## 68686 Federal Register / Vol. 75, No. 216 / Tuesday, November 9, 2010 / Rules and Regulations

EMBRAER Phenom Service Bulletin 500–21– 0001, dated December 9, 2009.

FAA AD Differences

Note: This AD differs from the MCAI and/ or service information as follows: No differences.

Other FAA AD Provisions

(g) The following provisions also apply to this AD:

(1) Alternative Methods of Compliance (AMOCs): The Manager, Standards 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: Karl Schletzbaum, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4146; fax: (816) 329–4090. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO.

(2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service.

(3) Reporting Requirements: For any reporting requirement in this AD, a Federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB Control Number. The OMB Control Number for this information collection is 2120–0056. Public reporting for this collection of information is estimated to be approximately 5 minutes per response, including the time for reviewing instructions, completing and reviewing the collection of information. All responses to this collection of information are mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at: 800 Independence Ave., SW., Washington, DC 20591, Attn: Information Collection Clearance Officer, AES–200.

Related Information

(h) Refer to MCAI AGE ˆ NCIA NACIONAL DE AVIAC

 ̧ A

 ̃ O CIVIL—BRAZIL (ANAC) AD No. 2010–08–01, dated September 3, 2010; and EMBRAER Phenom Service Bulletin 500–21–0001, dated December 9, 2009, for related information.
Material Incorporated by Reference

(i) You must use EMBRAER Phenom Service Bulletin 500–21–0001, dated December 9, 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 EMBRAER Empresa Brasileira de Aerona  ́ utica S.A., Phenom Maintenance Support, Av. Brig. Farina Lima, 2170, Sao Jose dos Campos—SP, CEP: 12227– 901—P.O. Box: 38/2, BRASIL, telephone: ++55 12 3927–5383; fax: ++55 12 3927–2610; E-mail: reliability.executive@embraer.com.br; Internet: http://www.embraer.com.br.

(3) You may review copies of the referenced service information at the FAA, Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call 816–329–4148.

(4) You may also review copies of the service information incorporated by reference for this AD 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 Kansas City, Missouri, on October 29, 2010. John Colomy, Acting Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2010–27974 Filed 11–8–10; 8:45 am]

**BILLING CODE 4910–13–P**



### DEPARTMENT OF TRANSPORTATION

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2010–0705; Directorate Identifier 2009–NM–206–AD; Amendment**  **39–16499; AD 2010–23–10]**

**RIN 2120–AA64**



### Airworthiness Directives; McDonnell **Douglas Corporation Model DC–9–14, DC–9–15, and DC–9–15F Airplanes;**  **and Model DC–9–20, DC–9–30, DC–9– 40, and DC–9–50 Series Airplanes** 

**AGENCY** 

### : Federal Aviation Administration (FAA), DOT.

**ACTION** 

### : Final rule.

**SUMMARY** 

### : We are superseding an existing airworthiness directive (AD) for the products listed above. That AD currently requires repetitive high frequency eddy current inspections to detect cracking in the vertical radius (also known as the ‘‘ vertical leg ’’ ) of the upper cap of the center wing rear spar, and repair if necessary. This new AD expands the area to be inspected by including inspections to detect cracking of the horizontal flange of the upper cap of the left and right center wing rear spar, and repair if necessary. This new AD also adds certain airplanes to the applicability. This AD was prompted by reports of cracking in the vertical radius of the upper cap of the center wing rear spar, and the horizontal flange on the inboard side of the of the rear spar upper cap, which resulted from stress corrosion. We are issuing this AD to detect and correct cracking in the vertical leg or the horizontal flange of the upper cap of the left or right center wing rear spar, which could cause a possible fuel leak, damage to the wing skin, and structural failure of the upper cap, and result in reduced structural integrity of the airplane.

**DATES** 

### : This AD is effective December 14, 2010.

The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of December 14, 2010.

**ADDRESSES** 

### : For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, 3855 Lakewood Boulevard, MC D800–0019, Long Beach, California 90846–0001; telephone 206–544–5000, extension 2; fax 206–766–5683; e-mail dse.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 address for the Docket Office (phone: 800–647–5527) is 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** 

### : Wahib Mina, Aerospace Engineer, Airframe Branch, ANM–120L, FAA, Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, California 90712–4137; telephone (562) 627–5324; fax (562) 627–5210.

**SUPPLEMENTARY INFORMATION** 

### :

Discussion

We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede airworthiness


## 68687 Federal Register / Vol. 75, No. 216 / Tuesday, November 9, 2010 / Rules and Regulations

directive (AD) 2004–23–11, Amendment 39–13866 (69 FR 65522, November 15, 2004). That AD applies to the specified products. The NPRM was published in the Federal Register on August 5, 2010 (75 FR 47242). That NPRM proposed to continue to require repetitive high frequency eddy current inspections to detect cracks in the vertical radius (also known as the ‘‘ vertical leg ’’ ) of the upper cap of the center wing rear spar, and repair if necessary. That NPRM also proposed to expand the area to be inspected by including inspections to detect cracking of the horizontal flange of the upper cap of the left and right center wing rear spar, and repair if necessary. In addition, that NPRM proposed to add certain airplanes to the applicability.

Comments

We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM or on the determination of the cost to the public.

Conclusion

We reviewed the relevant data and determined that air safety and the public interest require adopting the AD as proposed, except for minor editorial changes. We have determined that these minor changes:

• Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and

• Do not add any additional burden upon the public than was already proposed in the NPRM. Costs of Compliance

There are approximately 510 airplanes of the affected design in the worldwide fleet. We estimate that 322 airplanes of U.S. registry will be affected by this AD. The following table provides the estimated costs for U.S. operators to comply with this 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

Inspection ......... 3 $85 $0 $255 per inspection cycle. 322 $82,110 per inspection cycle.



### 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 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 removing airworthiness directive (AD) 2004–23–11, Amendment 39–13866 (69 FR 65522, November 15, 2004), and adding the following new AD: 2010–23–10 McDonnell Douglas Corporation: Amendment 39–16499; Docket No. FAA–2010–0705; Directorate Identifier 2009–NM–206–AD. Effective Date (a) This airworthiness directive (AD) is effective December 14, 2010.

Affected ADs

(b) This AD supersedes AD 2004–23–11, Amendment 39–13866.
Applicability

(c) This AD applies to McDonnell Douglas Corporation Model DC–9–14, DC–9–15, DC– 9–15F, DC–9–21, DC–9–31, DC–9–32, DC–9– 32 (VC–9C), DC–9–32F, DC–9–33F, DC–9–34, DC–9–34F, DC–9–32F (C–9A, C–9B), DC–9– 41, and DC–9–51 airplanes; certificated in any category; as identified in Boeing Service Bulletin DC9–57–223, Revision 1, dated August 13, 2009. Subject

(d) Air Transport Association (ATA) of America Code 57: Wings.

Unsafe Condition

(e) This AD results from reports of cracking in the vertical radius (also known as the

‘‘ vertical leg ’’ ) of the upper cap of the center wing rear spar, and the horizontal flange on the inboard side of the rear spar upper cap, which resulted from stress corrosion. The Federal Aviation Administration is issuing this AD to detect and correct cracking in the vertical leg or the horizontal flange of the upper cap of the left or right center wing rear spar, which could cause a possible fuel leak, damage to the wing skin, and structural failure of the upper cap, and result in reduced structural integrity 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.


## 68688 Federal Register / Vol. 75, No. 216 / Tuesday, November 9, 2010 / Rules and Regulations

Restatement of Requirements of AD 2004– 23–11, With Revised Service Information
Inspection

(g) For all airplanes except Model DC–9– 15F airplanes, at the later of the times specified in paragraphs (g)(1) and (g)(2) of this AD: Do a high frequency eddy current inspection to detect cracks in the vertical radius of the upper cap of the center wing rear spar, in accordance with the Accomplishment Instructions of Boeing Service Bulletin DC9–57–223, dated July 21, 2003; or Revision 1, dated August 13, 2009. After the effective date of this AD, only Revision 1 may be used.

(1) Before the accumulation of 25,000 total flight cycles.

(2) Within 15,000 flight cycles or 5 years after December 20, 2004 (the effective date of AD 2004–23–11), whichever occurs first.

Corrective Action

(h)(1) If no crack is found during any inspection required by paragraph (g) of this AD, then repeat the inspection thereafter at intervals not to exceed 15,000 flight cycles or 5 years, whichever occurs first, until the initial inspection required by paragraph (i) of this AD is done.

(2) If any crack is found during the inspection required by paragraph (g) of this AD, before further flight, repair per a method approved by the Manager, Los Angeles Aircraft Certification Office (ACO), FAA. For a repair method to be approved by the Manager, Los Angeles ACO, as required by this paragraph, the Manager’s approval letter must specifically refer to this AD.
New Requirements of This AD
Inspection

(i) At the later of the times specified in paragraphs (i)(1) and (i)(2) of this AD: Do a high frequency eddy current inspection to detect cracking in the vertical leg (also known as the ‘‘ vertical radius ’’ ) and horizontal flange of the left and right rear spar upper cap, inboard and outboard sides, at the bulkhead at wing station Xcw=58.500, in accordance with the Accomplishment Instructions of Boeing Service Bulletin DC9– 57–223, Revision 1, dated August 13, 2009. If no cracking is found, repeat the inspection thereafter at intervals not to exceed 15,000 flight cycles or 5 years, whichever occurs first. Accomplishment of the initial inspection required by paragraph (i) of this AD terminates the requirements of paragraphs (g) and (h)(1) of this AD.

(1) Before the accumulation of 25,000 total flight cycles.

(2) Within 15,000 flight cycles or 5 years after accomplishing the most recent high frequency eddy current inspection required by paragraph (g) of this AD, whichever occurs first.

Corrective Action

(j) If any cracking is found during any inspection required by paragraph (i) of this AD, before further flight, repair the cracking using a method approved in accordance with the procedures specified in paragraph (k) of this AD. Alternative Methods of Compliance (AMOCs)

(k)(1) The Manager, Los Angeles 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: Wahib Mina, Aerospace Engineer, Airframe Branch, ANM–120L, Los Angeles ACO, FAA, 3960 Paramount Boulevard, Lakewood, California 90712–4137; telephone (562) 627–5324; fax (562) 627–5210.

(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 refer to this AD.

(3) An AMOC that provides an acceptable level of safety may be used for any repair required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Los Angeles 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 2004–23–11, Amendment 39–13866, are approved as AMOCs for the corresponding provisions of paragraph (h)(2) of this AD.
Material Incorporated by Reference

(l) You must use Boeing Service Bulletin DC9–57–223, Revision 1, dated August 13, 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, 3855 Lakewood Boulevard, MC D800–0019, Long Beach, California 90846– 0001; telephone 206–544–5000, extension 2; fax 206–766–5683; e-mail dse.boecom@boeing.com; Internet https:// www.myboeingfleet.com.

(3) You may review copies of the service information at the FAA, 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. Issued in Renton, Washington, on October 21, 2010. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2010–28084 Filed 11–8–10; 8:45 am]

**BILLING CODE 4910–13–P**



### DEPARTMENT OF TRANSPORTATION

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2010–0483; Directorate Identifier 2010–NM–065–AD; Amendment**  **39–16502; AD 2010–23–13]**

**RIN 2120–AA64**



### Airworthiness Directives; The Boeing **Company Model 757 Airplanes**

**AGENCY** 

### : Federal Aviation Administration (FAA), DOT.

**ACTION** 

### : Final rule.

**SUMMARY** 

### : We are adopting a new airworthiness directive (AD) for all Model 757 airplanes. This AD requires changing the lower fixed leading edge panel assemblies immediately outboard of the nacelles at slats 4 and 7. This AD results from reports of Model 757 airplanes in service that have drain holes and unsealed panel assemblies in the fixed leading edge adjacent to the inboard end of slats 4 and 7 that are too close to the hot portion of the engines. We are issuing this AD to prevent fuel leaking onto an engine and a consequent fire.

**DATES** 

### : This AD is effective December 14, 2010.

The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of December 14, 2010.

**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)