### 1351 Federal Register / Vol. 76, No. 6 / Monday, January 10, 2011 / Rules and Regulations

T ABLE 

### 1—A PPLICABILITY

Model Serial Nos.

LC41–550FG ......... 41028, 41705, 411114, 411160, 411161, 411162, 411163, 411164, 411165, 411167, 411170, and 411171. LC42–550FG ......... 42517.

Subject

(d) Joint Aircraft System Component (JASC)/Air Transport Association (ATA) of America Code 57, Wings.

Unsafe Condition

(e) This AD was prompted by a Cessna Model LC41–550FG airplane that suffered a significant structural failure in the wing during a production acceptance flight test. The wing skin disbonded from the upper forward wing spar. The length of the disbond was approximately 7 feet. We are issuing this AD to prevent catastrophic failure of the wing due to disbonding of the wing skin from the wing spar.
Compliance

(f) Comply with this AD within the compliance times specified, unless already done.
Operation Restriction

(g) As of the effective date of this AD, do not operate the airplane without written approval from the Manager, Wichita Aircraft Certification Office (ACO). This written approval must clearly state that operation is approved per AD 2010–26–54.
Special Flight Permit

(h) A special flight permit requires written approval from the Manager, Wichita ACO. This written approval must clearly state that operation is approved per AD 2010–26–54.
Alternative Methods of Compliance (AMOCs)

(i)(1) The Manager, Wichita ACO, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the ACO, send it to the attention of the person identified in the Related Information section of this AD.

(2) Before using any approved AMOC, notify your Principal Maintenance Inspector or Principal Avionics Inspector, as appropriate, or lacking a principal inspector, your local Flight Standards District Office.

Related Information

(j) For further information about this AD, contact: Gary Park, Aerospace Engineer, Wichita ACO, FAA, 1801 Airport Road, Wichita, KS 67209; phone: (316) 946–4123; fax: (316) 946–4107; e-mail: gary.park@faa.gov. Issued in Kansas City, Missouri, on December 27, 2010. Earl Lawrence, Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2010–33336 Filed 1–7–11; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2010–1280; Directorate Identifier 2010–NM–270–AD; Amendment**  **39–16572; AD 2011–01–15]**

**RIN 2120–AA64**

**Airworthiness Directives; The Boeing Company Model 757–200, –200CB, and**  **–300 Series Airplanes**

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

**ACTION :**  Final rule; request for
comments.

**SUMMARY :**  We are adopting a new airworthiness directive (AD) for the products listed above. This AD requires repetitive inspections for cracking of the fuselage skin of the crown skin panel along the chem-milled step at stringers S–4 left and S–4 right, from stations (STA) 297 through 439, and repair if necessary. This AD also includes terminating action for the repetitive inspections of the repaired areas only. This AD was prompted by reports of cracking in the fuselage skin of the crown skin panel. We are issuing this AD to detect and correct fatigue cracking of the fuselage skin of the crown skin panel, which could result in pressure venting and consequent rapid decompression of the airplane.

**DATES :**  This AD is effective January 25,
2011.

The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of January 25, 2011.

We must receive comments on this AD by February 24, 2011.

**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 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 AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (phone: 800–647– 5527) is in the **ADDRESSES** section. Comments will be available in the AD docket shortly after receipt.

**FOR FURTHER INFORMATION CONTACT :**  Nancy Marsh, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 917–6440; fax (425) 917–6590; e-mail: nancy.marsh@faa.gov

. **SUPPLEMENTARY INFORMATION :** 

Discussion

We have received reports of cracking in the fuselage skin of the crown skin panel. On one airplane, the crack was 10.75 inches long, midway between stations (STA) 420 and 439, just above the lap joint at stringer 4L (left) of the chem-milled step. The airplane had accumulated 24,631 total flight cycles. On another airplane, there was an opening from a crack in the fuselage above and aft of the passenger entry doorway. One edge of the opening ranapproximately 18 inches in the forwardto-aft direction; the other edge ran approximately 12 inches along the chem-milled pocket edge above stringer 4L. Additionally, a 1.3-inch crack was found in the skin forward of the opening in the adjacent skin bay also in the chem-milled step above stringer 4L. The airplane had accumulated 22,450 total


### 1352 Federal Register / Vol. 76, No. 6 / Monday, January 10, 2011 / Rules and Regulations

flight cycles. The subject cracking is attributed to fatigue. Such cracking could initiate at multiple locations onthe interior surface along the chemmilled step edges above the stringer 4L or 4R (right) lap splices of the skin. This condition, if not corrected, could result in pressure venting and consequent rapid decompression of the airplane.

Relevant Service Information

We reviewed Boeing Special Attention Service Bulletin 757–53– 0097, dated November 22, 2010. The service information describes procedures for repetitive inspections for cracking of the fuselage skin of the crown skin panel along the chem-milled step at stringers S–4L and S–4R, from STA 297 through 439, as specified in the options below. If any crack is found, the service bulletin recommends contacting Boeing for damage removal and repair instructions.

• Option A Inspection: An external detailed inspection of the STA 297 through 439 crown skin panel at stringers S–4L and S–4R lap joints.

• Option B Inspection: An external sliding probe eddy current inspection of the STA 297 through 439 crown skin panel at stringers S–4L and S–4R lap joints.

• Option C Inspection: An external spot probe medium frequency eddy current inspection of the STA 297 through 439 crown skin panel at stringers S–4L and S–4R lap joints.

The compliance time for all of the initial inspections is before the accumulation of 15,000 total flight cycles, or within 30 days after the original issue date of the service bulletin, whichever occurs later. The repetitive interval is specified below.

• Option A: At intervals not to exceed 30 flight cycles.

• Option B: At intervals not to exceed 300 flight cycles.

• Option C: At intervals not to exceed 200 flight cycles.

The initial external detailed inspection specified in Option A, if done, is repeated until either the Option B or Option C inspection is accomplished within 90 days after the original date of the service bulletin, and thereafter, either the Option B or Option C inspection is repeated. Accomplishing the Option B or Option C inspection would eliminate the need for the Option A inspection.

A detailed external inspection may be applied no more than once for each repeat interval of 300 flight cycles to extend the Option B repeat inspection up to 330 flight cycles, and for each repeat interval of 200 flight cycles to extend the Option C inspection up to 230 flight cycles—not to exceed 30 flight cycles after accomplishing the inspection.

Boeing Special Attention Service Bulletin 757–53–0097, dated November 22, 2010, also includes certain exceptions to the inspection of the edge of the chem-milled pocket under an existing external repair doubler.

FAA’s Determination

We are issuing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design.
AD Requirements

This AD requires accomplishing the actions specified in the service information described previously, except as discussed under ‘‘ Difference Between the AD and the Service Information. ’’

Difference Between the AD and the Service Information

Boeing Special Attention Service Bulletin 757–53–0097, dated November 22, 2010, specifies to contact the manufacturer for instructions on how to repair certain conditions, but this AD would require repairing those conditions in one of the following ways:

• In accordance with 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 (ODA) whom we have authorized to make those findings. Interim Action

We consider this AD interim action. An investigation is ongoing and no terminating action has been developed yet. FAA’s Justification and Determination of the Effective Date

An unsafe condition exists that requires the immediate adoption of this AD. The FAA has found that the risk to the flying public justifies waiving notice and comment prior to adoption of this rule because fatigue cracking of the fuselage skin of the crown skin panel could result in pressure venting and consequent rapid decompression of the airplane. Therefore, we find that notice and opportunity for prior public comment are impracticable and that 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 was not preceded by notice and an opportunity for public comment. 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. FAA2010–1280; Directorate Identifier 2010– NM–270–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. Costs of Compliance

We estimate that this AD affects 683 airplanes of U.S. registry.

We estimate the following costs to comply with this AD:



### E STIMATED 

### C OSTS

Action Labor cost Parts cost Cost per product Cost on U.S. operators

Inspection ......... 1 work-hour × $85 per hour = $85 per inspection cycle. None ................. $85 per inspection cycle. $58,055 per inspection cycle.

We have received no definitive data that would enable us to provide a cost estimate for the on-condition actions specified in this AD. Authority for This Rulemaking

Title 49 of the United States Code specifies the FAA’s authority to issue


### 1353 Federal Register / Vol. 76, No. 6 / Monday, January 10, 2011 / Rules and Regulations

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

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 this AD:

(1) Is not a ‘‘ significant regulatory action ’’ under Executive Order 12866,

(2) Is not a ‘‘ significant rule ’’ under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979),

(3) Will not affect intrastate aviation in Alaska, and

(4) 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. 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 14 CFR part 39 as follows:

**PART 39—AIRWORTHINESS DIRECTIVES** 

■ 1. The authority citation for part 39 continues to read as follows:

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

**§ 39.13 [Amended]**

■ 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): 2011–01–15 The Boeing Company: Amendment 39–16572; Docket No. FAA–2010–1280; Directorate Identifier
2010–NM–270–AD.

Effective Date

(a) This AD is effective January 25, 2011.

Affected ADs

(b) None.
Applicability

(c) This AD applies to The Boeing Company Model 757–200, –200CB, and –300 series airplanes, certificated in any category, as identified in Boeing Special Attention Service Bulletin 757–53–0097, dated November 22, 2010.
Subject

(d) Joint Aircraft System Component (JASC)/Air Transport Association (ATA) of America Code 53: Fuselage.

Unsafe Condition

(e) This AD was prompted by reports of cracking in the fuselage skin of the crown skin panel. We are issuing this AD to detect and correct fatigue cracking of the fuselage skin, which could result in pressure venting and consequent rapid decompression of the airplane.
Compliance

(f) Comply with this AD within the compliance times specified, unless already done.
Repetitive Inspections/Repair

(g) At the applicable time specified in paragraph 1.E., ‘‘ Compliance, ’’ of Boeing Special Attention Service Bulletin 757–53– 0097, dated November 22, 2010, except as required by paragraph (i) of this AD: Do an external detailed, sliding probe eddy current, or spot-probe-medium-frequency eddy current inspection for cracking of the fuselage skin of the crown skin panel along the chem-milled step at stringers S–4L (left) and S–4R (right), stations (STA) 297 through 439, in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 757–53–0097, dated November 22, 2010. Repeat the applicable inspection thereafter at the interval specified in paragraph 1.E., ‘‘ Compliance, ’’ of Boeing Special Attention Service Bulletin 757–53– 0097, dated November 22, 2010.
Repair

(h) If any crack is found during any inspection required by paragraph (g) of this AD: Before further flight, repair using a method approved in accordance with the procedures specified in paragraph (j) of this AD. Doing the repair ends the repetitive inspections for the repaired area only.
Exception to Service Bulletin Specification

(i) Where Boeing Special Attention Service Bulletin 757–53–0097, dated November 22, 2010, specifies a compliance time after the date on that service bulletin, this AD requires compliance within the specified compliance time after the effective date of this AD. 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. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the ACO, send it to the attention of the person identified in the Related Information section of this AD. Information may be e-mailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov

.

(2) Before using any approved AMOC, notify your Principal Maintenance Inspector or Principal Avionics Inspector, as appropriate, or lacking a principal inspector, your local Flight Standards District Office.

(3) An AMOC that provides an acceptable level of safety may be used for any repair required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (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.

Related Information

(k) For more information about this AD, contact Nancy Marsh, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057– 3356; telephone (425) 917–6440; fax (425) 917–6590; e-mail: nancy.marsh@faa.gov

. Material Incorporated by Reference

(l) You must use Boeing Special Attention Service Bulletin 757–53–0097, dated November 22, 2010, 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 the 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.

(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 an NARA facility, call 202–741– 6030, or go to http://www.archives.gov/ federal

_register/code

_ of

_ federal

_ regulations/ ibr

_ locations.html.


### 1354 Federal Register / Vol. 76, No. 6 / Monday, January 10, 2011 / Rules and Regulations

Issued in Renton, Washington, on December 28, 2010. Jeffrey E. Duven, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2011–51 Filed 1–7–11; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 97**

**[Docket No. 30761; Amdt. No. 3406]**

**Standard Instrument Approach Procedures, and Takeoff Minimums**  **and Obstacle Departure Procedures; Miscellaneous Amendments** 

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

**ACTION :**  Final rule.

**SUMMARY :**  This establishes, amends, suspends, or revokes Standard Instrument Approach Procedures (SIAPs) and associated Takeoff Minimums and Obstacle Departure Procedures for operations at certain airports. These regulatory actions are needed because of the adoption of new or revised criteria, or because of changes occurring in the National Airspace System, such as the commissioning of new navigational facilities, adding new obstacles, or changing air traffic requirements. These changes are designed to provide safe and efficient use of the navigable airspace and to promote safe flight operations under instrument flight rules at the affected airports.

**DATES :**  This rule is effective January 10, 2011. The compliance date for each SIAP, associated Takeoff Minimums, and ODP is specified in the amendatory provisions.

The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of January 10,
2011.

**ADDRESSES :**  Availability of matters incorporated by reference in the amendment is as follows:

For Examination — 1. FAA Rules Docket, FAA Headquarters Building, 800 Independence Avenue, SW., Washington, DC 20591;

2. The FAA Regional Office of the region in which the affected airport is located;

3. The National Flight Procedures Office, 6500 South MacArthur Blvd., Oklahoma City, OK 73169, or 4. 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. Availability —All SIAPs and Takeoff Minimums and ODPs are available online free of charge. Visit http:// www.nfdc.faa.gov to register. Additionally, individual SIAP and Takeoff Minimums and ODP copies may be obtained from:

1. FAA Public Inquiry Center (APA– 200), FAA Headquarters Building, 800 Independence Avenue, SW., Washington, DC 20591; or

2. The FAA Regional Office of the region in which the affected airport is located.

**FOR FURTHER INFORMATION CONTACT :**  Harry J. Hodges, Flight Procedure Standards Branch (AFS–420), Flight Technologies and Programs Divisions, Flight Standards Service, Federal Aviation Administration, Mike Monroney Aeronautical Center, 6500 South MacArthur Blvd., Oklahoma City, OK 73169 (Mail Address: P.O. Box 25082, Oklahoma City, OK 73125); Telephone: (405) 954–4164.

**SUPPLEMENTARY INFORMATION :**  This rule amends Title 14 of the Code of Federal Regulations, Part 97 (14 CFR part 97), by establishing, amending, suspending, or revoking SIAPS, Takeoff Minimums and/or ODPS. The complete regulators description of each SIAP and its associated Takeoff Minimums or ODP for an identified airport is listed on FAA form documents which are incorporated by reference in this amendment under 5 U.S.C. 552(a), 1 CFR part 51, and 14 CFR part 97.20. The applicable FAA Forms are FAA Forms 8260–3, 8260–4, 8260–5, 8260–15A, and 8260–15B when required by an entry on 8260–15A.

The large number of SIAPs, Takeoff Minimums and ODPs, in addition to their complex nature and the need for a special format make publication in the Federal Register expensive and impractical. Furthermore, airmen do not use the regulatory text of the SIAPs, Takeoff Minimums or ODPs, but instead refer to their depiction on charts printed by publishers of aeronautical materials. The advantages of incorporation by reference are realized and publication of the complete description of each SIAP, Takeoff Minimums and ODP listed on FAA forms is unnecessary. This amendment provides the affected CFR sections and specifies the types of SIAPs and the effective dates of the associated Takeoff Minimums and ODPs. This amendment also identifies the airport and its location, the procedure, and the amendment number.

The Rule

This amendment to 14 CFR part 97 is effective upon publication of each separate SIAP, Takeoff Minimums and ODP as contained in the transmittal. Some SIAP and Takeoff Minimums and textual ODP amendments may have been issued previously by the FAA in a Flight Data Center (FDC) Notice to Airmen (NOTAM) as an emergency action of immediate flight safety relating directly to published aeronautical charts. The circumstances which created the need for some SIAP and Takeoff Minimums and ODP amendments may require making them effective in less than 30 days. For the remaining SIAPS and Takeoff Minimums and ODPS, an effective date at least 30 days after publication is provided.

Further, the SIAPs and Takeoff Minimums and ODPS contained in this amendment are based on the criteria contained in the U.S. Standard for Terminal Instrument Procedures (TERPS). In developing these SIAPS and Takeoff Minimums and ODPs, the TERPS criteria were applied to the conditions existing or anticipated at the affected airports. Because of the close and immediate relationship between these SIAPs, Takeoff Minimums and ODPs, and safety in air commerce, I find that notice and public procedures before adopting these SIAPS, Takeoff Minimums and ODPs are impracticable and contrary to the public interest and, where applicable, that good cause exists for making some SIAPs effective in less than 30 days.

Conclusion

The FAA has determined that this regulation only involves an established body of technical regulations for which frequent and routine amendments are necessary to keep them operationally current. It, therefore—(1) is not a

‘‘ significant regulatory action ’’ under Executive Order 12866; (2) is not a

‘‘ significant rule ’’ under DOT Regulatory Policies and Procedures (44 FR 11034; February 26,1979); and (3) does not warrant preparation of a regulatory evaluation as the anticipated impact is so minimal. For the same reason, the FAA certifies that this amendment will not have a significant economic impact on a substantial number of small entities under the criteria of the Regulatory Flexibility Act.