Document Headings

                    Document headings vary by document type but may contain                    the following:                  
                -                       the agency or agencies that issued and signed a document                    
                -                       the number of the CFR title and the number of each part                      the document amends, proposes to amend, or is directly                      related to                    
                -                       the agency docket number / agency internal file number                    
                -                       the RIN which identifies each regulatory action listed in                      the Unified Agenda of Federal Regulatory and Deregulatory                      Actions                    

                    See the                                          Document Drafting Handbook                                        for more details.                  

###### Department of Transportation

###### Federal Aviation Administration

          - 14 CFR Part 39
          - [Docket No. FAA-2009-1254; Directorate Identifier 2009-NM-040-AD; Amendment 39-16292; AD 2010-10-13]
          - RIN 2120-AA64

# AGENCY:

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

# ACTION:

Final rule.

# SUMMARY:

We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as:

During the removal of the wing removable leading edge on a BAe 146 aircraft for a repair (not related to the subject addressed by this AD), corrosion was found on the wing fixed leading edge structure. The investigation determined that the existing scheduled environmental and fatigue inspections would not have detected the corrosion or fatigue damage.

Corrosion or fatigue damage in this area, if not detected and corrected, could lead to degradation of the structural integrity of the wing.

* * * * *

We are issuing this AD to require actions to correct the unsafe condition on these products.

# DATES:

This AD becomes effective June 21, 2010.

The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of June 21, 2010.

# ADDRESSES:

                        You may examine the AD docket on the Internet at                         *http://www.regulations.gov*                         or in person at the U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC.                    

# FOR FURTHER INFORMATION CONTACT:

                        Todd Thompson, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton,                               ( print page 27420)                            Washington 98057-3356; telephone (425) 227-1175; fax (425) 227-1149.                    

# SUPPLEMENTARY INFORMATION:

## Discussion

                    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. That NPRM was published in the                     **Federal Register**                     on January 12, 2010 (75 FR 1560). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states:                

During the removal of the wing removable leading edge on a BAe 146 aircraft for a repair (not related to the subject addressed by this AD), corrosion was found on the wing fixed leading edge structure. The investigation determined that the existing scheduled environmental and fatigue inspections would not have detected the corrosion or fatigue damage.

Corrosion or fatigue damage in this area, if not detected and corrected, could lead to degradation of the structural integrity of the wing.

                        For the reason described above, this AD requires repetitive inspections of the wing fixed leading edge and front spar structure for corrosion and/or fatigue damage [                        *e.g.,*                         cracking] and repair, depending on findings.                    

There are two alternative inspection methods: Method 1 is a combination of a detailed visual inspection and a visual inspection; Method 2 is a detailed visual inspection. You may obtain further information by examining the MCAI in the AD docket.

## 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.

## Clarification of Compliance Time Language

We have revised paragraph (f)(1)(iii) of this AD to clarify the compliance time language as specified in Note 4 of this AD.

## Conclusion

We reviewed the available data, and determined that air safety and the public interest require adopting the AD with the change described previously. We determined that this change will not increase the economic burden on any operator or increase the scope of the AD.

## Differences Between This AD and the MCAI or Service Information

We have reviewed the MCAI and related service information and, in general, agree with their substance. But we might have found it necessary to use different words from those in the MCAI to ensure the AD is clear for U.S. operators and is enforceable. In making these changes, we do not intend to differ substantively from the information provided in the MCAI and related service information.

We might also have required different actions in this AD from those in the MCAI in order to follow our FAA policies. Any such differences are highlighted in a NOTE within the AD.

## Explanation of Change to Costs of Compliance

Since issuance of the NPRM, we have increased the labor rate used in the Costs of Compliance from $80 per work-hour to $85 per work-hour. The Costs of Compliance information, below, reflects this increase in the specified hourly labor rate.

## Costs of Compliance

We estimate that this AD will affect 1 product of U.S. registry. We also estimate that it will take about 12 work-hours per product to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this AD to the U.S. operator to be $1,020.

## 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 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 this AD:*

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.

## Examining the AD Docket

                    You may examine the AD docket on the Internet at                     *http://www.regulations.gov;*                     or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains the NPRM, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647-5527) is in the                     **ADDRESSES**                     section. Comments will be available in the AD docket shortly after receipt.                

# 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 

2. The FAA amends § 39.13 by adding the following new AD: 

**2010-10-13 BAE Systems (Operations) Limited:**                             Amendment 39-16292. Docket No. FAA-2009-1254; Directorate Identifier 2009-NM-040-AD.                        

## Effective Date

(a) This airworthiness directive (AD) becomes effective June 21, 2010.

## Affected ADs

(b) None.

## Applicability

                            (c) This AD applies to BAE Systems (Operations) Limited Model BAe 146-100A, -200A, and -300A series airplanes; and Model Avro 146-RJ70A, 146-RJ85A, and 146-RJ100A airplanes; certificated in any category, all serial numbers.                                  ( print page 27421)    

## Subject

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

## Reason

(e) The mandatory continuing airworthiness information (MCAI) states:

During the removal of the wing removable leading edge on a BAe 146 aircraft for a repair (not related to the subject addressed by this AD), corrosion was found on the wing fixed leading edge structure. The investigation determined that the existing scheduled environmental and fatigue inspections would not have detected the corrosion or fatigue damage.

Corrosion or fatigue damage in this area, if not detected and corrected, could lead to degradation of the structural integrity of the wing.

                            For the reason described above, this AD requires repetitive inspections of the wing fixed leading edge and front spar structure for corrosion and/or fatigue damage [                            *e.g.,*                             cracking] and repair, depending on findings.                        

There are two alternative inspection methods: Method 1 is a combination of a detailed visual inspection and a visual inspection; Method 2 is a detailed visual inspection.

## Actions and Compliance

(f) Unless already done, do the following actions.

(1) At the applicable time identified in paragraph (f)(1)(i), (f)(1)(ii), or (f)(1)(iii) of this AD: Perform a detailed visual inspection and visual inspection (Method 1) or a detailed visual inspection (Method 2) for cracking and corrosion of the wing fixed leading edge and front spar structure, in accordance with paragraph 2.C. or 2.D., as applicable, of the Accomplishment Instructions of BAE Systems (Operations) Limited Inspection Service Bulletin ISB.57-072, Revision 1, dated September 25, 2008.

(i) For airplanes with less than 9 years since date of issuance of the original airworthiness certificate or the date of issuance of the original export certificate of airworthiness as of the effective date of this AD: Within 18 months after the effective date of this AD.

(ii) For airplanes with 9 years or more, but less than 15 years, since date of issuance of the original airworthiness certificate or the date of issuance of the original export certificate of airworthiness as of the effective date of this AD: Within 18 months after the effective date of this AD or within 16 years since date of issuance of the original airworthiness certificate or the date of issuance of the original export certificate of airworthiness, whichever occurs first.

(iii) For airplanes with 15 years or more since date of issuance of the original airworthiness certificate or the date of issuance of the original export certificate of airworthiness as of the effective date of this AD: Within 6 months after the effective date of this AD.

# Note 1:

 Where BAE Systems (Operations) Limited Inspection Service Bulletin ISB.57-072, Revision 1, dated September 25, 2008, refers to a “visual inspection,” this term describes an inspection using visual inspection equipment as defined in Appendix 3 of that service bulletin. In other BAE Systems instructions for continued airworthiness, including the Maintenance Planning Document (MPD) and the Corrosion Prevention and Control Programme (CPCP), such an inspection is referred to as a “Special Detailed Inspection” (SDI).

# Note 2: 

At the discretion of the airplane owner/operator, corrosion protection may be embodied on those areas subject to a detailed visual inspection, in accordance with paragraph 2.E. or paragraph 2.F. of the Accomplishment Instructions of BAE Systems (Operations) Limited Inspection Service Bulletin ISB.57-072, Revision 1, dated September 25, 2008. Embodiment of enhanced corrosion protection in accordance with paragraph 2.E. of the Accomplishment Instructions of BAE Systems (Operations) Limited Inspection Service Bulletin ISB.57-072, Revision 1, dated September 25, 2008, allows the interval of the repetitive inspection (as required by paragraph (f)(2) of this AD) to be extended in the area(s) of application in accordance with paragraph (f)(2)(i) or (f)(2)(ii) of this AD, as applicable. 

(2) After doing the initial inspection required by paragraph (f)(1) of this AD, at the applicable intervals specified in paragraph (f)(2)(i) or (f)(2)(ii) of this AD, accomplish the repetitive inspections of the wing fixed leading edge and front spar structure for cracking and corrosion in the “area of inspection” specified in Table 1 of paragraph 1.D., “Compliance,” of BAE Systems (Operations) Limited Inspection Service Bulletin ISB.57-072, Revision 1, dated September 25, 2008. Do the inspections in accordance with paragraph 2.C. (Method 1) or paragraph 2.D. (Method 2) of the Accomplishment Instructions of BAE Systems (Operations) Limited Inspection Service Bulletin ISB.57-072, Revision 1, dated September 25, 2008. Where previously applied, enhanced corrosion protection may then be re-applied, as an option, in accordance with paragraph 2.E. of the Accomplishment Instructions of BAE Systems (Operations) Limited Inspection Service Bulletin ISB.57-072, Revision 1, dated September 25, 2008. Perform the repetitive inspections at the times specified in paragraph (f)(2)(i) or (f)(2)(ii) of this AD, as applicable.

(i) For airplanes having enhanced corrosion protection that was applied during the previous inspection: Inspect at intervals not to exceed 144 months.

(ii) For airplanes not having enhanced corrosion protection that was applied during the previous inspection: Inspect at intervals not to exceed 72 months.

(3) After doing the initial inspection required by paragraph (f)(1) of this AD, at intervals not to exceed 36,000 flight cycles, accomplish fatigue inspections in accordance with paragraph 2.C. (Method 1) or paragraph 2.D. (Method 2) of the Accomplishment Instructions of BAE Systems (Operations) Limited Inspection Service Bulletin ISB.57-072, Revision 1, dated September 25, 2008.

(4) If any cracking or corrosion is found during any inspection required by this AD, before further flight, repair in accordance with the Accomplishment Instructions of BAE Systems (Operations) Limited Inspection Service Bulletin ISB.57-072, Revision 1, dated September 25, 2008.

(5) No repair terminates the inspection requirements of this AD.

(6) Actions done before the effective date of this AD in accordance with BAE Systems (Operations) Limited Inspection Service Bulletin ISB.57-072, dated February 22, 2008, are considered acceptable for compliance with the corresponding actions specified in this AD.

                            (7) Submit a report of the findings (both positive and negative) of the inspection required by paragraph (f)(1) of this AD to Customer Liaison, Customer Support (Building 37), BAE Systems (Operations) Limited, Prestwick International Airport, Ayrshire, KA9 2RW, Scotland; fax +44 (0) 1292 675432; e-mail                             *raengliaison@baesystems.com,*                             at the applicable time specified in paragraphs (f)(7)(i) and (f)(7)(ii) of this AD. The report must include the inspection results, a description of any discrepancies found, the airplane serial number, and the number of landings and flight hours on the airplane.                        

(i) If the inspection was done on or after the effective date of this AD: Submit the report within 30 days after the inspection.

(ii) If the inspection was done before the effective date of this AD: Submit the report within 30 days after the effective date of this AD.

# Note 3:

 The inspections required by this AD prevail over the Maintenance Review Board Report (MRBR), MPD, CPCP, and Supplemental Structural Inspection Document (SSID) inspections defined in paragraph 1.C.(3) of BAE Systems (Operations) Limited Inspection Service Bulletin ISB.57-072, Revision 1, dated September 25, 2008.

## FAA AD Differences

# Note 4:

 This AD differs from the MCAI and/or service information as follows: Where the EASA AD refers to “since entry into service,” this AD specifies the date of issuance of the original airworthiness certificate or the date of issuance of the original export certificate of airworthiness.

## Other FAA AD Provisions

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

                            (1)                             *Alternative Methods of Compliance (AMOCs):*                             The Manager, International Branch, ANM-116, Transport Airplane Directorate, 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: Todd Thompson, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 227-1175; fax (425) 227-1149. 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.                                  ( print page 27422)    

                            (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, under the provisions of the Paperwork Reduction Act (44 U.S.C. 3501*et seq.*), the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120-0056.                        

## Related Information

(h) Refer to MCAI European Aviation Safety Agency Airworthiness Directive 2009-0014, dated January 21, 2009; and BAE Systems (Operations) Limited Inspection Service Bulletin ISB.57-072, Revision 1, dated September 25, 2008; for related information.

## Material Incorporated by Reference

(i) You must use BAE Systems (Operations) Limited Inspection Service Bulletin ISB.57-072, Revision 1, dated September 25, 2008, 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 BAE Systems Regional Aircraft, 13850 McLearen Road, Herndon, Virginia 20171; telephone 703-736-1080; e-mail                             *raebusiness@baesystems.com;*                             Internet                             *http://www.baesystems.com/​Businesses/​RegionalAircraft/​index.htm*.                        

(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 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 April 30, 2010.

Ali Bahrami,

Manager, Transport Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2010-11182 Filed 5-14-10; 8:45 am]

BILLING CODE 4910-13-P