Airworthiness Directives; Airbus Helicopters, 2039-2042 [2018-00478]

Download as PDF Federal Register / Vol. 83, No. 10 / Tuesday, January 16, 2018 / Rules and Regulations Issued in Renton, Washington, on January 9, 2018. Victor Wicklund, Manager, Transport Standards Branch, Policy and Innovation Division, Aircraft Certification Service. telephone 425–227–2432; facsimile 425–227–1149. SUPPLEMENTARY INFORMATION: Background On April 22, 2016, the Federal Register published a document designated as Docket No. FAA–2015– 4279, Final Special Conditions No. 25– 612–SC (81 FR 23573). The document issued special conditions pertaining to the installation of non-rechargeable lithium batteries in Gulfstream GVI airplanes. As published, the document contained an error in a title 14, Code of Federal Regulations (14 CFR) section citation in two locations in the final special conditions document. These citations inadvertently referred to the wrong amendment level for the certification basis of the various Gulfstream GVI airplanes. Therefore, we have corrected these special conditions to include the correct citations and amendment levels that apply to certification bases applicable to airplanes with non-rechargeable lithium-ion battery installations. daltland on DSKBBV9HB2PROD with RULES Correction In the final special conditions document (FR Doc. 2016–09311 Filed 4–21–16; 8:45 a.m.), published on April 22, 2016 (81 FR 23573), make the following corrections. 1. On page 23574, second column, change the following paragraph: These special conditions apply to all non-rechargeable lithium battery installations in lieu of § 25.1353(b)(1) through (b)(4) at Amendment 25–113. Sections 25.1353(b)(1) through (b)(4) at Amendment 25–113 remain in effect for other battery installations. To read: These special conditions apply to all non-rechargeable lithium battery installations in lieu of § 25.1353(b)(1) through (4) at Amendment 25–123 or § 25.1353(c)(1) through (4) at earlier amendments. Those regulations remain in effect for other battery installations. 2. On page 23577, third column, change the following paragraph: In lieu of § 25.1353(b)(1) through (b)(4) at Amendment 25–113, each nonrechargeable lithium battery installation must: To read: In lieu of § 25.1353(b)(1) through (4) at Amendment 25–123, or § 25.1353(c)(1) through (4) at earlier amendments, each non-rechargeable lithium battery installation must: VerDate Sep<11>2014 16:55 Jan 12, 2018 Jkt 244001 [FR Doc. 2018–00547 Filed 1–12–18; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2017–0826; Product Identifier 2016–SW–084–AD; Amendment 39–19153; AD 2018–01–12] RIN 2120–AA64 Airworthiness Directives; Airbus Helicopters Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are superseding Airworthiness Directive (AD) 2015–22– 53 for Airbus Helicopters Model AS350B3 helicopters. AD 2015–22–53 required revising the rotorcraft flight manual (RFM) to perform the yaw load compensator check after rotor shutdown and to state that the yaw servo hydraulic switch must be in the ‘‘ON’’ position before taking off. Since we issued AD 2015–22–53, Airbus Helicopters developed a modification of the ACCU TST switch. This new AD retains the requirements of AD 2015– 22–53 and requires modifying the yaw servo hydraulic switch (collective switch) and replacing the ACCU TST button. The actions of this AD are intended to address an unsafe condition on these products. DATES: This AD is effective February 20, 2018. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of February 20, 2018. ADDRESSES: For Airbus Helicopters service information identified in this final rule, contact Airbus Helicopters, 2701 N. Forum Drive, Grand Prairie, TX 75052; telephone (972) 641–0000 or (800) 232–0323; fax (972) 641–3775; or at https://www.helicopters.airbus.com/ website/en/ref/Technical-Support_ 73.html. You may view this 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 SUMMARY: PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 2039 and locating Docket No. FAA–2017– 0826. Examining the AD Docket You may examine the AD docket on the internet at https:// www.regulations.gov in Docket No. FAA–2017–0826; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the European Aviation Safety Agency (EASA) AD, any incorporated-by-reference information, the economic evaluation, any comments received, and other information. The address for the Docket Office (phone: 800–647–5527) is Document Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: George Schwab, Aviation Safety Engineer, Safety Management Section, Rotorcraft Standards Branch, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222–5110; email george.schwab@faa.gov. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to remove AD 2015–22–53, Amendment 39–18331 (80 FR 74982, December 1, 2015) and add a new AD. AD 2015–22–53 applied to Airbus Helicopters Model AS350B3 helicopters with a dual hydraulic system installed. AD 2015–22–53 required revising the pre-flight and post-flight procedures in the RFM to perform the yaw load compensator check (ACCU TST switch) after rotor shut-down instead of during preflight procedures and to state that the yaw servo hydraulic switch (collective switch) must be in the ‘‘ON’’ (forward) position before taking off. The NPRM published in the Federal Register on September 8, 2017 (82 FR 42487). The NPRM was prompted by AD No. 2016–0220, dated November 4, 2016, issued by EASA, which is the Technical Agent for the Member States of the European Union, to correct an unsafe condition for Airbus Helicopters Model AS 350 B3 helicopters. EASA advises that further analysis resulted in the recognition that a pilot could forget to activate a switch despite the RFM changes and that altering the bistable push button (push-on, push-off) ACCU TST switch is necessary. Accordingly, the NPRM proposed to retain the requirements of AD 2015–22– 53 and also proposed to require, within E:\FR\FM\16JAR1.SGM 16JAR1 2040 Federal Register / Vol. 83, No. 10 / Tuesday, January 16, 2018 / Rules and Regulations 350 hours time-in-service, installing a timer relay for the yaw servo hydraulic switch, installing an additional light on the caution and warning panel, and replacing the bistable ACCU TST button with a monostable button. The proposed requirements were intended to prevent takeoff without hydraulic pressure in the tail rotor (T/R) hydraulic system, loss of T/R flight control, and subsequent loss of control of the helicopter. daltland on DSKBBV9HB2PROD with RULES Comments After our NPRM was published, we received comments from two commenters. Requests The National Transportation Safety Board (NTSB) requested that the AD address the need for an alert when there is insufficient pressure in the T/R hydraulic system, which results in increased pedal loads. In support of this request, the NTSB stated that, for at least four events it investigated in which the yaw servo hydraulic switch was likely not returned to its correct position before takeoff, a salient alert could have cued the pilots of insufficient T/R hydraulic pressure. We partially agree. We agree that an aural and visual alert to the pilot to indicate loss of T/R hydraulic pressure would address this unsafe condition. However, Airbus Helicopters has not developed an alteration that provides such an alert. The FAA has determined the requirements proposed by the NPRM are appropriate to address this unsafe condition at this time. Should an aural and visual alert to the pilot to indicate loss of T/R hydraulic pressure be developed and approved, we might consider additional rulemaking at that time. We did not change the AD based on this comment. The NTSB also requested that we eliminate the requirement to move the yaw load compensator check (ACCU TST switch) to post-flight procedures instead of preflight procedures. In support of this request, the NTSB stated that performing this check post-flight does not ensure the yaw load compensator will remain functional for the next flight. We disagree. We determined that requiring this check post-flight with the RFM procedure to have the yaw servo hydraulic switch in the ‘‘ON’’ position before takeoff, along with the alterations to the yaw servo hydraulic switch and replacement of the ACCU TST button, reduces the risk of takeoff with the switch in the incorrect position to an acceptable level. We did not change the AD based on this comment. VerDate Sep<11>2014 16:55 Jan 12, 2018 Jkt 244001 Eagle Copters requested we change the AD to address helicopters that have replaced the factory console with a Geneva Aviation P122 or P132 electrical console under Eagle Copters USA, Inc. Supplemental Type Certificate No. SH4747NM. In support of this request, Eagle Copters noted that operators of these helicopters will need to request an Alternative Method of Compliance to comply with the AD, because the Airbus Helicopters service information required for replacing the bistable ACCU TST button does not apply to these helicopters. Eagle Copters proposed adding a requirement to the AD to replace the HYD TEST/ACCU TEST ESN–11 switch on the console from the locking bistable toggle switch to a locking momentary (monostable) toggle switch part number (P/N) MS24658– 16F. We agree. We revised the AD to require helicopters with a P122 or P132 electrical console installed to replace the bistable ACCU TEST switch (which may be marked ‘‘HYD TEST’’) with monostable toggle switch P/N MS24658–16F. FAA’s Determination We have reviewed the relevant information and determined that an unsafe condition exists and is likely to exist or develop on other helicopters of the same type design and that air safety and the public interest require adopting the AD requirements as proposed with the change previously described. This change is consistent with the intent of the proposals in the NPRM and will not increase the economic burden on any operator nor increase the scope of the AD. Related Service Information Under 1 CFR Part 51 We reviewed Airbus Helicopters Service Bulletin (SB) No. AS350– 67.00.64, Revision 0, dated February 25, 2015. This service information specifies procedures to install a timer relay and an additional indicator light on the caution and warning panel. This modification provides an ‘‘OFF’’ status indication of the yaw servo hydraulic switch by flashing a newly installed ‘‘HYD2’’ indicator light on the caution and warning panel. Airbus Helicopters identifies performance of this SB as modification 074622. This modification was available when AD 2015–22–53 was issued; however, it was determined unnecessary to address the unsafe condition at that time. We also reviewed Airbus Helicopters SB No. AS350–67.00.65, Revision 0, dated August 25, 2016. This service information specifies procedures to PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 replace the bistable push button ACCU TST switch with a monostable push button switch. Airbus Helicopters identifies performance of this SB as modification 074719. 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. Other Related Service Information We reviewed Airbus Helicopters SB No. AS350–67.00.66, Revision 1, dated October 22, 2015. This service information specifies inserting specific pages of the SB into the rotorcraft flight manual. These pages revise the preflight and post-flight hydraulic checks by moving the T/R yaw load compensator check from preflight to post-flight. These pages also revise terminology within the flight manuals for the different engine configurations. Costs of Compliance We estimate that this AD affects 86 helicopters of U.S. Registry. We estimate that operators may incur the following costs in order to comply with this AD. Labor costs are estimated at $85 per work-hour. Revising an RFM would take about 0.5 work-hour for a cost of $43 per helicopter and $3,698 for the U.S. fleet. Installing a timer relay for the yaw servo hydraulic switch and an indicator light would take about 9 work-hours and parts would cost about $2,224. Replacing the ACCU TST button would take about 1 work-hour and parts would cost about $2,244. Based on these figures, we estimate a total cost of $5,361 per helicopter and $461,046 for the U.S. fleet. 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 E:\FR\FM\16JAR1.SGM 16JAR1 Federal Register / Vol. 83, No. 10 / Tuesday, January 16, 2018 / Rules and Regulations products identified in this rulemaking action. result in loss of T/R flight control and subsequent loss of control of the helicopter. Regulatory Findings We have determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Is not a ‘‘significant rule’’ under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation in Alaska to the extent that a regulatory, 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. (c) Affected ADs This AD supersedes AD 2015–22–53, Amendment 39–18331 (80 FR 74982, December 1, 2015). 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 removing Airworthiness Directive (AD) 2015–22–53, Amendment 39–18331 (80 FR 74982, December 1, 2015), and adding the following new AD: ■ daltland on DSKBBV9HB2PROD with RULES 2018–01–12 Airbus Helicopters: Amendment 39–19153; Docket No. FAA–2017–0826; Product Identifier 2016–SW–084–AD. (a) Applicability This AD applies to Model AS350B3 helicopters with a dual hydraulic system installed, certificated in any category. Note 1 to paragraph (a) of this AD: The dual hydraulic system for Model AS350B3 helicopters is referred to as Airbus modification OP 3082 or OP 3346. (b) Unsafe Condition This AD defines the unsafe condition as lack of hydraulic pressure in a tail rotor (T/R) hydraulic system. This condition could VerDate Sep<11>2014 16:55 Jan 12, 2018 Jkt 244001 (d) Effective Date This AD becomes effective February 20, 2018. (e) 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. (f) Required Actions (1) Before further flight, insert a copy of this AD into the rotorcraft flight manual, Section 4 Normal Operating Procedures, or make pen and ink changes to the preflight and post-flight procedures as follows: (i) Stop performing the yaw load compensator check (ACCU TST switch) during preflight procedures, and instead perform the yaw load compensator check during post-flight procedures after rotor shutdown. (ii) The yaw servo hydraulic switch (collective switch) must be in the ‘‘ON’’ (forward) position before takeoff. Note 2 to paragraph (f)(1)(ii) of this AD: The yaw servo hydraulic switch is also called the hydraulic pressure switch or hydraulic cut off switch in various Airbus Helicopters rotorcraft flight manuals. (2) Within 350 hours time-in-service: (i) Install a timer relay for the yaw servo hydraulic switch (collective switch) by following the Accomplishment Instructions, paragraph 3.B.2.b.1, 3.B.2.b.2, 3.B.2.b.3, 3.B.2.b.4, 3.B.2.b.5, or 3.B.2.b.6, as applicable to the configuration of your helicopter, of Airbus Helicopters Service Bulletin (SB) No. AS350–67.00.64, Revision 0, dated February 25, 2015 (AS350–67.00.64). If your helicopter has an automatic pilot system, also comply with paragraph 3.B.2.b.7 of AS350–67.00.64. (ii) Install an indicator light on the caution and warning panel by following the Accomplishment Instructions, paragraph 3.B.2.c.1 or 3.B.2.c.2, as applicable to the configuration of your helicopter, of AS350– 67.00.64. (iii) For helicopters with a Geneva Aviation P122 or P132 electrical console installed, replace the ESN–11 HYD TEST (ACCU TST) switch with a monostable toggle switch part number MS24658–16F. (iv) For helicopters without a Geneva Aviation P122 or P132 electrical console installed, replace the bistable ACCU TST button on the control panel with a monostable button as depicted in Figure 1 or Figure 3, as applicable to the configuration of your helicopter, of Airbus Helicopters SB No. AS350–67.00.65, Revision 0, dated August 25, 2016. (3) After the effective date of this AD, do not install a bistable ACCU TST button on any helicopter. (g) Special Flight Permits A special flight permit may be issued for paragraph (f)(2) of this AD only. PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 2041 (h) Alternative Methods of Compliance (AMOCs) (1) The Manager, Safety Management Section, Rotorcraft Standards Branch, FAA, may approve AMOCs for this AD. Send your proposal to: George Schwab, Aviation Safety Engineer, Safety Management Section, Rotorcraft Standards Branch, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222–5110; email 9-ASWFTW-AMOC-Requests@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. (i) Additional Information (1) Airbus Helicopters SB No. AS350– 67.00.66, Revision 1, dated October 22, 2015, which is not incorporated by reference, contains additional information about the subject of this AD. For service information identified in this AD, contact Airbus Helicopters, 2701 N. Forum Drive, Grand Prairie, TX 75052; telephone (972) 641–0000 or (800) 232–0323; fax (972) 641–3775; or at https://www.helicopters.airbus.com/website/ en/ref/Technical-Support_73.html. You may view a copy of the service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy, Room 6N–321, Fort Worth, TX 76177. (2) The subject of this AD is addressed in European Aviation Safety Agency (EASA) AD No. 2016–0220, dated November 4, 2016. You may view the EASA AD on the internet at https://www.regulations.gov in Docket No. FAA–2017–0826. (j) Subject Joint Aircraft Service Component (JASC) Code: 2910, Main Hydraulic System. (k) 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) Airbus Helicopters Service Bulletin No. AS350–67.00.64, Revision 0, dated February 25, 2015. (ii) Airbus Helicopters Service Bulletin No. AS350–67.00.65, Revision 0, dated August 25, 2016. (3) For Airbus Helicopters service information identified in this AD, contact Airbus Helicopters, 2701 N. Forum Drive, Grand Prairie, TX 75052; telephone (972) 641–0000 or (800) 232–0323; fax (972) 641– 3775; or at https://www.helicopters. airbus.com/website/en/ref/TechnicalSupport_73.html. (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. E:\FR\FM\16JAR1.SGM 16JAR1 2042 Federal Register / Vol. 83, No. 10 / Tuesday, January 16, 2018 / Rules and Regulations (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call (202) 741–6030, or go to: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Fort Worth, Texas, on January 8, 2018. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2018–00478 Filed 1–12–18; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2017–0514; Product Identifier 2016–NM–206–AD; Amendment 39–19148; AD 2018–01–07] 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 A300 B4–600, B4–600R, and F4–600R series airplanes, and Model A300 C4–605R Variant F airplanes (collectively called Model A300–600 series airplanes) airplanes. This AD was prompted by a revision of certain airworthiness limitation item (ALI) documents, which require more restrictive maintenance requirements and airworthiness limitations. This AD requires revising the maintenance or inspection program, as applicable, to incorporate new maintenance requirements and airworthiness limitations. We are issuing this AD to address the unsafe condition on these products. SUMMARY: This AD is effective February 20, 2018. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of February 20, 2018. ADDRESSES: For service information identified in this final rule, contact Airbus SAS, Airworthiness Office— EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@ airbus.com; internet https:// daltland on DSKBBV9HB2PROD with RULES DATES: VerDate Sep<11>2014 16:55 Jan 12, 2018 Jkt 244001 www.airbus.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 https://www.regulations.gov by searching for and locating Docket No. FAA–2017– 0514. 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– 0514; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The street address for 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: Dan Rodina, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 1601 Lind Avenue SW, Renton, WA 98057–3356; telephone 425–227–2125; 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 A300 B4–600, B4–600R, and F4–600R series airplanes, and Model A300 C4–605R Variant F airplanes (collectively called Model A300–600 series airplanes). The NPRM published in the Federal Register on June 2, 2017 (82 FR 25552) (‘‘the NPRM’’). The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2016–0218, dated November 2, 2016 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for all Airbus Model A300 B4–600, B4– 600R, and F4–600R series airplanes, and Model A300 C4–605R Variant F airplanes (collectively called Model A300–600 series airplanes). The MCAI states: The airworthiness limitations for Airbus A300–600 aeroplanes, which are approved by EASA, are currently defined and published PO 00000 Frm 00014 Fmt 4700 Sfmt 4700 in the Airbus A300–600 Airworthiness Limitations Section (ALS) document(s). These instructions have been identified as mandatory actions for continued airworthiness. Failure to accomplish these instructions could result in an unsafe condition. EASA previously issued [EASA] AD 2014– 0124 (later revised) [which includes actions for Airbus A300–600 airplanes; those actions are included in FAA AD 2013–13–13, Amendment 39–17501 (79 FR 48957, August 19, 2014) (‘‘AD 2013–13–13’’)], requiring the actions described in Airbus A300–600 Airworthiness Limitation Item (ALI) Document at issue 13 and Temporary Revision (TR) 13.1. Since EASA AD 2014–0124R1 was issued, Airbus replaced A300–600 ALI Document issue 13, with A300–600 ALS Part 2 Revision 01 and then published the A300–600 ALS Part 2 Variation 1.1 and Variation 1.2, to introduce more restrictive maintenance requirements and/or airworthiness limitations. A300–600 ALS Part 2 Variation 1.1 also includes ALI 571067 and ALI 571068, superseding Service Bulletin A300–53–6154, which is referenced in EASA AD 2006–0257 [which corresponds to FAA AD 2007–22–05, Amendment 39–15241 (72 FR 60236, October 24, 2007) (‘‘AD 2007–22–05’’)]. For the reasons described above, this [EASA] AD retains part of the requirements of EASA AD 2014–0124R1, which will be superseded, and requires accomplishment of the actions specified in Airbus A300–600 ALS Part 2 Revision 01, and ALS Part 2 Variation 1.1 and ALS Part 2 Variation 1.2 (hereafter collectively referred to as ‘the ALS’ in this [EASA] AD), and supersedes EASA AD 2006–0257. The remaining requirements of EASA AD 2014–0124R1 are retained in AD 2016–0217, applicable to A310 aeroplanes, published at the same time as this [EASA] AD. 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–2017– 0514. 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. FedEx generally supported the NPRM. Request To Provide an Additional Compliance Time Grace Period United Parcel Service (UPS) requested that the compliance time specified in paragraph (g) of the NPRM be revised to add an additional grace period. UPS pointed out that there are several new or revised tasks with relatively low compliance time thresholds that would lead to short lead times on accomplishing those tasks after the effective date of the AD. UPS referenced the compliance time required in AD E:\FR\FM\16JAR1.SGM 16JAR1

Agencies

[Federal Register Volume 83, Number 10 (Tuesday, January 16, 2018)]
[Rules and Regulations]
[Pages 2039-2042]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-00478]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0826; Product Identifier 2016-SW-084-AD; Amendment 
39-19153; AD 2018-01-12]
RIN 2120-AA64


Airworthiness Directives; Airbus Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are superseding Airworthiness Directive (AD) 2015-22-53 for 
Airbus Helicopters Model AS350B3 helicopters. AD 2015-22-53 required 
revising the rotorcraft flight manual (RFM) to perform the yaw load 
compensator check after rotor shut-down and to state that the yaw servo 
hydraulic switch must be in the ``ON'' position before taking off. 
Since we issued AD 2015-22-53, Airbus Helicopters developed a 
modification of the ACCU TST switch. This new AD retains the 
requirements of AD 2015-22-53 and requires modifying the yaw servo 
hydraulic switch (collective switch) and replacing the ACCU TST button. 
The actions of this AD are intended to address an unsafe condition on 
these products.

DATES: This AD is effective February 20, 2018.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of February 20, 
2018.

ADDRESSES: For Airbus Helicopters service information identified in 
this final rule, contact Airbus Helicopters, 2701 N. Forum Drive, Grand 
Prairie, TX 75052; telephone (972) 641-0000 or (800) 232-0323; fax 
(972) 641-3775; or at https://www.helicopters.airbus.com/website/en/ref/Technical-Support_73.html. You may view this 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-2017-0826.

Examining the AD Docket

    You may examine the AD docket on the internet at https://www.regulations.gov in Docket No. FAA-2017-0826; or in person at the 
Docket Management Facility between 9 a.m. and 5 p.m., Monday through 
Friday, except Federal holidays. The AD docket contains this AD, the 
European Aviation Safety Agency (EASA) AD, any incorporated-by-
reference information, the economic evaluation, any comments received, 
and other information. The address for the Docket Office (phone: 800-
647-5527) is Document Management Facility, U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: George Schwab, Aviation Safety 
Engineer, Safety Management Section, Rotorcraft Standards Branch, FAA, 
10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222-5110; 
email [email protected].

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to remove AD 2015-22-53, Amendment 39-18331 (80 FR 74982, 
December 1, 2015) and add a new AD. AD 2015-22-53 applied to Airbus 
Helicopters Model AS350B3 helicopters with a dual hydraulic system 
installed. AD 2015-22-53 required revising the pre-flight and post-
flight procedures in the RFM to perform the yaw load compensator check 
(ACCU TST switch) after rotor shut-down instead of during preflight 
procedures and to state that the yaw servo hydraulic switch (collective 
switch) must be in the ``ON'' (forward) position before taking off.
    The NPRM published in the Federal Register on September 8, 2017 (82 
FR 42487). The NPRM was prompted by AD No. 2016-0220, dated November 4, 
2016, issued by EASA, which is the Technical Agent for the Member 
States of the European Union, to correct an unsafe condition for Airbus 
Helicopters Model AS 350 B3 helicopters. EASA advises that further 
analysis resulted in the recognition that a pilot could forget to 
activate a switch despite the RFM changes and that altering the 
bistable push button (push-on, push-off) ACCU TST switch is necessary.
    Accordingly, the NPRM proposed to retain the requirements of AD 
2015-22-53 and also proposed to require, within

[[Page 2040]]

350 hours time-in-service, installing a timer relay for the yaw servo 
hydraulic switch, installing an additional light on the caution and 
warning panel, and replacing the bistable ACCU TST button with a 
monostable button. The proposed requirements were intended to prevent 
takeoff without hydraulic pressure in the tail rotor (T/R) hydraulic 
system, loss of T/R flight control, and subsequent loss of control of 
the helicopter.

Comments

    After our NPRM was published, we received comments from two 
commenters.

Requests

    The National Transportation Safety Board (NTSB) requested that the 
AD address the need for an alert when there is insufficient pressure in 
the T/R hydraulic system, which results in increased pedal loads. In 
support of this request, the NTSB stated that, for at least four events 
it investigated in which the yaw servo hydraulic switch was likely not 
returned to its correct position before takeoff, a salient alert could 
have cued the pilots of insufficient T/R hydraulic pressure.
    We partially agree. We agree that an aural and visual alert to the 
pilot to indicate loss of T/R hydraulic pressure would address this 
unsafe condition. However, Airbus Helicopters has not developed an 
alteration that provides such an alert. The FAA has determined the 
requirements proposed by the NPRM are appropriate to address this 
unsafe condition at this time. Should an aural and visual alert to the 
pilot to indicate loss of T/R hydraulic pressure be developed and 
approved, we might consider additional rulemaking at that time. We did 
not change the AD based on this comment.
    The NTSB also requested that we eliminate the requirement to move 
the yaw load compensator check (ACCU TST switch) to post-flight 
procedures instead of preflight procedures. In support of this request, 
the NTSB stated that performing this check post-flight does not ensure 
the yaw load compensator will remain functional for the next flight.
    We disagree. We determined that requiring this check post-flight 
with the RFM procedure to have the yaw servo hydraulic switch in the 
``ON'' position before takeoff, along with the alterations to the yaw 
servo hydraulic switch and replacement of the ACCU TST button, reduces 
the risk of takeoff with the switch in the incorrect position to an 
acceptable level. We did not change the AD based on this comment.
    Eagle Copters requested we change the AD to address helicopters 
that have replaced the factory console with a Geneva Aviation P122 or 
P132 electrical console under Eagle Copters USA, Inc. Supplemental Type 
Certificate No. SH4747NM. In support of this request, Eagle Copters 
noted that operators of these helicopters will need to request an 
Alternative Method of Compliance to comply with the AD, because the 
Airbus Helicopters service information required for replacing the 
bistable ACCU TST button does not apply to these helicopters. Eagle 
Copters proposed adding a requirement to the AD to replace the HYD 
TEST/ACCU TEST ESN-11 switch on the console from the locking bistable 
toggle switch to a locking momentary (monostable) toggle switch part 
number (P/N) MS24658-16F.
    We agree. We revised the AD to require helicopters with a P122 or 
P132 electrical console installed to replace the bistable ACCU TEST 
switch (which may be marked ``HYD TEST'') with monostable toggle switch 
P/N MS24658-16F.

FAA's Determination

    We have reviewed the relevant information and determined that an 
unsafe condition exists and is likely to exist or develop on other 
helicopters of the same type design and that air safety and the public 
interest require adopting the AD requirements as proposed with the 
change previously described. This change is consistent with the intent 
of the proposals in the NPRM and will not increase the economic burden 
on any operator nor increase the scope of the AD.

Related Service Information Under 1 CFR Part 51

    We reviewed Airbus Helicopters Service Bulletin (SB) No. AS350-
67.00.64, Revision 0, dated February 25, 2015. This service information 
specifies procedures to install a timer relay and an additional 
indicator light on the caution and warning panel. This modification 
provides an ``OFF'' status indication of the yaw servo hydraulic switch 
by flashing a newly installed ``HYD2'' indicator light on the caution 
and warning panel. Airbus Helicopters identifies performance of this SB 
as modification 074622. This modification was available when AD 2015-
22-53 was issued; however, it was determined unnecessary to address the 
unsafe condition at that time.
    We also reviewed Airbus Helicopters SB No. AS350-67.00.65, Revision 
0, dated August 25, 2016. This service information specifies procedures 
to replace the bistable push button ACCU TST switch with a monostable 
push button switch. Airbus Helicopters identifies performance of this 
SB as modification 074719.
    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.

Other Related Service Information

    We reviewed Airbus Helicopters SB No. AS350-67.00.66, Revision 1, 
dated October 22, 2015. This service information specifies inserting 
specific pages of the SB into the rotorcraft flight manual. These pages 
revise the preflight and post-flight hydraulic checks by moving the T/R 
yaw load compensator check from preflight to post-flight. These pages 
also revise terminology within the flight manuals for the different 
engine configurations.

Costs of Compliance

    We estimate that this AD affects 86 helicopters of U.S. Registry. 
We estimate that operators may incur the following costs in order to 
comply with this AD. Labor costs are estimated at $85 per work-hour.
    Revising an RFM would take about 0.5 work-hour for a cost of $43 
per helicopter and $3,698 for the U.S. fleet. Installing a timer relay 
for the yaw servo hydraulic switch and an indicator light would take 
about 9 work-hours and parts would cost about $2,224. Replacing the 
ACCU TST button would take about 1 work-hour and parts would cost about 
$2,244.
    Based on these figures, we estimate a total cost of $5,361 per 
helicopter and $461,046 for the U.S. fleet.

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

[[Page 2041]]

products identified in this rulemaking action.

Regulatory Findings

    We have determined that this AD will not have federalism 
implications under Executive Order 13132. This AD will not have a 
substantial direct effect on the States, on the relationship between 
the national government and the States, or on the distribution of power 
and responsibilities among the various levels of government.
    For the reasons discussed above, I certify that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979),
    (3) Will not affect intrastate aviation in Alaska to the extent 
that a regulatory, and
    (4) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13   [Amended]

0
2. The FAA amends Sec.  39.13 by removing Airworthiness Directive (AD) 
2015-22-53, Amendment 39-18331 (80 FR 74982, December 1, 2015), and 
adding the following new AD:

2018-01-12 Airbus Helicopters: Amendment 39-19153; Docket No. FAA-
2017-0826; Product Identifier 2016-SW-084-AD.

(a) Applicability

    This AD applies to Model AS350B3 helicopters with a dual 
hydraulic system installed, certificated in any category.
    Note 1 to paragraph (a) of this AD: The dual hydraulic system 
for Model AS350B3 helicopters is referred to as Airbus modification 
OP 3082 or OP 3346.

(b) Unsafe Condition

    This AD defines the unsafe condition as lack of hydraulic 
pressure in a tail rotor (T/R) hydraulic system. This condition 
could result in loss of T/R flight control and subsequent loss of 
control of the helicopter.

(c) Affected ADs

    This AD supersedes AD 2015-22-53, Amendment 39-18331 (80 FR 
74982, December 1, 2015).

(d) Effective Date

    This AD becomes effective February 20, 2018.

(e) 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.

(f) Required Actions

    (1) Before further flight, insert a copy of this AD into the 
rotorcraft flight manual, Section 4 Normal Operating Procedures, or 
make pen and ink changes to the preflight and post-flight procedures 
as follows:
    (i) Stop performing the yaw load compensator check (ACCU TST 
switch) during preflight procedures, and instead perform the yaw 
load compensator check during post-flight procedures after rotor 
shut-down.
    (ii) The yaw servo hydraulic switch (collective switch) must be 
in the ``ON'' (forward) position before takeoff.
    Note 2 to paragraph (f)(1)(ii) of this AD: The yaw servo 
hydraulic switch is also called the hydraulic pressure switch or 
hydraulic cut off switch in various Airbus Helicopters rotorcraft 
flight manuals.
    (2) Within 350 hours time-in-service:
    (i) Install a timer relay for the yaw servo hydraulic switch 
(collective switch) by following the Accomplishment Instructions, 
paragraph 3.B.2.b.1, 3.B.2.b.2, 3.B.2.b.3, 3.B.2.b.4, 3.B.2.b.5, or 
3.B.2.b.6, as applicable to the configuration of your helicopter, of 
Airbus Helicopters Service Bulletin (SB) No. AS350-67.00.64, 
Revision 0, dated February 25, 2015 (AS350-67.00.64). If your 
helicopter has an automatic pilot system, also comply with paragraph 
3.B.2.b.7 of AS350-67.00.64.
    (ii) Install an indicator light on the caution and warning panel 
by following the Accomplishment Instructions, paragraph 3.B.2.c.1 or 
3.B.2.c.2, as applicable to the configuration of your helicopter, of 
AS350-67.00.64.
    (iii) For helicopters with a Geneva Aviation P122 or P132 
electrical console installed, replace the ESN-11 HYD TEST (ACCU TST) 
switch with a monostable toggle switch part number MS24658-16F.
    (iv) For helicopters without a Geneva Aviation P122 or P132 
electrical console installed, replace the bistable ACCU TST button 
on the control panel with a monostable button as depicted in Figure 
1 or Figure 3, as applicable to the configuration of your 
helicopter, of Airbus Helicopters SB No. AS350-67.00.65, Revision 0, 
dated August 25, 2016.
    (3) After the effective date of this AD, do not install a 
bistable ACCU TST button on any helicopter.

(g) Special Flight Permits

    A special flight permit may be issued for paragraph (f)(2) of 
this AD only.

(h) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Safety Management Section, Rotorcraft Standards 
Branch, FAA, may approve AMOCs for this AD. Send your proposal to: 
George Schwab, Aviation Safety Engineer, Safety Management Section, 
Rotorcraft Standards Branch, FAA, 10101 Hillwood Pkwy., Fort Worth, 
TX 76177; telephone (817) 222-5110; email [email protected].
    (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.

(i) Additional Information

    (1) Airbus Helicopters SB No. AS350-67.00.66, Revision 1, dated 
October 22, 2015, which is not incorporated by reference, contains 
additional information about the subject of this AD. For service 
information identified in this AD, contact Airbus Helicopters, 2701 
N. Forum Drive, Grand Prairie, TX 75052; telephone (972) 641-0000 or 
(800) 232-0323; fax (972) 641-3775; or at https://www.helicopters.airbus.com/website/en/ref/Technical-Support_73.html. 
You may view a copy of the service information at the FAA, Office of 
the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy, Room 
6N-321, Fort Worth, TX 76177.
    (2) The subject of this AD is addressed in European Aviation 
Safety Agency (EASA) AD No. 2016-0220, dated November 4, 2016. You 
may view the EASA AD on the internet at https://www.regulations.gov 
in Docket No. FAA-2017-0826.

(j) Subject

    Joint Aircraft Service Component (JASC) Code: 2910, Main 
Hydraulic System.

(k) 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) Airbus Helicopters Service Bulletin No. AS350-67.00.64, 
Revision 0, dated February 25, 2015.
    (ii) Airbus Helicopters Service Bulletin No. AS350-67.00.65, 
Revision 0, dated August 25, 2016.
    (3) For Airbus Helicopters service information identified in 
this AD, contact Airbus Helicopters, 2701 N. Forum Drive, Grand 
Prairie, TX 75052; telephone (972) 641-0000 or (800) 232-0323; fax 
(972) 641-3775; or at https://www.helicopters.airbus.com/website/en/ref/Technical-Support_73.html.
    (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.

[[Page 2042]]

    (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 January 8, 2018.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2018-00478 Filed 1-12-18; 8:45 am]
 BILLING CODE 4910-13-P

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