._ ...... ~..... 1~ ""-""""-. Federal Register /Val. 79, No. 150/Tuesday, August 5, 2014/Rules and Regulations 45335 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA-2014-0515; Directorate 

Identifier 2014-SW-{)36-AD; Amendment 

39-17921 ; AD 2014-12- 51) 

RIN 212<>-AA64 

Airworthiness Directives; Airbus 

Helicopters (Previously Eurocopter 

France) 

AGENCY: Federal Aviation 

Administration {FAA). Department of 

Transportation {DOT). 

ACTION: Final ruJe: request for 

comments. 

SUMMARY: We are publishing a new airworthiness directive (AD) for Airbus 

He! icopters Model EC130B4 and 

EC130T2 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 . Tht 

prompted by reports of a cr 

propagating through the j c o 1 ram 

on two EC130B4 belicopt rs. e 

actions are intended to de ect crack 

and to prevent failure of the Junction frame, which could result in loss of the Fenestron and subsequent loss of 

control of the helicopter. 

DATES: This AD becomes effective 

August 20. 2014 to all persons except 

those persons to whom it was made 

inunediately effective by Emergency AD 

(EAD) 2014-12-51, issued on June 10, 

2014, which contained the requirements 

of this AD. 

The Director of the Federal Register approved the incorporation by reference 

of a certain document listed in this AD 

as of August 20. 2014. 

We must receive comments on this 

AD by October 6. 2014. 

ADDRESSES: You may send comments by 

any of the following methods: • Federal eRulemaking Docket: Go to 

http://www.regulations.gov. Follow the 

online instructions for sending your comments electronically. 

• Fax: 202-493- 2251. • Mail: Send comments to the U.S. 

Department of Transportation , Docket 

Operations, M-30, West Building 

Ground Floor. Room W1 2-140, 1200 

New jersey Avenue SE .. Washington, DC 2059Q-0001. 

• Hand Delivery: Deliver to the "Mail" address between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

Examining the AD Docket 

You may examine the AD docket on the internet at http:/ I 

www.regulations.gov or in person at the 

Docket Operations Office between 9 

a.m. and 5 p.m., Monday througl1 

Friday, except Federal holidays. The AD 

docket contai ns this AD, the European 

Aviation Safety Agency (EASA) AD, any 

incorporated by reference service 

information, the economic 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 service information ide · e ·n. 

this AD, contact Airbu. opter . 

Inc .. 2701 N. Fo 0 ive, a 

52; t I (9 

~ 3. 72) 

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 Grant, Aviat.ion Safety Engineer, 

Safety Management Group, FAA, 2601 

Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222-5110; email 

robert.gra.nt@[aa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

This AD is a fina l rule that involves 

requirements affecting flight safety, and 

we did not provide you with notice and an opportunity to provide your 

comments prior to it becoming effective. 

However, we invite you to participate in 

this ruJemaking by submitting written 

comments. data, or views. We aJso 

invite comments relating to the economic, environmental, energy, or 

federalism impacts that resulted from 

adopting this AD. The most helpful 

comments reference a specific portion of 

the AD. explain the reason for any 

recommended change, and include 

supporting data. To ensure the docket 

does not contain duplicate comments. 

commenters should send only one copy 

of written comments. or if comments are filed electronically, commenters should submit them only one time. We will fil e 

in the docket all comments that we receive, as well as a report summarizing 

each substantive public contact with 

FAA personnel concerning this 

rulemaking during the comment period. 

We \-vill consider a1J the comments we 

receive and may conduct additional 

ruJemaking based on those comments. 

Discussion 

On June 10. 2014, we issued EAD 

2014-12-51, which applies to 

helicopters witJ1 690 or more hours time-in-service (TIS). and requires 

witbin 10 hours TIS, dye-penetrant 

inspecting certain areas of the junction 

frame for a crack. EAD 2014-12-51 aJso 

requires, at intervals not exceeding 25 

hours TIS. either repeating the dye· 

penetrant inspection or performing a 

borescope inspection of certain areas of 

the junction frame for a crack. If there 

is a crack, EAD 2014-12- 51 requires 

replacin mction frame. EAD 

2 51 w s sent previously to all 

k own S~ ers and operators of 

ll e, el c p e s. 

E 1 51 was prompted by 

SA . 2014- 0145-E, dated t n , 2 1 E D 2014- 0145-E). 

A, ic · the Technical Agent for 

e er ales of the European ion ed EAD 2014-0145-E to 

c ct an unsafe condition for Airbus 

Helicopters Model EC130B4 and 

EC130T2 helicopters. EASA advises that 

following unscheduled inspections, two events of crack propagation tbrougb the 

junction frame of the tailboom/ 

Fenestron were reported on EC130B4 

helicopters, and that an investigation 

revealed the cracks initiated in the 

lower right-hand part of the junction 

frame between the web and the flange where the lower spar of the tail boom is 

joined. EASA also advises that the 

cracks were of a significant length. and were not visible from the outside of the 

helicopter. Finally, EASA advises that 

this condition. if not detected, could 

lead to structural fai lure, possibly 

resulting in Fenestron detachment and 

consequent loss of control of the helicopter. EAD 2014-0145-E requires, 

within 10 hours TIS or 7 days. inspecting the junction frame in the 

radius between the web and the flange 

on the tailcone side for a crack. EAD 

2014-0145-E also requires, at intervals 

not exceeding 25 hours TIS. inspecting 

the frame web for a crack with a 

borescope. If there is a crack, the EASA 

AD requires contacting Airbus 

Helicopters for repair procedures. 

FAA's Determination 

These helicopters have been approved 

by the aviation authority of France and are approved for operation in the United 

States. Pursuant to our bilateral 

agreement with France, EASA, its technical representative, has notified us of the unsa fe condition described in the 

EASA AD. We are issuing this AD 

because we evaluated all information 

provided by EASA and determined the 

unsafe condition exists and is likely to 
45336 Federal Register I Vol. 79, No. 150 /Tuesday, August 5, 2014/ Rules and Regulations 

exist or develop on other helicopters of 

these same ·type designs. 

Related 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 inspecting, 

lhrough the inside of the tailboom, the 

web of the frame and in the radius 

between the web and the flange on the 

tail cone side for a crack. If there is a 

crack, EASB 05A017 directs operators to 

contact Airbus Helicopters for specific 

procedures to return the helicopter to 

conformity . 

AD Requirements 

This AD requires, for helicopters w· 

690 or more hours TIS: 

• Within 10 hours TIS, mo 

horizontal stabilizer, clea1 i 

junction frame, and dye- e ar 

inspecting the junction Er me 

in the areas shown in Figt e 1 

05A017: 

• Witb.in 25 hours oft e 

penetrant inspection, and at n r 

not exceeding 25 hours T , e' her 

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 there is a crack, this AD requires, 

before further !light, replacing the 

junction frame. 

Differences Between This AD and the 

EASAAD 

EAD 2014-0145-E allows a visual 

inspection for the initial 10 hour TIS 

inspection, while this AD requires a 

dye-penetrant inspection. If there is a 

crack, EAD 2014-0145-E requires 

contacting Airbus Helicopters for 

approved repair instructions, while this 

AD requires replacing the junction 

~arne. Finally, EAD 2014-0145-E 

requjres inspecting tl1e junction frame 

within 10 hours TIS or 7 days. 

whichever occurs earlier. while this AD 

requires inspecting within 10 hours TlS. 

Interim Action 

We consider this EAD to be an interim 

action. If final action is later identified, 

we might consider further rulemaking 

then. 

Costs of Compliauce 

We estimate that this AD will affect 

194 helicopters of U.S. Registry. We 

estimate that operators may incur the 

following costs in order to comply with 

!his AD. At an average labor rate of $85 

per hour, dye-penetrant inspecting tbe 

junction frame will 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 workhour, 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 would d y ~ implementin 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 this AD were 

impracticable 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 known U.S. owners 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 

effective to all persons. 

Authority for This Rulemakin,g 

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 Vll: 

Aviation Progran1s," describes in more 

detail the scope of the Agency's 

authority. 

We are issuing this rulemaking under 

the authority described in "Subtitle 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 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, I certify 

tl1at · 

. Is 

Air transportation, Aircraft. Aviation 

safely, 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 

• 1. The authority citation for parl39 

continues to read as follows: 

Authority: 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 Airbus Helicopters (previously 

Eurocopter France): Amendment 39-

17921; Docket No. FAA-2014- 0515; 

Directorate Identifier 2014-SW-036-AD. 

(a) Applicability 

This AD applies to Airbus Helicopters 

Model EC130B4 and EC130T2 helicopters, 

with 690 or more hours time· in-service (TIS), 

certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as a 

crack 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. 
Federal Register I Vol. 79. No. 150 /Tuesday, August 5, 2014/Rules and Regulations 45337 

(c) Effective Date 

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 contained 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 Actions 

(1) Within 10 hours TIS. remove the 

horizontal stabilizer, clean the jw1ction 

frame, and dye-penetrant inspect arow1d the 

circumference of the junction frame for a 

crack in the areas shown in Figure 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, 

crack 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) Special Flight Permits 

Special flight permits are prohibited. 

(g) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group. FAA, may approve AMOCs for Lbis 

AD. Send your proposal to: Robert 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 

lacking a principal inspector, the manager of 

the local flight standards district offic11 or 

certificate holding district office. before 

operating any aircraft complying with this 

AD through an AMOC. 

(h) Additional Information 

The subject 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 Certification Service. 

(FR Doc. 2014-18247 Filed 8-4-14: 8:45 ami 

BILLING CODE 4911)-1 3-P 

DEPARTMENT OFT 

[Dock o. FAA-2014-0056; Dire 

Ide er2013-NM-16D-AD; A 

;l 17906; AD 2014-15-04] 

RIN 212D-AA64 

Airworthiness ectlves; Saab AB, 

ems Airplanes 

AGENCY' ederal Aviation 

Ad · istration (FAA), Dep 

portation (DOT). 

·ACTION: Final rule. 

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 system, or 

the 

b 

inkoping, 

13 18 5591: fax 

ail saab2000.tech 

up.com; Internet 

abgroup.com. You may 

ion 

FOR FURTHER IN RMATION CONTACT: 

Shahram 0 eshmandi, Aerospace 

Engineer nternational Branch. M116, nsport Airplane Dire rate. 

F , 1601 Lind Avenue ., Renton, 

A 98057-3356: teleR ne 425-227-

1112; fax 425-227- "l9. 

Discussion 

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 Regist on February 25. 2014 

(79 FR 1043 . The NPRM was 

prom pte y a report of rudder 

restri on which was the res 

le ge at the inlet tubing an in-line 

eater in the lower 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 this as the Mandat Continuing 

Airworthiness lnfor on, or ''the