AD 2017-08-10

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.

Final rule; request for comments.

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, beforethe 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 FCssince
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, Issue2, 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, followingthis 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: ANE-AD-AMOC@faa.gov.

(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: robert.green@faa.gov.
(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.

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 serviceinformation 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 thisAD:

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.