Airworthiness Directives; BAE SYSTEMS (Operations) Limited Airplanes, 73477-73481 [2011-29804]
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Federal Register / Vol. 76, No. 229 / Tuesday, November 29, 2011 / Rules and Regulations
admission to the United States as a
derivative of an asylee.
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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).’’.
■
[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 fiancé(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:
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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);’’
■
PART 213a—AFFIDAVITS OF
SUPPORT ON BEHALF OF ALIENS
§ 213a.2
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).’’
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§ 244.14
[Corrected]
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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]
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);’’.
BILLING CODE 9111–97–P
PART 245—ADJUSTMENT OF STATUS
TO THAT OF PERSON ADMITTED FOR
PERMANENT RESIDENCE
[Docket No. FAA–2011–0908; Directorate
Identifier 2010–NM–251–AD; Amendment
39–16870; AD 2011–24–06]
§ 245.21
RIN 2120–AA64
■
[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:’’.
■
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
Airworthiness Directives; BAE
SYSTEMS (Operations) Limited
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
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
SUMMARY:
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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:
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* * * 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.
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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.
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 https://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.
DATES:
FOR FURTHER INFORMATION CONTACT:
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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
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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
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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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Federal Register / Vol. 76, No. 229 / Tuesday, November 29, 2011 / Rules and Regulations
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.
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.
Regulatory Findings
§ 39.13
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
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You may examine the AD docket on
the Internet at https://
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.
[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:
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05–10–01 ............................
05–10–05 1 ..........................
05–10–10 2 ..........................
05–10–15 ............................
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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.
Airframe Airworthiness Limitations before Life Extension Programme.
Airframe Airworthiness Limitations, Life Extension Programme Landings Life Extended.
Airframe Airworthiness Limitations, Life Extension Programme Calendar Life Extended.
Aircraft Equipment Airworthiness Limitations.
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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.
Subject
14:37 Nov 28, 2011
*
* * * 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.
TABLE 1—APPLICABLE AMM SUB-CHAPTERS
AMM Sub-chapter
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TABLE 1—APPLICABLE AMM SUB-CHAPTERS—Continued
AMM Sub-chapter
05–10–17 ............................
05–15–00 ............................
05–20–00 3 ..........................
05–20–01 ............................
05–20–05 1 ..........................
05–20–10 2 ..........................
05–20–15 ............................
1 Applicable
2 Applicable
Subject
Power Plant Airworthiness Limitations.
Critical Design Configuration Control Limitations (CDCCL)—Fuel System Description and Operation.
Scheduled Maintenance.
Airframe Scheduled Maintenance—Before Life Extension Programme.
Airframe Scheduled Maintenance—Life Extension Programme Landings Life Extended.
Airframe Scheduled Maintenance—Life Extension Programme Calendar Life Extended.
Aircraft Equipment Scheduled Maintenance.
only to airplanes post-modification HCM20011A or HCM20012A or HCM20013A.
only to airplanes post-modification HCM20010A.
5 and 6 only, on the Corrosion Prevention and Control Program (CPCP) and the Supplemental Structural Inspection Document
3 Paragraphs
(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.
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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.
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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
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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
E:\FR\FM\29NOR1.SGM
29NOR1
Federal Register / Vol. 76, No. 229 / Tuesday, November 29, 2011 / Rules and Regulations
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
https://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: https://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]
pmangrum on DSK3VPTVN1PROD with RULES
BILLING CODE 4910–13–P
VerDate Mar<15>2010
14:37 Nov 28, 2011
Jkt 226001
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
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
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:
SUMMARY:
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 https://
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
PO 00000
Frm 00007
Fmt 4700
Sfmt 4700
73481
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
E:\FR\FM\29NOR1.SGM
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]]>Agencies
[Federal Register Volume 76, Number 229 (Tuesday, November 29, 2011)]
[Rules and Regulations]
[Pages 73477-73481]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-29804]
=======================================================================
-----------------------------------------------------------------------
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
[[Page 73478]]
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 https://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
sub-chapters 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) 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.
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 work-hour. 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
[[Page 73479]]
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 https://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
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 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.
[[Page 73480]]
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.
------------------------------------------------------------------------
\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 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 Messier-Dowty 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
[[Page 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 https://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: https://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
