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# . Federal Re gi ster /Val. 79, No. 150/Tuesday, August 5, 2014/Rules and Re gulations 

### 4533 5
DEPARTMENT OF TRANSPORTATION Fede ral Aviation Administration 14 CF R Part 39 [ Docket No

. FAA-2014-0515 ; Directorate Identifier 2014-SW-{)36-AD ; Amendme n t 3 9-17921 ; AD 2014-12

- 51)
RIN 212<>-AA64 Airworthiness D irectives ; Airbus H e licopters (Previo u sly Eurocopter France)
AGEN CY : 

### Federal Aviation Administration {FAA)

. Department of Transportation {DOT). ACTION: 

### F i nal ruJe: request for co mments.
S UMMAR Y : 

### We are 

### publishing a new airworthiness directive (AD) for Airbus H

e! icopters Model EC130B4 and EC 1 30T2 helicopters, which was previously to 

### a1J known U

. . 

### o e and operators of these he! c t r . b s AD 

### requires repetitively i · g 

### th Fenestron to tailboom j tio fr e (junction frame) for a crac
. T ht prompted by r eports of a cr propagating thro ugh the j 

### c o 1 

### ram o n two EC130B4 belicop t rs. e ac tions are intended to de ect c rack a nd to prevent failure of th e Jun ction frame, which could res ult in l oss of th e Fenest ron and subsequent loss of control of the helicopter. DATE S: 

### This AD 

### becomes effective Augus t 20. 2014 to all persons excep t those persons to whom it 

### was made inuned iat e ly effective by Emergency AD ( EAD ) 2014-12-51, issued on Jun e 10, 20 14 , which contai ned the requirements of thi s AD.



### Th e Directo r of th e Federa l Register approved the incorporation by r e fer e nc e of a ce rt a in document li sted in this AD as of August 20

. 2014.

We must receive comments on thi s AD by October 6. 2014. ADDRE SS ES : 

### You may send comments by any of the following methods:

• Federal eRulemaking Docket: Go to http ://www. regulations. gov
. 

### Fo llow the o nline i nstructions for sending your co mm e nts elec tron i ca ll y.

• Fax : 20 2-4 93

- 2251. • Mail: 

### Send comments to th e U.S. Dep artment of Transportation , D oc ke t Operatio ns , M-30 , West Buil ding Ground Floor. Room W1 2-140 , 1200 New j ersey Avenue SE

.. Washington , DC 2059Q-0001.

• Hand Delivery: 

### Deliver to the

" Mai l " address between 9 a.m. and 5 p.m., Monday through Friday, except Federa l holidays
. Ex amining the AD Do c k et Y

o u may exam in e the AD docket on the intern et at http :/ I www.regulations.gov 

### or in perso n at the Doc ket Operati ons Office between 9 a.m. and 5 p.m., Monday throug l 1 Friday, excep t Federal h olidays
. The AD 

### d oc ket co nt ai n s this AD, th e European Aviation Safety Agency (EASA) A D , an y incorporated by reference service information, the economic evaluation, any comments r ece i ved, and other information. Th e stree t address for the Docket Op erations Office (telep hone 800-647-5527) is in th e ADDRESSES 

### section. Comments w ill be available in the AD docket s hortl y a fter rece ipt

.

For service information ide · e 

### ·n
. this AD , contac t Airbu. opter
. Inc

.. 2701 N

. Fo 0 

### ive, a 52; t I (9

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### i u



## 1J~p

**e** ay re i w t 

### ati 

### a 1



### Co s
. I 

### S thw s I d , 

## z 1 R F R INFORMATION CONTACT: 

### obert G rant, Aviat.ion Safety Engineer , Safety Management Group, FAA , 2601 Meacham Blvd. , Fort W orth , Texas 76137; te lephon e (817) 222-5110; email robert.gra.nt@[aa.gov. SUPPLEMENTARY I NFO RMAT ION: 

### Commen ts Invited

This AD is a fina l rule th at involves requirements affecting flight safety, and we did not prov id e yo u with notice and an opportunity to provide your comments pr ior to i t b eco ming effective. H owever , we in vite you to participa te in this ruJemakin g b y s ubmitting written co mments. data, or views. W e aJso invite comments re lat in g to th e econ omic, environmenta l, e n ergy, or federalism impacts that resulted from adoptin g this AD. The most helpful comments r eference a speci fi c portion of the AD. exp lain the r eason for any recommended change, a nd include supporting data. To e n su r e the docket does not contain duplicate comments. commenters shou ld se nd o nly one copy of written comments
. or i f comments are filed electronicall y, co mme nters should s ubmi t them o n l y one tim e. We will fil e in the docke t all comments that we rece iv e, as well as a report summar izin g each substantive publi c co nt act with FAA perso nnel co ncerning this rulemaking during the comment period. We \-vill consider 

### a1J the comment s we receive and may conduct additional ruJemaking based on those co mme nts. Di sc uss io n On Ju ne 10. 2014, we is s u ed EAD 2014- 1 2-5 1 , which appli es to h e li co pters witJ1 690 o r more hou rs tim e- in -service (TIS). and requires witbin 10 hour s TIS, dye-penetrant inspecting ce r ta i n areas of the junc ti on frame f or a crack

. EAD 2014-12 -51 aJso requires, at intervals not exceeding 25 h ou rs TIS. e ith er repeating the dye· penetrant inspection or per f orming a bo rescope inspection of certain areas of the junction frame for a crac k

. 

### I f there is a crack, EAD 2014-12

- 51 requires rep lacin mction frame. EAD 2 5 1 w s se n t pr ev iousl y to 

### all k 

### own

**S~** 

### e rs a nd operators of ll 

### e, e l 

### c p 

### e s.

E 

### 1 51 wa s prompted by SA

. 2014

- 0145-E, date d t 

### n , 2 1 E D 2014

- 0145-E ). A , ic · the Te c hni cal Agent for

e er al es of the Europ ean ion ed EA D 2014-0145-E to c ct an unsafe condition for Airbus H

elicopters Model EC 1 30B4 and EC130T2 helicopters. EASA adv i ses that f o ll owing unscheduled in specti ons, two events of crac k propagation tbrougb th e junctio n fra me o f the tailboom / Fe n es tro n were re po rted on EC130B4 h e li cop t e rs, and that an i nvestigati on r eveal e d th e c rac ks initiated i n the lo w er ri g ht

-hand part of the junction frame between the web and th e fl ange where the lower spar of the tailboom is joined. EASA also advises that the cracks we r e of a significant length. and we re not visible from th e outside of the helicopter. Finally, EASA advises th at this condi ti on. if not detected, could l ead to struc tural f ai lure, po ss ib ly resulting in F e n es tron d e tachm en t and 

### co n se qu ent lo ss of contro l of the he l ico pter. EAD 20 14 -0 14 5-E requ ires, within 10 ho ur s TIS or 7 

### days
. inspecting th e junction frame in the radius between the we b and the flange on the tailcone side for a crack. EAD 2014-0 145-E also requires, at intervals not exceeding 25 hours TIS

. in specting the frame web for a crack wi th a bo rescope. If there is a crack, the EASA AD requires contacting Airbus He li copte rs f or repair procedures

. FAA 's Determin ation

These h e li co pter s have been approved by the aviation authority of Fran ce and are approved for o p era tion in th e United Sta tes. Pursuan t to our bilateral ag r eement wi th France, EASA , it s technical representative, has notified us of the unsa f e co ndition described in the EASA AD. We are 

### issuing this AD because we evaluated al l information provided by EASA and determined th e unsafe co nditi o n exists and i s likely to

### 45336 

### Federal Regis ter 

### I Vol. 79, No. 150 /Tuesday, August 5, 2014/ Rules and Regulations

exist or deve l op on other helicopters of these same · type designs. Re l ated Service Information

Airbus Helicopters has issued Emergency Alert Service Bulletin No. 05A017, Rev is ion 0 , dated June 6, 2014 (EASB 05A017) for Model EC130B4 and EC130T2 helicopters. EASB 05A017 describes procedures for inspe cting, lhroug h the inside of the tailboom, the web of the frame and in the radius between the web and the flange on the tailcone side for a crac k. If there is a crack, EASB 05A017 directs operators to contac t Airbus Helicop ters for specif ic procedures to return the helicopter to conformit y
. 

### AD Requirements

This AD requires, for helicopters w· 690 or more hours TIS:

• Within 10 hours TIS, mo horizontal stabil i zer, clea1 i junction frame, and dye

- e ar inspecting the junction Er me in the areas shown in F igt e 1 05A017:

• Witb.in 25 hours oft e penetrant inspection, and at n r not exceeding 25 h o urs T , e' h er repeating the dye-penetrant mspection or. using a borescope, inspecting the junction frame for a crack in the areas shown in Figure 2 of EASB 05A017.



### • If ther e is a crack, this AD requires, before further !light, replacing the junction frame. Diff e rences Between This AD and the EA SAAD

EAD 2014-0145-E allows a visual inspection for the initial 10 hour TIS inspection, whi l e this AD requires a dye-penetrant inspection. If there is a crack, EAD 2014-0145-E requires co ntacting Airbus Helicopters for approved repair instructions, while this AD requires replacing the junction**~arne.** Finally , EAD 2014-0145-E requjres in spect ing tl1e junctio n frame within 10 hours TIS or 7 days. whichever occurs earl ier. while this AD requires inspecting within 10 hours TlS. Inter im Ac tion

We consider th is EAD to be an interim action. If final action is later identified, we might consider fur th er rulemaking then

. Cos ts o f Compliauce

We estimate that this AD will affect 194 helicopters of U.S. Registry. We es timate th at operators may incur the following costs in order to comply w ith !his AD. At an average labor rate of $85 per hour , dye-penetrant inspecting tbe junction frame w ill require 1 work-hour, for a cost per helicopter of $85, and a total cost of $16 ,490 for the fleet, per inspection cycle. Borescope inspecting the junction frame will require .5 work

hour, for a cost per helicopter of $43 and a total cost of $8,342 for the fleet. per inspection cycle.

If required, replacing the junction frame will require 50 work-hours, and required parts will cost $60,000, for a cost per helicopter of $64,250. FAA's Justification and Determination of the Effective Date

Providing 

### an opportunity for pu comments before adopting th requirements wou l d d y**~** imp l ementin t £ 

### y a · nee e I to correc
. know o · n T e ore,**~~** n n · ue

nd a s t h fly· p c**.** f · 

### s ·w 

### n ic 

### d i 

### r t ado t 

### n, s 

### I b e i tilre · ti be ithi s t' -service , E

e o a sed on the a 

### rera flig ur utilization rate of t ese · opters.

Since it was found that immediate corrective action was required , notice and opportunity for prior public comment before issuing thi s AD were impractic able and contrary to the public interest and that good cause existed to make the AD effective immediately by EAD 2014-12-51, issued on June 10, 2014, to all kn own U.S. owne r s and operators of these helicopters. These conditions still exist and the AD is hereby published in the Federal Register as an amendment to section 39.13 of the Federal Aviation Regulations (14 CFR 39.13) to make it effec tive to a ll persons. Authority for T his Rulemakin,g

Title 49 of the United States Code spec ifi es the FAA's authorit y to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. "Subti tle Vll: Aviation Progran1s," describes in more detail the scope of the Agency's authority.

We are issuing this rulemaking under the authority described in "Subtit l e 

## vn. Part 

### A, Subpart 

### TIT, 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 pract i ces. methods, and procedures the Administrator finds necessary for safety in a ir commerce
. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or deve l op on products identified in this ru lemaking action. Reg ul atory Findings We determined that this AD will not have federalism implications under Executive Order 13132. Thi s AD will not have a substantial direct effect on the States, on the relationsh i p 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, I cert ify tl1at ·

. Is

Air transportation, Aircraft. Aviation safe ly, Incorporation by reference, Safety. A doption of the Amendment

According l y, under the authority delegated to me by the Administrator , the FAA amends 14 CFR part 39 as follows: PART 39-AIRWORTHINESS DIRECTIVES

• 1

. The authority citation for parl39 continues to read as follows:

Au thority : 49 U.S

.C. 106(g), 40113,44701. §39.13 [Amended)

• 2. The FAA amends§ 39.13 by adding the following new airworthiness directive (AD): 2014-12

- 51 Airb u s Heli co pters (previo u s ly Eurocopter France): Amendment 39- 1792 1 ; Docket No. FAA-2014

- 0515 ; Directorate Identifier 2014-SW-036-AD. (a) Applica bili ty This AD applies to Airbus Helicopters Model EC13 0B4 and EC130T2 heli co pters , with 690 or more h ours t i me· in-service (TIS) , certificated in any category. (b) Unsaf e Conditio n This A D defines the unsafe condition as a c rack in the tailboom to Feneslron junction frame (junction frame). This condition could result in failure of the junction frame, which could result in loss of the Fenestron and subsequent loss of conlrol of the helicopter.

### Fe deral Reg i s ter I 

### Vol. 79. No. 150 /Tuesday, August 5, 2014/Rules and Regulations 45337
(c) Eff ective D ate This AD becomes e{fective August 20, 2014 to all persons excepllhose persons to whom it was made immediately effective by Emergency AD 2014-12-51, issued on June 10, 2014, which co nta in ed the requirements of this AD. (d) Compliance

You are responsible for performing each action required by this AD within the specified compliance time unless it has already been accomplished prior to that lime. (e) Required Acti ons

(1) Within 10 hours TIS. remove the horizontal stabilizer, clean the jw1 ction frame, and dye-p enetrant inspect arow1d the circumference of the junct ion frame for a crac k in the areas shown in F i gure 1 of Airbus Helicopters EC130 Emergency Alert Service Bulletin No. 05A017, Revision 0, dated June 6. 2014 (EASB 05A017). Pay particular attention to the area around the 4 spars (item b) of Figure 1 ofEASB 05A017. An example of a crack is shown in Figure ofEASB 05A017.

(2) Within 25 hours TIS of I e i required by paragraph (e}(1) f is thereafter at intervals not ex e d TIS. either perform the actio s a (e)(l) of this AD or, if the ar is cl a , 1si a borescope, inspect around t circumference of the junclim r, crac k in the areas shown in i e 05A017. Pay particular atte ion I th · a around the 4 spars (item b) o l rc 2 of EASB 05A017. An example of a crack is shown in Figure 3 of EASB 05A017.

(3) If there is a crack, before further night. replace the junction frame. (f) Spec i a l Flight Permits

Special flight permits are prohibited. (g) Alternative Methods of Comp li ance (AMOCs)

(1) The Manager, Safe ty Management Group. FAA, may approve AMOCs for Lbis AD. Send you r proposal to: R obert Granl. Aviation Safely Engineer, Safety Management Group, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222- 5110: email roberl

. gront@faa.gov.

(2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part 91, subpart K , we suggest that you notify your principal inspector, or la c king a principal inspector, the manager o f the lo cal flight standards district offic11 or cer tificate holding district office. before operati n g any aircraft comp lying with thi s AD through an AMOC. (h ) Addit i ona l Information The subj ect of this AD is addressed in European Aviation Safety Agency EAD No. 2014-0145 -E , dated June 6, 2014. You may view the EASA AD on the Internet at http: // www.regulations.gov in Docket No. FAA2014-0515. (i) Subject

joint Aircraft Service Component (JASC) Code: 5302: Rotorcraft Tail boom. LanceT

. Gant , Acting Directorate Manager. Rotorcroft Directorate, Aircraft Certifica tion Service. (FR Doc. 2014-18247 Filed 8-4-14: 8:45 ami BILLING CODE 4911)-1 3-P

DEPARTMENT OFT

[Doc k o

. FAA-2 014-0056 ; Dire Ide er2013-NM-16D-AD ; A ;l 17906; AD 2014-15-04] R IN 212D-AA64 Airworthiness ectlves ; Saab AB , ems Airplanes AGENCY' ederal Aviation Ad · istration (FAA), Dep portation (DOT).

·ACTION: Final rul e. SUMMARY: Wear Clopting a new airworthiness 1rective (AD) for certai Saab AB. Aerosystems Model SAAB 0 airplanes. This AD \ ted by a report or rudd pedal
r iction which was the ult of water eakage at the inlet tubi of an in-line heater in the lower t of the forward fuselage. Tilis equires deactivating the potable w r syste m, or the



### b inkoping, 13 18 5591: fax a il 

### saab2000.tech up.com; Internet 

### abgroup .com. You may ion

FOR FURTHER I N RMATION CONTACT: Shahram 0 eshmandi, Aerospace Engineer nternational Branch. M116, nsport Airp lane Dire rate. F , 1601 Lind Avenue ., Renton,

A 98057-3356: teleR ne 425-227

- 1112; fax 425 -2 27- "l9.

Disc u ss ion

We is ed a notice of proposed rule ing (NPRM) to amend CFR P. 39 by adding an AD th ould pply to certain Saab aab Aerosystems Model S i'\B 2000 airplanes. The NP published in the Federal Regis t on February 25. 2014 (79 FR 1 043

. The NPRM was prompte y a report of ru dder r estri on which was the res l e ge at the in let tubing a n in-line

eater in the l ower part the forward fuselage.

The European tation Safety Agency (EASA), whic · the Technical Agent for the Me er States of the Europe Commu · y. has issued EASA Airw 1iness Directive 2013 72R1. d September 6, 2013 (r erred to

ter thi s as the Mandat Continuing Airworthiness lnfor on, or ''t he