52412 Federal Register / Vol. 78, No. 164 / Friday, August 23, 2013 / Rules and Regulations 

(2) Visually inspect each weight and lever 

for corrosion and damage in the threaded 

areas as depicted in Figure 2 of ASB No. 

ASB–MBB–BK117–30–113, dated September 

23, 2008; ASB No. ASB BO105–30–116, 

dated September 23, 2008; or ASB No. ASB 

BO 105 LS 30–12, dated December 12, 2008; 

as applicable to your model helicopter. 

(i) If there is no corrosion or thread damage 

on either the weight or lever, before further 

flight, reinstall the weight by following 

paragraph (e)(3) of this AD. 

(ii) If there is corrosion or thread damage 

on the threaded portion of a weight: 

(A) If the total area of corrosion or thread 

damage, or both, covers less than 25 percent 

of the length of the threaded area, the weight 

can be threaded (screwed) onto the lever, and 

the cylindrical mating surface has no 

damage, before further flight, remove the 

corrosion and reinstall the weight by 

following paragraph (e)(3) of this AD. 

(B) If the total area of corrosion or thread 

damage, or both, covers 25 percent or more 

of the length of the threaded area, the weight 

cannot be threaded (screwed) onto the lever, 

or the cylindrical mating surface has damage, 

before further flight, replace the weight with 

an airworthy weight by following paragraph 

(e)(3) of this AD. 

(iii) If there is corrosion or thread damage 

on the threaded portion of the lever, polish 

out the corrosion and thread damage using a 

polishing cloth 600 and: 

(A) If the thread depth does not exceed 0.3 

millimeter (mm) and the diameter of the 

lever in the area before the threaded area is 

not less than 9.95 mm after polish out, before 

further flight, install airworthy weights to the 

lever by following paragraph (e)(3) of this 

AD. 

(B) If the thread depth is 0.3 mm or greater 

or the diameter of the lever in the area before 

the threaded area is less than 9.95 mm after 

polish out, before further flight, replace the 

lever with an airworthy lever. 

(3) Apply corrosion preventive paste onto 

the thread of the lever and install weights to 

the lever as depicted in Figure 1 of ASB No. 

ASB–MBB–BK117–30–113, dated September 

23, 2008; ASB No. ASB BO105–30–116, 

dated September 23, 2008; or ASB No. ASB 

BO 105 LS 30–12, dated December 12, 2008; 

as applicable to your model helicopter. 

Ensure during installation of the weights that 

the weights are correctly assigned and 

installed to the control lever in accordance 

with the applied marks. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Sharon Miles, 

Aviation Safety Engineer, Regulations and 

Policy Group, Rotorcraft Directorate, FAA, 

2601 Meacham Blvd., Fort Worth, TX 76137; 

telephone (817) 222–5110; email 

sharon.y.miles@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 

European Aviation Safety Agency (EASA) AD 

No. 2008–0206, dated November 25, 2008, 

and in Transport Canada Civil Aviation 

(TCCA) AD No. CF–2009–12, dated March 

24, 2009. You may view the EASA and the 

TCCA AD on the Internet at http://

www.regulations.gov in Docket No. FAA– 

2012–0887. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6420, Tail Rotor Head. 

(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 (ASB) 

No. ASB–MBB–BK117–30–113, dated 

September 23, 2008. 

(ii) Eurocopter ASB No. ASB BO105–30– 

116, dated September 23, 2008. 

(iii) Eurocopter ASB No. ASB BO 105 LS 

30–12, dated December 12, 2008. 

(3) For Eurocopter service information 

identified in this AD, contact American 

Eurocopter Corporation, 2701 N. Forum 

Drive, Grand Prairie, TX 75052; telephone 

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

641–3775; or at http://www.eurocopter.com/ 

techpub. 

(4) You may view this service information 

at FAA, Office of the Regional Counsel, 

Southwest Region, 2601 Meacham Blvd., 

Room 663, Fort Worth, TX 76137. For 

information on the availability of this 

material at the FAA, call (817) 222–5110. 

(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 August 2, 

2013. 

Lance T. Gant, 

Acting Directorate Manager, Rotorcraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–19442 Filed 8–22–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0020; Directorate 

Identifier 2010–SW–107–AD; Amendment 

39–17558; AD 2013–16–20] 

RIN 2120–AA64 

Airworthiness Directives; Eurocopter 

Deutschland GmbH (ECD) Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for ECD 

Model MBB–BK 117 C–2 helicopters. 

This AD requires inspecting the rigging 

of the power-boosted control system 

and, if there is a nonparallel gap 

between the rigging wedges and the 

inner sleeves, performing a rigging 

procedure. This AD was prompted by 

the discovery, during rigging of the 

main rotor controls, of movement of the 

longitudinal main rotor actuator piston 

after shut-down of the external pump 

drive. Such movement could cause 

incorrect rigging results. The actions of 

this AD are intended to prevent 

incorrect rigging results, which could 

impair freedom of movement of the 

upper controls and subsequent reduced 

control of the helicopter. 

DATES: This AD is effective September 

27, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain document listed in this AD 

as of September 27, 2013. 

ADDRESSES: For service information 

identified in this AD, contact American 

Eurocopter Corporation, 2701 N. Forum 

Drive, Grand Prairie, TX 75052, 

telephone (972) 641–0000 or (800) 232– 

0323, fax (972) 641–3775, or at http://

www.eurocopter.com/techpub. You may 

review the referenced service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 

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, any 

incorporated-by-reference service 

information, the foreign authority’s AD, 

the economic evaluation, any comments 

received, and other information. The 


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Federal Register / Vol. 78, No. 164 / Friday, August 23, 2013 / Rules and Regulations 52413 

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: Jim 

Grigg, Manager, FAA, Rotorcraft 

Directorate, Safety Management Group, 

2601 Meacham Blvd., Fort Worth, TX 

76137; telephone (817) 222–5110; email 

jim.grigg@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On April 22, 2013, at 78 FR 23696, the 

Federal Register published our notice of 

proposed rulemaking (NPRM), which 

proposed to amend 14 CFR part 39 to 

include an AD that would apply to 

Model MBB–BK 117 C–2 helicopters. 

The NPRM proposed to require 

inspecting the rigging of the powerboosted control system and, if there is 

a nonparallel gap between the rigging 

wedges and the inner sleeves, 

performing a rigging procedure. The 

proposed requirements were intended to 

prevent incorrect rigging results, which 

could impair freedom of movement of 

the upper controls and subsequent 

reduced control of the helicopter. 

The NPRM was prompted by AD No. 

2010–0248, dated November 26, 2010 

(AD 2010–0248), issued by the 

European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union. EASA issued AD 2010–0248 to 

correct an unsafe condition for the ECD 

Model MBB–BK 117 C–2 helicopter. 

EASA advises that during rigging of the 

main rotor controls, it was discovered 

that the piston of the longitudinal main 

rotor actuator had moved after shutdown of the external pump drive. 

Comments 

We gave the public the opportunity to 

participate in developing this AD, but 

we did not receive any comments on the 

NPRM (78 FR 23696, April 22, 2013). 

FAA’s Determination 

These helicopters have been approved 

by the aviation authority of Germany 

and are approved for operation in the 

United States. Pursuant to our bilateral 

agreement with Germany, EASA, its 

technical representative, has notified us 

of the unsafe 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 

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. 

Differences Between This AD and the 

EASA AD 

We do not require inserting temporary 

changes into the performance section of 

the Rotorcraft Flight Manual. 

Related Service Information 

ECD has issued Alert Service Bulletin 

ASB MBB BK117 C–2–67A–012, 

Revision 0, dated September 20, 2010 

(ASB). The ASB specifies a one-time 

verification of the correct adjustment of 

the rigging of the main rotor controls 

and provides the corresponding test 

procedure. The ASB further provides an 

improved rigging procedure as a 

temporary revision to the ECD BK117C2 

Aircraft Maintenance Manual. EASA 

classified this ASB as mandatory and 

issued AD 2010–0248 to ensure the 

continued airworthiness of these 

helicopters. 

Costs of Compliance 

We estimate that this AD will affect 

108 helicopters of U.S. Registry. 

We estimate that operators may incur 

the following costs in order to comply 

with this AD: 

• $680 for 8 work hours per 

helicopter to inspect the main rotor 

control rigging at an average labor rate 

of $85 per work hour; 

• No additional costs are associated 

with rigging adjustment, if necessary; 

and 

• $73,440 for the total cost of the AD 

on U.S. operators. 

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 

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): 

2013–16–20 Eurocopter Deutschland GmbH 

(ECD): Amendment 39–17558; Docket 

No. FAA–2013–0020; Directorate 

Identifier 2010–SW–107–AD. 

(a) Applicability 

This AD applies to Model MBB–BK 117 C– 

2 helicopters, certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

movement of the longitudinal main rotor 

actuator piston after shut-down of the 

external pump drive, during rigging of the 

main rotor controls, causing an incorrect 

rigging result. This condition could impair 

freedom of movement of the upper controls 

and subsequently reduce control of the 

helicopter. 

(c) Effective Date 

This AD becomes effective September 27, 

2013. 


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52414 Federal Register / Vol. 78, No. 164 / Friday, August 23, 2013 / Rules and Regulations 

(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 300 hours time-in-service: 

(1) Inspect the rigging of the power-boosted 

control system, referencing Figure 1 of 

Eurocopter Alert Service Bulletin ASB MBB 

BK117 C–2–67A–012, Revision 0, dated 

September 20, 2010 (ASB). Ensure the piston 

of the longitudinal actuator (right-hand side) 

is held in the fully extended position and the 

piston of the lateral actuator (left-hand side) 

is held in the fully retracted position against 

the mechanical stop. Also, ensure the gauge 

block is clamped between the sliding sleeve 

and the support tube. 

(2) Insert the rigging wedges with the 25.4 

degree (item 8 of Figure 1 of the ASB) and 

19.5 degree (item 7 of Figure 1 of the ASB) 

markings in the ‘‘A’’ side of the guide grooves 

of the rigging device (item 3 of Figure 1 of 

the ASB). 

(3) If the gap between the rigging wedges 

(items 7 and 8 of Figure 1 of the ASB) and 

the inner sleeves (item 9 of Figure 1 of the 

ASB) is closed, the rigging is correct. 

(4) If there is a nonparallel gap between the 

rigging wedges (items 7 and 8 of Figure 1 of 

the ASB) and the inner sleeves (item 9 of 

Figure 1 of the ASB), the rigging is not 

correct. Perform a rigging procedure. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Jim Grigg, 

Manager, Rotorcraft Directorate, 2601 

Meacham Blvd., Fort Worth, TX 76137, 

telephone (817) 222–5110, email Jim.Grigg@

faa.gov. 

(2) For operations conducted under 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 

(1) For service information identified in 

this AD, contact American Eurocopter 

Corporation, 2701 N. Forum Drive, Grand 

Prairie, TX 75052, telephone (972) 641–0000 

or (800) 232–0323, fax (972) 641–3775, or at 

http://www.eurocopter.com/techpub. You 

may review the referenced service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 2601 

Meacham Blvd., Room 663, Fort Worth, 

Texas 76137. 

(2) The subject of this AD is addressed in 

European Aviation Safety Agency (EASA) AD 

No. 2010–0248, dated November 26, 2010. 

You may view the EASA AD at http://

www.regulations.gov in Docket No. FAA– 

2013–0020. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6710 Main Rotor Control. 

(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 ASB 

MBB BK117 C–2–67A–012, Revision 0, dated 

September 20, 2010. 

(ii) Reserved. 

(3) For Eurocopter service information 

identified in this AD, contact American 

Eurocopter Corporation, 2701 N. Forum 

Drive, Grand Prairie, TX 75052, telephone 

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

641–3775, or at http://www.eurocopter.com/ 

techpub. 

(4) You may view this service information 

that is incorporated by reference at http://

www.regulations.gov in Docket No. FAA– 

2013–0020. 

(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 August 2, 

2013. 

Lance T. Gant, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–19443 Filed 8–22–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1076; Directorate 

Identifier 2011–NM–274–AD; Amendment 

39–17556; AD 2013–16–18] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Airbus Model A320–214, –232 and –233 

airplanes; and Model A321–211, –213, 

and –231 airplanes. This AD was 

prompted by a report of a missing 

fastener between certain stringers of the 

fuselage frame that connects the frame 

to a tee. This AD requires an inspection 

for a missing fastener, and a rototest 

inspection and a modification or repair 

of the fuselage frame at the affected area 

if necessary. We are issuing this AD to 

detect and correct cracking in the 

fuselage that could result in reduced 

structural integrity of the airplane. 

DATES: This AD becomes effective 

September 27, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of September 27, 2013. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue SE., 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone (425) 227–1405; 

fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. The 

NPRM was published in the Federal 

Register on October 16, 2012 (77 FR 

63270). The NPRM proposed to correct 

an unsafe condition for the specified 

products. The European Aviation Safety 

Agency (EASA), which is the aviation 

authority for the Member States of the 

European Community, has issued EASA 

Airworthiness Directive 2011–0229, 

dated December 6, 2011 (referred to 

after this as ‘‘the MCAI’’), to correct an 

unsafe condition for the specified 

products. The MCAI states: 

During a quality check in production of an 

A320 family aeroplane, it was discovered 

that a fastener was missing at [frame] FR 24 

between stringer (STRG) 25 and STRG 26 on 

the right-hand (RH) side. The purpose of the 

missing fastener, a 4 [millimeter] mm 

diameter aluminum rivet, Part Number (P/N) 

ASNA2050DXJ040, is to connect the FR 24 to 

the FR 24 Tee. The hole where the fastener 

was missing was not drilled. 

Further investigations revealed that the 

drilling was missing on the milling grid used 

for frame assembly of a limited group of 

aeroplanes. 

This condition, if not corrected, could 

impair the structural integrity of the affected 

aeroplanes. 

For the reasons described above, this 

[EASA] AD requires a special detailed 

inspection (SDI) [rototest inspection for 

cracking] of the affected area, and the 

accomplishment of the associated corrective 

actions [modification and/or repair]. 

You may obtain further information by 

examining the MCAI in the AD docket. 


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