Federal Register / Vol. 77, No. 54 / Tuesday, March 20, 2012 / Rules and Regulations 16137 

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 part 39 of the Federal 

Aviation Regulations (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) 

2012–03–52, Amendment 39–16958 

(77 FR 12179, February 29, 2012) and 

adding the following new AD: 

2012–05–09 Mooney Aviation Company, 

Inc. (Mooney): Amendment 39–16981; 

Docket No. FAA–2012–0275; Directorate 

Identifier 2012–CE–009–AD. 

(a) Effective Date 

This AD is effective March 20, 2012. 

(b) Affected ADs 

This AD supersedes AD 2012–03–52, 

Amendment 39–16958 (77 FR 12179, 

February 29, 2012). 

(c) Applicability 

This AD applies to Mooney Aviation 

Company, Inc. (Mooney) Models M20B, 

M20C, M20D, M20E, M20F, M20G, M20J, 

M20K, M20L, M20M, M20R, M20S, and 

M20TN airplanes, all serial numbers, 

certificated in any category. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 55; Stabilizers. 

(e) Unsafe Condition 

This AD was prompted by a report of an 

incident on a Mooney Model M20TN 

airplane regarding failure of the tail pitch 

trim assembly and the potential for this 

condition to exist on other airplane models, 

which could result in loss of control. We are 

issuing this AD to correct the unsafe 

condition on these products. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection 

Within the next 10 hours time-in-service 

March 20, 2012 (after the effective date of 

this AD), inspect the trim fitting, hinge, and 

filler plate of the tail pitch trim assembly for 

correct positioning and proper attachment; 

and also inspect that the Huck Bolt fasteners 

are properly secured following Mooney 

Aviation Company, Inc. Service Bulletin No. 

M20–313A, dated February 29, 2012. 

(h) Corrective Action 

If during the inspection required in 

paragraph (g) of this AD you find incorrect 

positioning or improper attachment of the 

trim fitting, hinge, and filler plate of the tail 

pitch trim assembly; and/or you find loose or 

improperly installed Huck Bolt fasteners, 

before further flight, repair and correct the 

discrepancies following Mooney Aviation 

Company, Inc. Service Bulletin No. M20– 

314A, dated February 29, 2012. 

(i) Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

(1) This paragraph provides credit for 

inspections required in paragraph (g) of this 

AD if already done before March 20, 2012 

(the effective date of this AD) following 

Mooney Aviation Company, Inc. Service 

Bulletin No. M20–313, dated February 7, 

2012. 

(2) This paragraph provides credit for 

repairs required in paragraph (h) of this AD 

if already done before March 20, 2012 (the 

effective date of this AD) following Mooney 

Aviation Company, Inc. Service Bulletin No. 

M20–314, dated February 10, 2012. 

(j) Special Flight Permit 

Special flight permits are prohibited for 

this AD. 

(k) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Fort Worth 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. 

(l) Related Information 

For more information about this AD, 

contact Andrew McAnaul, Aerospace 

Engineer, ASW–150 (c/o MIDO–43), 10100 

Reunion Place, Suite 650, San Antonio, 

Texas 78216; telephone: (210) 308–3365; 

facsimile: (210) 308–3370; email: 

andrew.mcanaul@faa.gov. 

(m) 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) under 5 

U.S.C. 552(a) and 1 CFR part 51: (i) Mooney 

Aviation Company, Inc. Service Bulletin No. 

M20–313A, dated February 29, 2012; and 

(ii) Mooney Aviation Company, Inc. 

Service Bulletin No. M20–314A, dated 

February 29, 2012. 

(2) For service information identified in 

this AD, contact Mooney Aviation Company, 

Inc., 165 Al Mooney Road North, Kerrville, 

Texas 78028; telephone: (830) 896–6000; 

email: technicalsupport@mooney.com; 

Internet: www.mooney.com. 

(3) 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. 

(4) You may also review copies of the 

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/ibr_locations.html. 

Issued in Kansas City, Missouri, on March 

13, 2012. 

James E. Jackson, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–6521 Filed 3–19–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0454; Directorate 

Identifier 2009–SW–54–AD; Amendment 39– 

16973; AD 2012–05–01] 

RIN 2120–AA64 

Airworthiness Directives; Eurocopter 

France Model Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

Eurocopter France (ECF) Model SA– 

365C, SA–365C1, SA–365C2, SA–365N, 

SA–365N1, AS–365N2, AS 365 N3, and 

SA–366G1 helicopters. This AD was 

prompted by some reports of 

deterioration and two reports of failure 

of Starflex star arm ends. The actions 

are intended to modify the main rotor 

frequency adapters to reduce the 

temperature in the area, to prevent 

failure of the star arm end, severe 

vibration, and subsequent loss of control 

of the helicopter. 

DATES: This AD is effective on April 24, 

2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain documents listed in this AD 

as of April 24, 2012. 

ADDRESSES: For service information 

identified in this AD, contact American 

Eurocopter Corporation, 2701 Forum 

Drive, Grand Prairie, Texas 75053–4005, 

telephone (800) 232–0323, fax (972) 


wreier-aviles on DSK5TPTVN1PROD with RULES
16138 Federal Register / Vol. 77, No. 54 / Tuesday, March 20, 2012 / Rules and Regulations 

641–3710 or at http:// 

www.eurocopter.com. 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. 

Examining the AD Docket: You may 

examine the AD docket on the Internet 

at http://www.regulations.gov or in 

person at the Docket Operations Office 

between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

The AD docket contains this AD, any 

incorporated-by-reference service 

information, the economic evaluation, 

any comments received, and other 

information. The street address for the 

Docket Operations Office (telephone: 

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: Gary 

Roach, ASW–111, Aviation Safety 

Engineer, Rotorcraft Directorate, 

Regulations and Guidance Group, 2601 

Meacham Blvd., Fort Worth, Texas 

76137, telephone (817) 222–5130, fax 

(817) 222–5961, email 

gary.b.roach@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On May 13, 2011, at 76 FR 27954, 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 ECF 

Model SA–365C, SA–365C1, SA–365C2, 

SA–365N, SA–365N1, AS–365N2, AS 

365 N3, and SA–366G1 helicopters, 

certificated in any category. The 

proposed requirements were intended to 

modify the main rotor frequency 

adapters to reduce the temperature in 

the area, to prevent failure of the star 

arm end, severe vibration, and 

subsequent loss of control of the 

helicopter. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Emergency AD 

(EAD) No. 2006–0362–E, dated 

November 30, 2006, to correct an unsafe 

condition for the specified Eurocopter 

model helicopters. EASA advises that 

this EAD is issued following some 

reports of deterioration and two reports 

of failure of Starflex star arm ends. 

EASA states that these deteriorations 

‘‘generated high-amplitude vibrations in 

flight, compelling the pilot to carry out 

a precautionary landing, in each of these 

cases. The failure of the Starflex star 

arm end could make it impossible to 

control the helicopter. These 

deteriorations are due to the strong 

effect of temperature on the strength of 

the bush-to-Starflex star arm end 

attachment.’’ As a result, EASA issued 

its EAD to require modification (MOD 

0762C39) of the frequency adapters and 

the frequency adapter bushes to 

improve the ventilation in the area on 

the star arm end on ‘‘helicopters 

operated in hot climatic conditions and/ 

or tropical and damp atmosphere.’’ 

Comments 

We gave the public an opportunity to 

participate in developing this AD, but 

we did not receive any comments on the 

NPRM. 

FAA’s Determination 

We have reviewed the relevant 

information and determined that an 

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 except for minor editorial and 

formatting changes. These minor 

editorial changes are consistent with the 

intent of the proposals in the NPRM and 

will not increase the economic burden 

on any operator nor increase the scope 

of this AD. 

Differences Between This AD and the 

EASA AD 

This AD differs from the EASA AD as 

follows: 

• We refer to flight hours as hours 

time-in-service. 

• We refer to a check as an inspection 

because it is an action performed by 

maintenance personnel rather than a 

pilot. 

• We omit the phrase ‘‘hot climatic 

conditions and/or in tropical and damp 

atmosphere’’ because it is 

unenforceable. 

Related Service Information 

ECF has issued one Emergency Alert 

Service Bulletin, dated November 23, 

2006, with four different numbers: No. 

62.00.24 is for the civil Model SA–365 

N, AS–365N1, AS–365N2, and AS 365 

N3; No. 62.14 is for the civil Model SA– 

366G1; No. 65.45 is for the Model SA– 

365C, C1, and C2; and No. 62.00.10 is 

for the non-FAA type certificated 

military Model 565 helicopters. The 

actions described in the EASA AD are 

intended to correct the same unsafe 

condition as that identified in the 

service information. 

Costs of Compliance 

We estimate that this AD will affect 

about 37 helicopters of U.S. registry. We 

estimate that operators may incur the 

following costs in order to comply with 

this AD: 

• $1,020 assuming 12 work-hours per 

helicopter to modify the frequency 

adapters and bushes at an average labor 

rate of $85 per work-hour, and 

• $960 per helicopter for required 

parts. 

Based on these figures, we estimate 

the cost of the AD on U.S. operators to 

be $73,260. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. Subtitle VII: 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701: 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

helicopters identified in this rulemaking 

action. 

Regulatory Findings 

This AD will not have federalism 

implications under Executive Order 

13132. This AD will not have a 

substantial direct effect on the States, on 

the relationship between the national 

government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Is not a ‘‘significant rule’’ under 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979), 

(3) Will not affect intrastate aviation 

in Alaska to the extent that it justifies 

making a regulatory distinction; and 

(4) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared an economic evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 


wreier-aviles on DSK5TPTVN1PROD with RULES
Federal Register / Vol. 77, No. 54 / Tuesday, March 20, 2012 / Rules and Regulations 16139 

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): 

2012–05–01 Eurocopter France: 

Amendment 39–16973; Docket No. 

FAA–2011–0454; Directorate Identifier 

2009–SW–54–AD. 

(a) Applicability 

This AD applies to Model SA–365C, SA– 

365C1, SA–365C2, SA–365N, SA–365N1, 

AS–365N2, AS 365 N3, and SA–366G1 

helicopters, certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

deterioration and failure of Starflex star arm 

ends. These deteriorations generated highamplitude vibrations in flight requiring 

precautionary landings. These deteriorations 

are due to the strong effect of temperature on 

the strength of the bush-to-Starflex star arm 

end attachment and require modification of 

the frequency adapters and the frequency 

adapter bushes to improve the ventilation in 

the area on the star arm end. This condition 

could result in failure of the star arm end, 

severe vibration, and subsequent loss of 

control of the helicopter. 

(c) Effective Date 

This AD becomes effective April 24, 2012. 

(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 

(1) For a main rotor head frequency 

adapter, pre MOD 0762C39, within 110 hours 

time-in-service (TIS), remove the main rotor 

blades, modify the frequency adapters and 

bushes, and change the part number of the 

frequency adapter as shown in Figures 1 

through 5 and by following the 

Accomplishment Instructions, paragraph 

2.B.2., of Eurocopter Emergency Alert Service 

Bulletin (EASB) No. 62.00.24 for the Model 

SA–365N, N1, AS–365N2, and AS 365 N3; 

No. 62.14 for the Model SA–366G1; and No. 

65.45 for the Model SA–365C, C1, and C2 

helicopters; all dated November 23, 2006. 

This modification is MOD 0762C39. 

(2) For each main rotor head frequency 

adapter modified per MOD 0762C39, within 

10 hours TIS, unless accomplished 

previously, and thereafter at intervals not to 

exceed 10 hours TIS, inspect to determine 

whether the safety wire is in place on the 

trailing edge of the frequency adapter and 

whether the holes in the frequency adapters 

and the frequency adapter bushes, as shown 

in Figure 5 of the EASB for your model 

helicopter, are blocked. 

(i) If the lockwire is missing from the 

trailing edge of the frequency adapter, before 

further flight, reposition the bush if it has 

turned and install more safety wire. 

(ii) If a hole is blocked, before further 

flight, unblock the hole. 

(3) Before installing a frequency adapter or 

bush, modify the frequency adapter or bush 

and change the part number in accordance 

with paragraph (e)(1) of this AD. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, DOT/FAA Southwest Region, FAA, 

may approve AMOCs for this AD. Send your 

proposal to: Gary Roach, ASW–111, Aviation 

Safety Engineer, Rotorcraft Directorate, 

Regulations and Guidance Group, 2601 

Meacham Blvd., Fort Worth, Texas 76137, 

telephone (817) 222–5130, fax (817) 222– 

5961, email gary.b.roach@faa.gov. 

(2) For operations conducted under a Part 

119 operating certificate or under 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) The Eurocopter EASB contains four 

different EASB numbers; three (Nos. 

62.00.24, 62.14, and 65.45) apply to different 

civil Eurocopter model helicopters; and one 

(No. 62.00.10) only applies to non-FAA typecertificated military Model 565 helicopters 

and is not incorporated by reference. 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. 

(2) The subject of this AD is addressed in 

European Aviation Safety Agency Emergency 

AD No. 2006–0362–E, dated November 30, 

2006. 

(h) Subject 

Joint Aircraft System/Component (JASC) 

Code 5311: Main Rotor Head. 

(i) 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. 

(i) Eurocopter Emergency Alert Service 

Bulletin (EASB) No. 62.00.24 (for the civil 

Model SA–365 N, AS–365N1, AS–365N2, 

and AS 365 N3), Revision 0, dated November 

23, 2006 

(ii) Eurocopter EASB No. 62.14 (for the 

civil Model SA–366G1), Revision 0, dated 

November 23, 2006 

(iii) Eurocopter EASB No. 65.45 (for the 

Model SA–365C, C1, and C2), Revision 0, 

dated November 23, 2006 

Note to paragraph (i)(2): These service 

bulletins were issued together as one 

document along with Eurocopter EASB No. 

62.00.10 (for the non-FAA type certificated 

military Model 565 helicopters), which is not 

incorporated by reference. 

(3) For service information identified in 

this AD, contact American Eurocopter 

Corporation, 2701 Forum Drive, Grand 

Prairie, Texas 75053–4005, telephone (800) 

232–0323, fax (972) 641–3710 or at http:// 

www.eurocopter.com. 

(4) You may review copies at the FAA, 

Office of the Regional Counsel, Southwest 

Region, 2601 Meacham Blvd., Room 663, Fort 

Worth, Texas, 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 February 

24, 2012. 

Lance T. Gant, 

Acting Manger, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–5622 Filed 3–19–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–1095; Directorate 

Identifier 2008–NE–34–AD; Amendment 39– 

16924; AD 2012–02–01] 

RIN 2120–AA64 

Airworthiness Directives; Pratt & 

Whitney (PW) Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for Pratt & 

Whitney (PW) PW2037, PW2037(M), 

and PW2040 turbofan engines with 

certain fan blades with a cutback 

leading edge, installed. This AD was 

prompted by reports from PW that fan 

blade leading edge erosion can result in 

a fan thrust deterioration mode (FTDM) 

condition, a condition that cannot be 

detected by the crew, and that reduces 

the engine’s capability of producing 

required thrust. This AD requires initial 

and repetitive maintenance to the 

leading edge of cutback fan blades or 

applying performance decrements as 

specified in the Airplane Flight Manual. 


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