81 FR 46000 - Airworthiness Directives; Rolls-Royce plc Turbofan Engines
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 136 (July 15, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 136 (July 15, 2016)
| Page Range | 46000-46002 | |
| FR Document | 2016-16646 |
[Federal Register Volume 81, Number 136 (Friday, July 15, 2016)] [Proposed Rules] [Pages 46000-46002] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-16646] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-6692; Directorate Identifier 2016-NE-13-AD] RIN 2120-AA64 Airworthiness Directives; Rolls-Royce plc Turbofan Engines AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). ----------------------------------------------------------------------- SUMMARY: We propose to adopt a new airworthiness directive (AD) for all Rolls-Royce plc (RR) RB211-Trent 875-17, RB211-Trent 877-17, RB211- Trent 884-17, RB211-Trent 884B-17, RB211-Trent 892-17, RB211-Trent 892B-17, and RB211-Trent 895-17 turbofan engines. This proposed AD was prompted by a report of cracking and material release from an engine upper bifurcation fairing. This proposed AD would require repetitive inspections of the engine upper bifurcation fairing and repairing or replacing any fairing that fails inspection. We are proposing this AD to prevent failure of the engine fire protection system, engine fire, and damage to the airplane. DATES: We must receive comments on this NPRM by September 13, 2016. ADDRESSES: You may send comments by any of the following methods:Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. Mail: Docket Management Facility, U.S. Department of Transportation, 1200 New Jersey Avenue SE., West Building Ground Floor, Room W12-140, Washington, DC 20590-0001. Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Fax: 202-493-2251. For service information identified in this proposed AD, contact Rolls-Royce plc, Corporate Communications, P.O. Box 31, Derby, England, DE24 8BJ; phone: 011-44-1332-242424; fax: 011-44-1332-249936; email: http://www.rolls-royce.com/contact/civil_team.jsp; Internet: https://customers.rolls-royce.com/public/rollsroycecare. You may view this service information at the FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA. For information on the availability of this material at the FAA, call 781-238-7125. 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- 6692; 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 proposed AD, the mandatory continuing airworthiness information (MCAI), the regulatory evaluation, any comments received, and other information. The address for the Docket Office (phone: 800- 647-5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Wego Wang, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA 01803; phone: 781-238-7134; fax: 781- 238-7199; email: [email protected]. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this NPRM. Send your comments to an address listed under the ADDRESSES section. Include ``Docket No. FAA-2016-6692; Directorate Identifier 2016-NE-13-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 based on those comments. We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this NPRM. Discussion The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA AD 2016-0084, dated April 28, 2016 (referred to hereinafter as ``the MCAI''), to correct an unsafe condition for the specified products. The MCAI states: Inspection of in-service Rolls-Royce RB211 Trent 800 engines has identified cracking and/or material release from the upper bifurcation fairing. This fairing hardware mates to the aeroplane thrust reverser upper bifurcation forward fire seal. Both sets of hardware create the engine firewall to isolate the engine compartment fire zone, which is a firewall feature of the aeroplane type design. Damage (missing materials and holes/ [[Page 46001]] openings) to the upper bifurcation fairing creates a breach of the engine fire wall, which may decrease the effectiveness of the engine fire detection and suppression systems due to excess fan air entering the engine compartment fire zone. This could delay or prevent the fire detection and suppression system from functioning properly, and can result in an increased risk of prolonged burning, potentially allowing a fire to reach unprotected areas of the engine, strut and wing. Failure to inspect the engine upper bifurcation fairing as proposed by this AD could result in failure of the engine fire protection system, engine fire, and damage to the airplane. You may obtain further information by examining the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-6692. Related Service Information RR has issued Alert Non-Modification Service Bulletin (NMSB) RB.211-72-AJ165, dated March 31, 2016. The NMSB describes procedures for inspecting and, if necessary, repairing or replacing the engine upper bifurcation fairing. FAA's Determination and Requirements of This Proposed AD This product has been approved by the aviation authority of the United Kingdom and is approved for operation in the United States. Pursuant to our bilateral agreement with the European Community, EASA has notified us of the unsafe condition described in the MCAI and service information referenced above. We are proposing 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 products of the same type design. This NPRM would require repetitive inspections of the engine upper bifurcation fairing and repairing or replacing any fairing that fails inspection. Costs of Compliance We estimate that this proposed AD affects 125 engines installed on airplanes of U.S. registry. We estimate that it would take about 3.25 hours to inspect the upper bifurcation fairing do the inspection. We estimate that 5 engine fairings will require repair at 8 hours per engine and that an additional 5 engine fairings will require replacement at 30 hours per engine. We also estimate that materials and parts costs would be $500 for each engine. The cost for repair or replacement would be about $5,900 or $15,250 respectively. The average labor rate is $85 per hour. Based on these figures, we estimate the cost of this proposed AD on U.S. operators to be $55,681. 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 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 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. 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): Rolls-Royce plc: Docket No. FAA-2016-6692; Directorate Identifier 2016-NE-13-AD. (a) Comments Due Date We must receive comments by September 13, 2016. (b) Affected ADs None. (c) Applicability This AD applies to Rolls-Royce plc (RR) RB211-Trent 875-17, RB211-Trent 877-17, RB211-Trent 884-17, RB211-Trent 884B-17, RB211- Trent 892-17, RB211-Trent 892B-17, and RB211-Trent 895-17 turbofan engines. (d) Reason This AD was prompted by a report of cracking and material release from an engine upper bifurcation fairing. We are issuing this AD to prevent failure of the engine fire protection system, engine fire, and damage to the airplane. (e) Actions and Compliance Comply with this AD within the compliance times specified, unless already done. (1) Within 7,500 engine flight hours (EFHs) time since new, or since last inspection, or within 150 flight cycles after the effective date of this AD, whichever occurs later, inspect the engine upper bifurcation fairing for cracks or missing material. Use paragraph (e)(3) of this AD to perform the inspections. (2) Repeat the inspection required by this AD within every 7,500 EFH time since last inspection. (3) Inspect the engine upper bifurcation fairing as follows. Refer to Figure 1 of RR Alert Non-Modification Service Bulletin (NMSB) RB.211-72-AJ165, dated March 31, 2016, for guidance on upper bifurcation fairing inspection locations. (i) Visually inspect upper bifurcation fairing seal face 22, seal support 23, and zone A for any cracks or material loss on the right side. (A) If fairing seal face 22 is found to have released material, repair or replace the fairing before further flight. (B) If there is a single crack found on fairing seal face 22, shorter than 6 mm, repair or replace the fairing within 100 engine flight cycles, or at the next shop visit, whichever occurs sooner. (C) If there is a single crack found on fairing seal face 22, longer than 6 mm, repair or replace the fairing within 15 engine flight cycles or at the next shop visit, whichever occurs sooner. (D) If there are two or more cracks found on fairing seal face 22, replace the fairing [[Page 46002]] within 15 engine flight cycles or at next shop visit, whichever occurs sooner. (E) If there is any cracking or material loss found on seal support 23, replace the fairing within 15 engine flight cycles or at next shop visit, whichever occurs sooner. (ii) If the visual inspection required by paragraph (e)(3)(i) of this AD does not detect any crack, fluorescent penetrant inspect zone A. Refer to AMM TASK 70-20-02, Water Washable Fluorescent Penetrant Inspection (Maintenance Process 213), or OMat 632, high sensitivity fluorescent penetrant inspection, for guidance on fluorescent penetrant inspection. (A) If a crack shorter than 6 mm is detected, repair or replace the fairing within 100 engine flight cycles, or at the next shop visit, whichever occurs sooner. (B) If a crack longer than 6 mm is detected, repair or replace the fairing within 15 engine flight cycles or at the next shop visit, whichever occurs sooner. Definition For the purpose of this AD, a ``shop visit'' is defined as induction of an engine into the shop for maintenance involving the separation of pairs of major mating engine flanges, except that the separation of engine flanges solely for the purposes of transportation without subsequent engine maintenance does not constitute an engine shop visit. (f) Alternative Methods of Compliance (AMOCs) The Manager, Engine Certification Office, FAA, may approve AMOCs for this AD. Use the procedures found in 14 CFR 39.19 to make your request. You may email your request to: [email protected]. (g) Related Information (1) For more information about this AD, contact Wego Wang, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA 01803; phone: 781-238-7134; fax: 781-238-7199; email: [email protected]. (2) Refer to MCAI European Aviation Safety Agency AD 2016-0084, dated April 28, 2016, for more information. You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating it in Docket No. FAA-2016-6692. (3) RR NMSB RB.211-72-AJ165, dated March 31, 2016, can be obtained from RR, using the contact information in paragraph (g)(4) of this proposed AD. (4) For service information identified in this proposed AD, contact Rolls-Royce plc, Corporate Communications, P.O. Box 31, Derby, England, DE24 8BJ; phone: 011-44-1332-242424; fax: 011-44- 1332-249936; email: http://www.rolls-royce.com/contact/civil_team.jsp; Internet: https://customers.rolls-royce.com/public/rollsroycecare. (5) You may view this service information at the FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA. For information on the availability of this material at the FAA, call 781-238-7125. Issued in Burlington, Massachusetts, on July 1, 2016. Ann C. Mollica, Acting Manager, Engine & Propeller Directorate, Aircraft Certification Service. [FR Doc. 2016-16646 Filed 7-14-16; 8:45 am] BILLING CODE 4910-13-P
![46000 Federal Register / Vol. 81, No. 136 / Friday, July 15, 2016 / Proposed Rules
GL 5000 GVFD AMM—Part II, Revision 9, DEPARTMENT OF TRANSPORTATION Examining the AD Docket
dated March 3, 2014; as applicable.
You may examine the AD docket on
(j) Corrective Action Federal Aviation Administration the Internet at http://
If any FCU fails any operational test www.regulations.gov by searching for
14 CFR Part 39 and locating Docket No. FAA–2016–
required by this AD: Before further flight,
repair using a method approved by the 6692; or in person at the Docket
[Docket No. FAA–2016–6692; Directorate
Manager, New York ACO, ANE–170, FAA; or Identifier 2016–NE–13–AD] Operations office between 9 a.m. and 5
Transport Canada Civil Aviation (TCCA); or p.m., Monday through Friday, except
Bombardier, Inc.’s TCCA Design Approval RIN 2120–AA64 Federal holidays. The AD docket
Organization (DAO). contains this proposed AD, the
(k) Other FAA AD Provisions Airworthiness Directives; Rolls-Royce mandatory continuing airworthiness
plc Turbofan Engines information (MCAI), the regulatory
The following provisions also apply to this
AD:
evaluation, any comments received, and
AGENCY: Federal Aviation other information. The address for the
(1) Alternative Methods of Compliance Administration (FAA), DOT.
(AMOCs): The Manager, New York Aircraft Docket Office (phone: 800–647–5527) is
ACTION: Notice of proposed rulemaking in the ADDRESSES section. Comments
Certification Office (ACO), ANE–170, FAA,
has the authority to approve AMOCs for this (NPRM). will be available in the AD docket
AD, if requested using the procedures found shortly after receipt.
in 14 CFR 39.19. In accordance with 14 CFR
SUMMARY: We propose to adopt a new
FOR FURTHER INFORMATION CONTACT:
39.19, send your request to your principal airworthiness directive (AD) for all
Rolls-Royce plc (RR) RB211–Trent 875– Wego Wang, Aerospace Engineer,
inspector or local Flight Standards District Engine Certification Office, FAA, Engine
Office, as appropriate. If sending information 17, RB211–Trent 877–17, RB211–Trent
884–17, RB211–Trent 884B–17, RB211– & Propeller Directorate, 1200 District
directly to the ACO, send it to ATTN: Avenue, Burlington, MA 01803; phone:
Program Manager, Continuing Operational Trent 892–17, RB211–Trent 892B–17,
and RB211–Trent 895–17 turbofan 781–238–7134; fax: 781–238–7199;
Safety, FAA, New York ACO, 1600 Stewart
Avenue, Suite 410, Westbury, NY 11590; engines. This proposed AD was email: wego.wang@faa.gov.
telephone 516–228–7300; fax 516–794–5531. prompted by a report of cracking and SUPPLEMENTARY INFORMATION:
Before using any approved AMOC, notify material release from an engine upper Comments Invited
your appropriate principal inspector, or bifurcation fairing. This proposed AD
lacking a principal inspector, the manager of We invite you to send any written
would require repetitive inspections of
the local flight standards district office/ relevant data, views, or arguments about
the engine upper bifurcation fairing and
certificate holding district office. The AMOC this NPRM. Send your comments to an
repairing or replacing any fairing that
approval letter must specifically reference address listed under the ADDRESSES
this AD. fails inspection. We are proposing this
section. Include ‘‘Docket No. FAA–
(2) Contacting the Manufacturer: For any AD to prevent failure of the engine fire
2016–6692; Directorate Identifier 2016–
requirement in this AD to obtain corrective protection system, engine fire, and
NE–13–AD’’ at the beginning of your
actions from a manufacturer, the action must damage to the airplane.
comments. We specifically invite
be accomplished using a method approved DATES: We must receive comments on comments on the overall regulatory,
by the Manager, New York ACO, ANE–170, this NPRM by September 13, 2016.
FAA; or TCCA; or Bombardier, Inc.’s TCCA economic, environmental, and energy
DAO. If approved by the DAO, the approval ADDRESSES: You may send comments by aspects of this NPRM. We will consider
must include the DAO-authorized signature. any of the following methods: all comments received by the closing
• Federal eRulemaking Portal: Go to date and may amend this NPRM based
(l) Related Information http://www.regulations.gov. Follow the on those comments.
(1) Refer to Mandatory Continuing instructions for submitting comments. We will post all comments we
Airworthiness Information (MCAI) Canadian • Mail: Docket Management Facility, receive, without change, to http://
Airworthiness Directive CF–2015–06R1, U.S. Department of Transportation, 1200 www.regulations.gov, including any
dated April 22, 2015, for related information. New Jersey Avenue SE., West Building personal information you provide. We
This MCAI may be found in the AD docket Ground Floor, Room W12–140, will also post a report summarizing each
on the Internet at http://www.regulations.gov
Washington, DC 20590–0001. substantive verbal contact with FAA
by searching for and locating Docket No.
FAA–2016–8177. • Hand Delivery: Deliver to Mail personnel concerning this NPRM.
(2) For service information identified in address above between 9 a.m. and 5
Discussion
this AD, contact Bombardier, Inc., 400 Côte- p.m., Monday through Friday, except
Vertu Road West, Dorval, Québec H4S 1Y9, Federal holidays. The European Aviation Safety Agency
Canada; telephone 514–855–5000; fax 514– • Fax: 202–493–2251. (EASA), which is the Technical Agent
855–7401; email thd.crj@ For service information identified in for the Member States of the European
aero.bombardier.com; Internet http:// this proposed AD, contact Rolls-Royce Community, has issued EASA AD 2016–
www.bombardier.com. You may view this plc, Corporate Communications, P.O. 0084, dated April 28, 2016 (referred to
service information at the FAA, Transport Box 31, Derby, England, DE24 8BJ; hereinafter as ‘‘the MCAI’’), to correct an
Airplane Directorate, 1601 Lind Avenue SW., phone: 011–44–1332–242424; fax: 011– unsafe condition for the specified
Renton, WA. For information on the products. The MCAI states:
44–1332–249936; email: http://
asabaliauskas on DSK3SPTVN1PROD with PROPOSALS
availability of this material at the FAA, call
425–227–1221.
www.rolls-royce.com/contact/civil_ Inspection of in-service Rolls-Royce RB211
team.jsp; Internet: https:// Trent 800 engines has identified cracking
Issued in Renton, Washington, on July 8, customers.rolls-royce.com/public/ and/or material release from the upper
2016. rollsroycecare. You may view this bifurcation fairing. This fairing hardware
Michael Kaszycki, service information at the FAA, Engine mates to the aeroplane thrust reverser upper
bifurcation forward fire seal. Both sets of
Acting Manager, Transport Airplane & Propeller Directorate, 1200 District hardware create the engine firewall to isolate
Directorate, Aircraft Certification Service. Avenue, Burlington, MA. For the engine compartment fire zone, which is
[FR Doc. 2016–16731 Filed 7–14–16; 8:45 am] information on the availability of this a firewall feature of the aeroplane type
BILLING CODE 4910–13–P material at the FAA, call 781–238–7125. design. Damage (missing materials and holes/
VerDate Sep<11>2014 16:59 Jul 14, 2016 Jkt 238001 PO 00000 Frm 00017 Fmt 4702 Sfmt 4702 E:\FR\FM\15JYP1.SGM 15JYP1](https://thefederalregister.org/doc/81_FR_46136/page/1.svg)
![Federal Register / Vol. 81, No. 136 / Friday, July 15, 2016 / Proposed Rules 46001
openings) to the upper bifurcation fairing respectively. The average labor rate is PART 39—AIRWORTHINESS
creates a breach of the engine fire wall, $85 per hour. Based on these figures, we DIRECTIVES
which may decrease the effectiveness of the estimate the cost of this proposed AD on
engine fire detection and suppression ■ 1. The authority citation for part 39
systems due to excess fan air entering the
U.S. operators to be $55,681.
continues to read as follows:
engine compartment fire zone. This could Authority for This Rulemaking
delay or prevent the fire detection and Authority: 49 U.S.C. 106(g), 40113, 44701.
suppression system from functioning Title 49 of the United States Code
properly, and can result in an increased risk specifies the FAA’s authority to issue § 39.13 [Amended]
of prolonged burning, potentially allowing a rules on aviation safety. Subtitle I, ■ 2. The FAA amends § 39.13 by adding
fire to reach unprotected areas of the engine, section 106, describes the authority of the following new airworthiness
strut and wing. the FAA Administrator. ‘‘Subtitle VII: directive (AD):
Failure to inspect the engine upper Aviation Programs,’’ describes in more Rolls-Royce plc: Docket No. FAA–2016–
bifurcation fairing as proposed by this detail the scope of the Agency’s 6692; Directorate Identifier 2016–NE–
AD could result in failure of the engine authority. 13–AD.
fire protection system, engine fire, and We are issuing this rulemaking under (a) Comments Due Date
damage to the airplane. the authority described in ‘‘Subtitle VII,
You may obtain further information We must receive comments by September
Part A, Subpart III, Section 44701: 13, 2016.
by examining the MCAI in the AD General requirements.’’ Under that
docket on the Internet at http:// section, Congress charges the FAA with (b) Affected ADs
www.regulations.gov by searching for promoting safe flight of civil aircraft in None.
and locating Docket No. FAA–2016– air commerce by prescribing regulations (c) Applicability
6692. for practices, methods, and procedures This AD applies to Rolls-Royce plc (RR)
Related Service Information the Administrator finds necessary for RB211–Trent 875–17, RB211–Trent 877–17,
safety in air commerce. This regulation RB211–Trent 884–17, RB211–Trent 884B–17,
RR has issued Alert Non-Modification is within the scope of that authority RB211–Trent 892–17, RB211–Trent 892B–17,
Service Bulletin (NMSB) RB.211–72– because it addresses an unsafe condition and RB211–Trent 895–17 turbofan engines.
AJ165, dated March 31, 2016. The that is likely to exist or develop on
NMSB describes procedures for (d) Reason
products identified in this rulemaking
inspecting and, if necessary, repairing or This AD was prompted by a report of
action. cracking and material release from an engine
replacing the engine upper bifurcation
fairing. Regulatory Findings upper bifurcation fairing. We are issuing this
AD to prevent failure of the engine fire
FAA’s Determination and Requirements We determined that this proposed AD protection system, engine fire, and damage to
of This Proposed AD would not have federalism implications the airplane.
This product has been approved by under Executive Order 13132. This (e) Actions and Compliance
the aviation authority of the United proposed AD would not have a
Comply with this AD within the
Kingdom and is approved for operation substantial direct effect on the States, on compliance times specified, unless already
in the United States. Pursuant to our the relationship between the national done.
bilateral agreement with the European Government and the States, or on the (1) Within 7,500 engine flight hours (EFHs)
Community, EASA has notified us of distribution of power and time since new, or since last inspection, or
responsibilities among the various within 150 flight cycles after the effective
the unsafe condition described in the date of this AD, whichever occurs later,
MCAI and service information levels of government.
inspect the engine upper bifurcation fairing
referenced above. We are proposing this For the reasons discussed above, I for cracks or missing material. Use paragraph
AD because we evaluated all certify this proposed regulation: (e)(3) of this AD to perform the inspections.
information provided by EASA and (1) Is not a ‘‘significant regulatory (2) Repeat the inspection required by this
determined the unsafe condition exists action’’ under Executive Order 12866, AD within every 7,500 EFH time since last
and is likely to exist or develop on other (2) Is not a ‘‘significant rule’’ under inspection.
the DOT Regulatory Policies and (3) Inspect the engine upper bifurcation
products of the same type design. This fairing as follows. Refer to Figure 1 of RR
NPRM would require repetitive Procedures (44 FR 11034, February 26,
Alert Non-Modification Service Bulletin
inspections of the engine upper 1979), (NMSB) RB.211–72–AJ165, dated March 31,
bifurcation fairing and repairing or (3) Will not affect intrastate aviation 2016, for guidance on upper bifurcation
replacing any fairing that fails in Alaska to the extent that it justifies fairing inspection locations.
inspection. making a regulatory distinction, and (i) Visually inspect upper bifurcation
(4) Will not have a significant fairing seal face 22, seal support 23, and zone
Costs of Compliance economic impact, positive or negative, A for any cracks or material loss on the right
We estimate that this proposed AD side.
on a substantial number of small entities
(A) If fairing seal face 22 is found to have
affects 125 engines installed on under the criteria of the Regulatory released material, repair or replace the fairing
airplanes of U.S. registry. We estimate Flexibility Act. before further flight.
that it would take about 3.25 hours to (B) If there is a single crack found on
inspect the upper bifurcation fairing do List of Subjects in 14 CFR Part 39
fairing seal face 22, shorter than 6 mm, repair
asabaliauskas on DSK3SPTVN1PROD with PROPOSALS
the inspection. We estimate that 5 Air transportation, Aircraft, Aviation or replace the fairing within 100 engine flight
engine fairings will require repair at 8 safety, Incorporation by reference, cycles, or at the next shop visit, whichever
hours per engine and that an additional Safety. occurs sooner.
5 engine fairings will require (C) If there is a single crack found on
The Proposed Amendment fairing seal face 22, longer than 6 mm, repair
replacement at 30 hours per engine. We or replace the fairing within 15 engine flight
also estimate that materials and parts Accordingly, under the authority cycles or at the next shop visit, whichever
costs would be $500 for each engine. delegated to me by the Administrator, occurs sooner.
The cost for repair or replacement the FAA proposes to amend 14 CFR part (D) If there are two or more cracks found
would be about $5,900 or $15,250 39 as follows: on fairing seal face 22, replace the fairing
VerDate Sep<11>2014 16:59 Jul 14, 2016 Jkt 238001 PO 00000 Frm 00018 Fmt 4702 Sfmt 4702 E:\FR\FM\15JYP1.SGM 15JYP1](https://thefederalregister.org/doc/81_FR_46136/page/2.svg)
![46002 Federal Register / Vol. 81, No. 136 / Friday, July 15, 2016 / Proposed Rules
within 15 engine flight cycles or at next shop Issued in Burlington, Massachusetts, on www.regulations.gov by searching for
visit, whichever occurs sooner. July 1, 2016. and locating Docket No. FAA–2016–
(E) If there is any cracking or material loss Ann C. Mollica, 8501; or in person at the Docket
found on seal support 23, replace the fairing Acting Manager, Engine & Propeller Operations Office between 9 a.m. and 5
within 15 engine flight cycles or at next shop Directorate, Aircraft Certification Service. p.m., Monday through Friday, except
visit, whichever occurs sooner.
(ii) If the visual inspection required by
[FR Doc. 2016–16646 Filed 7–14–16; 8:45 am] Federal holidays. The AD docket
paragraph (e)(3)(i) of this AD does not detect BILLING CODE 4910–13–P contains this proposed AD, the
any crack, fluorescent penetrant inspect zone economic evaluation, any comments
A. Refer to AMM TASK 70–20–02, Water received, and other information. The
Washable Fluorescent Penetrant Inspection DEPARTMENT OF TRANSPORTATION street address for the Docket Operations
(Maintenance Process 213), or OMat 632, Office (telephone 800–647–5527) is in
high sensitivity fluorescent penetrant Federal Aviation Administration the ADDRESSES section. Comments will
inspection, for guidance on fluorescent be available in the AD docket shortly
penetrant inspection. 14 CFR Part 39 after receipt.
(A) If a crack shorter than 6 mm is
[Docket No. FAA–2016–8501; Directorate For service information identified in
detected, repair or replace the fairing within
100 engine flight cycles, or at the next shop Identifier 2014–SW–042–AD] this proposed AD, contact Sikorsky
visit, whichever occurs sooner. RIN 2120–AA64
Aircraft Corporation, Customer Service
(B) If a crack longer than 6 mm is detected, Engineering, 124 Quarry Road,
repair or replace the fairing within 15 engine Airworthiness Directives; Sikorsky Trumbull, CT 06611; telephone 1–800-
flight cycles or at the next shop visit, Aircraft Corporation Helicopters Winged-S or 203–416–4299; email
whichever occurs sooner. sikorskywcs@sikorsky.com. You may
AGENCY: Federal Aviation review the referenced service
Definition
Administration (FAA), DOT. information at the FAA, Office of the
For the purpose of this AD, a ‘‘shop visit’’ ACTION: Notice of proposed rulemaking
is defined as induction of an engine into the Regional Counsel, Southwest Region,
(NPRM). 10101 Hillwood Pkwy., Room 6N–321,
shop for maintenance involving the
separation of pairs of major mating engine SUMMARY: We propose to adopt a new Fort Worth, Texas 76177.
flanges, except that the separation of engine airworthiness directive (AD) for FOR FURTHER INFORMATION CONTACT:
flanges solely for the purposes of Kristopher Greer, Aviation Safety
Sikorsky Aircraft Corporation (Sikorsky)
transportation without subsequent engine Engineer, Boston Aircraft Certification
maintenance does not constitute an engine Model S–92A helicopters. This
proposed AD would require inspecting Office, Engine & Propeller Directorate,
shop visit.
the main transmission forward (fwd) 1200 District Avenue, Burlington,
(f) Alternative Methods of Compliance and aft frame assembly and adjacent Massachusetts 01803; telephone (781)
(AMOCs) skins for a crack and loose fasteners and 238–7799; email Kristopher.Greer@
The Manager, Engine Certification Office, establishing life limits for certain frame faa.gov.
FAA, may approve AMOCs for this AD. Use assemblies. This proposed AD is SUPPLEMENTARY INFORMATION:
the procedures found in 14 CFR 39.19 to prompted by fatigue analysis indicating
make your request. You may email your Comments Invited
request to: ANE-AD-AMOC@faa.gov.
stress concentrations as well as the
discovery of a crack in the station (STA) We invite you to participate in this
(g) Related Information 362 frame and skin on a Model S–92A rulemaking by submitting written
(1) For more information about this AD, helicopter. The proposed actions are comments, data, or views. We also
contact Wego Wang, Aerospace Engineer, intended to detect a crack in a frame invite comments relating to the
Engine Certification Office, FAA, Engine & assembly and prevent failure of a frame economic, environmental, energy, or
Propeller Directorate, 1200 District Avenue, and subsequent loss of control of the federalism impacts that might result
Burlington, MA 01803; phone: 781–238– helicopter. from adopting the proposals in this
7134; fax: 781–238–7199; email: wego.wang@
faa.gov. DATES: We must receive comments on document. The most helpful comments
(2) Refer to MCAI European Aviation this proposed AD by September 13, reference a specific portion of the
Safety Agency AD 2016–0084, dated April 2016. proposal, explain the reason for any
28, 2016, for more information. You may recommended change, and include
ADDRESSES: You may send comments by
examine the MCAI in the AD docket on the supporting data. To ensure the docket
any of the following methods:
Internet at http://www.regulations.gov by does not contain duplicate comments,
searching for and locating it in Docket No. • Federal eRulemaking Docket: Go to
http://www.regulations.gov. Follow the commenters should send only one copy
FAA–2016–6692. of written comments, or if comments are
(3) RR NMSB RB.211–72–AJ165, dated online instructions for sending your
comments electronically. filed electronically, commenters should
March 31, 2016, can be obtained from RR,
using the contact information in paragraph • Fax: 202–493–2251. submit only one time.
(g)(4) of this proposed AD. • Mail: Send comments to the U.S. We will file in the docket all
(4) For service information identified in Department of Transportation, Docket comments that we receive, as well as a
this proposed AD, contact Rolls-Royce plc, Operations, M–30, West Building report summarizing each substantive
Corporate Communications, P.O. Box 31, Ground Floor, Room W12–140, 1200 public contact with FAA personnel
Derby, England, DE24 8BJ; phone: 011–44– concerning this proposed rulemaking.
asabaliauskas on DSK3SPTVN1PROD with PROPOSALS
New Jersey Avenue SE., Washington,
1332–242424; fax: 011–44–1332–249936; DC 20590–0001. Before acting on this proposal, we will
email: http://www.rolls-royce.com/contact/
• Hand Delivery: Deliver to the consider all comments we receive on or
civil_team.jsp; Internet: https:// before the closing date for comments.
customers.rolls-royce.com/public/ ‘‘Mail’’ address between 9 a.m. and 5
p.m., Monday through Friday, except We will consider comments filed after
rollsroycecare.
(5) You may view this service information Federal holidays. the comment period has closed if it is
at the FAA, Engine & Propeller Directorate, possible to do so without incurring
Examining the AD Docket expense or delay. We may change this
1200 District Avenue, Burlington, MA. For
information on the availability of this You may examine the AD docket on proposal in light of the comments we
material at the FAA, call 781–238–7125. the Internet at http:// receive.
VerDate Sep<11>2014 16:59 Jul 14, 2016 Jkt 238001 PO 00000 Frm 00019 Fmt 4702 Sfmt 4702 E:\FR\FM\15JYP1.SGM 15JYP1](https://thefederalregister.org/doc/81_FR_46136/page/3.svg)
Document Created: 2016-07-15 02:53:32
Document Modified: 2016-07-15 02:53:32
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Proposed Rules | |
| Action | Notice of proposed rulemaking (NPRM). | |
| Dates | We must receive comments on this NPRM by September 13, 2016. | |
| Contact | Wego Wang, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA 01803; phone: 781-238-7134; fax: 781- 238-7199; email: [email protected] | |
| FR Citation | 81 FR 46000 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
2025 Federal Register | Disclaimer | Privacy Policy
USC | CFR | eCFR