13046 Federal Register / Vol. 75, No. 52 / Thursday, March 18, 2010 / Proposed Rules 

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 AD: 

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. Would 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. You may get a copy 

of this summary at the address listed 

under ADDRESSES. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Safety. 

The Proposed Amendment 

Under the authority delegated to me 

by the Administrator, the Federal 

Aviation Administration proposes to 

amend 14 CFR part 39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive: 

CFM International, S.A.: Docket No. FAA– 

2010–0026; Directorate Identifier 2010– 

NE–03–AD. 

Comments Due Date 

(a) The Federal Aviation Administration 

(FAA) must receive comments on this 

airworthiness directive (AD) action by May 

17, 2010. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to CFM International 

CFM56–5, –5B, and –7B series turbofan 

engines with stage 3 low-pressure turbine 

(LPT) disks installed with the following 

serial numbers, (S/Ns) DE255844, DE256388, 

DE256622, DE256623, DE256625, DE256627, 

DE256628, DE256631, and DE256637. The –5 

and –5B series engines are installed on, but 

not limited to, Airbus A318, A319, A320, 

A321, and A340 airplanes, and the –7B series 

engines are installed on, but not limited to, 

Boeing 737 series airplanes. 

Unsafe Condition 

(d) This AD results from the discovery of 

a material nonconformity requiring removal 

of the disk before the certified disk life of 

certain stage 3 LPT disks. We are issuing this 

AD to prevent uncontained failure of the 

stage 3 LPT disk and damage to the airplane. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed within 

the compliance time specified unless the 

actions have already been done. 

Removal of Affected Stage 3 LPT Disks From 

Service 

(f) Before accumulating 9,500 cycles-sincenew, remove stage 3 LPT disks from service. 

(g) After the effective date of this AD do 

not reinstall any stage 3 LPT disk removed 

from service per paragraph (f) of this AD into 

any engine. 

Alternative Methods of Compliance 

(h) The Manager, Engine Certification 

Office, has the authority to approve 

alternative methods of compliance for this 

AD if requested using the procedures found 

in 14 CFR 39.19. 

Related Information 

(i) Contact Antonio Cancelliere, Aerospace 

Engineer, Engine Certification Office, FAA, 

Engine & Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; e-mail: antonio.cancelliere@faa.gov; 

telephone (781) 238–7751; fax (781) 238– 

7199, for more information about this AD. 

(j) CFM International, S.A. Service Bulletin 

(SB) No. CFM56–5B S/B 72–0733, dated 

October 26, 2009, and SB No. CFM56–7B 

S/B 72–0743, dated October 26, 2009, pertain 

to the subject of this AD. Contact CFM 

International, Technical Publications 

Department, 1 Neumann Way, Cincinnati, 

OH 45215; telephone (513) 552–2800; fax 

(513) 552–2816, for a copy of this service 

information. 

Issued in Burlington, Massachusetts, on 

March 11, 2010. 

Peter A. White, 

Assistant Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–5861 Filed 3–17–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0232; Directorate 

Identifier 2009–NM–032–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 747–200C, –200F, 

–400, –400D, and –400F 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 certain 

Model 747–200C, –200F, –400, –400D, 

and –400F series airplanes. The existing 

AD currently requires repetitive 

inspections for cracks in the 

overlapping (upper) skin, upper fastener 

row of the lap joints of the fuselage skin 

in sections 41, 42, and 46; and related 

investigative and corrective actions, if 

necessary. This proposed AD would 

expand the inspection area in the 

existing AD, and add a modification of 

certain lap joints and certain post-repair 

inspections of the lap joints. 

Accomplishing the modification would 

end the repetitive inspections required 

by the existing AD for the length of lap 

joint that is modified. This proposed AD 

results from a structural review of 

affected skin lap joints for widespread 

fatigue damage. We are proposing this 

AD to prevent fatigue cracking in certain 

lap joints, which could result in rapid 

depressurization of the airplane. 

DATES: We must receive comments on 

this proposed AD by May 3, 2010. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

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

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC 20590, between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. 

For service information identified in 

this proposed AD, contact Boeing 


pwalker on DSK8KYBLC1PROD with PROPOSALS
Federal Register / Vol. 75, No. 52 / Thursday, March 18, 2010 / Proposed Rules 13047 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, Washington 98124– 

2207; telephone 206–544–5000, 

extension 1; fax 206–766–5680; e-mail 

me.boecom@boeing.com; Internet 

https://www.myboeingfleet.com. You 

may review copies of the referenced 

service information at the FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington. 

For information on the availability of 

this material at the FAA, call 425–227– 

1221. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.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 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

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 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–2010–0232; Directorate Identifier 

2009–NM–032–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:// 

www.regulations.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 

On February 27, 2006, we issued AD 

2006–05–09, amendment 39–14506 (71 

FR 12122, March 9, 2006), for certain 

Model 747–200C, –200F, –400, –400D, 

and –400F series airplanes. That AD 

requires repetitive inspections for cracks 

in the overlapping (upper) skin, upper 

fastener row of the lap joints of the 

fuselage skin in sections 41, 42, and 46; 

and related investigative and corrective 

actions, if necessary. That AD resulted 

from fatigue tests and an analysis that 

identified areas of the fuselage lap joints 

where fatigue cracks can occur. We 

issued that AD to detect and correct 

fatigue cracks in the overlapping (upper) 

skin, upper fastener row of the lap joints 

of the fuselage skin in sections 41, 42, 

and 46, which could adversely affect the 

structural integrity of the airplane. 

Actions Since Existing AD Was Issued 

Since we issued AD 2006–05–09, the 

manufacturer has conducted a structural 

review of affected skin lap joints for 

widespread fatigue damage, and has 

identified additional necessary 

inspection and modification actions. It 

is recommended that all lap joints with 

an upper skin thickness of 0.09 inch or 

less should be inspected; therefore, the 

inspection area has been expanded to 

include a new Area 2 (i.e., the lap joint 

at STA 450, S–0 to S1L and the S–4L lap 

joint between STA 1970 and STA 2000). 

It is also recommended that lap joints in 

sections 41 and 42 with an upper skin 

thickness of 0.071 inch or less should be 

modified; and post-repair inspections 

have been identified. 

Revised Service Information 

We have reviewed Boeing Alert 

Service Bulletin 747–53A2499, Revision 

1, dated October 30, 2008. That service 

bulletin describes procedures for 

repetitive external surface high 

frequency eddy current (HFEC), external 

low frequency eddy current (LFEC), and 

internal LFEC inspections for cracks in 

the overlapping (upper) skin, upper 

fastener row of the lap joints of the 

fuselage skin in sections 41, 42, and 46; 

and related investigative and corrective 

actions, if necessary. 

For airplanes on which any crack is 

found, the related investigative actions 

include open-hole HFEC inspections of 

the fastener holes to find further 

cracking. The corrective actions include 

repairing any cracked lap joint and an 

open-hole HFEC inspection of the skin 

at all existing fastener locations 

common to the repair. The corrective 

actions also include repairing any crack 

found during accomplishment of the 

inspections. 

That service bulletin also describes a 

modification of the lap joints in sections 

41 and 42. The modification includes 

fabricating and installing skin doublers 

on affected lap joints. 

The compliance time for 

accomplishing the new Area 2 

inspections is before the accumulation 

of 22,000 total flight cycles, or within 

3,000 flight cycles after the last HFEC 

inspection of that area, as specified in 

the Boeing Model 747 Supplemental 

Structural Inspection Document, or 

within 1,000 flight cycles from the date 

on Revision 1 of the service bulletin; 

whichever occurs latest. 

For areas on which a lap joint repair 

was installed and the repair doubler is 

greater than or equal to 40 inches long, 

that service bulletin describes 

procedures for repetitive internal 

surface HFEC inspections of certain 

doublers of the lap joints for cracks. The 

compliance time for accomplishing the 

inspections is within 15,000 flight 

cycles after the repair was installed. 

That service bulletin specifies 

repeating the applicable inspection 

every 3,000 flight cycles, or every 1,500 

flight cycles for airplanes that have 

accumulated 30,000 total flight cycles or 

more. 

The compliance time for 

accomplishing the new lap joint 

modification is before the accumulation 

of 30,000 total flight cycles, or within 

3,000 flight cycles from the date of 

Revision 1 of the service bulletin, 

whichever is later. Accomplishing this 

modification eliminates the need for the 

repetitive inspections for the length of 

lap joint that is modified. 

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– 

05–09 and would retain the 

requirements of the existing AD. This 

proposed AD would also require 

accomplishing the actions specified in 

the service information described 

previously. 

Explanation of Change Made to This 

Proposed AD 

Boeing Commercial Airplanes has 

received an Organization Designation 

Authorization (ODA), which replaces 

the previous designation as a Delegation 

Option Authorization (DOA) holder. We 

have revised paragraph (n)(3) of this 

proposed AD to add delegation of 

authority to Boeing Commercial 

Airplanes ODA to approve an 

alternative method of compliance for 

any repair required by this AD. 

Change to Existing AD 

This proposed AD would retain all 

requirements of AD 2006–05–09. Since 

AD 2006–05–09 was issued, we have 


pwalker on DSK8KYBLC1PROD with PROPOSALS
13048 Federal Register / Vol. 75, No. 52 / Thursday, March 18, 2010 / Proposed Rules 

added a new paragraph to include the 

ATA code. As a result, the 

corresponding paragraph identifiers 

have changed in this proposed AD, as 

listed in the following table: 

REVISED PARAGRAPH IDENTIFIERS

Requirement in AD 

2006–05–09 

Corresponding requirement 

in this proposed AD 

paragraph (f) paragraph (g) 

paragraph (g) paragraph (h) 

paragraph (h) paragraph (l) 

Costs of Compliance 

There are about 735 airplanes of the 

affected design in the worldwide fleet. 

This proposed AD would affect about 96 

airplanes of U.S. registry. 

The actions that are required by AD 

2006–05–09 and retained in this 

proposed AD take about 541 work hours 

per airplane, at an average labor rate of 

$85 per work hour. Based on these 

figures, the estimated cost of the 

currently required actions is $45,985 per 

airplane, per inspection cycle. 

The new proposed Area 2 inspections 

would take about 124 work hours per 

airplane, at an average labor rate of $85 

per work hour. Based on these figures, 

the estimated cost of the new 

inspections specified in this proposed 

AD for U.S. operators is $1,011,880, or 

$10,540 per airplane, per inspection 

cycle. 

The new proposed modification 

would take about 4,799 work hours per 

airplane, at an average labor rate of $85 

per work hour. Required parts costs per 

airplane would be minimal. Based on 

these figures, the estimated cost of the 

new actions specified in this proposed 

AD for U.S. operators is $39,159,840, or 

$407,915 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 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, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

2. The FAA amends § 39.13 by 

removing amendment 39–14506 (71 FR 

12122, March 9, 2006) and adding the 

following new AD: 

The Boeing Company: Docket No. FAA– 

2010–0232; Directorate Identifier 2009– 

NM–032–AD. 

Comments Due Date 

(a) The FAA must receive comments on 

this AD action by May 3, 2010. 

Affected ADs 

(b) This AD supersedes AD 2006–05–09. 

Applicability 

(c) This AD applies to The Boeing 

Company Model 747–200C, –200F, –400, 

–400D, and –400F series airplanes, 

certificated in any category; as identified in 

Boeing Alert Service Bulletin 747–53A2499, 

Revision 1, dated October 30, 2008. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 53: Fuselage. 

Unsafe Condition 

(e) This AD results from a structural review 

of affected skin lap joints for widespread 

fatigue damage. The Federal Aviation 

Administration is issuing this AD to prevent 

fatigue cracking in certain lap joints, which 

could result in rapid depressurization of the 

airplane. 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Restatement of Requirements of AD 2006– 

05–09, With Revised Service Information 

Initial Inspections and Related Investigative 

and Corrective Actions 

(g) For airplanes identified in Boeing Alert 

Service Bulletin 747–53A2499, dated August 

11, 2005: At the applicable time specified in 

Table 1 of this AD, do an external surface 

high frequency eddy current (HFEC), external 

low frequency eddy current (LFEC), and 

internal LFEC inspection, as applicable, for 

cracks in the overlapping (upper) skin, upper 

fastener row of the lap joints of the fuselage 

skin in sections 41, 42, and 46, and any 

applicable related investigative and 

corrective actions by doing all of the actions 

in accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–53A2499, dated August 11, 2005; or 

Revision 1, dated October 30, 2008. Do any 

applicable related investigative and 

corrective actions before further flight. As of 

the effective date of this AD, only Revision 

1, dated October 30, 2008, of Boeing Alert 

Service Bulletin 747–53A2499 may be used. 


pwalker on DSK8KYBLC1PROD with PROPOSALS
Federal Register / Vol. 75, No. 52 / Thursday, March 18, 2010 / Proposed Rules 13049 

TABLE 1—INITIAL COMPLIANCE TIME

For airplanes on which Structural Significant 

Items (SSIs) F–25G, F–25H, and F–25I— Inspect— 

(1) Have not been inspected in accordance with 

paragraph (i) of AD 2004–07–22 R1, amendment 39–15326, using the HFEC method.

Before the accumulation of 22,000 total flight cycles, or within 1,000 flight cycles after April 13, 

2006 (the effective date of AD 2006–05–09), whichever occurs later. 

(2) Have been inspected in accordance with 

paragraph (i) of AD 2004–07–22 R1, using 

the HFEC method.

Within 3,000 flight cycles after the most recent supplemental structural inspection document 

(SSID) inspection of each applicable structural significant item (as given in Boeing Document D6–35022, ‘‘SSID for Model 747 Airplanes,’’ Revision G, dated December 2000), or 

within 1,000 flight cycles after April 13, 2006, whichever occurs later. 

Repetitive Inspections 

(h) Repeat the applicable inspections 

required by paragraph (g) of this AD 

thereafter at intervals not to exceed those 

specified in paragraph 1.E., ‘‘Compliance,’’ 

(including the note) of Boeing Alert Service 

Bulletin 747–53A2499, dated August 11, 

2005; or Revision 1, dated October 30, 2008. 

As of the effective date of this AD, only 

Revision 1, dated October 30, 2008, of Boeing 

Alert Service Bulletin 747–53A2499 may be 

used. 

New Requirements of This AD 

Repetitive Inspections/Investigative and 

Corrective Actions 

(i) For all airplanes: Do an external HFEC 

inspection of the lap joints in Sections 41, 42, 

and 46 for cracks, by doing all the actions, 

including all applicable related investigative 

and corrective actions, specified in the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2499, Revision 1, 

dated October 30, 2008. Do the inspection at 

the applicable time specified in paragraph 

1.E. of Boeing Alert Service Bulletin 747– 

53A2499, Revision 1, dated October 30, 2008; 

except as required by paragraph (m) of this 

AD. Do all applicable related investigative 

and corrective actions before further flight. 

Repeat the inspection thereafter at the times 

specified in paragraph 1.E. of Boeing Alert 

Service Bulletin 747–53A2499, Revision 1, 

dated October 30, 2008. Accomplishment of 

the inspections required by this paragraph 

terminates the inspections required by 

paragraphs (g) and (h) of this AD. 

(j) For areas on which a lap joint repair was 

installed and the repair doubler is greater 

than or equal to 40 inches long: Do initial 

and repetitive internal HFEC inspections for 

cracks by doing all the actions, including all 

applicable corrective actions, specified in the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2499, Revision 1, 

dated October 30, 2008, except as required by 

paragraph (l) of this AD. Do the inspections 

and corrective actions at the times specified 

in paragraph 1.E. of Boeing Alert Service 

Bulletin 747–53A2499, Revision 1, dated 

October 30, 2008, except as required by 

paragraph (m) of this AD. 

Terminating Action 

(k) Modify the applicable lap joints in 

sections 41 and 42 by doing all the applicable 

actions specified in the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–53A2499, Revision 1, dated October 30, 

2008, at the time specified in paragraph 1.E. 

of Boeing Alert Service Bulletin 747– 

53A2499, Revision 1, dated October 30, 2008; 

except as required by paragraphs (l) and (m) 

of this AD. Accomplishing this modification 

terminates the repetitive inspections of the 

skin lap joints in sections 41 and 42 required 

by paragraphs (i) and (j) of this AD for the 

length of lap joint that is modified. 

Exceptions to Service Bulletin Procedures 

(l) Where Boeing Alert Service Bulletin 

747–53A2499, Revision 1, dated October 30, 

2008, specifies to contact Boeing for 

appropriate action, before further flight, 

repair the crack using a method approved in 

accordance with the procedures specified in 

paragraph (n) of this AD. 

(m) Where Boeing Alert Service Bulletin 

747–53A2499, Revision 1, dated October 30, 

2008, specifies a compliance time after the 

date of the service bulletin, this AD requires 

compliance within the specified compliance 

time after the effective date of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(n)(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. Send information to Ivan Li, 

Aerospace Engineer, Airframe Branch, ANM– 

120S, FAA, Seattle ACO, 1601 Lind Avenue, 

SW., Renton, Washington 98057–3356; 

telephone (425) 917–6437; fax (425) 917– 

6590. Information may be e-mailed to: 9- 

ANM-Seattle-ACO-AMOC-Requests@faa.gov. 

(2) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Before using any approved AMOC on 

any airplane to which the AMOC applies, 

notify your principal maintenance inspector 

(PMI) or principal avionics inspector (PAI), 

as appropriate, or lacking a principal 

inspector, your local Flight Standards District 

Office. The AMOC approval letter must 

specifically reference this AD. 

(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 the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) or other 

person 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 and the 

approval must specifically refer to this AD. 

(4) AMOCS approved previously in 

accordance with AD 2006–05–09 are 

approved as alternative methods of 

compliance with the corresponding 

requirements of this AD. 

Issued in Renton, Washington, on March 

10, 2010. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–5940 Filed 3–17–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

[Docket No. FAA–2010–0049; Airspace 

Docket No. 08–AWA–1] 

RIN 2120–AA66 

Proposed Modification of Class B 

Airspace; Charlotte, NC 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM); correction. 

SUMMARY: This action provides the 

graphic chart for the proposed rule 

published in the Federal Register of 

March 3, 2010, regarding the 

modification of Class B airspace, 

Charlotte, NC. This correction adds the 

chart that was inadvertently omitted 

from the NPRM. 

DATES: Comments must be received on 

or before May 3, 2010. 

FOR FURTHER INFORMATION CONTACT: Paul 

Gallant, Airspace and Rules Group, 

Office of System Operations Airspace 

and AIM, Federal Aviation 

Administration, 800 Independence 

Avenue, SW., Washington, DC 20591; 

telephone: (202) 267–8783. 

Correction 

In proposed rule FR Doc. 2010–4377, 

beginning on page 9538 in the issue of 

March 3, 2010, make the following 

correction: On page 9544 in the first 

column, add the attached graphic chart 

before the Issue Date line. 


pwalker on DSK8KYBLC1PROD with PROPOSALS