Airworthiness Directives; Rolls-Royce Corporation Turboshaft Engines, 4609-4610 [2018-01900]

Download as PDF 4609 Federal Register / Vol. 83, No. 22 / Thursday, February 1, 2018 / Proposed Rules Issued in Kansas City, Missouri, on January 24, 2018. Pat Mullen, Acting Deputy Director, Policy & Innovation Division, Aircraft Certification Service. [FR Doc. 2018–01923 Filed 1–31–18; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 Examining the AD Docket [Docket No. FAA–2017–1118; Product Identifier 2017–NE–40–AD] RIN 2120–AA64 Airworthiness Directives; Rolls-Royce Corporation Turboshaft Engines Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for certain Rolls-Royce Corporation (RRC) model 250–C turboshaft engines. This proposed AD was prompted by several reports of engine power loss, one of which resulted in a fatal helicopter accident. This proposed AD would require removal of the bearing assembly, part number (P/N) 2544198, in the power turbine governor (PTG) and its replacement with a bearing assembly eligible for installation. We are proposing this AD to address the unsafe condition on these products. DATES: We must receive comments on this proposed AD by March 19, 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: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. SUMMARY: daltland on DSKBBV9HB2PROD with PROPOSALS For service information identified in this NPRM, contact Rolls-Royce Corporation, 450 South Meridian Street, Mail Code NB–02–05, Indianapolis, IN 46225; phone: 317–230–3774; email: indy.pubs.services@rolls-royce.com; internet: www.rolls-royce.com. You may view this service information at the FAA, Engine and Propeller Standards Branch, 1200 District Avenue, Burlington, MA. For information on the availability of this material at the FAA, call 781–238–7759. You may examine the AD docket on the internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2017– 1118; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this NPRM, the regulatory evaluation, any comments received, and other information. The street address for Docket Operations (phone: 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: John Tallarovic, Aerospace Engineer, Chicago ACO Branch, FAA, 2300 E. Devon Ave., Des Plaines, IL 60018; phone: 847–294– 8180; fax: 847–294–7834; email: john.tallarovic@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA– 2017–1118; Product Identifier 2017– NE–40–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this NPRM. We will consider all comments received by the closing date and may amend this NPRM because of 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 NPRM. Discussion We were prompted to issue this NPRM based upon several reports of loss of engine power on certain RRC model 250–C turboshaft engines installed on single-engine helicopters. One of these instances of power loss resulted in a fatal helicopter accident on May 4, 2016. During the course of the investigation of the 2016 fatal accident, RRC determined that the root cause of this engine power loss was the failure of the bearing assembly, P/N 2544198, in the PTG, due to lack of lubrication. Although RRC had issued a service bulletin in 2009 to address the failure of this bearing assembly, our risk assessment had not supported issuance of an AD at that time. Based on more recent service experience, and the fatal accident in 2016, we are now proposing an AD to remove the affected bearing assembly in the PTG and replace it with a bearing assembly with a new design. This condition, if not addressed, could result in failure of the PTG, failure of the engine, in-flight shutdown, and forced autorotation landing or accident. Related Service Information We reviewed Rolls-Royce Corporation Commercial Engine Bulletin (CEB) 1402, Revision 2, dated February 4, 2009. The CEB provides guidance on replacing the P/N 2544198 bearing assembly in the PTG with a bearing assembly eligible for installation. FAA’s Determination We are proposing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. Proposed AD Requirements This proposed AD would require removal of the affected bearing assembly in the PTG and its replacement with a bearing assembly eligible for installation. Costs of Compliance We estimate that this proposed AD affects 2,928 engines installed on airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: ESTIMATED COSTS Action Labor cost Remove and replace PTG bearing assembly 8 work-hours × $85 per hour = $680 ............. VerDate Sep<11>2014 16:25 Jan 31, 2018 Jkt 244001 PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 Parts cost E:\FR\FM\01FEP1.SGM $1,700 01FEP1 Cost per product $2,380 Cost on U.S. operators $6,968,640 4610 Federal Register / Vol. 83, No. 22 / Thursday, February 1, 2018 / Proposed Rules Authority for This Rulemaking List of Subjects in 14 CFR Part 39 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 engines, propellers, and associated appliances to the Manager, Engine and Propeller Standards Branch, Policy and Innovation Division. Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. daltland on DSKBBV9HB2PROD with PROPOSALS Regulatory Findings We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 this proposed regulation: (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. VerDate Sep<11>2014 16:25 Jan 31, 2018 Jkt 244001 The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ Roll-Royce Corporation (Type Certificate previously held by Allison Engine Company): Docket No. FAA–2017–1118; Product Identifier 2017–NE–40–AD. (a) Comments Due Date We must receive comments by March 19, 2018. (b) Affected ADs None. (c) Applicability This AD applies to Rolls-Royce Corporation (RRC) model 250–C10D, 250– C18, 250–C18A, 250–C18B, 250–C18C, 250– C19, 250–C20, 250–C20B, 250–C20C, 250– C20F, 250–C20J, 250–C20R, 250–C20R/1, 250–C20R/2, 250–C20R/4, 250–C20S, 250– C20W, 250–C28, 250–C28B, 250–C28C, 250– C30, 250–C30G, 250–C30G/2, 250–C30M, 250–C30P, 250–C30S, and 250–C30U turboshaft engines. (d) Subject Joint Aircraft System Component (JASC) Code 7323, Turbine Governor. (e) Unsafe Condition This AD was prompted by several reports of loss of power, one of which resulted in a fatal helicopter accident. We are issuing this AD to prevent failure of the bearing assembly in the power turbine governor (PTG). The unsafe condition, if not addressed, could result in failure of the PTG, failure of the engine, in-flight shutdown, and forced autorotation landing or accident. (f) Compliance Comply with this AD within the compliance times specified, unless already done. FIGURE 1 TO PARAGRAPH (g)— COMPLIANCE TIMES PTG operational hours (time since new/time since last overhaul) 0 to 750 ....................... 751 to 1000 ................. 1001 to 1250 ............... 1251 to 1500 ............... 1501 or greater ............ Frm 00006 Fmt 4702 Sfmt 9990 Not later than 750 hours. Not later than 1,000 hours. Not later than 1,250 hours. Not later than 1,500 hours. At the next removal of the PTG for any reason. (2) After such removal, replace the affected bearing assembly in the PTG with a part eligible for installation before further flight. (h) Alternative Methods of Compliance (AMOCs) (1) The Manager, Chicago ACO 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 manager of the Chicago ACO Branch, send it to the attention of the person identified in paragraph (i)(1) of this AD. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. (i) Related Information (1) For more information about this AD, contact John Tallarovic, Aerospace Engineer, Chicago ACO Branch, FAA, 2300 E Devon Ave., Des Plaines, IL 60018; phone: 847–294– 8180; fax: 847–294–7834; email: john.tallarovic@faa.gov. (2) For service information identified in this AD, contact Rolls-Royce Corporation, 450 South Meridian Street, Mail Code NB– 02–05, Indianapolis, IN 46225; phone: 317– 230–3774; email: indy.pubs.services@rollsroyce.com; internet: www.rolls-royce.com. You may view this referenced service information at the FAA, Engine and Propeller Standards Branch, 1200 District Avenue, Burlington, MA 01803. For information on the availability of this material at the FAA, call 781–238–7759. Issued in Burlington, Massachusetts, on January 25, 2018. Robert J. Ganley, Manager, Engine and Propeller Standards Branch, Aircraft Certification Service. [FR Doc. 2018–01900 Filed 1–31–18; 8:45 am] BILLING CODE 4910–13–P (g) Required Actions (1) Remove the bearing assembly, part number 2544198, from the PTG in accordance with the compliance times in Figure 1 to paragraph (g) of this AD, or within 90 days after the effective date of this AD, whichever occurs later. PO 00000 Compliance time E:\FR\FM\01FEP1.SGM 01FEP1

Agencies

[Federal Register Volume 83, Number 22 (Thursday, February 1, 2018)]
[Proposed Rules]
[Pages 4609-4610]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-01900]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-1118; Product Identifier 2017-NE-40-AD]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce Corporation Turboshaft 
Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
certain Rolls-Royce Corporation (RRC) model 250-C turboshaft engines. 
This proposed AD was prompted by several reports of engine power loss, 
one of which resulted in a fatal helicopter accident. This proposed AD 
would require removal of the bearing assembly, part number (P/N) 
2544198, in the power turbine governor (PTG) and its replacement with a 
bearing assembly eligible for installation. We are proposing this AD to 
address the unsafe condition on these products.

DATES: We must receive comments on this proposed AD by March 19, 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: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this NPRM, contact Rolls-
Royce Corporation, 450 South Meridian Street, Mail Code NB-02-05, 
Indianapolis, IN 46225; phone: 317-230-3774; email: 
royce.com">[email protected]royce.com; internet: www.rolls-royce.com. You 
may view this service information at the FAA, Engine and Propeller 
Standards Branch, 1200 District Avenue, Burlington, MA. For information 
on the availability of this material at the FAA, call 781-238-7759.

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-
1118; or in person at Docket Operations between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays. The AD docket contains 
this NPRM, the regulatory evaluation, any comments received, and other 
information. The street address for Docket Operations (phone: 800-647-
5527) is in the ADDRESSES section. Comments will be available in the AD 
docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: John Tallarovic, Aerospace Engineer, 
Chicago ACO Branch, FAA, 2300 E. Devon Ave., Des Plaines, IL 60018; 
phone: 847-294-8180; fax: 847-294-7834; email: [email protected].

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2017-1118; 
Product Identifier 2017-NE-40-AD'' at the beginning of your comments. 
We specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this NPRM. We will consider all 
comments received by the closing date and may amend this NPRM because 
of 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 NPRM.

Discussion

    We were prompted to issue this NPRM based upon several reports of 
loss of engine power on certain RRC model 250-C turboshaft engines 
installed on single-engine helicopters. One of these instances of power 
loss resulted in a fatal helicopter accident on May 4, 2016.
    During the course of the investigation of the 2016 fatal accident, 
RRC determined that the root cause of this engine power loss was the 
failure of the bearing assembly, P/N 2544198, in the PTG, due to lack 
of lubrication. Although RRC had issued a service bulletin in 2009 to 
address the failure of this bearing assembly, our risk assessment had 
not supported issuance of an AD at that time. Based on more recent 
service experience, and the fatal accident in 2016, we are now 
proposing an AD to remove the affected bearing assembly in the PTG and 
replace it with a bearing assembly with a new design. This condition, 
if not addressed, could result in failure of the PTG, failure of the 
engine, in-flight shutdown, and forced autorotation landing or 
accident.

Related Service Information

    We reviewed Rolls-Royce Corporation Commercial Engine Bulletin 
(CEB) 1402, Revision 2, dated February 4, 2009. The CEB provides 
guidance on replacing the P/N 2544198 bearing assembly in the PTG with 
a bearing assembly eligible for installation.

FAA's Determination

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

Proposed AD Requirements

    This proposed AD would require removal of the affected bearing 
assembly in the PTG and its replacement with a bearing assembly 
eligible for installation.

Costs of Compliance

    We estimate that this proposed AD affects 2,928 engines installed 
on airplanes of U.S. registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Remove and replace PTG bearing          8 work-hours x $85 per            $1,700          $2,380      $6,968,640
 assembly.                               hour = $680.
----------------------------------------------------------------------------------------------------------------


[[Page 4610]]

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 engines, propellers, and 
associated appliances to the Manager, Engine and Propeller Standards 
Branch, Policy and Innovation Division.

Regulatory Findings

    We determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 this proposed 
regulation:
    (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.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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):

Roll-Royce Corporation (Type Certificate previously held by Allison 
Engine Company): Docket No. FAA-2017-1118; Product Identifier 2017-
NE-40-AD.

(a) Comments Due Date

    We must receive comments by March 19, 2018.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Rolls-Royce Corporation (RRC) model 250-C10D, 
250-C18, 250-C18A, 250-C18B, 250-C18C, 250-C19, 250-C20, 250-C20B, 
250-C20C, 250-C20F, 250-C20J, 250-C20R, 250-C20R/1, 250-C20R/2, 250-
C20R/4, 250-C20S, 250-C20W, 250-C28, 250-C28B, 250-C28C, 250-C30, 
250-C30G, 250-C30G/2, 250-C30M, 250-C30P, 250-C30S, and 250-C30U 
turboshaft engines.

(d) Subject

    Joint Aircraft System Component (JASC) Code 7323, Turbine 
Governor.

(e) Unsafe Condition

    This AD was prompted by several reports of loss of power, one of 
which resulted in a fatal helicopter accident. We are issuing this 
AD to prevent failure of the bearing assembly in the power turbine 
governor (PTG). The unsafe condition, if not addressed, could result 
in failure of the PTG, failure of the engine, in-flight shutdown, 
and forced autorotation landing or accident.

(f) Compliance

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

(g) Required Actions

    (1) Remove the bearing assembly, part number 2544198, from the 
PTG in accordance with the compliance times in Figure 1 to paragraph 
(g) of this AD, or within 90 days after the effective date of this 
AD, whichever occurs later.

               Figure 1 to Paragraph (g)--Compliance Times
------------------------------------------------------------------------
 PTG operational hours (time since new/
        time since last overhaul)                 Compliance time
------------------------------------------------------------------------
0 to 750................................  Not later than 750 hours.
751 to 1000.............................  Not later than 1,000 hours.
1001 to 1250............................  Not later than 1,250 hours.
1251 to 1500............................  Not later than 1,500 hours.
1501 or greater.........................  At the next removal of the PTG
                                           for any reason.
------------------------------------------------------------------------

    (2) After such removal, replace the affected bearing assembly in 
the PTG with a part eligible for installation before further flight.

(h) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Chicago ACO 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 
manager of the Chicago ACO Branch, send it to the attention of the 
person identified in paragraph (i)(1) of this AD.
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.

(i) Related Information

    (1) For more information about this AD, contact John Tallarovic, 
Aerospace Engineer, Chicago ACO Branch, FAA, 2300 E Devon Ave., Des 
Plaines, IL 60018; phone: 847-294-8180; fax: 847-294-7834; email: 
[email protected].
    (2) For service information identified in this AD, contact 
Rolls-Royce Corporation, 450 South Meridian Street, Mail Code NB-02-
05, Indianapolis, IN 46225; phone: 317-230-3774; email: 
royce.com">[email protected]royce.com; internet: www.rolls-royce.com. 
You may view this referenced service information at the FAA, Engine 
and Propeller Standards Branch, 1200 District Avenue, Burlington, MA 
01803. For information on the availability of this material at the 
FAA, call 781-238-7759.

    Issued in Burlington, Massachusetts, on January 25, 2018.
Robert J. Ganley,
Manager, Engine and Propeller Standards Branch, Aircraft Certification 
Service.
[FR Doc. 2018-01900 Filed 1-31-18; 8:45 am]
 BILLING CODE 4910-13-P