5254 Federal Register / Vol. 79, No. 21 / Friday, January 31, 2014 / Rules and Regulations 

(3) Repeat the measurement requirement in 

paragraphs (e)(1) or (e)(2) of this AD as 

applicable to your helicopter each time the 

collective, locking stud, or locking strip is 

replaced; each time the locking strip setting 

is readjusted; or at intervals not exceeding 

660 hours TIS or 2 years, whichever occurs 

first. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Robert Grant, 

Aviation Safety Engineer, Safety Management 

Group, FAA, 2601 Meacham Blvd., Fort 

Worth, Texas 76137; telephone 817–222– 

5110; email robert.grant@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) Eurocopter Service Bulletin (SB) No. 

67.00.21, Revision 1, dated June 21, 2006, 

and SB No. 67.00.37, Revision 2, dated 

December 2, 2008, which are not 

incorporated by reference, contain additional 

information about the subject of this AD. 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. 2009–0019, dated February 3, 2009. You 

may view the EASA AD on the Internet at 

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

FAA–2013–0679. 

(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 Emergency Alert Service 

Bulletin No. 05.00.58, Revision 0, dated 

January 12, 2008. 

(ii) Reserved. 

Note 1 to paragraph (i)(2): Eurocopter 

Emergency Alert Service Bulletin (EASB) No. 

05.00.58, Revision 0, dated January 12, 2008, 

is co-published in one document with 

Eurocopter EASB No. 05.00.35, Revision 0, 

dated January 12, 2008, which is not 

incorporated by reference in this AD. 

(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. 

(4) You may view this service information 

at FAA, Office of the Regional Counsel, 

Southwest Region, 2601 Meacham Blvd., 

Room 663, Fort Worth, Texas 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 January 16, 

2014. 

Lance T. Gant, 

Acting Directorate Manager, Rotorcraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–01467 Filed 1–30–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0611; Directorate 

Identifier 2013–CE–019–AD; Amendment 

39–17731; AD 2014–02–03] 

RIN 2120–AA64 

Airworthiness Directives; Beechcraft 

Corporation Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2011–27– 

51 for certain Beechcraft Corporation 

Models 1900, 1900C, and 1900D 

airplanes. AD 2011–27–51 required 

inspecting the elevator bob-weight and 

attaching linkage for correct installation 

and for damage or deformation to the 

weight and/or weight bracket with 

corrective action as necessary. This AD 

requires installation of the secondary 

elevator bob-weight stop bolt. The 

elevator bob-weight (stabilizer weight) 

traveling past its stop bolt may allow the 

attaching linkage to move over-center 

and lead to reduced nose down elevator 

control. We are issuing this AD to 

correct the unsafe condition on these 

products. 

DATES: This AD is effective March 7, 

2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of March 7, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of January 18, 2012 (77 FR 

2439, January 18, 2012). 

ADDRESSES: For service information 

identified in this AD, contact Beechcraft 

Corporation at P.O. Box 85, Wichita, 

Kansas 67201–0085; telephone: (800) 

429–5372 or (316) 676–3140; Internet: 

http://www.beechcraft.com. Beechcraft 

Corporation publishes service 

information for the Beechcraft 

Corporation airplanes affected by this 

AD action. 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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2013– 

0611; 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 address for the 

Docket Office (phone: 800–647–5527) is 

Document 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 20590. 

FOR FURTHER INFORMATION CONTACT: Don 

Ristow, Aerospace Engineer, Wichita 

Aircraft Certification Office, FAA, 1801 

Airport Road, Room 100, Wichita, 

Kansas 67209; telephone: (316) 946– 

4120; fax: (316) 946–4107; email: 

donald.ristow@faa.gov. 

SUPPLEMENTARY INFORMATION:

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2011–27–51, 

Amendment 39–16915 (77 FR 2439, 

January 18, 2012), (‘‘AD 2011–27–51’’). 

AD 2011–27–51 applied to certain 

Beechcraft Corporation Models 1900, 

1900C, and 1900D airplanes. The NPRM 

published in the Federal Register on 

July 17, 2013 (78 FR 42724). The NPRM 

proposed to retain all of the 

requirements of AD 2011–27–51 and 

add the requirement to install the 

secondary elevator bob-weight stop bolt, 

Kit 114–5060. We are issuing this AD to 


emcdonald on DSK67QTVN1PROD with RULES
Federal Register / Vol. 79, No. 21 / Friday, January 31, 2014 / Rules and Regulations 5255 

prevent the elevator bob-weight 

(stabilizer weight) from traveling past its 

stop bolt and allowing the attaching 

linkage to move over-center and lead to 

reduced nose down elevator control, 

which could result in loss of control. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal and the FAA’s 

response to each comment. 

Requested Change to Compliance Time 

Pat Kremer requested we change the 

compliance time for installing the 

secondary elevator bob-weight stop bolt 

Kit 114–5060 from 600 hours time-inservice (TIS) to 1,200 hours TIS or 24 

months to coincide with the continuous 

inspection program for the Model 1900C 

airplanes. This requested change would 

minimize the impact or down time for 

the airplanes. 

We disagree with this comment. We 

do not believe that 1,200 hours TIS or 

24 months will adequately mitigate the 

unsafe condition on the entire affected 

airplane fleet. We determined that 600 

hours TIS is the appropriate compliance 

time to address the identified unsafe 

condition. The proposed compliance 

time change may be adequate to address 

the unsafe condition on certain 

individual airplanes, and the FAA will 

evaluate any alternative method of 

compliance (AMOC) request we receive 

as specified in paragraph (j) of this AD. 

We did not make any changes to this 

final rule AD action based on this 

comment. 

Requested Clarification of Kit 

Instructions 

Travis Reinhardt requested the service 

information specify that a collar be used 

with the optional Hi-Lok pin. He also 

requested the service information 

contain better instructions for inhibiting 

and un-inhibiting the control system 

during installation of the secondary 

elevator bob-weight stop bolt Kit 114– 

5060. 

We agree with this comment. The 

collar should be specified to provide 

complete instructions for installation of 

the secondary elevator bob-weight stop 

bolt Kit 114–5060. The manufacturer 

has revised the kit installation 

instructions to specify the collar for use 

with the optional Hi-Lok pin and to 

clarify the intent for inhibiting the 

control system during installation of the 

kit. However, these clarification changes 

to the kit installation instructions do not 

affect the language used in this AD 

action or require any additional action 

for those airplanes that previously had 

the kit incorporated. 

We did not make any changes to the 

actions required in this final rule AD 

action based on this comment. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting this AD 

with the changes described previously 

and minor editorial changes. We have 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (78 FR 

42724, July 17, 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 42724, 

July 17, 2013). 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this AD. 

Costs of Compliance 

We estimate that this AD affects 165 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Inspection of the elevator bob-weight and 

attaching linkage.

1 work-hour × $85 per hour = $85 ........... Not applicable ........... $85 $14,025 

Installation of the secondary elevator bobweight stop bolt, Kit 114-5060.4 work-hours × $85 per hour = $340 ....... $2,740 ....................... 3,080 508,200 

The on-condition costs for any 

corrective action that may be necessary 

based on the above inspection would 

vary from airplane to airplane, and we 

have no way of determining that cost. 

The cost of the inspection is a 

retained cost from AD 2011–27–51 (77 

FR 2439, January 18, 2012) and does not 

add a burden over what was already 

imposed. 

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 have 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 

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. 

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: 


emcdonald on DSK67QTVN1PROD with RULES
5256 Federal Register / Vol. 79, No. 21 / Friday, January 31, 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 

removing Airworthiness Directive (AD) 

2011–27–51, Amendment 39–16915 (77 

FR 2439, January 18, 2012), and adding 

the following new AD: 

2014–02–03 Beechcraft Corporation: 

Amendment 39–17731 ; Docket No. 

FAA–2013–0611; Directorate Identifier 

2013–CE–019–AD. 

(a) Effective Date 

This AD is effective March 7, 2014. 

(b) Affected ADs 

This AD supersedes AD 2011–27–51, 

Amendment 39–16915 (77 FR 2439, January 

18, 2012). 

(c) Applicability 

This AD applies to the following 

Beechcraft Corporation airplanes in table 1 to 

paragraph (c) of this AD, certificated in any 

category: 

TABLE 1 TO PARAGRAPH (C) OF THIS

AD—APPLICABILITY

Models Serial Nos. 

(1) 1900 ........ UA–3. 

(2) 1900C ..... UB–1 through UB–74 and 

UC–1 through UC–174. 

(3) 1900C 

(Military).

UD–1 through UD–6. 

(4) 1900D ..... UE–1 through UE–439. 

(d) Subject 

Joint Aircraft System Component (JASC)/

Air Transport Association (ATA) of America 

Code 27, Flight Controls. 

(e) Unsafe Condition 

This AD was prompted by reports of the 

elevator bob-weight (stabilizer weight) 

traveling past its stop bolt and allowing the 

attaching linkage to move over-center, which 

could lead to reduced nose down elevator 

control. Also, Beechcraft Corporation 

designed a secondary elevator bob-weight 

stop bolt to reduce the possibility of the bobweight from traveling past the stop bolt. We 

are issuing this AD to prevent the elevator 

bob-weight (stabilizer weight) from traveling 

past its stop bolt and allowing the attaching 

linkage to move over-center and lead to 

reduced nose down elevator control, which 

could result in loss of control. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. Paragraph (g) of this AD only applies 

to airplanes where the inspection required by 

AD 2011–27–51 (77 FR 2439, January 18, 

2012) has not been done. 

(g) Retained Inspections 

Within the next 10 hours time-in-service 

(TIS) after January 18, 2012 (the effective date 

of AD 2011–27–51 (77 FR 2439, January 18, 

2012)), inspect the elevator bob-weight 

installation for the following conditions 

specified in paragraphs (g)(1) through (g)(4) 

in this AD. Use Hawker Beechcraft 

Corporation Safety Communique ́ No. 321, 

dated December 2011. 

(1) The correct positioning of the elevator 

control column link assembly, (part number 

(P/N) 101–524112–1 (1900/1900C) or P/N 

101–524112–5 (1900D)). With the elevator 

control column in the full nose down 

position (control column forward), the link 

must form an angle between the link 

attachment point at the control column and 

the bell crank pivot point as shown in the 

Hawker Beechcraft Corporation Safety 

Communique ́ photo labeled ‘‘Correct Link 

Orientation.’’ The link should be trailing aft 

from the control column assembly. The term 

‘‘nose down’’ corresponds to the airplane 

nose down, down elevator, and control 

column forward position as used in this AD 

and Hawker Beechcraft Corporation Safety 

Communique ́ No. 321, dated December 2011. 

(2) The clearance of the bob-weight stop 

bolt. With the elevator control column in the 

full nose down position (control column 

forward), the stabilizer weight stop bolt must 

have positive clearance with the face of the 

stabilizer weight. 

(3) The condition of the bob-weight and 

alignment with the stop bolt. Inspect for 

evidence of scraping along either side of the 

weight by the stop bolt. With side pressure 

applied by hand to the stabilizer weight, no 

part of the stop bolt should protrude beyond 

the face of the stabilizer weight on either 

edge. 

(4) The condition of the bob-weight support 

bracket. Inspect for evidence of damage or 

deformation by contact with the weight 

assembly. 

(h) Installation of Kit 114–5060 

Within the next 600 hours TIS after March 

7, 2014 (the effective date of this AD), install 

the secondary elevator bob-weight stop bolt, 

Kit 114–5060, following Beechcraft 

Corporation Mandatory Service Bulletin No. 

SB 27–4119, dated June 2013. 

(i) Corrective Actions 

If any discrepancies are found during the 

inspection required in paragraph (g) of this 

AD, including all subparagraphs, and during 

the installation required in paragraph (h) of 

this AD, before further flight, contact 

Beechcraft Corporation Technical Support. If 

a deviation from FAA-approved type design 

is required, then request an alternative 

method of compliance (AMOC) as described 

in paragraph (j) of this AD. You may contact 

Beechcraft Technical Support by telephone at 

(800) 429–5372 or (316) 676–3140. 

(j) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Wichita 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 the 

Related Information section of this AD. 

(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) AMOCs approved for AD 2011–27–51 

(77 FR 2439, January 18, 2012) are approved 

as AMOCs for the corresponding provisions 

of this AD. 

(k) Related Information 

For more information about this AD, 

contact Don Ristow, Aerospace Engineer, 

Wichita ACO, FAA, 1801 Airport Road, 

Room 100, Wichita, Kansas 67209; telephone: 

(316) 946–4120; fax: (316) 946–4107; email: 

donald.ristow@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. 

(3) The following service information was 

approved for IBR on March 7, 2014. 

(i) Beechcraft Corporation Mandatory 

Service Bulletin No. SB 27–4119, dated June 

2013. 

(ii) Reserved. 

(4) The following service information was 

approved for IBR on January 18, 2012 (77 FR 

2439, January 18, 2012). 

(i) Hawker Beechcraft Corporation Safety 

Communique ́ No. 321, dated December 2011. 

(ii) Reserved. 

(5) For service information identified in 

this AD, contact Beechcraft Corporation at 

P.O. Box 85, Wichita, Kansas 67201–0085; 

telephone: (800) 429–5372 or (316) 676–3140; 

Internet: http://www.beechcraft.com. 

(6) 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. 

(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 Kansas City, Missouri, on January 

15, 2014. 

Steven W. Thompson, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–01832 Filed 1–30–14; 8:45 am] 

BILLING CODE 4910–13–P 


emcdonald on DSK67QTVN1PROD with RULES