Federal Register / Vol. 72, No. 15 / Wednesday, January 24, 2007 / Rules and Regulations 3047 

doing a local repair) that are 12 inches or less 

along the longeron: Within 15,000 flight 

cycles after doing the optional action, use 

only the external general visual inspection 

method for discrepancies of the unrepaired 

areas at longeron 28 between the bolted 

connection of the tail section to forward of 

the flat aft pressure bulkhead, on both the left 

and right sides, and do all applicable related 

investigative and corrective actions before 

further flight. Do all actions in accordance 

with the Accomplishment Instructions of 

Boeing Alert Service Bulletin DC8–53A080, 

dated June 22, 2004. Repeat the external 

general visual inspection thereafter at 

intervals not to exceed 5,000 flight cycles. 

(ii) For repairs (full-length preventive 

modification, doing a full-length repair, or 

doing a local repair) that are more than 12 

inches in length along the longeron: Within 

15,000 flight cycles after doing the optional 

action, use only the low-frequency eddy 

current (LFEC) inspection method for cracks 

of the unrepaired areas at longeron 28 

between the bolted connection of the tail 

section to forward of the flat aft pressure 

bulkhead, on both the left and right sides, 

and do all applicable related investigative 

and corrective actions before further flight. 

Do all actions in accordance with Boeing DC–

8 Service Rework Drawing SR08530032, 

dated January 13, 2004, including Boeing 

Parts List PL SR08530032, dated January 7, 

2004, Boeing Advance Engineering Order, 

Advanced Drawing Change A, dated April 1, 

2004, and Boeing Engineering Order, dated 

January 13, 2004. Repeat the LFEC inspection 

thereafter at intervals not to exceed 10,000 

flight cycles, using only LFEC inspection 

outward along all four edges of the doubler. 

Reporting of Results 

(e) Submit a report of positive findings of 

the inspections required by paragraphs (b) 

and (d) of this AD to Boeing Commercial 

Airplanes, Manager, Structure/Payloads, 

Technical and Fleet Support, Service 

Engineering/Commercial Aviation Services, 

Long Beach Division, 3855 Lakewood 

Boulevard, Long Beach, California 90846, at 

the applicable time specified in paragraph 

(e)(1) or (e)(2) of this AD. The report must 

include the inspection results, a description 

of any discrepancies found, the airplane 

fuselage number, and the total number of 

landings and flight hours on the airplane. 

Information collection requirements 

contained in this AD have been approved by 

the Office of Management and Budget (OMB) 

under the provisions of the Paperwork 

Reduction Act (44 U.S.C. 3501 et seq.) and 

have been assigned OMB Control Number 

2120–0056. 

(1) For airplanes on which the inspection 

is accomplished after the effective date of 

this AD: Submit the report within 30 days 

after performing the inspection. 

(2) For airplanes on which the inspection 

was accomplished prior to the effective date 

of this AD: Submit the report within 30 days 

after the effective date of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(f)(1) In accordance with 14 CFR 39.19, the 

Manager, Los Angeles Aircraft Certification 

Office (ACO), FAA, is authorized to approve 

AMOCs for this AD. 

(2) Before using any AMOC approved in 

accordance with § 39.19 on any airplane to 

which the AMOC applies, notify the 

appropriate principal inspector in the FAA 

Flight Standards Certificate Holding District 

Office. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD, if it is approved by an 

Authorized Representative for the Boeing 

Commercial Airplanes Delegation Option 

Authorization Organization who has been 

authorized by the Manager, Los Angeles 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane and 14 

CFR 25.571, Amendment 45, and the 

approval must specifically refer to this AD. 

Incorporation by Reference 

(g) Unless otherwise specified in this AD, 

the actions must be done in accordance with 

Boeing Alert Service Bulletin DC8–53A080, 

dated June 22, 2004; and Boeing DC–8 

Service Rework Drawing SR08530032, dated 

January 13, 2004, including Boeing Parts List 

PL SR08530032, dated January 7, 2004, 

Boeing Advance Engineering Order, 

Advanced Drawing Change A, dated April 1, 

2004, and Boeing Engineering Order, dated 

January 13, 2004; as applicable. This 

incorporation by reference was approved by 

the Director of the Federal Register in 

accordance with 5 U.S.C. 552(a) and 1 CFR 

part 51. To get copies of this service 

information, contact Boeing Commercial 

Airplanes, Long Beach Division, 3855 

Lakewood Boulevard, Long Beach, California 

90846, Attention: Data and Service 

Management, Dept. C1–L5A (D800–0024). To 

inspect copies of this service information, go 

to the FAA, Transport Airplane Directorate, 

1601 Lind Avenue, SW., Renton, 

Washington; to the FAA, Los Angeles 

Aircraft Certification Office, 3960 Paramount 

Boulevard, Lakewood, California; or to the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at the NARA, 

call (202) 741–6030, or go to http:// 

www.archives.gov/federal_register/ 

code_of_federal_regulations/ 

ibr_locations.html. 

Effective Date 

(h) This amendment becomes effective on 

February 28, 2007. 

Issued in Renton, Washington, on January 

5, 2007. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E7–710 Filed 1–23–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2006–26694; Directorate 

Identifier 2006–CE–91–AD; Amendment 

39–14899; AD 2007–02–12] 

RIN 2120–AA64 

Airworthiness Directives; Reims 

Aviation S.A. F406 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: 

* * * several reports regarding discovery of 

cracks about the rudder pulley bracket part 

number 6015511–1. This pulley bracket is 

installed with the ‘‘Camera Hole’’ option. 

This AD requires actions that are 

intended to address the unsafe 

condition described in the MCAI. 

DATES: This AD becomes effective 

February 13, 2007. 

The Director of the Federal Register 

approved the incorporation by reference 

of REIMS AVIATION INDUSTRIES 

Service Bulletin No. F406–58, Rev. 1, 

dated October 27, 2006, listed in this 

AD as of February 13, 2007. 

We must receive comments on this 

AD by February 23, 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 


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3048 Federal Register / Vol. 72, No. 15 / Wednesday, January 24, 2007 / Rules and Regulations 

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–

5227) is in the ADDRESSES section. 

Comments will be available in the AD 

docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Mike Kiesov, Aerospace Engineer, FAA, 

Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri, 

64106; telephone: (816) 329–4144; 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 AD references the MCAI and 

related service information that we 

considered in forming the engineering 

basis to correct the unsafe condition. 

The AD contains text copied from the 

MCAI and for this reason might not 

follow our plain language principles. 

Discussion 

The Direction Genorale de L’Aviation 

Civile (DGAC), which is the aviation 

authority for France, has issued AD No. 

F–2005–080, Issue date: May 25, 2005, 

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

correct an unsafe condition for the 

specified products. 

The MCAI states: 

* * * several reports regarding discovery of 

cracks about the rudder pulley bracket part 

number 6015511–1. This pulley bracket is 

installed with the ‘‘Camera Hole’’ option. 

This condition, if left uncorrected, could 

result in the loss of rudder control on the 

airplane. 

The MCAI requires: 

Prior to the next flight, perform initial 

inspection as specified in the REIMS 

AVIATION INDUSTRIES Service Bulletin 

No. F406–58. If no cracking is found 

following the initial inspection, repeat the 

inspection every 50 flight hours or 1 month 

whichever occurs first and at the latest 

within the next 100 flight hours or 2 months 

after the effective date of this AD whichever 

occurs first, install the modified pulley 

bracket as specified in the REIMS AVIATION 

INDUSTRIES Service Bulletin No F406–58. If 

any cracking is found, prior to next flight, 

install the modified pulley bracket as 

specified in the REIMS AVIATION 

INDUSTRIES Service Bulletin No F406–58. 

You may obtain further information 

by examining the MCAI in the AD 

docket. 

Relevant Service Information 

Reims Aviation S.A. has issued 

REIMS AVIATION INDUSTRIES Service 

Bulletin No. F406–58, Rev. 1, dated 

October 27, 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 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 undetected cracks in the 

pulley bracket could result in rudder 

control failure. 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–2006–26694; 

Directorate Identifier 2006–CE–91–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:// 

dms.dot.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. 


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Federal Register / Vol. 72, No. 15 / Wednesday, January 24, 2007 / Rules and Regulations 3049 

For the reasons discussed above, I 

certify that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

(2) Is not a ‘‘significant rule’’ under 

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. 

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: 

2007–02–12 Reims Aviation S.A.: 

Amendment 39–14899; Docket No. 

FAA–2006–26694; Directorate Identifier 

2006–CE–91–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective February 13, 2007. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to the following model 

and serial number airplanes, certificated in 

any category. 

Model Serial Nos. 

F406 ............................ 0002, 0003, 0004, 0006, 0008, 0009, 0010, 0012, 0013, 0017, 0024, 0025, 0039, 0042, 0044, 0045, 0066, 0070, 0073, 

0074, 0075, 0077, 0080 through 0090, and 0092. 

Reason 

(d) The mandatory continuing 

airworthiness information (MCAI) states: 

* * * several reports regarding discovery of 

cracks about the rudder pulley bracket part 

number 6015511–1. This pulley bracket is 

installed with the ‘‘Camera Hole’’ option. 

This condition, if left uncorrected, could 

result in the loss of rudder control on the 

airplane. 

Actions and Compliance 

(e) Unless already done, do the following 

actions. 

(1) Within the next 10 hours time-inservice (TIS) after February 13, 2007. (the 

effective of this AD), perform the initial 

inspection as specified in REIMS AVIATION 

INDUSTRIES Service Bulletin No. F406–58, 

Rev. 1, dated October 27, 2006. 

(2) If no cracking is found following the 

initial inspection required in paragraph (e)(1) 

of this AD, repeat the inspection every 50 

flight hours or 1 month, whichever occurs 

first, until the conditions specified in 

paragraph (e)(3) of this AD are met. 

(3) Within the next 100 hours TIS or 2 

months after February 13, 2007. (the effective 

of this AD), whichever occurs first, install the 

modified pulley bracket as specified in 

REIMS AVIATION INDUSTRIES Service 

Bulletin No F406–58, Rev. 1, dated October 

27, 2006. 

(4) If any cracking is found during the 

inspection required in paragraph (e)(1) of this 

AD, prior to next flight, install the modified 

pulley bracket as specified in REIMS 

AVIATION INDUSTRIES Service Bulletin No 

F406–58, Rev. 1, dated October 27, 2006. 

(5) The modified pulley bracket specified 

in REIMS AVIATION INDUSTRIES Service 

Bulletin No F406–58, Rev. 1, dated October 

27, 2006, may be installed at any time after 

the inspection required in paragraph (e)(1) of 

this AD, but must be installed prior to further 

flight if cracking is found. 

FAA AD Differences 

Note: This AD differs from the MCAI and/ 

or service information as follows: No 

differences. 

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: 

Mike Kiesov, Aerospace Engineer, 901 

Locust, Room 301, Kansas City, Missouri 

64106; telephone: (816) 329–4144; 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 Direction Ge ́ne ́rale de 

L’Aviation Civile AD No. F–2005–080, Issue 

date: May 25, 2005, and REIMS AVIATION 

INDUSTRIES Service Bulletin No. F406–58, 

Rev. 1, dated October 27, 2006, for related 

information. 

Material Incorporated by Reference 

(h) You must use REIMS AVIATION 

INDUSTRIES Service Bulletin No. F406–58, 

Rev. 1, dated October 27, 2006, 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 REIMS AVIATION 

INDUSTRIES, Ae ́rodrome de Reims Prunay, 

51360 Prunay, France, A l’attention du 

Support Client; telephone 03.26.48.46.53; 

fax: 03.26.49.18.57. 

(3) You may review copies at the FAA, 

Central Region, Office of the Regional 

Counsel, 901 Locust, Kansas City, Missouri 

64106; 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/ 

code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Kansas City, Missouri on January 

12, 2007. 

Kim Smith, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. E7–774 Filed 1–23–07; 8:45 am] 

BILLING CODE 4910–13–P 


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