Federal Register / Vol. 77, No. 204 / Monday, October 22, 2012 / Proposed Rules 64439 

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. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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: 

Burkhart GROB Luft-und Raumfahrt GmbH: 

Docket No. FAA–2012–1124; Directorate 

Identifier 2012–CE–041–AD. 

(a) Comments Due Date 

We must receive comments by December 6, 

2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Burkhart GROB Luftund Raumfahrt GmbH Models GROB G 109 

and GROB G 109B sailplanes, all serial 

numbers, certificated in any category. 

(d) Subject 

Air Transport Association of America 

(ATA) Code 27: Flight Controls. 

(e) Reason 

This AD was prompted by 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 corrosion 

and/or cracking of the elevator control rod. 

We are issuing this proposed AD to detect 

and correct corrosion and/or cracking of the 

elevator control rod, which could lead to 

failure of the elevator control rod with 

consequent loss of control. 

(f) Actions and Compliance 

Unless already done, do the following 

actions: 

(1) Within the next 25 hours time-inservice (TIS) after the effective date of this 

AD or within the next 60 days after the 

effective date of this AD, whichever occurs 

first, and repetitively thereafter at intervals 

not to exceed every 5 years, inspect the 

elevator control rod in the vertical fin for 

corrosion or cracking following the 

accomplishment instructions in Grob Aircraft 

AG Service Bulletin No. MSB817–64/2, dated 

September 6, 2012. 

(2) For the purposes of this AD, we define 

slight corrosion as corrosion you can remove 

with metal wool and that has no visible 

pitting in the base metal. If you cannot 

remove the corrosion with metal wool or if 

there is visible pitting in the base metal, we 

define it as heavy corrosion. 

(3) If any cracks or heavy corrosion are 

found during any of the inspections required 

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

flight, replace the elevator control rod with 

an airworthy part following the 

accomplishment instructions in Grob Aircraft 

AG Service Bulletin No. MSB817–64/2, dated 

September 6, 2012, for your applicable 

sailplane model. 

(4) If only slight or no corrosion of the 

elevator control rod is found during any of 

the inspections required in paragraph (f)(1) of 

this AD, before further flight, clean the rod 

surface and apply a corrosion inhibitor, as 

applicable, following the accomplishment 

instructions in Grob Aircraft AG Service 

Bulletin No. MSB817–64/2, dated September 

6, 2012. 

Note 1 to paragraph (f) of this AD: Grob 

Aircraft AG incorporated the repetitive 

inspections required by this AD into the 

instructions for continued airworthiness of 

the aircraft maintenance manual for the 

applicable sailplanes. 

(g) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Standards Office, 

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: Jim Rutherford, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4165; fax: (816) 329– 

4090; email: jim.rutherford@faa.gov. Before 

using any approved AMOC on any airplane 

to which the AMOC applies, notify your 

appropriate principal inspector (PI) in the 

FAA Flight Standards District Office (FSDO), 

or lacking a PI, your local FSDO. 

(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, a federal 

agency may not conduct or sponsor, and a 

person is not required to respond to, nor 

shall a person be subject to a penalty for 

failure to comply with a collection of 

information subject to the requirements of 

the Paperwork Reduction Act unless that 

collection of information displays a current 

valid OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0056. Public reporting for 

this collection of information is estimated to 

be approximately 5 minutes per response, 

including the time for reviewing instructions, 

completing and reviewing the collection of 

information. All responses to this collection 

of information are mandatory. Comments 

concerning the accuracy of this burden and 

suggestions for reducing the burden should 

be directed to the FAA at: 800 Independence 

Ave. SW., Washington, DC 20591, Attn: 

Information Collection Clearance Officer, 

AES–200. 

(h) Related Information 

Refer to European Aviation Safety Agency 

(EASA), which is the Technical Agent for the 

Member States of the European Community, 

AD No.: 2012–0181, dated September 7, 

2012; and Grob Aircraft AG Service Bulletin 

No. MSB817–64/2, dated September 6, 2012, 

for related information. For service 

information related to this AD, contact Grob 

Aircraft AG, Lettenbachstrasse 9, D–86874 

Tussenhausen-Mattsies, Germany; phone: 

+49 (0) 8268 998 139; fax: +49 (0) 8268 998 

200; email: productsupport@grobaircraft.com; Internet: www.grobaircraft.com/62.html. 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. 

Issued in Kansas City, Missouri, on 

October 15, 2012. 

Pat Mullen, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–25891 Filed 10–19–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1127; Directorate 

Identifier 2010–SW–035–AD] 

RIN 2120–AA64 

Airworthiness Directives; Bell 

Helicopter Textron Canada (Bell) Model 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA) DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for Bell 

Model 430 helicopters, which would 

require replacing certain components of 

the air data system. This proposed AD 

is prompted by the discovery of 

incorrect indicated airspeed when the 

helicopter was tested to the cold 

temperature limits (¥40 degrees 

centigrade) required for Category A 

operations. The proposed actions are 

intended to correct the published Vne

and to correct the indicated airspeed. 

DATES: We must receive comments on 

this proposed AD by December 21, 

2012. 


wreier-aviles on DSK5TPTVN1PROD with 
64440 Federal Register / Vol. 77, No. 204 / Monday, October 22, 2012 / Proposed Rules 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Docket: Go to 

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

instructions for sending your comments 

electronically. 

• Fax: 202–493–2251. 

• Mail: Send comments to the U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590–0001. 

• Hand Delivery: Deliver to the 

‘‘Mail’’ address between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

Examining The AD Docket: You may 

examine the AD docket on the Internet 

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

person at the Docket Operations Office 

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

through Friday, except Federal holidays. 

The AD docket contains this proposed 

AD, the economic evaluation, any 

comments received, and other 

information. The street address for the 

Docket Operations Office (telephone 

800–647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

For service information identified in 

this proposed AD, contact Bell 

Helicopter Textron Canada Limited, 

12,800 Rue de l’Avenir, Mirabel, Quebec 

J7J1R4, telephone (450) 437–2862 or 

(800) 363–8023, fax (450) 433–0272, or 

http://www.bellcustomer.com/files/. 

You may review the referenced service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 

2601 Meacham Blvd., Room 663, Fort 

Worth, Texas 76137. 

FOR FURTHER INFORMATION CONTACT: 

Mark F. Wiley, Aviation Safety 

Engineer, FAA, Rotorcraft Directorate, 

Regulations and Policy Group, 2601 

Meacham Blvd., Fort Worth, Texas 

76137, telephone (817) 222–5110, fax 

(817) 222–5961, email mark.wiley@faa.

gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to participate in this 

rulemaking by submitting written 

comments, data, or views. We also 

invite comments relating to the 

economic, environmental, energy, or 

federalism impacts that might result 

from adopting the proposals in this 

document. The most helpful comments 

reference a specific portion of the 

proposal, explain the reason for any 

recommended change, and include 

supporting data. To ensure the docket 

does not contain duplicate comments, 

commenters should send only one copy 

of written comments, or if comments are 

filed electronically, commenters should 

submit only one time. 

We will file in the docket all 

comments that we receive, as well as a 

report summarizing each substantive 

public contact with FAA personnel 

concerning this proposed rulemaking. 

Before acting on this proposal, we will 

consider all comments we receive on or 

before the closing date for comments. 

We will consider comments filed after 

the comment period has closed if it is 

possible to do so without incurring 

expense or delay. We may change this 

proposal in light of the comments we 

receive. 

Discussion 

Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued Canadian AD No. 

CF–2005–30, dated August 3, 2005, to 

correct an unsafe condition for the Bell 

Model 430 helicopters. Discrepancies in 

the processing and display of air data 

were revealed when testing at low 

temperatures to minus 40 degrees 

Centigrade (¥40 °C). The TCCA advises 

that modification to the instrumentation 

is required to reflect the Vne airspeed 

values tested at temperatures to ¥40 °C. 

The TCCA states ‘‘This modification 

affects the software in the Vne Overspeed 

Warning computer (required for 

Category A operations) and in the AFCS 

[Automatic Flight Control System] Air 

Data Computer.’’ TCAA issued AD CF– 

2005–30 to require the procedures in 

Bell Alert Service Bulletin (ASB) No. 

430–05–35, dated June 21, 2005, for 

replacing the affected instruments. Bell 

also issued ASB No. 430–01–22, dated 

April 30, 2001 (ASB 430–01–22), which 

provided a temporary Rotorcraft Flight 

Manual Supplement and placards with 

information on airspeed corrections. 

TCCA did not issue an AD to mandate 

the provisions of ASB 430–01–22. 

FAA’s Determination 

These helicopters have been approved 

by the TCCA and are approved for 

operation in the United States. Pursuant 

to our bilateral agreement with Canada, 

TCCA has notified us of the unsafe 

condition described in the Canadian 

AD. 

We are proposing this AD because we 

have evaluated all relevant information 

and determined that an unsafe 

condition exists and is likely to exist or 

develop on other helicopters of this 

same type design. 

Related Service Information 

Bell has issued ASB No. 430–05–35, 

dated June 21, 2005, which specifies, for 

helicopters with an overspeed warning 

system, replacing the overspeed 

warning computer, Vne converter, and 

pilot and copilot airspeed indicator; 

leak testing the pilot pitot static system; 

and operationally testing the overspeed 

warning system. For helicopters with a 

single or dual Automatic Flight Control 

System (AFCS) with a Flight Director, 

ASB No. 430–05–35 specifies replacing 

the AFCS air data computer adapter 

module; leak testing the pilot pitot static 

system; and power-up and self-testing 

the ALT/VSI. This ASB also specifies 

removing the Vne-unreliable decals on 

the instrument panel on both 

configurations of these helicopters. 

TCCA classified ASB No. 430–05–35 as 

mandatory and issued AD CF–2005–30, 

dated August 3, 2005, to ensure the 

continued airworthiness of these 

helicopters. 

Proposed AD Requirements 

This proposed AD would require 

within 1 year, unless done previously: 

• For helicopters with Overspeed 

Warning System: 

Æ Replacing the overspeed warning 

computer, the Vne converter, and the 

pilot and copilot airspeed indicator; 

Æ Removing decal, P/N 430–075– 

070–103, if installed, from below the 

pilot and copilot airspeed indicators; 

Æ Leak testing the pilot pitot static 

system; and 

Æ Operationally testing the overspeed 

warning system. 

• For helicopters with a Single or 

Dual AFCS with a Flight Director: 

Æ Replacing the AFCS air data 

computer adapter module; 

Æ Removing decal, P/N 430–075– 

070–101, if installed, from above the 

pilot and copilot electronic attitude 

direction indicators airspeed indicators; 

Æ Leak testing the pilot pitot static 

system; and 

Æ Power-up testing the altimeter/ 

vertical speed indicator (ALT/VSI) and 

self-testing the ALT/VSI of the AFCS air 

data computer. 

Differences Between This Proposed AD 

and the TCCA AD 

We do not use the compliance date of 

July 31, 2007. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 52 helicopters of U.S. 

registry. We estimate that operators may 

incur the following costs in order to 

comply with this AD: 

• $680 to replace the overspeed 

warning computer, pilot and copilot 

airspeed indicators, Vne converter, and 

AFCS air data computer adapter module 

for each helicopter, assuming 8 work 

hours for each helicopter at an average 

labor rate of $85 per work hour, and 


wreier-aviles on DSK5TPTVN1PROD with 
Federal Register / Vol. 77, No. 204 / Monday, October 22, 2012 / Proposed Rules 64441 

• $46,074 per helicopter for the 

required parts. 

Based on these figures, we estimate 

the total cost impact of the proposed AD 

on U.S. operators to be $2,431,208 for 

the fleet. 

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 proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would 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, I certify 

this proposed regulation: 

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); 

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 proposed AD and placed it in the 

AD docket. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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). 

Bell Helicopter Textron Canada: Docket No. 

FAA–2012–1127; Directorate Identifier 

2010–SW–035–AD. 

(a) Applicability 

This AD applies to Model 430 helicopters: 

serial number (S/N) 49001 through 49103, 

with Overspeed Warning Kit, part number (P/ 

N) 430–706–004–101 or P/N 430–706–004– 

103, installed; S/N 49001 through 49100, 

with Single Automatic Flight Control System 

(AFCS) with Flight Director Kit, P/N 430– 

705–009–103, –105, –109, –111, –115, –117, 

or P/N 430–705–011–109, –111, –121, or 

–123, installed; and S/N 49001 through 

49100, with Dual AFCS with Flight Director 

Kit, P/N 430–705–011–103, –105, –115, –117, 

–125, –127, –129, –133, –135, or –137, 

installed, certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

inability of the helicopters, based on testing, 

to operate at the published Vne indicated 

airspeeds within the cold temperature limits 

(¥40 degrees centigrade) required for 

Category A operations. 

(c) 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. 

(d) Required Actions 

Within 1 year: 

(1) For helicopters with an Overspeed 

Warning System, replace the Overspeed 

Warning Computer, P/N 430–375–013–103, 

with the Overspeed Warning Computer, P/N 

430–375–013–105; the Vne Converter, P/N 

ADI–21280–000, with the Vne Converter, P/N 

ADI–21280–100; and the pilot and copilot 

Airspeed Indicator, P/N 222–375–027–117, 

with the pilot and copilot airspeed Indicator, 

P/N 222–375–027–119; 

(i) If installed, remove the decal, P/N 430– 

075–070–103, from below the pilot and 

copilot airspeed indicators; 

(ii) Leak test the pilot pitot static system; 

and 

(iii) Operationally test the overspeed 

warning system. 

(2) For helicopters with a Single or Dual 

Automatic Flight Control System (AFCS) 

with a Flight Director, replace the AFCS Air 

Data Computer Adapter Module, P/N 065– 

05041–0021, with P/N 065–05041–0031; 

(i) If installed, remove the decal, P/N 430– 

075–070–101, from above the pilot and 

copilot electronic attitude direction 

indicators airspeed indicators; 

(ii) Leak test the pilot pitot static system; 

(iii) Power-up test the altimeter/vertical 

speed indicator (ALT/VSI) and self-test the 

ALT/VSI of the AFCS air data computer. 

(e) Alternative Methods of Compliance 

(AMOC) 

(1) The Manager, Rotorcraft Standards 

Staff, FAA may approve AMOCs for this AD. 

Send your proposal to: Mark F. Wiley, 

Aviation Safety Engineer, Rotorcraft 

Directorate, Regulations and Policy Group, 

2601 Meacham Blvd., Fort Worth, Texas 

76137, telephone (817) 222–5134, fax (817) 

222–5961, email mark.wiley@faa.gov. 

(2) For operations conducted under a 14 

CFR part 119 operating certificate or under 

14 CFR part 91, subpart K, we suggest that 

you notify your principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office or 

certificate holding district office before 

operating any aircraft complying with this 

AD through an AMOC. 

(f) Additional Information 

(1) Bell Helicopter Textron Alert Service 

Bulletin (ASB) No. 430–05–35, dated June 21, 

2005, and ASB No. 430–01–22, dated April 

30, 2001, which are not incorporated by 

reference, contain additional information 

about the subject of this AD. For service 

information identified in this AD, contact 

Bell Helicopter Textron Canada Limited, 

12,800 Rue de l’Avenir, Mirabel, Quebec 

J7J1R4, telephone (450) 437–2862 or (800) 

363–8023, fax (450) 433–0272, or http://www.

bellcustomer.com/files/. You may review the 

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 

Transport Canada Civil Aviation AD No. CF 

2005–30, dated August 3, 2005. 

(g) Subject 

Joint Aircraft System/Component Code: 

3417 Air Data Computer. 

Issued in Fort Worth, Texas, on October 12, 

2012. 

Kim Smith, 

Manager, Rotorcraft Directorate, Aircraft 

Certification Service. 

[FR Doc. 2012–25899 Filed 10–19–12; 8:45 am] 

BILLING CODE 4910–13–P 


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