Federal Register / Vol. 75, No. 7 / Tuesday, January 12, 2010 / Rules and Regulations 1529 

Unsafe Condition 

(e) This AD results from a report of a hole 

in the fuselage skin common to stringer S– 

1 and S–2 left, between STA 827 and STA 

847 on an airplane that diverted to an 

alternate airport due to cabin 

depressurization and subsequent deployment 

of the oxygen masks. We are issuing this AD 

to detect and correct fatigue cracking of the 

fuselage skin panels at the chem-milled 

steps, which could result in sudden fracture 

and failure of the fuselage skin panels, and 

consequent rapid decompression 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. 

Initial and Repetitive Inspections 

(g) Before the accumulation of 35,000 total 

flight cycles, or within 500 flight cycles after 

the effective date of this AD, whichever 

occurs later: Except as provided by paragraph 

(i) of this AD, do an external non-destructive 

inspection (NDI) to detect cracks in the 

fuselage skin along the chem-mill steps at 

stringers S–1 and S–2 right, between STA 

827 and STA 847, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–53A1301, dated 

September 3, 2009. If no cracking is found, 

repeat the inspection thereafter at intervals 

not to exceed 500 flight cycles, except as 

provided by paragraph (i) of this AD. 

Repair 

(h) If any crack is found during any 

inspection required by this AD, and Boeing 

Alert Service Bulletin 737–53A1301, dated 

September 3, 2009, specifies to contact 

Boeing for repair instructions: Before further 

flight, repair the crack using a method 

approved in accordance with the procedures 

specified in paragraph (j) of this AD. 

Optional Terminating Action for Repetitive 

Inspections 

(i) Installing an external repair doubler 

along the chem-milled steps at stringers S– 

1 and S–2 right, between STA 827 and STA 

847, constitutes terminating action for the 

repetitive inspections required by paragraph 

(g) of this AD for the repaired area only, 

provided all of the conditions specified in 

paragraphs (i)(1), (i)(2), and (i)(3) of this AD 

are met. The initial inspection required by 

paragraph (g) of this AD must be 

accomplished. 

(1) The repair is installed after September 

3, 2009; 

(2) The repair was approved by the FAA 

or by a Boeing Company Authorized 

Representative or the Boeing Commercial 

Airplanes Organization Designation 

Authorization (ODA) authorized by the FAA 

to make such findings; and 

(3) The repair extends a minimum of three 

rows of fasteners on each side of the chemmill line in the circumferential direction. 

Alternative Methods of Compliance 

(AMOCs) 

(j)(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 ATTN: 

Wayne Lockett, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

ACO, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone (425) 

917–6447; fax (425) 917–6590. Or, e-mail 

information to 9-ANM-Seattle-ACO-AMOCRequests@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 ODA that 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, and the 

approval must specifically refer to this AD. 

Material Incorporated by Reference 

(k) You must use Boeing Alert Service 

Bulletin 737–53A1301, dated September 3, 

2009, 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 Boeing 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. 

(3) You may review copies of the 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 or 425–227–1152. 

(4) You may also review copies of the 

service information that is incorporated by 

reference 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 Renton, Washington, on 

December 21, 2009. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–31288 Filed 1–11–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–1226; Directorate 

Identifier 2009–NM–149–AD; Amendment 

39–16164; AD 2008–10–10 R1] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 737–600, –700, –700C, 

–800, and –900 Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is revising an 

existing airworthiness directive (AD), 

which applies to certain Model 737– 

600, –700, –700C, –800, and –900 series 

airplanes. That AD currently requires 

revising the Airworthiness Limitations 

(AWLs) section of the Instructions for 

Continued Airworthiness by 

incorporating new limitations for fuel 

tank systems to satisfy Special Federal 

Aviation Regulation No. 88 

requirements. That AD also requires an 

initial inspection to phase in certain 

repetitive AWL inspections, and repair 

if necessary. This AD clarifies the 

intended effect of the AD on spare and 

on-airplane fuel tank system 

components. This AD results from a 

design review of the fuel tank systems. 

We are issuing this AD to prevent the 

potential for ignition sources inside fuel 

tanks caused by latent failures, 

alterations, repairs, or maintenance 

actions, which, in combination with 

flammable fuel vapors, could result in a 

fuel tank explosion and consequent loss 

of the airplane. 

DATES: This AD is effective January 27, 

2010. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of January 27, 2010. 

On June 12, 2008 (73 FR 25986, May 

8, 2008), the Director of the Federal 

Register approved the incorporation by 

reference of a certain other publication 

listed in the AD. 

We must receive any comments on 

this AD by February 26, 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– 

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1530 Federal Register / Vol. 75, No. 7 / Tuesday, January 12, 2010 / Rules and Regulations 

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 AD, contact Boeing 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. 

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 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: 

Thomas Thorson, Aerospace Engineer, 

Propulsion Branch, ANM–140S, Seattle 

Aircraft Certification Office, FAA, 1601 

Lind Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 917–6508; 

fax (425) 917–6590. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On April 29, 2008, we issued AD 

2008–10–10, Amendment 39–15516 (73 

FR 25986, May 8, 2008). That AD 

applied to certain Model 737–600, –700, 

–700C, –800, and –900 series airplanes. 

That AD required revising the 

Airworthiness Limitations (AWLs) 

section of the Instructions for Continued 

Airworthiness (ICA) by incorporating 

new limitations for fuel tank systems to 

satisfy Special Federal Aviation 

Regulation No. 88 requirements. That 

AD also requires an initial inspection to 

phase in certain repetitive AWL 

inspections, and repair if necessary. 

That AD resulted from a design review 

of the fuel tank systems. The actions 

specified in that AD are intended to 

prevent the potential for ignition 

sources inside fuel tanks caused by 

latent failures, alterations, repairs, or 

maintenance actions, which, in 

combination with flammable fuel 

vapors, could result in a fuel tank 

explosion and consequent loss of the 

airplane. 

Critical design configuration control 

limitations (CDCCLs) are limitation 

requirements to preserve a critical 

ignition source prevention feature of the 

fuel tank system design that is necessary 

to prevent the occurrence of an unsafe 

condition. The purpose of a CDCCL is 

to provide instruction to retain the 

critical ignition source prevention 

feature during configuration change that 

may be caused by alterations, repairs, or 

maintenance actions. A CDCCL is not a 

periodic inspection. 

Actions Since AD Was Issued 

Since we issued that AD, we have 

determined that it is necessary to clarify 

the AD’s intended effect on spare and 

on-airplane fuel tank system 

components, regarding the use of 

maintenance manuals and instructions 

for continued airworthiness. 

Section 91.403(c) of the Federal 

Aviation Regulations (14 CFR 91.403(c)) 

specifies the following: 

No person may operate an aircraft for 

which a manufacturer’s maintenance manual 

or instructions for continued airworthiness 

has been issued that contains an 

airworthiness limitation section unless the 

mandatory * * * procedures * * * have 

been complied with. 

Some operators have questioned 

whether existing components affected 

by the new CDCCLs must be reworked. 

We did not intend for the AD to 

retroactively require rework of 

components that had been maintained 

using acceptable methods before the 

effective date of the AD. Owners and 

operators of the affected airplanes 

therefore are not required to rework 

affected components identified as 

airworthy or installed on the affected 

airplanes before the required revisions 

of the AWLs. But once the CDCCLs are 

incorporated into the AWLs, future 

maintenance actions on components 

must be done in accordance with those 

CDCCLs. 

Relevant Service Information 

AD 2008–10–10 cites Boeing 

Temporary Revision 09–020, dated 

March 2008, to the Boeing 737–600/700/ 

800/900 Maintenance Planning Data 

(MPD) Document, D626A001–CMR. 

Since we issued that AD, Boeing has 

revised Section 9 of the referenced 

service information. We have reviewed 

the revised document. Section 9, 

Revision September 2009, dated 

September 2009, of Boeing 737–600/ 

700/800/900 MPD, Document 

D626A001–CMR, adds no new 

procedures in regard to fuel tank safety. 

We have added paragraph (l) of this AD 

to give credit for actions required by 

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

were done before the effective date of 

this AD in accordance with Section 9, 

Revision September 2009, dated 

September 2009, of Boeing 737–600/ 

700/800/900 MPD Document, 

D626A001–CMR, and the following 

earlier revisions: Revision March 2008, 

Revision April 2008, Revision June 

2008, Revision February 2009, Revision 

March 2009, and Revision August 2009. 

FAA’s Determination and Requirements 

of This AD 

The unsafe condition described 

previously is likely to exist or develop 

on other airplanes of the same type 

design. For this reason, we are issuing 

this AD to revise AD 2008–10–10. This 

new AD retains the requirements of the 

existing AD, and adds a new note to 

clarify the intended effect of the AD on 

spare and on-airplane fuel tank system 

components. 

Explanation of Additional Changes to 

AD 

AD 2008–10–10 allowed the use of 

alternative inspections, intervals, or 

CDCCLs if they are part of a later 

revision of the Boeing 737–600/700/ 

800/900 MPD Document, D626A001– 

CMR, Revision March 2008. AD 2008– 

10–10 also allowed the use of later 

revisions of the Boeing 737–600/700/ 

800/900 MPD Document, D626A001– 

CMR. Those provisions have been 

removed from this AD. Allowing the use 

of ‘‘a later revision’’ or ‘‘later FAAapproved revisions’’ of specific service 

documents violates Office of the Federal 

Register regulations for approving 

materials that are incorporated by 

reference. Affected operators, however, 

may request approval to use a later 

revision or an alternative CDCCL, 

inspection, or interval, that is part of a 

later revision of the referenced service 

documents as an alternative method of 

compliance, under the provisions of 

paragraph (m) of this AD. 

We have revised paragraphs (g)(1), 

(g)(2), (g)(3), and (h) of this AD to 

remove the term ‘‘Revision March 2008 

of the MPD,’’ which is defined in 

paragraph (f) of this AD. We have 

provided the full document citation 

throughout this AD to avoid any 

confusion about which specific 

document is being referenced. However, 

we have not removed the ‘‘Service 

Information Reference’’ paragraph from 

this AD. Because this AD revises AD 

2008–10–10, we cannot change 

paragraph references, which would 

adversely affect compliance. Therefore, 

we have determined that leaving 

paragraph (f) of this AD unchanged is a 

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Federal Register / Vol. 75, No. 7 / Tuesday, January 12, 2010 / Rules and Regulations 1531 

less burdensome approach for operators, 

while still adhering to standard drafting 

guidance. 

We have revised this AD to identify 

the legal name of the manufacturer as 

published in the most recent type 

certificate data sheet for the affected 

airplane models. 

Costs of Compliance 

This revision imposes no additional 

economic burden. The current costs for 

this AD are repeated for the 

convenience of affected operators, as 

follows: 

There are about 1,960 airplanes of the 

affected design in the worldwide fleet. 

The following table provides the 

estimated costs, at an average labor rate 

of $80 per work hour, for U.S. operators 

to comply with this AD. 

ESTIMATED COSTS

Action Work hours Parts Cost per 

airplane 

Number of 

U.S.-registered 

airplanes 

Fleet cost 

AWLs revision ....................................................................... 8 None ............ $640 682 $436,480 

Inspection .............................................................................. 8 None ............ 640 682 436,480 

FAA’s Justification and Determination 

of the Effective Date 

This revision merely clarifies the 

intended effect on spare and on-airplane 

fuel tank system components, and 

makes no substantive change to the 

AD’s requirements. For this reason, it is 

found that notice and opportunity for 

prior public comment for this action are 

unnecessary, and good cause exists for 

making this amendment effective in less 

than 30 days. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not provide you with notice and 

an opportunity to provide your 

comments before it becomes effective. 

However, we invite you to send any 

written data, views, or arguments about 

this AD. Send your comments to an 

address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2009–1226; Directorate Identifier 2009– 

NM–149–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:// 

www.regulations.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 have 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. 

For the reasons discussed above, I 

certify that the 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 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. 

Adoption of the Amendment 

■ Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends part 39 of the Federal 

Aviation Regulations (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 39–15516 (73 FR 

25986, May 8, 2008) and adding the 

following new AD: 

2008–10–10 R1 The Boeing Company: 

Amendment 39–16164. Docket No. 

FAA–2009–1226; Directorate Identifier 

2009–NM–149–AD. 

Effective Date 

(a) This airworthiness directive (AD) is 

effective January 27, 2010. 

Affected ADs 

(b) This AD revises AD 2008–10–10, 

Amendment 39–15516. 

Applicability 

(c) This AD applies to The Boeing 

Company Model 737–600, –700, –700C, 

–800, and –900 series airplanes, certificated 

in any category, with an original standard 

airworthiness certificate or original export 

certificate of airworthiness issued before 

March 31, 2006. 

Note 1: Airplanes with an original standard 

airworthiness certificate or original export 

certificate of airworthiness issued on or after 

March 31, 2006, must already be in 

compliance with the airworthiness 

limitations specified in this AD because 

those limitations were applicable as part of 

the airworthiness certification of those 

airplanes. 

Note 2: This AD requires revisions to 

certain operator maintenance documents to 

include new inspections. Compliance with 

these inspections is required by 14 CFR 

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1532 Federal Register / Vol. 75, No. 7 / Tuesday, January 12, 2010 / Rules and Regulations 

91.403(c). For airplanes that have been 

previously modified, altered, or repaired in 

the areas addressed by these inspections, the 

operator may not be able to accomplish the 

inspections described in the revisions. In this 

situation, to comply with 14 CFR 91.403(c), 

the operator must request approval for an 

alternative method of compliance (AMOC) 

according to paragraph (m) of this AD. The 

request should include a description of 

changes to the required inspections that will 

ensure the continued operational safety of 

the airplane. 

Unsafe Condition 

(d) This AD results from a design review 

of the fuel tank systems. We are issuing this 

AD to prevent the potential for ignition 

sources inside fuel tanks caused by latent 

failures, alterations, repairs, or maintenance 

actions, which, in combination with 

flammable fuel vapors, could result in a fuel 

tank explosion and consequent loss 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. 

Restatement of Requirements of AD 2008– 

10–10, With Revised Service Information 

Service Information Reference 

(f) The term ‘‘Revision March 2008 of the 

MPD,’’ as used in this AD, means Boeing 

Temporary Revision (TR) 09–020, dated 

March 2008, to the Boeing 737–600/700/800/ 

900 Maintenance Planning Data (MPD) 

Document, D626A001–CMR, Revision March 

2008. 

Revision to Airworthiness Limitations 

(AWLs) Section 

(g) Before December 16, 2008, revise the 

AWLs section of the Instructions for 

Continued Airworthiness (ICA) by 

incorporating into the MPD the information 

in the subsections specified in paragraphs 

(g)(1), (g)(2), and (g)(3) of this AD; except that 

the initial inspection required by paragraph 

(h) of this AD must be done at the applicable 

compliance time specified in that paragraph. 

(1) Subsection E, ‘‘AIRWORTHINESS 

LIMITATIONS—FUEL SYSTEMS,’’ of Boeing 

TR 09–020, dated March 2008, to the Boeing 

737–600/700/800/900 MPD Document, 

D626A001–CMR, Revision March 2008; or of 

Section 9, Revision September 2009, dated 

September 2009, of the Boeing 737–600/700/ 

800/900 Maintenance Planning Data (MPD) 

Document, D626A001–CMR. 

(2) Subsection F, ‘‘PAGE FORMAT: FUEL 

SYSTEM AIRWORTHINESS LIMITATIONS,’’ 

of Boeing TR 09–020, dated March 2008, to 

the Boeing 737–600/700/800/900 MPD 

Document, D626A001–CMR, Revision March 

2008; or Section 9, Revision September 2009, 

dated September 2009, of the Boeing 737– 

600/700/800/900 MPD Document, 

D626A001–CMR. 

(3) Subsection G, ‘‘AIRWORTHINESS 

LIMITATIONS—FUEL SYSTEM AWLs,’’ 

AWLs No. 28–AWL–01 through No. 28– 

AWL–22 inclusive, of Boeing TR 09–020, 

dated March 2008, to the Boeing 737–600/ 

700/800/900 MPD Document, D626A001– 

CMR, Revision March 2008; or Section 9, 

Revision September 2009, dated September 

2009, of the Boeing 737–600/700/800/900 

MPD Document, D626A001–CMR. As an 

optional action, AWLs No. 28–AWL–23 and 

No. 28–AWL–24, as identified in Subsection 

G of Boeing TR 09–020, dated March 2008, 

to the Boeing 737–600/700/800/900 MPD 

Document, D626A001–CMR, Revision March 

2008; or Section 9, Revision September 2009, 

dated September 2009, of the Boeing 737– 

600/700/800/900 MPD Document, 

D626A001–CMR; also may be incorporated 

into the AWLs section of the ICA. 

Initial Inspection and Repair if Necessary 

(h) At the later of the compliance times 

specified in paragraphs (h)(1) and (h)(2) of 

this AD, do a special detailed inspection of 

the lightning shield to ground termination on 

the out-of-tank fuel quantity indication 

system (FQIS) wiring to verify functional 

integrity, in accordance with AWL No. 

28–AWL–03 of Subsection G of Boeing TR 

09–020, dated March 2008, to the Boeing 

737–600/700/800/900 MPD Document, 

D626A001–CMR, Revision March 2008; or 

Section 9, Revision September 2009, dated 

September 2009, of the Boeing 737–600/700/ 

800/900 MPD Document, D626A001–CMR. If 

any discrepancy is found during the 

inspection, repair the discrepancy before 

further flight in accordance with AWL No. 

28–AWL–03 of Subsection G of Boeing TR 

09–020, dated March 2008, to the Boeing 

737–600/700/800/900 MPD Document, 

D626A001–CMR, Revision March 2008; or 

Section 9, Revision September 2009, dated 

September 2009, of the Boeing 737–600/700/ 

800/900 MPD Document, D626A001–CMR. 

Accomplishing AWL No. 28–AWL–03 as part 

of an FAA-approved maintenance program 

before the applicable compliance time 

specified in paragraph (h)(1) or (h)(2) of this 

AD constitutes compliance with the 

requirements of this paragraph. 

Note 3: For the purposes of this AD, a 

special detailed inspection is: ‘‘An intensive 

examination of a specific item, installation, 

or assembly to detect damage, failure, or 

irregularity. The examination is likely to 

make extensive use of specialized inspection 

techniques and/or equipment. Intricate 

cleaning and substantial access or 

disassembly procedure may be required.’’ 

(1) Within 120 months since the date of 

issuance of the original standard 

airworthiness certification or the date of 

issuance of the original export certificate of 

airworthiness. 

(2) Within 24 months after June 12, 2008 

(the effective date of AD 2008–10–10). 

No Alternative Inspections, Inspection 

Intervals, or Critical Design Configuration 

Control Limitations (CDCCLs) 

(i) After accomplishing the actions 

specified in paragraphs (g) and (h) of this AD, 

no alternative inspections, inspection 

intervals, or CDCCLs may be used unless the 

inspections, intervals, or CDCCLs are 

approved as an AMOC in accordance with 

the procedures specified in paragraph (m) of 

this AD. 

Credit for Actions Done According to 

Previous Revisions of the MPD 

(j) Actions done before June 12, 2008, in 

accordance with the following MPDs are 

acceptable for compliance with the 

corresponding requirements of paragraphs (g) 

and (h) of this AD: Section 9 of the Boeing 

737–600/700/700C/700IGW/800/900 MPD 

Document, D626A001–CMR, Revision March 

2006; Revision May 2006; Revision October 

2006; Revision November 2006; or Revision 

November 2006 R1; or Section 9 of the 

Boeing 737–600/700/800/900 MPD 

Document, D626A001–CMR, Revision March 

2007; Revision March 2007 R1; Revision 

March 2007 R2; or Revision February 2008. 

Terminating Action for AD 2008–06–03, 

Amendment 39–15415 

(k) Incorporating AWLs No. 28–AWL–21, 

No. 28–AWL–22, and No. 28–AWL–24 into 

the AWLs section of the ICA in accordance 

with paragraph (g) of this AD terminates the 

action required by paragraph (h)(1) of AD 

2008–06–03. 

New Information 

Explanation of CDCCL Requirements 

Note 4: Notwithstanding any other 

maintenance or operational requirements, 

components that have been identified as 

airworthy or installed on the affected 

airplanes before the revision of the AWLs, as 

required by paragraph (g) of this AD, do not 

need to be reworked in accordance with the 

CDCCLs. However, once the AWLs have been 

revised, future maintenance actions on these 

components must be done in accordance 

with the CDCCLs. 

Credit for Actions Done According to 

Previous Revisions of the MPD 

(l) Actions done before the effective date of 

this AD, in accordance with the following 

MPDs are acceptable for compliance with the 

corresponding requirements of paragraphs (g) 

and (h) of this AD: Section 9 of the Boeing 

737–600/700/800/900 MPD Document, 

D626A001–CMR, Revision March 2008; 

Revision April 2008; Revision June 2008; 

Revision February 2009; Revision March 

2009; or Revision August 2009. 

Alternative Methods of Compliance 

(AMOCs) 

(m)(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 ATTN: 

Thomas Thorson, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue, SW., Renton, Washington 98057– 

3356; telephone (425) 917–6508; fax (425) 

917–6590. Or, e-mail information to 9-ANMSeattle-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 

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Federal Register / Vol. 75, No. 7 / Tuesday, January 12, 2010 / Rules and Regulations 1533 

inspector, your local FSDO. The AMOC 

approval letter must specifically reference 

this AD. 

(3) AMOCs approved previously in 

accordance with AD 2008–10–10 are 

approved as AMOCs for the corresponding 

provisions of this AD. 

Material Incorporated by Reference 

(n) You must use Boeing Temporary 

Revision 09–020, dated March 2008, to the 

Boeing 737–600/700/800/900 Maintenance 

Planning Data (MPD) Document D626A001– 

CMR; or Section 9, Revision September 2009, 

dated September 2009, of the Boeing 737– 

600/700/800/900 MPD Document, 

D626A001–CMR; 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 

Section 9, Revision September 2009, dated 

September 2009, of the Boeing 737–600/700/ 

800/900 MPD Document, D626A001–CMR, 

under 5 U.S.C. 552(a) and 1 CFR part 51. 

(2) The Director of the Federal Register 

previously approved the incorporation by 

reference of Boeing Temporary Revision 09– 

020, dated March 2008, to the Boeing 737– 

600/700/800/900 Maintenance Planning Data 

(MPD) Document, D626A001–CMR, on June 

12, 2008 (73 FR 25986, May 8, 2008). 

(3) For service information identified in 

this AD, contact Boeing 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. 

(4) You may review copies of the 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 or 425–227–1152. 

(5) You may also review copies of the 

service information that is incorporated by 

reference 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 Renton, Washington, on 

December 23, 2009. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–31031 Filed 1–11–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0655; Directorate 

Identifier 2008–NM–192–AD; Amendment 

39–16157; AD 2010–01–01] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 747–200F, 747–200C, 

747–400, 747–400D, and 747–400F 

Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is superseding an 

existing airworthiness directive (AD), 

which applies to all Model 747–200F, 

747–200C, 747–400, 747–400D, and 

747–400F series airplanes. That AD 

currently requires repetitive inspections 

for cracking of certain fuselage internal 

structure (i.e., Sections 42 and 46 

fuselage frames, upper deck floor beams, 

electronic bay access door cutout, nose 

wheel well, and main entry doors and 

door cutouts), and repair if necessary. 

This new AD requires additional 

repetitive inspections for cracking of 

certain fuselage structure (i.e., Section 

41 fuselage frames where they connect 

to upper deck floor beams, and Section 

41 fuselage frames between stringers (S– 

8 and S–12)), and related investigative/ 

corrective actions if necessary. This AD 

also reduces the inspection threshold 

and repetitive inspection intervals for 

certain airplanes. This AD results from 

fatigue tests and analysis that identified 

additional areas of the fuselage where 

fatigue cracks can occur. We are issuing 

this AD to prevent the loss of structural 

integrity of the fuselage, which could 

result in rapid depressurization of the 

airplane. 

DATES: This AD becomes effective 

February 16, 2010. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of February 16, 2010. 

The Director of the Federal Register 

approved the incorporation by reference 

of Boeing Alert Service Bulletin 747– 

53A2500, dated December 21, 2004, as 

of April 6, 2006 (71 FR 10605, March 2, 

2006). 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

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. 

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 AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (telephone 800–647–5527) 

is the Document Management Facility, 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue, SE., 

Washington, DC 20590. 

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: 

Discussion 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that 

supersedes AD 2006–05–02, 

Amendment 39–14499 (71 FR 10605, 

March 2, 2006). The existing AD applies 

to all Model 747–200F, 747–200C, 747– 

400, 747–400D, and 747–400F series 

airplanes. That NPRM was published in 

the Federal Register on July 23, 2009 

(74 FR 36417). That NPRM proposed to 

continue to require repetitive 

inspections for cracking of certain 

fuselage internal structure (i.e., Sections 

42 and 46 fuselage frames, upper deck 

floor beams, electronic bay access door 

cutout, nose wheel well, and main entry 

doors and door cutouts), and repair if 

necessary. That NPRM proposed to 

require additional repetitive inspections 

for cracking of certain fuselage structure 

(i.e., Section 41 fuselage frames where 

they connect to upper deck floor beams, 

and Section 41 fuselage frames between 

stringer (S–8 and S–12)), and related 

investigative/corrective actions if 

necessary. That NPRM also proposed to 

reduce the inspection threshold and 

repetitive inspection intervals for 

certain airplanes. That NPRM resulted 

from fatigue tests and analysis that 

identified areas of the fuselage where 

fatigue cracks can occur. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

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