20780 Federal Register / Vol. 72, No. 80 / Thursday April 26, 2007 / Proposed Rules 

Issued in Renton, Washington, on April 19, 

2007. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E7–7979 Filed 4–25–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–27680; Directorate 

Identifier 2007–CE–026–AD] 

RIN 2120–AA64 

Airworthiness Directives; 

AEROTECHNIC Vertriebs-u. Service 

GmbH Honeywell CAS67A ACAS II 

Systems Appliances 

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) 

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: 

It was detected by the STC holder that in 

earlier installations of the ACASII system 

there were no isolation diodes installed in 

the Heading and Attitude Valid lines. The 

absence of an isolation diode in the valid 

lines can prevent the valid flag to come up 

even if a gyro fault exists. The problem has 

only been detected for Heading Valid lines 

but could equally affect the Altitude Valid 

lines. 

With installation of the ACASII, the 

heading and attitude valid lines have to be 

connected to the TPU67A. On valid state, the 

signals are +28VDC. On invalid, the signals 

are open. This condition of direct connection 

(without an isolation diode installed) of the 

valid lines to the TPU67A, if not corrected, 

could cause the TPU67A to feed current into 

the open stated valid lines. This prevents the 

flag to appear even if the gyro is invalid, 

providing the flight crew with erroneous 

navigation information. 

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 May 29, 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: Go to 

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, Missouri 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. This 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–2007–27680; Directorate Identifier 

2007–CE–026–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:// 

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 No. 

2007–0059 dated March 5, 2007 

(referred to after this as ‘‘the MCAI’’), to 

correct an unsafe condition for the 

specified products. 

The MCAI states: 

It was detected by the STC holder that in 

earlier installations of the ACASII system 

there were no isolation diodes installed in 

the Heading and Attitude Valid lines. The 

absence of an isolation diode in the valid 

lines can prevent the valid flag to come up 

even if a gyro fault exists. The problem has 

only been detected for Heading Valid lines 

but could equally affect the Attitude Valid 

lines. 

With installation of the ACASII, the 

heading and attitude valid lines have to be 

connected to the TPU67A. On valid state, the 

signals are +28VDC. On invalid, the signals 

are open. This condition of direct connection 

(without an isolation diode installed) of the 

valid lines to the TPU67A, if not corrected, 

could cause the TPU67A to feed current into 

the open stated valid lines. This prevents the 

flag to appear even if the gyro is invalid, 

providing the flight crew with erroneous 

navigation information. 

For the reasons stated above, this 

Airworthiness Directive (AD) requires the 

installation of isolation diodes into the signal 

lines to the TPU67A to prevent reverse feed 

of the valid lines. 

You may obtain further information 

by examining the MCAI in the AD 

docket. 

Relevant Service Information 

Aerotechnic Vertiebs -u. Service 

GmbH has issued Service Bulletin No. 

DO228–119780–0104, Revision 2, dated 

December 21, 2006. The actions 

described in this service information are 

intended to correct the unsafe condition 

identified in the MCAI. 


jlentini on PROD1PC65 with PROPOSALS
Federal Register / Vol. 72, No. 80 / Thursday April 26, 2007 / Proposed Rules 20781 

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 

highlighted in a NOTE within the 

proposed AD. 

Costs of Compliance 

The FAA is not aware of any airplanes 

on the U.S. Registry that have the 

affected equipment installed. All 

airplanes with this equipment included 

in the applicability of this rule currently 

are operated by non-U.S. operators 

under foreign registry; therefore, they 

are not directly affected by this AD 

action at this time. However, the FAA 

considers this rule necessary to ensure 

that the unsafe condition is addressed in 

the event that any of these subject 

airplanes are imported and placed on 

the U.S. Registry. 

Should an affected airplane be 

imported and placed on the U.S. 

Registry, accomplishment of the 

required action would take 

approximately 8 work-hours at an 

average labor rate of $80 per work-hour. 

Required parts would cost about $50 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, the total cost 

impact of this AD would be $690 per 

airplane. 

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 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: 

AEROTECHNIC Vertriebs-u. Service GmbH: 

Docket No. FAA–2007–27680; 

Directorate Identifier 2007–CE–026–AD. 

Comments Due Date 

(a) We must receive comments by May 29, 

2007. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Honeywell CAS67A 

ACAS II systems that are installed on, but not 

limited to, DORNIER LUFTFAHRT GmbH 

Models Dornier 228–100, Dornier 228–101, 

Dornier 228–200, Dornier 228–201, and 

Dornier 228–212 airplanes that: 

(1) Had Supplemental Type Certificate No. 

SA1310 installed prior to January 31, 2005; 

and 

(2) Are certificated in any category. 

Subject 

(d) Air Transport Association of America 

(ATA) Code 34: Navigation. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

It was detected by the STC holder that in 

earlier installations of the ACAS II system 

there were no isolation diodes installed in 

the Heading and Attitude Valid lines. The 

absence of an isolation diode in the valid 

lines can prevent the valid flag to come up 

even if a gyro fault exists. The problem has 

only been detected for Heading Valid lines 

but could equally affect the Attitude Valid 

lines. 

With installation of the ACAS II, the 

heading and attitude valid lines have to be 

connected to the TPU67A. On valid state, the 

signals are +28VDC. On invalid, the signals 

are open. This condition of direct connection 

(without an isolation diode installed) of the 

valid lines to the TPU67A, if not corrected, 

could cause the TPU67A to feed current into 

the open stated valid lines. This prevents the 

flag to appear even if the gyro is invalid, 

providing the flight crew with erroneous 

navigation information. 

For the reasons stated above, this 

Airworthiness Directive (AD) requires the 

installation of isolation diodes into the signal 

lines to the TPU67A to prevent reverse feed 

of the valid lines. 

Actions and Compliance 

(f) Unless already done, within 100 flight 

hours time-in-service (TIS) after the effective 

date of this AD, modify the Honeywell 

CAS67A ACAS II System Installation 

following Aerotechnic Service Bulletin No. 

DO228–119780–0104, Revision 2, dated 

December 21, 2006. 


jlentini on PROD1PC65 with PROPOSALS
20782 Federal Register / Vol. 72, No. 80 / Thursday April 26, 2007 / Proposed Rules 

FAA AD Differences 

Note: This AD differs from the MCAI and/ 

or service information as follows: No 

differences. 

Other FAA AD Provisions 

(g) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Standards Staff, 

FAA, ATTN: Karl Schletzbaum, Aerospace 

Engineer, FAA, Small Airplane Directorate, 

901 Locust, Room 301, Kansas City, Missouri 

64106; telephone: (816) 329–4146; fax: (816) 

329–4090, has the authority to approve 

AMOCs for this AD, if requested using the 

procedures found in 14 CFR 39.19. 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, 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 

(h) Refer to MCAI European Aviation 

Safety Agency (EASA) AD No. 2007–0059, 

dated March 5, 2007; and Service Bulletin 

No. DO228–119780–0104 Revision 2, dated 

December 21, 2006, for related information. 

Issued in Kansas City, Missouri, on April 

20, 2007. 

Charles L. Smalley, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E7–7993 Filed 4–25–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–28015; Directorate 

Identifier 2006–NM–210–AD] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 747–100, 747–100B, 747–100B 

SUD, 747–200B, 747–200C, 747–300, 

747–400, 747–400D, and 747SR Series 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to 

supersede an existing airworthiness 

directive (AD) that applies to all Boeing 

Model 747–100, 747–100B, 747–100B 

SUD, 747–200B, 747–200C, 747–300, 

747–400, 747–400D, and 747SR series 

airplanes. The existing AD currently 

requires repetitive inspections for 

cracking of the station 800 frame 

assembly, and repair if necessary. This 

proposed AD would revise certain 

applicabilities and compliance times in 

the existing AD. This proposed AD 

results from several reports of cracks of 

the station 800 frame assembly on 

airplanes that had accumulated fewer 

total flight cycles than the initial 

inspection threshold in the original AD. 

We are proposing this AD to detect and 

correct fatigue cracks that could extend 

and fully sever the frame, which could 

result in development of skin cracks 

that could lead to rapid 

depressurization of the airplane. 

DATES: We must receive comments on 

this proposed AD by June 11, 2007. 

ADDRESSES: Use one of the following 

addresses to submit comments on this 

proposed AD. 

• DOT Docket Web site: Go to 

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

instructions for sending your comments 

electronically. 

• Government-wide rulemaking Web 

site: Go to http://www.regulations.gov 

and follow the instructions for sending 

your comments electronically. 

• Mail: Docket Management Facility; 

U.S. Department of Transportation, 400 

Seventh Street, SW., Nassif Building, 

Room PL–401, Washington, DC 20590. 

• Fax: (202) 493–2251. 

• 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. 

Contact Boeing Commercial 

Airplanes, P.O. Box 3707, Seattle, 

Washington 98124–2207, for service 

information identified in this proposed 

AD. 

FOR FURTHER INFORMATION CONTACT: Ivan 

Li, Aerospace Engineer, Airframe 

Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 917–6437; 

fax (425) 917–6590. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to submit any relevant 

written data, views, or arguments 

regarding this proposed AD. Send your 

comments to an address listed in the 

ADDRESSES section. Include the docket 

number ‘‘Docket No. FAA–2007–28015; 

Directorate Identifier 2006–NM–210–

AD’’ at the beginning of your comments. 

We specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

the proposed AD. We will consider all 

comments received by the closing date 

and may amend the proposed AD in 

light of those comments. 

We will post all comments we 

receive, without change, to http:// 

dms.dot.gov, including any personal 

information you provide. We will also 

post a report summarizing each 

substantive verbal contact with FAA 

personnel concerning this proposed AD. 

Using the search function of that Web 

site, anyone can find and read the 

comments in any of our dockets, 

including the name of the individual 

who sent the comment (or signed the 

comment on behalf of an association, 

business, labor 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), or may can visit http:// 

dms.dot.gov. 

Examining the Docket 

You may examine the AD docket on 

the Internet at http://dms.dot.gov, or in 

person at the Docket Management 

Facility office between 9 a.m. and 5 p.m. 

Monday through Friday, except Federal 

holidays. The Docket Management 

Facility office (telephone (800) 647–

5227) is located on the plaza level of the 

Nassif Building at the DOT street 

address stated in the ADDRESSES section. 

Comments will be available in the AD 

docket shortly after the Docket 

Management System receives them. 

Discussion 

On May 31, 2006, we issued AD 

2006–12–12, amendment 39–14638 (71 

FR 33595, June 12, 2006), for all Boeing 

Model 747–100, 747–100B, 747–100B 

SUD, 747–200B, 747–200C, 747–300, 

747–400, 747–400D, and 747SR series 

airplanes. That AD requires repetitive 

inspections for cracking of the station 

800 frame assembly, and repair if 

necessary. That AD resulted from 

several reports of cracks of the station 

800 frame assembly on airplanes that 

had accumulated fewer total flight 

cycles than the initial inspection 

threshold in an existing AD that AD 

2006–12–12 superseded. We issued AD 

2006–12–12 to detect and correct fatigue 

cracks that could extend and fully sever 

the frame, which could result in 

development of skin cracks that could 


jlentini on PROD1PC65 with PROPOSALS