73906 Federal Register / Vol. 77, No. 239 / Wednesday, December 12, 2012 / Rules and Regulations 

(1) For airplanes on which the special 

detailed inspection specified in AWL 53–61– 

153 of Bombardier TR 2B–2187, dated June 

22, 2011; or Canadair Regional Jet TR 2B– 

2109, dated October 13, 2005; has not been 

done as of the effective date of this AD: The 

initial compliance time for AWL 53–61–153 

is at the applicable time specified in 

paragraph (i)(1)(i) or (i)(1)(ii) of this AD. 

(i) For airplanes that have accumulated 

10,500 total flight cycles or less as of the 

effective date of this AD: Before the 

accumulation of 12,000 total flight cycles. 

(ii) For airplanes that have accumulated 

more than 10,500 total flight cycles as of the 

effective date of this AD: Within 1,500 flight 

cycles after the effective date of this AD. 

(2) For airplanes on which the special 

detailed inspection specified in AWL 53–61– 

153 of Bombardier TR 2B–2187, dated June 

22, 2011; or Canadair Regional Jet TR 2B– 

2109, dated October 13, 2005; has been done 

as of the effective date of this AD: The initial 

compliance time for AWL 53–61–153 is 

within 4,360 flight cycles after accomplishing 

the most recent special detailed inspection, 

or within 1,500 flight cycles after 

accomplishing the most recent detailed 

inspection as specified in AWL 53–61–153 of 

Canadair Regional Jet TR 2B–2109, dated 

October 13, 2005, whichever occurs later. 

(j) No Alternative Actions or Intervals 

After accomplishing the revisions required 

by paragraph (i) of this AD, no alternative 

actions (e.g., inspections) or intervals may be 

used other than those specified in 

Bombardier TR 2B–2187, dated June 22, 

2011, to Appendix B—Airworthiness 

Limitations, of Part 2 of the Bombardier CL– 

600–2B19 MRM, unless the actions and 

intervals are approved as an AMOC in 

accordance with the procedures specified in 

paragraph (l)(1) of this AD. 

(k) New Action of This AD: General Revision 

of the MRM 

The maintenance program revision 

required by paragraph (i) of this AD may be 

done by inserting a copy of Bombardier TR 

2B–2187, dated June 22, 2011, into Appendix 

B—Airworthiness Limitations, of Part 2 of 

the Bombardier CL–600–2B19 MRM. When 

this TR has been included in general 

revisions of the MRM, the general revisions 

may be inserted in the MRM, provided the 

relevant information in the general revision 

is identical to that in this TR. 

(l) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York Aircraft 

Certification Office (ACO), ANE–170, 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 ATTN: Program Manager, Continuing 

Operational Safety, FAA, New York ACO, 

1600 Stewart Avenue Suite 410, Westbury, 

New York 11590; telephone (516) 228–7300; 

fax (516) 794–5531. 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. AMOCs 

approved previously in accordance with AD 

2005–23–01, Amendment 39–14359 (70 FR 

69073, November 14, 2005), are approved as 

AMOCs with the corresponding requirements 

of paragraphs (g) and (h) of this AD only. 

(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. 

(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 the AD specifies otherwise. 

(3) The following service information was 

approved for IBR on January 16, 2013. 

(i) Bombardier TR 2B–2187, dated June 22, 

2011, to Appendix B—Airworthiness 

Limitations, of Part 2 of the Bombardier CL– 

600–2B19 MRM. 

(ii) Reserved. 

(4) The following service information was 

approved for IBR on November 29, 2005 (70 

FR 69073, November 14, 2005). 

(i) Canadair Regional Jet Temporary 

Revision 2B–2109, dated October 13, 2005, to 

the Canadair Regional Jet Maintenance 

Requirements Manual, Part 2, Appendix B, 

‘‘Airworthiness Limitations.’’ 

(ii) Reserved. 

(5) For service information identified in 

this AD, contact Bombardier, Inc., 400 CoˆteVertu Road West, Dorval, Que ́bec H4S 1Y9, 

Canada; telephone 514–855–5000; fax 514– 

855–7401; email 

thd.crj@aero.bombardier.com; Internet http:// 

www.bombardier.com. 

(6) You may review copies of the 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 

November 30, 2012. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–29708 Filed 12–11–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0501; Directorate 

Identifier 2009–SW–083–AD; Amendment 

39–17258; AD 2012–23–02] 

RIN 2120–AA64 

Airworthiness Directives; Agusta 

S.p.A. Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for Agusta 

S.p.A. (Agusta) Model A109E and 

Model A109S helicopters with certain 

lower semichannel assemblies installed. 

This AD requires a one-time inspection 

of the lower semichannel assemblies to 

determine if metallic spacers are 

installed. If the metallic spacers are 

installed, this AD requires an inspection 

for the correct installation of the 

metallic spacers on the semichannels 

and for the correct seating of the gaskets. 

If the metallic spacers are not installed 

with rivets, the lower semichannel 

assemblies must be modified, and the 

main drive shaft must be inspected for 

damage. This AD was prompted by 

reports of damage to the main drive 

shaft caused by improperly secured 

metallic spacers on some A109 model 

helicopters. The actions of this AD are 

intended to detect missing spacer rivets, 

which could allow the metallic spacers 

to rotate and lead to damage and failure 

of the main drive shaft, and subsequent 

loss of helicopter control. 

DATES: This AD is effective January 16, 

2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain documents listed in this AD 

as of January 16, 2013. 

ADDRESSES: For service information 

identified in this AD, contact Agusta 

Westland, Customer Support & Services, 

Via Per Tornavento 15, 21019 Somma 

Lombardo (VA) Italy, ATTN: Giovanni 

Cecchelli; telephone 39–0331–711133; 

fax 39 0331 711180; or at http:// 

www.agustawestland.com/technicalbullettins. 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:// 


emcdonald on DSK67QTVN1PROD with 
Federal Register / Vol. 77, No. 239 / Wednesday, December 12, 2012 / Rules and Regulations 73907 

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 economic evaluation, 

any comments received, and other 

information. The street address for the 

Docket Operations Office (phone: 800– 

647–5527) is U.S. Department of 

Transportation, Docket Operations 

Office, M–30, West Building Ground 

Floor, Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: Jim 

Grigg, Manager, Safety Management 

Group, Rotorcraft Directorate, FAA, 

2601 Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5110; email 

jim.grigg@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On May 22, 2012, at 77 FR 30234, 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 A109E helicopters, up to and 

including serial number (S/N) 11694, 

except 11633 and 11634; and Model 

A109S helicopters, up to and including 

S/N 22034, except 22026 and 22033; 

with lower semichannel assemblies, 

part number (P/N)109–0641–10–213 or 

109–0642–01–171, installed. That 

NPRM proposed to require a one-time 

inspection of the lower semichannel 

assemblies to determine if metallic 

spacers are installed. If the metallic 

spacers are installed, the AD proposed 

to require an inspection for the correct 

installation of the metallic spacers and 

correct seating of the gaskets. If the 

metallic spacers are installed without 

rivets, the AD proposed to require 

modification of the lower semichannel 

assemblies and inspection of the main 

drive shaft for damage. The proposed 

requirements were intended to detect 

missing spacer rivets, which could 

allow the metallic spacers to rotate and 

lead to damage and failure of the main 

drive shaft, and subsequent loss of 

helicopter control. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Emergency AD 

No. 2007–0192–E, dated July 13, 2007 

(EAD 2007–0192–E), to correct an 

unsafe condition for certain serialnumbered Agusta Model A109E, A109S, 

and A109LUH helicopters with lower 

semichannel assemblies, P/N 109–0641– 

10–213 or 109–0642–01–171, installed. 

EASA advises that some cases of 

interference between the metallic 

spacer, P/N 109–0642–01–195, and the 

main drive shaft, P/N 109–0415–06– 

103, have been detected on the Model 

A109LUH helicopter, a military version 

of the Model A109 helicopter that is not 

type certificated in the U.S., and that 

this interference has damaged the main 

drive shaft. EASA advises that this 

condition, if not corrected, could lead to 

failure of the main drive shaft ‘‘with 

significant effects on the safety of the 

helicopter.’’ 

Comments 

We gave the public the opportunity to 

participate in developing this AD, but 

we received no comments on the NPRM 

(77 FR 30234, May 22, 2012). 

FAA’s Determination 

These helicopters have been approved 

by the aviation authority of Italy and are 

approved for operation in the United 

States. Pursuant to our bilateral 

agreement with Italy, 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 

This AD differs from the EASA AD as 

follows: 

• This AD is not applicable to 

A109LUH model helicopters because 

they are not type certificated for use in 

the United States; 

• This AD does not require 

compliance ‘‘not later than September 

30, 2007’’ because that date has passed; 

• This AD uses the term ‘‘hours timein-service’’ rather than ‘‘flight hours’’ 

when referring to compliance times; and 

• This AD does not contain the steps 

necessary to install the main drive shaft. 

Related Service Information 

Agusta has issued Mandatory Alert 

Bollettino Tecnico No. 109EP–79, dated 

July 12, 2007 (BT 109EP–79), which 

applies to certain S/Ns of the model 

A109E helicopter, and Mandatory Alert 

Bollettino Tecnico No. 109S–15, dated 

July 12, 2007 (BT 109S–15), which 

applies to certain S/Ns of the model 

A109S helicopter. Both BT 109EP–79 

and BT 109S–15 specify performing an 

inspection on the left side and right side 

lower semichannel assemblies to 

determine if metallic spacers are 

installed. If the metallic spacers are 

installed, BT 109EP–79 and BT 109S–15 

specify inspecting the metallic spacers 

for correct installation, inspecting the 

gaskets for correct seating, modifying 

the semichannel assemblies by 

installing missing rivets, and inspecting 

the main drive shaft for damage if the 

metallic spacers are installed without 

rivets. 

Costs of Compliance 

We estimate that this AD will affect 

about 90 helicopters of U.S. registry. We 

also estimate an average labor rate of 

$85 per work hour. Based on these 

assessments, we calculate the following 

costs: 

• Inspecting the lower semichannel 

assembly for metallic spacers will take 

about 15 minutes for a labor cost of $21 

per helicopter. No parts will be needed, 

so the total cost for the 90-helicopter 

fleet will be $1,890. 

• Inspecting for missing rivets will 

take about three work-hours for a total 

labor cost of $255 per helicopter. Parts 

will cost $10, increasing the perhelicopter cost to $265. 

• Removing, inspecting for damage, 

and reinstalling the main drive shaft 

will take four work-hours for a labor 

cost of $340. No parts will be required. 

• Replacing the main drive shaft. This 

task also will take four work-hours, so 

that labor costs will again total $340. 

Parts will cost $20,824 for a total perhelicopter cost of $21,164. 

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 


emcdonald on DSK67QTVN1PROD with 
73908 Federal Register / Vol. 77, No. 239 / Wednesday, December 12, 2012 / Rules and Regulations 

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): 

2012–23–02 Agusta S.p.A.: Amendment 39– 

17258; Docket No. FAA–2012–0501; 

Directorate Identifier 2009–SW–083–AD. 

(a) Applicability 

This AD applies to Model A109E 

helicopters, up to and including serial 

number (S/N) 11694, except 11633 and 

11634; and Model A109S helicopters, up to 

and including S/N 22034, except S/N 22026 

and 22033; with lower semichannel 

assemblies, part number (P/N) 109–0641–10– 

213 or 109–0642–01–171, installed; 

certificated in any category. 

Note to paragraph (a) of this AD: The 

lower semichannel assemblies are subcomponents of the forward firewall assembly. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

missing spacer rivets, which could allow the 

metallic spacers to rotate and lead to damage 

and failure of the main drive shaft, and 

subsequent loss of control of the helicopter. 

(c) Effective Date 

This AD becomes effective January 16, 

2013. 

(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 50 hours time-in-service: 

(1) Inspect the left-side and right-side 

lower semichannel assemblies by referring to 

Figures 1 and 2, and in accordance with 

Paragraph 3. of the Compliance Instructions 

in the Agusta Bollettino Tecnico (BT) No. 

109EP–79 for the Model A109E helicopter, or 

BT No. 109S–15 for the Model A109S 

helicopter, both dated July 12, 2007, to 

determine if metallic spacers, P/N 109–0642– 

01–195, are installed. If metallic spacers are 

not installed, no further actions are required. 

(2) For each semichannel assembly with a 

metallic spacer, remove the semichannel 

assembly from the helicopter firewall and 

note whether it is the left-side or right-side 

semichannel assembly. 

(3) Inspect each removed semichannel 

assembly and determine whether there is a 

fixing rivet, P/N MS20427M3–5, 

MS20426T3–5, or A298A04TW02, installed 

that holds the spacer to the lower 

semichannel assembly and whether the 

gasket is properly seated. 

(4) For each semichannel assembly without 

a fixing rivet on each side of the lower 

semichannel assembly or those where the 

gasket is improperly seated, separate the 

lower semichannel from the upper 

semichannel, noting the orientation of each 

spacer and gasket. Modify the lower 

semichannel assembly by installing a fixing 

rivet on each side of the lower semichannel 

assembly, and reattaching the lower and 

upper semichannel assemblies in accordance 

with paragraphs 4.2 through 4.7 of the 

appropriate BT for your model helicopter. 

Paragraph 4.2 of the BT states ‘‘remove the 

fixing rivets’’; this AD changes that provision 

to ‘‘remove the screws, P/N MS27039–08– 

05.’’ 

(5) Inspect each main drive shaft for a nick, 

a scratch, or other damage in the 

semichannel area. If a nick, a scratch, or 

other damage is found that exceeds those 

allowable damage tolerances in the 

maintenance manual, replace the main drive 

shaft with an airworthy main drive shaft. 

(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, Safety Management Group, 

Rotorcraft Directorate, FAA, 2601 Meacham 

Blvd., Fort Worth, Texas 76137; telephone 

(817) 222–5110; email jim.grigg@faa.gov. 

(2) For operations conducted under a 14 

CFR part 119 operating certificate or under 

14 CFR part 91, subpart K, we suggest that 

you notify your principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office or 

certificate holding district office, before 

operating any aircraft complying with this 

AD through an AMOC. 

(g) Additional Information 

The subject of this AD is addressed in the 

European Aviation Safety Agency Emergency 

AD No. 2007–0192–E, dated July 13, 2007 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 7100, powerplant system. 

(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) Agusta Bollettino Tecnico No. 109EP– 

79, dated July 12, 2007. 

(ii) Agusta Bollettino Tecnico No. 109S–15, 

dated July 12, 2007. 

(3) For Agusta S.p.A. service information 

identified in this AD, contact Agusta 

Westland, Customer Support & Services, Via 

Per Tornavento 15, 21019 Somma Lombardo 

(VA) Italy, ATTN: Giovanni Cecchelli; 

telephone 39–0331–711133; fax 39 0331 

711180; or at http:// 

www.agustawestland.com/technicalbullettins. 

(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 November 

6, 2012. 

Kim Smith, 

Directorate Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–28432 Filed 12–11–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0678; Directorate 

Identifier 2011–NM–285–AD; Amendment 

39–17280; AD 2012–24–10] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 


emcdonald on DSK67QTVN1PROD with