Airworthiness Directives; Piper Aircraft, Inc. Airplanes, 31892-31899 [2017-14375]

Download as PDF 31892 Federal Register / Vol. 82, No. 131 / Tuesday, July 11, 2017 / Rules and Regulations or she believes to be confidential and exempt by law from public disclosure should submit via email, postal mail, or hand delivery two well-marked copies: One copy of the document marked confidential including all the information believed to be confidential, and one copy of the document marked non-confidential with the information believed to be confidential deleted. Submit these documents via email or on a CD, if feasible. DOE will make its own determination about the confidential status of the information and treat it according to its determination. Factors of interest to DOE when evaluating requests to treat submitted information as confidential include: (1) A description of the items; (2) whether and why such items are customarily treated as confidential within the industry; (3) whether the information is generally known by or available from other sources; (4) whether the information has previously been made available to others without obligation concerning its confidentiality; (5) an explanation of the competitive injury to the submitting person which would result from public disclosure; (6) when such information might lose its confidential character due to the passage of time; and (7) why disclosure of the information would be contrary to the public interest. See 10 CFR 429.7. It is DOE’s policy that all comments be included in the public docket, without change and as received, including any personal information provided in the comments (except information deemed to be exempt from public disclosure). III. Approval of the Office of the Secretary The Secretary of Energy has approved publication of this request for information. Issued in Washington, DC, on June 30, 2017. Steven Chalk, Acting Assistant Secretary Energy Efficiency and Renewable Energy. [FR Doc. 2017–14472 Filed 7–10–17; 8:45 am] mstockstill on DSK30JT082PROD with RULES BILLING CODE 6450–01–P VerDate Sep<11>2014 16:47 Jul 10, 2017 Jkt 241001 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–9254; Directorate Identifier 2015–CE–030–AD; Amendment 39–18948; AD 2017–14–04] RIN 2120–AA64 Airworthiness Directives; Piper Aircraft, Inc. Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are superseding Airworthiness Directive (AD) 95–26–13 for certain Piper Aircraft, Inc. Models PA–28–140, PA–28–150, PA–28–151, PA–28–161, PA–28–160, PA–28–180, PA–28–181, PA–28–235, PA–28–236, PA–28R–180, PA–28R–200, PA–28R– 201, PA–28S–160, PA–28S–180, PA– 32–260, PA–32–300, PA–32–301, PA– 32–301T, PA–32R–300, PA–32R–301 (SP), PA–32R–301 (HP), PA–32R–301T, PA–32RT–300, PA–32RT–300T, and PA–32S–300 airplanes equipped with oil cooler hose assemblies that do not meet certain technical standard order (TSO) requirements. AD 95–26–13 required inspections, replacement, and adjustment of the oil cooler hose assemblies, as well as providing for a terminating action. This AD retains all of the requirements of AD 95–26–13 and adds language to clarify those requirements. This AD was prompted by several inquiries asking for clarification of the AD’s applicability and compliance requirements. We are issuing this AD to correct the unsafe condition on these products. DATES: This AD is effective August 15, 2017. 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–2016– 9254; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (phone: 800–647–5527) is Document Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Gary Wechsler, Aerospace Engineer, FAA, PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 Atlanta Aircraft Certification Office, 1701 Columbia Avenue, College Park, Georgia 30337; telephone: (404) 474– 5575; fax: (404) 474–5606; email: gary.wechsler@faa.gov. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 95–26–13, Amendment 39–9472 (60 FR 67321, December 29, 1995) (‘‘AD 95–26–13’’). AD 95–26–13 applied to certain Piper Aircraft, Inc. Models PA–28–140, PA– 28–150, PA–28–151, PA–28–161, PA– 28–160, PA–28–180, PA–28–181, PA– 28–235, PA–28–236, PA–28R–180, PA– 28R–200, PA–28R–201, PA–28S–160, PA–28S–180, PA–32–260, PA–32–300, PA–32–301, PA–32–301T, PA–32R–300, PA–32R–301 (SP), PA–32R–301 (HP), PA–32R–301T, PA–32RT–300, PA– 32RT–300T, and PA–32S–300 airplanes equipped with oil cooler hose assemblies that do not meet technical standard order C53a (TSO–C53a) Type D requirements. The NPRM published in the Federal Register on October 21, 2016 (81 FR 72742). The NPRM was prompted by several inquiries asking for clarification of the AD’s applicability and compliance requirements. The NPRM proposed to retain all of the requirements of AD 95–26–13 and add language to clarify those requirements. We are issuing this AD to correct the unsafe condition on these products. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM and the FAA’s response to each comment. Request the Unsafe Condition Be Addressed by Department of Commerce G. Fenton requested this unsafe condition be addressed through the Department of Commerce instead of the Federal Aviation Administration because the NPRM applied to airplanes used for commercial purposes. We disagree with this comment because the Federal Aviation Administration is charged by Congress to provide for the safe and efficient use of national airspace by commercial and private airplane operators. We have not changed the AD based on this comment. Request To Change Labor Rate in Cost of Compliance G. Fenton requested we change the labor rate in the Cost of Compliance section to $72.50 per hour instead of $85 per hour. He thought the increased E:\FR\FM\11JYR1.SGM 11JYR1 Federal Register / Vol. 82, No. 131 / Tuesday, July 11, 2017 / Rules and Regulations cost from $60 per hour from the 1995 AD to $85 per hour for this AD is unnecessary. He thought we should adjust the cost of the labor rate to a value between the two. We disagree with this comment. The rate of $85 per hour is provided by the FAA Office of Aviation Policy and Plans for us to use when estimating the labor costs of complying with AD requirements. We have not changed the AD based on this comment. Request We Compile Changes From the Previous AD Into One Location Jonathan Hartley requested we put all of the changes to this AD from AD 95– 26–13 in a conspicuous location to reduce confusion and workload associated with compliance. We partially agree with this comment. We agree there are instances where compliance confusion and workload could exist with the wording in the NPRM. However, we disagree with compiling the changes into one location because of formatting constraints in the AD structure. We have made language changes to the regulatory text in the AD to clarify the compliance confusion and to reduce workload. Request We Include an Outline for Maintaining Other Types of Oil Cooler Hoses Jonathan Hartley requested we include in this AD an outline maintaining specific requirements for other types of oil cooler hoses. 31893 We disagree with this comment. The unsafe condition addressed by this AD applies only to Type C and Type D oil cooler hoses. The requirements for maintaining other types of oil cooler hoses are not required to comply with the actions of this AD. We have not changed the AD based on this comment. hose assembly being terminating action for the AD. We agree with this comment. The installation of the Type D oil cooler hose assembly terminates the requirement for the installation inspection. We have changed the language in the AD to address the contradiction. Request We Include Additional Information Describing the Types of Hoses Conclusion George Ballard requested we include in the AD information explaining what constitutes a Type C and Type D hose assembly. He doesn’t think the TSO adequately explains the difference between the Type C and Type D hose assemblies. We disagree with this comment. The differences between the Type C and Type D hoses are provided in great detail in TSO–C53a and its referenced documents. This AD does not require that level of detail to comply with the inspections or corrective actions specified in the AD. We have not changed the AD based on this comment. Request We Clarify Terminating Action for Installation of Type D Hose Assemblies Greg Dodson stated the requirement to inspect the oil cooler hose assembly installation for an oil cooler mounted in a location other than at or aft of the rear of the engine any time the oil cooler hose assembly is replaced conflicts with the installation of a Type D oil cooler We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this AD with the changes described previously and minor editorial changes. We have determined that these minor changes: • Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM. We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. Costs of Compliance We estimate that this AD affects 23,643 airplanes of U.S. registry. This AD retains the same actions as AD 95–26–13 and the costs do not add any cost burden than that already in effect by AD 95–26–13. The difference in the Costs of Compliance with this AD and AD 95–26–13 is that we use $85 an hour as a labor rate in 2016 as opposed to $60 per hour in 1995. We estimate the following costs to comply with this AD: ESTIMATED COSTS Labor cost Inspection of the oil cooler hose assembly. Inspection of the clearance between the oil cooler hose assembly and the front exhaust stacks. Replacement of the oil cooler hose assembly. 1 work-hour × $85 per hour = $85 ...... Not applicable $85 .5 work-hour × $85 per hour = 42.50 .. Not applicable $42.50 1 work-hour × $85 per hour = $85 ...... $430 ................ mstockstill on DSK30JT082PROD with RULES Note: The estimated cost of the inspection of the clearance between the oil cooler hose assembly and the front exhaust stacks is for all airplanes affected by this AD; however, the inspection applies only to airplanes with the oil cooler mounted in a location other VerDate Sep<11>2014 16:47 Jul 10, 2017 Jkt 241001 Parts cost Cost per product Action than at or aft of the rear of the engine. We have no way of knowing how many affected airplanes have that particular installation. We estimate the following costs to do any necessary adjustments that would PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 $515 Cost on U.S. operators $2,009,655. $1,004,827.50 See note 1 to Cost of Compliance. $12,176,145. be required based on the results of the inspection. We have no way of determining the number of aircraft that might need these adjustments: E:\FR\FM\11JYR1.SGM 11JYR1 31894 Federal Register / Vol. 82, No. 131 / Tuesday, July 11, 2017 / Rules and Regulations ON-CONDITION COSTS Action Labor cost Parts cost Adjustment of the clearance between the oil cooler hose assembly and the front exhaust stacks. 1 work-hour × $85 per hour = $85 .......... Not applicable .......................................... 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. mstockstill on DSK30JT082PROD with RULES Regulatory Findings We have 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 that this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Is not a ‘‘significant rule’’ under 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, VerDate Sep<11>2014 16:47 Jul 10, 2017 Jkt 241001 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. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. [Amended] 2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 95–26–13, Amendment 39–9472 (60 FR 67321, December 29, 1995), and adding the following new AD: ■ 2017–14–04 Piper Aircraft, Inc.: Amendment 39–18948; Docket No. FAA–2016–9254; Directorate Identifier 2015–CE–030–AD. (a) Effective Date This AD is effective August 15, 2017. (b) Affected ADs This AD replaces AD 95–26–13, Amendment 39–9472 (60 FR 67321, December 29, 1995) (‘‘AD 95–26–13’’). (c) Applicability This AD applies to Piper Aircraft, Inc. Models PA–28–140, PA–28–150, PA–28–151, PA–28–161, PA–28–160, PA–28–180, PA– 28–181, PA–28–235, PA–28–236, PA–28R– 180, PA–28R–200, PA–28R–201, PA–28S– 160, PA–28S–180, PA–32–260, PA–32–300, PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 $85 PA–32–301, PA–32–301T, PA–32R–300, PA– 32R–301 (SP), PA–32R–301 (HP), PA–32R– 301T, PA–32RT–300, PA–32RT–300T, and PA–32S–300 airplanes, all serial numbers, that are: (1) Equipped with one or more oil cooler hose assemblies that do not meet technical standard order C53a (TSO–C53a), Type D requirements; and (2) Certificated in any category. (d) Subject Joint Aircraft System Component (JASC)/ Air Transport Association (ATA) of America Code 79, Engine Oil. (e) Unsafe Condition PART 39—AIRWORTHINESS DIRECTIVES § 39.13 Cost per product AD 95–26–13 was prompted by numerous incidents/accidents caused by rupture or failure of the oil cooler hose assemblies. This AD action was prompted by requests to clarify the intent of AD 95–26–13. We are issuing this AD to prevent rupture or failure of the oil cooler hose assemblies, which could result in engine stoppage with consequent loss of control. (f) Compliance Comply with this AD within the compliance times specified, unless already done. You may review the flow chart found in appendix 1 to assist you in complying with the actions of this AD. (g) Inspection Procedures for an Oil Cooler Mounted AT or AFT of the Rear of the Engine For any oil cooler hose assemblies that do not meet TSO–C53a, Type D requirements: Within the next 100 hours time-in-service (TIS) after February 5, 1996 (the effective date retained from AD 95–26–13), and repetitively thereafter at intervals not to exceed 100 hours TIS, inspect the fire sleeve of each oil cooler hose assembly for soaked oil, a brownish or whitish color, and any evidence of brittleness or deterioration as a result of heat or oil seepage. See figure 1 to paragraphs (g) and (h) of this AD for additional information. E:\FR\FM\11JYR1.SGM 11JYR1 Federal Register / Vol. 82, No. 131 / Tuesday, July 11, 2017 / Rules and Regulations mstockstill on DSK30JT082PROD with RULES (h) Inspection Procedures for an Oil Cooler Mounted in a Location Other Than AT or AFT of the Rear of the Engine (1) For any oil cooler hose assemblies that do not meet TSO–C53a, Type D requirements: Within the next 100 hours TIS VerDate Sep<11>2014 16:47 Jul 10, 2017 Jkt 241001 after February 5, 1996 (the effective date retained from AD 95–26–13), and repetitively thereafter at intervals not to exceed 100 hours TIS, inspect the fire sleeve of each oil cooler hose assembly for soaked oil, a brownish or whitish color, and any evidence of brittleness or deterioration as a result of heat or oil seepage. See figure 1 to paragraphs (g) and (h) of this AD for additional information. (2) For any oil cooler hose assemblies that do not meet TSO–C53a, Type D requirements: Within the next 100 hours TIS after February 5, 1996 (the effective date retained from AD 95–26–13) and repetitively thereafter at intervals not to exceed 100 hours TIS, inspect the oil cooler hose assemblies to ensure the installation conditions in paragraphs (h)(2)(i) through (iii) of this AD are met. See figure 1 to paragraphs (g) and PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 (h) of this AD for additional information. If the conditions listed in paragraphs (h)(2)(i) through (iii) of this AD are not met, before further flight, make any necessary adjustments. See figure 2 to paragraph (h)(2) of this AD for additional information. (i) The oil cooler hose assemblies pass underneath and behind the electrical ground cable and in front of the lower of the two engine mounts. (ii) The oil cooler hose assemblies are secured to the engine mount strut and a clearance of at least 2 inches exists between the oil cooler hose assemblies and the exhaust stack. (iii) Oil cooler hose assemblies with a minimum outer diameter of 0.75 inch are installed with a bend radius of at least 6.5 inches. E:\FR\FM\11JYR1.SGM 11JYR1 ER11JY17.016</GPH> Note 1 to paragraphs (g) and (h)(1) of this AD: Although not required by this AD, the FAA recommends that an oil cooler hose assembly flexibility test be done at 100-hour TIS intervals by gently lifting each oil cooler hose assembly in several places along its bottom surface, ideally at the center of an arc. If the oil cooler hose assembly moves slightly, either from side-to-side or upward, then some flexibility remains. If the oil cooler hose assembly appears hardened or inflexible, replacement is recommended. 31895 Federal Register / Vol. 82, No. 131 / Tuesday, July 11, 2017 / Rules and Regulations mstockstill on DSK30JT082PROD with RULES (i) Corrective Actions (1) If any of the conditions described in paragraph (g) or (h)(1) of this AD are found on an oil cooler hose assembly during the inspection required in paragraph (g) or (h)(1) of this AD, as applicable, before further flight, replace the oil cooler hose assembly with a serviceable new or used TSO–C53a Type D oil cooler hose assembly or TSO– C53a Type C oil cooler hose assembly. If a used TSO–C53a Type C oil cooler hose assembly is installed, it must have documented hours TIS. Note 2 to paragraphs (i)(1) and (j) of this AD: If only one of the two oil cooler hose assemblies requires replacement, the FAA recommends replacing both of the oil cooler hose assemblies to simplify tracking the hours TIS of the assemblies. (2) If a newly installed oil cooler hose assembly is a TSO–C53a Type C oil cooler hose assembly and it is mounted in a location other than at or aft of the rear of the engine, then replacement of the oil cooler hose assembly must meet the conditions listed in paragraphs (h)(2)(i) through (iii) of this AD. VerDate Sep<11>2014 16:47 Jul 10, 2017 Jkt 241001 (3) If compliance with paragraphs (i)(1) and (i)(2) of this AD results in both oil cooler hose assemblies of an airplane meeting TSO– C53a Type D requirements, then the requirements of this AD are terminated for the airplane. (j) Life Limit of TSO–C53a Type C Oil Cooler Hose Assemblies (1) When a TSO–C53a Type C oil cooler hose assembly accumulates 8 years or 1,000 hours TIS, whichever occurs first, replace the oil cooler hose assembly with a serviceable new or used TSO–C53a Type D oil cooler hose assembly or TSO–C53a Type C oil cooler hose assembly. If a used TSO–C53a Type C oil cooler hose assembly is installed, it must have documented hours TIS. If the newly installed oil cooler is a TSO–C53a Type C oil cooler hose assembly and it is mounted in a location other than at or aft of the rear of the engine the installation must meet the conditions listed in paragraphs (h)(2)(i) through (iii) of this AD. (2) You may at any time before a TSO– C53a Type C oil cooler hose assembly exceeds the life limit in paragraph (j)(1) of PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 this AD, replace a TSO–C53a Type C oil cooler hose assembly with a TSO–C53a Type D oil cooler hose assembly. (3) If compliance with paragraphs (j)(1) or (j)(2) of this AD results in both oil cooler hose assemblies of an airplane meeting TSO–C53a Type D requirements, then the requirements of this AD are terminated for the airplane. (k) Alternative Methods of Compliance (AMOCs) (1) The Manager, Atlanta Aircraft Certification Office (ACO), 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 manager of the ACO, send it to the attention of the person identified in paragraph (k) of this AD. (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. E:\FR\FM\11JYR1.SGM 11JYR1 ER11JY17.001</GPH> 31896 Federal Register / Vol. 82, No. 131 / Tuesday, July 11, 2017 / Rules and Regulations mstockstill on DSK30JT082PROD with RULES (3) AMOCs approved for AD 95–26–13 (60 FR 67321, December 29, 1995) are not approved as AMOCs for the corresponding provisions of this AD. VerDate Sep<11>2014 16:47 Jul 10, 2017 Jkt 241001 (l) Related Information For more information about this AD, contact Gary Wechsler, Aerospace Engineer, FAA, Atlanta Aircraft Certification Office, PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 31897 1701 Columbia Avenue, College Park, Georgia 30337; telephone: (404) 474–5575; fax: (404) 474–5606; email: gary.wechsler@ faa.gov. BILLING CODE 4910–13–P E:\FR\FM\11JYR1.SGM 11JYR1 31898 Federal Register / Vol. 82, No. 131 / Tuesday, July 11, 2017 / Rules and Regulations Appendix 1 to AD 201 7-14-04 ( Start ) AD paragraph references are noted with () PA-28 & PA-32 airplanes of (c) equipped with one or more oil cooler hose that are not TSO-CS3a, Type D compliant per (c)(l) No End Yes Inspect each non- Yes , - - - - - - - - - . 1 compliant hose per (c)(l) ~---< for condition within 100 hrs TIS per (g) Good Oil Cooler Mounted at or Aft of the rear of the Engine per Figure 1? No Inspect each non>---.! compliant hose per (c)(l) ~------, for condition within 100 hrs TIS per (h)(1) Bad Bad Good Inspection good or bad? No Will the hose reach 8 yrs TIS or accumulate 1000 TIS before the next 100 hrs TIS? Yes Replace hose with Type Cor TypeD hose per (i)(l) Type C TypeD Two Yes TypeD hoses in airplane Terminate AD Yes Two No Type D hoses > - - - - - - - - - - - - - - - - " in airplane End VerDate Sep<11>2014 16:47 Jul 10, 2017 Jkt 241001 PO 00000 Frm 00012 Fmt 4700 Sfmt 4725 E:\FR\FM\11JYR1.SGM 11JYR1 ER11JY17.018</GPH> mstockstill on DSK30JT082PROD with RULES No Federal Register / Vol. 82, No. 131 / Tuesday, July 11, 2017 / Rules and Regulations Issued in Kansas City, Missouri, on June 29, 2017. Pat Mullen, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017–14375 Filed 7–10–17; 8:45 am] BILLING CODE 4910–13–C DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2017–0060; Directorate Identifier 2016–SW–090–AD; Amendment 39–18949; AD 2017–14–05] RIN 2120–AA64 Airworthiness Directives; Airbus Helicopters Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. AGENCY: We are adopting a new airworthiness directive (AD) for Airbus Helicopters Model SA330J helicopters. This AD requires replacing certain hydraulic pumps and is prompted by reports of broken screws that attach the cover of the hydraulic pump. The actions of this AD are intended to prevent an unsafe condition on these products. SUMMARY: This AD becomes effective July 26, 2017. We must receive comments on this AD by September 11, 2017. 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. DATES: mstockstill on DSK30JT082PROD with RULES 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– 0060; or in person at the Docket Operations Office between 9 a.m. and 5 p.m., Monday through Friday, except VerDate Sep<11>2014 16:47 Jul 10, 2017 Jkt 241001 Federal holidays. The AD docket contains this 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 final 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 https:// www.airbushelicopters.com/techpub/ FO/scripts/myFO_login.php. You may review the referenced service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy, Room 6N–321, Fort Worth, TX 76177. FOR FURTHER INFORMATION CONTACT: Matt Fuller, Senior Aviation Safety Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 10101 Hillwood Pkwy, Fort Worth, TX 76177; telephone (817) 222–5110; email matthew.fuller@ faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited This AD is a final rule that involves requirements affecting flight safety, and we did not provide you with notice and an opportunity to provide your comments prior to it becoming effective. However, we invite you to participate in this rulemaking by submitting written comments, data, or views. We also invite comments relating to the economic, environmental, energy, or federalism impacts that resulted from adopting this AD. The most helpful comments reference a specific portion of the AD, explain the reason for any recommended change, and include supporting data. To ensure the docket does not contain duplicate comments, commenters should send only one copy of written comments, or if comments are filed electronically, commenters should submit them only one time. We will file in the docket all comments that we receive, as well as a report summarizing each substantive public contact with FAA personnel concerning this rulemaking during the comment period. We will consider all the comments we receive and may conduct additional rulemaking based on those comments. Discussion EASA, which is the Technical Agent for the Member States of the European Union, has issued EASA Emergency AD No. 2016–264–E, dated December 22, PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 31899 2016, to correct an unsafe condition for Airbus Helicopters Model SA330J helicopters. EASA advises of reports of broken screws that attach the cover of the hydraulic pump. A subsequent investigation identified a batch of screws delivered between July 1, 2015, and November 1, 2016, that have intrinsic embrittlement and reduced mechanical properties. Hydrogen was introduced into this batch of screws during production, causing the screws to become brittle and lack sufficient strength. These screws were installed in a batch of hydraulic pumps, part number (P/N) FR65WEO2005–175A, identified by certain serial numbers, EASA advises. This condition, if not detected and corrected, could lead to the failure of a cover bolt and loss of fluid from the hydraulic pump, resulting in loss of the hydraulic system and subsequent loss of helicopter control. As a result, EASA AD No. 2016–264–E requires replacing the hydraulic pumps. FAA’s Determination These helicopters have been approved by the aviation authority of France and are approved for operation in the United States. Pursuant to our bilateral agreement with France, EASA, its technical representative, has notified us of the unsafe condition described in the EASA AD. We are issuing this AD because we evaluated all information provided by EASA and determined the unsafe condition exists and is likely to exist or develop on other helicopters of these same type designs. Related Service Information We reviewed Airbus Helicopters Emergency Alert Service Bulletin No. SA330–29.12, Revision 0, dated December 22, 2016 (Airbus EASB), for Model SA330J helicopters and military model SA330L, SA330Jm, SA330S1, and SA330Sm helicopters. The Airbus EASB specifies removing Nexter Mechanics hydraulic pumps P/N FR65WEO2005–175A with certain serial numbers. If both the right-hand (RH) and left-hand (LH) hydraulic pumps have an affected P/N and serial number, the Airbus EASB specifies replacing the RH hydraulic pump before further flight and the LH hydraulic pump within 110 flying hours or 6 months. If only one hydraulic pump has an affected P/N and serial number, the Airbus EASB specifies replacing it within 110 flying hours or 6 months. The Airbus EASB also specifies that, for 6 months after receipt of the Airbus EASB, before installing an affected hydraulic pump it must be ‘‘returned to conformity’’ by complying with Nexter Mechanics Alert E:\FR\FM\11JYR1.SGM 11JYR1

Agencies

[Federal Register Volume 82, Number 131 (Tuesday, July 11, 2017)]
[Rules and Regulations]
[Pages 31892-31899]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-14375]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-9254; Directorate Identifier 2015-CE-030-AD; 
Amendment 39-18948; AD 2017-14-04]
RIN 2120-AA64


Airworthiness Directives; Piper Aircraft, Inc. Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are superseding Airworthiness Directive (AD) 95-26-13 for 
certain Piper Aircraft, Inc. Models PA-28-140, PA-28-150, PA-28-151, 
PA-28-161, PA-28-160, PA-28-180, PA-28-181, PA-28-235, PA-28-236, PA-
28R-180, PA-28R-200, PA-28R-201, PA-28S-160, PA-28S-180, PA-32-260, PA-
32-300, PA-32-301, PA-32-301T, PA-32R-300, PA-32R-301 (SP), PA-32R-301 
(HP), PA-32R-301T, PA-32RT-300, PA-32RT-300T, and PA-32S-300 airplanes 
equipped with oil cooler hose assemblies that do not meet certain 
technical standard order (TSO) requirements. AD 95-26-13 required 
inspections, replacement, and adjustment of the oil cooler hose 
assemblies, as well as providing for a terminating action. This AD 
retains all of the requirements of AD 95-26-13 and adds language to 
clarify those requirements. This AD was prompted by several inquiries 
asking for clarification of the AD's applicability and compliance 
requirements. We are issuing this AD to correct the unsafe condition on 
these products.

DATES: This AD is effective August 15, 2017.

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-2016-
9254; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this AD, the regulatory evaluation, any comments received, and 
other information. The address for the Docket Office (phone: 800-647-
5527) is Document Management Facility, U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Gary Wechsler, Aerospace Engineer, 
FAA, Atlanta Aircraft Certification Office, 1701 Columbia Avenue, 
College Park, Georgia 30337; telephone: (404) 474-5575; fax: (404) 474-
5606; email: gary.wechsler@faa.gov.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 95-26-13, Amendment 39-9472 (60 FR 67321, 
December 29, 1995) (``AD 95-26-13''). AD 95-26-13 applied to certain 
Piper Aircraft, Inc. Models PA-28-140, PA-28-150, PA-28-151, PA-28-161, 
PA-28-160, PA-28-180, PA-28-181, PA-28-235, PA-28-236, PA-28R-180, PA-
28R-200, PA-28R-201, PA-28S-160, PA-28S-180, PA-32-260, PA-32-300, PA-
32-301, PA-32-301T, PA-32R-300, PA-32R-301 (SP), PA-32R-301 (HP), PA-
32R-301T, PA-32RT-300, PA-32RT-300T, and PA-32S-300 airplanes equipped 
with oil cooler hose assemblies that do not meet technical standard 
order C53a (TSO-C53a) Type D requirements. The NPRM published in the 
Federal Register on October 21, 2016 (81 FR 72742). The NPRM was 
prompted by several inquiries asking for clarification of the AD's 
applicability and compliance requirements. The NPRM proposed to retain 
all of the requirements of AD 95-26-13 and add language to clarify 
those requirements. We are issuing this AD to correct the unsafe 
condition on these products.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the NPRM and 
the FAA's response to each comment.

Request the Unsafe Condition Be Addressed by Department of Commerce

    G. Fenton requested this unsafe condition be addressed through the 
Department of Commerce instead of the Federal Aviation Administration 
because the NPRM applied to airplanes used for commercial purposes.
    We disagree with this comment because the Federal Aviation 
Administration is charged by Congress to provide for the safe and 
efficient use of national airspace by commercial and private airplane 
operators.
    We have not changed the AD based on this comment.

Request To Change Labor Rate in Cost of Compliance

    G. Fenton requested we change the labor rate in the Cost of 
Compliance section to $72.50 per hour instead of $85 per hour. He 
thought the increased

[[Page 31893]]

cost from $60 per hour from the 1995 AD to $85 per hour for this AD is 
unnecessary. He thought we should adjust the cost of the labor rate to 
a value between the two.
    We disagree with this comment. The rate of $85 per hour is provided 
by the FAA Office of Aviation Policy and Plans for us to use when 
estimating the labor costs of complying with AD requirements.
    We have not changed the AD based on this comment.

Request We Compile Changes From the Previous AD Into One Location

    Jonathan Hartley requested we put all of the changes to this AD 
from AD 95-26-13 in a conspicuous location to reduce confusion and 
workload associated with compliance.
    We partially agree with this comment. We agree there are instances 
where compliance confusion and workload could exist with the wording in 
the NPRM. However, we disagree with compiling the changes into one 
location because of formatting constraints in the AD structure.
    We have made language changes to the regulatory text in the AD to 
clarify the compliance confusion and to reduce workload.

Request We Include an Outline for Maintaining Other Types of Oil Cooler 
Hoses

    Jonathan Hartley requested we include in this AD an outline 
maintaining specific requirements for other types of oil cooler hoses.
    We disagree with this comment. The unsafe condition addressed by 
this AD applies only to Type C and Type D oil cooler hoses. The 
requirements for maintaining other types of oil cooler hoses are not 
required to comply with the actions of this AD.
    We have not changed the AD based on this comment.

Request We Include Additional Information Describing the Types of Hoses

    George Ballard requested we include in the AD information 
explaining what constitutes a Type C and Type D hose assembly. He 
doesn't think the TSO adequately explains the difference between the 
Type C and Type D hose assemblies.
    We disagree with this comment. The differences between the Type C 
and Type D hoses are provided in great detail in TSO-C53a and its 
referenced documents. This AD does not require that level of detail to 
comply with the inspections or corrective actions specified in the AD.
    We have not changed the AD based on this comment.

Request We Clarify Terminating Action for Installation of Type D Hose 
Assemblies

    Greg Dodson stated the requirement to inspect the oil cooler hose 
assembly installation for an oil cooler mounted in a location other 
than at or aft of the rear of the engine any time the oil cooler hose 
assembly is replaced conflicts with the installation of a Type D oil 
cooler hose assembly being terminating action for the AD.
    We agree with this comment. The installation of the Type D oil 
cooler hose assembly terminates the requirement for the installation 
inspection.
    We have changed the language in the AD to address the 
contradiction.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
this AD with the changes described previously and minor editorial 
changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM for correcting the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM.
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this AD.

Costs of Compliance

    We estimate that this AD affects 23,643 airplanes of U.S. registry.
    This AD retains the same actions as AD 95-26-13 and the costs do 
not add any cost burden than that already in effect by AD 95-26-13. The 
difference in the Costs of Compliance with this AD and AD 95-26-13 is 
that we use $85 an hour as a labor rate in 2016 as opposed to $60 per 
hour in 1995.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                  Cost per      Cost on U.S.
              Action                      Labor cost            Parts cost        product         operators
----------------------------------------------------------------------------------------------------------------
Inspection of the oil cooler hose   1 work-hour x $85 per  Not applicable......        $85  $2,009,655.
 assembly.                           hour = $85.
Inspection of the clearance         .5 work-hour x $85     Not applicable......     $42.50  $1,004,827.50 See
 between the oil cooler hose         per hour = 42.50.                                       note 1 to Cost of
 assembly and the front exhaust                                                              Compliance.
 stacks.
Replacement of the oil cooler hose  1 work-hour x $85 per  $430................       $515  $12,176,145.
 assembly.                           hour = $85.
----------------------------------------------------------------------------------------------------------------


    Note: The estimated cost of the inspection of the clearance 
between the oil cooler hose assembly and the front exhaust stacks is 
for all airplanes affected by this AD; however, the inspection 
applies only to airplanes with the oil cooler mounted in a location 
other than at or aft of the rear of the engine. We have no way of 
knowing how many affected airplanes have that particular 
installation.

    We estimate the following costs to do any necessary adjustments 
that would be required based on the results of the inspection. We have 
no way of determining the number of aircraft that might need these 
adjustments:

[[Page 31894]]



                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                 Action                           Labor cost                  Parts cost              product
----------------------------------------------------------------------------------------------------------------
Adjustment of the clearance between the   1 work-hour x $85 per hour  Not applicable............             $85
 oil cooler hose assembly and the front    = $85.
 exhaust stacks.
----------------------------------------------------------------------------------------------------------------

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 have 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 that this AD:

    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under 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.

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 removing Airworthiness Directive (AD) 
95-26-13, Amendment 39-9472 (60 FR 67321, December 29, 1995), and 
adding the following new AD:

2017-14-04 Piper Aircraft, Inc.: Amendment 39-18948; Docket No. FAA-
2016-9254; Directorate Identifier 2015-CE-030-AD.

(a) Effective Date

    This AD is effective August 15, 2017.

(b) Affected ADs

    This AD replaces AD 95-26-13, Amendment 39-9472 (60 FR 67321, 
December 29, 1995) (``AD 95-26-13'').

(c) Applicability

    This AD applies to Piper Aircraft, Inc. Models PA-28-140, PA-28-
150, PA-28-151, PA-28-161, PA-28-160, PA-28-180, PA-28-181, PA-28-
235, PA-28-236, PA-28R-180, PA-28R-200, PA-28R-201, PA-28S-160, PA-
28S-180, PA-32-260, PA-32-300, PA-32-301, PA-32-301T, PA-32R-300, 
PA-32R-301 (SP), PA-32R-301 (HP), PA-32R-301T, PA-32RT-300, PA-32RT-
300T, and PA-32S-300 airplanes, all serial numbers, that are:
    (1) Equipped with one or more oil cooler hose assemblies that do 
not meet technical standard order C53a (TSO-C53a), Type D 
requirements; and
    (2) Certificated in any category.

(d) Subject

    Joint Aircraft System Component (JASC)/Air Transport Association 
(ATA) of America Code 79, Engine Oil.

(e) Unsafe Condition

    AD 95-26-13 was prompted by numerous incidents/accidents caused 
by rupture or failure of the oil cooler hose assemblies. This AD 
action was prompted by requests to clarify the intent of AD 95-26-
13. We are issuing this AD to prevent rupture or failure of the oil 
cooler hose assemblies, which could result in engine stoppage with 
consequent loss of control.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done. You may review the flow chart found in appendix 
1 to assist you in complying with the actions of this AD.

(g) Inspection Procedures for an Oil Cooler Mounted AT or AFT of the 
Rear of the Engine

    For any oil cooler hose assemblies that do not meet TSO-C53a, 
Type D requirements: Within the next 100 hours time-in-service (TIS) 
after February 5, 1996 (the effective date retained from AD 95-26-
13), and repetitively thereafter at intervals not to exceed 100 
hours TIS, inspect the fire sleeve of each oil cooler hose assembly 
for soaked oil, a brownish or whitish color, and any evidence of 
brittleness or deterioration as a result of heat or oil seepage. See 
figure 1 to paragraphs (g) and (h) of this AD for additional 
information.

[[Page 31895]]

[GRAPHIC] [TIFF OMITTED] TR11JY17.016


     Note 1 to paragraphs (g) and (h)(1) of this AD:  Although not 
required by this AD, the FAA recommends that an oil cooler hose 
assembly flexibility test be done at 100-hour TIS intervals by 
gently lifting each oil cooler hose assembly in several places along 
its bottom surface, ideally at the center of an arc. If the oil 
cooler hose assembly moves slightly, either from side-to-side or 
upward, then some flexibility remains. If the oil cooler hose 
assembly appears hardened or inflexible, replacement is recommended.

(h) Inspection Procedures for an Oil Cooler Mounted in a Location Other 
Than AT or AFT of the Rear of the Engine

    (1) For any oil cooler hose assemblies that do not meet TSO-
C53a, Type D requirements: Within the next 100 hours TIS after 
February 5, 1996 (the effective date retained from AD 95-26-13), and 
repetitively thereafter at intervals not to exceed 100 hours TIS, 
inspect the fire sleeve of each oil cooler hose assembly for soaked 
oil, a brownish or whitish color, and any evidence of brittleness or 
deterioration as a result of heat or oil seepage. See figure 1 to 
paragraphs (g) and (h) of this AD for additional information.
    (2) For any oil cooler hose assemblies that do not meet TSO-
C53a, Type D requirements: Within the next 100 hours TIS after 
February 5, 1996 (the effective date retained from AD 95-26-13) and 
repetitively thereafter at intervals not to exceed 100 hours TIS, 
inspect the oil cooler hose assemblies to ensure the installation 
conditions in paragraphs (h)(2)(i) through (iii) of this AD are met. 
See figure 1 to paragraphs (g) and (h) of this AD for additional 
information. If the conditions listed in paragraphs (h)(2)(i) 
through (iii) of this AD are not met, before further flight, make 
any necessary adjustments. See figure 2 to paragraph (h)(2) of this 
AD for additional information.
    (i) The oil cooler hose assemblies pass underneath and behind 
the electrical ground cable and in front of the lower of the two 
engine mounts.
    (ii) The oil cooler hose assemblies are secured to the engine 
mount strut and a clearance of at least 2 inches exists between the 
oil cooler hose assemblies and the exhaust stack.
    (iii) Oil cooler hose assemblies with a minimum outer diameter 
of 0.75 inch are installed with a bend radius of at least 6.5 
inches.

[[Page 31896]]

[GRAPHIC] [TIFF OMITTED] TR11JY17.001

(i) Corrective Actions

    (1) If any of the conditions described in paragraph (g) or 
(h)(1) of this AD are found on an oil cooler hose assembly during 
the inspection required in paragraph (g) or (h)(1) of this AD, as 
applicable, before further flight, replace the oil cooler hose 
assembly with a serviceable new or used TSO-C53a Type D oil cooler 
hose assembly or TSO-C53a Type C oil cooler hose assembly. If a used 
TSO-C53a Type C oil cooler hose assembly is installed, it must have 
documented hours TIS.

    Note 2 to paragraphs (i)(1) and (j) of this AD: If only one of 
the two oil cooler hose assemblies requires replacement, the FAA 
recommends replacing both of the oil cooler hose assemblies to 
simplify tracking the hours TIS of the assemblies.

    (2) If a newly installed oil cooler hose assembly is a TSO-C53a 
Type C oil cooler hose assembly and it is mounted in a location 
other than at or aft of the rear of the engine, then replacement of 
the oil cooler hose assembly must meet the conditions listed in 
paragraphs (h)(2)(i) through (iii) of this AD.
    (3) If compliance with paragraphs (i)(1) and (i)(2) of this AD 
results in both oil cooler hose assemblies of an airplane meeting 
TSO-C53a Type D requirements, then the requirements of this AD are 
terminated for the airplane.

(j) Life Limit of TSO-C53a Type C Oil Cooler Hose Assemblies

    (1) When a TSO-C53a Type C oil cooler hose assembly accumulates 
8 years or 1,000 hours TIS, whichever occurs first, replace the oil 
cooler hose assembly with a serviceable new or used TSO-C53a Type D 
oil cooler hose assembly or TSO-C53a Type C oil cooler hose 
assembly. If a used TSO-C53a Type C oil cooler hose assembly is 
installed, it must have documented hours TIS. If the newly installed 
oil cooler is a TSO-C53a Type C oil cooler hose assembly and it is 
mounted in a location other than at or aft of the rear of the engine 
the installation must meet the conditions listed in paragraphs 
(h)(2)(i) through (iii) of this AD.
    (2) You may at any time before a TSO-C53a Type C oil cooler hose 
assembly exceeds the life limit in paragraph (j)(1) of this AD, 
replace a TSO-C53a Type C oil cooler hose assembly with a TSO-C53a 
Type D oil cooler hose assembly.
    (3) If compliance with paragraphs (j)(1) or (j)(2) of this AD 
results in both oil cooler hose assemblies of an airplane meeting 
TSO-C53a Type D requirements, then the requirements of this AD are 
terminated for the airplane.

(k) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Atlanta Aircraft Certification Office (ACO), 
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 manager of the ACO, send it to the 
attention of the person identified in paragraph (k) of this AD.
    (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.

[[Page 31897]]

    (3) AMOCs approved for AD 95-26-13 (60 FR 67321, December 29, 
1995) are not approved as AMOCs for the corresponding provisions of 
this AD.

(l) Related Information

    For more information about this AD, contact Gary Wechsler, 
Aerospace Engineer, FAA, Atlanta Aircraft Certification Office, 1701 
Columbia Avenue, College Park, Georgia 30337; telephone: (404) 474-
5575; fax: (404) 474-5606; email: gary.wechsler@faa.gov.
BILLING CODE 4910-13-P

[[Page 31898]]

[GRAPHIC] [TIFF OMITTED] TR11JY17.018




[[Page 31899]]


    Issued in Kansas City, Missouri, on June 29, 2017.
Pat Mullen,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2017-14375 Filed 7-10-17; 8:45 am]
BILLING CODE 4910-13-C