Federal Register / Vol. 79, No. 43 / Wednesday, March 5, 2014 / Rules and Regulations 12373 

(1) Within 30 days after the effective date 

of this AD, install warning placards on the 

inside of the passenger door and service 

doors, in accordance with the 

Accomplishment Instructions of Dornier 

Service Bulletin SB–328–11–454, dated May 

3, 2004 (for Model 328–100 airplanes); or 

Dornier Service Bulletin SB–328J–11–209, 

dated May 3, 2004 (for Model 328–300 

airplanes); as applicable. 

(2) Within 12 months after the effective 

date of this AD, modify the hinge supports 

and support struts of the passenger doors, in 

accordance with the Accomplishment 

Instructions of 328 Support Services Service 

Bulletin SB–328–52–460, Revision 2, dated 

March 1, 2012 (for Model 328–100 airplanes); 

or 328 Support Services Service Bulletin SB– 

328J–52–213, Revision 1, dated August 17, 

2011 (for Model 328–300 airplanes); as 

applicable. 

(i) New Replacement of Fasteners for All 

Airplanes 

For airplanes on which 26 part number 

NAS6703U1 fasteners were installed as 

specified in the service information in 

paragraphs (g)(2)(i) and (g)(2)(iii) of this AD: 

Within 6 months after the effective date of 

this AD, replace the 20 affected part number 

NAS6703U1 fasteners with new fasteners 

having part number NAS6703U2, in 

accordance with the Accomplishment 

Instructions of 328 Support Services Service 

Bulletin SB–328–52–460, Revision 2, dated 

March 1, 2012 (for Model 328–100 airplanes); 

or 328 Support Services Service Bulletin SB– 

328J–52–213, Revision 1, dated August 17, 

2011 (for Model 328–300 airplanes); as 

applicable. 

Note 1 to paragraph (i) of this AD: 328 

Support Services Service Bulletin SB–328– 

52–460, Revision 2, dated March 1, 2012, and 

328 Support Services Service Bulletin SB– 

328J–52–213, Revision 1, dated August 17, 

2011, identify 20 of 26 part number 

NAS6703U1 fasteners requiring to be 

replaced due to incorrect length. 

(j) Credit for Previous Actions 

This paragraph provides credit for certain 

actions required by paragraph (g) and (h)(2) 

of this AD, if those actions were performed 

before the effective date of this AD using 328 

Support Services Service Bulletin SB–328– 

52–460, Revision 1, dated August 17, 2011, 

which is not incorporated by reference. 

(k) 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: 

Todd Thompson, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone (425) 227–1175; fax (425) 227– 

1149. Information may be emailed to: 9- 

ANM-116-AMOC-REQUESTS@faa.gov. 

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. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(l) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) European 

Aviation Safety Agency Airworthiness 

Directive 2012–0183R1, dated September 28, 

2012, for related information. You may 

examine the MCAI in the AD docket on the 

Internet at http://www.regulations.gov/

#!docketDetail;D=FAA-2013-0702. 

(2) Service information identified in this 

AD that is not incorporated by reference in 

this AD may be obtained at the addresses 

specified in paragraphs (m)(3) and (m)(4) of 

this AD. 

(m) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless this AD specifies otherwise. 

(3) The following service information was 

approved for IBR on April 9, 2014. 

(i) 328 Support Services Service Bulletin 

SB–328–52–460, Revision 2, dated March 1, 

2012. 

(ii) 328 Support Services Service Bulletin 

SB–328J–52–213, Revision 1, dated August 

17, 2011. 

(4) The following service information was 

approved for IBR on August 21, 2008 (73 FR 

40955, July 17, 2008). 

(i) Dornier Service Bulletin SB–328–11– 

454, dated May 3, 2004. 

(ii) Dornier Service Bulletin SB–328J–11– 

209, dated May 3, 2004. 

(iii) Dornier Service Bulletin SB–328–52– 

460, dated February 4, 2005. 

(iv) Dornier Service Bulletin SB–328J–52– 

213, dated February 4, 2005. 

(5) For service information identified in 

this AD, contact 328 Support Services GmbH, 

Global Support Center, P.O. Box 1252, D– 

82231 Wessling, Federal Republic of 

Germany; telephone +49 8153 88111 6666; 

fax +49 8153 88111 6565; email gsc.op@

328support.de; Internet http://

www.328support.de. 

(6) 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. 

(7) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on January 

31, 2014. 

John P. Piccola, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–02995 Filed 3–4–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0351; Directorate 

Identifier 2009–SW–049–AD; Amendment 

39–17770; AD 2014–04–11] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters (Type Certificate 

Previously Held by Eurocopter France) 

(Airbus Helicopters) 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for Airbus 

Helicopters Model AS350B, BA, B1, B2, 

B3, and D, and Model AS355E, F, F1, 

F2, and N helicopters with certain tail 

rotor (T/R) blades. This AD requires 

installing additional rivets to secure 

each T/R blade trailing edge tab (tab), 

and inspecting for evidence of 

debonding of the tab after the rivets are 

installed. This AD was prompted by 

reports of T/R blade tab debonding. The 

actions of this AD are intended to 

prevent loss of a T/R blade tab, which 

could result in excessive vibration and 

loss of control of the helicopter. 

DATES: This AD is effective April 9, 

2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain documents listed in this AD 

as of April 9, 2014. 

ADDRESSES: For service information 

identified in this AD, contact Airbus 

Helicopters, Inc., 2701 N. Forum Drive, 

Grand Prairie, TX 75052; telephone 

(972) 641–0000 or (800) 232–0323; fax 

(972) 641–3775; or at http://

www.airbushelicopters.com/techpub. 

You may review the referenced service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 


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12374 Federal Register / Vol. 79, No. 43 / Wednesday, March 5, 2014 / Rules and Regulations 

2601 Meacham Blvd., Room 663, Fort 

Worth, Texas 76137. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov or in person at the 

Docket Operations Office between 9 

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

Friday, except Federal holidays. The AD 

docket contains this AD, the foreign 

authority’s ADs, any incorporated-byreference service information, the 

economic evaluation, any comments 

received, and other information. The 

street address for the Docket Operations 

Office (phone: 800–647–5527) is U.S. 

Department of Transportation, Docket 

Operations Office, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: Gary 

Roach, Aviation Safety Engineer, 

Regulations and Policy Group, 

Rotorcraft Directorate, FAA, 2601 

Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5110; email 

gary.b.roach@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On April 22, 2013, at 78 FR 23692, the 

Federal Register published our notice of 

proposed rulemaking (NPRM), which 

proposed to amend 14 CFR part 39 by 

adding an AD that would apply to 

Eurocopter France (now Airbus 

Helicopters) Model AS350B, BA, B1, B2, 

B3, D; and AS355E, F, F1, F2, and N 

helicopters with a T/R blade, part 

number (P/N) 355A12–0040–00, 355A– 

12–0040–01, 355A12–0040–02, 

355A12–0040–03, 355A–12–0040–04, 

355A12–0040–05, 355A–12–0040–07, 

355A–12–0040–08, or 355A12–0040–14, 

all serial numbers (S/N); or P/N 

355A12–0050–04, 355A12–0050–10, or 

355A12–0050–12, with a S/N 8400 

through 9224. The NPRM proposed to 

require installing additional rivets to 

secure each tab, and inspecting for 

evidence of debonding of the tab after 

the rivets are installed. The proposed 

requirements were intended to prevent 

loss of a T/R blade tab, which could 

result in excessive vibration and loss of 

control of the helicopter. 

The NPRM was prompted by AD No. 

F–2004–178, dated November 10, 2004, 

issued by the Direction Generale de 

l’Aviation Civile (DGAC), which is the 

aviation authority for France, for Model 

AS350B, BA, BB, B1, B2, B3, and D 

helicopters, fitted with certain T/R 

blades. The DGAC also issued AD No. 

F–2004–176, dated November 10, 2004, 

for Model AS355E, F, F1, F2, and N 

helicopters with certain T/R blades. The 

DGAC advises of reports of T/R blade 

tab debonding, and that the loss of the 

tab leads to a significant increase in the 

aircraft’s vibration level. As a result, the 

ADs mandate compliance with the 

manufacturer’s service information to 

install additional rivets on the tabs. 

Since we issued the NPRM, 

Eurocopter France changed its name to 

Airbus Helicopters. This AD reflects 

that change and updates the contact 

information to obtain service 

information. 

Comments 

After our NPRM (78 FR 23692, April 

22, 2013) was published, we received 

comments from one commenter. 

Request 

American Eurocopter Corp. requested 

that we remove tail rotor blade P/Ns 

355A12–0040–14, 355A12–0050–10, 

and 355A12–0050–12 from the 

applicability of our AD. The commenter 

stated that these tail rotor blades have 

trailing tabs that are integral with the 

tail rotor blade skin and not bonded on, 

and therefore are not susceptible to the 

unsafe condition identified in our AD. 

We agree and have made the requested 

change. 

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, the DCAG, its 

technical representative, has notified us 

of the unsafe condition described in its 

AD. We are issuing this AD because we 

evaluated all information provided by 

the DGAC and determined the unsafe 

condition exists and is likely to exist or 

develop on other helicopters of these 

same type designs and that air safety 

and the public interest require adopting 

the AD requirements as proposed, 

except we have changed the 

applicability from Eurocopter France to 

Airbus Helicopters and removed tail 

rotor blades, P/N 355A12–0040–14, 

355A12–0050–10, and 355A12–0050– 

12, from the Applicability section. 

These changes are consistent with the 

intent of the proposals in the NPRM (78 

FR 23692, April 22, 2013) and will not 

increase the economic burden on any 

operator nor increase the scope of the 

AD. 

Differences Between This AD and the 

DGAC AD 

This AD does not include the Model 

AS350 BB because it does not have an 

FAA-issued type certificate. This AD 

requires compliance within 100 hours 

time-in-service. The DGAC ADs require 

compliance within 100 flying hours 

‘‘without exceeding 3 months.’’ 

Related Service Information 

We reviewed Eurocopter Alert Service 

Bulletin (ASB) No. 64.00.05, Revision 2, 

dated February 15, 2007, for Model 

AS350B, BA, BB, B1, B2, B3, and D 

helicopters, and ASB No. 64.00.04, 

Revision 2, dated February 15, 2007, for 

Model AS355E, F, F1, F2, and N 

helicopters. 

These ASBs specify, within 100 flying 

hours without exceeding three months, 

installing additional rivets on T/R blade 

tabs and inspecting each tab for 

debonding after the rivets have been 

installed. The DGAC classified these 

ASBs as mandatory and issued AD No. 

F–2004–176 and AD No. F–2004–178 to 

ensure the continued airworthiness of 

these helicopters. 

Costs of Compliance 

We estimate that this AD affects 654 

helicopters of U.S. registry and that 

labor costs average $85 a work-hour. 

Based on these estimates, we expect the 

following costs: 

• Installing rivets and inspecting for 

tab debonding takes 1 hour for a labor 

cost of $85. Parts cost $100 for a total 

cost of $185 per helicopter. The cost for 

the U.S. fleet totals $120,990. 

• Replacing the tab with an airworthy 

tab, if needed, takes 4 hours for a total 

labor cost of $340. Parts cost $100, for 

a total cost of $440 per helicopter. 

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 

helicopters identified in this rulemaking 

action. 

Regulatory Findings 

This AD will not have federalism 

implications under Executive Order 

13132. This AD will not have a 


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Federal Register / Vol. 79, No. 43 / Wednesday, March 5, 2014 / Rules and Regulations 12375 

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 that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

(2) Is not a ‘‘significant rule’’ under 

DOT Regulatory Policies and Procedures 

(44 FR 11034, 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 substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared an economic evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

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 Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

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): 

2014–04–11 Airbus Helicopters (Type 

Certificate Previously Held by 

Eurocopter France): Amendment 39– 

17770; Docket No. FAA–2013–0351; 

Directorate Identifier 2009–SW–049–AD. 

(a) Applicability 

This AD applies to Model AS350B, BA, B1, 

B2, B3, D; and AS355E, F, F1, F2, and N 

helicopters with a tail rotor (T/R) blade, part 

number (P/N) 355A12–0040–00, 355A–12– 

0040–01, 355A12–0040–02, 355A12–0040– 

03, 355A–12–0040–04, 355A12–0040–05, 

355A–12–0040–07, 355A–12–0040–08, all 

serial numbers (S/N); or P/N 355A12–0050– 

04, with a S/N 8400 through 9224, 

certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

T/R blade trailing edge tab (tab) debonding. 

This condition could result in excessive 

vibration of the helicopter and loss of control 

of the helicopter. 

(c) Effective Date 

This AD becomes effective April 9, 2014. 

(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 time. 

(e) Required Actions 

Within 100 hours time-in-service, install 

additional rivets on the trailing edge tab of 

each T/R blade, according to the following 

procedures, referencing Figure 1 of 

Eurocopter Alert Service Bulletin (ASB) No. 

64.00.05, Revision 2, dated February 15, 

2007, or ASB No. 64.00.04, Revision 2, dated 

February 15, 2007, whichever is applicable to 

your model helicopter: 

(1) Lightly sand the area to be drilled, 

using No. 80 then No. 220 sandpaper. 

(2) Locate and drill eight 2.5 mm-diameter 

holes (T): 4 holes (T) 12 mm from the existing 

rivets (E) and on the centerline of the existing 

rivets (E), then 4 holes (T) 24 mm from the 

existing rivets (E) and on the centerline of the 

existing rivets (E). 

(3) Deburr and clean the area around the 

drilled holes. 

(4) Install 8 rivets (1) on tab (L). Any 

installation direction of the rivets is 

permissible (pressure face or suction face of 

the T/R blade). 

(5) Inspect the tab for debonding. 

(i) If there is no debonding, paint the area. 

(ii) If there is debonding, replace the tab. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, Rotorcraft Directorate, FAA, may 

approve AMOCs for this AD. Send your 

proposal to: Gary Roach, Aviation Safety 

Engineer, Regulations and Policy Group, 

Rotorcraft Directorate, FAA, 2601 Meacham 

Blvd., Fort Worth, Texas 76137; telephone 

(817) 222–5110; email gary.b.roach@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 office or 

certificate holding district office, before 

operating any aircraft complying with this 

AD through an AMOC. 

(g) Additional Information 

The subject of this AD is addressed in the 

Direction Generale de l’Aviation Civile 

(DGAC) AD No. F–2004–176 and AD No. F– 

2004–178, both dated November 10, 2004. 

You may view the DCAG ADs on the Internet 

at http://www.regulations.gov in Docket No. 

FAA–2013–0351. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6410, Tail rotor blades. 

(i) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Eurocopter Alert Service Bulletin 

64.00.05, Revision 2, dated February 15, 

2007. 

(ii) Eurocopter Alert Service Bulletin 

64.00.04, Revision 2, dated February 15, 

2007. 

(3) For Eurocopter service information 

identified in this AD, contact Airbus 

Helicopters, Inc., 2701 N. Forum Drive, 

Grand Prairie, TX 75052; telephone (972) 

641–0000 or (800) 232–0323; fax (972) 641– 

3775; or at http://

www.airbushelicopters.com/techpub. 

(4) You may view this service information 

that is incorporated by reference at the FAA, 

Office of the Regional Counsel, Southwest 

Region, 2601 Meacham Blvd., Room 663, Fort 

Worth, Texas 76137. 

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

(202) 741–6030, or go to: http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Fort Worth, Texas, on February 

19, 2014. 

Lance T. Gant, 

Acting Directorate Manager, Rotorcraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–04285 Filed 3–4–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0830; Directorate 

Identifier 2013–NM–128–AD; Amendment 

39–17776; AD 2014–05–03] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 777 

airplanes. This AD was prompted by a 

report of cracking in the fuselage skin 

underneath the satellite communication 

(SATCOM) antenna adapter. This AD 

requires repetitive inspections of the 

visible fuselage skin and doubler if 

installed, for cracking, corrosion, and 

any indication of contact of a certain 

fastener to a bonding jumper, and repair 

if necessary. We are issuing this AD to 

detect and correct cracking and 

corrosion in the fuselage skin, which 

could lead to rapid decompression and 


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