12370 Federal Register / Vol. 79, No. 43 / Wednesday, March 5, 2014 / Rules and Regulations 

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): 

2014–03–06 The Boeing Company: 

Amendment 39–17743; Docket No. 

FAA–2013–0866; Directorate Identifier 

2013–NM–131–AD. 

(a) Effective Date 

This AD is effective April 9, 2014. 

(b) Affected ADs 

None. 

(c) Applicability 

(1) This AD applies to all The Boeing 

Company Model 737–100, –200, –200C, 

–300, –400, and –500 series airplanes, 

certificated in any category. 

(2) Installation of Supplemental Type 

Certificate (STC) ST01219SE (http:// 

rgl.faa.gov/Regulatory_and_Guidance_

Library/rgstc.nsf/0/

2C6E3DBDDD36F91C862576A4005D64E2?

OpenDocument&Highlight=st01219se) does 

not affect the ability to accomplish the 

actions required by this AD. Therefore, for 

airplanes on which STC ST01219SE is 

installed, a ‘‘change in product’’ alternative 

method of compliance (AMOC) approval 

request is not necessary to comply with the 

requirements of 14 CFR 39.17. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Unsafe Condition 

This AD was prompted by reports of cracks 

found in the aft support fitting for the main 

landing gear (MLG) beam, and the rear spar 

upper chord and rear spar web. We are 

issuing this AD to detect and correct such 

cracks, which could grow and result in a fuel 

leak and possible fire. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspections: Group 1 

For airplanes identified in Group 1 of 

Boeing Special Attention Service Bulletin 

737–57–1318, dated May 15, 2013: At the 

applicable time specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Special Attention 

Service Bulletin 737–57–1318, dated May 15, 

2013, except as required by paragraph (i) of 

this AD, do inspections and applicable 

corrective actions using a method approved 

in accordance with the procedures specified 

in paragraph (j) of this AD. 

(h) Inspections: Groups 2–7 

For airplanes identified in Groups 2 

through 7 of Boeing Special Attention 

Service Bulletin 737–57–1318, dated May 15, 

2013: At the applicable time specified in 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Special Attention Service Bulletin 737–57– 

1318, dated May 15, 2013, except as required 

by paragraph (i) of this AD, do high 

frequency eddy current inspections to detect 

cracking of the aft support fitting for the MLG 

beam, and the rear spar upper chord and rear 

spar web in the area of rear spar station 

224.14, as applicable, in accordance with 

Option 1, 2, or 3 of the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 737–57–1318, dated May 15, 

2013. 

(1) If no crack is found, repeat the 

inspection thereafter at the time specified in 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Special Attention Service Bulletin 737–57– 

1318, dated May 15, 2013, as applicable. 

Accomplishment of the inspection of the 12 

fastener holes (locations 1–12) in accordance 

with Option 2, Action 3; or Option 3, Action 

3; as specified in note (b) of tables 2 through 

5 of paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Special Attention Service Bulletin 737–57– 

1318, dated May 15, 2013; terminates only 

the corresponding inspections that include 

note (b) in the ‘‘Repeat Interval’’ column of 

the applicable table. 

(2) If any crack is found during any 

inspection required by paragraph (g) or (g)(1) 

of this AD, repair before further flight using 

a method approved in accordance with the 

procedures specified in paragraph (j) of this 

AD. 

(i) Exception to Service Information 

Specifications 

Where Boeing Special Attention Service 

Bulletin 737–57–1318, dated May 15, 2013, 

specifies a compliance time ‘‘after the 

original issue date of this service bulletin,’’ 

this AD requires compliance within the 

specified compliance time after the effective 

date of this AD. 

(j) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO), 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 manager of the ACO, send it to the 

attention of the person identified in 

paragraph (k) of this AD. Information may be 

emailed to: 9–ANM-Seattle-ACO–AMOCRequests@faa.gov. 

(2) 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. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA), which has 

been authorized by the Manager, Seattle 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(k) Related Information 

For more information about this AD, 

contact Nancy Marsh, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office (ACO), 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: 425–917–6440; fax: 425–917–6590; 

email: nancy.marsh@faa.gov. 

(l) 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) Boeing Special Attention Service 

Bulletin 737–57–1318, dated May 15, 2013. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P. O. Box 3707, MC 2H–65, 

Seattle, WA 98124–2207; telephone 206– 

544–5000, extension 1; fax 206–766–5680; 

Internet https://www.myboeingfleet.com. 

(4) You may view this service information 

at 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. 

(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 Renton, Washington, on January 

18, 2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–02521 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–2013–0702; Directorate 

Identifier 2012–NM–181–AD; Amendment 

39–17753; AD 2014–03–15] 

RIN 2120–AA64 

Airworthiness Directives; 328 Support 

Services GmbH (Type Certificate 

Previously Held by AvCraft Aerospace 

GmbH; Fairchild Dornier GmbH; 

Dornier Luftfahrt GmbH) Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding 

airworthiness directive (AD) 2008–14– 


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16 for certain 328 Support Services 

GmbH (Type Certificate Previously Held 

by AvCraft Aerospace GmbH; Fairchild 

Dornier GmbH; Dornier Luftfahrt GmbH) 

Model 328–100 and 328–300 airplanes. 

AD 2008–14–16 required installing 

warning placards on the inside of the 

passenger door and service doors and 

modifying the hinge supports and 

support struts of the passenger doors. 

This new AD continues to require the 

actions required by AD 2008–14–16 and 

also requires replacing the fasteners 

which were installed as part of the 

modification with new fasteners of the 

correct length, adds new airplanes, and 

removes one airplane. This AD was 

prompted by reports that certain 

fasteners, which were installed as part 

of the modification, are the wrong 

length. We are issuing this AD to 

prevent incidents of inadvertent 

opening and possible detachment of a 

passenger door in-flight, resulting in 

damage to airframe and systems and 

loss of control of the airplane. 

DATES: This AD becomes effective April 

9, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of April 9, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of August 21, 2008 (73 FR 

40955, July 17, 2008). 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov/#!docketDetail;

D=FAA–2013–0702; or in person at the 

Docket Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC. 

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. You 

may view this referenced 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. 

FOR FURTHER INFORMATION CONTACT: 

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. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2008–14–16, 

Amendment 39–15611 (73 FR 40955, 

July 17, 2008). AD 2008–14–16 applied 

to certain 328 Support Services GmbH 

(Type Certificate Previously Held by 

AvCraft Aerospace GmbH; Fairchild 

Dornier GmbH; Dornier Luftfahrt GmbH) 

Model 328–100 and 328–300 airplanes. 

The NPRM published in the Federal 

Register on August 27, 2013 (78 FR 

52872). The NPRM was prompted by 

reports that certain fasteners, which 

were installed as part of the 

modification, are the wrong length. The 

NPRM proposed to continue to require 

installing warning placards on the 

inside of the passenger door and service 

doors and modifying the hinge supports 

and support struts of the passenger 

doors. The NPRM also proposed to 

require replacing the fasteners which 

were installed as part of the 

modification with new fasteners of the 

correct length, adds new airplanes, and 

removes one airplane. We are issuing 

this AD to prevent incidents of 

inadvertent opening and possible 

detachment of a passenger door inflight, resulting in damage to airframe 

and systems and loss of control of the 

airplane. 

The European Aviation Safety Agency 

(EASA), which is the aviation authority 

for Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2012–0183R1, 

dated September 28, 2012 (referred to 

after this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for the specified products. The MCAI 

states: 

At least one incident occurred where, 

immediately after take-off, the passenger door 

of a Dornier 328 aeroplane completely 

opened. The flight crew reportedly had no 

cockpit indication or audible chime prior to 

this event. The aeroplane returned to the 

departure airfield and made an uneventful 

emergency landing. Substantial damage to 

the door, handrails, door hinge arms and 

fuselage skin were found. 

The subsequent investigation could not 

find any deficiency in the design of the main 

cabin door locking mechanism. In addition, 

no technical failure could be determined that 

precipitated the event. The flight data 

recorder showed that the door was closed 

and locked before take-off and opened 

shortly afterwards. Although final proof 

could not be obtained, the most likely way 

in which the door opened was that the door 

handle was inadvertently operated during the 

take-off run. 

In response to the incident, AvCraft (the 

TC holder at the time) developed a placard 

set to warn the occupants against touching 

the door handle, as well as a structural 

modification of the passenger door hinge 

supports described in [Dornier 328 Support 

Services] Service Bulletin (SB) SB–328–52– 

460 and SB–328J–52–213 to make certain 

that the door does not separate from the 

aeroplane when inadvertently opened during 

flight, allowing a safe descent and landing. 

EASA issued AD 2007–0199 (http://

ad.easa.europa.eu/ad/2007-0199) to require 

the installation of warning placards and 

modification as detailed in these SB 

instructions. 

Since that [EASA] AD [2007–0199] was 

issued, 328 Support Services GmbH (the 

current type certificate holder) have 

determined that certain fasteners, identified 

by Part Number (P/N) NAS6703U1 and P/N 

NAS6703U2, which were installed as part of 

the modification, have the wrong length and 

must be replaced. 

For the reasons described above, this 

[EASA] AD retains the requirements of EASA 

AD 2007–0199, which is superseded, and 

requires replacement of the affected fasteners 

by the ones that have the correct length. 

This [EASA] AD has been revised to 

correct and clarify the actions required by 

paragraph (3). 

This AD also adds new airplanes and 

removes one airplane from the 

applicability of this AD. You may 

examine the MCAI in the AD docket on 

the Internet at http://

www.regulations.gov/

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

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (78 

FR 52872, August 27, 2013), or on the 

determination of the cost to the public. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting this AD 

as proposed except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (78 FR 

52872, August 27, 2013) for correcting 

the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (78 FR 52872, 

August 27, 2013). 

Costs of Compliance 

We estimate that this AD affects 35 

airplanes of U.S. registry. 

The actions that are required by AD 

2008–14–16, Amendment 39–15611 (73 

FR 40955, July 17, 2008), and retained 

in this AD take about 38 work-hours per 

product, at an average labor rate of $85 

per work-hour. Required parts cost 

about $11,961 per product. Based on 

these figures, the estimated cost of the 


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actions that were required by AD 2008– 

14–16 is $15,191 per product. 

We also estimate that it will take 

about 25 work-hours per product to 

comply with the new basic 

requirements of this AD. The average 

labor rate is $85 per work-hour. 

Required parts will cost about $0 per 

product. Based on these figures, we 

estimate the cost of this AD on U.S. 

operators to be $74,375, or $2,125 per 

product. 

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 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 above, I 

certify that this AD: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); 

3. Will not affect intrastate aviation in 

Alaska; 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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2013-0702; or in 

person at the Docket Management 

Facility between 9 a.m. and 5 p.m., 

Monday through Friday, except Federal 

holidays. The AD docket contains this 

AD, the regulatory evaluation, any 

comments received, and other 

information. The street address for the 

Docket Operations 

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 

removing Airworthiness Directive (AD) 

2008–14–16, Amendment 39–15611 (73 

FR 40955, July 17, 2008), and adding the 

following new AD: 

2014–03–15 328 Support Services GmbH 

(Type Certificate Previously Held by 

AvCraft Aerospace GmbH; Fairchild 

Dornier GmbH; Dornier Luftfahrt 

GmbH): Amendment 39–17753. Docket 

No. FAA–2013–0702; Directorate 

Identifier 2012–NM–181–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective April 9, 2014. 

(b) Affected ADs 

This AD supersedes AD 2008–14–16, 

Amendment 39–15611 (73 FR 40955, July 17, 

2008). 

(c) Applicability 

This AD applies to 328 Support Services 

GmbH (Type Certificate previously held by 

AvCraft Aerospace GmbH; Fairchild Dornier 

GmbH; Dornier Luftfahrt GmbH) airplanes, 

certificated in any category, identified in 

paragraphs (c)(1) and (c)(2) of this AD. 

(1) Model 328–100 airplanes, serial 

numbers 3005 through 3101 inclusive, 3103, 

3104, 3106, 3109, 3110, 3112, 3113, 3115, 

3117, and 3119. 

(2) Model 328–300 airplanes, all serial 

numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 11, Placards and Markings; 

and Code 52, Doors. 

(e) Reason 

This AD was prompted by reports that 

certain fasteners, which were installed as 

part of a modification, are the wrong length. 

We are issuing this AD to prevent incidents 

of inadvertent opening and possible 

detachment of a passenger door in-flight, 

resulting in damage to airframe and systems 

and loss of control of the airplane. 

(f) Compliance 

You are responsible for having the actions 

required by this AD performed within the 

compliance times specified, unless the 

actions have already been done. 

(g) Retained Installation and Modification 

for Airplanes Identified in AD 2008–14–16, 

Amendment 39–15611 (73 FR 40955, July 17, 

2008) With Revised Service Information 

This paragraph restates the requirements of 

paragraph (f) of AD 2008–14–16, Amendment 

39–15611 (73 FR 40955, July 17, 2008), with 

revised service information. 

(1) For Model 328–100 airplanes, serial 

numbers 3005 through 3098 inclusive, 3100, 

3106, 3109, 3110, 3112, 3113, 3115, 3117, 

and 3119; and Model 328–300 airplanes, 

having serial numbers 3102, 3105, 3108, 

3111, 3114, 3116, 3118, and 3120 through 

3224 inclusive: Within 30 days after August 

21, 2008, (the effective date of AD 2008–14– 

16, Amendment 39–15611 (73 FR 40955, July 

17, 2008)), install warning placards on the 

inside of the passenger door and service 

doors, in accordance with the 

Accomplishment Instructions of the service 

information specified in paragraph (g)(1)(i) or 

(g)(1)(ii) of this AD, as applicable. 

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

454, dated May 3, 2004 (for Model 328–100 

airplanes). 

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

209, dated May 3, 2004 (for Model 328–300 

airplanes). 

(2) For Model 328–100 airplanes, serial 

numbers 3005 through 3098 inclusive, 3100, 

3106, 3109, 3110, 3112, 3113, 3115, 3117, 

and 3119; and Model 328–300 airplanes, 

having serial numbers 3102, 3105, 3108, 

3111, 3114, 3116, 3118, and 3120 through 

3224 inclusive: Within 12 months after 

August 21, 2008, the effective date of AD 

2008–14–16, Amendment 39–15611 (73 FR 

0955, July 17, 2008), modify the hinge 

supports and support struts of the passenger 

doors, in accordance with the 

Accomplishment Instructions of the service 

information specified in paragraphs (g)(2)(i) 

through (g)(2)(iv) of this AD, as applicable. 

As of the effective date of this AD only the 

service information specified in paragraph 

(g)(2)(ii) or (g)(2)(iv) of this AD, as applicable, 

may be used. 

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

460, dated February 4, 2005 (for Model 328– 

100 airplanes). 

(ii) 328 Support Services Service Bulletin 

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

2012 (for Model 328–100 airplanes). 

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

213, dated February 4, 2005, (for Model 328– 

300 airplanes). 

(iv) 328 Support Services Service Bulletin 

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

17, 2011 (for Model 328–300 airplanes). 

(h) New Installation and Modification for 

Newly Added Airplanes 

For airplanes not identified in paragraph 

(g) of this AD, do the actions required by 

paragraphs (h)(1) and (h)(2) of this AD. 


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(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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