36134 Federal Register / Vol. 77, No. 117 / Monday, June 18, 2012 / Rules and Regulations 

(h) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Chicago Aircraft 

Certification Office, FAA, may approve 

AMOCs for this AD. Send your proposal to: 

Gregory J. Michalik, Enstrom Program 

Manager, FAA, Chicago Aircraft Certification 

Office, 2300 East Devon Avenue, Room 107, 

Des Plaines, Illinois, 60018; telephone (847) 

294–7135; fax (847) 294–7834; email: 

gregory.michalik@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. 

(i) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6710: Main Rotor Control. 

(j) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the following service information 

under 5 U.S.C. 552(a) and 1 CFR part 51. 

(2) You must use the following service 

information to do the actions required by this 

AD, unless the AD specifies otherwise. 

(3) The following service information was 

approved for IBR on July 3, 2012. 

(i) Enstrom Service Directive Bulletin No. 

0110, Revision 4, dated January 23, 2012, for 

Model F–28C, F–28C–2, F–28F, 280C, 280F, 

and 280FX helicopters. 

(4) The following service information was 

approved for IBR on January 23, 2012 (77 FR 

729, January 6, 2012). 

(i) Enstrom Service Directive Bulletin No. 

T–039, Revision 3, dated July 6, 2011, for 

Model TH–28, 480, and 480B helicopters. 

(5) For service information identified in 

this AD, contact Enstrom Helicopter 

Corporation, 2209 22nd St., Menominee, 

Michigan, 49858–0490; telephone: 906–863– 

1200; email: customerservice@

enstromhelicopter.com; Web site: http://

www.enstromhelicopter.com/enstrom_new/ 

enstrom_support_tec.html. 

(6) You may review a copy of the 

referenced service information at the FAA, 

Office of the Regional Counsel, Southwest 

Region, 2601 Meacham Blvd., Room 663, Fort 

Worth, Texas 76137 or 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/code_of_federal_regulations/ibr_

locations.html. 

Issued in Fort Worth, Texas, on May 17, 

2012. 

Kim Smith, 

Manager, Rotorcraft Directorate, Aircraft 

Certification Service. 

[FR Doc. 2012–14634 Filed 6–15–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–1254; Directorate 

Identifier 2010–NM–178–AD; Amendment 

39–17083; AD 2012–12–04] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) for 

certain The Boeing Company Model 

737–300, –400, and –500 series 

airplanes. That AD currently requires 

repetitive external detailed inspections 

or non-destructive inspections to detect 

cracks in the fuselage skin along the 

chem-mill steps at stringers S–1 and S– 

2R, between station (STA) 400 and STA 

460, and repair if necessary. This new 

AD adds inspections for cracking in 

additional fuselage skin locations, and 

repair if necessary. This new AD also 

reduces the inspection thresholds and 

repetitive intervals for certain airplanes. 

This AD was prompted by reports of 

additional crack findings of the fuselage 

skin at the chem-mill steps. We are 

issuing this AD to detect and correct 

fatigue cracking of the fuselage skin 

panels at the chem-mill steps, which 

could result in sudden fracture and 

failure of the fuselage skin panels, and 

consequent rapid decompression of the 

airplane. 

DATES: This AD is effective July 23, 

2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of July 23, 2012. 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, Washington 98124– 

2207; telephone 206–544–5000, 

extension 1; fax 206–766–5680; Internet 

https://www.myboeingfleet.com. You 

may review copies of the referenced 

service information at the FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue SW., Renton, Washington. 

For information on the availability of 

this material at the FAA, call 425–227– 

1221. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; 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: 

Wayne Lockett, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; phone: 425– 

917–6447; fax: 425–917–6590; email: 

wayne.lockett@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2008–19–03, 

Amendment 39–15670 (73 FR 56958, 

October 1, 2008). That AD applies to the 

specified products. The NPRM 

published in the Federal Register on 

November 28, 2011 (76 FR 72853). That 

NPRM proposed to continue to require 

repetitive external detailed inspections 

or non-destructive inspections to detect 

cracks in the fuselage skin along the 

chem-mill steps at stringers S–1 and S– 

2R, between station (STA) 400 and STA 

460, and repair if necessary. That NPRM 

also proposed to add inspections for 

cracking in additional fuselage skin 

locations, and repair if necessary. That 

NPRM also proposed to reduce the 

inspection thresholds and repetitive 

intervals for certain airplanes. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal (76 FR 72853, 

November 28, 2011) and the FAA’s 

response to each comment. 

Support for the NPRM (76 FR 72853, 

November 28, 2011) 

The National Transportation Board 

supports the NPRM (76 FR 72853, 

November 28, 2011). 

Request To Revise Paragraph (j) of the 

NPRM (76 FR 72853, November 28, 

2011) 

Boeing asked that we include Boeing 

Alert Service Bulletin 737–53A1293, 

Revision 1, dated July 7, 2010, in the 

exception to the service bulletin 


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Federal Register / Vol. 77, No. 117 / Monday, June 18, 2012 / Rules and Regulations 36135 

specified in paragraph (j) of the NPRM 

(76 FR 72853, November 28, 2011). 

(Paragraph (j) of the NPRM is identified 

as paragraph (j)(1) in this final rule.) 

Boeing stated that the compliance times 

in paragraph 1.E. ‘‘Compliance’’ of 

Boeing Service Bulletin 737–53A1293, 

Revision 2, dated August 10, 2011, are 

based on the release date of Boeing Alert 

Service Bulletin 737–53A1293, Revision 

1, dated July 7, 2010. Boeing added that 

paragraph (j) of the NPRM should be 

changed to reference Boeing Alert 

Service Bulletin 737–53A1293, Revision 

1, dated July 7, 2010. 

We agree with the commenter’s 

request for the reason provided. We 

have changed paragraph (j)(1) of this AD 

accordingly. 

Request To Clarify the Language in 

Paragraph (k) of the NPRM (76 FR 

72853, November 28, 2011) 

Boeing asked that the language 

specified in paragraph (k) of the NPRM 

(76 FR 72853, November 28, 2011) be 

clarified. (Paragraph (k) of the NPRM is 

identified as paragraph (j)(2) in this final 

rule.) Boeing stated that the intent of 

paragraph (k) of the NPRM is ‘‘to specify 

an exception to the compliance time for 

accomplishing the next service bulletin 

inspection, being the effective date of 

the AD, for the condition addressed by 

the paragraph.’’ Boeing added that the 

language does not clearly describe that 

it is an exception to the compliance 

time; rather, it could be interpreted as 

an exception to the condition. 

We agree to provide clarification. 

Paragraph (j)(2) of this AD is an 

exception to the conditions, and is 

provided to establish a date from which 

to determine if an inspection has been 

previously accomplished. Therefore, we 

have made no change to the AD in this 

regard. 

Change to Final Rule 

This final rule has been changed to 

include an optional modification of the 

chem-milled steps at any location 

identified in Boeing Service Bulletin 

737–53A1293, Revision 2, dated August 

10, 2011, which would eliminate the 

need for the repetitive inspections 

required by paragraph (g) of this AD. We 

have determined that we can better 

ensure long-term continued operational 

safety by including this modification. 

Therefore, we have added a new 

paragraph (i) to this AD to include this 

modification, and reidentified 

subsequent paragraphs accordingly. In 

addition, we have indicated in the Costs 

of Compliance section of this AD that 

we do not have data regarding the cost 

of the optional terminating action. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting the 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 (76 FR 

72853, November 28, 2011) for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (76 FR 72853, 

November 28, 2011). 

Interim Action 

We consider this AD interim action. If 

final action is identified later, we might 

consider further rulemaking then. 

Costs of Compliance 

We estimate that this AD affects 596 

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 

Inspections (required actions in 

AD 2008–19–03, Amendment 39–15670 (73 FR 

56958, October 1, 2008).

5 work-hours × $85 per hour = 

$425 per inspection cycle.

N/A $425 per inspection cycle ....... $253,300 per inspection cycle. 

New inspections ...................... Between 7 and 15 work-hours, 

depending on airplane configuration = between $595 

and $1,275 per inspection 

cycle.

N/A Between $595 and $1,275 per 

inspection cycle.

Between $354,620 and 

$759,900 per inspection 

cycle. 

We have received no definitive data 

that would enable us to provide a cost 

estimate for the on-condition actions or 

the optional terminating action 

specified in this AD. 

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. 


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36136 Federal Register / Vol. 77, No. 117 / Monday, June 18, 2012 / Rules and Regulations 

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) 

2008–19–03, Amendment 39–15670 (73 

FR 56958, October 1, 2008), and adding 

the following new AD: 

2012–12–04 The Boeing Company: 

Amendment 39–17083; Docket No. 

FAA–2011–1254; Directorate Identifier 

2010–NM–178–AD. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective July 23, 2012. 

(b) Affected ADs 

This AD supersedes AD 2008–19–03, 

Amendment 39–15670 (73 FR 56958, October 

1, 2008). 

(c) Applicability 

This AD applies to The Boeing Company 

Model 737–300, –400, and –500 series 

airplanes, certificated in any category; as 

identified in Boeing Service Bulletin 737– 

53A1293, Revision 2, dated August 10, 2011. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by reports of 

additional crack findings of the fuselage skin 

at the chem-mill steps. We are issuing this 

AD to detect and correct fatigue cracking of 

the fuselage skin panels at the chem-mill 

steps, which could result in sudden fracture 

and failure of the fuselage skin panels, and 

consequent rapid decompression of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Repetitive Inspections 

At the applicable times specified in 

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

Service Bulletin 737–53A1293, Revision 2, 

dated August 10, 2011, except as provided by 

paragraphs (j)(1) and (j)(2) of this AD: Do 

both a detailed inspection and a 

nondestructive inspection (NDI) (medium 

frequency eddy current, magneto optical 

imaging, C-scan, or ultrasonic phased array) 

to detect cracks in the fuselage skin along the 

chem-mill steps at stringers S–1 and S–2R, 

between station (STA) 400 and STA 460, in 

accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 737– 

53A1293, Revision 2, dated August 10, 2011. 

Repeat the applicable inspections thereafter 

at intervals not to exceed those specified in 

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

Service Bulletin 737–53A1293, Revision 2, 

dated August 10, 2011. 

(h) Repair 

(1) If any crack is found during any 

inspection required by paragraph (g) of this 

AD, before further flight, repair in accordance 

with the Accomplishment Instructions of 

Boeing Service Bulletin 737–53A1293, 

Revision 2, dated August 10, 2011; except as 

provided by paragraph (h)(2) of this AD. 

Installation of a repair that meets the 

conditions specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Service Bulletin 

737–53A1293, Revision 2, dated August 10, 

2011, terminates the repetitive inspections 

required by paragraph (g) of this AD for the 

repaired area only. 

(2) If any crack is found during any 

inspection required by paragraph (g) of this 

AD and Boeing Service Bulletin 737– 

53A1293, Revision 2, dated August 10, 2011, 

specifies to contact Boeing for repair: Before 

further flight, repair using a method 

approved in accordance with the procedures 

specified in paragraph (l) of this AD. 

(i) Optional Modification 

Accomplishing a modification of the chemmilled steps at any location identified in 

Boeing Service Bulletin 737–53A1293, 

Revision 2, dated August 10, 2011, using a 

method approved in accordance with the 

procedures specified in paragraph (l)(1) of 

this AD, terminates the repetitive inspections 

required by paragraph (g) of this AD for the 

modified area only. 

(j) Exceptions to Service Bulletin 

(1) Where Boeing Service Bulletin 737– 

53A1293, Revision 2, dated August 10, 2011, 

specifies a compliance time relative to the 

date of Boeing Alert Service Bulletin 737– 

53A1293, Revision 1, dated July 7, 2010, this 

AD requires compliance within the specified 

compliance time after the effective date of 

this AD. 

(2) Where the Condition column of 

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

Service Bulletin 737–53A1293, Revision 2, 

dated August 10, 2011, specifies a condition 

based on whether an airplane has or has not 

been inspected, this AD bases the condition 

on whether an airplane has or has not been 

inspected as of the effective date of this AD. 

(3) The post-repair inspection specified in 

Tables 4 and 6 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Service Bulletin 

737–53A1293, Revision 2, August 10, 2011, 

is not required by this AD. 

Note 1 to paragraph (j)(3) of this AD: The 

damage tolerance inspections specified in 

Tables 4 and 6 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Service Bulletin 

737–53A1293, Revision 2, August 10, 2011, 

may be used in support of compliance with 

section 121.1109(c)(2) or 129.109(c)(2) of the 

Federal Aviation Regulations (14 CFR 

121.1109(c)(2) or 14 CFR 129.109(c)(2)). 

(k) Credit for Previous Actions 

This paragraph provides credit for the 

actions required by paragraphs (g), (h), and 

(i) of this AD, if those actions were performed 

before the effective date of this AD using 

Boeing Alert Service Bulletin 737–53A1293, 

Revision 1, dated July 7, 2010. 

(l) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle 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. 

Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@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 ODA that 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. 

(4) AMOCs approved for AD 2008–19–03, 

Amendment 39–15670 (73 FR 56958, October 

1, 2008), are approved as AMOCs for the 

corresponding requirements in this AD. 

(m) Related Information 

For more information about this AD, 

contact Wayne Lockett, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; phone: 425–917–6447; fax: 425–917– 

6590; email: wayne.lockett@faa.gov. 

(n) Material Incorporated by Reference 

(1) You must use the following service 

information to do the actions required by this 

AD, unless the AD specifies otherwise. The 

Director of the Federal Register approved the 

incorporation by reference (IBR) of the 

following service information under 5 U.S.C. 

552(a) and 1 CFR part 51: 

(i) Boeing Service Bulletin 737–53A1293, 

Revision 2, dated August 10, 2011. 

(2) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, Washington 98124–2207; telephone 

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

5680; Internet https:// 

www.myboeingfleet.com. 

(3) You may review copies of the 

referenced service information at the FAA, 

Transport Airplane Directorate, 1601 Lind 

Avenue SW., Renton, Washington. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

(4) You may also review copies of the 

service information that is incorporated by 


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Federal Register / Vol. 77, No. 117 / Monday, June 18, 2012 / Rules and Regulations 36137 

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/ibr_locations.html. 

Issued in Renton, Washington, on May 31, 

2012. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–14377 Filed 6–15–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0600; Directorate 

Identifier 2012–SW–017–AD; Amendment 

39–17076; AD 2012–11–12] 

RIN 2120–AA64 

Airworthiness Directives; AGUSTA 

S.p.A. Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for Agusta 

S.p.A. (Agusta) Model AW139 

helicopters to determine if the hardware 

that attaches the upper end of collective 

control rod C2 to torque tube C3 is 

properly installed. This AD is prompted 

by the discovery of an incorrectlyattached collective control rod. These 

actions are intended to prevent 

separation of the collective control rod 

from the torque tube, loss of control of 

the collective pitch, and subsequent loss 

of control of the helicopter. 

DATES: This AD becomes effective July 

3, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of July 3, 2012. 

We must receive comments on this 

AD by August 17, 2012. 

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 AD, the 

economic evaluation, any comments 

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 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.agusta

westland.com/technical-bullettins. 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: 

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. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not provide you with notice and 

an opportunity to provide your 

comments prior to it becoming effective. 

However, 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 resulted from 

adopting this AD. The most helpful 

comments reference a specific portion of 

the AD, 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 them 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 

rulemaking during the comment period. 

We will consider all the comments we 

receive and may conduct additional 

rulemaking based on those comments. 

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. 2011– 

0226–E, dated December 2, 2011 (EASA 

AD 2011–0226–E), to correct an unsafe 

condition for the Agusta AW139 

helicopters. EASA advises that an 

occurrence of incorrect installation of a 

collective control rod has been reported. 

This improper installation was 

identified on an in-service helicopter 

during the first annual inspection. 

The subsequent investigation by the 

manufacturer led it to conclude that this 

discrepancy could affect other 

helicopters because the production 

quality control procedures did not 

require recording the applied torque on 

the bolt attaching the collective control 

rod to the torque tube. To address this 

unsafe condition, AgustaWestland 

issued Bollettino Tecnico (BT) No. 139– 

275, dated December 1, 2011, (BT 139– 

275) and EASA issued AD 2011–0226– 

E to require an inspection of the 

attaching point of the flight control rod 

to the torque tube and if improperly 

installed, reinstalling the parts. 

This condition, if not detected and 

corrected, could lead to in-flight 

separation of the collective control rod 

from the torque tube, loss of control of 

the collective pitch, and subsequent loss 

of control of the helicopter. 

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, the 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 the EASA and determined 

the unsafe condition is likely to exist or 

develop on other helicopters of the same 

type design. 

Related Service Information 

We reviewed BT 139–275, which 

contains procedures to inspect for the 

proper installation of control rod C2 in 

the roof area and to ensure that the 

attaching hardware that connects the 

control rod to the torque tube is 

properly installed. 

AD Requirements 

This AD requires: 

• Within 5 hours time-in-service or 7 

days, whichever occurs earlier, visually 

inspecting the connection between 


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