### 39185 Federal Register / Vol. 75, No. 130 / Thursday, July 8, 2010 / Proposed Rules

The Privacy Act allows Government agencies to exempt certain records from the access and amendment provisions. If an agency claims an exemption, however, it must issue a Notice of Proposed Rulemaking to make clear to the public the reasons why a particular exemption is claimed.

DHS is claiming exemptions from certain requirements of the Privacy Act for DHS/ALL—029 Civil Rights and Civil Liberties Records System of
Records. Some information in DHS/ ALL—029 Civil Rights and Civil Liberties Records System of Records relates to official DHS national security, law enforcement, immigration, intelligence activities, and protective
services to the President of the United States or other individuals pursuant to
Section 3056 and 3056A of Title 18. These exemptions are needed to protect information relating to DHS activities from disclosure to subjects or others related to these activities. Specifically, the exemptions are required to preclude subjects of these activities from frustrating these processes; to avoid disclosure of activity techniques; to protect the identities and physical safety
of confidential informants and law enforcement personnel; to ensure DHS’ ability to obtain information from third parties and other sources; to protect the privacy of third parties; to safeguard classified information; and to safeguard records in connection with providing protective services to the President of
the United States or other individuals pursuant to Section 3056 and 3056A of
Title 18. Disclosure of information to the subject of the inquiry could also permit the subject to avoid detection or apprehension.

The exemptions proposed here are
standard law enforcement and national security exemptions exercised by a large
number of federal law enforcement and intelligence agencies. In appropriate circumstances, where compliance would not appear to interfere with or adversely affect the law enforcement purposes of this system and the overall law enforcement process, the applicable exemptions may be waived on a case by
case basis.

A notice of system of records for DHS/ ALL—029 Civil Rights and Civil Liberties Records System of Records is also published in this issue of the Federal Register

. List of Subjects in 6 CFR Part 5

Freedom of information; Privacy.

For the reasons stated in the preamble, DHS proposes to amend Chapter I of Title 6, Code of Federal Regulations, as follows: **PART 5—DISCLOSURE OF RECORDS**
**AND INFORMATION**

1. The authority citation for Part 5
continues to read as follows:

Authority: 6 U.S.C. 101 et seq.; Pub. L. 107–296, 116 Stat. 2135; 5 U.S.C. 301. Subpart A also issued under 5 U.S.C. 552. Subpart B also issued under 5 U.S.C. 552a.

2. Add to Appendix C to Part 5 the following new paragraph ‘‘49 ’’ : Appendix C to Part 5—DHS Systems of Records Exempt From the Privacy Act

* * * * *

49. The DHS/ALL—029 Civil Rights and Civil Liberties Records System of Records consists of electronic and paper records and will be used by DHS and its components. The DHS/ALL—029 Civil Rights and Civil Liberties Records System of Records is a repository of information held by DHS in
connection with its several and varied missions and functions, including, but not
limited to the enforcement of civil and criminal laws; investigations, inquiries, and proceedings thereunder; national security and intelligence activities; and protection of
the President of the United States or other individuals pursuant to Section 3056 and
3056A of Title 18. The DHS/ALL—029 Civil Rights and Civil Liberties Records System of
Records contains information that is collected by, on behalf of, in support of, or in cooperation with DHS and its components and may contain personally identifiable information collected by other federal, state, local, tribal, foreign, or international government agencies. The Secretary of Homeland Security has exempted this system from the following provisions of the Privacy Act, subject to limitations set forth in 5 U.S.C. 552a(c)(3); (d); (e)(1), (e)(4)(G), (e)(4)(H), (e)(4)(I); and (f) pursuant to 5 U.S.C. 552a(k)(1), (k)(2), (k)(3), and (k)(5). Exemptions from these particular subsections are justified, on a case-by-case basis to be determined at the time a request is made, for the following reasons:

(a) From subsection (c)(3) (Accounting for Disclosures) because release of the accounting of disclosures could alert the individual who is the subject of an investigation of an actual or potential criminal, civil, or regulatory violation to the existence of that investigation and reveal investigative interest on the part of DHS as well as the recipient agency. Disclosure of the accounting would, therefore, present a serious impediment to law enforcement efforts and/or efforts to preserve national security. Disclosure of the accounting would also permit the individual who is the subject of a record to impede the investigation, to tamper with witnesses or evidence, and to avoid detection or apprehension, which would undermine the entire investigative

process.

(b) From subsection (d) (Access to Records)
because access to the records contained in this system of records could inform the individual who is the subject of an investigation of an actual or potential criminal, civil, or regulatory violation to the existence of that investigation and reveal investigative interest on the part of DHS or another agency. Access to the records could permit the individual who is the subject of a record to impede the investigation, to tamper with witnesses or evidence, and to avoid detection or apprehension.
Amendment of the records could interfere with ongoing investigations and law enforcement activities and would impose an unreasonable administrative burden by requiring investigations to be continually reinvestigated. In addition, permitting access
and amendment to such information could disclose security-sensitive information that could be detrimental to homeland security.

(c) From subsection (e)(1) (Relevancy and Necessity of Information) because in the course of investigations into potential violations of federal law, the accuracy of
information obtained or introduced occasionally may be unclear, or the information may not be strictly relevant or necessary to a specific investigation. In the interests of effective law enforcement, it is appropriate to retain all information that may aid in establishing patterns of unlawful activity.

(d) From subsections (e)(4)(G), (e)(4)(H), and (e)(4)(I) (Agency Requirements) and (f) (Agency Rules), because portions of this system are exempt from the individual access provisions of subsection (d) for the reasons noted above, and therefore DHS is not required to establish requirements, rules, or procedures with respect to such access. Providing notice to individuals with respect to existence of records pertaining to them in the system of records or otherwise setting up procedures pursuant to which individuals may access and view records pertaining to themselves in the system would undermine investigative efforts and reveal the identities of witnesses, and potential witnesses, and
confidential informants.

* * * * *

Dated: June 30, 2010. Mary Ellen Callahan, Chief Privacy Officer, Department of Homeland Security.

[FR Doc. 2010–16580 Filed 7–7–10; 8:45 am]

**BILLING CODE 9110–9B–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2010–0679; Directorate Identifier 2009–NM–179–AD]** 

**RIN 2120–AA64**

**Airworthiness Directives; The Boeing Company Model 747–100, 747–100B,**  **747–100B SUD, 747–200B, 747–200C, 747–200F, 747–300, 747SR, and 747SP**  **Series Airplanes**

**AGENCY :**  Federal Aviation Administration (FAA), Department of Transportation (DOT).


### 39186 Federal Register / Vol. 75, No. 130 / Thursday, July 8, 2010 / Proposed Rules

**ACTION :**  Notice of proposed rulemaking (NPRM).

**SUMMARY :**  The FAA proposes to supersede an existing airworthiness directive (AD) that applies to certain Model 747–100, 747–100B, 747–100B SUD, 747–200B, 747–200C, 747–200F, 747–300, 747SR, and 747SP series airplanes. The existing AD requires repetitive inspections and torque checks of the hanger fittings and strut forward bulkhead of the forward engine mount and adjacent support structure, and visual inspections of the internal angle
and external bulkhead chord and detailed inspection of internal angles, and corrective actions if necessary. The existing AD also provides for an optional inspection. This proposed AD would also require additional inspections of airplanes that have hi-lok bolts and collars at all of the Group B fastener locations, except fastener 13, and related investigative and corrective actions. This proposed AD would require repetitive inspections of the internal angle and corrective actions, if necessary. This proposed AD also would require, for certain airplanes, replacing the fasteners, which terminates certain repetitive inspections. This proposed AD results from the reports of undertorqued or loose fasteners, a cracked bulkhead chord, and a fractured back-up angle. We are proposing this AD to prevent loose fasteners and/or damaged or cracked hanger fittings, back-up angles, and bulkhead of the forward engine mount, which could lead to failure of the hanger fitting and bulkhead and consequent separation of the engine from the airplane.

**DATES :**  We must receive comments on this proposed AD by August 23, 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 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 or 425–227–1152.
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 :**  Ken Paoletti, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 917–6434; 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–2010–0679; Directorate Identifier

2009–NM–179–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 September 14, 2007, we issued AD 2007–19–19, Amendment 39–15210 (72 FR 53939, September 21, 2007), for certain Boeing Model 747–100, 747– 100B, 747–100B SUD, 747–200B, 747– 200C, 747–200F, 747–300, 747SR, and 747SP series airplanes. That AD requires repetitive inspections and torque checks of the hanger fittings and
strut forward bulkhead of the forward engine mount and adjacent support structure, and visual inspections of the internal angle and external bulkhead chord and detailed inspection of internal angles, and corrective actions if necessary. The existing AD also provides for an optional inspection. That AD resulted from reports of undertorqued or loose fasteners, a cracked bulkhead chord, and a fractured back-up angle after operators accomplished the terminating action required by AD 2001–15–02, Amendment 39–12336 (66 FR 37884, July 20, 2001), which was superseded by AD 2007–19–19. We issued that AD
to detect and correct loose fasteners and/or damaged or cracked hanger fittings, back-up angles, and bulkhead of the forward engine mount, which could lead to failure of the hanger fitting and bulkhead and consequent separation of the engine from the airplane.

Actions Since Existing AD Was Issued

The preamble to AD 2007–19–19 specifies that we consider the requirements ‘‘ interim action’’ and that we were considering requiring the inspections and applicable related investigative and corrective actions specified in Part 7 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–54A2203, Revision 1, dated August 9, 2007, and
we have determined that further rulemaking is indeed necessary; this proposed AD follows from that
determination.

Relevant Service Information

AD 2007–19–19 cited Boeing Alert Service Bulletin 747–54A2203, Revision 1, dated August 9, 2007, as the relevant
source of information. Since we issued AD 2007–19–19, the manufacturer has revised the service information. Boeing
has released Alert Service Bulletin 747– 54A2203, Revision 2, dated July 9, 2009.

Boeing Alert Service Bulletin 747– 54A2203, Revision 2, dated July 9, 2009, specifies that hi-lok bolts and collars at all of the Group B fastener locations, except fastener 13, need to be replaced with bolts specified in the service
bulletin within 18 months after the service bulletin is released. (Boeing Alert Service Bulletin 747–54A2203, dated August 31, 2000; and Revision 1, dated August 9, 2007; specified that the hi-lok bolts on these airplanes did not have to be replaced according to Part 6 of the Accomplishment Instructions if they met the inspection requirements of Part 2.) The related corrective actions are replacing the fasteners; removing loose fasteners; tightening all Group A


### 39187 Federal Register / Vol. 75, No. 130 / Thursday, July 8, 2010 / Proposed Rules

and Group B fasteners; tightening all under-torqued or loose Group A and Group B fasteners; and removing loose fasteners, inspecting the hole, installing fasteners, and applying optional torque stripes. In addition, that service bulletin specifies that the fasteners on these airplanes need to be replaced in
accordance with Part 6—Fastener Replacement. The related investigative actions are doing repetitive detailed inspections, a torque stripe inspection, and torque checks.

Boeing Alert Service Bulletin 747– 54A2203, Revision 2, dated July 9, 2009, specifies a compliance time of within 90 days after the date of Revision 2 of that
service bulletin for the Part 2 inspection, and within 18 months after
the date of Revision 2 of that service bulletin for the Part 6 replacement. For the related investigative actions, that service bulletin specifies a compliance time ranging from before further flight to
within 18 months after the fasteners are replaced. For the related corrective actions, that service bulletin specifies a compliance time ranging from before further flight to within 18 months after under-torqued or loose fasteners were
found.

For all airplanes, Boeing Alert Service Bulletin 747–54A2203, Revision 2, dated July 9, 2009, clarifies the requirements for conditions in which the torque stripe is not applied and for which no under-torqued or loose fastener was found by reordering the steps. In addition, Boeing Alert Service Bulletin 747–54A2203, Revision 2, dated July 9, 2009, adds an option for supporting the engine weight, instead of removing the engine, in Part 7—HFEC Internal Angle Inspection of the Accomplishment Instructions of that service bulletin. Boeing Alert Service Bulletin 747–54A2203, Revision 2, dated July 9, 2009, also no longer includes the 60-month compliance time for doing Part 6 of the Accomplishment
Instructions of that service bulletin.

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 2007–
19–19 and would retain certain requirements of the existing AD. This proposed AD would also require repetitive inspections of the internal angle, and corrective actions if necessary, and this proposed AD would also require, for certain airplanes, replacing the fasteners. Differences Between the Proposed AD
and Service Information

The service information specifies to
contact the manufacturer for instructions on how to repair certain conditions, but this AD requires repairing those conditions in one of the following ways:

• Using a method that we approve; or

• Using data that meet the certification basis of the airplane, and that have been approved by the Boeing Commercial Airplanes Organization Designation Authorization whom we have authorized to make those findings.

Part 7—HFEC Internal Angle Inspection of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–54A2203, Revision 2, dated July 9, 2009, also provides an option to support the engine weight rather than removing the engine. This AD requires the removal of the engine to perform the inspection.

Costs of Compliance

There are about 266 airplanes of the affected design in the worldwide fleet. The following table provides the estimated costs for U.S. operators to comply with this proposed AD.



### E STIMATED 

### C OSTS

Action Work hours Average labor rate per hour Parts Cost per airplane Number of U.S.- registered airplanes Fleet cost

Actions (required by AD 2007–19–19) ............................ 40 $85 $0 $3,400 121 $411,400 Internal Angle Inspection (new proposed action) ............ 16 85 0 1,360 121 164,560 Replacement of fasteners (new proposed action) ........... 24 85 0 2,040 121 246,840

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:


### 39188 Federal Register / Vol. 75, No. 130 / Thursday, July 8, 2010 / Proposed Rules

**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 39–15210 (72 FR 53939, September 21, 2007) and adding the following new AD:

The Boeing Company: Docket No. FAA– 2010–0679; Directorate Identifier 2009–

NM–179–AD.

Comments Due Date

(a) The FAA must receive comments on this AD action by August 23, 2010.

Affected ADs

(b) This AD supersedes AD 2007–19–19,
Amendment 39–15210.

Applicability

(c) This AD applies to The Boeing Company Model 747–100, 747–100B, 747– 100B SUD, 747–200B, 747–200C, 747–200F, 747–300, 747SR, and 747SP series airplanes, certificated in any category; as identified in Boeing Alert Service Bulletin 747–54A2203, Revision 2, dated July 9, 2009.

Subject

(d) Air Transport Association (ATA) of America Code 54: Nacelles/Pylons.

Unsafe Condition

(e) This AD results from the development of a mandating action. The Federal Aviation Administration is issuing this AD to detect and correct loose fasteners and/or damaged or cracked hanger fittings, back-up angles, and bulkhead of the forward engine mount, which could lead to failure of the hanger fitting and bulkhead and consequent separation of the engine from 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 a Requirement of AD 2007– 19–19, With Updated Service Information

Inspections and Related Investigative and

Corrective Actions

(g) Except as provided by paragraphs (i), (l), and (n) of this AD: At the applicable compliance times and repeat intervals listed in Tables 1 and 2 of paragraph 1.E.,

‘‘ Compliance, ’’ of Boeing Alert Service Bulletin 747–54A2203, Revision 1, dated August 9, 2007, do the inspections and applicable related investigative and
corrective actions in accordance with Parts 2 and 8 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–54A2203, Revision 1, dated August 9, 2007; or Revision 2, dated July 9, 2009. After the effective date of this AD, use only Boeing Alert Service Bulletin 747–54A2203, Revision 2, dated July

9, 2009. New Requirements of This AD

Mandatory Initial and Repetitive Inspections and Related Investigative and Corrective

Actions

(h) For all airplanes: Except as provided by paragraph (m) of this AD, at the applicable time in Table 2 of paragraph 1.E.,

‘‘ Compliance, ’’ of Boeing Alert Service Bulletin 747–54A2203, Revision 2, dated July 9, 2009, do the initial inspection and related investigative and corrective actions in
accordance with Part 7 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–54A2203, Revision 2, dated July 9, 2009, except as required by paragraphs (k) and (n) of this AD. Repeat the inspection thereafter at the applicable time in paragraph 1.E., ‘‘Compliance, ’’ of Boeing Alert Service Bulletin 747–54A2203, Revision 2, dated July 9, 2009.

(i) For airplanes that were inspected in accordance with Boeing Alert Service Bulletin 747–54A2203, dated August 31, 2000; or Revision 1, dated August 9, 2007;
and that have hi-lock bolts and collars at all of the Group B fastener locations: Except as provided by paragraph (m) of this AD, at the applicable time in paragraph 1.E.,

‘‘Compliance, ’’ of Boeing Alert Service Bulletin 747–54A2203, Revision 2, dated July 9, 2009, do the initial inspection and related investigative and corrective actions in
accordance with Part 2 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–54A2203, Revision 2, dated July 9, 2009, except as required by paragraph (n) of this AD. Repeat the inspection at the applicable interval in paragraph 1.E., ‘‘ Compliance, ’’ of Boeing Alert Service Bulletin 747–54A2203, Revision 2, dated July 9, 2009.

Replacement of Hi-Lok Group B Fasteners

(j) For airplanes that were inspected in accordance with Boeing Alert Service Bulletin 747–54A2203, dated August 31, 2000, and that have hi-lock bolts and collars at all of the Group B fastener locations:
Within 18 months after the effective date of this AD, replace all hi-lok Group B fasteners
in accordance with Part 6 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–54A2203, Revision 2, dated July 9, 2009. Repeat the inspection required by Part 2 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–54A2203, Revision 2, dated July 9, 2009, at the applicable interval in paragraph 1.E.,

‘‘Compliance, ’’ of Boeing Alert Service Bulletin 747–54A2203, Revision 2, dated July

9, 2009.

Exceptions to Service Bulletin

(k) Where Step 3 of Part 7 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–54A2203, Revision 1, dated August 9, 2007; or Revision 2, dated July 9, 2009; provides the option to support the engine weight instead of removing the engine, this AD does not allow that option. This AD requires that the engine be removed before performing the inspections required by paragraph (h) of this AD.

(l) Where Boeing Alert Service Bulletin 747–54A2203, Revision 1, dated August 9, 2007, specifies a compliance time after the date of that service bulletin, this AD requires compliance within the specified compliance time after October 9, 2007 (the effective date of AD 2007–19–19).

(m) Where Boeing Alert Service Bulletin 747–54A2203, Revision 2, dated July 9, 2009, specifies a compliance time after the date of
Revision 1 or Revision 2 of that service bulletin, this AD requires compliance within the specified compliance time after the
effective date of this AD.

(n) Where Boeing Alert Service Bulletin 747–54A2203, Revision 1, dated August 9, 2007; or Boeing Alert Service Bulletin 747– 54A2203, Revision 2, dated July 9, 2009; specifies to contact Boeing for appropriate action, this AD requires, before further flight, repair of the discrepancy or replacement of the discrepant part using a method approved in accordance with the Boeing Commercial Airplanes Organization Designation
Authorization or in accordance with the procedures specified in paragraph (p) of this

AD.

Credit for Actions Previously Accomplished

(o) Actions performed before the effective date of this AD, in accordance with Boeing Alert Service Bulletin 747–53A2203, Revision 1, dated August 9, 2007, are acceptable for compliance with the corresponding actions specified in paragraphs (h), (i), and (j) of this AD.

Alternative Methods of Compliance (AMOCs)

(p)(1) The Manager, Seattle Aircraft Certification Office, 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: Ken Paoletti, Aerospace Engineer, Airframe Branch, ANM– 120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 917–6434; 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 Organization Designation Authorization who has been authorized by the Manager, Seattle ACO, to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane, and the approval must specifically refer to this AD.

(4) AMOCs approved previously in accordance with AD 2007–19–19, Amendment 39–15210, are approved as AMOCs for the corresponding provisions of
this AD.


### 39189 Federal Register / Vol. 75, No. 130 / Thursday, July 8, 2010 / Proposed Rules

Issued in Renton, Washington, on June 25,

2010. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2010–16606 Filed 7–7–10; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2010–0674; Directorate Identifier 2010–NM–012–AD]** 

**RIN 2120–AA64**

**Airworthiness Directives; The Boeing Company Model 747 Airplanes** 

**AGENCY :**  Federal Aviation Administration (FAA), DOT.

**ACTION :**  Notice of proposed rulemaking (NPRM).

**SUMMARY :**  We propose to adopt a new airworthiness directive (AD) for all Model 747 airplanes. This proposed AD would require repetitive inspections for cracking in the body skin around the aft corners of the nose wheel well; for certain airplanes, repetitive inspections for cracking in the skin splice plate at the aft corners of the nose wheel well; and related investigative and corrective actions if necessary. This proposed ADwould also require repetitive postmodification inspections for cracking in the body skin and the skin splice plate; for certain airplanes, an inspection for steel cross-shaped doublers on the larger aluminum doublers; and corrective action if necessary. This proposed AD would also require repetitive surface high frequency eddy current (HFEC) inspections of a certain bulkhead outer chord, skin splice plate, and outer chord radius filler for cracking; repetitive detailed inspections for cracking of the bulkhead frame web and body skin; and corrective actions if necessary. This proposed AD would provide for optional terminating action for certain repetitive inspections. This proposed AD results from reports of cracking of the fuselage skin and adjacent internal skin splice plate at the left and right nose wheel well aft corners, and the outer chord of the body station (BS) 400 bulkhead. We are proposing this AD to detect and correct cracking of the fuselage skin or splice plate, which, together with cracking of the bulkhead outer chord, could result in large skin cracks and subsequent in-flight rapid decompression of the airplane.

**DATES :**  We must receive comments on this proposed AD by August 23, 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 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–2010–0674; Directorate Identifier

2010–NM–012–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

We have received reports of cracking of the fuselage skin and adjacent internal skin splice plate at the left and right nose wheel well aft corners, and the outer chord of the body station (BS)
400 bulkhead. Cracks were found in the skin on an airplane that had accumulated about 6,355 total flight cycles. In addition, small cracks were found in the outer chord of the body station (BS) 400 bulkhead on airplanes that had accumulated fewer than 20,000 total flight cycles. Cracking of the fuselage skin or splice plate, together with cracking of the bulkhead outer chord, if not detected and corrected, could result in large skin cracks and subsequent in-flight rapid decompression of the airplane.

Relevant Service Information

We have reviewed Boeing Alert Service Bulletin 747–53A2305, Revision 2, dated January 15, 2009. The service bulletin describes procedures for repetitive external detailed inspections for cracking in the body skin around the aft corners of the nose wheel well; for certain airplanes, repetitive external detailed inspections for cracking in the skin splice plate at the aft corners of the nose wheel well, and modification of any cracked aft corners of the nose wheel well by installing modification doublers; and, for certain airplanes, and a one-time external general visual inspection for steel cross-shaped doublers. The modification, which, if accomplished to repair cracks or to eliminate the need for certain repetitive inspections, includes related investigative actions and corrective actions if necessary. The relatedinvestigative actions include an openhole HFEC inspection for cracking at
fasteners common to the bulkhead outer chord, and a surface HFEC inspection or penetrant inspection for cracking of the skin if necessary. The corrective actions include repairing the crack, installing cross-shaped doublers, and contacting Boeing for repair instructions and doing the repair.