Federal Register / Vol. 78, No. 100 / Thursday, May 23, 2013 / Proposed Rules 30793 

(1) For Models Ka2B, Ka 6, Ka 6 B, Ka 6 

BR, Ka 6 C, Ka 6 CR, K7, K8, and K 8 B: 

Unless already done, within the next 10 

hours time–in–service (TIS) after April 13, 

1964 (the effective date retained from AD 64– 

07–05, Amendment 701 (29 FR 3227, March 

1, 1964)), inspect the automatic elevator 

control rod for conformity following 

Alexander Schleicher Automatic Elevator 

Connection document, dated December 5, 

1961. 

(2) For Models Ka2B, Ka 6, Ka 6 B, Ka 6 

BR, Ka 6 C, Ka 6 CR, K7, K8, and K 8 B: If 

any discrepancy is found during the 

inspection required in paragraph (f)(1) of this 

AD, before further flight, make any necessary 

repairs or modification following Civil 

Aeronautics Manual (CAM) 18, dated 

February 11, 1936, which can be found at the 

following Web site: http://ntl1.special

collection.net/scripts/ws.dll?websearch&site=

dot_cams. 

(3) For Models Ka2B, K7, K8 and K 8 B: 

Unless already done, within the next 10 

hours TIS after April 13, 1964 (the effective 

date retained from AD 64–07–05, 

Amendment 701 (29 FR 3227, March 1, 

1964)), install an additional push pull rod 

support. For Models Ka2B, follow Alexander 

Schleicher Modification No. 7, dated July 4, 

1962. For Models K7, follow Alexander 

Schleicher Modification No. 8, dated 

November 23, 1961. For Models K8, follow 

Alexander Schleicher Modification No. 7, 

dated November 24, 1961. 

(g) New Actions and Compliance 

Unless already done, do the following 

actions specified in paragraphs (g)(1) and 

(g)(2) of this AD. 

(1) For all models: Within 90 days after the 

effective date of this AD and repetitively 

thereafter at intervals not to exceed 12 

months, inspect the elevator control rod in 

the tailplane following the Action section in 

Alexander Schleicher Technical Note for Ka 

2 and Ka 2b–TM–Nr. 13, Ka 6–TM–Nr. 26, K 

7–TM–Nr. 24, K 8–TM–Nr. 30, ASK 13–TM– 

Nr. 19, ASK 18–TM–Nr. 9, Revision 1, dated 

January 8, 2013. 

(2) For all models: During any inspection 

required in paragraph (g)(1) of this AD, if any 

bend and/or misaligned elevator control 

connection is detected, before further flight 

after the inspection, replace the elevator 

control connection with a serviceable part. 

Do the replacement following the Action 

section in Alexander Schleicher Technical 

Note for Ka 2 and Ka 2b–TM–Nr. 13, 

Ka 6–TM–Nr. 26, K 7–TM–Nr. 24, K 8–TM– 

Nr. 30, ASK 13–TM–Nr. 19, ASK 18–TM–Nr. 

9, Revision 1, dated January 8, 2013. 

(h) Credit for Actions Done Following 

Previous Service Information 

This AD provides credit for the initial 

inspection required in paragraph (g)(1) of this 

AD and any necessary replacement required 

in paragraph (g)(2) of this AD if already done 

before the effective date of this AD following 

the Action sections in Alexander Schleicher 

Technical Note for Ka 2 and Ka 2b–TM–Nr. 

13, Ka 6–TM–Nr. 26, K 7–TM–Nr. 24, K 

8–TM–Nr. 30, ASK 13–TM–Nr. 19, ASK 18– 

TM–Nr. 9, dated August 30, 2012. 

(i) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Standards Office, 

FAA, has the authority to approve AMOCs 

for this AD, if requested using the procedures 

found in 14 CFR 39.19. Send information to 

ATTN: Jim Rutherford, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4165; fax: (816) 329– 

4090; email: jim.rutherford@faa.gov. Before 

using any approved AMOC on any sailplane 

to which the AMOC applies, notify your 

appropriate principal inspector (PI) in the 

FAA Flight Standards District Office (FSDO), 

or lacking a PI, your local FSDO. 

(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. 

(j) Related Information 

Refer to MCAI European Aviation Safety 

Agency (EASA) AD No. 2013–0091, dated 

April 12, 2013; Alexander Schleicher 

Automatic Elevator Connection document, 

dated December 5, 1961; Civil Aeronautics 

Manual (CAM) 18, dated February 11, 1936; 

Alexander Schleicher Modification No. 7 

Glider Ka 2 and Ka 2B, L–140 and L–203, 

dated July 4, 1962; Alexander Schleicher 

Modification No. 8 Glider K 7 L–211 (US 

7G3), dated November 23, 1961; Alexander 

Schleicher Modification No. 7 Glider K 8 

L–216 (US 7G4), dated November 24, 1961; 

Alexander Schleicher Technische Mitteilungt 

fu ̈r Technical Note for Ka 2 and Ka 2b–TM– 

Nr. 13, Ka 6–TM–Nr. 26, K 7–TM–Nr. 24, 

K 8–TM–Nr. 30, ASK 13–TM–Nr. 19, ASK 

18–TM–Nr. 9, dated August 30, 2012; and 

Alexander Schleicher Technische Mitteilungt 

fu ̈r Technical Note for Ka 2 and Ka 2b–TM– 

Nr. 13, Ka 6–TM–Nr. 26, K 7–TM–Nr. 24, 

K 8–TM–Nr. 30, ASK 13–TM–Nr. 19, ASK 

18–TM–Nr. 9, Revision 1, dated January 8, 

2013, for related information. For service 

information related to this AD, contact 

Alexander Schleicher GmbH & Co 

Segelflugzeugbau, Stra+e 1 D–36163 

Poppenhausen, Germany; phone: ++49 (0) 

6658/89–0, fax: +49 (0) 6658/89–40, email: 

info@alexander-schleicher.de; Internet: 

http://www.alexander-schleicher.de. You 

may review copies of the referenced service 

information at the FAA, Small Airplane 

Directorate, 901 Locust, Kansas City, 

Missouri 64106. For information on the 

availability of this material at the FAA, call 

(816) 329–4148. 

Issued in Kansas City, Missouri, on May 

17, 2013. 

Earl Lawrence, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. 2013–12308 Filed 5–22–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0446; Directorate 

Identifier 2010–SW–007–AD] 

RIN 2120–AA64 

Airworthiness Directives; Eurocopter 

Deutschland GmbH Model Helicopters 

AGENCY: Federal Aviation 

Administration (FAA) DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for 

Eurocopter Deutschland GmbH 

(Eurocopter) Model EC135 P1, P2, P2+, 

T1, T2, and T2+ helicopters to require 

inspecting each linear transducer 

bearing (bearing) for freedom of 

movement. This proposed AD would 

also require replacing the bearing if 

there is binding or rough turning or if 

there is chafing or damage on the lower 

side of the floor. Also, this proposed AD 

would require modifying and reidentifying a certain rod. This proposed 

AD is prompted by an incident 

involving limited control of a tail rotor 

because of the binding of a bearing. The 

proposed actions are intended to detect 

and replace each bearing subject to 

binding, which could lead to 

subsequent loss of control of the 

helicopter. 

DATES: We must receive comments on 

this proposed AD by July 22, 2013. 

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 W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590–0001. 

• 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:// 

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 proposed AD, the 

economic evaluation, any comments 


tkelley on DSK3SPTVN1PROD with PROPOSALS
30794 Federal Register / Vol. 78, No. 100 / Thursday, May 23, 2013 / Proposed Rules 

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 identified in 

this proposed 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. 

FOR FURTHER INFORMATION CONTACT: Matt 

Fuller, Senior Aviation Safety Engineer, 

Safety Management Group, Rotorcraft 

Directorate, FAA, 2601 Meacham Blvd., 

Fort Worth, Texas 76137; telephone 

(817) 222–5110; email 

matthew.fuller@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to participate in this 

rulemaking by submitting written 

comments, data, or views. We also 

invite comments relating to the 

economic, environmental, energy, or 

federalism impacts that might result 

from adopting the proposals in this 

document. The most helpful comments 

reference a specific portion of the 

proposal, 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 only one time. 

We will file in the docket all 

comments that we receive, as well as a 

report summarizing each substantive 

public contact with FAA personnel 

concerning this proposed rulemaking. 

Before acting on this proposal, we will 

consider all comments we receive on or 

before the closing date for comments. 

We will consider comments filed after 

the comment period has closed if it is 

possible to do so without incurring 

expense or delay. We may change this 

proposal in light of the comments we 

receive. 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD No. 2006– 

0318 R1, dated October 27, 2006, to 

correct an unsafe condition for all 

Eurocopter Model EC 135 helicopters. 

EASA advises of an incident in which 

impaired control of an EC 135 tail rotor 

was detected. EASA states that 

according to examinations, the bearing 

of the linear transducer was subject to 

binding, which limited the control 

range. 

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 its 

AD. We are proposing this AD because 

we evaluated all known relevant 

information and determined that an 

unsafe condition exists and is likely to 

exist or develop on other helicopters of 

these same type designs. 

Related Service Information 

Eurocopter has issued Alert Service 

Bulletin EC135–67A–012, Revision 1, 

dated October 18, 2006 (ASB), which 

specifies inspecting the bearing of the 

linear transducer for freedom of 

movement and the lower side of the 

floor for chafing or damage. If there is 

binding, the ASB specifies replacing the 

bearing. If there is chafing or damage on 

the floor, the ASB specifies replacing 

the bearing and repairing the floor. The 

ASB also specifies modifying and 

reidentifying a certain rod. EASA 

classified this ASB as mandatory and 

issued EASA AD 2006–0318 R1, dated 

October 27, 2006, to ensure the 

continued airworthiness of these 

helicopters. 

Proposed AD Requirements 

This proposed AD would require, at 

specified intervals, inspecting each 

bearing for freedom of movement. If 

there is binding or rough turning, this 

proposed AD would require, before 

further flight, replacing the bearing or if 

there is chafing or damage on the lower 

side of the floor, replacing the bearing 

and repairing the floor, and, thereafter, 

installing a Teflon strip. This proposed 

AD would also require modifying the 

rod and re-identifying the rod and lever 

with a new part number. 

Differences Between This Proposed AD 

and the EASA AD 

This proposed AD does not refer to 

the compliance date of October 31, 

2006, because that date has passed; 

instead we propose compliance within 

100 hours TIS. The proposed AD would 

not require contacting Eurocopter 

customer support. This proposed AD 

would require modifying each rod 

within 100 hours TIS, rather than 

within 800 hours TIS as specified in the 

EASA AD. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 214 helicopters of U.S. 

Registry. We estimate that operators 

may incur the following costs in order 

to comply with this AD: It would take 

about 10 work-hours to inspect the 

bearing for freedom of movement at an 

average labor rate of $85 per work hour. 

No parts or materials are required for 

the inspection. Based on these 

estimates, the cost would be $850 per 

helicopter or $181,900 for the fleet of all 

U.S.-registered helicopters. If necessary, 

replacing the bearing would require 3 

additional work-hours, and parts would 

cost $50. Repairing the floor would 

require 3 additional work hours and 

minimal cost for materials. 

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 proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would 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 

this proposed regulation: 

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 to the extent that it justifies 

making a regulatory distinction; and 


tkelley on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 78, No. 100 / Thursday, May 23, 2013 / Proposed Rules 30795 

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 proposed 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. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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): 

Eurocopter Deutschland GmbH: Docket No. 

FAA–2013–0446; Directorate Identifier 

2010–SW–007–AD. 

(a) Applicability 

This AD applies to Model EC135 P1, P2, 

P2+, T1, T2, and T2+ helicopters, with 

bearing, part number (P/N) LN9367GE6N2; 

rod, P/N L671M5040205; lever, P/N 

L671M5040101; and floor, P/N 

L533M1014101, L533M1014102, 

L533M1014103, L533M1014104, 

L533M1014105 or L533M1014106, installed, 

certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

limited control of a tail rotor because of the 

binding of a bearing. This condition could 

result in subsequent loss of control of the 

helicopter. 

(c) 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. 

(d) Required Actions 

(1) Within 100 hours time-in-service (TIS) 

and thereafter at intervals not to exceed 800 

hours TIS, inspect each bearing for freedom 

of movement by turning and tilting the 

bearing as depicted in Figure 2 of Eurocopter 

Alert Service Bulletin No. EC135–67A–012, 

Revision 1, dated October 18, 2006 (ASB). 

During any inspection: 

(i) If there is binding or rough turning, 

before further flight, replace the bearing with 

an airworthy bearing. 

(ii) If there is chafing on the lower side of 

the floor that does not extend through the 

panel outer layer, before further flight, 

replace the bearing with an airworthy 

bearing. 

(iii) If there is damage on the lower side 

of the floor in the area of the assembly 

opening that extends through the panel outer 

layer (revealing an open honeycomb cell or 

layer), before further flight, replace the 

bearing with an airworthy bearing and repair 

the floor. 

(2) After performing the actions in (d)(1)(i) 

through (iii) of this AD, before further flight, 

install a Teflon strip and identify the floor by 

following the Accomplishment Instructions, 

paragraphs 3.E.(1) through 3.E.(4), of the 

ASB. 

(3) Within 100 hours TIS, modify and reidentify the rod as depicted in Figure 1 of the 

ASB and by following the Accomplishment 

Instructions, paragraphs 3.H.(1) through 

3.H.(3)(f), of the ASB. 

(e) Alternative Methods of Compliance 

(AMOC) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Matt Fuller, 

Senior Aviation Safety Engineer, Safety 

Management Group, Rotorcraft Directorate, 

FAA, 2601 Meacham Blvd., Fort Worth, 

Texas 76137; telephone (817) 222–5110; 

email matthew.fuller@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. 

(f) 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 copies of the 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 AD No. 

2006–0318 R1, dated October 27, 2006. 

(g) Subject 

The Joint Aircraft System/Component 

(JASC) Code is 6720: Tail Rotor Control 

System. 

Issued In Fort Worth, Texas, on May 14, 

2013. 

Kim Smith, 

Directorate Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–12309 Filed 5–22–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0262; Directorate 

Identifier 2013–NE–13–AD] 

RIN 2120–AA64 

Airworthiness Directives; Hamilton 

Standard Division and Hamilton 

Sundstrand Corporation Propellers 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for 

Hamilton Standard Division model 6/ 

5500/F and 24PF and Hamilton 

Sundstrand Corporation model 14RF, 

14SF, 247F, and 568F series propellers. 

This proposed AD was prompted by the 

amount of corrosion detected during 

major inspections (MIs). This proposed 

AD would require incorporating 

inspections, based on a calendar time, 

into the propeller maintenance 

schedule. We are proposing this AD to 

prevent corrosion that could result in 

propeller failure and loss of airplane 

control. 

DATES: We must receive comments on 

this proposed AD by July 22, 2013. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

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

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact Hamilton 

Sundstrand Corporation, One Hamilton 

Road, Mail Stop 1A–3–C63, Windsor 

Locks, CT 06096–1010; or Hamilton 

Standard Division, One Hamilton Road, 

United Technologies Corporation, Mail 

Stop 1A–3–C63, Windsor Locks, CT 

06096–1010; phone: 877–808–7575; fax: 

860–660–0372; email: 

tech.solutions@hs.utc.com; Internet: 

http://myhs.hamiltonsundstrand.com. 

You may view this service 

information at the FAA, Engine & 

Propeller Directorate, 12 New England 


tkelley on DSK3SPTVN1PROD with PROPOSALS