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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Federal Register / Vol. 74, No. 111 / Thursday, June 11, 2009 / Rules and Regulations 27687 

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 FURTHER INFORMATION CONTACT: 

Cesar Gomez, Aerospace Engineer, 

Airframe and Propulsion Branch, ANE– 

171, FAA, New York Aircraft 

Certification Office, 1600 Stewart 

Avenue, Suite 410, Westbury, New York 

11590; telephone (516) 228–7318; fax 

(516) 794–5531. 

SUPPLEMENTARY INFORMATION: 

Discussion 

Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued Canadian 

Airworthiness Directive CF–2009–16, 

dated April 20, 2009 (referred to after 

this as ‘‘the MCAI’’), to correct an unsafe 

condition for the specified products. 

The MCAI states: 

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. Subsequent 

investigation determined that the failure was 

the result of a material defect and that the 

shafts installed on a total of 88 suspect PCUs 

* * * may contain a similar defect. 

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 directive mandates an identification 

check for elevator PCU serial numbers, a 

daily check for correct operation of all 

suspect PCUs and, finally, replacement of all 

suspect PCUs. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

Bombardier has issued Service 

Bulletin 84–27–32, Revision A, dated 

January 18, 2008; and Q400 All 

Operator Message 217B, dated April 26, 

2007. The actions described in this 

service information are intended to 

correct the unsafe condition identified 

in the MCAI. 

FAA’s Determination and Requirements 

of This AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are issuing this 

AD because we evaluated all pertinent 

information and determined the unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Differences Between the AD and the 

MCAI or Service Information 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. But 

we might have found it necessary to use 

different words from those in the MCAI 

to ensure the AD is clear for U.S. 

operators and is enforceable. In making 

these changes, we do not intend to differ 

substantively from the information 

provided in the MCAI and related 

service information. 

We might also have required different 

actions in this AD from those in the 

MCAI in order to follow FAA policies. 

Any such differences are highlighted in 

a Note within the AD. 

FAA’s Determination of the Effective 

Date 

An unsafe condition exists that 

requires the immediate adoption of this 

AD. The FAA has found that the risk to 

the flying public justifies waiving notice 

and comment prior to adoption of this 

rule because the power control unit 

(PCU), part number P/N 390600–1007, 

has been identified as having a shaft 

(tailstock) failure. Each elevator on the 

affected model airplane contains three 

PCUs which are powered independently 

as a means of redundancy. Due to this 

built-in redundancy, a fracture to the 

elevator PCU shaft can remain 

undetected while decreasing airplane 

safety. Furthermore, the continual use of 

the failed shaft in the PCUs can result 

in damage to additional systems such as 

hydraulic lines, and could result in loss 

of controllability of the airplane. Since 

this is a dormant failure, it is necessary 

to identify and replace any defective 

units within 30 days after the effective 

date of this AD. Therefore, we 

determined that notice and opportunity 

for public comment before issuing this 

AD are impracticable and that good 

cause exists for making this amendment 

effective in fewer than 30 days. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not precede it by notice and 

opportunity for public comment. We 

invite you to send any written relevant 

data, views, or arguments about this AD. 

Send your comments to an address 

listed under the ADDRESSES section. 

Include ‘‘Docket No. FAA–2009–0530; 

Directorate Identifier 2009–NM–079– 

AD’’ at the beginning of your comments. 

We specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

this AD. We will consider all comments 

received by the closing date and may 

amend this AD because of those 

comments. 

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 we receive 

about 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 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 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 regulatory evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 


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27688 Federal Register / Vol. 74, No. 111 / Thursday, June 11, 2009 / Rules and Regulations 

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: 

2009–12–13 Bombardier, Inc. (Formerly de 

Havilland, Inc.): Amendment 39–15936. 

Docket No. FAA–2009–0530; Directorate 

Identifier 2009–NM–079–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective June 26, 2009. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Bombardier Model 

DHC–8–400, DHC–8–401, and DHC–8–402 

airplanes, certificated in any category, serial 

numbers 4135 through 4149 inclusive. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 27: Flight Controls. 

Reason 

(e) The mandatory continued airworthiness 

information (MCAI) states: 

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. Subsequent 

investigation determined that the failure was 

the result of a material defect and that the 

shafts installed on a total of 88 suspect PCUs 

* * * may contain a similar defect. 

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 directive mandates an identification 

check for elevator PCU serial numbers, a 

daily check for correct operation of all 

suspect PCUs and, finally, replacement of all 

suspect PCUs. 

Actions and Compliance 

(f) Unless already done, do the following 

actions. 

(1) Within 30 days after the effective date 

of this AD, inspect the serial number of each 

of the six installed elevator PCUs having P/ 

N 390600–1007. If one or more of the six 

installed elevator PCUs, P/N 390600–1007, 

have any of the PCU serial numbers 238, 698, 

783 through 788 inclusive, 790, 793, 795, 

802, 806, 807, 810, 820 through 823 

inclusive, 826 through 828 inclusive, 831, 

835, 838, 840, 886 through 889 inclusive, or 

898 through 955 inclusive; without a suffix 

‘‘A’’ after the serial number: Within 30 days 

after the effective date of this AD, perform a 

check for the correct operation of all installed 

elevator PCUs in accordance with the 

procedures detailed in Appendix A, B, or C 

of Bombardier Q400 All Operator Message 

217B, dated April 26, 2007. Repeat the check 

thereafter before the first flight of each day 

until the replacement specified in paragraph 

(f)(3) of this AD is done. The checks in 

Appendix A and B of Bombardier Q400 All 

Operator Message 217B, dated April 26, 

2007, must be performed by the flight crew, 

while the check specified in Appendix C of 

the all operators message must be performed 

by certificated maintenance personnel. 

Note 1: Suffix ‘‘A’’ after the serial number 

indicates that the PCU has already passed a 

magnetic particle inspection and is cleared 

for continued use. 

(2) If incorrect operation of any elevator 

PCU is found during any check required by 

paragraph (f)(1) of this AD, before further 

flight, replace the elevator PCU with a PCU, 

P/N 390600–1007, having a serial number not 

specified in paragraph (f)(1) of this AD; or 

with a PCU, P/N 390600–1007, having the 

suffix ‘‘A’’ after the serial number; in 

accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

84–27–32, Revision A, dated January 18, 

2008. 

(3) Replacing all PCUs, P/N 390600–1007, 

having a serial number specified in 

paragraph (f)(1) of this AD, and not having 

suffix ‘‘A’’ after the serial number, with a 

PCU, P/N 390600–1007, having a serial 

number not specified in paragraph (f)(1) of 

this AD; or with a PCU, P/N 390600–1007, 

having the suffix ‘‘A’’ after the serial number; 

in accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

84–27–32, Revision A, dated January 18, 

2008; terminates the requirements of 

paragraph (f)(1) of this AD. 

(4) Actions accomplished before the 

effective date of this AD according to 

Bombardier Service Bulletin 84–27–32, dated 

May 1, 2007, are considered acceptable for 

compliance with the corresponding action 

specified in this AD. 

FAA AD Differences 

Note 2: This AD differs from the MCAI 

and/or service information as follows: Unlike 

the Canadian airworthiness directive CF– 

2009–16, dated April 20, 2009, this AD does 

not require the eventual replacement of all 

elevator PCUs identified in paragraph (f)(1) of 

this AD. The planned compliance times for 

those actions would allow enough time to 

provide notice and opportunity for prior 

public comment on the merits of those 

actions. Therefore, we are considering further 

rulemaking to address this issue. 

Other FAA AD Provisions 

(g) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Airframe and 

Propulsion Branch, ANE–171, FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. Send information to ATTN: Cesar 

Gomez, Aerospace Engineer, Airframe and 

Propulsion Branch, ANE–171, FAA, New 

York Aircraft Certification Office, 1600 

Stewart Avenue, Suite 410, Westbury, New 

York 11590; telephone (516) 228–7318; fax 

(516) 794–5531. Before using any approved 

AMOC on any airplane to which the AMOC 

applies, notify your principal maintenance 

inspector (PMI) or principal avionics 

inspector (PAI), as appropriate, or lacking a 

principal inspector, your local Flight 

Standards District Office. The AMOC 

approval letter must specifically reference 

this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(3) Reporting Requirements: For any 

reporting requirement in this AD, under the 

provisions of the Paperwork Reduction Act, 

the Office of Management and Budget (OMB) 

has approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(h) Refer to MCAI Canadian Airworthiness 

Directive CF–2009–16, dated April 20, 2009; 

Bombardier Service Bulletin 84–27–32, 

Revision A, dated January 18, 2008; and 

Bombardier Q400 All Operator Message 

217B, dated April 26, 2007; for related 

information. 

Material Incorporated by Reference 

(i) You must use Bombardier Service 

Bulletin 84–27–32, Revision A, dated January 

18, 2008, or Bombardier Q400 All Operator 

Message 217B, dated April 26, 2007 to do the 

actions required by this AD, unless the AD 

specifies otherwise. 

(1) 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. 

(2) For service information identified in 

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

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

855–7401; e-mail 

thd.qseries@aero.bombardier.com; Internet 

http://www.bombardier.com. 

(3) You may review copies of the 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 or 425–227–1152. 

(4) You may also review copies of the 

service information that is incorporated by 

reference at the National Archives and 


cprice-sewell on PRODPC61 with RULES
Federal Register / Vol. 74, No. 111 / Thursday, June 11, 2009 / Rules and Regulations 27689 

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 Renton, Washington, on June 3, 

2009. 

Stephen P. Boyd, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. E9–13570 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–2009–0531; Directorate 

Identifier 2009–CE–030–AD; Amendment 

39–15938; AD 2009–12–15] 

RIN 2120–AA64 

Airworthiness Directives; GROB– 

Werke Model G120A Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), 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) 

issued by the aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: 

The manufacturer has advised of receiving 

a report from a G 120A operator of an 

electrical fire caused by a chafed/scorched 

cable loom. It has been found that the RH 

main power distribution cable chafed on the 

instrument panel combing. It is likely that 

vibrations made the wiring to chafe. The 

chafing caused eventually electrical arcing 

and subsequently an in-flight fire that 

damaged partially the instrument panel 

cover. 

This AD requires actions that are 

intended to address the unsafe 

condition described in the MCAI. 

DATES: This AD becomes effective July 

1, 2009. 

On July 1, 2009, the Director of the 

Federal Register approved the 

incorporation by reference of certain 

publications listed in this AD. 

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 20590, 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 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 street address for 

the Docket Office (telephone (800) 647– 

5527) is in the ADDRESSES section. 

Comments will be available in the AD 

docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: Karl 

Schletzbaum, Aerospace Engineer, FAA, 

Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4146; fax: (816) 

329–4090. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued AD No.: 2009– 

0107, dated May 8, 2009 (referred to 

after this as ‘‘the MCAI’’), to correct an 

unsafe condition for the specified 

products. The MCAI states: 

The manufacturer has advised of receiving 

a report from a G 120A operator of an 

electrical fire caused by a chafed/scorched 

cable loom. It has been found that the RH 

main power distribution cable chafed on the 

instrument panel combing. It is likely that 

vibrations made the wiring to chafe. The 

chafing caused eventually electrical arcing 

and subsequently an in-flight fire that 

damaged partially the instrument panel 

cover. 

For the reasons stated above, this new AD 

mandates inspection of all cable looms in the 

front of the instrument panel cover, repair as 

necessary and installation of a protective 

cover on the edge of the instrument panel 

combing. 

You may obtain further information 

by examining the MCAI in the AD 

docket. 

Relevant Service Information 

GROB Aircraft AG has issued Service 

Bulletin No. MSB1121–108, dated 

March 18, 2009, and Service Bulletin 

No. MSB1121–108/1, dated April 27, 

2009. The actions described in this 

service information are intended to 

correct the unsafe condition identified 

in the MCAI. 

FAA’s Determination and Requirements 

of the AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with this State of 

Design Authority, they have notified us 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are issuing this 

AD because we evaluated all 

information provided by the State of 

Design Authority and determined the 

unsafe condition exists and is likely to 

exist or develop on other products of the 

same type design. 

Differences Between This AD and the 

MCAI or Service Information 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. But 

we might have found it necessary to use 

different words from those in the MCAI 

to ensure the AD is clear for U.S. 

operators and is enforceable. In making 

these changes, we do not intend to differ 

substantively from the information 

provided in the MCAI and related 

service information. 

We might have also required different 

actions in this AD from those in the 

MCAI in order to follow FAA policies. 

Any such differences are described in a 

separate paragraph of the AD. These 

requirements take precedence over 

those copied from the MCAI. 

FAA’s Determination of the Effective 

Date 

An unsafe condition exists that 

requires the immediate adoption of this 

AD. The FAA has found that the risk to 

the flying public justifies waiving notice 

and comment prior to adoption of this 

rule because if left uncorrected, the 

power distribution cable could chafe 

leading to electrical arcing and an inflight fire. Therefore, we determined 

that notice and opportunity for public 

comment before issuing this AD are 

impracticable and that good cause exists 

for making this amendment effective in 

fewer than 30 days. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not precede it by notice and 

opportunity for public comment. We 

invite you to send any written relevant 


cprice-sewell on PRODPC61 with RULES