82 FR 24236 - Airworthiness Directives; Rolls-Royce Deutschland Ltd & Co KG Turbofan Engines
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 82, Issue 101 (May 26, 2017)
Federal Aviation Administration
Federal Register Volume 82, Issue 101 (May 26, 2017)
| Page Range | 24236-24239 | |
| FR Document | 2017-10437 |
[Federal Register Volume 82, Number 101 (Friday, May 26, 2017)] [Rules and Regulations] [Pages 24236-24239] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2017-10437] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2017-0186; Directorate Identifier 2017-NE-07-AD; Amendment 39-18899; AD 2017-10-25] RIN 2120-AA64 Airworthiness Directives; Rolls-Royce Deutschland Ltd & Co KG Turbofan Engines AGENCY: Federal Aviation Administration (FAA), DOT. [[Page 24237]] ACTION: Final rule; request for comments. ----------------------------------------------------------------------- SUMMARY: We are adopting a new airworthiness directive (AD) for all Rolls-Royce Deutschland Ltd & Co KG (RRD) model Spey 506-14A, Spey 555- 15, Spey 555-15H, Spey 555-15N, and Spey 555-15P turbofan engines. This AD requires reducing the maximum approved life limits for certain high- pressure compressor (HPC) stage 12 rotor disks. We are issuing this AD to correct the unsafe condition on these products. DATES: This AD becomes effective June 12, 2017. We must receive comments on this AD by July 10, 2017. 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: 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 AD, contact Rolls-Royce Deutschland Ltd & Co KG, Eschenweg 11-15827 Dahlewitz, Blankenfelde- Mahlow, Germany; phone: +49 0 33-7086-1944; fax: +49 0 33-7086-3276. You may view this service information at the FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA 01803. 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-2017- 0186; 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 mandatory continuing airworthiness information (MCAI), 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: Robert Green, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA 01803; phone: 781-238-7754; fax: 781- 238-7199; email: [email protected]. SUPPLEMENTARY INFORMATION: Comments Invited This AD is a final rule that involves requirements affecting flight safety, and we did not precede it by notice and opportunity for public comment. We invite you to send any written relevant data, views, or arguments about this AD. Send your comments to an address listed under the ADDRESSES section. Include ``Docket No. FAA-2017-0186; Directorate Identifier 2017-NE-07-AD'' at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this AD. We will consider all comments received by the closing date and may amend this AD 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 with FAA personnel concerning this AD. Discussion The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA AD 2017-0014, dated January 30, 2017 (referred to hereinafter as ``the MCAI''), to correct an unsafe condition for the specified products. The MCAI states: Based on revised stress analysis and life calculation, Rolls- Royce Deutschland (RRD) determined new provisional life limits for high pressure compressor (HPC) stage 12 rotor disks, Part Number (P/ N) EU25917, P/N EU56963, P/N JR10242 and P/N JR18449, reducing the maximum approved life limits currently defined in the RRD Spey 555- 15 Engine Maintenance Manual (EMM), Chapter 5-10-1, currently at the revision dated July 2015 and the Engine Overhaul Manual (EOM), Chapter 5-10, revision dated November 2014. The Spey 506-14A EMM, Chapter 5-10-1 revision dated October 1993 as well as the Spey 506- 14A EOM, Chapter 5-10 revision dated November 1992 already contain the applicable life limit. Failure to replace an affected HPC stage 12 rotor disk before exceeding these limits, could lead to an uncontained engine failure, possibly resulting in damage to, and/or reduced control of, the aeroplane. To address this potential unsafe condition, RRD issued Alert Non-Modification Service Bulletin (NMSB) Sp72-A1071 to provide instructions to determine (re-calculate) the consumed and remaining service life for each part. For the reasons described above, this AD requires re-calculation of the service life (consumed and remaining) of the affected HPC stage 12 rotor disks and, depending on the results, implementation of the life limits. It is expected that the affected reduced life limits are introduced into a next revision of the RRD Spey 555-15 Engine EMM and EOM. 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-2017-0186. Related Service Information RRD has issued Alert Non-Modification Service Bulletin (NMSB) Sp72- A1071, Revision 1, dated January 27, 2017. The Alert NMSB provides instructions to re-calculate the consumed and remaining service life for HPC stage 12 rotor disks, part number (P/N) EU25917, P/N EU56963, P/N JR10242, and P/N JR18449. This service information is available by the means identified in the ADDRESSES section. FAA's Determination and Requirements of This AD This product has been approved by the aviation authority of Germany, 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. 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 products of the same type design. This AD requires reducing the maximum approved life limits and re-calculating the consumed and remaining service life for HPC stage 12 rotor disks P/N EU25917, P/N EU56963, P/N JR10242, and P/N JR18449. FAA's Determination of the Effective Date No domestic operators use this product. Therefore, we find that notice and opportunity for prior public comment are unnecessary and that good cause exists for making this amendment effective in less than 30 days. Costs of Compliance We estimate that this AD affects 0 engines installed on airplanes of U.S. registry. We estimate the following costs to comply with this AD: [[Page 24238]] Estimated Costs ---------------------------------------------------------------------------------------------------------------- Cost per Cost on U.S. Action Labor cost Parts cost product operators ---------------------------------------------------------------------------------------------------------------- Pro-rated lost life............... 1 work-hour x $85 per $3,900 $3,985 $0 hour = $85. ---------------------------------------------------------------------------------------------------------------- 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 above, I certify this AD: (1) Is not a ``significant regulatory action'' under Executive Order 12866, (2) Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation in Alaska 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): 2017-10-25 Rolls-Royce Deutschland Ltd & Co KG: Amendment 39-18899; Docket No. FAA-2017-0186; Directorate Identifier 2017-NE-07-AD. (a) Effective Date This AD is effective June 12, 2017. (b) Affected ADs None. (c) Applicability This AD applies to Rolls-Royce Deutschland Ltd & Co KG (RRD) Spey 506-14A, Spey 555-15, Spey 555-15H, Spey 555-15N, and Spey 555- 15P turbofan engines with high-pressure compressor (HPC) stage 12 rotor disks, part number (P/N) EU25917, P/N EU56963, P/N JR10242, or P/N JR18449, installed. (d) Subject Joint Aircraft System Component (JASC) 7230, Turbine Engine Compressor Section. (e) Reason This AD was prompted by RRD re-calculating the life limits for HPC stage 12 rotor disks, P/N EU25917, P/N EU56963, P/N JR10242, and P/N JR18449. We are issuing this AD to prevent failure of the HPC stage 12 rotor disk, uncontained HPC stage 12 rotor disk release, damage to the engine, and damage to the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Required Actions (1) Within 30 days after the effective date of this AD, determine if: (i) The affected part was ever operated in a Spey 555-15, Spey 555-15H, Spey 555-15N, or Spey 555-15P engine model, or (ii) the affected part was operated soley in a Spey 506-14A engine. (2) If the affected part was operated solely in a Spey 506-14A engine with no history of operating in a Spey 555-15, Spey 555-15H, Spey 555-15N, or Spey 555-15P engine, no further action is required. (3) If the affected part was operated in in both Spey 506-14A and Spey 555-15, Spey 555-15H, Spey 555-15N, or Spey 555-15P engine models, or solely in Spey 555-15, Spey 555-15H, Spey 555-15N, or Spey 555-15P engines, re-calculate the consumed cyclic life (and remaining service life) using the Maximum Approved Life for each engine model and take-off monitoring procedure as defined in Figures 1 and 2 to paragraph (g) of this AD. (4) After the effective date of this AD, the Maximum Approved Lives for the affected parts are as defined in Figure 2 to paragraph (g) of this AD. Calculate the consumed cyclic life (and remaining service life) using the Spey 555-15, Spey 555-15H, Spey 555-15N, or Spey 555-15P Maximum Approved Lives in Figure 2 to paragraph (g) of this AD. (5) For Spey 506-14A engines with an affected part installed, that do not have an engine shop visit after the effective date of this AD before the re-calculated consumed cyclic life of the affected part exceeds 14,700 flight cycles (FC), remove the affected part from service before the re-calculated consumed cyclic life exceeds 14,700 FC, or 50 FC or 30 days after the effective date of this AD, whichever occurs later. (6) For Spey 555-15, Spey 555-15H, Spey 555-15N, or Spey 555-15P engines with an affected part installed, that do not have an engine shop visit after the effective date of this AD before the re- calculated consumed cyclic life of the affected part exceeds the Maximum Approved Lives in Figure 2 to paragraph (g) of this AD, remove the affected part from service before the re-calculated consumed cyclic life exceeds the later of the following: (i) Maximum Approved Lives in Figure 2 to paragraph (g) of this AD, or (ii) 200 FC or 90 days after the effective date of this AD, or before exceeding the In-Service Replacement Limits defined in Figure 3 to paragraph (g) of this AD, whichever occurs first. [[Page 24239]] Figure 1 to Paragraph (g)--Spey 506-14A High-Pressure Compressor (HPC) Stage 12 Rotor Disk Maximum Approved Life ------------------------------------------------------------------------ Flight cycles ------------------------------------------------------------------------ HPC stage 12 rotor disk, P/N EU25917, EU56963, and 14,700 JR10242............................................. ------------------------------------------------------------------------ Figure 2 to Paragraph (g)--Spey 555-15, Spey 555-15H, Spey 555-15N, or Spey 555-15P HPC Stage 12 Rotor Disk, P/N EU25917, EU56963, JR10242, and JR18449, Maximum Approved Life ------------------------------------------------------------------------ Maximum approved Take-off monitoring procedure lives (flight cycles) ------------------------------------------------------------------------ (A) With no high-pressure (HP) revolutions per minute 11,500 (RPM) monitoring.................................... HP RPM monitoring; stated RPM not exceeded on more than 15% of occasions: (B) 100% N2...................................... 13,600 (C) 99% N2....................................... 17,100 (D) 98% N2....................................... 19,300 (E) 97% N2....................................... 20,500 (F) No HP RPM monitoring required Datum (Average N2 16,800 at 99.5%)........................................... ------------------------------------------------------------------------ Figure 3 to Paragraph (g)--Spey 555-15, Spey 555-15H, Spey 555-15N, or Spey 555-15P HPC Stage 12 Rotor Disk, P/N EU25917, EU56963, JR10242, and JR18449, In-Service Replacement Limits ------------------------------------------------------------------------ In-service replacement Take-off monitoring procedure limits (flight cycles) ------------------------------------------------------------------------ (A) With no HP RPM monitoring........................ 13,800 HP RPM monitoring; stated RPM not exceeded on more than 15% of occasions: (B) 100% N2...................................... 15,600 (C) 99% N2....................................... 17,600 (D) 98% N2....................................... 19,700 (E) 97% N2....................................... 22,100 (F) No HP RPM monitoring required Datum (Average N2 17,300 at 99.5%)........................................... ------------------------------------------------------------------------ (h) Installation Prohibition After the effective date of this AD, installation of a serviceable spare engine or release to service of an engine after any shop visit is allowed, provided the affected part has not exceeded the Maximum Approved Lives in Figures 1 or 2 to paragraph (g) of this AD. (i) Definition For the purpose of this AD, a shop visit is the induction of an engine into the shop for maintenance or overhaul. The separation of engine flanges solely for the purpose of transporting the engine without subsequent engine maintenance does not constitute an engine shop visit. (j) 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]. (k) Related Information (1) For more information about this AD, contact Robert Green, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA 01803; phone: 781-238-7754; fax: 781-238-7199; email: [email protected]. (2) Refer to MCAI European Aviation Safety Agency (EASA), AD 2017-0014, dated January 30, 2017, 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-2017-0186. (3) RRD Alert Non-Modification Service Bulletin Sp72-A1071, Revision 1, dated January 27, 2017, which is not incorporated by reference in this AD, can be obtained from RRD, using the contact information in paragraph (k)(4) of this AD. (4) For RRD service information identified in this AD, contact Rolls-Royce Deutschland Ltd & Co KG, Eschenweg 11-15827 Dahlewitz, Blankenfelde-Mahlow, Germany; phone: +49 0 33-7086-1944; fax: +49 0 33-7086-3276. (5) You may view this service information at FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA 01803. For information on the availability of this material at the FAA, call 781-238-7125. Issued in Burlington, Massachusetts, on May 9, 2017. Robert J. Ganley, Acting Manager, Engine & Propeller Directorate, Aircraft Certification Service. [FR Doc. 2017-10437 Filed 5-25-17; 8:45 am] BILLING CODE 4910-13-P
![24236 Federal Register / Vol. 82, No. 101 / Friday, May 26, 2017 / Rules and Regulations
intended to protect the airplane and its the airplane and occupants. Previously non-rechargeable lithium battery
occupants if failure occurs. certified non-rechargeable lithium installation must:
Special conditions 3, 7, and 8 are self- battery installations, as used in this 1. Be designed to maintain safe cell
explanatory. paragraph, are those installations temperatures and pressures under all
Special condition no. 4 makes it clear approved for certification projects foreseeable operating conditions to
that the flammable fluid fire protection applied for on or before the effective prevent fire and explosion.
requirements of § 25.863 apply to non- date of these special conditions. A 2. Be designed to prevent the
rechargeable lithium battery cosmetic change is a change in occurrence of self-sustaining,
installations. Section 25.863 is appearance only, and does not change uncontrollable increases in temperature
applicable to areas of the airplane that any function or safety characteristic of or pressure.
could be exposed to flammable fluid the battery installation. These special 3. Not emit explosive or toxic gases,
leakage from airplane systems. Non- conditions are also not applicable to either in normal operation or as a result
rechargeable lithium batteries contain unchanged, previously certified non- of its failure, that may accumulate in
an electrolyte that is a flammable fluid. rechargeable lithium battery hazardous quantities within the
Special condition no. 5 requires that installations that are affected by a airplane.
each non-rechargeable lithium battery change in a manner that improves the 4. Meet the requirements of § 25.863.
installation not damage surrounding safety of its installation. The FAA 5. Not damage surrounding structure
structure or adjacent systems, determined that these exclusions are in or adjacent systems, equipment, or
equipment, or electrical wiring from the public interest because the need to electrical wiring from corrosive fluids or
corrosive fluids or gases that may escape meet all of the special conditions might gases that may escape in such a way as
in such a way as to cause a major or otherwise deter these design changes to cause a major or more severe failure
more severe failure condition. that improve safety. condition.
While special condition no. 5 6. Have provisions to prevent any
addresses corrosive fluids and gases, Conclusion hazardous effect on airplane structure or
special condition no. 6 addresses heat. This action affects only a certain systems caused by the maximum
Special condition no. 6 requires that novel or unusual design feature on one amount of heat it can generate due to
each non-rechargeable lithium battery model of airplane. It is not a rule of any failure of it or its individual cells.
installation have provisions to prevent general applicability. 7. Have a failure sensing and warning
any hazardous effect on airplane The substance of these special system to alert the flightcrew if its
structure or systems caused by the conditions has been subjected to the failure affects safe operation of the
maximum amount of heat the battery notice and comment period in prior airplane.
installation can generate due to any instances and has been derived without 8. Have a means for the flightcrew or
failure of it or its individual cells. The substantive change from those maintenance personnel to determine the
means of meeting special conditions previously issued. It is unlikely that battery charge state if the battery’s
nos. 5 and 6 may be the same, but the prior public comment would result in a function is required for safe operation of
requirements are independent and significant change from the substance the airplane.
address different hazards. contained herein. Therefore, the FAA Note: A battery system consists of the
These special conditions apply to all has determined that prior public notice battery and any protective, monitoring, and
non-rechargeable lithium battery and comment are unnecessary and alerting circuitry or hardware inside or
installations in lieu of § 25.1353(b)(1) impracticable, and good cause exists for outside of the battery. It also includes vents
adopting these special conditions upon (where necessary) and packaging. For the
through (4) at Amendment 25–123 or purpose of these special conditions, a
§ 25.1353(c)(1) through (4) at earlier publication in the Federal Register. The ‘‘battery’’ and ‘‘battery system’’ are referred to
amendments. Those regulations remain FAA is requesting comments to allow as a battery.
in effect for other battery installations. interested persons to submit views that
These special conditions contain the may not have been submitted in Issued in Renton, Washington, on May 17,
additional safety standards that the response to the prior opportunities for 2017.
Administrator considers necessary to comment described above. Michael Kaszycki,
establish a level of safety equivalent to Assistant Manager, Transport Airplane
List of Subjects in 14 CFR Part 25
that established by the existing Directorate, Aircraft Certification Service.
airworthiness standards. Aircraft, Aviation safety, Reporting [FR Doc. 2017–10843 Filed 5–25–17; 8:45 am]
and recordkeeping requirements. BILLING CODE 4910–13–P
Applicability The authority citation for these
These special conditions are special conditions is as follows:
applicable to the 787–9 series airplanes. Authority: 49 U.S.C. 106(g), 40113, 44701, DEPARTMENT OF TRANSPORTATION
Should Boeing apply at a later date for 44702, 44704.
a change to the type certificate to Federal Aviation Administration
include another model incorporating the The Special Conditions
same novel or unusual design feature, Accordingly, pursuant to the 14 CFR Part 39
these special conditions would apply to authority delegated to me by the [Docket No. FAA–2017–0186; Directorate
that model as well. Administrator, the following special Identifier 2017–NE–07–AD; Amendment 39–
These special conditions are only conditions are issued as part of the type 18899; AD 2017–10–25]
applicable to design changes applied for certification basis for the Boeing Model
mstockstill on DSK30JT082PROD with RULES
after the effective date. RIN 2120–AA64
787–9 series airplanes.
These special conditions are not
Non-Rechargeable Lithium Battery Airworthiness Directives; Rolls-Royce
applicable to changes to previously
Installations Deutschland Ltd & Co KG Turbofan
certified non-rechargeable lithium
Engines
battery installations where the only In lieu of § 25.1353(b)(1) through (4)
change is either cosmetic or to relocate at Amendment 25–123 or § 25.1353(c)(1) AGENCY:Federal Aviation
the installation to improve the safety of through (4) at earlier amendments, each Administration (FAA), DOT.
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ESTIMATED COSTS
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
Pro-rated lost life .................... 1 work-hour × $85 per hour = $85 ......................................... $3,900 $3,985 $0
Authority for This Rulemaking Adoption of the Amendment (i) The affected part was ever operated in
a Spey 555–15, Spey 555–15H, Spey 555–
Title 49 of the United States Code Accordingly, under the authority
15N, or Spey 555–15P engine model, or
specifies the FAA’s authority to issue delegated to me by the Administrator,
(ii) the affected part was operated soley in
rules on aviation safety. Subtitle I, the FAA amends 14 CFR part 39 as a Spey 506–14A engine.
section 106, describes the authority of follows: (2) If the affected part was operated solely
the FAA Administrator. ‘‘Subtitle VII: in a Spey 506–14A engine with no history of
Aviation Programs,’’ describes in more PART 39—AIRWORTHINESS
operating in a Spey 555–15, Spey 555–15H,
detail the scope of the Agency’s DIRECTIVES
Spey 555–15N, or Spey 555–15P engine, no
authority. further action is required.
We are issuing this rulemaking under ■ 1. The authority citation for part 39
continues to read as follows: (3) If the affected part was operated in in
the authority described in ‘‘Subtitle VII, both Spey 506–14A and Spey 555–15, Spey
Part A, Subpart III, Section 44701: Authority: 49 U.S.C. 106(g), 40113, 44701.
555–15H, Spey 555–15N, or Spey 555–15P
General requirements.’’ Under that engine models, or solely in Spey 555–15,
§ 39.13 [Amended]
section, Congress charges the FAA with Spey 555–15H, Spey 555–15N, or Spey 555–
promoting safe flight of civil aircraft in ■ 2. The FAA amends § 39.13 by adding 15P engines, re-calculate the consumed
air commerce by prescribing regulations the following new airworthiness cyclic life (and remaining service life) using
for practices, methods, and procedures directive (AD): the Maximum Approved Life for each engine
the Administrator finds necessary for 2017–10–25 Rolls-Royce Deutschland Ltd & model and take-off monitoring procedure as
safety in air commerce. This regulation Co KG: Amendment 39–18899; Docket defined in Figures 1 and 2 to paragraph (g)
is within the scope of that authority No. FAA–2017–0186; Directorate of this AD.
because it addresses an unsafe condition Identifier 2017–NE–07–AD. (4) After the effective date of this AD, the
that is likely to exist or develop on (a) Effective Date Maximum Approved Lives for the affected
products identified in this rulemaking parts are as defined in Figure 2 to paragraph
This AD is effective June 12, 2017.
action. (g) of this AD. Calculate the consumed cyclic
(b) Affected ADs life (and remaining service life) using the
Regulatory Findings
None. Spey 555–15, Spey 555–15H, Spey 555–15N,
We determined that this AD will not or Spey 555–15P Maximum Approved Lives
have federalism implications under (c) Applicability
in Figure 2 to paragraph (g) of this AD.
Executive Order 13132. This AD will This AD applies to Rolls-Royce (5) For Spey 506–14A engines with an
not have a substantial direct effect on Deutschland Ltd & Co KG (RRD) Spey 506– affected part installed, that do not have an
the States, on the relationship between 14A, Spey 555–15, Spey 555–15H, Spey 555–
engine shop visit after the effective date of
the national government and the States, 15N, and Spey 555–15P turbofan engines
with high-pressure compressor (HPC) stage this AD before the re-calculated consumed
or on the distribution of power and 12 rotor disks, part number (P/N) EU25917, cyclic life of the affected part exceeds 14,700
responsibilities among the various P/N EU56963, P/N JR10242, or P/N JR18449, flight cycles (FC), remove the affected part
levels of government. installed. from service before the re-calculated
For the reasons discussed above, I consumed cyclic life exceeds 14,700 FC, or
certify this AD: (d) Subject
50 FC or 30 days after the effective date of
(1) Is not a ‘‘significant regulatory Joint Aircraft System Component (JASC) this AD, whichever occurs later.
action’’ under Executive Order 12866, 7230, Turbine Engine Compressor Section. (6) For Spey 555–15, Spey 555–15H, Spey
(2) Is not a ‘‘significant rule’’ under (e) Reason 555–15N, or Spey 555–15P engines with an
the DOT Regulatory Policies and affected part installed, that do not have an
This AD was prompted by RRD re-
Procedures (44 FR 11034, February 26, calculating the life limits for HPC stage 12 engine shop visit after the effective date of
1979), rotor disks, P/N EU25917, P/N EU56963, P/ this AD before the re-calculated consumed
(3) Will not affect intrastate aviation N JR10242, and P/N JR18449. We are issuing cyclic life of the affected part exceeds the
in Alaska to the extent that it justifies this AD to prevent failure of the HPC stage Maximum Approved Lives in Figure 2 to
making a regulatory distinction, and 12 rotor disk, uncontained HPC stage 12 rotor paragraph (g) of this AD, remove the affected
(4) Will not have a significant disk release, damage to the engine, and part from service before the re-calculated
economic impact, positive or negative, damage to the airplane. consumed cyclic life exceeds the later of the
on a substantial number of small entities (f) Compliance following:
under the criteria of the Regulatory (i) Maximum Approved Lives in Figure 2
Comply with this AD within the
Flexibility Act. compliance times specified, unless already
to paragraph (g) of this AD, or
done. (ii) 200 FC or 90 days after the effective
List of Subjects in 14 CFR Part 39 date of this AD, or before exceeding the In-
Air transportation, Aircraft, Aviation (g) Required Actions Service Replacement Limits defined in
safety, Incorporation by reference, Figure 3 to paragraph (g) of this AD,
mstockstill on DSK30JT082PROD with RULES
(1) Within 30 days after the effective date
Safety. of this AD, determine if: whichever occurs first.
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![Federal Register / Vol. 82, No. 101 / Friday, May 26, 2017 / Rules and Regulations 24239
FIGURE 1 TO PARAGRAPH (g)—SPEY 506–14A HIGH-PRESSURE COMPRESSOR (HPC) STAGE 12 ROTOR DISK MAXIMUM
APPROVED LIFE
Flight cycles
HPC stage 12 rotor disk, P/N EU25917, EU56963, and JR10242 ............................................................................................... 14,700
FIGURE 2 TO PARAGRAPH (g)—SPEY 555–15, SPEY 555–15H, SPEY 555–15N, OR SPEY 555–15P HPC STAGE 12
ROTOR DISK, P/N EU25917, EU56963, JR10242, AND JR18449, MAXIMUM APPROVED LIFE
Maximum
Take-off monitoring procedure approved lives
(flight cycles)
(A) With no high-pressure (HP) revolutions per minute (RPM) monitoring .................................................................................. 11,500
HP RPM monitoring; stated RPM not exceeded on more than 15% of occasions:
(B) 100% N2 ........................................................................................................................................................................... 13,600
(C) 99% N2 ............................................................................................................................................................................. 17,100
(D) 98% N2 ............................................................................................................................................................................. 19,300
(E) 97% N2 ............................................................................................................................................................................. 20,500
(F) No HP RPM monitoring required Datum (Average N2 at 99.5%) ........................................................................................... 16,800
FIGURE 3 TO PARAGRAPH (g)—SPEY 555–15, SPEY 555–15H, SPEY 555–15N, OR SPEY 555–15P HPC STAGE 12
ROTOR DISK, P/N EU25917, EU56963, JR10242, AND JR18449, IN-SERVICE REPLACEMENT LIMITS
In-service
Take-off monitoring procedure replacement limits
(flight cycles)
(A) With no HP RPM monitoring ................................................................................................................................................... 13,800
HP RPM monitoring; stated RPM not exceeded on more than 15% of occasions:
(B) 100% N2 ........................................................................................................................................................................... 15,600
(C) 99% N2 ............................................................................................................................................................................. 17,600
(D) 98% N2 ............................................................................................................................................................................. 19,700
(E) 97% N2 ............................................................................................................................................................................. 22,100
(F) No HP RPM monitoring required Datum (Average N2 at 99.5%) ........................................................................................... 17,300
(h) Installation Prohibition (2) Refer to MCAI European Aviation DEPARTMENT OF TRANSPORTATION
After the effective date of this AD, Safety Agency (EASA), AD 2017–0014, dated
installation of a serviceable spare engine or January 30, 2017, for more information. You Federal Aviation Administration
release to service of an engine after any shop may examine the MCAI in the AD docket on
visit is allowed, provided the affected part the Internet at http://www.regulations.gov by 14 CFR Part 39
has not exceeded the Maximum Approved searching for and locating it in Docket No.
[Docket No. FAA–2017–0451; Directorate
Lives in Figures 1 or 2 to paragraph (g) of this FAA–2017–0186. Identifier 2017–CE–015–AD; Amendment
AD. (3) RRD Alert Non-Modification Service 39–18885; AD 2017–10–11]
(i) Definition Bulletin Sp72–A1071, Revision 1, dated
January 27, 2017, which is not incorporated RIN 2120–AA64
For the purpose of this AD, a shop visit is by reference in this AD, can be obtained from
the induction of an engine into the shop for RRD, using the contact information in
Airworthiness Directives; Stemme AG
maintenance or overhaul. The separation of
paragraph (k)(4) of this AD.
Gliders
engine flanges solely for the purpose of
(4) For RRD service information identified AGENCY: Federal Aviation
transporting the engine without subsequent
engine maintenance does not constitute an in this AD, contact Rolls-Royce Deutschland Administration (FAA), DOT.
engine shop visit. Ltd & Co KG, Eschenweg 11–15827 ACTION: Final rule; request for
Dahlewitz, Blankenfelde-Mahlow, Germany; comments.
(j) Alternative Methods of Compliance phone: +49 0 33–7086–1944; fax: +49 0 33–
(AMOCs) 7086–3276. SUMMARY: We are adopting a new
The Manager, Engine Certification Office, (5) You may view this service information airworthiness directive (AD) for Stemme
FAA, may approve AMOCs for this AD. Use at FAA, Engine & Propeller Directorate, 1200 AG Model S10–VT gliders (type
the procedures found in 14 CFR 39.19 to District Avenue, Burlington, MA 01803. For certificate previously held by Stemme
make your request. You may email your information on the availability of this GmbH & Co. KG). This AD results from
request to: ANE-AD-AMOC@faa.gov. material at the FAA, call 781–238–7125. mandatory continuing airworthiness
(k) Related Information Issued in Burlington, Massachusetts, on information (MCAI) issued by the
mstockstill on DSK30JT082PROD with RULES
(1) For more information about this AD, May 9, 2017. aviation authority of another country to
contact Robert Green, Aerospace Engineer, identify and correct an unsafe condition
Robert J. Ganley,
Engine Certification Office, FAA, Engine & on an aviation product. The MCAI
Acting Manager, Engine & Propeller describes the unsafe condition as certain
Propeller Directorate, 1200 District Avenue,
Directorate, Aircraft Certification Service. propeller front transmission gear wheels
Burlington, MA 01803; phone: 781–238–
7754; fax: 781–238–7199; email: [FR Doc. 2017–10437 Filed 5–25–17; 8:45 am] having insufficient material strength
robert.green@faa.gov. BILLING CODE 4910–13–P because of improper heat treatment
VerDate Sep<11>2014 17:49 May 25, 2017 Jkt 241001 PO 00000 Frm 00029 Fmt 4700 Sfmt 4700 E:\FR\FM\26MYR1.SGM 26MYR1](https://thefederalregister.org/doc/82_FR_24337/page/4.svg)
Document Created: 2017-05-26 02:24:14
Document Modified: 2017-05-26 02:24:14
| 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 | Rules and Regulations | |
| Action | Final rule; request for comments. | |
| Dates | This AD becomes effective June 12, 2017. | |
| Contact | Robert Green, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA 01803; phone: 781-238-7754; fax: 781- 238-7199; email: [email protected] | |
| FR Citation | 82 FR 24236 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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