81 FR 78085 - Airworthiness Directives; Airbus Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 81, Issue 215 (November 7, 2016)

We propose to supersede Airworthiness Directive (AD) 2012-22- 12, for all Airbus Model A330-243, -243F, -341, -342, and -343 airplanes. AD 2012-22-12 currently requires inspecting piccolo tubes, piccolo tube mount links, the aft side of the forward bulkhead, and outer boundary angles (OBAs) for cracks, fractures, and broken links, and doing corrective actions if necessary. Since we issued AD 2012-22- 12, we have received reports of loose and missing attachment rivets of the inner boundary angles (IBA) and OBA of the forward bulkhead. This proposed AD would retain certain requirements of AD 2012-22-12, and add repetitive inspections for pulled, loose, and missing attachment rivets of the IBA and OBA of the forward bulkhead, and related investigative and corrective actions if necessary. We are proposing this AD to detect and correct degraded structural integrity of the engine nose cowl, which in the case of forward bulkhead damage in conjunction with a broken piccolo tube, could lead to damage to the engine and operation in icing conditions with reduced thermal anti-ice (TAI) performance.

[Federal Register Volume 81, Number 215 (Monday, November 7, 2016)]
[Proposed Rules]
[Pages 78085-78088]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2016-26521]



[[Page 78085]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA- 2016-9305; Directorate Identifier 2016-NM-073-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to supersede Airworthiness Directive (AD) 2012-22-
12, for all Airbus Model A330-243, -243F, -341, -342, and -343 
airplanes. AD 2012-22-12 currently requires inspecting piccolo tubes, 
piccolo tube mount links, the aft side of the forward bulkhead, and 
outer boundary angles (OBAs) for cracks, fractures, and broken links, 
and doing corrective actions if necessary. Since we issued AD 2012-22-
12, we have received reports of loose and missing attachment rivets of 
the inner boundary angles (IBA) and OBA of the forward bulkhead. This 
proposed AD would retain certain requirements of AD 2012-22-12, and add 
repetitive inspections for pulled, loose, and missing attachment rivets 
of the IBA and OBA of the forward bulkhead, and related investigative 
and corrective actions if necessary. We are proposing this AD to detect 
and correct degraded structural integrity of the engine nose cowl, 
which in the case of forward bulkhead damage in conjunction with a 
broken piccolo tube, could lead to damage to the engine and operation 
in icing conditions with reduced thermal anti-ice (TAI) performance.

DATES: We must receive comments on this proposed AD by December 22, 
2016.

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.
     Fax: 202-493-2251.
     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.
     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, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.
    For Airbus service information identified in this NPRM, contact 
Airbus SAS--Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte, 
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 
93 45 80; email [email protected]; Internet http://www.airbus.com.
    For Rolls-Royce service information identified in this NPRM, 
contact Rolls-Royce Plc, Technical Publications, P.O. Box 31, Derby, 
DE24 8BJ, United Kingdom; telephone 44 (0) 1332 245882; fax 44 (0) 1332 
249936; Internet http://www.Rolls-Royce.com.
    You may view this referenced service information at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For 
information on the availability of this material at the FAA, call 425-
227-1221.

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-
9305; 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 proposed AD, the regulatory evaluation, any comments 
received, and other information. The street address for the Docket 
Operations office (telephone 800-647-5527) is in the ADDRESSES section. 
Comments will be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1138; 
fax 425-227-1149.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2016-9305; 
Directorate Identifier 2016-NM-073-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD based on 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 proposed AD.

Discussion

    On October 26, 2012, we issued AD 2012-22-12, Amendment 39-17248 
(77 FR 67263, November 9, 2012) (``AD 2012-22-12''). AD 2012-22-12 
requires actions intended to address an unsafe condition on all Airbus 
Model 330-243, -243F, -341, -342, and -343 airplanes.
    Since we issued AD 2012-22-12, we have received reports of loose or 
missing attachment rivets of the IBA and OBA of the forward bulkhead.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive, 2016-0086R1, dated May 13, 2016 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for all Airbus Model 330-
243, -243F, -341, -342, and -343 airplanes. The MCAI states:
    During shop visit, cracks were found in several primary 
structural parts of Rolls Royce (RR) Trent 700 engine air intake 
cowls, specifically in the forward bulkhead web, web stiffeners and 
outer boundary angles (OBA). In addition, several attachment links 
were found severely worn, and some became detached. In two cases, 
the thermal anti-ice (TAI) piccolo tube was found fractured. 
Investigation results show that the cracks are most likely due to 
acoustic excitation and vibration.
    A broken piccolo tube, if not detected and corrected, in 
conjunction with forward air intake cowl bulkhead damage, could lead 
to in-flight detachment of the outer barrel, possibly resulting in 
damage to the engine or reduced control of the aeroplane.
    To address this potential unsafe condition, Airbus issued 
Service Bulletin (SB) A330-71-3025, making reference to RR SB 
RB.211-71-AG416, to provide inspection instructions, and, depending 
on findings, accomplishment of applicable corrective action(s).
    Consequently, EASA issued AD 2011-0062 [http://ad.easa.europa.eu/blob/easa_ad_2011_0062_superseded.pdf/AD_2011-0062_1] [which corresponds to FAA AD 2012-22-12] to require 
repetitive special detailed inspections (SDI) [borescope] of the 
piccolo tube and affected mount links, the aft side of forward 
bulkhead, inner boundary angles (IBA) and OBA of the RR Trent 700 
air intake cowl assemblies, and, depending on findings, 
accomplishment of applicable corrective action(s).
    Since EASA AD 2011-0062 was issued, some occurrences were 
reported of finding attachment rivets of the IBA and OBA either 
pulled, loose, or missing during inspection. It was determined that 
the affected IBA and OBA rivets may not have been previously 
inspected if operators accomplished the required inspection in 
accordance with the instructions of RR SB RB.211-71-AG416 at 
original issue.

[[Page 78086]]

    To address this potentially missed inspection, Airbus published 
SB A330-71-3033, providing instructions for a one-time detailed 
inspection of the IBA and OBA attachment rivets, to be accomplished 
if the previous inspection was accomplished using the instructions 
of RR SB RB.211-71-AG416 at original issue. Airbus also published SB 
A330-71-3025 Revision 2, adding an inspection of the IBA and OBA 
attachment rivets, to be used if the previous inspection was 
accomplished using RR SB RB.211-71-AG416 at issue 1 or later. Airbus 
also published SB A330-71-3032 to introduce a modification (mod) 
that would eliminate the need for repetitive inspections.
    For the reasons described above, this [EASA] AD partially 
retains the requirements of EASA AD 2011-0062, which is superseded, 
and requires an additional [special] detailed inspection [borescope] 
of IBA and OBA forward bulkhead attachment rivets. This [EASA] AD 
also introduces an optional terminating action (Airbus mod 204615, 
embodied in production, which can be embodied in service with Airbus 
SB A330-71-3032) for the repetitive inspections required by this 
[EASA] AD.
    This [EASA] AD is revised to improve clarity, including Airbus 
and RR SB references and inserting Notes to identify the Part 
Numbers (P/N) of the affected engine air intake nose cowl 
assemblies.

    Related investigative actions include inspecting for cracked or 
fractured piccolo tubes and for broken piccolo tube links. Corrective 
actions include replacing the engine air intake cowl assembly and 
repair of pulled, loose, or missing rivets.
    The compliance times for the related investigative and corrective 
actions range from before further flight to within 100 flight cycles, 
depending on the findings of the inspections.
    The repetitive inspection interval for the IBA, OBA, and forward 
bulkhead varies depending on inspection findings, and ranges between 
200 and 5,000 flight cycles. The repetitive inspection interval for the 
piccolo tubes and links is 2,500 flight cycles.
    You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
9305.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletin A330-71-3025, Revision 02, 
including Appendices 01 and 02, dated December 9, 2015. This service 
information describes procedures for doing inspections of the piccolo 
tube and mount links, the aft side of the forward bulkhead, the IBA, 
OBA, and the forward bulkhead on the engine air intake cowl assemblies; 
and related investigative and corrective actions.
    Airbus has issued Service Bulletin A330-71-3032, dated December 10, 
2014. This service information describes procedures for doing a 
modification that improves the air intake primary structure and adds a 
new piccolo tube supporting structure on the engine air intake cowl 
assemblies.
    Airbus has issued Service Bulletin A330-71-3033, dated December 14, 
2015. This service information describes procedures for doing an 
inspection for pulled, loose, and missing attachment rivets of the IBA 
and OBA of the forward bulkhead of the forward bulkhead, and corrective 
actions.
    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 and Requirements of This Proposed AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI and service 
information referenced above. We are proposing this AD because we 
evaluated all pertinent information and determined an unsafe condition 
exists and is likely to exist or develop on other products of the same 
type design.

Costs of Compliance

    We estimate that this proposed AD affects 47 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                    Cost per       Cost on U.S.
               Action                        Labor cost           Parts cost        product         operators
----------------------------------------------------------------------------------------------------------------
Inspections (new proposed action)...  12 work-hours x $85 per              $0       $1,020 per      $47,940 per
                                       hour = $1,020 per                            inspection       inspection
                                       inspection cycle.                                 cycle           cycle.
----------------------------------------------------------------------------------------------------------------


                                      Estimated Costs for Optional Actions
----------------------------------------------------------------------------------------------------------------
                Action                            Labor cost              Parts cost        Cost per product
----------------------------------------------------------------------------------------------------------------
Modification..........................  Up to 142 work-hours x $85                [1]   Up to $12,070.
                                         per hour = $12,070.
----------------------------------------------------------------------------------------------------------------
[1] We have received no definitive data that would enable us to provide material cost estimates for the optional
  actions specified in this proposed AD.

    We estimate the following costs to do any necessary repairs that 
would be required based on the results of the proposed inspection. We 
have no way of determining the number of aircraft that might need these 
repairs:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                  Action                                Labor cost                 Parts cost        product
----------------------------------------------------------------------------------------------------------------
Repairs...................................  16 work-hours x $85 per hour =                 [2]           $1,360
                                             $1,360.
----------------------------------------------------------------------------------------------------------------
[2] We have received no definitive data that would enable us to provide material cost estimates for the on-
  condition actions specified in this proposed AD.


[[Page 78087]]

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 proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 proposed 
regulation:
    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; 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.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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) 
2012-22-12, Amendment 39-17248 (77 FR 67263, November 9, 2012), and 
adding the following new AD: Airbus: Docket No. FAA-2016-9305; 
Directorate Identifier 2016-NM-073-AD.

(a) Comments Due Date

    We must receive comments by December 22, 2016.

(b) Affected ADs

    This AD replaces AD 2012-22-12, Amendment 39-17248 (77 FR 67263, 
November 9, 2012) (``AD 2012-22-12'').

(c) Applicability

    This AD applies to Airbus Model A330-243, -243F, -341, -342, and 
-343 airplanes, certificated in any category, all serial numbers.

(d) Subject

    Air Transport Association (ATA) of America Code 71, Powerplant.

(e) Reason

    This AD was prompted by reports of cracking of air intake cowls 
on Rolls-Royce Trent engines, worn and detached attachment links, 
and fractured thermal anti-ice (TAI) piccolo tubes, and loose, or 
missing attachment rivets of the inner boundary angles (IBA) and the 
outer boundary angles (OBA) of the forward bulkhead. We are issuing 
this AD to detect and correct degraded structural integrity of the 
engine nose cowl, which in the case of forward bulkhead damage in 
conjunction with a broken piccolo tube, could lead to damage to the 
engine and operation in icing conditions with reduced thermal anti-
ice (TAI) performance.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Affected Engine Air Intake Nose Cowl Assemblies

    The engine air intake nose cowl assemblies affected by this AD 
have part number (P/N) SJ30020, P/N SJ30361, P/N SJ30687, P/N 
SJ30810, and P/N SJ30811, as specified in Rolls-Royce Service 
Bulletin RB.211-71-H205, dated July 7, 2014.
    (1) The engine air intake nose cowl assemblies having P/N 
SJ30020, P/N SJ30361, and P/N SJ30687 can be modified (reworked and 
re-identified as P/N SJ30810 (for P/N SJ30020, P/N SJ30361) and P/N 
SJ30811 (for P/N SJ30687)), as specified in Rolls-Royce Service 
Bulletin RB.211-71-H205, dated July 7, 2014.
    (2) The engine air intake nose cowl assemblies having P/N 
SJ30810 and P/N SJ30811 can be modified (reworked and re-identified 
as P/N SJ30820 and P/N SJ30821, respectively), as specified in 
Rolls-Royce Service Bulletin RB.211-71-H847, dated December 2, 2014.

(h) Inspections, Related Investigative Actions, and Corrective Actions

    For airplanes in pre-Airbus Modification 204615 and pre-Airbus 
Service Bulletin A330-71-3032 configuration: At the applicable times 
specified in paragraph (h)(1) or (h)(2) of this AD, do a special 
detailed inspection of the piccolo tube and affected mount links, 
the aft side of the forward bulkhead, and the IBA and OBA of the 
affected engine air intake cowl assemblies specified in paragraph 
(g) of this AD; and do all applicable related investigative and 
corrective actions; in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A330-71-3025, Revision 02, 
including Appendices 01 and 02, dated December 9, 2015, except as 
required by paragraph (i) of this AD. Do all applicable related 
investigative and corrective actions at the applicable time 
specified in paragraph 1.E., ``Compliance,'' of Airbus Service 
Bulletin A330-71-3025, Revision 02, including Appendices 01 and 02, 
dated December 9, 2015. Repeat the inspections of the piccolo tube 
and affected mount links, the aft side of the forward bulkhead, and 
the IBA and OBA of the engine air intake cowl assemblies thereafter 
at the applicable intervals specified in paragraph 1.E., 
``Compliance,'' of Airbus Service Bulletin A330-71-3025, Revision 
02, including Appendices 01 and 02, dated December 9, 2015. 
Accomplishment of corrective actions does not constitute terminating 
action for the repetitive inspections required by this paragraph.
    (1) For any engine air intake cowl assembly that has accumulated 
fewer than 5,000 flight cycles since its first installation on an 
airplane as of the effective date of this AD: Inspect within 24 
months after the engine air intake cowl assembly has accumulated 
5,000 total flight cycles.
    (2) For any engine air intake cowl assembly that has accumulated 
5,000 or more flight cycles since its first installation on an 
airplane as of the effective date of this AD: Inspect within 24 
months after the effective date of this AD.

 (i) Service Information Exception

    Where Airbus Service Bulletin A330-71-3025, Revision 02, 
including Appendices 01 and 02, dated December 9, 2015, specifies to 
contact Bombardier Aerospace-Shorts for instructions, before further 
flight, repair using a method approved by the Manager, International 
Branch, ANM-116, Transport Airplane Directorate, FAA; or the 
European Aviation Safety Agency (EASA); or Airbus's EASA Design 
Organization Approval (DOA).

(j) Optional Terminating Action

    Modification of an airplane in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A330-71-3032, 
dated December 10, 2014, constitutes terminating action for the 
repetitive inspections required by paragraph (h) of this AD for the 
modified airplane only.

 (k) Parts Installation Limitation

    As of the effective date of this AD, any pre-Airbus modification 
204615 part may be installed on any airplane provided that, at

[[Page 78088]]

the earlier of the applicable times specified in paragraphs (h)(1) 
and (h)(2) of this AD following installation, the actions required 
by paragraph (h) of this AD have been accomplished on the pre-Airbus 
Modification 204615 part.

 (l) Credit for Previous Actions

    This paragraph provides credit for actions required by paragraph 
(h) of this AD, if those actions were performed before the effective 
date of this AD using Airbus Service Bulletin A330-71-3025, dated 
January 10, 2011; or Airbus Service Bulletin A330-71-3025, Revision 
01, dated October 24, 2012; provided that, within 1,050 flight 
cycles after the effective date of this AD, a special detailed 
inspection for pulled, loose, and missing attachment rivets of the 
IBA and OBA of the forward bulkhead is accomplished; and all 
applicable corrective actions are done; in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A330-71-3033, 
dated December 14, 2015. Do all applicable corrective actions before 
further flight. Accomplishment of corrective actions does not 
constitute terminating action for the repetitive inspections 
required by paragraph (h) of this AD.

 (m) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
has the authority to approve AMOCs for this AD, if requested using 
the procedures found in 14 CFR 39.19. In accordance with 14 CFR 
39.19, send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the International Branch, send it to ATTN: Vladimir 
Ulyanov, Aerospace Engineer, International Branch, ANM-116, 
Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, 
WA 98057-3356; telephone 425-227-1138; fax 425-227-1149. Information 
may be emailed to: [email protected].
    (i) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office. The AMOC approval letter must specifically 
reference this AD.
    (ii) AMOCs approved previously in accordance with 2012-22-12 are 
not approved as AMOCs with this AD.
    (2) Contacting the Manufacturer: As of the effective date of 
this AD, for any requirement in this AD to obtain corrective actions 
from a manufacturer, the action must be accomplished using a method 
approved by the Manager, International Branch, ANM-116, Transport 
Airplane Directorate, FAA; or the European Aviation Safety Agency 
(EASA); or Airbus's EASA Design Organization Approval (DOA). If 
approved by the DOA, the approval must include the DOA-authorized 
signature.
    (3) Required for Compliance (RC): If any service information 
contains procedures or tests that are identified as RC, those 
procedures and tests must be done to comply with this AD; any 
procedures or tests that are not identified as RC are recommended. 
Those procedures and tests that are not identified as RC may be 
deviated from using accepted methods in accordance with the 
operator's maintenance or inspection program without obtaining 
approval of an AMOC, provided the procedures and tests identified as 
RC can be done and the airplane can be put back in an airworthy 
condition. Any substitutions or changes to procedures or tests 
identified as RC require approval of an AMOC.

(n) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2016-0086R1, dated May 13, 2016, 
for related information. This MCAI may be found in the AD docket on 
the Internet at http://www.regulations.gov by searching for and 
locating Docket No. FAA-2016-9305.
    (2) For Airbus service information identified in this AD, 
contact Airbus SAS--Airworthiness Office--EAL, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; 
fax +33 5 61 93 45 80; email [email protected]; 
Internet http://www.airbus.com.
    (3) For Rolls-Royce service information identified in this AD, 
contact Rolls-Royce Plc, Technical Publications, P.O. Box 31, Derby, 
DE24 8BJ, United Kingdom; telephone 44 (0) 1332 245882; fax 44 (0) 
1332 249936; Internet http://www.Rolls-Royce.com.
    (4) You may view this service information at the FAA, Transport 
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For 
information on the availability of this material at the FAA, call 
425-227-1221.

    Issued in Renton, Washington, on October 28, 2016.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.

[FR Doc. 2016-26521 Filed 11-4-16; 8:45 am]
BILLING CODE 4910-13-P