Federal Register / Vol. 76, No. 229 / Tuesday, November 29, 2011 / Rules and Regulations 73477 

admission to the United States as a 

derivative of an asylee. 

* * * * * 

PART 212—DOCUMENTARY 

REQUIREMENTS: NONIMMIGRANTS; 

WAIVERS; ADMISSION OF CERTAIN 

INADMISSIBLE ALIENS; PAROLE 

§ 212.2 [Corrected] 

■ 9. On page 53786, second column, 

remove amendment 64.a and 

redesignate 64b through f as 64a through 

e accordingly. 

§ 212.7 [Corrected] 

■ 10. On page 53787, first column, 

remove amendment 69.a. and 

redesignate 69b through m as 69a 

through l accordingly. 

§ 212.15 [Corrected] 

■ 11. On page 53788, first column, 

revise amendatory instruction 75h. to 

read as follows: 

75. * * * 

■ h. ‘‘Revising the term ‘‘Form I–905’’ to 

read ‘‘the request’’ in paragraph 

(m)(2).’’. 

PART 213a—AFFIDAVITS OF 

SUPPORT ON BEHALF OF ALIENS 

§ 213a.2 [Corrected] 

■ 12. On page 53788, second column, 

revise amendatory instruction 80–82d. 

to read as follows: 

‘‘80–82 * * * 

■ d. Revising the phrase ‘‘the Form 

I–130 or Form I–600 immigrant visa 

petition (or the Form I–129F petition, 

for a K nonimmigrant seeking 

adjustment)’’ to read ‘‘a relative, orphan 

or fiance ́(e) petition’’ in the first 

sentence of paragraph (b)(1);’’. 

■ 13. On page 53788, second column, 

revise amendatory instruction 80–82e. 

to read as follows: 

‘‘80–82 * * * 

■ e. Revising the phrase ‘‘Form I–864P 

Poverty Guidelines’’ to read ‘‘the 

Poverty Guidelines’’ in paragraph 

(c)(2)(i)(A);’’. 

■ 14. On page 53788, third column, 

revise the introductory text to 

amendatory instruction 80–82l. to read 

as follows: 

‘‘80–82 * * * 

■ l. Section 213a.2 is further amended 

by revising the term ‘‘Forms I–864’’ to 

read ‘‘affidavits of support’’ and the 

term ‘‘A Form I–864’’ to read ‘‘An 

affidavit of support’’ and the terms 

‘‘Form I–864’’ and ‘‘the Form I–864’’ to 

read ‘‘an affidavit of support’’ wherever 

those terms appear in the following 

places:’’ 

■ 15. On page 53788, third column, 

amendment 80–82, add new 

instructions n. and o. to read as follows: 

■ n. Section 213a.2 is further amended 

by revising the terms ‘‘any Forms 

I–864A’’ to read ‘‘any affidavit of 

support attachments’’ and the term ‘‘any 

Form I–864A’’ to read ‘‘any affidavit of 

support attachment’’ wherever those 

terms appear in paragraphs (a)(1)(ii), 

(iii), (iv), and (v). 

■ o. Section 213a.2 is further amended 

by revising the term ‘‘Form I–864 or 

I–864A’’ to read ‘‘affidavit of support 

and any required attachments’’; the term 

‘‘I–864A’’ to read ‘‘affidavit of support 

attachment’’; and the term ‘‘a Form 

I–864 or I–864A’’ to read ‘‘an affidavit 

of support and any required 

attachments’’ wherever those terms 

appear in the following places: 

i. Paragraph (a)(1)(v)(A); 

ii. Paragraph (c)(2)(v); and 

iii. Paragraph (e)(2)(i)(D).’’ 

PART 244—TEMPORARY PROTECTED 

STATUS FOR NATIONALS OF 

DESIGNATED STATES 

§ 244.7 [Corrected] 

■ 16. On pages 53791, third column, 

revise amendatory instruction 108.b. to 

read as follows: 

‘‘108. * * * 

■ b. Revising the term ‘‘the Attorney 

General’’ to read ‘‘DHS’’ in paragraph 

(b);’’ 

§ 244.14 [Corrected] 

■ 17. On pages 53792, second column, 

revise amendatory instruction 113.d. to 

read as follows: 

‘‘113. * * * 

■ d. Revising the term ‘‘the Attorney 

General’’ to read ‘‘DHS’’ in paragraph 

(a)(3);’’. 

PART 245—ADJUSTMENT OF STATUS 

TO THAT OF PERSON ADMITTED FOR 

PERMANENT RESIDENCE 

§ 245.21 [Corrected] 

■ 18. On page 53794, first column, 

amendment 129–130, remove 

instruction j. and redesignate 

instructions k. and l. as j. and k., 

respectively. 

■ 19. On page 53794, first column, 

revise the introductory text to newly 

redesignated amendatory instruction 

129–130k to read as follows: 

‘‘129–130. * * * 

■ k. By revising the terms ‘‘Service’’, 

‘‘The Service’’ and ‘‘the Service’’ to read 

‘‘USCIS’’ and the term ‘‘Service’s’’ to 

read ‘‘USCIS’s’’ wherever the terms 

appear in the following paragraphs:’’. 

PART 324—SPECIAL CLASSES OF 

PERSONS WHO MAY BE 

NATURALIZED: WOMEN WHO HAVE 

LOST UNITED STATES CITIZENSHIP 

BY MARRIAGE AND FORMER 

CITIZENS WHOSE NATURALIZATION 

IS AUTHORIZED BY PRIVATE LAW 

§ 324.2 [Corrected] 

■ 20. On page 53800, first column, 

revise amendatory instruction 191 to 

read as follows: 

■ ‘‘191. In § 324.2, paragraph (b) is 

amended by revising the term ‘‘Form 

N–400, as required by § 316.4 of this 

chapter’’ to read ‘‘the form designated 

by USCIS in accordance with the form 

instructions and with the fee prescribed 

in 8 CFR 103.7(b)(1) as required by 8 

CFR 316.4’’.’’ 

PART 335—EXAMINATION ON 

APPLICATION FOR NATURALIZATION\ 

§ 335.9 [Corrected] 

■ 21. On page 53801, third column, 

revise amendatory instruction 220.b. to 

read as follows: 

‘‘220. * * * 

b. Revising the terms ‘‘district 

director’’, ‘‘The district director’’, ‘‘the 

district director’’, and ‘‘the Service’’ to 

read ‘‘USCIS’’ and the term ‘‘Service’s’’ 

to read ‘‘USCIS’s’’.’’ 

Christina E. McDonald, 

Associate General Counsel for Regulatory 

Affairs. 

[FR Doc. 2011–30510 Filed 11–28–11; 8:45 am] 

BILLING CODE 9111–97–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0908; Directorate 

Identifier 2010–NM–251–AD; Amendment 

39–16870; AD 2011–24–06] 

RIN 2120–AA64 

Airworthiness Directives; BAE 

SYSTEMS (Operations) Limited 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) 

that 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. This AD 

results from mandatory continuing 


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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 

amended Chapter 05–10–15 of the AMM 

[aircraft maintenance manual] to introduce a 

new hydraulic filter assembly life limit and 

to remove the tables containing the 

Mandatory Life Limitations (Landings) on the 

Bolts and Pins as the information is now 

included in the SSID [supplemental 

structural inspection document] which is 

already mandated by the same AD. In 

addition, BAE Systems amended Chapter 05– 

10–15 of the AMM to enable the use of RJ85 

MLG [main landing gear] main fittings for 

lighter weight 146–200 aircraft using the 

same safe life of 50,000 Flight Cycles (FC) 

and the use of RJ100 MLG main fittings for 

lighter weight RJ85, 146–200 and 146–300 

aircraft using the same safe life of 40,000 FC. 

* * * * * 

The unsafe condition is fatigue cracking 

of certain structural elements which 

could adversely affect the structural 

integrity of these airplanes. We are 

issuing this AD to require actions to 

correct the unsafe condition on these 

products. 

DATES: This AD becomes effective 

January 3, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of January 3, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of June 25, 2010 (75 FR 

28463, May 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, 

Washington 98057–3356; phone: (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 August 26, 2011 (76 FR 

53348), and proposed to supersede AD 

2010–10–22, Amendment 39–16301 (75 

FR 28463, May 21, 2010). That NPRM 

proposed to correct an unsafe condition 

for the specified products. 

Since we issued AD 2010–10–22, 

Amendment 39–16301 (75 FR 28463, 

May 21, 2010), we have determined that 

new life limits on certain MLG 

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, 

Amendment 39–16301 (75 FR 28463, May 21, 

2010)] 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 different 

standards 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. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (76 

FR 53348, August 26, 2011) or on the 

determination of the cost to the public. 

Changes to the AD 

Since we issued the NPRM (76 FR 

53348, August 26, 2011), we have 

reviewed EASA AD 2011–0048, dated 

March 18, 2011, which supersedes 

EASA AD 2010–0166, dated August 6, 

2010, and has no substantive changes. 

The actions required by this AD 

correspond with the actions specified in 

EASA AD 2011–0048, dated March 18, 

2011. We have revised the Summary 

and paragraphs (e) and (m) of this AD 

to refer to EASA AD 2011–0048, dated 

March 18, 2011. No other changes have 

been made to this AD. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting the AD 

with the changes described previously. 

We determined that these changes 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. 

Costs of Compliance 

We estimate that this AD will affect 

about 2 products of U.S. registry. 

The actions that are required by AD 

2010–10–22, Amendment 39–16301 (75 

FR 28463, May 21, 2010) and retained 

in this AD take about 2 work-hours per 

product, at an average labor rate of $85 

per work-hour. Required parts cost 

about $0 per product. Based on these 

figures, the estimated cost of the 

currently required actions is $170 per 

product. 

We estimate that it will take about 1 

work-hour per product to comply with 

the new basic requirements of this AD. 

The average labor rate is $85 per workhour. Based on these figures, we 

estimate the cost of this AD to the 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 


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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 (76 FR 53348, 

August 26, 2011), 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 [Amended] 

■ 2. The FAA amends § 39.13 by 

removing Amendment 39–16301 (75 FR 

28463, May 21, 2010) and adding the 

following new AD: 

2011–24–06 BAE SYSTEMS (Operations) 

Limited: Amendment 39–16870. Docket 

No. FAA–2011–0908; Directorate 

Identifier 2010–NM–251–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective January 3, 2012. 

Affected ADs 

(b) This AD supersedes AD 2010–10–22, 

Amendment 39–16301 (75 FR 28463, May 21, 

2010). 

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)(1) 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 

amended Chapter 05–10–15 of the AMM 

[aircraft maintenance manual] to introduce a 

new hydraulic filter assembly life limit and 

to remove the tables containing the 

Mandatory Life Limitations (Landings) on the 

Bolts and Pins as the information is now 

included in the SSID [Supplemental 

Structural Inspection Document] which is 

already mandated by the same AD. In 

addition, BAE Systems amended Chapter 05– 

10–15 of the AMM to enable the use of RJ85 

MLG [main landing gear] main fittings for 

lighter weight 146–200 aircraft using the 

same safe life of 50,000 Flight Cycles (FC) 

and the use of RJ100 MLG main fittings for 

lighter weight RJ85, 146–200 and 146–300 

aircraft using the same safe life of 40,000 FC. 

* * * * * 

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, Amendment 39–16301 (75 FR 

28463, May 21, 2010) 

New Airworthiness Limitations Revisions 

(g) Within 90 days after June 25, 2010 (the 

effective date of AD 2010–10–22, 

Amendment 39–16301 (75 FR 28463, May 21, 

2010)), revise the maintenance program, by 

incorporating Chapter 5 of the BAE 

SYSTEMS (Operations) Limited BAe146 

Series/Avro 146–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/Avro 146–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—APPLICABLE AMM SUB-CHAPTERS

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. 


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TABLE 1—APPLICABLE AMM SUB-CHAPTERS—Continued 

AMM Sub-chapter Subject 

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. 

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. 

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

2Applicable only to airplanes post-modification HCM20010A. 

3Paragraphs 5 and 6 only, on the Corrosion Prevention and Control Program (CPCP) and the Supplemental Structural Inspection Document 

(SSID). 

Note 3: Sub-chapter 05–15–00 of the BAE 

SYSTEMS (Operations) Limited BAe146 

Series/Avro 146–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 main 

landing 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 Subject 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 Subject 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 Subject 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)(1) of 

this AD. 

FAA AD Differences 

Note 7: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

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 emailed 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 2011–0048, dated March 18, 2011; 

Subject 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 

Messier-Dowty Service Bulletin 146–32–171, 

dated August 11, 2009; for related 

information. 

Material Incorporated by Reference 

(n) You must use Subject 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 Aircraft Maintenance Manual 

(AMM), Revision 104, dated April 15, 2011, 

to do the applicable actions required by this 

AD, unless the AD specifies otherwise. If you 

do the optional modification specified in this 

AD, you must use Messier-Dowty Service 

Bulletin 146–32–171, dated August 11, 2009, 

to do those actions, unless the AD specifies 


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Federal Register / Vol. 76, No. 229 / Tuesday, November 29, 2011 / Rules and Regulations 73481 

otherwise. Only the transmittal letter and 

Chapter 05 List of Effective Pages contain the 

date of Revision 104 of the BAE Systems 

(Operations) Limited BAe 146 Series/Avro 

146–RJ Series AMM. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

Subject 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, under 5 

U.S.C. 552(a) and 1 CFR part 51. 

(2) The Director of the Federal Register 

previously approved the incorporation by 

reference of Messier-Dowty Service Bulletin 

146–32–171, dated August 11, 2009, on June 

25, 2010 (75 FR 28463, May 21, 2010). 

(3) For BAE Systems (Operations) Limited 

service information identified in this 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; email 

RApublications@baesystems.com; Internet 

http://www.baesystems.com/Businesses/ 

RegionalAircraft/index.htm. 

(4) For Messier-Dowty service information 

identified in this AD, contact Messier-Dowty: 

Messier Services Americas, Customer 

Support Center, 45360 Severn Way, Sterling, 

Virginia 20166–8910; telephone (703) 450– 

8233; fax (703) 404–1621; Internet https:// 

techpubs.services/messier-dowty.com. 

(5) 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. 

(6) 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 

November 8, 2011. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–29804 Filed 11–28–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0720; Directorate 

Identifier 2010–NM–252–AD; Amendment 

39–16867; AD 2011–24–03] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Bombardier, Inc. Model DHC–8–400 

series airplanes. 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: 

There has been one reported incident 

where the main landing gear (MLG) failed to 

extend during testing of the MLG alternate 

release system. Investigation revealed that 

the door release lever bushing was worn, 

causing an increase in the lateral movement 

of the release cable system. An increase in 

free-play within the release cable system 

would cause additional wear to the door 

release lever bushing and may lead to the 

turnbuckle fouling against the nacelle frame. 

The bushing wear at the door release lever 

and turnbuckle fouling could cause a failure 

in the alternate release system, preventing 

the landing gear from extending in the case 

of a failure of the normal MLG extension/ 

retraction system. 

* * * * * 

The unsafe condition is loss of control 

during landing. We are issuing this AD 

to require actions to correct the unsafe 

condition on these products. 

DATES: This AD becomes effective 

January 3, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of January 3, 2012. 

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: 

Fabio Buttitta, Aerospace Engineer, 

Airframe and Mechanical Systems 

Branch, ANE–171, FAA, New York 

Aircraft Certification Office, 1600 

Stewart Avenue, Suite 410, Westbury, 

New York 11590; telephone (516) 228– 

7303; fax (516) 794–5531. 

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 August 1, 2011 (76 FR 

45713). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

There has been one reported incident 

where the main landing gear (MLG) failed to 

extend during testing of the MLG alternate 

release system. Investigation revealed that 

the door release lever bushing was worn, 

causing an increase in the lateral movement 

of the release cable system. An increase in 

free-play within the release cable system 

would cause additional wear to the door 

release lever bushing and may lead to the 

turnbuckle fouling against the nacelle frame. 

The bushing wear at the door release lever 

and turnbuckle fouling could cause a failure 

in the alternate release system, preventing 

the landing gear from extending in the case 

of a failure of the normal MLG extension/ 

retraction system. 

This [Transport Canada Civil Aviation] 

directive is to mandate the incorporation of 

a new maintenance task to prevent excessive 

free-play of the turnbuckle and cable within 

the alternate release system. 

The unsafe condition is loss of control 

during landing. 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 

considered the comment received. 

Request To Refer to Revision 

Incorporating Temporary Revision 

Horizon Air Industries, Inc. (the 

commenter) requested that we revise 

paragraph (g) of the NPRM (76 FR 

45713, August 1, 2011) to reference 

Revision 7, dated June 5, 2010, of the 

Bombardier Q400 Dash 8 Maintenance 

Requirements Manual (MRM), PSM 1– 

84–7, instead of Bombardier Temporary 

Revision (TR) MRB–46, dated February 

4, 2010, to Section 1–32, Systems/ 

Powerplant Maintenance Program, of 

the Maintenance Review Board (MRB) 

Report Part 1, of the Bombardier Q400 

Dash 8 MRM, PSM 1–84–7. The 

commenter explained that this TR was 

removed from this MRM by Revision 7 

of this MRM; therefore, this TR does not 

exist. The commenter reasoned that 

referencing Bombardier TR MRB–46 in 

the final rule will force operators to 

request an alternative method of 


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