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 


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Federal Register / Vol. 72, No. 80 / Thursday April 26, 2007 / Proposed Rules 20783 

lead to rapid depressurization of the 

airplane. 

Actions Since Existing AD Was Issued 

Since we issued AD 2006–12–12, 

errors have been found in the 

applicability of paragraphs (f) and (g), 

and the compliance times in Tables 1 

and 2 of that AD. Therefore, we have 

made the following changes: 

• We have removed the Model 747–

200F from paragraphs (f) and (g) of this 

NPRM. The Model 747–200F was not 

included in the applicability of AD 

2006–12–12 because the Model 747–

200F is not subject to the unsafe 

condition. 

• We have added the Model 747SR to 

paragraphs (f) and (g) of this NPRM and 

added a new Table 2 to accommodate it. 

These airplanes were identified in the 

main applicability in paragraph (c) of 

AD 2006–12–12. 

• We have removed the Model 747–

100B SUD from paragraphs (f) and (g) of 

this NPRM because they are not subject 

to the requirements of AD 2001–14–22 

(the AD that was superseded by AD 

2006–12–12). 

• We have revised the thresholds in 

paragraphs (f)(2), (f)(3), (h)(2), and (h)(3) 

of this NPRM to correct an inadvertent 

error in the compliance times. 

FAA’s Determination and Requirements 

of the Proposed AD 

We have evaluated all pertinent 

information and identified an unsafe 

condition that is likely to develop on 

other airplanes of the same type design. 

For this reason, we are proposing this 

AD, which would supersede AD 2006–

12–12 and would retain the 

requirements of the existing AD. This 

proposed AD would also revise certain 

applicabilities and compliance times in 

the existing AD. 

Costs of Compliance 

There are about 900 airplanes of the 

affected design in the worldwide fleet. 

This proposed AD would affect about 

156 airplanes of U.S. registry. 

The repetitive inspections would take 

between 12 and 14 work hours per 

airplane, depending on the airplane 

configuration. The average labor rate is 

$80 per work hour. Based on these 

figures, the estimated cost of the 

currently required actions is between 

$149,760 and $174,720, or between 

$960 and $1,120 per airplane, per 

inspection cycle. 

The repetitive inspections of the 

expanded area would take between 18 

and 20 work hours per airplane, at an 

average labor rate of $80 per work hour. 

Based on these figures, the estimated 

cost of the new actions specified in this 

proposed AD for U.S. operators is 

between $224,640 and $249,600, or 

between $1,440 and $1,600 per airplane, 

per inspection cycle. 

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 have 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 that the 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. See the ADDRESSES section 

for a location to examine the regulatory 

evaluation. 

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 Federal Aviation 

Administration (FAA) amends § 39.13 

by removing amendment 39–14638 (71 

FR 33595, June 12, 2006) and adding the 

following new airworthiness directive 

(AD): 

Boeing: Docket No. FAA–2007–28015; 

Directorate Identifier 2006–NM–210–AD. 

Comments Due Date 

(a) The FAA must receive comments on 

this AD action by June 11, 2007. 

Affected ADs 

(b) This AD supersedes AD 2006–12–12. 

Applicability 

(c) This AD 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, certificated 

in any category. 

Unsafe Condition 

(d) This 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 existing AD. We are issuing 

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. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Requirements of AD 2006–12–12 With 

Revised Appicabilities and Thresholds 

Repetitive Inspections 

(f) For Boeing Model 747–100, 747–100B, 

747–200B, 747–200C, and 747SR series 

airplanes, as identified in Boeing Alert 

Service Bulletin 747–53A2451, including 

Appendix A, dated October 5, 2000: Do 

detailed, surface high-frequency eddy current 

(HFEC), and open-hole HFEC inspections, as 

applicable, for cracking of the station 800 

frame assembly (including the inner chord 

strap, angles, and exposed web) between 

stringers 14 and 18, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2451, including 

Appendix A, dated October 5, 2000; or 

Boeing Alert Service Bulletin 747–53A2451, 

Revision 1, dated November 10, 2005; after 

the effective date of this AD, only Revision 

1 of the service bulletin may be used. Except 

as provided by paragraph (g) of this AD, do 

the inspection at the applicable time 

specified in Table 1 or Table 2 of this AD, 

as applicable, and repeat the inspections 

thereafter at intervals not to exceed 3,000 


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20784 Federal Register / Vol. 72, No. 80 / Thursday April 26, 2007 / Proposed Rules 

flight cycles until the initial inspections required by paragraph (h) of this AD are 

accomplished. 

TABLE 1.—COMPLIANCE TIMES FOR BOEING MODEL 747–100, 747–100B, 747–200B, AND 747–200C SERIES

AIRPLANES

Total flight cycles as of August 30, 2001 (the effective date of AD 

2001–14–22, amendment 39–12333, which was superseded by AD 

2006–12–12) 

Do the inspection in paragraph (f) of this AD at this time 

(1) Fewer than 19,000 .............................................................................. Before the accumulation of 19,000 total flight cycles, or within 1,500 

flight cycles after August 30, 2001, whichever comes later. 

(2) 19,000 or more, but 24,250 or fewer .................................................. Within 1,500 flight cycles or 12 months after August 30, 2001, whichever comes first. 

(3) 24,251 or more ................................................................................... Within 750 flight cycles or 12 months after August 30, 2001, whichever 

comes first. 

TABLE 2.—COMPLIANCE TIMES FOR BOEING MODEL 747SR SERIES AIRPLANES

Total flight cycles as of the effective date of this AD Do the inspection in paragraph (f) of this AD at this time 

(4) Fewer than 19,000 .............................................................................. Before the accumulation of 19,000 total flight cycles, or within 1,500 

flight cycles after the effective date of this AD, whichever comes 

later. 

(5) 19,000 or more, but 24,250 or fewer .................................................. Within 1,500 flight cycles or 12 months after the effective date of this 

AD, whichever comes first. 

(6) 24,251 or more ................................................................................... Within 750 flight cycles or 12 months after the effective date of this AD, 

whichever comes first. 

Adjustments to Compliance Time: Cabin 

Differential Pressure 

(g) For Boeing Model 747–100, 747–100B, 

747–200B, and 747–200C series airplanes, as 

identified in Boeing Alert Service Bulletin 

747–53A2451, including Appendix A, dated 

October 5, 2000, that were inspected before 

July 17, 2006 (the effective date of AD 2006–

12–12); and for Boeing Model 747SR 

airplanes, as identified in Boeing Alert 

Service Bulletin 747–53A2451, that were 

inspected before the effective date of this AD: 

Except as provided by paragraph (i) of this 

AD, for the purposes of calculating the 

compliance threshold and repetitive interval 

for the actions required by paragraph (f) of 

this AD, the number of flight cycles in which 

cabin differential pressure is at 2.0 pounds 

per square inch (psi) or less need not be 

counted when determining the number of 

flight cycles that have occurred on the 

airplane, provided that the flight cycles with 

momentary spikes in cabin differential 

pressure above 2.0 psi are included as full 

pressure cycles. For this provision to apply, 

all cabin pressure records must be 

maintained for each airplane: No fleetaveraging of cabin pressure is allowed. 

Repetitive Inspections of Expanded Area at a 

New Reduced Threshold 

(h) For all airplanes, at the applicable time 

specified in Table 3 of this AD, except as 

provided by paragraph (i) of this AD, do the 

following inspections of the station 800 

frame assembly in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2451, Revision 1, 

dated November 10, 2005: A detailed 

inspection for cracking of the inner chord 

strap, angles, and exposed web adjacent to 

the inner chords on the station 800 frame 

between stringer 14 and stringer 18; and 

surface HFEC and open-hole HFEC 

inspections for cracking of the inner chord 

strap and angles. Do the initial inspections at 

the applicable time specified in Table 3 of 

this AD, and repeat the inspections thereafter 

at intervals not to exceed 3,000 flight cycles. 

Accomplishing the initial inspections 

required by this paragraph terminates the 

inspection requirements of paragraph (f) of 

this AD. 

TABLE 3.—REVISED COMPLIANCE TIMES

Total flight cycles as of July 17, 2006— Do the inspections in paragraph (h) of this AD at this time—

(1) Fewer than 16,000 .............................................................................. Before the accumulation of 16,000 total flight cycles, or within 1,500 

flight cycles after July 17, 2006, whichever comes later. 

(2) 16,000 or more, but 21,250 or fewer .................................................. Within 1,500 flight cycles after July 17, 2006, or within 1,000 flight cycles after the effective date of this AD, whichever comes later. 

(3) 21,251 or more ................................................................................... Within 750 flight cycles after the July 17, 2006 or within 500 flight cycles after the effective date of this AD, whichever comes later. 

Adjustments to Compliance Time: Cabin 

Differential Pressure 

(i) For the purposes of calculating the 

compliance threshold and repetitive interval 

for actions required by paragraphs (f) and (h) 

of this AD, for Boeing Model 747–100, 747–

100B, 747–200B, and 747–200C series 

airplanes, on or after July 17, 2006; and for 

Boeing Model 747SR series airplanes, on or 

after the effective date of this AD: All flight 

cycles, including the number of flight cycles 

in which cabin differential pressure is at 2.0 

psi or less, must be counted when 

determining the number of flight cycles that 

have occurred on the airplane. However, for 

airplanes on which the repetitive interval for 

the actions required by paragraph (f) of this 

AD have been calculated in accordance with 

paragraph (g) of this AD by excluding the 

number of flight cycles in which cabin 

differential pressure is at 2.0 pounds psi or 

less: Continue to adjust the repetitive 

inspection interval in accordance with 

paragraph (g) of this AD until the initial 

inspections required by paragraph (h) of this 

AD are accomplished. Thereafter, no 

adjustment to compliance times based on 

paragraph (g) of this AD is allowed. 

Repair 

(j) If any cracking is detected during any 

inspection required by paragraph (f) or (h) of 

this AD, and the service bulletin specifies to 

contact Boeing for appropriate action: Before 

further flight, repair using a method 

approved in accordance with the procedures 

specified in paragraph (l) of this AD. 


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Federal Register / Vol. 72, No. 80 / Thursday April 26, 2007 / Proposed Rules 20785 

No Report Required 

(k) Although the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–53A2451, including Appendix A, dated 

October 5, 2000; and Boeing Alert Service 

Bulletin 747–53A2451, Revision 1, dated 

November 10, 2005; describe procedures for 

reporting certain information to the 

manufacturer, this AD does not require that 

report. 

Alternative Methods of Compliance (AMOCs) 

(l)(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested in accordance with the procedures 

found in 14 CFR 39.19. 

(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, Seattle ACO, to 

make those findings. For a repair method to 

be approved, the repair must meet the 

certification basis of the airplane. 

(4) AMOCs approved previously in 

accordance with AD 2001–14–22, are 

approved as AMOCs for the corresponding 

provisions of paragraphs (f) and (j) of this 

AD. 

(5) AMOCS approved previously in 

accordance with AD 2006–12–12, are 

approved as alternative methods of 

compliance with this AD. 

Issued in Renton, Washington, on April 19, 

2007. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E7–7978 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–2007–28017; Directorate 

Identifier 2007–NM–005–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A310–203, A310–204, A310–222, A310–

304, A310–322, and A310–324 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), 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: 

* * * some structural areas have been 

identified for which existing recommended 

SB (service bulletin) needs to be rendered 

mandatory. 

As a consequence, and because it has been 

shown that the torque applied to the tension 

bolts connecting the beam (stringer 49) to the 

forward and aft beam extension at FR11 and 

FR17 may be insufficient, this AD renders 

mandatory the replacement of those tension 

bolts, in order to limit the risks of damage or 

corrosion of the specified areas. 

Damage or corrosion of the specified 

areas could result in reduced structural 

integrity of the airplane. 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: 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: Tom 

Stafford, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 227–1622; 

fax (425) 227–1149. 

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–2007–28017; Directorate Identifier 

2007–NM–005–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 based on 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 

Airworthiness Directive 2006–0367, 

dated December 5, 2006 (referred to 

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

unsafe condition for the specified 

products. The MCAI states: 

During the A310 life extension exercise 

performed by Airbus, the Airlines 

Representatives and the Airworthiness 

Authorities, some structural areas have been 

identified for which existing recommended 

SB (service bulletin) needs to be rendered 

mandatory. 


jlentini on PROD1PC65 with PROPOSALS