D E PARTMENT OF TRANSPORTATION F ederal Aviation Administration 14 CFR Part 39 14910-13-PI

!Docket No. FAA-2015-0625; Directorate Identifier 2015-NE-09-AD; Amendment 39-18253; AD 2015-17-20] RIN 2120-AA64 Ai r · worthine ss Directives; G E Aviation Czech s. r.o. Turboprop Engines AGENCY: Federal Aviatio n Administration (FAA) , D OT. ACTION: Fina l ru l e. SUMMARY: We arc adopting a new a irwo rth in ess di r ective (AD) fo r certain seria l number (SIN) GE Aviation Czech s.r . o. M60 I E-ll , M60 1E-l l A, and M60 IF turboprop engines with certain part numb er (P / N) gas generator turbine (GGT) blades, installed. This AD require s removing f rom se rv ice any affected e ngine wi th ce rt ai n GG T blade s installed. This AD was prompted by the determination that certain GGT b lades are s u scep tibl e to blade fa i lure. We are issuing this AD to prevent GGT blade failure, which
cou ld lead to eng in e fai lure and lo ss of the airplane. DATES: This AD becomes effect ive [ INSERT DATE 35 DAYS AFTER DATE OF PUBLIC AT ION IN TH E FEDERAL REG I STER]. ADDRESSES: Sec the For Furthe r Information Contact sec tion. Examining tbc AD Docket You may exami ne the AD docket on the Internet at http: //www.regulatio ns. gov by searching for and l ocat i ng Docket No. F AA-20 1 5-0625; or in person at the Docket Management Faci lity between 9 a.m. and 5 p . m., Monday through Friday, except Federal h o lidays. The AD docket contains this AD, the mand ato ry cont inuing airworthin ess info r mation (MCA I) , the regulatory eval uation , any comme nts rece ived , and otherinformation. The address for the Dock et Office (phone: 800-647

- 5527) is Document Management Facility, U.S. Departm ent of Transportation , Docket Op e rat ions, M-30 , West Building Ground Floor, Room W 12-140 , 1200 New Jersey A venue SE. , Wa s hingto n , DC 20590

. 

### FOR FU R THE R I NF O R 1 \1AT ION CONTACT : Robert Green , Aerospace Engineer, E n gine Certification Office, F AA, Engine & Prope ll er Directorate , 1 2 New Eng land Exec utive Park , Burlington , MA 01803; phone : 781 -238 -7754; fax : 781-238-7199; email:
rober t. green @ faa. go v. 

### SUPP LEMENTA R Y I NFORMA TI ON: D iscu ss ion We issued a notice of propo se d rulemaking (NPRM) to amend 1 4 CFR part 39 by adding an AD that would apply to the spec ified produ c t s . The NPRM was published in the Federal Regi ster on April21 , 2015 (80 FR 22136). The NPRM propo s ed to correct an
un sa fe co n dition for th e specified products. The MCA I s tates:



### Co mm e nts It has been demonstrated that non- s hot peened Gas Gener ato r Turbine (GGT ) blades are s u sceptibl e to blade separation in the shank a r ea due to their reduced fatigue life. Thi s condition, if not corrected, could lead to an i n-flight e ngine shutdown and, consequ e ntly , reduced contro l of the aeroplane.

We gave th e public th e opportunity to participate in developing this AD. We
rec e ived no comment s on the NPRM (80 FR 22 1 36 , April2 1 , 2015). In our review of the N P RM , we found that we had included an SIN f rom th e MCAI that was in e rro r. We corrected th e e rror by remo v ing SIN 961001 from paragraph (c)(2) of thi s AD.

2Conclusion We rev iewe d th e available data a nd determined that air s afety a nd the pub li c inte rest require adopt in g thi s AD with the c h a n ges described previous ly. We determined that the se c h anges will not incr ease the econom ic bu rden o n a ny operato r or increa se the
sco p e of t hi s 

### 1\0. 

### Costs of Co mpli ance W e estimate that this A D affect s one engine installed on an a irpl a ne of U

. S

. registry . We a lso es timate that it would take a b o ut 64 hours p e r e n g in e to comp ly with this AD. Th e average labo r rate is $85 per hour. Req uired parts cost about $28,765 per
e ngin e. B ased o n these figures , we est imate the cost of this AD o n U.S. operators to be $34,205

. Authority for This Rulemaking Title 49 of th e Uni ted States Co de spec ifics the FAA's autho ri ty to issue rules on
av iation safety. Sub titl e I , section I 06 , describes the authority of the FA A A dministrator.

" Subt it le V II : Aviati on Programs ," describes in more d etai l th e scope of the Agency's authority . W e a r e iss uin g this rul e makin g und e r th e a uthority describ e d in "S ubtitle VII , Part A, Subpart III , Section 44701: G e ner a l re quirements. " Und e r that sec tion , Congress charges the FAA wi th promoting safe fli gh t o f civi l aircraft in air commerc e by pre scribin g regu lat ions f or practi ces , m et hods , a nd proc ed ures the Adm ini s tra tor find s necessary for safe t y in air commerce. Thi s regulation is w ithin th e sco p e o f that authority because it addresses an unsafe condition th a t is likely to ex ist o r d eve lop on product s id e nt ified in this rulemaking action. Regul atory F indin gs We determined that this A D will no t have federalism im plica ti o n s under Execut i ve Order 1 3 1 32. Thi s AD w ill not have a substantial direct effect o n th e Sta tes , on 3the relationship between the national gove rnm e nt and the States , o r on the distribution of power and re spo n s ib ili ti es amon g the var ious l eve ls of govern me nt. For th e reasons discussed above , I certify thi s AD: (1) Is not a "s ig nificant regulatory action" under Exec utive Order 12866 , (2) Is not a "s ignificant rul e" under the D OT R egulato ry Policies and Procedures (44 F R 11034 , February 26, 1979) , (3) Wi ll not affect intras tate av iation in A las ka to the exten t that it justifies
m akin g a regulat ory dist inction , and (4) Will not have a significant economic impact, positive or negative , on a
s ubstantial number of small entities under th e criteria of the Regu latory Flexibility Act. L ist of Subjects in 

### 14 CFR Part 

### 39 A ir transpo rta ti o n , A ircraft, Avia tion safety, Incorporation by r eference, Safety. Adoption of the Amendment Accord i ng ly, under th e authority de legated to me by the Adm inistrator , the FAA
ame nds 14 CFR part 39 as fo ll ows: PART 

### 39 -AIRWORTHINESS DIRE C TIVES 1. T he au th o rity c itati on for part 39 contin ues to read as follows: Authority: 49 U.S

. C. 1 06(g) , 401 13, 4470 1

. 

### § 39.13 [Amended 

## I 2. The 

## r: AA amen ds § 39.13 by adding the following new airworthiness directive (AD): 2015-17-20 GE Aviation Cze ch s. r.o. (Ty p e Certificate prev iou s l y held b y WALTER Engines a.s., Walter a.s., and MOTORL ET a.s.): Amendment 39- 1 8253; Do cket 

## 1:1o. F AA-20 1 5-0625 ; Directorate Id entifier 20 15-NE-09-AD

.

4**(~ )**  Ef f ectiv e Date This AD becomes effective [INSERT DATE 35 DAYS AFTER DATE OF PUBLICATION IN THE FED E RAL REGISTE R). (b) A ff ecte d ADs None. (c) App li cabi li ty This AD app li es to certain seri a l number (SIN) GE Aviati on Czech s.r.o . M601 Ell, M601 E- ll A, and M601 F turboprop engi ne models , with gas ge nerat o r turbine (GGT) blade , p art num ber ( P IN) M601-3372.6 or M601-3372.51 , installed , as follows: ( 1 )Model M601E

- 11: SINs862001 , 863008 , 894018,034005 , 034006 , 034007 , 034008 , 041003 , and 042002. (2) Model M601E-llA: SIN s 042003,042004,044001, and 044002. (3) Mode l M60IF: SINs 024001 , 002001 , 003001 , 934001 ,93 4002 , 961001. (d) Reason This AD wa s prompted by the determination that certain GGT blades are susceptib le to blade failure. These b lad es are identified as blade 

### P INs M601-3372.6 and M601-3372.51 , and are installed on a n eng ine SIN identified in paragraph (c) of this AD. We are i ss uing this AD to prevent GGT b lade failure , wh i ch could lead t o engine failure and loss of the airplane. (e) Actio ns and Comp li a n ce Comp ly with thi s AD w i th i n the compliance times specified , unle ss a lr eady done. Afte r the effect ive date of this AD: (I) D o no t r e turn to service any affec ted eng i n e w ith GGT blade , PIN M601- 3372.6 or M601- 3372.5 1 , installed , after 300 hour s time in service or six months , wh icheve r occurs first , after the effec ti ve date of this AD.

5(2) lfthe affected engines are s ub seque ntly disassembl ed or overhauled, the nons h ot pee ned GGT blades , 

### P I N M60 1-3372.6 or M60 1- 3372.5 1 , arc not e li g ib le fo r insta ll ation in any other engine after removal. ( t) A lte rn a ti ve Me th ods of Co mpli an ce (AM O Cs) The Mana ge r, Eng ine Certification Offi ce, FAA , may approve AM OC s for this AD. Use the proced ures found in 14 CFR 39. 19 to make your request. You may email your request to: ANE-AD-AMOC@faa.gov. ( g) R e l a te d Inf o rm ation (I) For m o r e information about this A D , contact Robert Green , Aerospace Engineer , E ngine Certi fication Office , FAA, Engine & Prope ll er Dir ec torate, 12 New E ng land Exe cu t ive Park, Burli ngton , MA 01803; phone : 78 1-238-7754; fax: 781-238- 7199; ema iI: robert.green @f aa.gov. (2) Refer toMCAT European Aviation Safety Agency AD 2015-0015, dated January 30 , 20 1 5 , for more information. You may examine the MCAI in the AD docket
on the Inte rn e t a t http: //www.regulations.gov by searching fo r and lo catin g it in http: //www.regulations.gov/#!doc um e ntD e taii ;D=FAA -2015-06 25 -0002. ( h) Mate ri a l In co rp o rate d 

### b y R e fere nce None.

I ssued i n Burlington , Massachusetts, on A u gust 20 , 2015

.

Co ll een M

. D ' Alessandro, Directorate Mana ge r, Engine & Propeller D irectorate , Aircraft Certification Service.



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