Federal Register / Vol. 72, No. 3 / Friday, January 5, 2007 / Proposed Rules 485 

the Limitations Section of the Airplane Flight 

Manual (AFM) to incorporate the following. 

(i) Takeoff with frost, ice, snow, or slush 

on the wing, control surfaces, horizontal tail, 

and air intakes, and flight into icing 

conditions are prohibited. 

(ii) Prior to each flight in which ground 

icing conditions exist as described in EADS 

SOCATA MS760 Aircraft Mandatory Service 

Bulletin SB 76–053, ATA No. 30, dated 

October 2006, perform a visual/tactile check. 

No visible trace of frost is acceptable 

particularly on stabilizers and wing upper 

surfaces and leading edges as well as on air 

intakes. 

(2) The owner/operator holding at least a 

private pilot certificate as authorized by 

section 43.7 of the Federal Aviation 

Regulations (14 CFR 43.7) may do the actions 

of this AD. Make an entry into the aircraft 

records showing compliance with this AD in 

accordance with section 43.9 of the Federal 

Aviation Regulations (14 CFR 43.9). 

FAA AD Differences 

Note: This AD differs from the MCAI and/ 

or service information as follows: We added 

information in paragraph (e) that allows the 

owner/operator to insert a copy of this AD 

into the Limitation Section of the AFM. 

Without this information, a licensed 

mechanic would be required to do the AFM 

insertion. 

Other FAA AD Provisions 

(f) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Standards Staff, 

FAA, Small Airplane Directorate, ATTN: 

Albert J. Mercado, Aerospace Engineer, 901 

Locust, Room 301, Kansas City, Missouri 

64106; telephone: (816) 329–4119; fax: (816) 

329–4090, has the authority to approve 

AMOCs for this AD, if requested using the 

procedures found in 14 CFR 39.19. 

(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 

(44 U.S.C. 3501 et seq.), the Office of 

Management and Budget (OMB) has 

approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(g) Refer to MCAI European Aviation 

Safety Agency Emergency Airworthiness 

Directive AD No. 2006–0348–E, dated 

November 20, 2006, and EADS SOCATA 

MS760 Aircraft Mandatory Service Bulletin 

SB 76–053, ATA No. 30, dated October 2006, 

for related information. 

Issued in Kansas City, Missouri, on 

December 28, 2006. 

John Colomy, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E6–22578 Filed 1–4–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2006–26497; Directorate 

Identifier 2006–CE–82–AD] 

RIN 2120–AA64 

Airworthiness Directives; 

Przedsiebiorstwo DoswiadczalnoProdukcyjne Szybownictwa ‘‘PZL–

Bielsko’’ Model SZD–50–3 ‘‘Puchacz’’

Gliders 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for the 

products listed above. This proposed 

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. The MCAI describes the unsafe 

condition as: 

Some cases of turnbuckle adjusting screws 

fatigue failure have occurred, due to lateral 

load component applied by pilot’s foot. Such 

events may lead to rudder and pedals 

disconnection. 

The proposed AD would require 

actions that are intended to address the 

unsafe condition described in the MCAI. 

DATES: We must receive comments on 

this proposed AD by February 5, 2007. 

ADDRESSES: You may sent comments by 

any of the following methods: 

• DOT Docket Web Site: Go to 

http://dms.dot.gov and follow the 

instructions for sending your comments 

electronically. 

• Fax: (202) 493–2251. 

• Mail: Docket Management Facility, 

U.S. Department of Transportation, 400 

Seventh Street, SW., Nassif Building, 

Room PL–401, Washington, DC 20590–

0001. 

• Hand Delivery: Room PL–401 on 

the plaza level of the Nassif Building, 

400 Seventh Street, SW., Washington, 

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

through Friday, except Federal holidays. 

• Federal eRulemaking Portal: http:// 

www.regulations.gov. Follow the 

instructions for submitting comments. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://dms.dot.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 

proposed AD, the regulatory evaluation, 

any comments received, and other 

information. The street address for the 

Docket Office (telephone (800) 647–

5227) is in the ADDRESSES section. 

Comments will be available in the AD 

docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Gregory Davison, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 

Locust, Room 301, Kansas City, 

Missouri 64106; telephone: (816) 329–

4130; fax: (816) 329–4090. 

SUPPLEMENTARY INFORMATION: 

Streamlined Issuance of AD 

The FAA is implementing a new 

process for streamlining the issuance of 

ADs related to MCAI. The streamlined 

process will allow us to adopt MCAI 

safety requirements in a more efficient 

manner and will reduce safety risks to 

the public. This process continues to 

follow all FAA AD issuance processes to 

meet legal, economic, Administrative 

Procedure Act and Federal Register 

requirements. We also continue to meet 

our technical decision-making 

responsibilities to identify and correct 

unsafe conditions on U.S.-certificated 

products. 

This proposed AD references the 

MCAI and related service information 

that we considered in forming the 

engineering basis to correct the unsafe 

condition. The proposed AD contains 

text copied from the MCAI and for this 

reason might not follow our plain 

language principles. 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2006–26497; Directorate Identifier 

2006–CE–82–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD because of those 

comments. 

We will post all comments we 

receive, without change, to http:// 


cprice-sewell on PROD1PC66 with PROPOSALS
486 Federal Register / Vol. 72, No. 3 / Friday, January 5, 2007 / Proposed Rules 

dms.dot.gov, including any personal 

information you provide. We will also 

post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA AD 2006–

0317, dated October 16, 2006, referred 

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

an unsafe condition for the specified 

products. The MCAI states: 

Some cases of turnbuckle adjusting screws 

fatigue failure have occurred, due to lateral 

load component applied by pilot’s foot. Such 

events may lead to rudder and pedals 

disconnection. 

The MCAI requires: 

Within the next 3 months after the effective 

date of this directive, modify the aircraft by 

introducing the extra pull rod between rear 

pedals and turnbuckle adjusting screws in 

accordance with the instructions contained 

in AllStar PZL Glider Mandatory Bulletin No. 

BE–057/SZD–50–3/2006 ‘‘PUCHACZ’’. 

You may obtain further information 

by examining the MCAI in the AD 

docket. 

Relevant Service Information 

Allstar PZL Glider Sp. Z o.o. has 

issued Mandatory Service Bulletin No. 

BE–057/SZD–50–3/2006 ‘‘PUCHACZ’’, 

dated October 16, 2006. 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 Proposed 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 proposing this 

AD because we evaluated all 

information and determined the unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Differences Between This Proposed 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 proposed 

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 

proposed AD. These requirements, if 

ultimately adopted, will take 

precedence over the actions copied from 

the MCAI. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 8 products of U.S. registry. 

We also estimate that it would take 

about 2 work-hours per product to 

comply with the proposed AD. The 

average labor rate is $80 per work-hour. 

Required parts would cost about $100 

per product. Where the service 

information lists required parts costs 

that are covered under warranty, we 

have assumed that there will be no 

charge for these costs. As we do not 

control warranty coverage for affected 

parties, some parties may incur costs 

higher than estimated here. Based on 

these figures, we estimate the cost of the 

proposed AD on U.S. operators to be 

$2,080, or $260, per product. 

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 Program,’’ 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 above, 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); 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 proposed AD and placed it in the 

AD docket. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, 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: 

Przedsiebiorstwo DoswiadczalnoProdukcyjne Szybownictwa ‘‘PZLBielsko’’: Docket No. FAA–2006–26497; 

Directorate Identifier 2006–CE–82–AD 

Comments Due Date 

(a) We must receive comments by February 

5, 2007. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Model SZD–50–3 

‘‘Puchacz’’ Gliders, all serial numbers, 

certificated in any category. 

Reason 

(d) The mandatory continuing 

airworthiness information (MCAI) states: 

Some cases of turnbuckle adjusting screws 

fatigue failure have occurred, due to lateral 

load component applied by pilot’s foot. Such 

events may lead to rudder and pedals 

disconnection. 

Actions and Compliance 

(e) Unless already done, within the next 3 

calendar months after the effective date of 

this AD, install the extra pull rod between 

the rear pedals and turnbuckle adjusting 

screws following Allstar PZL Glider Sp. Z 

o.o. Mandatory Service Bulletin No. BE–057/ 

SZD–50–3/2006 ‘‘PUCHACZ’’, dated October 

16, 2006, except as specified in paragraphs 

(e)(1) through (e)(4) of this AD. For owners/ 


cprice-sewell on PROD1PC66 with PROPOSALS
Federal Register / Vol. 72, No. 3 / Friday, January 5, 2007 / Proposed Rules 487 

operators that have installed an additional 

short cable between the rear seat pedal and 

turnbuckle prior to Allstar PZL’s issuance of 

Mandatory Service Bulletin No. BE–057/ 

SZD–50–3/2006 ‘‘PUCHACZ’’, dated October 

16, 2006, this additional short cable assembly 

must comply with the requirements of Allstar 

PZL Glider Sp. Z o.o. Mandatory Service 

Bulletin No. BE–057/SQD–50–3/2006 

‘‘PUCHACZ’’, dated October 16, 2006. Upon 

completion, a logbook entry is required. 

Reference Allstar PZL Glider Sp. Z o.o. 

Mandatory Service Bulletin No. BE–054/ 

SZD–050–3/2003. 

Other FAA AD Provisions: 

(1) Paragraph 1 of Allstar PZL Glider Sp. 

Z o.o. Mandatory Service Bulletin No. BE–

057/SZD–50–3/2006 ‘‘PUCHACZ’’, dated 

October 16, 2006, describes the dimension 

length of the extra segment pull rod to be 140 

mm. Modify this to read: ‘‘140 mm (5.5118 

inches)’’. 

(2) Paragraph 4 of Allstar PZL Glider Sp. 

Z o.o. Mandatory Service Bulletin No. BE–

057/SZD–50–3/2006 ‘‘PUCHACZ’’, dated 

October 16, 2006, describes the dimensions 

of the short pull rod to be 3 mm diameter 

core and approximately 140 mm. Modify this 

to read: ‘‘3 mm (0.1181 inch) and 140 mm 

(5.5118 inches)’’. 

(3) Paragraph 4.4 of Allstar PZL Glider Sp. 

Z o.o. Mandatory Service Bulletin No. BE–

057/SZD–50–3/2006 ‘‘PUCHACZ’’, dated 

October 16, 2006, describes a 1 mm diameter 

cotter pin. Modify this to read: ‘‘1 mm 

(0.03937 inch)’’. 

(4) Paragraph 5 of Allstar PZL Glider Sp. 

Z o.o. Mandatory Service Bulletin No. BE–

057/SZD–50–3/2006 ‘‘PUCHACZ’’, dated 

October 16, 2006, reads, ‘‘The parts necessary 

for modification are available at Allstar PZL 

Glider, or substitute aircraft parts may be 

used—capable to withstand a load of 6100N 

at minimum.’’ Change this to read: ‘‘The 

parts necessary for modification are available 

at Allstar PZL Glider, or substitute aircraft 

parts may be used—capable to withstand a 

load of 6100N (1,372 lbs) at minimum. If a 

substitute part is used, the hole diameter 

specified in Figure 1 of the service bulletin 

as ‘; 6 Hg’ means a 6 mm (0.2362 inch) 

diameter hole with a dimensional tolerance 

of +0.03 mm (+0.0012 inch). Contact the 

manufacturer for further details.’’

FAA AD Differences 

Note: This AD differs from the MCAI and/ 

or service information as follows: Paragraphs 

(e)(1) and (e)(4) of this AD have been added 

to clarify certain procedures in the service 

bulletin. 

(f) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Standards Staff, 

FAA, ATTN: Gregory Davison, Aerospace 

Engineer, FAA, Small Airplane Directorate, 

901 Locust, Room 301, Kansas City, Missouri 

64106; telephone: (816) 329–4130; fax: (816) 

329–4090, has the authority to approve 

AMOCs for this AD, if requested using the 

procedures found in 14 CFR 39.19. 

(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 

(44 U.S.C. 3501 et seq.), the Office of 

Management and Budget (OMB) has 

approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(g) Refer to MCAI EASA AD 2006–0317, 

dated October 16, 2006, and Allstar PZL 

Glider Sp. Z o.o. Mandatory Service Bulletin 

No. BE–057/SZD–50–3/2006 ‘‘PUCHACZ’’, 

dated October 16, 2006, for related 

information. 

Issued in Kansas City, Missouri, on 

December 27, 2006. 

John R. Colomy, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 06–9988 Filed 1–4–07; 8:45 am] 

BILLING CODE 4910–13–M 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2006–26493; Directorate 

Identifier 2006–CE–78–AD] 

RIN 2120–AA64 

Airworthiness Directives; Alpha 

Aviation Design Limited (Type 

Certificate No. A48EU Previously Held 

by APEX Aircraft and AVIONS PIERRE 

ROBIN) Model R2160 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for the 

products listed above. This proposed 

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. The MCAI describes the unsafe 

condition as: ‘‘an occurrence of 

inadvertent manipulation of the fuel 

shut-off control has been reported.’’ The 

proposed AD would require actions that 

are intended to address the unsafe 

condition described in the MCAI. 

DATES: We must receive comments on 

this proposed AD by February 5, 2007. 

ADDRESSES: You may send comments by 

any of the following methods: 

• DOT Docket Web site: Go to 

http://dms.dot.gov and follow the 

instructions for sending your comments 

electronically. 

• Fax: (202) 493–2251. 

• Mail: Docket Management Facility, 

U.S. Department of Transportation, 400 

Seventh Street, SW., Nassif Building, 

Room PL–401, Washington, DC 20590–

0001. 

• Hand Delivery: Room PL–401 on 

the plaza level of the Nassif Building, 

400 Seventh Street, SW., Washington, 

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

through Friday, except Federal holidays. 

• Federal eRulemaking Portal: http:// 

www.regulations.gov. Follow the 

instructions for submitting comments. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://dms.dot.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 

proposed AD, the regulatory evaluation, 

any comments received, and other 

information. The street address for the 

Docket Office (telephone (800) 647–

5227) 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, MO, 64106; 

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

329–4090. 

SUPPLEMENTARY INFORMATION: 

Streamlined Issuance of AD 

The FAA is implementing a new 

process for streamlining the issuance of 

ADs related to MCAI. The streamlined 

process will allow us to adopt MCAI 

safety requirements in a more efficient 

manner and will reduce safety risks to 

the public. This process continues to 

follow all FAA AD issuance processes to 

meet legal, economic, Administrative 

Procedure Act, and Federal Register 

requirements. We also continue to meet 

our technical decision-making 

responsibilities to identify and correct 

unsafe conditions on U.S.-certificated 

products. 

This proposed AD references the 

MCAI and related service information 

that we considered in forming the 

engineering basis to correct the unsafe 

condition. The proposed AD contains 

text copied from the MCAI and for this 

reason might not follow our plain 

language principles. 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 


cprice-sewell on PROD1PC66 with PROPOSALS