Airworthiness Directives; Rolls-Royce plc Turbofan Engines

[Federal Register Volume 82, Number 77 (Monday, April 24, 2017)]
[Rules and Regulations]
[Pages 18849-18852]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-07983]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-1015; Directorate Identifier 2013-NE-37-AD; 
Amendment 39-18859; AD 2017-08-10]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce plc Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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

SUMMARY: We are superseding airworthiness directive (AD) 2017-01-01 for 
all Rolls-Royce plc (RR) RB211-Trent 970-84, RB211-Trent 970B-84, 
RB211-Trent 972-84, RB211-Trent 972B-84, RB211-Trent 977-84, RB211-
Trent 977B-84, and RB211-Trent 980-84 turbofan engines. AD 2017-01-01 
required inspections of the low-pressure turbine (LPT) exhaust case and 
support assembly or tail bearing housing (TBH) to detect cracks or 
damage. This AD corrects references to certain service bulletins in the 
compliance section of AD 2017-01-01. This AD was prompted by reports 
that references to service bulletins in AD 2017-01-01 are incorrect. We 
are issuing this AD to correct the unsafe condition on these products.

DATES: This AD is effective May 9, 2017.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of January 26, 
2017 (82 FR 3146, January 11, 2017).
    We must receive any comments on this AD by June 8, 2017.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
    <bullet> Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
    <bullet> Fax: 202-493-2251.
    <bullet> Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
    <bullet> Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    For service information identified in this AD, contact Rolls-Royce 
plc, Corporate Communications, P.O. Box 31, Derby, England, DE24 8BJ; 
phone: 011-44-1332-242424; fax: 011-44-1332-245418, or email: http://www.rolls-royce.com/contact/civil_team.jsp. 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. It is also available on 
the Internet at http://www.regulations.gov by searching for and 
locating Docket No. FAA-2013-1015.

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-2013-
1015; or in person at the Docket Management Facility 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, 
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 provide you with notice and an opportunity to 
provide your comments before it becomes effective. However, we invite 
you to send any written data, views, or arguments about this AD. Send 
your comments to an address listed under the ADDRESSES section. Include 
``Docket No. FAA-2013-1015; Directorate Identifier 2013-NE-37-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 we 
receive about this AD.

Discussion

    On December 22, 2016, we issued AD 2017-01-01, Amendment 39-18768 
(82 FR 3146, January 11, 2017), for all RR RB211-Trent 970-84, RB211-
Trent 970B-84, RB211-Trent 972-84, RB211-Trent 972B-84, RB211-Trent 
977-84, RB211-Trent 977B-84, and RB211-Trent 980-84 turbofan engines. 
AD 2017-01-01 required inspections of the LPT exhaust case and support 
assembly or TBH to detect cracks or damage. AD 2017-01-01 resulted from 
RR performing additional analysis of inspection results and determining 
that the existing inspections need to be modified. We issued AD 2017-
01-01 to

[[Page 18850]]

prevent failure of the TBH, resulting in damage to the engine and to 
the airplane.

Actions Since AD 2017-01-01 Was Issued

    Since we issued AD 2017-01-01, we learned that certain references 
to certain service bulletins in AD 2017-01-01 are incorrect. In the 
fourth row, second column of Table 2 to paragraph (f) of AD 2017-01-01, 
the applicable Alert Non-Modification Service Bulletin (NMSB) states 
``RB.211-72-AJ101'' but the correct reference is ``RB.211-72-AH154.'' 
In addition, two references to ``NMSB RB.211-72-J024'' in Table 1 and 
Table 2 to paragraph (f) of AD 2017-01-01 should say ``SB RB.211-72-
J024''. We have corrected those references in this AD.

Related Service Information Under 1 CFR Part 51

    RR has issued Alert NMSB RB.211-72-AG971, Revision 2, dated May 5, 
2016; Alert NMSB RB.211-72-AH154, Revision 5, dated May 5, 2016; Alert 
NMSB RB.211-72-AJ101, dated May 5, 2016; and Service Bulletin (SB) 
RB.211-72-J055, dated March 22, 2016. RR Alert NMSB RB.211-72-AG971 
describes procedures for on-wing or in-shop inspection of the TBH mount 
lug run-outs. RR Alert NMSB RB.211-72-AH154 describes procedures for an 
on-wing or in-shop inspection of a pre-mod 72-J024 TBH. RR Alert NMSB 
RB.211-72-AJ101 describes procedures for on-wing or in-shop inspection 
of a post-mod 72-J024 TBH. RR SB RB.211-72-J055 describes procedures 
for modifying the engine by introducing a revised TBH. This service 
information is reasonably available because the interested parties have 
access to it through their normal course of business or by the means 
identified in the ADDRESSES section.

FAA's Determination

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

AD Requirements

    This AD requires inspections of the LPT exhaust case and support 
assembly or TBH to detect cracks or damage.

FAA's Justification and 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:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                   Cost on U.S.
              Action                      Labor cost         Parts cost       Cost per product       operators
----------------------------------------------------------------------------------------------------------------
Inspection of the TBH.............  8 work-hours x $85                 $0  $680 per inspection                $0
                                     per hour = $680.                       cycle.
----------------------------------------------------------------------------------------------------------------

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

    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 that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979),
    (3) Will not affect intrastate aviation in Alaska to the extent 
that it justifies making a regulatory distinction, and
    (4) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends part 39 of the Federal Aviation 
Regulations (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 removing airworthiness directive (AD) 
2017-01-01, Amendment 39-18768 (82 FR 3146, January 11, 2017), and 
adding the following new AD:

2017-08-10 Rolls-Royce plc: Amendment 39-18859; Docket No. FAA-2013-
1015; Directorate Identifier 2013-NE-37-AD.

(a) Effective Date

    This AD is effective May 9, 2017.

(b) Affected ADs

    This AD replaces AD 2017-01-01, Amendment 39-18768 (82 FR 3146, 
January 11, 2017).

(c) Applicability

    This AD applies to all Rolls-Royce plc (RR) RB211-Trent 970-84, 
RB211-Trent 970B-84, RB211-Trent 972-84, RB211-Trent 972B-84, RB211-
Trent 977-84, RB211-Trent 977B-84, and RB211-Trent 980-84 turbofan 
engines.

(d) Subject

    Joint Aircraft System Component (JASC) Code 7200, Engine 
(Turbine/Turboprop).

[[Page 18851]]

(e) Unsafe Condition

    This AD was prompted by reports that references to certain 
service bulletins are incorrect. We are issuing this AD to prevent 
failure of the tail bearing housing (TBH), resulting in damage to 
the engine and to the airplane.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.
    (1) Within the compliance times and using the service 
information specified in Table 1 to paragraph (f) of this AD, 
accomplish on-wing inspections of the TBH features using the 
following instructions, as applicable.
    (i) If during any on-wing inspection of the TBH mount lug run-
outs done using the Accomplishment Instructions, paragraph 3.A.(1), 
of RR Alert Non-Modification Service Bulletin (NMSB) RB.211-72-
AG971, Revision 2, dated May 5, 2016, any cracks less than or equal 
to 2 mm in length are found, remove the engine from service within 
10 flight cycles (FCs). If any cracks greater than 2 mm are found, 
remove the engine from service before further flight.
    (ii) If during any on-wing inspection of the TBH mount lug run-
outs done using the Accomplishment Instructions, paragraph 3.A.(2), 
of RR Alert NMSB RB.211-72-AG971, Revision 2, dated May 5, 2016, any 
crack indications resulting in an inspection signal with an 
amplitude of 50% full screen height or more are found, remove the 
engine from service before further flight.
    (iii) If during any on-wing inspection of a pre-mod 72-J024 TBH, 
any crack or damage is found on the TBH mount lug forging leading 
edge (LE) areas, re-inspect the engine or remove the engine from 
service in accordance with the Accomplishment Instructions, 
paragraph 3.A.(3)(t), of RR Alert NMSB RB.211-72-AH154, Revision 5, 
dated May 5, 2016.
    (iv) If during any on-wing inspection of a post-mod 72-J024 TBH, 
any crack is found on the TBH mount lug forging LE or cutback areas, 
re-inspect the engine or remove the engine from service in 
accordance with the Accomplishment Instructions, paragraph 
3.A.(3)(t), of RR Alert NMSB RB.211-72-AJ101, dated May 5, 2016.
    (2) Within the compliance times and using the service 
information specified in Table 2 to paragraph (f) of this AD, 
perform in-shop inspections of the TBH features using the following 
instructions, as applicable.
    (i) If during any in-shop inspection of the TBH, any crack is 
found on the TBH mount lug or central male catcher run-outs, replace 
the TBH with a TBH eligible for installation before the engine is 
returned to service.
    (ii) If during any in-shop inspection of the TBH, any crack is 
found on the top core vanes, reject as unserviceable or repair the 
TBH in accordance with the Accomplishment Instructions, paragraph 
3.C.(1)(f), of RR Alert NMSB RB.211-72-AG971 Revision 2, dated May 
5, 2016, before the engine is returned to service.
    (iii) If during any in-shop inspection of a pre-mod 72-J024 TBH, 
any crack or damage is found on the TBH mount lug forging LE areas, 
reject as unserviceable or repair the TBH in accordance with the 
Accomplishment Instructions, paragraph 3.B.(2)(u)(ii), of RR Alert 
NMSB RB.211-72-AH154, Revision 5, dated May 5, 2016, or the 
Accomplishment Instructions, paragraph 3.C.(1)(f), of RR Alert NMSB 
RB.211-72-AG971, Revision 2, dated May 5, 2016, before the engine is 
returned to service.
    (iv) If during any in-shop inspection of a post-mod 72-J024 TBH, 
any crack is found on the TBH mount lug forging LE or cutback areas, 
repair the TBH in accordance with the Accomplishment Instructions, 
paragraph 3.B.(2)(u)(ii), of RR Alert NMSB RB.211-72-AJ101, dated 
May 5, 2016, or the Accomplishment Instructions, paragraph 
3.C.(1)(f), of Alert NMSB RB.211-72-AG971, Revision 2, dated May 5, 
2016, before the engine is returned to service.

                                Table 1 to Paragraph (f)--TBH On-Wing Inspections
----------------------------------------------------------------------------------------------------------------
                                                       Alternate NMSB
                                   Applicable NMSB      instructions                          Repeat inspection
  Affected TBH P/N and feature     and paragragph      acceptable for    Initial inspection    interval (not to
                                                      prior compliance                             exceed)
----------------------------------------------------------------------------------------------------------------
All--Mount Lug Run-outs........  RB.211-72-AG971,    In-shop: RB.211-72- Before exceeding    2,200 FCs.
                                  Revision 2,         AG971, Revision     2,200 FCs since
                                  Paragraph 3.A.      2, Paragraph 3.B    new.
                                                      or 3.C.
Pre-mod 72-J024 TBH--Mount Lug   RB.211-72-AH154,    In-shop: RB.211-72- Before exceeding    1,000 FCs.
 Forging LE Areas--for a TBH      Revision 5,         AH154, Revision     1,000 FCs since
 that has not exceeded 900 FCs    Paragraph 3.A.      5, Paragraph        new.
 since new on April 7, 2014.                          3.B., or
                                                      RB.211[dash]72-AG
                                                      971, Revision 2,
                                                      Paragraph 3.C.
Pre-mod 72-J024 TBH--Mount Lug   RB.211-72-AH154,    In-shop: RB.211-72- Within 100 FCs      1,000 FCs.
 Forging LE Areas--for a TBH      Revision 5,         AH154, Revision     after April 7,
 that has exceeded 900 FCs        Paragraph 3.A.      5, Paragraph        2014.
 since new on April 7, 2014.                          3.B., or
                                                      RB.211[dash]72-AG
                                                      971, Revision 2,
                                                      Paragraph 3.C.
Post-mod 72-J024 TBH--Mount Lug  RB.211-72-AJ101,    In-shop: RB.211-72- Before exceeding    1,000 FCs.
 Forging LE and Cutback Areas.    Paragraph 3.A.      AG971, Revison 2,   1,000 FCs since
                                                      Paragraph 3.C, or   SB
                                                      RB.211-72-AJ101,    RB.211[dash]72[da
                                                      Paragraph 3.B.      sh]J024
                                                                          embodiment.
----------------------------------------------------------------------------------------------------------------


                                Table 2 to Paragraph (f)--TBH In-Shop Inspections
----------------------------------------------------------------------------------------------------------------
                                                       Alternate NMSB
                                   Applicable NMSB      instructions                          Repeat inspection
  Affected TBH P/N and feature      and paragraph      acceptable for    Initial inspection    interval (not to
                                                      prior compliance                             exceed)
----------------------------------------------------------------------------------------------------------------
All--Mount Lug Run-outs........  RB.211-72-AG971,    On-wing: RB.211-72- Before exceeding    2,200 FCs.
                                  Revision 2,         AG971, Revision     2,200 flight FCs
                                  Paragraph 3.        2, Paragraph        since new.
                                                      3.A., or
                                                     In-shop: RB.211-72-
                                                      AG971, Revision
                                                      2, Paragraph 3.C.
All--Top Core Vanes and Central  RB.211-72-AG971,    None..............  Before exceeding    3,800 FCs.
 Male Catcher Run[dash]outs.      Revision 2,                             3,800 FCs since
                                  Paragraph 3.C.                          new.

[[Page 18852]]

 
Pre-mod 72-J024 TBH--Mount Lug   RB.211-72-AH154,    On-wing: RB.211-72- Before exceeding    1,000 FCs.
 Forging LE Areas--for a TBH      Revision 5,         AH154, Revision     1,000 FCs since
 that has not exceeded 900 FCs    Paragraph 3.B.      5, Section 3.A,     new.
 since new on April 7, 2014.                          or
                                                     In-shop: RB.211-72-
                                                      AG971, Revision
                                                      2, Paragraph 3.C.
Pre-mod 72-J024 TBH--Mount Lug   RB.211-72-AH154,    On-wing: RB.211-72- Within 100 FCs      1,000 FCs.
 Forging LE Areas--for a TBH      Revision 5,         AH154, Revision     after the
 that has exceeded 900 FCs        Paragraph 3.B.      5, Section 3.A,     effective date of
 since new on April 7, 2014.                          or                  this AD.
                                                     In-shop: RB.211-72-
                                                      AG971, Revision
                                                      2, Paragraph 3.C.
Post-mod 72-J024 TBH--Mount Lug  RB.211-72-AJ101,    On-wing: RB.211-72- Before exceeding    1,000 FCs.
 Forging LE and Cutback Areas.    Paragraph 3.B.      AJ101, Section      1,000 FCs since
                                                      3.A, or             SB RB.211[dash]72-
                                                     In-shop: RB.211-72-  J024 embodiment.
                                                      AG971, Revision
                                                      2, Paragraph 3.C.
----------------------------------------------------------------------------------------------------------------

(g) Credit for Previous Actions

    (1) If you performed inspections and corrective actions on an 
engine before the effective date of this AD, in accordance with 
earlier versions of RR Alert NMSB RB.211-72-AG971, Revision 2, dated 
May 5, 2016, or RR Alert NMSB RB.211-72-AH154, Revision 5, dated May 
5, 2016, you met the requirements of paragraph (f)(1) or (2) of this 
AD, as applicable.
    (2) If, on or before April 7, 2014, you performed the 
inspections and corrective actions required by paragraphs (f)(1) and 
(2) of this AD using RR Technical Variance (TV) No. 124801, Issue 2, 
dated July 4, 2012 or earlier versions; or RR TV No. 124851, Issue 
2, dated July 4, 2012 or earlier versions; you met the requirements 
for a mount lug run-out inspection.
    (3) If, on or before April 7, 2014, you performed the 
inspections and corrective actions required by paragraphs (f)(1) and 
(2) of this AD using RR Repeater TV No. 132043, Issue 1, dated March 
25, 2013 or earlier versions; or using RR Repeater TV No. 132217, 
Issue 5, dated May 23, 2013 or earlier versions; you met the 
requirements for the mount lug forging LE inspections of this AD.

(h) Optional Terminating Action

    (1) Accomplishment of corrective actions required by paragraphs 
(f)(1) and (2) of this AD does not constitute terminating action for 
the repetitive inspections required by this AD.
    (2) Modification of an engine in accordance with the 
instructions of RR Service Bulletin RB.211-72-J055, dated March 22, 
2016, constitutes terminating action for the repetitive inspections 
required by paragraphs (f)(1) and (2) of this AD for that engine, 
provided that, following this modification, no affected TBH is 
installed on that engine.

(i) 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].

(j) 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 AD 2016-0193, 
dated September 30, 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-2013-1015.
    (3) RR TV No. 124801, Issue 2, dated July 4, 2012; RR TV No. 
124851, Issue 2, dated July 4, 2012, Repeater TV No. 132043, Issue 
1, dated March 25, 2013, and Repeater TV No. 132217, Issue 5, dated 
May 23, 2013; which are not incorporated by reference in this AD, 
can be obtained from RR using the contact information in paragraph 
(k)(3) of this AD.

(k) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (3) The following service information was approved for IBR on 
January 26, 2017 (82 FR 3146, January 11, 2017).
    (i) Rolls-Royce plc (RR) Service Bulletin RB.211-72-J055, dated 
March 22, 2016.
    (ii) RR Alert Non-Modification Service Bulletin (NMSB) RB.211-
72-AJ101, dated May 5, 2016;
    (iii) RR Alert NMSB RB.211-72-AG971, Revision 2, dated May 5, 
2016; and
    (iv) RR Alert NMSB RB.211-72-AH154, Revision 5, dated May 5, 
2016.
    (4) For RR service information identified in this AD, contact 
Rolls-Royce plc, Corporate Communications, P.O. Box 31, Derby, 
England, DE24 8BJ; phone: 011-44-1332-242424; fax: 011-44-1332-
245418, or email: http://www.rolls-royce.com/contact/civil_team.jsp.
    (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.
    (6) You may view this service information at the National 
Archives and Records Administration (NARA). For information on the 
availability of this material at NARA, call 202-741-6030, or go to: 
http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Burlington, Massachusetts, on April 12, 2017.
Robert J. Ganley,
Acting Manager, Engine & Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 2017-07983 Filed 4-21-17; 8:45 am]
 BILLING CODE 4910-13-P

The complete text was extracted from the official GovInfo HTML edition for this publication. Acquired 2026-10-09T02:21:53.665547+00:00. Text extraction preserves the recorded source wording; it does not determine current requirements.

Open the captured official edition

Source SHA-256

324beb05f74668dcaf3bacae0314afbe87c40e622f4397b91338ccedeccadb2b

Text SHA-256

5f39baf20fbbbd06b2e38a9884d7acfb231726fdd74df1bf7d004ebaeef0c555