Federal Register / Vol. 76, No. 193 / Wednesday, October 5, 2011 / Rules and Regulations 61559 

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 street address for 

the Docket Operations office (phone: 

(800) 647–5527) is provided in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

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 AD: 

2011–19–02 Dowty Propellers (formerly 

Dowty Aerospace; Dowty Rotol Limited; 

and Dowty Rotol): Amendment 39– 

16807. Docket No. FAA–2011–0735; 

Directorate Identifier 2011–NE–01–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective November 9, 2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Dowty Propellers 

type R212/4–30–4/22 propeller assemblies 

with hub and driving center assembly part 

number (P/N) 601022105, 601022211, 

601022294, 601021426, 601021858, or 

601021859 installed, and type R251/4–30–4/ 

49 propeller assemblies with hub and driving 

center assembly P/N 660207202 or P/N 

660207203 installed. 

Reason 

(d) This AD results from mandatory 

continuing airworthiness information (MCAI) 

issued by an aviation authority of another 

country to identify and correct an unsafe 

condition on an aviation product. We are 

issuing this AD to prevent propeller hub 

failure due to cracks in the hub, which could 

result in damage to the airplane. 

Actions and Compliance 

(e) Unless already done, do the following: 

(1) Within 500 flight hours after the 

effective date of this AD, and thereafter at 

intervals not exceeding 500 flight hours, 

inspect the buttress threads in the propeller 

hub and driving center assembly for cracks. 

(2) Use paragraphs 2.A.(1) through 

2.A.(4)(a) of Accomplishment Instructions of 

Dowty Propellers Alert Service Bulletin No. 

61–1043, Revision 7, dated March 1, 2011, 

and NDT Technique NDT 175U (Appendix A 

of Dowty Propellers Alert Service Bulletin 

No. 61–1043, Revision 7, dated March 1, 

2011), to do the inspection. 

(3) If a crack is found, remove the propeller 

assembly from service before further flight. 

(4) After the effective date of this AD, do 

not install this propeller on any airplane 

unless the propeller hub and driving center 

has passed the inspections required by this 

AD. 

FAA AD Differences 

(f) This AD differs from the service 

information as follows: 

(1) Although the service bulletin tells you 

to return the affected parts to the 

manufacturer, this AD does not require that 

action. 

(2) Although the service bulletin tells you 

to submit information to the manufacturer, 

this AD does not require that action. 

Alternative Methods of Compliance 

(AMOCs) 

(g) The Manager, Boston Aircraft 

Certification Office, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

Related Information 

(h) Refer to MCAI European Aviation 

Safety Agency AD 2011–0012, dated January 

20, 2011, for related information. 

(i) Contact Michael Schwetz, Aerospace 

Engineer, Boston Aircraft Certification Office, 

FAA, Engine & Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; phone: 781–238–7761; fax: 781–238– 

7170, e-mail: michael.schwetz@faa.gov for 

more information about this AD. 

Material Incorporated by Reference 

(j) You must use Dowty Propellers Alert 

Service Bulletin No. 61–1043, Revision 7, 

dated March 1, 2011, to do the actions 

required by this AD, unless the AD specifies 

otherwise. 

(k) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(l) For service information identified in 

this AD, contact Dowty Propellers, 114 

Powers Court, Sterling, VA 20166, phone: 

703–421–4434; fax: 703–450–0087. 

(m) You may review copies at the FAA, 

New England Region, 12 New England 

Executive Park, Burlington, MA; 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/cfr/ibrlocations.html. 

Issued in Burlington, Massachusetts, on 

September 7, 2011. 

Peter A. White, 

Manager, Engine & Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–25653 Filed 10–4–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0392; Directorate 

Identifier 2011–NE–12–AD; Amendment 39– 

16808; AD 2011–19–03] 

RIN 2120–AA64 

Airworthiness Directives; General 

Electric Company (GE) CT7–8, CT7–8A, 

CT7–8A1, CT7–8E, and CT7–8F5 

Turboshaft Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This AD was 

prompted by four reports of 

unrecoverable engine stalls, during 

hover in a left-roll attitude. This AD 

requires the installation of an accessory 

gearbox (AGB) axis-A oil slinger nut to 

the axis-A shaft assembly. We are 

issuing this AD to prevent an 

unrecoverable engine stall, leading to a 

helicopter forced landing or accident. 

DATES: This AD is effective November 9, 

2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of November 9, 2011. 

ADDRESSES: For service information 

identified in this AD, contact GE– 

Aviation, M/D Rm. 285, One Neumann 

Way, Cincinnati, OH 45215; phone: 

513–552–3272; e-mail: geaeaoc@ge.com. 

You may review copies of the 

referenced service information at the 

FAA, Engine & Propeller Directorate, 12 

New England Executive Park, 

Burlington, MA. For information on the 

availability of this material at the FAA, 

call 781–238–7125. 

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: 

Walter Meibaum, Aerospace Engineer, 


jlentini on DSK4TPTVN1PROD with RULES
61560 Federal Register / Vol. 76, No. 193 / Wednesday, October 5, 2011 / Rules and Regulations 

Engine & Propeller Directorate, FAA, 12 

New England Executive Park, 

Burlington, MA 01803; phone: 781– 

238–7119; fax: 781–238–7199; e-mail: 

walter.meibaum@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We received four reports of GE CT7– 

8 series turboshaft helicopter engines 

experiencing unrecoverable engine 

stalls, during hover in a left-roll 

attitude. Investigation revealed that 

during a prolonged left roll, excessive 

return oil from the AGB may return to 

the A-sump and exceed the sump’s 

scavenging capability. The sump then 

floods, leading to over-heated oil, which 

preheats the air entering the engine’s 

compressor. This preheated air causes 

inlet thermal distortion. This condition, 

if not corrected, could result in an 

unrecoverable engine stall, leading to a 

helicopter forced landing or accident. 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM published in the Federal 

Register on May 2, 2011 (76 FR 24407). 

That NPRM proposed to require the 

installation of an AGB axis-A oil slinger 

nut to the axis-A shaft assembly. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM 

published in the Federal Register on 

May 2, 2011 (76 FR 24407). 

Since we issued the NPRM published 

in the Federal Register on May 2, 2011 

(76 FR 24407), GE issued a revision to 

the service bulletin we are incorporating 

by reference in this AD. The revision 

includes new information in the 

procedure required to torque the oil 

slinger nut. This AD incorporates by 

reference, GE Aircraft Engines CT7–8 

Turboshaft Engine Service Bulletin No. 

CT7–8 S/B 72–0033, Revision 1, dated 

April 28, 2011. 

Also since we issued the NPRM 

published in the Federal Register on 

May 2, 2011 (76 FR 24407), we 

discovered that in the applicability 

paragraph, we inadvertently omitted 

engine serial number 953071. We 

corrected that omission in paragraph (c) 

(4) by changing ‘‘CT7–8E, engine S/Ns 

953068 and below, and S/Ns 953070 

and 953072’’ to ‘‘CT7–8E, engine S/Ns 

953068 and below, and S/Ns 953070 

through 953072’’. 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed except for minor editorial 

changes. We have determined that these 

minor changes are consistent with the 

intent that was proposed in the NPRM 

published in the Federal Register on 

May 2, 2011 (76 FR 24407) for 

correcting the unsafe condition. 

Costs of Compliance 

We estimate that this AD will affect 

80 engines installed on helicopters of 

U.S. registry. We also estimate that it 

will take about one work-hour per 

engine to perform the actions required 

by this AD, and that the average labor 

rate is $85 per work-hour. Required 

parts will cost about $700 per engine. 

Based on these figures, we estimate the 

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

be $62,800. 

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 

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: 

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): 

2011–19–03 General Electric Company: 

Amendment 39–16808; Docket No. 

FAA–2011–0392; Directorate Identifier 

2011–NE–12–AD. 

Effective Date 

(a) This AD is effective November 9, 2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to the following 

General Electric Company (GE) turboshaft 

engines: 

(1) CT7–8, all engine serial numbers (S/ 

Ns). 

(2) CT7–8A, engine S/Ns 947565 and 

below. 

(3) CT7–8A1, engine S/Ns 530017 and 

below. 

(4) CT7–8E, engine S/Ns 953068 and 

below, and S/Ns 953070 through 953072. 

(5) CT7–8F5, engine S/Ns 731005 and 

below, and S/Ns 731007, 731008, 817021, 

and 817022. 

Unsafe Condition 

(d) This AD was prompted by four reports 

of unrecoverable engine stalls, during hover 

in a left-roll attitude. We are issuing this AD 

to prevent an unrecoverable engine stall, 

leading to a helicopter forced landing or 

accident. 

Compliance 

(e) Comply with this AD at the next engine 

shop visit, the next 1,500-hour helicopter 

inspection, or before operation after next 

engine installation, whichever occurs first. 

Installation of Accessory Gearbox (AGB) 

Axis-A Oil Slinger Nut 

(f) Install the AGB axis-A oil slinger nut to 

the axis-A shaft assembly. Use 

Accomplishment Instructions, paragraphs 

3.A. through 3.C. of GE Aircraft Engines 

CT7–8 Turboshaft Engine Service Bulletin 

No. CT7–8 S/B 72–0033, Revision 1, dated 

April 28, 2011, to do the installation. 


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Federal Register / Vol. 76, No. 193 / Wednesday, October 5, 2011 / Rules and Regulations 61561 

Previous Credit 

(g) An oil slinger nut installation 

performed before the effective date of this AD 

using GE Aircraft Engines CT7–8 Turboshaft 

Engine Service Bulletin No. CT7–8 S/B 72– 

0033, dated February 11, 2011, satisfies the 

installation requirements of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(h) The Manager, Engine Certification 

Office, FAA, has the authority to approve 

AMOCs for this AD, if requested using the 

procedures found in 14 CFR 39.19. 

Related Information 

(i) For more information about this AD, 

contact Walter Meibaum, Aerospace 

Engineer, Engine & Propeller Directorate, 

FAA, 12 New England Executive Park, 

Burlington, MA 01803; phone: 781–238– 

7119; fax: 781–238–7199; e-mail: 

walter.meibaum@faa.gov. 

Material Incorporated by Reference 

(j) 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 of the 

following service information on the date 

specified: 

(1) GE Aircraft Engines CT7–8 Turboshaft 

Engine Service Bulletin No. CT7–8 S/B 72– 

0033, Revision 1, dated April 28, 2011, 

approved for IBR November 9, 2011. 

(2) For service information identified in 

this AD, contact GE–Aviation, M/D Rm. 285, 

One Neumann Way, Cincinnati, OH 45215; 

phone: 513–552–3272; e-mail: 

geaeaoc@ge.com. 

(3) You may review copies of the service 

information at the FAA, Engine & Propeller 

Directorate, 12 New England Executive Park, 

Burlington, MA. For information on the 

availability of this material at the FAA, call 

781–238–7125. 

(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 an NARA facility, call 202–741– 

6030, or go to http://www.archives.gov/ 

federal_register/code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Burlington, Massachusetts, on 

September 8, 2011. 

Peter A. White, 

Manager, Engine & Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–25654 Filed 10–4–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–1313; Directorate 

Identifier 2010–NM–158–AD; Amendment 

39–16823; AD 2011–20–10] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 737–600, –700, –700C, 

–800, –900, and –900ER Series 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This AD requires 

inspecting to determine the clearance 

and any wire bundle damage between 

wire bundle W443 and the left forward 

rudder quadrant, followed by adjusting 

the minimum clearance between the 

wire bundle and the left forward rudder 

quadrant, and repairing any wire bundle 

damage. This AD was prompted by 

reports of contact between wire bundle 

W443 and the left forward rudder 

quadrant. We are issuing this AD to 

detect and correct contact between the 

wire bundle and the left forward rudder 

quadrant. Damage to the wire bundle 

from contact between the wire bundle 

and the left forward rudder quadrant 

could result in uncommanded stabilizer 

trim and autopilot disconnects due to 

shorted wires, potentially affecting the 

capability of the flightcrew during high 

work load and consequently reducing 

control of the airplane. Restricted 

movement of the rudder quadrant at full 

right rudder travel would reduce 

controllability of the airplane. 

DATES: This AD is effective November 9, 

2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of November 9, 2011. 

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; e-mail 

me.boecom@boeing.com; 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: 

Dean Thompson, Aerospace Engineer, 

Systems and Equipment Branch, ANM– 

130S, FAA, Seattle Aircraft Certification 

Office, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 917–6409; fax (425) 917–6590. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an airworthiness 

directive (AD) that would apply to the 

specified products. That NPRM was 

published in the Federal Register on 

January 18, 2011 (76 FR 2840). That 

NPRM proposed to require inspecting to 

determine the clearance and any wire 

bundle damage between wire bundle 

W443 and the left forward rudder 

quadrant, followed by adjusting the 

minimum clearance between the wire 

bundle and the left forward rudder 

quadrant, and repairing any wire bundle 

damage. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

have considered the comments received. 

The following presents the comments 

received on the proposal and the FAA’s 

response to each comment. 

Support for the NPRM 

American Airlines, Delta Air Lines, 

and Continental Airlines (CAL) support 

the NPRM (76 FR 2840, January 18, 

2011), and stated that they have been 

inspecting the affected airplanes in 

accordance with the original issue and 

revision 1 of the service information 

cited in the NPRM. 

Request for Boeing To Add Instructions 

for Continued Airworthiness (ICAs) 

CAL requested that the FAA ask 

Boeing to add the appropriate ICAs to 


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