Schempp-Hirth Flugzeugbau GmbH production. We are issuing this AD to Avenue, College Park, Georgia 30337;
Technical Note No. 380–2/396–17/868–22/ correct the unsafe condition on these phone: (404) 474–5551; fax: (404) 474–
890–14, Revision 1, issued July 13, 2015 products. 5606; email: gregory.noles@faa.gov.
(published as a single document). DATES: This AD is effective October 29, SUPPLEMENTARY INFORMATION:
(ii) Schempp-Hirth Flugzeugbau GmbH
Working instruction for Technical Note No.
2015. Discussion
380–2/396–17/868–22/890–14, Ausgabe The Director of the Federal Register
approved the incorporation by reference We received a report from Piper
(English translation: issue) 1, Datum (English
of a certain publication listed in this AD Aircraft, Inc. of a production quality
translation: dated) May 11, 2015.
(3) For Schempp-Hirth Flugzeugbau GmbH as of October 29, 2015. control problem on certain Models PA–
service information identified in this AD, We must receive comments on this 28–161, PA–28–181, and PA–28R–201
contact Schempp-Hirth Flugzeugbau GmbH, AD by November 30, 2015. airplanes. A change in production
Krebenstrasse 25, 73230 Kirchheim/Teck, ADDRESSES: You may send comments,
tooling and processes caused cracks to
Germany; telephone: +49 7021 7298–0; fax:
using the procedures found in 14 CFR form along the edge of rib stiffening
+49 7021 7298–199; email: info@schempp- beads during manufacture. These cracks
hirth.com; Internet: http://www.schempp- 11.43 and 11.45, by any of the following
methods: cause reduced structural integrity of the
hirth.com. wing, which results in the inability of
(4) You may view this service information • Federal eRulemaking Portal: Go to
http://www.regulations.gov. Follow the the wing rib to carry ultimate load.
at the FAA, Small Airplane Directorate, 901
This condition, if not corrected, could
Locust, Kansas City, Missouri 64106. For instructions for submitting comments.
result in reduced structural integrity of
information on the availability of this • Fax: 202–493–2251.
material at the FAA, call (816) 329–4148. In • Mail: U.S. Department of the wing with consequent loss of
addition, you can access this service Transportation, Docket Operations, M– control. We are issuing this AD to
information on the Internet at http:// 30, West Building Ground Floor, Room correct the unsafe condition on these
www.regulations.gov by searching for and
W12–140, 1200 New Jersey Avenue SE., products.
locating Docket No. FAA–2015–3224.
(5) You may view this service information Washington, DC 20590. Related Service Information Under 1
that is incorporated by reference at the • Hand Delivery: U.S. Department of CFR Part 51
National Archives and Records Transportation, Docket Operations, M– We reviewed Piper Aircraft, Inc.
Administration (NARA). For information on 30, West Building Ground Floor, Room Service Bulletin No. 1279, dated August
the availability of this material at NARA, call W12–140, 1200 New Jersey Avenue SE., 26, 2015. The service bulletin describes
202–741–6030, or go to: http:// Washington, DC 20590, between 9 a.m.
www.archives.gov/federal-register/cfr/ibr- procedures for inspecting the right wing
and 5 p.m., Monday through Friday, rib at wing station 140.09 for cracks and
locations.html. except Federal holidays.
Issued in Kansas City, Missouri, on for obtaining an FAA-approved repair if
For service information identified in cracks are found. This service
October 1, 2015. this AD, contact Piper Aircraft, Inc.,
Melvin Johnson, information is reasonably available
Customer Service, 2926 Piper Drive, because the interested parties have
Acting Manager, Small Airplane Directorate, Vero Beach, Florida 32960; telephone:
Aircraft Certification Service. access to it through their normal course
(877) 879–0275; fax: none; email: of business or by the means identified
[FR Doc. 2015–25710 Filed 10–13–15; 8:45 am] customer.service@piper.com; Internet: in the ADDRESSES section of this AD.
BILLING CODE 4910–13–P www.piper.com. You may review the
referenced service information at the FAA’s Determination
FAA, Small Airplane Directorate, 901 We are issuing this AD because we
DEPARTMENT OF TRANSPORTATION Locust, Kansas City, Missouri 64106. evaluated all the relevant information
For information on the availability of and determined the unsafe condition
Federal Aviation Administration this material at the FAA, call (816) 329– described previously is likely to exist or
4148. It is also available on the Internet develop in other products of the same
14 CFR Part 39 at http://www.regulations.gov by type design.
[Docket No. FAA–2015–4085; Directorate searching for locating Docket No. FAA–
Identifier 2015–CE–033–AD; Amendment 2015–4085. AD Requirements
39–18292; AD 2015–20–13]
Examining the AD Docket This AD requires accomplishing the
actions specified in the service
RIN 2120–AA64 You may examine the AD docket on information described previously.
the Internet at http://
Airworthiness Directives; Piper FAA’s Justification and Determination
www.regulations.gov by searching for
Aircraft, Inc. Airplanes of the Effective Date
and locating Docket No. FAA–2015–
AGENCY: Federal Aviation 4085; or in person at the Docket An unsafe condition exists that
tkelley on DSK3SPTVN1PROD with RULES
Administration (FAA), DOT. Management Facility between 9 a.m. requires the immediate adoption of this
ACTION: Final rule; request for and 5 p.m., Monday through Friday, AD. The FAA has found that the risk to
comments. except Federal holidays. The AD docket the flying public justifies waiving notice
contains this AD, the regulatory and comment prior to adoption of this
SUMMARY: We are adopting a new evaluation, any comments received, and rule because cracks in the wing rib, if
airworthiness directive (AD) for certain other information. The street address for not detected and corrected immediately,
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Document Created: 2018-02-27 08:50:36
Document Modified: 2018-02-27 08:50:36
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Rules and Regulations | |
| Action | Final rule. | |
| Dates | This AD is effective November 18, 2015. | |
| 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: [email protected] | |
| FR Citation | 80 FR 61722 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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