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### [4910-13

- P] D E PARTMENT
OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-2701; Directorate Identifier 2016-NE-03-AD; Amendment 39-18440; AD 2016-06-09] RIN 2120-AA64 Ainvorthiness Directives; Turbomeca S.A. Turbo

s haft Engines AGENCY: Federal Aviat

i on Admin

i stra

t ion (FAA), DOT. 

### ACTION: Final rule

; request
fo r comments. 

### SUM MARY: We are adopting

a new airwort
hi ness
d i rective 

### (AD) for certain Turbomeca S.A. Makila 2A and 2A

l tu rb os h aft engines. Thi
s AD req uir es tighteni

n g the nut attach in g the swive

l union to the engine power turbine module M04. Th

i s 

### AD was prompted by two occurrences

of commanded

in -flig h t s hutdown

fo ll owing

l ow oi l pre ss ure wa rnin g. We are

i ss uin g this AD to prevent

l ooseni

n g of the nut and oil leakage from the low-pressure
oil system, which co uld lead to in-flight sh utd own of the e n g in e a nd forced

l and

i ng. 

### DATES: This 

### AD becomes effective [INSERT DATE
15 DAYS AFTER DATE OF PUBLICATION

IN THE FEDERAL REGISTER]. We must receive comments
on this AD by [rN SERT DATE 45 DAYS AFTER DATE OF PUBLICA TJON IN THE FEDERAL REGISTER]. 

### ADDRESSES: You may send comments
by any of the following methods:•FederaleRulemakingPortal:Gotohttp://www.regulations.gov.Followtheinstructionsforsubmittingcomments.•Mail:U.S.DepartmentofTransportation,1200NewJerseyAvenueSE.,WestBuildingGroundFloor,RoomW12-140,Washington,DC20590-0001.•HandDelivery:DelivertoMailaddressabovebetween9a.m.and5p.m.,MondaythroughFriday,exceptFederalholidays.•Fax:202-493-2251.ForinformationontheavailabilityofthismaterialattheFAA,call781-238-7125.ItisalsoavailableontheInternetathttp://www.regulations.govbysearchingforandlocatingDocketNo.FAA-2016-2701.ExaminingtheADDocketYoumayexamine theADdocketontheInternetathttp://www.regulations.govbysearchingforandlocatingDocketNo.FAA:.2o16-2701;orinpersonattheDocketOperationsofficebetween9a.m.and5p.m.,MondaythroughFriday,exceptFederalholidays.TheADdocketcontainsthisAD,themandatorycontinuingairworthinessinformation(MCAI),regulatoryevaluation,anycommentsreceived,andotherinformation.TheaddressfortheDocketOffice(phone:800-647-5527)isintheADDRESSESsection.CommentswillbeavailableintheADdocketshortlyafterreceipt.FORFURTHERINFORMATIONCONTACT:BesianLuga,AerospaceEngineer,EngineCertificationOffice,FAA,Engine&PropellerDirectorate,1200DistrictAvenue,Burlington,MA01803;phone:781-238-7750;fax:781-238-7199;email:besian.luga@faa.gov.2SUPPLEMENTARY INFORMATION: Comments Invited This AD is a final rule that involves requirements affecting flight safety, and we did not precede

it by notice and opportunity
for public comment. We invite you to send any written relevant data

, views, or argument

s about this AD. Send your comments

to an address listed under the ADDRESSES section. Include "Docket No. F AA-20 16-2701

; Directorate Identifier
20 16-NE-03-AD

" at the beginning
of your comments. We specifically invite comments
on the ov era ll regulatory, economic, environmental,
and energy aspects of thi s AD. We will consider all comments recei ved by the closing date and may amend this AD because of tho se comments. We will post all comments we receive

, without change

, to http: // www.regulations.gov

, including any per
s onal information you provide. We will a l so po st a report

s ummarizing each

s ub s tantive verbal contact with FAA personnel concerning this AD. Discussion The European Aviation Safety Agency (EASA), which
is th e Tec hnical Agent for the Member States of th e European Co mmunity

, ha s issued EASA AD 20 16-0016

, dated January 15,2016

( r e f erre d to herein afte
r as
" th e MCAI"),

to co rre ct an unsafe cond ition for the spec ifi e d products. The MCAI

s t ates: Two occurrences
of co mmand ed in-flight
sh ut down following low oil pressure warning were reported.

In both cases the nut attach in g the swive

l union to the power turbine module 04 was found comp

l etely loose. After further investigation,

it was determined that the app li cation ofTurbomeca Service Bulletin (SB) No. 298 79 2831 may have led to incorrect torque application

or loosening of the nut.

3Turbomeca S.A. has issued Alert Mandatory Service Bulletin No. A298 79 2835, Version A, dated January
14
, 2016, to provide guidance

to assist operators

in resolving thi s unsafe condition. You may obtain further information

by examining the MCAI in the AD docket on the Internet
at http:/ /www.re gulations.gov

by searching for and locating Docket No. FAA-2016-2701. FAA's Determination
and Requirements ofThis AD This product has been approved
by the aviation authority of France and is approved for operation
in the United States. Pursuant

to our bilateral agreement with the European Community, EASA has notified

u s of the un safe condition described
in the MCAI and serv ice information referenced above. We are

i ss uing this AD because we evaluated
all information provided by EASA and determined the unsafe condition exists and is lik ely to exist or develop on other products of the same type design. This AD requires tightening the nut attaching the swivel union to the engine power turbine module M04. Related Service Information Turbomeca S.A. has issued Alert Mandatory Service Bulletin No. A298 79 2835, Version A, dated January 14, 2016. The service information describes procedures for tightening the nut attaching the swivel union to the engine power turbine module (M04). This service information

is reasonably available because
th e intere sted parties have access to it through their normal course of business
or by the means identified

in the ADDRESSES section of this document



### 4

### FAA's Determination

of the Effective Date An unsafe condition exists that requires the immediate adoption of t h is AD. The FAA ha s found that the risk to the flying public justifies waiving notice and comment prior to adoption of t h is rule because operators are required
to take act
i on with
7 days or 30 engine hours after the effective date of this AD. Therefore, we find that not

i ce and opportunity
for prior pu bl ic comment arc imp
r acticable and

t h at good cause exists for making this amendment effective

in less than 30 days. 

### Cos

t s o f Co mplian ce We estimate that this AD affects 10 engines
in s talled on airplanes ofU.S. registry. We also estimate that it will take about

1 hour per engine
to comply with this AD. The average

l abor rate is $85 per hour. No additiona

l part
s are required. Based on these figures, we estimate

t h e total cost of the AD to U.S. operators

to be $850. 

### A uth or i ty fo r T hi s Rul e makin

g Title 49 of the United States Code specifies the FAA's authority

to issue rules on aviation safety.

S u bti tl e I, section 106, describes the authority of the FAA Administrator. "Subtitle VII: Aviation Programs," describes

i n more detail the sco pe of the Agency's authority. We are issuing this rulemaking under the authority

d escribed

in "Subt itle VII, Part A, Subpart III

, Section 44701: General requirements."

U nd e r that sectio
n , Congress charges the FAA with promoting safe flight of c i vi l aircraft
in air commerce
by prescribing regu

l ations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation

is within the scope of that authority 

### 5because

it addresses
an un safe condition that

i s likely to ex
i st or develop on products identified

in this rulemaking action. Regulatory Findings We determined that
this AD will not have federalism implications under Exec utive Order 13132. This AD will not have

a s ubstantial 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) I s not a "s ignificant regulatory action" under Executive Order 12866, (2)
I s not a "s ignificant rule" under the DOT R eg ulat ory Policies and Procedures ( 44 FR
1 I 034, 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 s ub s tantial 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 Adm ini strator, the FAA amends
14 CFR part 39 as follows: PART 39

- AIRWORTHINESS DIRECTIVES I. The authority citation for part 39 continues

to read as follows: Authority:
49 U.S.C. 106(g), 40113,44701.

6

# § 39.13 [Amended] 2. The FAA amends§ 39.13 by adding the following new airworthiness directive (AD): 2016-06-09 Turbomeca S.A.: Amendment

39 -18440; Docket No. FAA-2016-2701; Directorate Identifier 2016-NE-03-AD. (a) Effective Date This AD

i s effective [INSERT DATE 15 DAYS AFTER DATE OF PUBLICATION



# IN THE FEDERAL REGISTER). (b) Affected ADs None. (c) Applicability This AD applies
to all Turbomeca S.A. Makila 2A and 2A 1 turboshaft engines that have incorporated Turbomeca S.A. Service Bulletin No. 298 79 2831, Version B, dated November
13, 2015, or earlier. (d) Reason This AD was prompted
by two occurrences
of in-flight shutdow ns as a result of the nut

, attaching the swivel union to the power turbine module M04

, coming loose. We are issuing this AD to prevent loosening
of the nut, and oil

l eakage from the low pressure oil system, which could lead to in-flight shutdown
of the engine and forced landing. (e) Actions and Compliance Comply with this AD within the compliance times specified, unless already done

. (1) Within 30 engine hour

s or 7 days after the effective date ofthis AD, whichever occurs fir st, apply 15 Newton-meters torque to the nut

, part number 79560130990, attaching the swivel union to the engine power turbine module M04. Use
a backup wrench
to prevent the swive

l union from rotating. 

### (f) Alternative Methods
of Compliance (AMOCs) The Manager, Engi
n e Certification Office

, FAA, may approve AMOCs for this AD. Use the procedures found in 14 CFR 39.19 to make your

r eq u est. You may email your request to: ANE

- AD-AMOC@faa.gov. (g) Related Information (1) For more information about this AD, contact Be s ian Luga, Aerospace Engineer, Engine Certification Office, FAA, Engine
& Prope
ll er Dir ectora te , 1200 District Avenue, Burlington, MA
0 1803

; phone: 781-238-7750;
fax: 781-238-7199; emai

l : besian.luga@faa.gov

. (2) Refer to MCAI European A v
i at ion Safety Agency AD 2016-0016, dated January 15, 2016, for more information. You may examine the MCAI in the AD docket on th e Internet
at http: //www .regulations.gov

by sea rching for and locating



### it in D ocket No. FAA-2016-270

1. (3) Turbomeca S.A. Alert Mandatory Service Bu ll etin No. A298 79 2835, Version A, dated January 14, 2016, which
is not incorporated

by reference
in this AD, / can be obtained from T urbomeca S.A., using the contact information

in paragraph (g)( 4) of this AD. ( 4) For service information identified

in this AD, contact Turbomeca S.A., 40220 Tamos, France; phone: 33 0 5 59 74 40 00; telex: 570 042; fax: 33 0 5 59 74 45 16. 

### 8(5)YoumayviewthisserviceinformationattheFAA,Engine&PropellerDirectorate,1200DistrictAvenue,Burlington,MA01803.ForinformationontheavailabilityofthismaterialattheFAA,call781-238-7125.(h)MaterialIncorporatedbyReferenceNone.IssuedinBurlington,Massachusetts,onMarch14,2016.AnnC.Mollica,ActingManager,Engine&PropellerDirectorate,AircraftCertificationService.9