Airworthiness Directives; Bell Helicopter Textron Canada Helicopters, 17103-17107 [2017-06710]

Download as PDF Federal Register / Vol. 82, No. 67 / Monday, April 10, 2017 / Rules and Regulations response to the prior opportunities for comment described above. List of Subjects in 14 CFR Part 25 Aircraft, Aviation safety, Reporting and recordkeeping requirements. The authority citation for these special conditions is as follows: Issued in Renton, Washington, on March 15, 2017. Dionne Palermo, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017–07060 Filed 4–7–17; 8:45 am] BILLING CODE 4910–13–P Authority: 49 U.S.C. 106(g), 40113, 44701, 44702, 44704. DEPARTMENT OF TRANSPORTATION The Special Conditions Federal Aviation Administration Accordingly, pursuant to the authority delegated to me by the Administrator, the following special conditions are issued as part of the type certification basis for Embraer Model ERJ 190–300 airplanes. 14 CFR Part 39 1. General Limiting Requirements Airworthiness Directives; Bell Helicopter Textron Canada Helicopters a. Onset characteristics of each envelope protection feature must be smooth, appropriate to the phase of flight and type of maneuver, and not in conflict with the ability of the pilot to satisfactorily change airplane flight path, speed, or attitude as needed. b. Limit values of protected flight parameters (and if applicable, associated warning thresholds) must be compatible with the following: i. Airplane structural limits, ii. Required safe and controllable maneuvering of the airplane, and iii. Margins to critical conditions. Unsafe flight characteristics/conditions must not result if dynamic maneuvering, airframe and system tolerances (both manufacturing and inservice), and non-steady atmospheric conditions, in any appropriate combination and phase of flight, can produce a limited flight parameter beyond the nominal design-limit value. c. The airplane must be responsive to intentional dynamic maneuvering to within a suitable range of the parameter limit. Dynamic characteristics such as damping and overshoot must also be appropriate for the flight maneuver and limit parameter in question. d. When simultaneous envelope limiting is engaged, adverse coupling or adverse priority must not result. pmangrum on DSK3GDR082PROD with RULES 2. Failure States a. Electronic flight-control-system failures (including sensors) must not result in a condition where a parameter is limited to such a reduced value that safe and controllable maneuvering is no longer available. b. The crew must be alerted by suitable means if any change in envelope limiting or maneuverability is produced by single or multiple failures of the electronic flight-control system not shown to be extremely improbable. VerDate Sep<11>2014 14:16 Apr 07, 2017 Jkt 241001 [Docket No. FAA–2017–0189; Directorate Identifier 2017–SW–008–AD; Amendment 39–18847; AD 2017–05–51] RIN 2120–AA64 Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: We are publishing a new airworthiness directive (AD) for Bell Helicopter Textron Canada (Bell) Model 429 helicopters. This AD requires inspecting the condenser blower motor (motor) and condenser blower (blower) to determine if the motor is securely attached to the blower support (shroud). This AD is prompted by a report that the motor detached from the blower. The actions of this AD are intended to prevent an unsafe condition on these products. DATES: This AD becomes effective April 25, 2017 to all persons except those persons to whom it was made immediately effective by Emergency AD 2017–05–51, issued on March 3, 2017, which contains the requirements of this AD. The Director of the Federal Register approved the incorporation by reference of a certain document listed in this AD as of April 25, 2017. We must receive comments on this AD by June 9, 2017. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Docket: Go to https://www.regulations.gov. Follow the online instructions for sending your comments electronically. • Fax: 202–493–2251. • Mail: Send comments to the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590–0001. • Hand Delivery: Deliver to the ‘‘Mail’’ address between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. SUMMARY: PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 17103 Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2017– 0189; or in person at the Docket Operations Office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, any incorporated by reference service information, 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 Air Comm Corporation, 1575 West 124th Avenue, Westminster, CO 80234; telephone: (303) 440–4075 (during business hours) or (720) 233–8330 (after hours); email: service@aircommcorp.com; Web site: https://www.aircommcorp.com/contact. 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. It is also available on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2017– 0189. FOR FURTHER INFORMATION CONTACT: Matthew Bryant, Aerospace Engineer, Denver Aircraft Certification Office, FAA, Technical Operations Center, 26805 East 68th Avenue, Room 214, Denver CO 80249; phone (303) 342– 1092; fax (303) 342–1088; email Matthew.Bryant@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 E:\FR\FM\10APR1.SGM 10APR1 17104 Federal Register / Vol. 82, No. 67 / Monday, April 10, 2017 / Rules and Regulations 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 On March 3, 2017, we issued Emergency AD 2017–05–51 to correct an unsafe condition on Bell Model 429 helicopters with an Air Comm Corporation (Air Comm) air conditioning system part number (P/N) 429EC–200 or 429EC–202 installed. Emergency AD 2017–05–51 was sent previously to all known U.S. owners and operators of these helicopters. Emergency AD 2017–05–51 requires inspecting the motor and blower to determine if the motor is securely attached to the shroud. Emergency AD 2017–05–51 was prompted by a report that the motor detached from the blower. The motor is secured to the shroud by three screw fasteners with thread locker applied. The report states that the detached motor was resting on the flight controls. An initial investigation indicates that the motor mount fasteners may not have had the thread locker adhesive applied during production. However, the root cause is under investigation. The motor fell on the collective control tube, causing wear damage to the control tube. The motor’s power wiring also was on the collective control tube near hydraulic and fuel lines. The actions in Emergency AD 2017–05–51 are intended to prevent the motor from detaching, causing failure of the primary flight controls and subsequent loss of helicopter control. pmangrum on DSK3GDR082PROD with RULES FAA’s Determination We are issuing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of these same type designs. Related Service Information Under 1 CFR Part 51 We reviewed Air Comm Service Bulletin 429–201–1, Revision NC, dated February 17, 2017 (SB 429–201–1), which advises inspecting the motor to determine whether it is attached to the blower assembly within 20 flight hours. If the motor is not attached to the blower assembly, SB 429–201–1 advises reporting the detachment to Air Comm and inspecting the surrounding area for damage. If any surrounding parts are damaged, SB 429–201–1 specifies replacing or repairing the damaged VerDate Sep<11>2014 14:16 Apr 07, 2017 Jkt 241001 parts. SB 429–201–1 then specifies replacing the blower assembly if parts are available and deactivating the air conditioning system if parts are not available. SB 429–201–1 also provides instructions if any P/N MS27039–1–15 fasteners are missing or loose or if the motor is not secured firmly to the blower assembly. These instructions include rotating the fan blades by hand and verifying the clearance between the blades and the shroud. If the fan blades are scraping or rubbing against the shroud or if the blades cause visible damage to the shroud, SB 429–201–1 advises replacing the blower assembly if parts are available. If parts are not available, SB 429–201–1 advises deactivating the air conditioning system. If the motor is secure, SB 429– 201–1 provides instructions for replacing any missing fasteners and removing and reinstalling any existing fasteners with thread locker. 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. AD Requirements This AD requires, before further flight and at intervals not to exceed 25 hours time-in-service (TIS), inspecting the air conditioner condenser blower for motor attachment and for missing or loose fasteners. If the motor is not attached or if a fastener is missing or loose, this AD requires deactivating the air conditioning system. If the motor is not attached, this AD also requires inspecting the collective flight control tube, the area under the forward transmission cowling, and each wiring harness, and depending on the findings, repairing or replacing the affected parts. Additionally, if the motor is not attached or if the motor is attached but any fasteners are missing, this AD requires inspecting for and removing any found detached hardware. Deactivating the air conditioning system constitutes terminating action for the repetitive inspections required by this AD. This AD also requires reporting certain information to the FAA within 10 days. Differences Between This AD and the Service Information SB 429–201–1 advises performing the initial inspection within 20 hours TIS. This AD requires the initial inspection before further flight. SB 429–201–1 advises reporting certain incidents to Air Comm, whereas this AD requires reporting certain information to the FAA. SB 429–201–1 does not specify inspecting for and removing missing PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 hardware, whereas this AD does. If replacement parts are available, SB 429– 201–1 advises replacing the blower, while this AD makes no allowance for replacing the blower except by alternate means of compliance. If fasteners are missing or loose but the motor is secure, SB 429–201–1 advises replacing missing fasteners and removing and reinstalling existing fasteners with thread locker and a torque stripe. This AD requires removing the blower assembly if fasteners are missing or loose but the motor is still secure. SB 429–201–1 does not require repetitive inspections, while this AD requires the inspection every 25 hours time-in-service until the air conditioning system is deactivated. Interim Action We consider this AD to be an interim action. The inspection report that is required by this AD will enable us to obtain better insight into the cause of the motor’s detachment, and help us develop final action to address this unsafe condition. The design approval holder is also currently developing a modification that will address the unsafe condition identified in this AD. Once this modification is developed, approved, and available, we might consider additional rulemaking. Costs of Compliance We estimate that this AD affects 78 helicopters of U.S. Registry and that labor costs average $85 per work-hour. Based on these estimates, we expect the following costs: • Inspecting the motor attachment requires 1 work-hour and no parts for a total cost of $85 per helicopter, and $6,630 for the U.S. fleet, per inspection cycle. • Removing the motor and deactivating the air conditioning requires 2 work-hours and no parts for a total cost of $170 per helicopter. • Removing the blower assembly and deactivating the air conditioning requires 13 work-hours and no parts for a total cost of $1,105 per helicopter. • Reporting the findings to the FAA requires 1 work-hour and no parts for a total cost of $85 per helicopter. Paperwork Reduction Act A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB control number. The control number for the collection of information required by this AD is 2120–0056. The E:\FR\FM\10APR1.SGM 10APR1 Federal Register / Vol. 82, No. 67 / Monday, April 10, 2017 / Rules and Regulations paperwork cost associated with this AD has been detailed in the Costs of Compliance section of this document and includes time for reviewing instructions, as well as completing and reviewing the collection of information. Therefore, all reporting required by this AD is mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at 800 Independence Ave. SW., Washington, DC 20591. ATTN: Information Collection Clearance Officer, AES–200. pmangrum on DSK3GDR082PROD with RULES FAA’s Justification and Determination of the Effective Date Providing an opportunity for public comments prior to adopting these AD requirements would delay implementing the safety actions needed to correct this known unsafe condition. Therefore, we found and continue to find that the risk to the flying public justifies waiving notice and comment prior to the adoption of this rule because the required initial inspection must be accomplished before further flight and the recurring inspection must be accomplished at intervals not to exceed 25 hours TIS. These helicopters, typically used for police and medical transport, are expected to reach 25 hours TIS within a few weeks. Since it was found that immediate corrective action was required, notice and opportunity for prior public comments before issuing this AD were impracticable and contrary to public interest and good cause existed to make the AD effective immediately by Emergency AD 2017–05–51, issued on March 3, 2017, to all known U.S. owners and operators of these helicopters. These conditions still exists and the AD is hereby published in the Federal Register as an amendment to section 39.13 of the Federal Aviation Regulations (14 CFR 39.13) to make it effective to all persons. 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 VerDate Sep<11>2014 14:16 Apr 07, 2017 Jkt 241001 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, 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 to the extent that it justifies making a regulatory distinction; 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. We prepared an economic evaluation of the estimated costs to comply with this AD and placed it in the AD docket. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by Reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ 2017–05–51 Bell Helicopter Textron Canada: Amendment 39–18847; Docket No. FAA–2017–0189; Directorate Identifier 2017–SW–008–AD. (a) Applicability This AD applies to Bell Helicopter Textron Canada (Bell) Model 429 helicopters with an Air Comm Corporation air conditioning system part number (P/N) 429EC–200 or PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 17105 429EC–202 installed, certificated in any category. Note 1 to paragraph (a) of this AD: Air conditioning system P/N 429EC–200 and 429EC–202 are identifiable by a three-screw installation as depicted in Figure 1 of Air Comm Corporation Service Bulletin 429–201–1, Revision NC, dated February 17, 2017 (SB 429– 201–1). (b) Unsafe Condition This AD defines the unsafe condition as a condenser blower motor (motor) detaching from the condenser blower support (shroud). This condition could lead to failure of the primary flight controls and subsequent loss of helicopter control. (c) Effective Date This AD becomes effective April 25, 2017 to all persons except those persons to whom it was made immediately effective by Emergency AD 2017–05–51, issued on March 3, 2017, which contains the requirements of this AD. (d) Compliance You are responsible for performing each action required by this AD within the specified compliance time unless it has already been accomplished prior to that time. (e) Required Actions Before further flight, and thereafter at intervals not to exceed 25 hours time-inservice: (1) Inspect the motor and condenser blower to determine whether the motor is attached to the shroud. (i) If the motor is not attached, before further flight: (A) Inspect the collective flight control tube for loss of protective primer, a scratch, any gouging, and a dent. If there is any loss of protective primer, a scratch, any gouging, or a dent, repair or replace the control tube. (B) Inspect the area under the forward transmission cowling for loss of protective primer, a scratch, any gouging, and a dent. Inspect each wiring harness for any cuts, chafing, and exposed wires. If there is any loss of protective primer, a scratch, any gouging, a dent, or if any wiring harness has a cut, chafing, or an exposed wire, repair or replace the affected parts. (C) Inspect the area under the forward transmission cowling for the three fasteners as depicted in Figure 1 of SB 429–201–1. Also inspect for the crimpon external fan retaining ring (crimp ring) and the slotted fan drive spring (commonly known as a roll pin), which may have fallen loose with the motor. E:\FR\FM\10APR1.SGM 10APR1 17106 Federal Register / Vol. 82, No. 67 / Monday, April 10, 2017 / Rules and Regulations Remove any fasteners, the crimp ring, and the roll pin if found detached. (D) Deactivate the air conditioning system by following the instructions in Procedure, paragraphs B.2.d.i. through B.2.d.v., of SB 429–201–1. (ii) If the motor is attached to the shroud but a fastener is missing or loose, before further flight: (A) Remove any detached fasteners found in the area under the forward transmission cowling. (B) Deactivate the air conditioning system as follows: (1) Pull and red collar the air conditioning COND circuit breaker. (2) Pull and red collar the airconditioning COMP circuit breaker. (3) Remove the compressor drive belt. (4) Remove the condenser blower assembly. (2) Deactivating the air conditioning system as required by paragraph (e)(1) of this AD constitutes terminating action for the repetitive inspections required by paragraph (e)(1) of this AD. (3) If the air conditioning system is deactivated as required by paragraph (e)(1) of this AD, within 10 days after completing the inspection, report the information requested in Appendix 1 to this AD by mail to the Manager, Denver Aircraft Certification Office, FAA, Technical Operations Center, 26805 East 68th Avenue, Room 214, Denver, CO 80249, ATTN: Matthew Bryant; by fax to (303) 342–1088; or by email to Matthew.Bryant@faa.gov. (f) Alternative Methods of Compliance (AMOCs) (1) The Manager, Denver Aircraft Certification Office, FAA, may approve AMOCs for this AD. Send your proposal to: Matthew Bryant, Aerospace Engineer, Denver Aircraft Certification Office, FAA, Technical Operations Center, 26805 East 68th Avenue, Room 214, Denver, CO 80249; fax (303) 342– 1088; email Matthew.Bryant@faa.gov. (2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part 91, subpart K, we suggest that you notify your principal inspector, or lacking a principal inspector, the manager of the local flight standards district office or certificate holding district office before operating any aircraft complying with this AD through an AMOC. (g) Subject (4) You may view this service information at FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy, Room 6N–321, Fort Worth, TX 76177. For information on the availability of this material at the FAA, call (817) 222–5110. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call (202) 741–6030, or go to: https://www.archives.gov/ federal-register/cfr/ibr-locations.html. Joint Aircraft Service Component (JASC) Code: 2150, Cabin Cooling System. Issued in Fort Worth, Texas, on March 29, 2017. (h) Material Incorporated by Reference Scott A. Horn, (1) The Director of the Federal Register approved the incorporation by reference 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) Air Comm Corporation Service Bulletin 429–201–1, Revision NC, dated February 17, 2017. (ii) Reserved. (3) For Air Comm Corporation service information identified in this AD, contact Air Comm Corporation, 1575 West 124th Avenue, Westminster, CO 80234; telephone: (303) 440–4075 (during business hours) or (720) 233– Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. AD 2017–05–51 Appendix 1 to AD 2017–05–51 Provide the following information by mail to the Manager, Denver Aircraft Certification Office, FAA, Technical Operations Center, 26805 East 68th Avenue, Room 214, Denver, CO 80249, ATTN: Matthew Bryant; by fax to (303) 342–1088; or by email to Matthew.Bryant@faa.gov: For inspection being accomplished (Initial or Repetitive), record inspection findings below and provide photos if possible. Inspection findings Aircraft S/N or N-Number ......................................................................... Air Conditioner Installation S/N (Laser etched on compressor mount) ... Aircraft Location ........................................................................................ Condition ................................................................................................... Is this a single evaporator installation or a dual evaporator installation? Was the motor still attached? ................................................................... Were there any missing or loose fasteners? ........................................... Were any of the loose fasteners found in the surrounding area? ........... Did the found fasteners show evidence of thread locker being applied? Has the condenser blower (blower) been replaced following the initial installation of the air conditioning system? What was the reason for the blower replacement? ................................. Aircraft TIS when blower was replaced ................................................... pmangrum on DSK3GDR082PROD with RULES 8330 (after hours); email: service@ aircommcorp.com; Web site: https:// www.aircommcorp.com/contact. Aircraft hours time-in-service (TIS). Aircraft TIS when air conditioning system was installed. Estimated percent air conditioner operating time. Operator and maintenance facility contact information. Findings. [FR Doc. 2017–06710 Filed 4–7–17; 8:45 am] BILLING CODE 4910–13–P VerDate Sep<11>2014 16:44 Apr 07, 2017 Jkt 241001 PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 E:\FR\FM\10APR1.SGM 10APR1 Federal Register / Vol. 82, No. 67 / Monday, April 10, 2017 / Rules and Regulations DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–8851; Directorate Identifier 2016–NM–070–AD; Amendment 39–18831; AD 2017–06–07] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for all Airbus Model A330–200 Freighter, –200, and –300 series airplanes; and Airbus Model A340–200, –300, –500, and –600 series airplanes. This AD was prompted by reports that nonconforming aluminum alloy was used to manufacture several structural parts on the inboard flap. This AD requires identification of the potentially affected inboard flap parts, a one-time eddy current inspection to identify which material the parts are made of, and, depending on findings, replacement with serviceable parts. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective May 15, 2017. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of May 15, 2017. ADDRESSES: For service information identified in this final rule, contact Airbus SAS, Airworthiness Office— EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email airworthiness.A330-A340@ airbus.com; Internet https:// www.airbus.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227– 1221. It is also available on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2016–8851. pmangrum on DSK3GDR082PROD with RULES SUMMARY: Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 8851; or in person at the Docket Management Facility between 9 a.m. VerDate Sep<11>2014 16:44 Apr 07, 2017 Jkt 241001 and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (telephone 800–647– 5527) is Docket 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: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1138; fax 425–227–1149. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to all Airbus Model A330–200 Freighter, –200, and –300 series airplanes; and Airbus Model A340–500 and –600 series airplanes. The NPRM published in the Federal Register on August 31, 2016 (81 FR 59922) (‘‘the NPRM’’). The NPRM was prompted by reports that nonconforming aluminum alloy was used to manufacture several structural parts on the inboard flap. The NPRM proposed to require identification of the potentially affected inboard flap parts, a one-time eddy current inspection to identify which material the parts are made of, and, depending on findings, replacement with serviceable parts. We are issuing this AD to detect and correct structural parts of inboard flaps made of nonconforming aluminum alloy, which could result in reduced structural integrity of the airplane. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2016–0231, dated November 22, 2016 (‘‘EASA AD 2016–0231’’) (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), which superseded EASA Airworthiness Directive 2016– 0082, dated April 27, 2016 (‘‘EASA AD 2016–0082’’), to correct an unsafe condition all Airbus Model A330–200 Freighter, –200, and –300 series airplanes; and Airbus Model A340–200, –300, –500 and –600 series airplanes. The MCAI states: Following an Airbus quality control review on the final assembly line, it was discovered that non-conforming aluminium alloy was used to manufacture several structural parts on the inboard flap. PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 17107 This condition, if not detected and corrected, could reduce the structural integrity of the aeroplane. To address this potential unsafe condition, Airbus issued Service Bulletin (SB) A330– 57–3120 and SB A340–57–5036 to provide instructions to identify and inspect the potentially affected parts. Consequently, EASA issued AD 2016–0082 to require identification of the potentially affected inboard flap parts, a one-time special detailed inspection (SDI) [eddy current measurement] to identify which material they are made of and, depending on findings, replacement with serviceable parts. Since EASA AD 2016–0082 was issued, it was confirmed that flaps, initially installed on A340–500 and A340–600 aeroplanes, may also have been installed in service on A340– 200 or A340–300 aeroplanes. As this installation was not done during production, no SB was published for these models. For the reason described above, this [EASA] AD retains the requirements of EASA AD 2016–0082 [which corresponded to the FAA NPRM], which is superseded, expands the Applicability to include A340–200 and A340–300 aeroplanes, corrects a typographical error in Appendix 1 of this [EASA] AD for one affected flap, Right Hand (RH) serial number (s/n) ‘‘TB 11411’’ in place of ‘‘TB 14411’’ (date of first operation: 19/04/ 13) and identified in bold in Appendix 1, and adds the prefix ‘‘TB’’ to the s/n’s of all Left Hand (LH) and RH flaps, which was inadvertently omitted in Appendix 1 of [EASA] AD 2016–0082. This [EASA] AD also allows, under certain conditions, installation of an affected inboard flap on an aeroplane. Airbus Model A340–200 and –300 series airplanes have been added to the applicability of this AD. Since there are currently no domestic operators of these added airplanes, notice and opportunity for public comment before issuing this AD are unnecessary. You may examine the MCAI in the AD docket on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 8851. 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 To Account for a Superseding EASA Airworthiness Directive Airbus commented that EASA was planning to supersede EASA AD 2016– 0082 with EASA AD 2016–0231, which would update the AD applicability, correct a certain part serial number, and add the prefix ‘‘TB’’ to the serial E:\FR\FM\10APR1.SGM 10APR1

Agencies

[Federal Register Volume 82, Number 67 (Monday, April 10, 2017)]
[Rules and Regulations]
[Pages 17103-17107]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-06710]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0189; Directorate Identifier 2017-SW-008-AD; 
Amendment 39-18847; AD 2017-05-51]
RIN 2120-AA64


Airworthiness Directives; Bell Helicopter Textron Canada 
Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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SUMMARY: We are publishing a new airworthiness directive (AD) for Bell 
Helicopter Textron Canada (Bell) Model 429 helicopters. This AD 
requires inspecting the condenser blower motor (motor) and condenser 
blower (blower) to determine if the motor is securely attached to the 
blower support (shroud). This AD is prompted by a report that the motor 
detached from the blower. The actions of this AD are intended to 
prevent an unsafe condition on these products.

DATES: This AD becomes effective April 25, 2017 to all persons except 
those persons to whom it was made immediately effective by Emergency AD 
2017-05-51, issued on March 3, 2017, which contains the requirements of 
this AD.
    The Director of the Federal Register approved the incorporation by 
reference of a certain document listed in this AD as of April 25, 2017. 
We must receive comments on this AD by June 9, 2017.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Docket: Go to https://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.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2017-
0189; or in person at the Docket Operations Office between 9 a.m. and 5 
p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this AD, any incorporated by reference service information, 
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 Air 
Comm Corporation, 1575 West 124th Avenue, Westminster, CO 80234; 
telephone: (303) 440-4075 (during business hours) or (720) 233-8330 
(after hours); email: service@aircommcorp.com; Web site: https://www.aircommcorp.com/contact. 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. It is 
also available on the Internet at https://www.regulations.gov by 
searching for and locating Docket No. FAA-2017-0189.

FOR FURTHER INFORMATION CONTACT: Matthew Bryant, Aerospace Engineer, 
Denver Aircraft Certification Office, FAA, Technical Operations Center, 
26805 East 68th Avenue, Room 214, Denver CO 80249; phone (303) 342-
1092; fax (303) 342-1088; email Matthew.Bryant@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

[[Page 17104]]

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

    On March 3, 2017, we issued Emergency AD 2017-05-51 to correct an 
unsafe condition on Bell Model 429 helicopters with an Air Comm 
Corporation (Air Comm) air conditioning system part number (P/N) 429EC-
200 or 429EC-202 installed. Emergency AD 2017-05-51 was sent previously 
to all known U.S. owners and operators of these helicopters. Emergency 
AD 2017-05-51 requires inspecting the motor and blower to determine if 
the motor is securely attached to the shroud.
    Emergency AD 2017-05-51 was prompted by a report that the motor 
detached from the blower. The motor is secured to the shroud by three 
screw fasteners with thread locker applied. The report states that the 
detached motor was resting on the flight controls.
    An initial investigation indicates that the motor mount fasteners 
may not have had the thread locker adhesive applied during production. 
However, the root cause is under investigation. The motor fell on the 
collective control tube, causing wear damage to the control tube. The 
motor's power wiring also was on the collective control tube near 
hydraulic and fuel lines. The actions in Emergency AD 2017-05-51 are 
intended to prevent the motor from detaching, causing failure of the 
primary flight controls and subsequent loss of helicopter control.

FAA's Determination

    We are issuing this AD because we evaluated all the relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of these same type 
designs.

Related Service Information Under 1 CFR Part 51

    We reviewed Air Comm Service Bulletin 429-201-1, Revision NC, dated 
February 17, 2017 (SB 429-201-1), which advises inspecting the motor to 
determine whether it is attached to the blower assembly within 20 
flight hours. If the motor is not attached to the blower assembly, SB 
429-201-1 advises reporting the detachment to Air Comm and inspecting 
the surrounding area for damage. If any surrounding parts are damaged, 
SB 429-201-1 specifies replacing or repairing the damaged parts. SB 
429-201-1 then specifies replacing the blower assembly if parts are 
available and deactivating the air conditioning system if parts are not 
available. SB 429-201-1 also provides instructions if any P/N MS27039-
1-15 fasteners are missing or loose or if the motor is not secured 
firmly to the blower assembly. These instructions include rotating the 
fan blades by hand and verifying the clearance between the blades and 
the shroud. If the fan blades are scraping or rubbing against the 
shroud or if the blades cause visible damage to the shroud, SB 429-201-
1 advises replacing the blower assembly if parts are available. If 
parts are not available, SB 429-201-1 advises deactivating the air 
conditioning system. If the motor is secure, SB 429-201-1 provides 
instructions for replacing any missing fasteners and removing and 
reinstalling any existing fasteners with thread locker.
    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.

AD Requirements

    This AD requires, before further flight and at intervals not to 
exceed 25 hours time-in-service (TIS), inspecting the air conditioner 
condenser blower for motor attachment and for missing or loose 
fasteners. If the motor is not attached or if a fastener is missing or 
loose, this AD requires deactivating the air conditioning system. If 
the motor is not attached, this AD also requires inspecting the 
collective flight control tube, the area under the forward transmission 
cowling, and each wiring harness, and depending on the findings, 
repairing or replacing the affected parts. Additionally, if the motor 
is not attached or if the motor is attached but any fasteners are 
missing, this AD requires inspecting for and removing any found 
detached hardware. Deactivating the air conditioning system constitutes 
terminating action for the repetitive inspections required by this AD. 
This AD also requires reporting certain information to the FAA within 
10 days.

Differences Between This AD and the Service Information

    SB 429-201-1 advises performing the initial inspection within 20 
hours TIS. This AD requires the initial inspection before further 
flight. SB 429-201-1 advises reporting certain incidents to Air Comm, 
whereas this AD requires reporting certain information to the FAA. SB 
429-201-1 does not specify inspecting for and removing missing 
hardware, whereas this AD does. If replacement parts are available, SB 
429-201-1 advises replacing the blower, while this AD makes no 
allowance for replacing the blower except by alternate means of 
compliance. If fasteners are missing or loose but the motor is secure, 
SB 429-201-1 advises replacing missing fasteners and removing and 
reinstalling existing fasteners with thread locker and a torque stripe. 
This AD requires removing the blower assembly if fasteners are missing 
or loose but the motor is still secure. SB 429-201-1 does not require 
repetitive inspections, while this AD requires the inspection every 25 
hours time-in-service until the air conditioning system is deactivated.

Interim Action

    We consider this AD to be an interim action. The inspection report 
that is required by this AD will enable us to obtain better insight 
into the cause of the motor's detachment, and help us develop final 
action to address this unsafe condition. The design approval holder is 
also currently developing a modification that will address the unsafe 
condition identified in this AD. Once this modification is developed, 
approved, and available, we might consider additional rulemaking.

Costs of Compliance

    We estimate that this AD affects 78 helicopters of U.S. Registry 
and that labor costs average $85 per work-hour. Based on these 
estimates, we expect the following costs:
     Inspecting the motor attachment requires 1 work-hour and 
no parts for a total cost of $85 per helicopter, and $6,630 for the 
U.S. fleet, per inspection cycle.
     Removing the motor and deactivating the air conditioning 
requires 2 work-hours and no parts for a total cost of $170 per 
helicopter.
     Removing the blower assembly and deactivating the air 
conditioning requires 13 work-hours and no parts for a total cost of 
$1,105 per helicopter.
     Reporting the findings to the FAA requires 1 work-hour and 
no parts for a total cost of $85 per helicopter.

Paperwork Reduction Act

    A federal agency may not conduct or sponsor, and a person is not 
required to respond to, nor shall a person be subject to penalty for 
failure to comply with a collection of information subject to the 
requirements of the Paperwork Reduction Act unless that collection of 
information displays a current valid OMB control number. The control 
number for the collection of information required by this AD is 2120-
0056. The

[[Page 17105]]

paperwork cost associated with this AD has been detailed in the Costs 
of Compliance section of this document and includes time for reviewing 
instructions, as well as completing and reviewing the collection of 
information. Therefore, all reporting required by this AD is mandatory. 
Comments concerning the accuracy of this burden and suggestions for 
reducing the burden should be directed to the FAA at 800 Independence 
Ave. SW., Washington, DC 20591. ATTN: Information Collection Clearance 
Officer, AES-200.

FAA's Justification and Determination of the Effective Date

    Providing an opportunity for public comments prior to adopting 
these AD requirements would delay implementing the safety actions 
needed to correct this known unsafe condition. Therefore, we found and 
continue to find that the risk to the flying public justifies waiving 
notice and comment prior to the adoption of this rule because the 
required initial inspection must be accomplished before further flight 
and the recurring inspection must be accomplished at intervals not to 
exceed 25 hours TIS. These helicopters, typically used for police and 
medical transport, are expected to reach 25 hours TIS within a few 
weeks.
    Since it was found that immediate corrective action was required, 
notice and opportunity for prior public comments before issuing this AD 
were impracticable and contrary to public interest and good cause 
existed to make the AD effective immediately by Emergency AD 2017-05-
51, issued on March 3, 2017, to all known U.S. owners and operators of 
these helicopters. These conditions still exists and the AD is hereby 
published in the Federal Register as an amendment to section 39.13 of 
the Federal Aviation Regulations (14 CFR 39.13) to make it effective to 
all persons.

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, 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 to the extent that 
it justifies making a regulatory distinction; 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.
    We prepared an economic evaluation of the estimated costs to comply 
with this AD and placed it in the AD docket.

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 airworthiness 
directive (AD):

2017-05-51 Bell Helicopter Textron Canada: Amendment 39-18847; 
Docket No. FAA-2017-0189; Directorate Identifier 2017-SW-008-AD.

(a) Applicability

    This AD applies to Bell Helicopter Textron Canada (Bell) Model 429 
helicopters with an Air Comm Corporation air conditioning system part 
number (P/N) 429EC-200 or 429EC-202 installed, certificated in any 
category.
    Note 1 to paragraph (a) of this AD: Air conditioning system P/N 
429EC-200 and 429EC-202 are identifiable by a three-screw installation 
as depicted in Figure 1 of Air Comm Corporation Service Bulletin 429-
201-1, Revision NC, dated February 17, 2017 (SB 429-201-1).

(b) Unsafe Condition

    This AD defines the unsafe condition as a condenser blower motor 
(motor) detaching from the condenser blower support (shroud). This 
condition could lead to failure of the primary flight controls and 
subsequent loss of helicopter control.

(c) Effective Date

    This AD becomes effective April 25, 2017 to all persons except 
those persons to whom it was made immediately effective by Emergency AD 
2017-05-51, issued on March 3, 2017, which contains the requirements of 
this AD.

(d) Compliance

    You are responsible for performing each action required by this AD 
within the specified compliance time unless it has already been 
accomplished prior to that time.

(e) Required Actions

    Before further flight, and thereafter at intervals not to exceed 25 
hours time-in-service:
    (1) Inspect the motor and condenser blower to determine whether the 
motor is attached to the shroud.
    (i) If the motor is not attached, before further flight:
    (A) Inspect the collective flight control tube for loss of 
protective primer, a scratch, any gouging, and a dent. If there is any 
loss of protective primer, a scratch, any gouging, or a dent, repair or 
replace the control tube.
    (B) Inspect the area under the forward transmission cowling for 
loss of protective primer, a scratch, any gouging, and a dent. Inspect 
each wiring harness for any cuts, chafing, and exposed wires. If there 
is any loss of protective primer, a scratch, any gouging, a dent, or if 
any wiring harness has a cut, chafing, or an exposed wire, repair or 
replace the affected parts.
    (C) Inspect the area under the forward transmission cowling for the 
three fasteners as depicted in Figure 1 of SB 429-201-1. Also inspect 
for the crimp-on external fan retaining ring (crimp ring) and the 
slotted fan drive spring (commonly known as a roll pin), which may have 
fallen loose with the motor.

[[Page 17106]]

Remove any fasteners, the crimp ring, and the roll pin if found 
detached.
    (D) Deactivate the air conditioning system by following the 
instructions in Procedure, paragraphs B.2.d.i. through B.2.d.v., of SB 
429-201-1.
    (ii) If the motor is attached to the shroud but a fastener is 
missing or loose, before further flight:
    (A) Remove any detached fasteners found in the area under the 
forward transmission cowling.
    (B) Deactivate the air conditioning system as follows:
    (1) Pull and red collar the air conditioning COND circuit breaker.
    (2) Pull and red collar the air-conditioning COMP circuit breaker.
    (3) Remove the compressor drive belt.
    (4) Remove the condenser blower assembly.
    (2) Deactivating the air conditioning system as required by 
paragraph (e)(1) of this AD constitutes terminating action for the 
repetitive inspections required by paragraph (e)(1) of this AD.
    (3) If the air conditioning system is deactivated as required by 
paragraph (e)(1) of this AD, within 10 days after completing the 
inspection, report the information requested in Appendix 1 to this AD 
by mail to the Manager, Denver Aircraft Certification Office, FAA, 
Technical Operations Center, 26805 East 68th Avenue, Room 214, Denver, 
CO 80249, ATTN: Matthew Bryant; by fax to (303) 342-1088; or by email 
to Matthew.Bryant@faa.gov.

(f) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Denver Aircraft Certification Office, FAA, may 
approve AMOCs for this AD. Send your proposal to: Matthew Bryant, 
Aerospace Engineer, Denver Aircraft Certification Office, FAA, 
Technical Operations Center, 26805 East 68th Avenue, Room 214, Denver, 
CO 80249; fax (303) 342-1088; email Matthew.Bryant@faa.gov.
    (2) For operations conducted under a 14 CFR part 119 operating 
certificate or under 14 CFR part 91, subpart K, we suggest that you 
notify your principal inspector, or lacking a principal inspector, the 
manager of the local flight standards district office or certificate 
holding district office before operating any aircraft complying with 
this AD through an AMOC.

(g) Subject

    Joint Aircraft Service Component (JASC) Code: 2150, Cabin Cooling 
System.

(h) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the incorporation 
by reference 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) Air Comm Corporation Service Bulletin 429-201-1, Revision NC, 
dated February 17, 2017.
    (ii) Reserved.
    (3) For Air Comm Corporation service information identified in this 
AD, contact Air Comm Corporation, 1575 West 124th Avenue, Westminster, 
CO 80234; telephone: (303) 440-4075 (during business hours) or (720) 
233-8330 (after hours); email: service@aircommcorp.com; Web site: 
https://www.aircommcorp.com/contact.
    (4) You may view this service information at FAA, Office of the 
Regional Counsel, Southwest Region, 10101 Hillwood Pkwy, Room 6N-321, 
Fort Worth, TX 76177. For information on the availability of this 
material at the FAA, call (817) 222-5110.
    (5) You may view this service information that is incorporated by 
reference at the National Archives and Records Administration (NARA). 
For information on the availability of this material at NARA, call 
(202) 741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Fort Worth, Texas, on March 29, 2017.

Scott A. Horn,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.

Appendix 1 to AD 2017-05-51

    Provide the following information by mail to the Manager, Denver 
Aircraft Certification Office, FAA, Technical Operations Center, 26805 
East 68th Avenue, Room 214, Denver, CO 80249, ATTN: Matthew Bryant; by 
fax to (303) 342-1088; or by email to Matthew.Bryant@faa.gov:
    For inspection being accomplished (Initial or Repetitive), record 
inspection findings below and provide photos if possible.

------------------------------------------------------------------------
             AD 2017-05-51                     Inspection findings
------------------------------------------------------------------------
Aircraft S/N or N-Number...............  Aircraft hours time-in-service
                                          (TIS).
Air Conditioner Installation S/N (Laser  Aircraft TIS when air
 etched on compressor mount).             conditioning system was
                                          installed.
                                         Estimated percent air
                                          conditioner operating time.
Aircraft Location......................  Operator and maintenance
                                          facility contact information.
Condition..............................  Findings.
Is this a single evaporator              ...............................
 installation or a dual evaporator
 installation?.
Was the motor still attached?..........  ...............................
Were there any missing or loose          ...............................
 fasteners?.
Were any of the loose fasteners found    ...............................
 in the surrounding area?.
Did the found fasteners show evidence    ...............................
 of thread locker being applied?.
Has the condenser blower (blower) been   ...............................
 replaced following the initial
 installation of the air conditioning
 system?
What was the reason for the blower       ...............................
 replacement?.
Aircraft TIS when blower was replaced..  ...............................
------------------------------------------------------------------------

[FR Doc. 2017-06710 Filed 4-7-17; 8:45 am]
 BILLING CODE 4910-13-P
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