## 53348 Federal Register / Vol. 76, No. 166 / Friday, August 26, 2011 / Proposed Rules

date of this AD, whichever occurs later, do a high frequency eddy current (HFEC) inspection for cracking of the left and right rib hinge bearing lugs of the aft face of the center section of the horizontal stabilizer, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin MD80–55A069, dated January 19, 2011. For any crack-free lug, repeat the inspection on that lug thereafter at intervals not to exceed 8,200 flight cycles.

(h) If, during any inspection required by paragraph (g) of this AD, any crack is found, before further flight, measure the length of the crack between the points specified in Boeing Alert Service Bulletin MD80–55A069, dated January 19, 2011. Do the action in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin MD80–55A069, dated January 19, 2011.

(1) If the crack length between points ‘A’ and ‘B’ is less than or equal to 0.15 inch and the crack length between points ‘C’ and ‘D’ is less than or equal to 0.05 inch: Before further flight, blend out the crack, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin MD80–55A069, dated January 19, 2011. Within 15,600 flight cycles after doing the blend out, do an HFEC inspection of the blend out on the center section rib hinge bearing lug for cracking, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin MD80–55A069, dated January 19, 2011, and repeat that inspection thereafter at intervals not to exceed 3,900 flight cycles.

(2) If the crack length between points ‘A’ and ‘B’ is greater than 0.15 inch or the crack length between points ‘C’ and ‘D’ is greater than 0.05 inch: Before further flight, replace the horizontal stabilizer center section rib with a new horizontal stabilizer center section rib, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin MD80–55A069, dated January 19, 2011. Repeat the inspection required by paragraph (g) of this AD one time before the accumulation of 23,000 total flight cycles on the new horizontal stabilizer center section rib, and thereafter at intervals not to exceed 11,300 flight cycles.

Actions on Horizontal Stabilizer Ribs Made From 7050–T7451 Material

(i) For Group 2 airplanes, as identified in Boeing Alert Service Bulletin MD80–55A069, dated January 19, 2011: Before the accumulation of 23,000 total flight cycles, or within 4,383 flight cycles after the effective date of this AD, whichever occurs later, do an HFEC inspection for cracking of the left and right rib hinge bearing lugs of the aft face of the center section of the horizontal stabilizer, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin MD80–55A069, dated January 19, 2011. For any crack-free lug, repeat the inspection on that lug thereafter at intervals not to exceed 11,300 flight cycles.

(j) If, during any inspection required by paragraph (i) of this AD, any crack is found, before further flight, measure the length of the crack between the points specified in and in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin MD80–55A069, dated January 19, 2011. (1) If the crack length between points ‘A’ and ‘B’ is less than or equal to 0.15 inch and the crack length between points ‘C’ and ‘D’ is less than or equal to 0.05 inch: Before further flight, blend out the crack, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin MD80–55A069, dated January 19, 2011. Within 15,600 flight cycles after doing the blend out, do an HFEC inspection of the blend out on the center section rib hinge bearing lug for cracking, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin MD80–55A069, dated January 19, 2011, and repeat that inspection thereafter at intervals not to exceed 5,800 flight cycles.

(2) If the crack length between points ‘A’ and ‘B’ is greater than 0.15 inch or the crack length between points ‘C’ and ‘D’ is greater than 0.05 inch: Before further flight, replace the horizontal stabilizer center section rib with a new horizontal stabilizer center section rib, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin MD80–55A069, dated January 19, 2011. Repeat the inspection required by paragraph (i) of this AD one time before the accumulation of 23,000 total flight cycles on the new horizontal stabilizer center section rib, and thereafter at intervals not to exceed 11,300 flight cycles.
No Reporting Requirement

(k) Although Boeing Alert Service Bulletin MD80–55A069, dated January 19, 2011, specifies to submit certain information to the manufacturer, this AD does not include that requirement.
Alternative Methods of Compliance (AMOCs)

(l)(1) The Manager, Los Angeles 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.

(2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding 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, 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 14 CFR 25.571, Amendment 45, and the approval must specifically refer to this AD.

Related Information

(m) For more information about this AD, contact Roger Durbin, Aerospace Engineer, Airframe Branch, ANM–120L, FAA, Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, California 90712–4137; phone: 562–627–5233; fax 562– 627–5210; e-mail: roger.durbin@faa.gov.

(n) 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.

Issued in Renton, Washington, on August 19, 2011. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2011–21853 Filed 8–25–11; 8:45 am]

**BILLING CODE 4910–13–P**



### DEPARTMENT OF TRANSPORTATION

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2011–0908; Directorate Identifier 2010–NM–251–AD]** 

**RIN 2120–AA64**



### Airworthiness Directives; BAE **SYSTEMS (Operations) Limited Model BAe 146 Airplanes and Model Avro**  **146–RJ Airplanes**

**AGENCY** 

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

**ACTION** 

### : Notice of proposed rulemaking (NPRM).

**SUMMARY** 

### : We propose to adopt a new airworthiness directive (AD) for the products listed above that would supersede an existing AD. This proposed 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:

* * * * *

* * * BAE Systems (Operations) Limited has amended the AMM [aircraft maintenance manual] to remove the life limits on shock absorber assemblies, but not the individual shock absorber components, and amend the life limits on the different standards of Main Landing Gear (MLG) Up-Locks and MLG Door Up-Locks in sub-chapter 05–10–15. In addition BAE Systems has amended Chapter 05–10–15 of the AMM to introduce and amend life limits on MLG components.


### * * * * * The unsafe condition is fatigue cracking of certain structural elements which


## 53349 Federal Register / Vol. 76, No. 166 / Friday, August 26, 2011 / Proposed Rules

could adversely affect the structural integrity of these airplanes. The proposed AD would require actions that are intended to address the unsafe condition described in the MCAI.

**DATES** 

### : We must receive comments on this proposed AD by October 11, 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, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.

For service information identified in this proposed AD, contact BAE SYSTEMS (OPERATIONS) LIMITED, Customer Information Department, Prestwick International Airport, Ayrshire, KA9 2RW, Scotland, United Kingdom; telephone +44 1292 675207; fax +44 1292 675704; e-mail RApublications@baesystems.com; Internet http://www.baesystems.com/ Businesses/RegionalAircraft/index.htm. 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 Operations office 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 Operations 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** 

### : 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.

**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–2011–0908; Directorate Identifier 2010–NM–251–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 based on 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 May 3, 2010, we issued AD 2010– 10–22, Amendment 39–16301 (75 FR 28463, May 21, 2010). That AD required actions intended to address an unsafe condition on the products listed above.

Since we issued AD 2010–10–22, we have determined that new life limits on certain main landing gear components are necessary. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA Airworthiness Directive 2010– 0166, dated August 6, 2010 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states:

The BAe 146/AVRO 146–RJ Aircraft Maintenance Manual (AMM) includes chapters 05–10 ‘‘Time Limits’’, 05–15 ‘‘Critical Design Configuration Control Limitations (CDCCL)—Fuel System Description and Operation’’ and 05–20‘‘Scheduled Maintenance Checks’’, some subchapters of which have been identified as requirements for continued airworthiness and [EASA] AD 2009–0215 [which corresponds to FAA AD 2010–10–22] was issued to require operators to comply with those instructions.

Since the issuance of that AD [2009–0215] BAE Systems (Operations) Limited has amended the AMM to remove the life limits on shock absorber assemblies, but not the individual shock absorber components, and amend the life limits on the differentstandards of Main Landing Gear (MLG) UpLocks and MLG Door Up-Locks in subchapter 05–10–15. In addition BAE Systems has amended Chapter 05–10–15 of the AMM to introduce and amend life limits on MLG components.

For the reasons described above, this [EASA] AD amends the requirements of AD 2009–0215, which is superseded, and requires the implementation of the instructions, limitations, inspections and corrective measures as specified in the defined parts of Chapter 05 of the AMM at Revision 100. 

### The unsafe condition is fatigue cracking of certain structural elements which could adversely affect the structural integrity of these airplanes. You may obtain further information by examining the MCAI in the AD docket.

Relevant Service Information

BAE SYSTEMS (Operations) Limited has issued Subject 05–10–15, ‘‘Aircraft Equipment Airworthiness Limitations,’’ of Chapter 05, ‘‘Time Limits/ Maintenance Checks,’’ of BAe 146 Series/AVRO 146–RJ Series Aircraft Maintenance Manual, Revision 104, dated April 15, 2011. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. FAA’s Determination and Requirements of This Proposed AD

This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of the same type design.

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 proposed different actions in this AD from those in the MCAI in order to follow FAA policies. Any such differences are highlighted in a NOTE within the proposed AD. Costs of Compliance

Based on the service information, we estimate that this proposed AD would affect about 2 products of U.S. registry.

The actions that are required by AD 2010–10–22 and retained in this proposed AD take about 2 work-hours per product, at an average labor rate of $85 per work hour. Required parts cost


## 53350 Federal Register / Vol. 76, No. 166 / Friday, August 26, 2011 / Proposed Rules

about $0 per product. Based on these figures, the estimated cost of the currently required actions is $170 per product.

We estimate that it would take about 1 work-hour per product to comply with the new basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of the proposed AD on U.S. operators to be $170, or $85 per product. 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 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 this 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),

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. 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:

**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 39–16301 (75 FR 28463, May 21, 2010) and adding the following new AD:
BAE SYSTEMS (OPERATIONS) LIMITED: Docket No. FAA–2011–0908; Directorate Identifier 2010–NM–251–AD.

Comments Due Date

(a) We must receive comments by October 11, 2011.

Affected ADs

(b) This AD supersedes AD 2010–10–22, Amendment 39–16301.
Applicability

(c) This AD applies to all BAE SYSTEMS (OPERATIONS) LIMITED Model BAe 146– 100A, –200A, and –300A airplanes; and Model Avro 146–RJ70A, 146–RJ85A, and 146–RJ100A airplanes; certificated in any category.

Note 1: This AD requires revisions to certain operator maintenance documents to include new actions ( e.g., inspections) and/ or Critical Design Configuration Control Limitations (CDCCLs). Compliance with these actions and/or CDCCLs is required by 14 CFR 91.403(c). For airplanes that have been previously modified, altered, or repaired in the areas addressed by this AD, the operator may not be able to accomplish the actions described in the revisions. In this situation to comply with 14 CFR 91.403(c), the operator must request approval of an alternative method of compliance (AMOC) according to paragraph (l) of this AD. The request should include a description of changes to the required actions that will ensure the continued operational safety of the airplane.

Subject

(d) Air Transport Association (ATA) of America Code 05

Reason

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


### * * * * *

* * * BAE Systems (Operations) Limited has amended the AMM [aircraft maintenance manual] to remove the life limits on shock absorber assemblies, but not the individual shock absorber components, and amend the life limits on the different standards of Main Landing Gear (MLG) Up-Locks and MLG Door Up-Locks in sub-chapter 05–10–15. In addition BAE Systems has amended Chapter 05–10–15 of the AMM to introduce and amend life limits on MLG components.


### * * * * *
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 Certain Requirements of AD
2010–10–22

New Airworthiness Limitations Revisions

(g) Within 90 days after June 25, 2010 (the effective date of AD 2010–10–22), revise the maintenance program, by incorporating Chapter 5 of the BAE SYSTEMS (Operations) Limited BAe146 Series/Avro146–RJ Series AMM to incorporate new and more restrictive life limits for certain items and new and more restrictive inspections to detect fatigue cracking in certain structures, and to add fuel system critical design configuration control limitations (CDCCLs) to prevent ignition sources in the fuel tanks, in accordance with a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA) (or its delegated agent).

Note 2: Guidance on revising Chapter 5 of the BAE SYSTEMS (Operations) Limited BAe146 Series/Avro146–RJ Series AMM, Revision 97, dated July 15, 2009, can be found in the applicable sub-chapters listed in Table 1 of this AD.



### TABLE 

### 1—A PPLICABLE 

### AMM S UB

### -C HAPTERS

AMM Sub-chapter Subject

05–10–01 ..................................... Airframe Airworthiness Limitations before Life Extension Programme. 05–10–05 1 .................................. Airframe Airworthiness Limitations, Life Extension Programme Landings Life Extended. 05–10–10 2 .................................. Airframe Airworthiness Limitations, Life Extension Programme Calendar Life Extended. 05–10–15 ..................................... Aircraft Equipment—Airworthiness Limitations. 05–10–17 ..................................... Power Plant Airworthiness Limitations. 05–15–00 ..................................... Critical Design Configuration Control Limitations (CDCCL)—Fuel System Description and Operation. 05–20–00 3 .................................. Scheduled Maintenance.


## 53351 Federal Register / Vol. 76, No. 166 / Friday, August 26, 2011 / Proposed Rules

TABLE 

### 1—A PPLICABLE 

### AMM S UB

### -C HAPTERS

### —Continued

AMM Sub-chapter Subject

05–20–01 ..................................... Airframe Scheduled Maintenance—Before Life Extension Programme. 05–20–05 1 .................................. Airframe Scheduled Maintenance—Life Extension Programme Landings Life Extended. 05–20–10 2 .................................. Airframe Scheduled Maintenance—Life Extension Programme Calendar Life Extended. 05–20–15 ..................................... Aircraft Equipment Scheduled Maintenance.

1 Applicable only to airplanes post-modification HCM20011A or HCM20012A or HCM20013A.

2 Applicable only to airplanes post-modification HCM20010A.

3 Paragraphs 5 and 6 only, on the Corrosion Prevention and Control Program (CPCP) and the Supplemental Structural Inspection Docu ment (SSID).

Note 3: Sub-chapter 05–15–00 of the BAE SYSTEMS (Operations) Limited BAe146 Series/Avro146–RJ Series AMM, is the CDCCL.

Note 4: Within Sub-chapter 05–20–00 of the BAE SYSTEMS (Operations) Limited BAe146 Series/Avro 146–RJ Series AMM, the relevant issues of the support documents are as follows: BAE SYSTEMS (Operations) Limited BAe 146 Series/Avro 146–RJ Corrosion Prevention and Control Program Document CPCP–146–01, Revision 3, dated July 15, 2008, including BAE SYSTEMS (Operations) Limited Temporary Revision (TR) 2.1, dated December 2008; and BAE SYSTEMS (Operations) Limited BAe146 Series Supplemental Structural Inspection Document SSID–146–01, Revision 1, dated June 15, 2009.

Note 5: Within Sub-chapter 05–20–01 of the BAE SYSTEMS (Operations) Limited BAe146 Series/Avro146–RJ Series AMM, the relevant issue of BAE SYSTEMS (Operations) Limited BAe 146/Avro 146–RJ Maintenance Review Board Report Document MRB 146– 01, Issue 2, is Revision 15, dated March 2009 (mis-identified in EASA AD 2009–0215, dated October 7, 2009, as being dated May 2009).

Note 6: Notwithstanding any other maintenance or operational requirements, components that have been identified as airworthy or installed on the affected airplanes before revision of Chapter 5 of the AMM, as required by paragraph (g) of this AD; do not need to be reworked in accordance with the CDCCLs. However, once the ALS or AMM has been revised, future maintenance actions on these components must be done in accordance with the CDCCLs.

(h) Except as specified in paragraphs (i) and (j) of this AD: After the actions specified in paragraph (g) of this AD have been accomplished, no alternative inspections or inspection intervals may be approved for the structural elements specified in the documents listed in paragraph (g) of this AD.

(i) Modifying the main fittings of the mainlanding gear in accordance with MessierDowty Service Bulletin 146–32–171, dated August 11, 2009, extends the safe limit of the main landing gear main fitting from 32,000 landings to 50,000 landings on the main fitting.
New Requirements of This AD

New Airworthiness Limitations Revisions

(j) Within 90 days after the effective date of this AD, revise the maintenance program, by incorporating Sub-chapter 05–10–15, ‘‘Aircraft Equipment Airworthiness Limitations’’ of Chapter 05, ‘‘Time Limits/ Maintenance Checks,’’ of the BAE SYSTEMS (Operations) Limited BAe 146 Series/Avro 146–RJ Series AMM, Revision 104, dated April 15, 2011, to remove life limits on shock absorber assemblies, but not the individual shock absorber components, amend life limits on MLG up-locks and door up-locks, and to introduce and amend life limits on MLG components. Incorporating the new life limits and inspections into the maintenance program terminates the requirements of paragraph (g) of this AD for Sub-chapter 05– 10–15, ‘‘Aircraft Equipment Airworthiness Limitations’’ of Chapter 05, ‘‘Time Limits/ Maintenance Checks,’’ of the BAE SYSTEMS (Operations) Limited BAe 146 Series/Avro 146–RJ Series AMM, Revision 104, dated April 15, 2011, and after incorporation has been done, the limitations required by paragraph (g) of this AD for Sub-chapter 05– 10–15, ‘‘Aircraft Equipment Airworthiness Limitations’’ of Chapter 05, ‘‘Time Limits/ Maintenance Checks,’’ of the BAE SYSTEMS (Operations) Limited BAe 146 Series/Avro 146–RJ Series AMM, Revision 104, dated April 15, 2011, may be removed from the maintenance program.
No Alternative Actions, Intervals, and/or Critical Design Configuration Control Limitations (CDCCLs)

(k) After accomplishing the revision required by paragraph (j) of this AD, no alternative actions ( e.g., inspections), intervals, and/or CDCCLs may be used, unless the actions, intervals, and/or CDCCLs are approved as an alternative method of compliance (AMOC) in accordance with the procedures specified in paragraph (l) of this AD.

FAA AD Differences

Note 7: This AD differs from the MCAI and/or service information as follows: Although EASA Airworthiness Directive 2010–0166, dated August 6, 2010, specifies both revising the maintenance program to include limitations, and doing certain repetitive actions ( e.g., inspections) and/or maintaining CDCCLs, this AD only requires the revision. Requiring a revision of the maintenance program, rather than requiring individual repetitive actions and/or maintaining CDCCLs, requires operators to record AD compliance only at the time the revision is made. Repetitive actions and/or maintaining CDCCLs specified in the airworthiness limitations must be complied within accordance with 14 CFR 91.403(c). Other FAA AD Provisions (l) The following provisions also apply to this AD:

(1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, 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 International Branch, send it 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. Information may be e-mailed to: 9- ANM-116-AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. The AMOC approval letter must specifically reference this AD.

(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.

Related Information

(m) Refer to MCAI EASA Airworthiness Directive 2010–0166, dated August 6, 2010; and Sub-chapter 05–10–15, ‘‘Aircraft Equipment Airworthiness Limitations,’’ of Chapter 05, ‘‘Time Limits/Maintenance Checks,’’ of the BAE SYSTEMS (Operations) Limited BAe 146 Series/Avro 146–RJ Series AMM, Revision 104, dated April 15, 2011; for related information.

Issued in Renton, Washington, on August
19, 2011. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2011–21851 Filed 8–25–11; 8:45 am]

**BILLING CODE 4910–13–P**