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AD 2017-02-01

Published 2017-02-27 · Document 2017-03739

This is a dated source edition. Current legal effect, aircraft applicability, installed configuration and compliance remain unknown. It has not been promoted as a regulatory determination or qualified as paid-report evidence.

Effective date printed in this source
2017-03-14
Source acquired
2026-09-28
PDF corroboration
Not verified in this HTML-only batch

Open the official complete publication · Find this AD number in the FAA catalog

Applicability wording in this source

(c) Applicability

    This AD applies to Rolls-Royce plc (RR) Trent 1000-A, Trent 
1000-C, Trent 1000-D, Trent 1000-E, Trent 1000-G, and Trent 1000-H 
turbofan engines with high-pressure turbine (HPT) blades, part 
number (P/N) FW63853, installed.

Serial numbers, installed parts, exceptions and service-document requirements have not been evaluated. An engine model mentioned here is not evidence that an aircraft has that engine installed.

Fully written literal labels recorded in this clause:

This literal index is partial. Shorthand, ranges and broken lines have not been expanded or repaired.

Historical relationship wording

(b) Affected ADs

    None.

This wording records what this edition said at publication. It does not determine current supersession or current independent burden.

Recorded rule paragraphs

These exact source paragraphs include conditions and maintenance wording. They are not a conclusion that work applies to, or was completed on, an individual aircraft. Referenced manufacturer service documents are link-only and are not mirrored.

(a) Effective Date
(a) Effective Date

    This AD is effective March 14, 2017.
(b) Affected ADs
(b) Affected ADs

    None.
(c) Applicability
(c) Applicability

    This AD applies to Rolls-Royce plc (RR) Trent 1000-A, Trent 
1000-C, Trent 1000-D, Trent 1000-E, Trent 1000-G, and Trent 1000-H 
turbofan engines with high-pressure turbine (HPT) blades, part 
number (P/N) FW63853, installed.
(d) Subject
(d) Subject

    Joint Aircraft System Component (JASC) 7250, Turbine/Turboprop 
Engine/Turbine Section.
(e) Reason
(e) Reason

    This AD was prompted by high engine vibration due to HPT blade 
deterioration resulting in operational disruptions. We are issuing 
this AD to prevent HPT blade failure, loss of engine thrust control, 
and reduced control of the airplane.
(f) Compliance
(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.
    (1) Perform an initial inspection of each HPT blade before 
exceeding the following, whichever occurs later:
    (i) 1,750 engine flight cycles (FCs) since new or 11,000 engine 
flight hours (FHs) since new, whichever occurs first; or
    (ii) 30 days after the effective date of this AD.
    (2) Thereafter, perform repetitive inspections of the HPT blades 
at intervals not to exceed 250 engine FCs or 1,125 engine FHs, 
whichever occurs first.
    (3) Use the Accomplishment Instructions, paragraph 3, of RR Non-
Modification Service Bulletin (NMSB) Trent 1000 72-J039, Revision 3, 
dated October 14, 2016, to perform the inspections.
    (4) If any crack is found during any inspection, follow the 
applicable corrective action and reduced follow-on inspection 
interval as defined in the Accomplishment Instructions, paragraph 
3.A.(3), of RR NMSB Trent 1000 72-J039, Revision 3, dated October 
14, 2016.
(g) Installation Prohibition
(g) Installation Prohibition

    After the effective date of this AD, do not install an HPT 
blade, P/N FW63853, on any engine.
(h) Credit for Previous Actions
(h) Credit for Previous Actions

    You may take credit for inspections and corrective action that 
are required by paragraph (f) of this AD, if you performed these 
actions and corrective action before the effective date of this AD, 
using RR NMSB Trent 1000 72-J039, Revision 2, or earlier versions.
(i) Alternative Methods of Compliance (AMOCs)
(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
(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 EASA AD 2016-0215, dated October 27, 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-2016-9510.

[[Page 11803]]
(k) Material Incorporated by Reference
(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.
    (i) Rolls-Royce plc (RR) Non-Modification Service Bulletin Trent 
1000 72-J039, Revision 3, dated October 14, 2016.
    (ii) Reserved.
    (3) 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-
249936; email: http://www.rolls-royce.com/contact/civil_team.jsp; 
Internet: https://customers.rolls-royce.com/public/rollsroycecare.
    (4) 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.
    (5) 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.