Airworthiness Directives; Rolls-Royce plc Turbofan Engines

[Federal Register Volume 81, Number 231 (Thursday, December 1, 2016)]
[Rules and Regulations]
[Pages 86567-86570]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-28663]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-6692; Directorate Identifier 2016-NE-13-AD; 
Amendment 39-18725; AD 2016-24-08]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce plc Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for all

[[Page 86568]]

Rolls-Royce plc (RR) RB211-Trent 875-17, RB211-Trent 877-17, RB211-
Trent 884-17, RB211-Trent 884B-17, RB211-Trent 892-17, RB211-Trent 
892B-17, and RB211-Trent 895-17 turbofan engines. This AD requires 
repetitive inspections of the engine upper bifurcation fairing and 
repairing or replacing any fairing that fails inspection. This AD was 
prompted by a report of cracking and material release from an engine 
upper bifurcation fairing. We are issuing this AD to prevent failure of 
the engine fire protection system, engine fire, and damage to the 
airplane.

DATES: This AD becomes effective January 5, 2017.

ADDRESSES: For service information identified in this final rule, 
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. You may view 
this service information at the FAA, Engine & Propeller Directorate, 
1200 District Avenue, Burlington, MA. 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-2016-
6692; 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 
(MCAI), the regulatory evaluation, any comments received, and other 
information. The address for the Docket Office (phone: 800-647-5527) is 
Document Management Facility, U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Wego Wang, Aerospace Engineer, Engine 
Certification Office, FAA, Engine & Propeller Directorate, 1200 
District Avenue, Burlington, MA 01803; phone: 781-238-7134; fax: 781-
238-7199; email: [email protected].

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to the specified products. The 
NPRM was published in the Federal Register on July 15, 2016 (81 FR 
46000). The NPRM proposed to correct an unsafe condition for the 
specified products. The MCAI states:

    Inspection of in-service Rolls-Royce RB211 Trent 800 engines has 
identified cracking and/or material release from the upper 
bifurcation fairing. This fairing hardware mates to the aeroplane 
thrust reverser upper bifurcation forward fire seal. Both sets of 
hardware create the engine firewall to isolate the engine 
compartment fire zone, which is a firewall feature of the aeroplane 
type design. Damage (missing materials and holes/openings) to the 
upper bifurcation fairing creates a breach of the engine fire wall, 
which may decrease the effectiveness of the engine fire detection 
and suppression systems due to excess fan air entering the engine 
compartment fire zone. This could delay or prevent the fire 
detection and suppression system from functioning properly, and can 
result in an increased risk of prolonged burning, potentially 
allowing a fire to reach unprotected areas of the engine, strut and 
wing.

    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-2016-6692.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We considered the comment received.

Request To Remove Reference to Guidance in Compliance

    American Airlines, Inc. (AAL) requested that paragraph (e)(3)(ii) 
in this AD be revised to eliminate the references to Aircraft 
Maintenance Manual (AMM) Task 70-20-02 and to OMat 632. AAL indicated 
that AMM 70-20-02 requires the use of OMat 653 and TAM (PSM-5) TST 
panels for testing fluorescent penetrants for contamination and 
effectiveness. AAL noted that the Overhaul Material Manual (OMat 6) 
allows the use of any products specified in the SAE-AMS-2644 Qualified 
Product List Group 1A2 as an alternative to OMat 653.
    We disagree. Paragraph (e)(3)(ii) in this AD refers to AMM Task 70-
20-02 and OMat 632 as guidance that operators may use when performing 
fluorescent penetrant inspection. This AD does not require that AMM 
TASK 70-20-02 or OMat 632 be followed when performing fluorescent 
penetrant inspection. We did not change this AD.

Conclusion

    We reviewed the relevant data, considered the comment received, and 
determined that air safety and the public interest require adopting 
this AD as proposed except for minor editorial changes. We have 
determined that these minor changes:
    <bullet> Are consistent with the intent that was proposed in the 
NPRM for correcting the unsafe condition; and
    <bullet> Do not add any additional burden upon the public than was 
already proposed in the NPRM.

Related Service Information

    RR has issued Alert Non-Modification Service Bulletin (NMSB) 
RB.211-72-AJ165, dated March 31, 2016. The NMSB describes procedures 
for inspecting and, if necessary, repairing or replacing the engine 
upper bifurcation fairing.

Costs of Compliance

    We estimate that this AD affects 125 engines installed on airplanes 
of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                    Cost per       Cost on U.S.
             Action                        Labor cost             Parts cost        product         operators
----------------------------------------------------------------------------------------------------------------
Inspection......................  3.25 work-hours x $85 per                $0          $276.25          $34,531
                                   hour = $276.25.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary replacements 
that would be required based on the results of the proposed inspection. 
We estimate that 5 engines will need this repair and 5 engines will 
need this replacement:

[[Page 86569]]



                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                   Action                                 Labor cost                Parts cost        product
----------------------------------------------------------------------------------------------------------------
Repair of engine upper bifurcation fairing.  8 work-hours x $85 per hour = $680.            $500          $1,180
Replacement of engine upper bifurcation      30 work hours x $85 per hour =                  500           3,050
 fairing.                                     $2,550.
----------------------------------------------------------------------------------------------------------------

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):

2016-24-08 Rolls-Royce plc: Amendment 39-18725; Docket No. FAA-2016-
6692; Directorate Identifier 2016-NE-13-AD.

(a) Effective Date

    This AD becomes effective January 5, 2017.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Rolls-Royce plc (RR) RB211-Trent 875-17, 
RB211-Trent 877-17, RB211-Trent 884-17, RB211-Trent 884B-17, RB211-
Trent 892-17, RB211-Trent 892B-17, and RB211-Trent 895-17 turbofan 
engines.

(d) Reason

    This AD was prompted by a report of cracking and material 
release from an engine upper bifurcation fairing. We are issuing 
this AD to prevent failure of the engine fire protection system, 
engine fire, and damage to the airplane.

(e) Actions and Compliance

    Comply with this AD within the compliance times specified, 
unless already done.
    (1) Within 7,500 engine flight hours (FHs) time since new, or 
since last inspection, or within 150 flight cycles (FCs) after the 
effective date of this AD, whichever occurs later, inspect the 
engine upper bifurcation fairing for cracks or missing material. Use 
paragraph (e)(3) of this AD to perform the inspections.
    (2) Repeat the inspection required by this AD within every 7,500 
engine FHs time since last inspection.
    (3) Inspect the engine upper bifurcation fairing as follows. 
Refer to Figure 1 of RR Alert Non-Modification Service Bulletin 
(NMSB) RB.211-72-AJ165, dated March 31, 2016, for guidance on upper 
bifurcation fairing inspection locations.
    (i) Visually inspect upper bifurcation fairing seal face 22, 
seal support 23, and zone A for any cracks or material loss on the 
right side.
    (A) If fairing seal face 22 is found to have released material, 
repair or replace the fairing before further flight.
    (B) If there is a single crack found on fairing seal face 22, 
shorter than 6 mm, repair or replace the fairing within 100 engine 
flight cycles, or at the next shop visit, whichever occurs sooner.
    (C) If there is a single crack, longer than 6 mm, found on 
fairing seal face 22, repair or replace the fairing within 15 engine 
FCs or at the next shop visit, whichever occurs sooner.
    (D) If there are two or more cracks found on fairing seal face 
22, replace the fairing within 15 engine FCs or at next shop visit, 
whichever occurs sooner.
    (E) If there is any cracking or material loss found on seal 
support 23, replace the fairing within 15 engine FCs or at next shop 
visit, whichever occurs sooner.
    (ii) If the visual inspection required by paragraph (e)(3)(i) of 
this AD does not detect any crack, fluorescent penetrant inspect 
zone A. Refer to AMM TASK 70-20-02, Water Washable Fluorescent 
Penetrant Inspection (Maintenance Process 213), or OMat 632, high 
sensitivity fluorescent penetrant inspection, for guidance on 
fluorescent penetrant inspection.
    (A) If a crack shorter than 6 mm is detected, repair or replace 
the fairing within 100 engine FCs, or at the next shop visit, 
whichever occurs sooner.
    (B) If a crack longer than 6 mm is detected, repair or replace 
the fairing within 15 engine FCs or at the next shop visit, 
whichever occurs sooner.

(f) Definition

    For the purpose of this AD, a ``shop visit'' is defined as 
induction of an engine into the shop for maintenance involving the 
separation of pairs of major mating engine flanges, except that the 
separation of engine flanges solely for the purposes of 
transportation without subsequent engine maintenance does not 
constitute an engine shop visit.

(g) 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].

(h) Related Information

    (1) For more information about this AD, contact Wego Wang, 
Aerospace Engineer, Engine Certification Office, FAA, Engine & 
Propeller Directorate, 1200 District Avenue, Burlington, MA 01803; 
phone: 781-238-7134; fax: 781-238-7199; email: [email protected].

[[Page 86570]]

    (2) Refer to MCAI European Aviation Safety Agency AD 2016-0084, 
dated April 28, 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-2016-6692.
    (3) RR Alert NMSB RB.211-72-AJ165, dated March 31, 2016, which 
is not incorporated by reference in this AD, can be obtained from 
RR, using the contact information in paragraph (h)(4) of this AD.
    (4) 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-
249936; email: http://www.rolls-royce.com/contact/civil_team.jsp; 
Internet: https://customers.rolls-royce.com/public/rollsroycecare.
    (5) You may view this service information at the FAA, Engine & 
Propeller Directorate, 1200 District Avenue, Burlington, MA. For 
information on the availability of this material at the FAA, call 
781-238-7125.

(i) Material Incorporated by Reference

    None.

    Issued in Burlington, Massachusetts, on November 16, 2016.
Colleen M. D'Alessandro,
Manager, Engine & Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-28663 Filed 11-30-16; 8:45 am]
 BILLING CODE 4910-13-P

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