Airworthiness Directives; ATR-GIE Avions de Transport Régional Airplanes, 223-229 [2017-28147]

Download as PDF Federal Register / Vol. 83, No. 2 / Wednesday, January 3, 2018 / Rules and Regulations DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2017–1177; Product Identifier 2015–NM–195–AD; Amendment 39–19139; AD 2017–26–08] RIN 2120–AA64 Airworthiness Directives; ATR–GIE ´ Avions de Transport Regional Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: We are adopting a new airworthiness directive (AD) for certain ´ ATR–GIE Avions de Transport Regional Model ATR42–500 and ATR72–212A airplanes. This AD requires revising the airplane flight manual (AFM) to provide procedures to the flight crew for operational restrictions affecting inflight use of the autopilot (AP) or yaw damper (YD) during dual-engine operation. This AD also provides an optional software modification, which would terminate the AFM requirement. This AD was prompted by flight test evaluations that revealed that after engine failure during AP or YD reengagement, the YD unit commanded the rudder to return to neutral position, leading to inadequate balancing of the asymmetric power. We are issuing this AD to address the unsafe condition on these products. DATES: This AD becomes effective January 18, 2018. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of January 18, 2018. We must receive comments on this AD by February 20, 2018. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. jstallworth on DSKBBY8HB2PROD with RULES SUMMARY: VerDate Sep<11>2014 15:15 Jan 02, 2018 Jkt 244001 For service information identified in this final rule, contact ATR–GIE Avions ´ ´ de Transport Regional, 1, Allee Pierre Nadot, 31712 Blagnac Cedex, France; telephone +33 (0) 5 62 21 62 21; fax +33 (0) 5 62 21 67 18; email continued.airworthiness@atraircraft.com. You may view this referenced service information at the FAA, Transport Standards Branch, 1601 Lind Avenue SW, Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. It is also available on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2017– 1177. 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– 1177; 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, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Shahram Daneshmandi, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 1601 Lind Avenue SW, Renton, WA 98057– 3356; telephone 425–227–1112; fax 425–227–1149. SUPPLEMENTARY INFORMATION: Discussion The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2015– 00237R1, dated December 16, 2015 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’) to correct an unsafe condition for certain ATR–GIE Avions ´ de Transport Regional Model ATR42– 500 and ATR72–212A airplanes. The MCAI states: During flight evaluations performed on Flight Synthetic Test Devices of ATR airplanes equipped with New Avionics Suite (also known as ‘Glass Cockpit’), with one Air Data Computer (ADC) or one Attitude and Heading Reference System (AHRS) inoperative, it was found that, after engine failure during autopilot (AP) or Yaw Damper (YD) re-engagement, the YD unit commanded the rudder to return to neutral position leading to inadequate balancing of the asymmetric power. Subsequent flight tests confirmed the YD unit behavior observed during flight PO 00000 Frm 00015 Fmt 4700 Sfmt 4700 223 simulator evaluation and identified that a software issue is the root cause of this system reaction. Additionally, it was identified that the failure of one of the Direct Current (DC) Generators with a concurrent shutdown of the opposite engine leads to loss of the AHRS#2 and ADC#2 and resulting in YD command the rudder into neutral position. This condition, if not corrected, could result in loss of control of the airplane. To address this potential unsafe condition EASA issued AD 2015–0230 to introduce operational restrictions affecting in-flight use of AP and/or YD with an inoperative AHRS, or ADC and the relevant dispatch limitations. Since that [EASA] AD was issued, it was determined that airplanes modified in service by incorporating New Avionics Suite Standard 2 are not affected and that the operation of an airplane with combination of inoperative ADC, AHRS and DC Generator items is allowed. Additional investigation has resulted in prohibiting the use of AP or YD also in case of both engine operative, when an ADC or an AHRS becomes inoperative. For the reasons described above, this [EASA] AD retains the requirements of EASA AD 2015–0230, which is superseded, and introduces AP or YD operational restrictions applicable for dual engine operation. This [EASA] AD is considered an interim action and further [EASA] AD action may follow. This [EASA] AD is revised to specify the Reason leading to AD issuance. Required actions also include AP or YD operational restrictions applicable for dual engine operation. You may examine the MCAI on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2017– 1177. Related Service Information Under 1 CFR Part 51 ´ Avions de Transport Regional has issued ATR Service Bulletin ATR42– 31–0091, Revision 1, dated May 05, 2015; and ATR Service Bulletin ATR72– 31–1092, Revision 2, dated March 31, 2015. The service information describes procedures for, among other things, modifying the software for the integrated avionics display (IAD), the core processing module (CPM), the switch module (SWM), and the flight warning main configuration file (FWMCF). These documents are distinct since they apply to different airplane models. 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. FAA’s Determination and Requirements of This AD This product has been approved by the aviation authority of another E:\FR\FM\03JAR1.SGM 03JAR1 224 Federal Register / Vol. 83, No. 2 / Wednesday, January 3, 2018 / Rules and Regulations country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are issuing this AD because we evaluated all pertinent information and determined the unsafe condition exists and is likely to exist or develop on other products of these same type designs. FAA’s Determination of the Effective Date There are currently no domestic operators of this product. Therefore, we find good cause that notice and opportunity for prior public comment are unnecessary. In addition, for the reason(s) stated above, we find that good cause exists for making this amendment effective in less than 30 days. Comments Invited This AD is a final rule that involves requirements affecting flight safety, and we did not precede it by notice and opportunity for public comment. We invite you to send any written relevant data, views, or arguments about this AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2017–1177; Product Identifier 2015–NM–195–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this AD. We will consider all comments received by the closing date and may amend this AD based on those comments. We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this AD. jstallworth on DSKBBY8HB2PROD with RULES Costs of Compliance Currently, there are no affected U.S.registered airplanes. If an affected airplane is imported and placed on the U.S. Register in the future, we provide the following cost estimates to comply with this AD: We estimate that it will take about 1 work-hour per product to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this AD will be $85 per product. In addition, we estimate that the optional modification will take about 3 work-hours for a cost of $255 per product. VerDate Sep<11>2014 15:15 Jan 02, 2018 Jkt 244001 Authority for This Rulemaking Adoption of the Amendment Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ‘‘Subtitle VII: Aviation Programs,’’ describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in ‘‘Subtitle VII, Part A, Subpart III, Section 44701: General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. This AD is issued in accordance with authority delegated by the Executive Director, Aircraft Certification Service, as authorized by FAA Order 8000.51C. In accordance with that order, issuance of ADs is normally a function of the Compliance and Airworthiness Division, but during this transition period, the Executive Director has delegated the authority to issue ADs applicable to transport category airplanes to the Director of the System Oversight Division. Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: Regulatory Findings We determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska; and 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. 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): ■ 2017–26–08 ATR–GIE Avions de Transport ´ Regional: Amendment 39–19139; Docket No. FAA–2017–1177; Product Identifier 2015–NM–195–AD. (a) Effective Date This AD becomes effective January 18, 2018. (b) Affected ADs None. (c) Applicability This AD applies to ATR–GIE Avions de ´ Transport Regional Model ATR42–500 airplanes, and Model ATR72–212A airplanes; certificated in any category; all manufacturer serial numbers on which ATR–GIE Avions de ´ Transport Regional Modification 5948 (New Avionics Suite installation) has been embodied in production, except those airplanes identified in paragraphs (c)(1) and (c)(2) of this AD. (1) Airplanes on which ATR–GIE Avions ´ de Transport Regional Mod 6977 (New Avionics Suite Standard 2) has been embodied in production. (2) Airplanes on which ATR Service Bulletin ATR42–31–0091, or ATR Service Bulletin ATR72–31–1092, has been incorporated. (d) Subject Air Transport Association (ATA) of America Code 31, Instruments. (e) Reason This AD was prompted by flight evaluations that revealed that after engine failure during autopilot (AP) or yaw damper (YD) re-engagement, the YD unit commanded the rudder to return to neutral position, leading to inadequate balancing of the asymmetric power. We are issuing this AD to provide procedures to the flightcrew for operational restrictions affecting in-flight use of the autopilot (AP) or yaw damper (YD) during dual-engine operation. List of Subjects in 14 CFR Part 39 (f) Compliance Comply with this AD within the compliance times specified, unless already done. Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. (g) Revise the Airplane Flight Manual Within 30 days after the effective date of this AD, revise the Limitations Section of the PO 00000 Frm 00016 Fmt 4700 Sfmt 4700 E:\FR\FM\03JAR1.SGM 03JAR1 Federal Register / Vol. 83, No. 2 / Wednesday, January 3, 2018 / Rules and Regulations 225 of an airplane by inserting a copy of this AD into the applicable AFM of that airplane is acceptable to comply with the requirements of this paragraph for that airplane. (h) Minimum Equipment List (MEL) (1) Within 30 days after the effective date of this AD, amend the operator’s ATR MEL, as applicable, by incorporating the dispatch restrictions listed in figure 2 to paragraph (h)(1) of this AD, and thereafter operate the airplane accordingly. ER03JA18.005</GPH> BILLING CODE 4910–13–P VerDate Sep<11>2014 15:15 Jan 02, 2018 Jkt 244001 PO 00000 Frm 00017 Fmt 4700 Sfmt 4725 E:\FR\FM\03JAR1.SGM 03JAR1 ER03JA18.004</GPH> jstallworth on DSKBBY8HB2PROD with RULES applicable ATR–42 and ATR–72 airplane flight manuals (AFMs) to include figure 1 to paragraph (g) of this AD. Amending the AFM 226 Federal Register / Vol. 83, No. 2 / Wednesday, January 3, 2018 / Rules and Regulations Figure 2 to paragraph (h)(l) ofthis AD- MEL Amendment continued (1.2) Associated procedures Dispatch Deviation Guide ATA 24- ELECTRICAL POWER 30-1 DC generator channel (generator+ related GCU) OPERATIONAL PROCEDURES: )> Check of remaining generator feeder integrity: 6 minutes are necessary to establish the temperature difference between the feeders if one line is broken. So aircraft should not line up until 6 minutes elapsed after operative generator comes on line. )> Operational test of TRU (if installed): Note: During the test, the ACW electrical network must be available (The AC GPU connected or ACW generators running). Checking are performed only on Main Electrical Panel (left hand panel): - Switch OFF the pushbutton DC EXTERNAL POWER (if selected ON) - Switch OFF the push buttons DC GEN 1 & 2 (if selected ON) On Main Electrical Panel; check that the following caution lights are switched ON: - BATTERY ARROWS - Both BUS OFF - INVERTER 2 FAULT - Both DC BUS OFF - SHED LEGEND OF DC SVCE/UTLY BUS Check that the following systems are supplied: -VHF 1 - FUEL QTY INDICATOR - FLAPS POSITION INDICATOR On Main Electrical Panel; press the TRU push-button; then check that: - The TRU push-button is switched ON - The TRU ARROW caution light is switched ON - The BATIERIES ARROWS caution lights are not illuminated - The UNDV legend of OVRD/UNDV push-button is not illuminated On Main Electrical Panel, check that the BATIERY AMMETER shows zero load either if BAT selector switch is placed in EMER or MAIN position. Check that the following systems are still supplied: -VHF 1 - FUEL QTY INDICATOR - FLAPS POSITION INDICATOR On Main Electrical Panel, switch off the TRU push-button; then check that: - The TRU push-button is not illuminated - The TRU ARROW caution light is not illuminated - The BATIERY ARROWS caution lights are switched ON - Pull C/B AFCS/YAW SERVO, secure and tag VerDate Sep<11>2014 15:15 Jan 02, 2018 Jkt 244001 PO 00000 Frm 00018 Fmt 4700 Sfmt 4725 E:\FR\FM\03JAR1.SGM 03JAR1 ER03JA18.006</GPH> jstallworth on DSKBBY8HB2PROD with RULES MAINTENANCE PROCEDURES: Federal Register / Vol. 83, No. 2 / Wednesday, January 3, 2018 / Rules and Regulations 227 Figure 2 to paragraph (h)(l) of this AD- MEL Amendment continued ADC or AHRS fault (2) (2.1) Dispatch conditions ATA 34- NAVIGATION ATA CHAPTER 1 2- REPAIR INTERVAL CATEGORY 3- NUMBER INSTALLED 4- NUMBER REQUIRED FOR DISPATCH ITEM - 5- REMARKS OR CONDITIONS Air Data System 11-1 Air Data Computer (ADC) A 2 1 * (o) (m) One ADC may be inoperative provided: (a) The Autopilot and Yaw Damper are deactivated, and (b) TheTLU manual mode is operative (c) The IESI is operative, and (d) All the IOM DC are operative, and (e) The operations are limited to two flights, and (f) For day VMC flight only, and (g) ForETOPS, the ADC#1 must be operative Note: When TLU automatic mode is inoperative Refer to MMEL 27 item 23-2 - Attitude- Heading 20-1 AHRS A 2 1 * (m) One may be inoperative, provided: (a) The Autopilot and Yaw Damper are deactivated, and (b) TheiESiisoperative,and (c) For dayVMC flight only, and (d) Operations are limited to two flights, and (e) ForETOPS,AHRS#1must be operative VerDate Sep<11>2014 15:15 Jan 02, 2018 Jkt 244001 PO 00000 Frm 00019 Fmt 4700 Sfmt 4725 E:\FR\FM\03JAR1.SGM 03JAR1 ER03JA18.007</GPH> jstallworth on DSKBBY8HB2PROD with RULES This new dispatch condition only supersedes the related current approved MMEL items, on the basis of which the operator's MEL is established, applicable to ATR 42-500 and ATR 72-212A fitted with ATR Modification 5948, except airplanes modified in accordance with ATR modification 6977, the others dispatch conditions remain valid. Federal Register / Vol. 83, No. 2 / Wednesday, January 3, 2018 / Rules and Regulations jstallworth on DSKBBY8HB2PROD with RULES BILLING CODE 4910–13–C (2) Amending the operator’s ATR MEL, as applicable, of an airplane by inserting a copy of this AD, or incorporating a later MMEL revision which includes the same dispatch restrictions as specified in figure 2 to paragraph (h)(1) of this AD is acceptable for compliance with the requirements of paragraph (h)(1) of this AD for that airplane. (3) As of the effective date of this AD: If any of the systems identified in paragraph (h)(3)(i), (h)(3)(ii), and (h)(3)(iii) of this AD are inoperative, an airplane may be operated as specified in the MMEL, provided that the MEL of that airplane has been amended to be consistent with the MEL restrictions specified in figure 2 of this AD. (i) One of two ADCs. (ii) One of two AHRSs. (iii) One of two DC generators. (i) Optional Software Modification Installation of new avionics suite standard 2 software on an airplane, in accordance with the Accomplishment Instructions of ATR Service Bulletin ATR42–31–0091, Revision 1, VerDate Sep<11>2014 15:15 Jan 02, 2018 Jkt 244001 dated May 05, 2015, or ATR Service Bulletin ATR72–31–1092, Revision 2, dated March 31, 2015, as applicable, terminates the AFM and MEL revisions required by paragraphs (g) and (h) of this AD, for that airplane. (j) Credit for Previous Actions This paragraph provides credit for actions required by paragraph (i) of this AD, if those actions were performed before the effective date of this AD using ATR Service Bulletin ATR42–31–0091, dated December 17, 2014; or ATR Service Bulletin ATR72–31–1092, dated October 7, 2014, or Revision 1, dated December 9, 2014, as applicable. (k) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Section, Transport Standards Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal PO 00000 Frm 00020 Fmt 4700 Sfmt 4700 inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Section, send it to the attention of the person identified in paragraph (l)(2) of this AD. Information may be emailed to: 9-ANM-116-AMOCREQUESTS@faa.gov. 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. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or EASA; ´ or ATR–GIE Avions de Transport Regional’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. (l) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD E:\FR\FM\03JAR1.SGM 03JAR1 ER03JA18.008</GPH> 228 Federal Register / Vol. 83, No. 2 / Wednesday, January 3, 2018 / Rules and Regulations 2015–00237R1, dated December 16, 2015, for related information. You may examine the MCAI on the internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2017–1177. (2) For more information about this AD, contact Shahram Daneshmandi, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 1601 Lind Avenue SW, Renton, WA 98057–3356; telephone 425–227–1112; fax 425–227–1149. (3) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (m)(3) and (m)(4) of this AD. (m) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (i) ATR Service Bulletin ATR42–31–0091, Revision 1, dated May 05, 2015. (ii) ATR Service Bulletin ATR72–31–1092, Revision 2, dated March 31, 2015. (3) For service information identified in this AD, contact ATR–GIE Avions de ´ ´ Transport Regional, 1, Allee Pierre Nadot, 31712 Blagnac Cedex, France; telephone +33 (0) 5 62 21 62 21; fax +33 (0) 5 62 21 67 18; email continued.airworthiness@atraircraft.com. (4) You may view this service information at the FAA, Transport Standards Branch, 1601 Lind Avenue SW, Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Renton, Washington, on December 20, 2017. Michael Kaszycki, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2017–28147 Filed 1–2–18; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration jstallworth on DSKBBY8HB2PROD with RULES 14 CFR Part 39 [Docket No. FAA–2017–0519; Product Identifier 2017–NM–001–AD; Amendment 39–19138; AD 2017–26–07] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. AGENCY: VerDate Sep<11>2014 15:15 Jan 02, 2018 Jkt 244001 ACTION: Final rule. We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 757–200, –200CB, and –300 series airplanes. This AD was prompted by a report of fatigue cracking found in a certain fuselage frame web. This AD requires inspection of the fuselage frame for existing repairs, repetitive inspections of the frame, and applicable repairs. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective February 7, 2018. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of February 7, 2018. ADDRESSES: For service information identified in this final rule, contact Boeing Commercial Airplanes, Attention: Contractual & Data Services (C&DS), 2600 Westminster Blvd., MC 110–SK57, Seal Beach, CA 90740; telephone 562–797–1717; internet https://www.myboeingfleet.com. You may view this service information at the FAA, Transport Standards Branch, 1601 Lind Avenue SW, Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. It is also available on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2017– 0519. SUMMARY: Examining the AD Docket You may examine the AD docket on the internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2017– 0519; 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 final rule, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (phone: 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: Muoi Vuong, Aerospace Engineer, Airframe Section, FAA, Los Angeles ACO Branch, 3960 Paramount Boulevard, Lakewood, CA 90712–4137; phone: 562–627–5205; fax: 562–627– 5210; email: muoi.vuong@faa.gov. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR PO 00000 Frm 00021 Fmt 4700 Sfmt 4700 229 part 39 by adding an AD that would apply to certain The Boeing Company Model 757–200, –200CB, and –300 series airplanes. The NPRM published in the Federal Register on June 2, 2017 (82 FR 25550). The NPRM was prompted by a report of fatigue cracking found in the fuselage frame web at station (STA) 1681, below the floor line at stringer S–17L. The NPRM proposed to require inspection of the fuselage frame for existing repairs, repetitive inspections of the frame, and applicable repairs. We are issuing this AD to detect and correct cracking of the fuselage frame at STA 1681, which could result in reduced structural integrity of the airplane. Comments We gave the public the opportunity to participate in developing this final rule. The following presents the comments received on the NPRM and the FAA’s response to each comment. Support for the NPRM United Airlines agreed with the content of the NPRM, and has started the proposed inspections. FedEx’s fleet of Model 757–200 airplanes was converted by VT Mobile Aerospace Engineering, Inc. (VT MAE), supplemental type certificate (STC) ST03562AT to a configuration similar to that of Boeing Model 757–200SF airplanes, and is no longer configured as passenger airplanes. FedEx stated, however, that per the VT MAE comments to the NPRM, the AD would still be effective for the converted FedEx fleet. FedEx noted that VT MAE has recommended that the airplane configuration groups identified in Boeing Alert Service Bulletin 757– 53A0100, dated November 14, 2016, apply to the FedEx fleet. FedEx stated that it agrees with the airplane configuration groups cited by VT MAE and will comply with the actions in the proposed AD accordingly. Request To Reference the Latest Service Information Boeing asked that we add Boeing Alert Service Bulletin 757–53A0100, Revision 1, dated September 14, 2017, to paragraphs (c), (g), (h)(1), and (h)(2) of the proposed AD as an alternative to using Boeing Alert Service Bulletin 757–53A0100, dated November 14, 2016 (referenced in the NPRM as the appropriate source of service information for accomplishing the actions). Boeing stated that the revised service information provides alternative inspections that allow longer inspection intervals. E:\FR\FM\03JAR1.SGM 03JAR1

Agencies

[Federal Register Volume 83, Number 2 (Wednesday, January 3, 2018)]
[Rules and Regulations]
[Pages 223-229]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-28147]



[[Page 223]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-1177; Product Identifier 2015-NM-195-AD; Amendment 
39-19139; AD 2017-26-08]
RIN 2120-AA64


Airworthiness Directives; ATR-GIE Avions de Transport 
R[eacute]gional Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
ATR-GIE Avions de Transport R[eacute]gional Model ATR42-500 and ATR72-
212A airplanes. This AD requires revising the airplane flight manual 
(AFM) to provide procedures to the flight crew for operational 
restrictions affecting in-flight use of the autopilot (AP) or yaw 
damper (YD) during dual-engine operation. This AD also provides an 
optional software modification, which would terminate the AFM 
requirement. This AD was prompted by flight test evaluations that 
revealed that after engine failure during AP or YD re-engagement, the 
YD unit commanded the rudder to return to neutral position, leading to 
inadequate balancing of the asymmetric power. We are issuing this AD to 
address the unsafe condition on these products.

DATES: This AD becomes effective January 18, 2018.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of January 18, 
2018.
    We must receive comments on this AD by February 20, 2018.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE, Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE, Washington, DC, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.
    For service information identified in this final rule, contact ATR-
GIE Avions de Transport R[eacute]gional, 1, All[eacute]e Pierre Nadot, 
31712 Blagnac Cedex, France; telephone +33 (0) 5 62 21 62 21; fax +33 
(0) 5 62 21 67 18; email aircraft.com">[email protected]aircraft.com. You 
may view this referenced service information at the FAA, Transport 
Standards Branch, 1601 Lind Avenue SW, Renton, WA. For information on 
the availability of this material at the FAA, call 425-227-1221. It is 
also available on the internet at http://www.regulations.gov by 
searching for and locating Docket No. FAA-2017-1177.

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-
1177; 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, the regulatory evaluation, any comments received, and 
other information. The street address for the Docket Operations office 
(telephone 800-647-5527) is in the ADDRESSES section. Comments will be 
available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Shahram Daneshmandi, Aerospace 
Engineer, International Section, Transport Standards Branch, FAA, 1601 
Lind Avenue SW, Renton, WA 98057-3356; telephone 425-227-1112; fax 425-
227-1149.

SUPPLEMENTARY INFORMATION: 

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA AD 
2015-00237R1, dated December 16, 2015 (referred to after this as the 
Mandatory Continuing Airworthiness Information, or ``the MCAI'') to 
correct an unsafe condition for certain ATR-GIE Avions de Transport 
R[eacute]gional Model ATR42-500 and ATR72-212A airplanes. The MCAI 
states:

    During flight evaluations performed on Flight Synthetic Test 
Devices of ATR airplanes equipped with New Avionics Suite (also 
known as `Glass Cockpit'), with one Air Data Computer (ADC) or one 
Attitude and Heading Reference System (AHRS) inoperative, it was 
found that, after engine failure during autopilot (AP) or Yaw Damper 
(YD) re-engagement, the YD unit commanded the rudder to return to 
neutral position leading to inadequate balancing of the asymmetric 
power.
    Subsequent flight tests confirmed the YD unit behavior observed 
during flight simulator evaluation and identified that a software 
issue is the root cause of this system reaction.
    Additionally, it was identified that the failure of one of the 
Direct Current (DC) Generators with a concurrent shutdown of the 
opposite engine leads to loss of the AHRS#2 and ADC#2 and resulting 
in YD command the rudder into neutral position.
    This condition, if not corrected, could result in loss of 
control of the airplane.
    To address this potential unsafe condition EASA issued AD 2015-
0230 to introduce operational restrictions affecting in-flight use 
of AP and/or YD with an inoperative AHRS, or ADC and the relevant 
dispatch limitations.
    Since that [EASA] AD was issued, it was determined that 
airplanes modified in service by incorporating New Avionics Suite 
Standard 2 are not affected and that the operation of an airplane 
with combination of inoperative ADC, AHRS and DC Generator items is 
allowed. Additional investigation has resulted in prohibiting the 
use of AP or YD also in case of both engine operative, when an ADC 
or an AHRS becomes inoperative.
    For the reasons described above, this [EASA] AD retains the 
requirements of EASA AD 2015-0230, which is superseded, and 
introduces AP or YD operational restrictions applicable for dual 
engine operation.
    This [EASA] AD is considered an interim action and further 
[EASA] AD action may follow.
    This [EASA] AD is revised to specify the Reason leading to AD 
issuance.

    Required actions also include AP or YD operational restrictions 
applicable for dual engine operation. You may examine the MCAI on the 
internet at http://www.regulations.gov by searching for and locating 
Docket No. FAA-2017-1177.

Related Service Information Under 1 CFR Part 51

    Avions de Transport R[eacute]gional has issued ATR Service Bulletin 
ATR42-31-0091, Revision 1, dated May 05, 2015; and ATR Service Bulletin 
ATR72-31-1092, Revision 2, dated March 31, 2015. The service 
information describes procedures for, among other things, modifying the 
software for the integrated avionics display (IAD), the core processing 
module (CPM), the switch module (SWM), and the flight warning main 
configuration file (FWMCF). These documents are distinct since they 
apply to different airplane models.
    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.

FAA's Determination and Requirements of This AD

    This product has been approved by the aviation authority of another

[[Page 224]]

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

FAA's Determination of the Effective Date

    There are currently no domestic operators of this product. 
Therefore, we find good cause that notice and opportunity for prior 
public comment are unnecessary. In addition, for the reason(s) stated 
above, we find that good cause exists for making this amendment 
effective in less than 30 days.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not precede it by notice and opportunity for public 
comment. We invite you to send any written relevant data, views, or 
arguments about this AD. Send your comments to an address listed under 
the ADDRESSES section. Include ``Docket No. FAA-2017-1177; Product 
Identifier 2015-NM-195-AD'' at the beginning of your comments. We 
specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this AD. We will consider all 
comments received by the closing date and may amend this AD based on 
those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this AD.

Costs of Compliance

    Currently, there are no affected U.S.-registered airplanes. If an 
affected airplane is imported and placed on the U.S. Register in the 
future, we provide the following cost estimates to comply with this AD:
    We estimate that it will take about 1 work-hour per product to 
comply with the basic requirements of this AD. The average labor rate 
is $85 per work-hour. Based on these figures, we estimate the cost of 
this AD will be $85 per product.
    In addition, we estimate that the optional modification will take 
about 3 work-hours for a cost of $255 per product.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation 
Programs,'' describes in more detail the scope of the Agency's 
authority.
    We are issuing this rulemaking under the authority described in 
``Subtitle VII, Part A, Subpart III, Section 44701: General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.
    This AD is issued in accordance with authority delegated by the 
Executive Director, Aircraft Certification Service, as authorized by 
FAA Order 8000.51C. In accordance with that order, issuance of ADs is 
normally a function of the Compliance and Airworthiness Division, but 
during this transition period, the Executive Director has delegated the 
authority to issue ADs applicable to transport category airplanes to 
the Director of the System Oversight Division.

Regulatory Findings

    We determined that this 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 the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979);
    3. Will not affect intrastate aviation in Alaska; and
    4. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

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

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):

2017-26-08 ATR-GIE Avions de Transport R[eacute]gional: Amendment 
39-19139; Docket No. FAA-2017-1177; Product Identifier 2015-NM-195-
AD.

(a) Effective Date

    This AD becomes effective January 18, 2018.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to ATR-GIE Avions de Transport R[eacute]gional 
Model ATR42-500 airplanes, and Model ATR72-212A airplanes; 
certificated in any category; all manufacturer serial numbers on 
which ATR-GIE Avions de Transport R[eacute]gional Modification 5948 
(New Avionics Suite installation) has been embodied in production, 
except those airplanes identified in paragraphs (c)(1) and (c)(2) of 
this AD.
    (1) Airplanes on which ATR-GIE Avions de Transport 
R[eacute]gional Mod 6977 (New Avionics Suite Standard 2) has been 
embodied in production.
    (2) Airplanes on which ATR Service Bulletin ATR42-31-0091, or 
ATR Service Bulletin ATR72-31-1092, has been incorporated.

(d) Subject

    Air Transport Association (ATA) of America Code 31, Instruments.

(e) Reason

    This AD was prompted by flight evaluations that revealed that 
after engine failure during autopilot (AP) or yaw damper (YD) re-
engagement, the YD unit commanded the rudder to return to neutral 
position, leading to inadequate balancing of the asymmetric power. 
We are issuing this AD to provide procedures to the flightcrew for 
operational restrictions affecting in-flight use of the autopilot 
(AP) or yaw damper (YD) during dual-engine operation.

(f) Compliance

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

(g) Revise the Airplane Flight Manual

    Within 30 days after the effective date of this AD, revise the 
Limitations Section of the

[[Page 225]]

applicable ATR-42 and ATR-72 airplane flight manuals (AFMs) to 
include figure 1 to paragraph (g) of this AD. Amending the AFM of an 
airplane by inserting a copy of this AD into the applicable AFM of 
that airplane is acceptable to comply with the requirements of this 
paragraph for that airplane.
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(h) Minimum Equipment List (MEL)

    (1) Within 30 days after the effective date of this AD, amend 
the operator's ATR MEL, as applicable, by incorporating the dispatch 
restrictions listed in figure 2 to paragraph (h)(1) of this AD, and 
thereafter operate the airplane accordingly.
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    (2) Amending the operator's ATR MEL, as applicable, of an 
airplane by inserting a copy of this AD, or incorporating a later 
MMEL revision which includes the same dispatch restrictions as 
specified in figure 2 to paragraph (h)(1) of this AD is acceptable 
for compliance with the requirements of paragraph (h)(1) of this AD 
for that airplane.
    (3) As of the effective date of this AD: If any of the systems 
identified in paragraph (h)(3)(i), (h)(3)(ii), and (h)(3)(iii) of 
this AD are inoperative, an airplane may be operated as specified in 
the MMEL, provided that the MEL of that airplane has been amended to 
be consistent with the MEL restrictions specified in figure 2 of 
this AD.
    (i) One of two ADCs.
    (ii) One of two AHRSs.
    (iii) One of two DC generators.

(i) Optional Software Modification

    Installation of new avionics suite standard 2 software on an 
airplane, in accordance with the Accomplishment Instructions of ATR 
Service Bulletin ATR42-31-0091, Revision 1, dated May 05, 2015, or 
ATR Service Bulletin ATR72-31-1092, Revision 2, dated March 31, 
2015, as applicable, terminates the AFM and MEL revisions required 
by paragraphs (g) and (h) of this AD, for that airplane.

(j) Credit for Previous Actions

    This paragraph provides credit for actions required by paragraph 
(i) of this AD, if those actions were performed before the effective 
date of this AD using ATR Service Bulletin ATR42-31-0091, dated 
December 17, 2014; or ATR Service Bulletin ATR72-31-1092, dated 
October 7, 2014, or Revision 1, dated December 9, 2014, as 
applicable.

(k) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Section, Transport Standards Branch, FAA, has the 
authority to approve AMOCs for this AD, if requested using the 
procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, 
send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the International Section, send it to the attention of 
the person identified in paragraph (l)(2) of this AD. Information 
may be emailed to: [email protected]. 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.
    (2) Contacting the Manufacturer: For any requirement in this AD 
to obtain corrective actions from a manufacturer, the action must be 
accomplished using a method approved by the Manager, International 
Section, Transport Standards Branch, FAA; or EASA; or ATR-GIE Avions 
de Transport R[eacute]gional's EASA Design Organization Approval 
(DOA). If approved by the DOA, the approval must include the DOA-
authorized signature.

(l) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA AD

[[Page 229]]

2015-00237R1, dated December 16, 2015, for related information. You 
may examine the MCAI on the internet at http://www.regulations.gov 
by searching for and locating Docket No. FAA-2017-1177.
    (2) For more information about this AD, contact Shahram 
Daneshmandi, Aerospace Engineer, International Section, Transport 
Standards Branch, FAA, 1601 Lind Avenue SW, Renton, WA 98057-3356; 
telephone 425-227-1112; fax 425-227-1149.
    (3) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (m)(3) and (m)(4) of this AD.

(m) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless this AD specifies otherwise.
    (i) ATR Service Bulletin ATR42-31-0091, Revision 1, dated May 
05, 2015.
    (ii) ATR Service Bulletin ATR72-31-1092, Revision 2, dated March 
31, 2015.
    (3) For service information identified in this AD, contact ATR-
GIE Avions de Transport R[eacute]gional, 1, All[eacute]e Pierre 
Nadot, 31712 Blagnac Cedex, France; telephone +33 (0) 5 62 21 62 21; 
fax +33 (0) 5 62 21 67 18; email aircraft.com">[email protected]aircraft.com.
    (4) You may view this service information at the FAA, Transport 
Standards Branch, 1601 Lind Avenue SW, Renton, WA. For information 
on the availability of this material at the FAA, call 425-227-1221.
    (5) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on December 20, 2017.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2017-28147 Filed 1-2-18; 8:45 am]
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