27684 Federal Register / Vol. 74, No. 111 / Thursday, June 11, 2009 / Rules and Regulations 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0082; Directorate 

Identifier 2008–NE–42–AD; Amendment 39– 

15914; AD 2009–11–04] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

Corporation AE 2100D2, AE 2100D2A, 

AE 2100D3, and AE 2100J Turboprop 

Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for RollsRoyce Corporation (RRC) AE 2100D2, 

AE 2100D2A, AE 2100D3, and AE 2100J 

turboprop engines with certain 

propeller gearbox (PGB) shaft-andcarrier assemblies installed. These 

engines are U.S. type-certificated but as 

of the effective date of this AD are only 

installed on military airplanes. This AD 

requires monitoring a certain population 

of PGB shaft-and-carrier assemblies for 

vibration during flight, and borescopeinspecting the PGB shaft for cracks if 

vibration is experienced. This AD 

would also require removing the 

affected population of PGB shaft-andcarrier assemblies from service and 

installing serviceable PGB shaft-andcarrier assemblies. This AD results from 

a report of a crack found in the forward 

cone of a PGB shaft in an RRC AE 

2100D3 turboprop engine that was 

removed from service due to high 

vibration. We are issuing this AD to 

prevent separation of the propeller from 

the airplane, which could result in 

injury, and damage to the airplane. 

DATES: This AD becomes effective June 

26, 2009. The Director of the Federal 

Register approved the incorporation by 

reference of certain publications listed 

in the regulations as of June 26, 2009. 

We must receive any comments on 

this AD by August 10, 2009. 

ADDRESSES: Use one of the following 

addresses to comment on this AD: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov and follow 

the instructions for sending your 

comments electronically. 

• Mail: U.S. Docket Management 

Facility, Department of Transportation, 

1200 New Jersey Avenue, SE., West 

Building Ground Floor, Room W12–140, 

Washington, DC 20590–0001. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

• Fax: (202) 493–2251. 

FOR FURTHER INFORMATION CONTACT: 

Michael Downs, Aerospace Engineer, 

Chicago Aircraft Certification Office, 

FAA, Small Airplane Directorate, 2300 

E. Devon Ave., Des Plaines, IL 60018; email: michael.downs@faa.gov; 

telephone (847) 294–7870; fax (847) 

294–7834. 

Contact Rolls-Royce Corporation, P.O. 

Box 420, Indianapolis, IN 46206; 

telephone (317) 230–3774; fax (317) 

230–6084; e-mail: 

indy.pubs.services@rolls-royce.com for 

the service information identified in this 

AD. 

SUPPLEMENTARY INFORMATION: In March 

of 2007, the Chicago Aircraft 

Certification Office received a report of 

a crack found in the forward cone of a 

PGB shaft. The PGB shaft was installed 

in an RRC AE 2100D3 turboprop engine 

that was removed from service due to 

high vibration. RRC investigated and 

determined that a certain population of 

PGB shaft-and-carrier assemblies could 

fail due to cracks developing in the 

forward shaft cone. The affected 

population, manufactured before June 

2005, could have a high stress 

concentration in the bottom of a certain 

drilled hole, due to improper surface 

finish. RRC issued alert service bulletins 

to borescope-inspect the affected 

population of PGB shafts for cracks. 

Based on the inspection results, we 

determined that AD action is necessary. 

These engines are U.S. type-certificated, 

but as of the effective date of this AD are 

only installed on military airplanes. 

Failure to inspect the PGB shaft forward 

cone for cracks could result in 

separation of the propeller from the 

airplane, which could result in injury, 

and damage to the airplane. 

Relevant Service Information 

We have reviewed and approved the 

technical contents of RRC Service 

Bulletin (SB) No. AE 2100D2–A–72– 

073, Revision 1, dated February 18, 

2008, RRC SB No. AE 2100D3–A–72– 

256, Revision 1, dated February 18, 

2008, and RRC SB No. AE 2100J–A–72– 

071, Revision 1, dated February 18, 

2008. Those SBs list the affected 

population of PGB shaft-and-carrier 

assemblies by serial number (SN). 

FAA’s Determination and Requirements 

of This AD 

Although no airplanes that are 

registered in the United States use these 

turboprop engines, the possibility exists 

that the engines could be used on 

airplanes that are registered in the 

United States in the future. The unsafe 

condition described previously is likely 

to exist or develop on other engines of 

the same type design. We are issuing 

this AD to prevent separation of the 

propeller from the airplane, which 

could result in injury, and damage to 

the airplane. This AD requires: 

• Monitoring the affected population 

of PGB shaft-and-carrier assemblies for 

vibration during flight; 

• Borescope-inspecting the forward 

cone of the PGB shaft for cracking if 

vibration is experienced; and 

• Removing the affected PGB shaftand-carrier assembly at the next shop 

visit for PGB inspection or repair. 

Replacing the affected PGB shaft-andcarrier assembly with a shaft and carrier 

assembly that is eligible for installation, 

is terminating action for the vibration 

monitoring required by this AD. 

You must use the service information 

described previously to determine SN 

applicability of PGB shaft-and-carrier 

assemblies. 

FAA’s Determination of the Effective 

Date 

Since there are no domestic operators 

of these RRC AE 2100D2, AE 2100D2A, 

AE 2100D3, and AE 2100J turboprop 

engines as of the effective date of this 

AD, notice and opportunity for public 

comment before issuing this AD are 

unnecessary. A situation exists that 

allows the immediate adoption of this 

regulation. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety and 

was not preceded by notice and an 

opportunity for public comment; 

however, we invite you to send us any 

written relevant data, views, or 

arguments regarding this AD. Send your 

comments to an address listed under 

ADDRESSES. Include ‘‘AD Docket No. 

FAA–2009–0082; Directorate Identifier 

2008–NE–42–AD’’ in the subject line of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of the rule that might suggest a 

need to modify it. 

We will post all comments we 

receive, without change, to http:// 

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact with FAA 

personnel concerning this AD. Using the 

search function of the Web site, anyone 

can find and read the comments in any 

of our dockets, including, if provided, 

the name of the individual who sent the 

comment (or signed the comment on 

behalf of an association, business, labor 


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Federal Register / Vol. 74, No. 111 / Thursday, June 11, 2009 / Rules and Regulations 27685 

union, etc.). You may review the DOT’s 

complete Privacy Act Statement in the 

Federal Register published on April 11, 

2000 (65 FR 19477–78). 

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 regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations office (telephone 

(800) 647–5527) is the same as the Mail 

address provided in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

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 the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); and 

3. 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 a summary of the costs 

to comply with this AD and placed it in 

the AD Docket. You may get a copy of 

this summary at the address listed 

under ADDRESSES. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

■ Under the authority delegated to me 

by the Administrator, the Federal 

Aviation Administration 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 adding 

the following new airworthiness 

directive: 

2009–11–04 Rolls-Royce Corporation 

(formerly Allison Engine Company): 

Amendment 39–15914. Docket No. 

FAA–2009–0082; Directorate Identifier 

2008–NE–42–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective June 26, 2009. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Rolls-Royce 

Corporation (RRC) AE 2100D2, AE 2100D2A, 

AE 2100D3, and AE 2100J turboprop engines 

with certain serial number (SN) propeller 

gearbox (PGB) shaft-and-carrier assemblies 

installed. These engines are U.S. typecertificated but as of the effective date of this 

AD are only installed on military airplanes. 

For the SNs affected, see the Effectivity 

section of the applicable service bulletin in 

Table 1 of this AD. 

TABLE 1—APPLICABLE LISTS OF AFFECTED PGB SHAFT-AND-CARRIER ASSEMBLIES

For engine model: Reference service bulletin: 

AE 2100D2, AE 2100D2A .................................................. AE 2100D2–A–72–073, Revision 1, dated February 18, 2008.

AE 2100D3 ......................................................................... AE 2100D3–A–72–256, Revision 1, dated February 18, 2008. 

AE 2100J ............................................................................ AE 2100J–A–72–071, Revision 1, dated February 18, 2008. 

These engines are U.S. type-certificated 

and are installed on, but not limited to, 

Lockheed Martin C130–J and Lockheed/ 

Alenia C–27J military airplanes. 

Unsafe Condition 

(d) This AD results from a report of a crack 

found in the forward cone of a PGB shaft in 

an RRC AE 2100D3 turboprop engine that 

was removed from service due to high 

vibration. We are issuing this AD to prevent 

separation of the propeller from the airplane, 

which could result in injury, and damage to 

the airplane. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified unless the 

actions have already been done. 

Monitoring for PGB Vibration During Flight 

(f) During flight, monitor affected engines 

for vibration in the PGB shaft and carrier 

assemblies, using the vibration monitoring 

system in the cockpit. 

(g) Whenever a vibration message is 

displayed on the airplane’s Advisory Caution 

and Warning System, borescope-inspect the 

PGB shaft-and-carrier assembly for cracks, 

before any additional flights. 

(h) If any crack is found, remove the engine 

from service. 

(i) Guidance on borescope-inspecting, 

vibration monitoring, and fault isolation 

procedures can be found in the applicable 

service bulletin listed in Table 2 of this AD. 

TABLE 2—INFORMATION ON BORESCOPE-INSPECTING, VIBRATION MONITORING, AND FAULT ISOLATION PROCEDURES

For engine model: Reference service bulletin: 

AE 2100D2, AE 2100D2A .................................................. AE 2100D2–A–72–074, dated April 7, 2008. 

AE 2100D3 ......................................................................... AE 2100D3–A–72–258, dated April 7, 2008. 


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27686 Federal Register / Vol. 74, No. 111 / Thursday, June 11, 2009 / Rules and Regulations 

TABLE 2—INFORMATION ON BORESCOPE-INSPECTING, VIBRATION MONITORING, AND FAULT ISOLATION PROCEDURES— 

Continued 

For engine model: Reference service bulletin: 

AE 2100J ............................................................................ AE 2100J–A–72–070, dated September 17, 2007. 

AE 2100J–A–72–073, dated October 11, 2007. 

Terminating Action—Removal of Affected 

PGB Shaft-and-Carrier Assemblies 

(j) At the next shop visit for PGB 

inspection or repair after the effective date of 

this AD, remove the affected PGB shaft-andcarrier assembly from service and install an 

eligible PGB shaft-and-carrier assembly. 

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

not install any PGB shaft and carrier 

assembly in any aircraft if it was removed for 

cracks. 

Definition 

(l) For the purpose of this AD, a PGB shaftand-carrier assembly is eligible for 

installation if it was manufactured after June 

2005, or if it is P/N 23087076 or P/N 

23087077. 

Alternative Methods of Compliance 

(m) The Manager, Chicago Aircraft 

Certification Office, has the authority to 

approve alternative methods of compliance 

for this AD if requested using the procedures 

found in 14 CFR 39.19. 

Related Information 

(n) Contact Rolls-Royce Corporation, P.O. 

Box 420, Indianapolis, IN 46206; telephone: 

(317) 230–3774; fax (317) 230–6084; e-mail: 

indy.pubs.services@rolls-royce.com, for the 

service information identified in this AD. 

(o) Contact Michael Downs, Aerospace 

Engineer, Chicago Aircraft Certification 

Office, FAA, Small Airplane Directorate, 

2300 E. Devon Ave., Des Plaines, IL 60018; 

e-mail: michael.downs@faa.gov; telephone 

(847) 294–7870, fax (847) 294–7834, for more 

information about this AD. 

(p) You must use the service information 

specified in Table 3 of this AD to determine 

the SNs of PGB shaft-and-carrier assemblies 

affected by this AD. The Director of the 

Federal Register approved the incorporation 

by reference of the documents listed in Table 

3 of this AD in accordance with 5 U.S.C. 

552(a) and 1 CFR part 51. Contact RollsRoyce Corporation, P.O. Box 420, 

Indianapolis, IN 46206; telephone (317) 230– 

3774; fax (317) 230–6084; e-mail: 

indy.pubs.services@rolls-royce.com for a 

copy of this service information. 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/ibr-locations.html. 

TABLE 3—INCORPORATION BY REFERENCE

Service bulletin no. Page Revision Date 

AE 2100D2–A–72–073, Total Pages: 5 .............................................................................. All ................ 1 February 18, 2008. 

AE 2100D3–A–72–256, Total Pages: 16 ............................................................................ All ................ 1 February 18, 2008. 

AE 2100J–A–72–071, Total Pages: 4 ................................................................................. All ................ 1 February 18, 2008. 

Issued in Burlington, Massachusetts, on 

May 14, 2009. 

Peter A. White, 

Assistant Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. E9–11992 Filed 6–10–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0530; Directorate 

Identifier 2009–NM–079–AD; Amendment 

39–15936; AD 2009–12–13] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier 

Model DHC–8–400 Series Airplanes 

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 the 

products listed above. This AD results 

from mandatory continuing 

airworthiness information (MCAI) 

originated by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: 

There has been one case reported of failure 

of a shaft (tailstock) on an elevator Power 

Control Unit (PCU), Part Number (P/N) 

390600–1007. Continued actuation of the 

affected PCU caused damage to the 

surrounding structure. * * * 

Each elevator surface has three PCUs, 

powered by separate independent hydraulic 

systems, and a single elevator PCU shaft 

failure may remain dormant. Such a dormant 

loss of redundancy, coupled with the 

potential for a failed shaft to produce 

collateral damage, including damage to 

hydraulic lines, could possibly affect the 

controllability of the aircraft. 

* * * * * 

This AD requires actions that are 

intended to address the unsafe 

condition described in the MCAI. 

DATES: This AD becomes effective June 

26, 2009. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of June 26, 2009. 

We must receive comments on this 

AD by July 13, 2009. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC, 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 regulatory 

evaluation, any comments received, and 

other information. The street address for 


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