Airworthiness Directives; Airbus Helicopters, 31899-31901 [2017-14372]

Download as PDF Federal Register / Vol. 82, No. 131 / Tuesday, July 11, 2017 / Rules and Regulations Issued in Kansas City, Missouri, on June 29, 2017. Pat Mullen, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017–14375 Filed 7–10–17; 8:45 am] BILLING CODE 4910–13–C DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2017–0060; Directorate Identifier 2016–SW–090–AD; Amendment 39–18949; AD 2017–14–05] RIN 2120–AA64 Airworthiness Directives; Airbus Helicopters Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. AGENCY: We are adopting a new airworthiness directive (AD) for Airbus Helicopters Model SA330J helicopters. This AD requires replacing certain hydraulic pumps and is prompted by reports of broken screws that attach the cover of the hydraulic pump. The actions of this AD are intended to prevent an unsafe condition on these products. SUMMARY: This AD becomes effective July 26, 2017. We must receive comments on this AD by September 11, 2017. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Docket: Go to http://www.regulations.gov. Follow the online instructions for sending your comments electronically. • Fax: 202–493–2251. • Mail: Send comments to the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590–0001. • Hand Delivery: Deliver to the ‘‘Mail’’ address between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. DATES: mstockstill on DSK30JT082PROD with RULES Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2017– 0060; or in person at the Docket Operations Office between 9 a.m. and 5 p.m., Monday through Friday, except VerDate Sep<11>2014 16:47 Jul 10, 2017 Jkt 241001 Federal holidays. The AD docket contains this AD, the European Aviation Safety Agency (EASA) AD, the economic evaluation, any comments received, and other information. The street address for the Docket Operations Office (telephone 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. For service information identified in this final rule, contact Airbus Helicopters, 2701 N. Forum Drive, Grand Prairie, TX 75052; telephone (972) 641–0000 or (800) 232–0323; fax (972) 641–3775; or at https:// www.airbushelicopters.com/techpub/ FO/scripts/myFO_login.php. You may review the referenced service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy, Room 6N–321, Fort Worth, TX 76177. FOR FURTHER INFORMATION CONTACT: Matt Fuller, Senior Aviation Safety Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 10101 Hillwood Pkwy, Fort Worth, TX 76177; telephone (817) 222–5110; email matthew.fuller@ faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited This AD is a final rule that involves requirements affecting flight safety, and we did not provide you with notice and an opportunity to provide your comments prior to it becoming effective. However, we invite you to participate in this rulemaking by submitting written comments, data, or views. We also invite comments relating to the economic, environmental, energy, or federalism impacts that resulted from adopting this AD. The most helpful comments reference a specific portion of the AD, explain the reason for any recommended change, and include supporting data. To ensure the docket does not contain duplicate comments, commenters should send only one copy of written comments, or if comments are filed electronically, commenters should submit them only one time. We will file in the docket all comments that we receive, as well as a report summarizing each substantive public contact with FAA personnel concerning this rulemaking during the comment period. We will consider all the comments we receive and may conduct additional rulemaking based on those comments. Discussion EASA, which is the Technical Agent for the Member States of the European Union, has issued EASA Emergency AD No. 2016–264–E, dated December 22, PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 31899 2016, to correct an unsafe condition for Airbus Helicopters Model SA330J helicopters. EASA advises of reports of broken screws that attach the cover of the hydraulic pump. A subsequent investigation identified a batch of screws delivered between July 1, 2015, and November 1, 2016, that have intrinsic embrittlement and reduced mechanical properties. Hydrogen was introduced into this batch of screws during production, causing the screws to become brittle and lack sufficient strength. These screws were installed in a batch of hydraulic pumps, part number (P/N) FR65WEO2005–175A, identified by certain serial numbers, EASA advises. This condition, if not detected and corrected, could lead to the failure of a cover bolt and loss of fluid from the hydraulic pump, resulting in loss of the hydraulic system and subsequent loss of helicopter control. As a result, EASA AD No. 2016–264–E requires replacing the hydraulic pumps. FAA’s Determination These helicopters have been approved by the aviation authority of France and are approved for operation in the United States. Pursuant to our bilateral agreement with France, EASA, its technical representative, has notified us of the unsafe condition described in the EASA AD. We are issuing this AD because we evaluated all information provided by EASA and determined the unsafe condition exists and is likely to exist or develop on other helicopters of these same type designs. Related Service Information We reviewed Airbus Helicopters Emergency Alert Service Bulletin No. SA330–29.12, Revision 0, dated December 22, 2016 (Airbus EASB), for Model SA330J helicopters and military model SA330L, SA330Jm, SA330S1, and SA330Sm helicopters. The Airbus EASB specifies removing Nexter Mechanics hydraulic pumps P/N FR65WEO2005–175A with certain serial numbers. If both the right-hand (RH) and left-hand (LH) hydraulic pumps have an affected P/N and serial number, the Airbus EASB specifies replacing the RH hydraulic pump before further flight and the LH hydraulic pump within 110 flying hours or 6 months. If only one hydraulic pump has an affected P/N and serial number, the Airbus EASB specifies replacing it within 110 flying hours or 6 months. The Airbus EASB also specifies that, for 6 months after receipt of the Airbus EASB, before installing an affected hydraulic pump it must be ‘‘returned to conformity’’ by complying with Nexter Mechanics Alert E:\FR\FM\11JYR1.SGM 11JYR1 31900 Federal Register / Vol. 82, No. 131 / Tuesday, July 11, 2017 / Rules and Regulations Service Bulletin No. NM/INGE/16–140, Revision 0, dated December 22, 2016 (Nexter ASB). After 6 months or 110 flying hours, whichever occurs first, the Airbus EASB states the affected hydraulic pumps are unfit for flight. before issuing this AD are impracticable and contrary to the public interest and that good cause exists to make this AD effective in less than 30 days. AD Requirements This AD requires, within 15 hours time-in-service (TIS), removing the RH hydraulic pump if both hydraulic pumps are listed in the applicability section of this AD. This AD also prohibits installing an affected hydraulic pump on any helicopter. 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. Differences Between This AD and the EASA AD The EASA AD requires replacing the LH hydraulic pump with a serviceable part within 110 hours TIS or 6 months, whichever comes first, if both the LH and RH hydraulic pumps are affected parts. The EASA AD also requires, if only one hydraulic pump is an affected part, replacing it with a serviceable part within 110 hours TIS or 6 months, whichever comes first. This AD makes no such requirements. We are considering requiring those actions. However, the planned compliance time for those actions would allow enough time to provide notice and opportunity for prior public comment. The EASA AD allows a hydraulic pump to be installed if it has been repaired in accordance with the Nexter ASB, while this AD does not. mstockstill on DSK30JT082PROD with RULES Costs of Compliance We estimate that this AD affects 24 helicopters and that labor costs average $85 per work-hour. Based on these estimates, we expect that replacing a hydraulic pump requires 2 work-hours and parts cost $2,500 for a total cost of $2,670 per helicopter and $64,080 for the U.S. fleet. FAA’s Justification and Determination of the Effective Date Providing an opportunity for public comments prior to adopting these AD requirements would delay implementing the safety actions needed to correct this known unsafe condition. Therefore, we find that the risk to the flying public justifies waiving notice and comment prior to the adoption of this rule because the required corrective actions must be accomplished within 15 hours TIS, a very short time period based on the typical utilization rate of these helicopters in off-shore oil operations. Since an unsafe condition exists that requires the immediate adoption of this AD, we determined that notice and opportunity for prior public comment VerDate Sep<11>2014 16:47 Jul 10, 2017 Jkt 241001 Authority for This Rulemaking Regulatory Findings We determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed, I certify that this AD: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska to the extent that it justifies making a regulatory distinction; and 4. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. 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: PO 00000 Frm 00014 Fmt 4700 Sfmt 4700 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): ■ 2017–14–05 Airbus Helicopters: Amendment 39–18949; Docket No. FAA–2017–0060; Directorate Identifier 2016–SW–090–AD. (a) Applicability This AD applies to Airbus Helicopters Model SA330J helicopters, certificated in any category, with a left-hand and a right-hand hydraulic pump part number FR65WEO2005–175A with a serial number 4108, 4141, 4177, 4227, 4241, 4284, 4377, 4422, 4570, 4573, 4574, 4641, 4649, 4668, 4766, 4802, 4821, 4831, 4837, 4888, 4896, 4946, 4985, 5023, 5071, 5304, 5366, 5376, 5409, 5442, 5486, 5599, 5630, 94075/01, or 94048/01 installed. (b) Unsafe Condition This AD defines the unsafe condition as failure of a screw attaching the hydraulic pump cover. This condition could result in failure of a cover bolt and loss of fluid from the hydraulic pump, resulting in loss of the hydraulic system and subsequent loss of helicopter control. (c) Effective Date This AD becomes effective July 26, 2017. (d) Compliance You are responsible for performing each action required by this AD within the specified compliance time unless it has already been accomplished prior to that time. (e) Required Actions (1) Within 15 hours time-in-service, replace the right-hand hydraulic pump with an airworthy hydraulic pump that is not listed in paragraph (a) of this AD. (2) After the effective date of this AD, do not install on any helicopter a hydraulic pump that is listed in paragraph (a) of this AD. (f) Special Flight Permits Special flight permits are prohibited. (g) Alternative Methods of Compliance (AMOCs) (1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to: Matt Fuller, Senior Aviation Safety Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 10101 Hillwood Pkwy, Fort Worth, TX 76177; telephone (817) 222–5110; email 9ASW-FTW-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 E:\FR\FM\11JYR1.SGM 11JYR1 Federal Register / Vol. 82, No. 131 / Tuesday, July 11, 2017 / Rules and Regulations the local flight standards district office or certificate holding district office, before operating any aircraft complying with this AD through an AMOC. (h) Additional Information (1) Airbus Helicopters Emergency Alert Service Bulletin (EASB) No. SA330–29.12, Revision 0, dated December 22, 2016, and Nexter Mechanics Alert Service Bulletin No. NM/INGE/16–140, Revision 0, dated December 22, 2016, which are not incorporated by reference, contain 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 http:// www.airbushelicopters.com/techpub. You may review 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. 2016–264–E, dated December 22, 2016. You may view the EASA AD on the Internet at http://www.regulations.gov by searching for and locating it in Docket No. FAA–2017– 0060. (i) Subject Joint Aircraft Service Component (JASC) Code: 2913, Hydraulic Pump (Electric/ Engine) Main. Issued in Fort Worth, Texas, on June 30, 2017. Scott A. Horn, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2017–14372 Filed 7–10–17; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–6693; Directorate Identifier 2015–SW–033–AD; Amendment 39–18886; AD 2017–10–12] RIN 2120–AA64 Airworthiness Directives; Airbus Helicopters Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for Airbus Helicopters Model AS332C, AS332C1, AS332L, AS332L1, AS332L2, and EC225LP helicopters. This AD requires repetitive inspections of the intermediate gear box (IGB) fairing. This AD was prompted by separation of the IGB fairing from the fairing gutter and subsequent interference with the drive mstockstill on DSK30JT082PROD with RULES SUMMARY: VerDate Sep<11>2014 16:47 Jul 10, 2017 Jkt 241001 shaft. The actions of this AD are intended to prevent an unsafe condition on these products. DATES: This AD is effective August 15, 2017. The Director of the Federal Register approved the incorporation by reference of certain documents listed in this AD as of August 15, 2017. ADDRESSES: For service information identified in this final rule, contact Airbus Helicopters, 2701 N. Forum Drive, Grand Prairie, TX 75052; telephone (972) 641–0000 or (800) 232– 0323; fax (972) 641–3775; or at https:// www.airbushelicopters.com/techpub/ FO/scripts/myFO_login.php. You may review the referenced service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy, Room 6N–321, Fort Worth, TX 76177. It is also available on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 6693. Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 6693; 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 European Aviation Safety Agency (EASA) AD, any incorporated-by-reference service information, the economic evaluation, any comments received, and other information. The street address for the Docket Operations Office (phone: 800– 647–5527) is U.S. Department of Transportation, Docket Operations Office, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: David Hatfield, Aviation Safety Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 10101 Hillwood Pkwy, Fort Worth, TX 76177; telephone (817) 222–5116; email david.hatfield@faa.gov. SUPPLEMENTARY INFORMATION: Discussion On January 5, 2017, at 82 FR 1260, the Federal Register published our notice of proposed rulemaking (NPRM), which proposed to amend 14 CFR part 39 by adding an AD that would apply to Airbus Helicopters Model AS332C, AS332C1, AS332L, AS332L1, AS332L2, and EC225LP helicopters with an IGB fairing part number (P/N) 332A24– 0303–05XX, 332A24–0303–06XX, PO 00000 Frm 00015 Fmt 4700 Sfmt 4700 31901 332A08–1391–00, or 332A08–1391–01 installed, where ‘‘XX’’ is any two alphanumeric characters. The NPRM proposed to require repetitive inspections of the IGB fairing. The proposed requirements were intended to prevent the detachment of the angle section of an IGB and subsequent interference between an IGB fairing and tail rotor inclined drive shaft. This condition could result in failure of a tail rotor drive shaft, loss of the tail rotor drive, and subsequent loss of control of the helicopter. The NPRM was prompted by AD No. 2015–0092, dated May 26, 2015, issued by EASA, which is the Technical Agent for the Member States of the European Union, to correct an unsafe condition for the Airbus Model AS332C, AS332C1, AS332L, AS332L1, AS332L2, and EC225LP helicopters with certain part-numbered IGB fairings installed. EASA advises of occurrences involving separation of the angle section of the IGB fairing from the IGB fairing gutter, which caused interference with the tail rotor (T/R) inclined drive shaft. EASA states that this condition, if not detected and corrected, could lead to failure of the T/R drive shaft, loss of the T/R drive, and consequent reduced control of the helicopter. To address this condition, EASA issued a series of ADs, including AD No. 2015–0092, to require repetitive inspections of the IGB fairing and its attachment supports and installation of a new IGB fairing, P/N 332A24–0322–00, as terminating action for the inspections. Comments An individual commented that he supports the NPRM. FAA’s Determination These helicopters have been approved by the aviation authority of France and are approved for operation in the United States. Pursuant to our bilateral agreement with France, EASA, its technical representative, has notified us of the unsafe condition described in the EASA AD. We are issuing this AD because we evaluated all information provided by EASA and determined the unsafe condition exists and is likely to exist or develop on other helicopters of these same type designs and that air safety and the public interest require adopting the AD requirements as proposed. Differences Between This AD and the EASA AD The EASA AD requires replacing the IGB fairing with the composite fairing within 31 months. This AD requires this E:\FR\FM\11JYR1.SGM 11JYR1

Agencies

[Federal Register Volume 82, Number 131 (Tuesday, July 11, 2017)]
[Rules and Regulations]
[Pages 31899-31901]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-14372]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0060; Directorate Identifier 2016-SW-090-AD; 
Amendment 39-18949; AD 2017-14-05]
RIN 2120-AA64


Airworthiness Directives; Airbus Helicopters

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule; request for comments.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for Airbus 
Helicopters Model SA330J helicopters. This AD requires replacing 
certain hydraulic pumps and is prompted by reports of broken screws 
that attach the cover of the hydraulic pump. The actions of this AD are 
intended to prevent an unsafe condition on these products.

DATES: This AD becomes effective July 26, 2017.
    We must receive comments on this AD by September 11, 2017.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Docket: Go to http://www.regulations.gov. Follow the online instructions for sending your 
comments electronically.
     Fax: 202-493-2251.
     Mail: Send comments to the U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590-0001.
     Hand Delivery: Deliver to the ``Mail'' address between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017-
0060; or in person at the Docket Operations Office between 9 a.m. and 5 
p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this AD, the European Aviation Safety Agency (EASA) AD, the 
economic evaluation, any comments received, and other information. The 
street address for the Docket Operations Office (telephone 800-647-
5527) is in the ADDRESSES section. Comments will be available in the AD 
docket shortly after receipt.
    For service information identified in this final rule, contact 
Airbus Helicopters, 2701 N. Forum Drive, Grand Prairie, TX 75052; 
telephone (972) 641-0000 or (800) 232-0323; fax (972) 641-3775; or at 
https://www.airbushelicopters.com/techpub/FO/scripts/myFO_login.php. 
You may review the referenced service information at the FAA, Office of 
the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy, Room 6N-
321, Fort Worth, TX 76177.

FOR FURTHER INFORMATION CONTACT: Matt Fuller, Senior Aviation Safety 
Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 10101 
Hillwood Pkwy, Fort Worth, TX 76177; telephone (817) 222-5110; email 
matthew.fuller@faa.gov.

SUPPLEMENTARY INFORMATION:

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not provide you with notice and an opportunity to 
provide your comments prior to it becoming effective. However, we 
invite you to participate in this rulemaking by submitting written 
comments, data, or views. We also invite comments relating to the 
economic, environmental, energy, or federalism impacts that resulted 
from adopting this AD. The most helpful comments reference a specific 
portion of the AD, explain the reason for any recommended change, and 
include supporting data. To ensure the docket does not contain 
duplicate comments, commenters should send only one copy of written 
comments, or if comments are filed electronically, commenters should 
submit them only one time. We will file in the docket all comments that 
we receive, as well as a report summarizing each substantive public 
contact with FAA personnel concerning this rulemaking during the 
comment period. We will consider all the comments we receive and may 
conduct additional rulemaking based on those comments.

Discussion

    EASA, which is the Technical Agent for the Member States of the 
European Union, has issued EASA Emergency AD No. 2016-264-E, dated 
December 22, 2016, to correct an unsafe condition for Airbus 
Helicopters Model SA330J helicopters. EASA advises of reports of broken 
screws that attach the cover of the hydraulic pump. A subsequent 
investigation identified a batch of screws delivered between July 1, 
2015, and November 1, 2016, that have intrinsic embrittlement and 
reduced mechanical properties. Hydrogen was introduced into this batch 
of screws during production, causing the screws to become brittle and 
lack sufficient strength. These screws were installed in a batch of 
hydraulic pumps, part number (P/N) FR65WEO2005-175A, identified by 
certain serial numbers, EASA advises.
    This condition, if not detected and corrected, could lead to the 
failure of a cover bolt and loss of fluid from the hydraulic pump, 
resulting in loss of the hydraulic system and subsequent loss of 
helicopter control. As a result, EASA AD No. 2016-264-E requires 
replacing the hydraulic pumps.

FAA's Determination

    These helicopters have been approved by the aviation authority of 
France and are approved for operation in the United States. Pursuant to 
our bilateral agreement with France, EASA, its technical 
representative, has notified us of the unsafe condition described in 
the EASA AD. We are issuing this AD because we evaluated all 
information provided by EASA and determined the unsafe condition exists 
and is likely to exist or develop on other helicopters of these same 
type designs.

Related Service Information

    We reviewed Airbus Helicopters Emergency Alert Service Bulletin No. 
SA330-29.12, Revision 0, dated December 22, 2016 (Airbus EASB), for 
Model SA330J helicopters and military model SA330L, SA330Jm, SA330S1, 
and SA330Sm helicopters. The Airbus EASB specifies removing Nexter 
Mechanics hydraulic pumps P/N FR65WEO2005-175A with certain serial 
numbers. If both the right-hand (RH) and left-hand (LH) hydraulic pumps 
have an affected P/N and serial number, the Airbus EASB specifies 
replacing the RH hydraulic pump before further flight and the LH 
hydraulic pump within 110 flying hours or 6 months. If only one 
hydraulic pump has an affected P/N and serial number, the Airbus EASB 
specifies replacing it within 110 flying hours or 6 months. The Airbus 
EASB also specifies that, for 6 months after receipt of the Airbus 
EASB, before installing an affected hydraulic pump it must be 
``returned to conformity'' by complying with Nexter Mechanics Alert

[[Page 31900]]

Service Bulletin No. NM/INGE/16-140, Revision 0, dated December 22, 
2016 (Nexter ASB). After 6 months or 110 flying hours, whichever occurs 
first, the Airbus EASB states the affected hydraulic pumps are unfit 
for flight.

AD Requirements

    This AD requires, within 15 hours time-in-service (TIS), removing 
the RH hydraulic pump if both hydraulic pumps are listed in the 
applicability section of this AD. This AD also prohibits installing an 
affected hydraulic pump on any helicopter.

Differences Between This AD and the EASA AD

    The EASA AD requires replacing the LH hydraulic pump with a 
serviceable part within 110 hours TIS or 6 months, whichever comes 
first, if both the LH and RH hydraulic pumps are affected parts. The 
EASA AD also requires, if only one hydraulic pump is an affected part, 
replacing it with a serviceable part within 110 hours TIS or 6 months, 
whichever comes first. This AD makes no such requirements. We are 
considering requiring those actions. However, the planned compliance 
time for those actions would allow enough time to provide notice and 
opportunity for prior public comment. The EASA AD allows a hydraulic 
pump to be installed if it has been repaired in accordance with the 
Nexter ASB, while this AD does not.

Costs of Compliance

    We estimate that this AD affects 24 helicopters and that labor 
costs average $85 per work-hour. Based on these estimates, we expect 
that replacing a hydraulic pump requires 2 work-hours and parts cost 
$2,500 for a total cost of $2,670 per helicopter and $64,080 for the 
U.S. fleet.

FAA's Justification and Determination of the Effective Date

    Providing an opportunity for public comments prior to adopting 
these AD requirements would delay implementing the safety actions 
needed to correct this known unsafe condition. Therefore, we find that 
the risk to the flying public justifies waiving notice and comment 
prior to the adoption of this rule because the required corrective 
actions must be accomplished within 15 hours TIS, a very short time 
period based on the typical utilization rate of these helicopters in 
off-shore oil operations.
    Since an unsafe condition exists that requires the immediate 
adoption of this AD, we determined that notice and opportunity for 
prior public comment before issuing this AD are impracticable and 
contrary to the public interest and that good cause exists to make this 
AD effective in less than 30 days.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation 
Programs,'' describes in more detail the scope of the Agency's 
authority.
    We are issuing this rulemaking under the authority described in 
``Subtitle VII, Part A, Subpart III, Section 44701: General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

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

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):

2017-14-05 Airbus Helicopters: Amendment 39-18949; Docket No. FAA-
2017-0060; Directorate Identifier 2016-SW-090-AD.

(a) Applicability

    This AD applies to Airbus Helicopters Model SA330J helicopters, 
certificated in any category, with a left-hand and a right-hand 
hydraulic pump part number FR65WEO2005-175A with a serial number 
4108, 4141, 4177, 4227, 4241, 4284, 4377, 4422, 4570, 4573, 4574, 
4641, 4649, 4668, 4766, 4802, 4821, 4831, 4837, 4888, 4896, 4946, 
4985, 5023, 5071, 5304, 5366, 5376, 5409, 5442, 5486, 5599, 5630, 
94075/01, or 94048/01 installed.

(b) Unsafe Condition

    This AD defines the unsafe condition as failure of a screw 
attaching the hydraulic pump cover. This condition could result in 
failure of a cover bolt and loss of fluid from the hydraulic pump, 
resulting in loss of the hydraulic system and subsequent loss of 
helicopter control.

(c) Effective Date

    This AD becomes effective July 26, 2017.

(d) Compliance

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

(e) Required Actions

    (1) Within 15 hours time-in-service, replace the right-hand 
hydraulic pump with an airworthy hydraulic pump that is not listed 
in paragraph (a) of this AD.
    (2) After the effective date of this AD, do not install on any 
helicopter a hydraulic pump that is listed in paragraph (a) of this 
AD.

(f) Special Flight Permits

    Special flight permits are prohibited.

(g) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Safety Management Group, FAA, may approve AMOCs 
for this AD. Send your proposal to: Matt Fuller, Senior Aviation 
Safety Engineer, Safety Management Group, Rotorcraft Directorate, 
FAA, 10101 Hillwood Pkwy, Fort Worth, TX 76177; telephone (817) 222-
5110; email 9-ASW-FTW-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

[[Page 31901]]

the local flight standards district office or certificate holding 
district office, before operating any aircraft complying with this 
AD through an AMOC.

(h) Additional Information

    (1) Airbus Helicopters Emergency Alert Service Bulletin (EASB) 
No. SA330-29.12, Revision 0, dated December 22, 2016, and Nexter 
Mechanics Alert Service Bulletin No. NM/INGE/16-140, Revision 0, 
dated December 22, 2016, which are not incorporated by reference, 
contain 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 http://www.airbushelicopters.com/techpub. You may review 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. 2016-264-E, dated December 22, 2016. You 
may view the EASA AD on the Internet at http://www.regulations.gov 
by searching for and locating it in Docket No. FAA-2017-0060.

(i) Subject

    Joint Aircraft Service Component (JASC) Code: 2913, Hydraulic 
Pump (Electric/Engine) Main.


    Issued in Fort Worth, Texas, on June 30, 2017.
Scott A. Horn,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2017-14372 Filed 7-10-17; 8:45 am]
 BILLING CODE 4910-13-P