Document ID: FAA-2017-0186-0001
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Rolls-Royce Deutschland Ltd and Co KG Turbofan Engines
Posted Date: 2017-05-26T04:00Z

[Federal Register Volume 82, Number 101 (Friday, May 26, 2017)]
[Rules and Regulations]
[Pages 24236-24239]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-10437]

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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.

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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: robert.green@faa.gov.

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: ANE-AD-AMOC@faa.gov.

(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: robert.green@faa.gov.
    (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