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

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 threerows 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–


### 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


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

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.



### E STIMATED 

### C OSTS

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


### 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


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

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