Airworthiness Directives; Airbus Airplanes, 7007-7010 [2012-3105]
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Federal Register / Vol. 77, No. 28 / Friday, February 10, 2012 / Proposed Rules
(C) Attach each revised page 11–1–7
(ASB121, page 11) through 11–1–10
(ASB121, page 14) to the unrevised samenumbered page in the Performance section of
the RFM.
(ii) Within 50 hours time-in-service (TIS),
unless accomplished previously:
(A) Revise the RFM as required by
paragraph (1)(i)(B) and (1)(i)(C) of this AD;
and
(B) Affix the placard as required by
paragraph (1)(i)(A) of this AD or comply with
paragraph (1)(iii) of this AD.
(iii) At intervals not to exceed 600 hours
TIS:
(A) Before operating between a 16,000 ft
PA and 18,000 ft PA, perform the ‘‘MAX N1
CHECK’’ by following the Accomplishment
Instructions, paragraph 2.B.1.1., of ASB121.
If the OEI rating is not reached, either affix
a placard as required by paragraph (1)(i)(A)
or comply with paragraph (1)(iii)(B) or
(1)(iii)(C) of this AD.
(B) Before operating between 13,000 ft PA
and 16,000 ft PA, perform the ‘‘MAX N1
CHECK’’ by following the Accomplishment
Instructions, paragraph 2.B.1.4., of ASB121.
(1) If the OEI rating is reached, affix a
placard to the instrument panel in plain view
of the pilot(s), which states: ‘‘Maximum
operating altitude is 16,000 ft PA.’’
(2) If the OEI rating is not reached, either
affix a placard as required by paragraph
(1)(i)(A) of this AD or comply with paragraph
(1)(iii)(C) of this AD.
(C) Before operating between 10,000 ft PA
and 13,000 ft PA, perform the ‘‘MAX N1
CHECK’’ by following the Accomplishment
Instructions, paragraph 2.B.1.7., of ASB121.
(1) If the OEI rating is reached, affix a
placard to the instrument panel in plain view
of the pilot(s), which states: ‘‘Maximum
operating altitude is 13,000 ft PA.’’
(2) If the OEI rating is not reached, affix a
placard as required by paragraph (1)(i)(A) of
this AD.
(2) For Model MBB–BK 117 C–2
helicopters:
(i) Before any flight operation at or above
a PA of 10,000 feet, unless accomplished
previously:
(A) Affix a placard to the instrument panel
in plain view of the pilot(s), which states:
‘‘Maximum altitude for takeoff, landing, and
hovering is 10,000 ft PA. Maximum operating
altitude above effective translational lift is
13,000 ft PA,’’ or comply with paragraph
(2)(iii) of this AD. The term ‘‘hovering’’ as
used in this placard includes both IGE and
OGE hovering.
(B) Revise the Altitude Limitations section
of the RFM in accordance with paragraph
A.2.3. on page 10 and paragraph 2.8. on page
11 of Eurocopter ASB No. MBB BK117 C–2–
71A–003, Revision 3, dated December 11,
2007 (ASB003).
(ii) Within 50 hours TIS, unless
accomplished previously:
(A) Revise the RFM as required by
paragraph (2)(i)(B) of this AD; and
(B) Affix a placard as required by
paragraph (2)(i)(A) of this AD or comply with
paragraph (2)(iii) of this AD.
(iii) At intervals not to exceed 600 hours
TIS:
(A) Before operating between 16,000 ft PA
and 18,000 ft PA, perform the ‘‘MAX N1
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CHECK’’ by following the Accomplishment
Instructions, paragraph 3.A.(1) (on pages 4
and 5), of ASB003. If the OEI rating is not
reached, either affix a placard as required by
paragraph (2)(i)(A) or comply with paragraph
(2)(iii)(B) or (2)(iii)(C) of this AD.
(B) Before operating between 13,000 ft PA
and 16,000 ft PA, perform the ‘‘MAX N1
CHECK’’ by following the Accomplishment
Instructions, paragraph 3.A.(1) (on pages 5
and 6) of ASB003.
(1) If the OEI rating is reached, affix a
placard to the instrument panel in plain view
of the pilot(s), which states: ‘‘Maximum
operating altitude is 16,000 ft PA.’’
(2) If the OEI rating is not reached, either
affix a placard as required by paragraph
(2)(i)(A) or comply with paragraph (2)(iii)(C)
of this AD.
(C) Before operating between 10,000 ft PA
and 13,000 ft PA, perform the ‘‘MAX N1
CHECK’’ by following the Accomplishment
Instructions, paragraph 3.A.1. (on page 7) of
ASB003.
(1) If the OEI rating is reached, affix a
placard to the instrument panel in plain view
of the pilot(s), which states: ‘‘Maximum
operating altitude is 13,000 ft PA.’’
(2) If the OEI rating is not reached, affix a
placard as required by paragraph (2)(i)(A) of
this AD.
(3) If an engine, FCU, engine module 2 or
engine module 3 is replaced, before any flight
operation at or above a PA of 10,000 feet,
comply with the requirements of paragraph
(1) of this AD for the Model MBB–BK 117
C–1 helicopter or paragraph (2) of this AD for
the Model MBB–BK 117 C–2 helicopter.
(4) Modifying both engines with
Turbomeca Modification TU 358 is
terminating action for the requirements of
this AD. After modifying both engines,
remove from the RFM the revised altitude
limitations and the revised performance
pages required by this AD.
(e) Alternative Methods of Compliance
(AMOC)
(1) The Manager, Safety Management
Group, FAA, may approve AMOCs for this
AD. Send your proposal to: Ed Cuevas,
Aviation Safety Engineer, Safety Management
Group, Rotorcraft Directorate, FAA, 2601
Meacham Blvd., Fort Worth, Texas 76137;
telephone (817) 222–5110; email
ed.cuevas@faa.gov.
(2) For operations conducted under a Part
119 operating certificate or under Part 91,
Subpart K, we suggest that you notify your
principal inspector, or lacking a principal
inspector, the manager of the local flight
standards district office or certificate holding
district office before operating any aircraft
complying with this AD through an AMOC.
(f) Additional Information
The subject of this AD is addressed in
European Aviation Safety Agency (Germany)
AD No.: 2008–0061, dated March 27, 2008.
(g) Subject
Joint Aircraft Service Component (JASC)
Code: 1100, Placards and Markings.
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Issued in Fort Worth, Texas, on January 27,
2012.
Lance T. Gant,
Acting Manager, Rotorcraft Directorate,
Aircraft Certification Service.
[FR Doc. 2012–3187 Filed 2–9–12; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2012–0111; Directorate
Identifier 2011–NM–089–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for certain
Airbus Model A330–200 series
airplanes; Model A330–300 series
airplanes, Model A340–200 series
airplanes; Model A340–300 series
airplanes; Model A340–541 airplanes;
and Model A340–642 airplanes. This
proposed AD was prompted by reports
of cracks in the bogie pivot pin caused
by material heating due to friction
between the bogie pivot pin and bush.
This proposed AD would require
performing a detailed inspection for
degradation of the bogie pivot pins and
pivot pin bushes of the main and central
landing gear for any cracks and damage,
and repairing or replacing bogie pivot
pins and pivot pin bushes, if necessary.
We are proposing this AD to correct and
detect cracks and damage to the main
and central landing gear, which could
result in the collapse of the landing gear
and adversely affect the airplane’s
continued safe flight and landing.
DATES: We must receive comments on
this proposed AD by March 26, 2012.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: (202) 493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations,
M–30, West Building Ground Floor,
Room W12–140, 1200 New Jersey
Avenue SE., Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations,
M–30, West Building Ground Floor,
Room W12–140, 1200 New Jersey
SUMMARY:
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Avenue SE., Washington, DC, between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays.
For service information identified in
this proposed AD, contact Airbus SAS—
Airworthiness Office—EAL, 1 Rond
Point Maurice Bellonte, 31707 Blagnac
Cedex, France; telephone +33 5 61 93 36
96; fax +33 5 61 93 45 80; email
airworthiness.A330-A340@airbus.com;
Internet https://www.airbus.com. You
may review copies of the referenced
service information at the FAA,
Transport Airplane Directorate, 1601
Lind Avenue SW., Renton, Washington.
For information on the availability of
this material at the FAA, call (425) 227–
1221.
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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 this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Operations
office (telephone (800) 647–5527) is in
the ADDRESSES section. Comments will
be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT:
Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton,
Washington 98057–3356; telephone
(425) 227–1138; fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2012–0111; Directorate Identifier
2011–NM–089–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD based on those comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
The European Aviation Safety Agency
(EASA), which is the Technical Agent
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for the Member States of the European
Community, has issued EASA
Airworthiness Directive 2011–0040,
dated March 8, 2011 (referred to after
this as ‘‘the MCAI’’), to correct an unsafe
condition for the specified products.
The MCAI states:
During removals of A330/340 Main
Landing Gear Bogie Beams and A340–500/
600 Centre Landing Gear Bogie Beams, cracks
in the Bogie Pivot Pin (BPP) have been found.
Investigations indicated that the main root
cause is material heating due to friction
between bogie pivot pin and bush.
Consequences of that heating are chrome
detachment and stress corrosion cracking
(SCC).
This situation, if not corrected, could result
in the collapse of the main or central landing
gear.
As a precautionary measure, this [EASA]
AD requires a one-time [detailed] inspection
of the main landing gear (all types of A330
and A340) and central landing gear (A340–
500/600 only) to detect degradation * * * of
the BPP [and cracks and damages of the
bushes], as applicable to aeroplane model,
and the reporting of inspections results.
Required actions also include, for
certain airplanes, a magnetic particle
inspection of the bogie pivot pin for
corrosion and base metal cracks. The
corrective actions include replacing any
cracked or damaged pivot pin bush with
a new or serviceable pivot pin bush, and
replacing any corroded or cracked bogie
pin with a new bogie pin. You may
obtain further information by examining
the MCAI in the AD docket.
Relevant Service Information
Airbus has issued the following
service bulletins:
• Airbus Mandatory Service Bulletin
A330–32–3240, including Appendix 1,
dated December 8, 2010 (for Model
A330–200 series airplanes and Model
A330–300 series airplanes);
• Airbus Mandatory Service Bulletin
A340–32–4281, including Appendix 1,
dated December 8, 2010 (for Model
A340–200 series airplanes and Model
A340–300 series airplanes); and
• Airbus Mandatory Service Bulletin
A340–32–5096, including Appendix 1,
dated December 8, 2010 (for Model
A340–541 airplanes and A340–642
airplanes).
The actions described in this service
information are intended to correct the
unsafe condition identified in the
MCAI.
FAA’s Determination and Requirements
of This Proposed AD
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
bilateral agreement with the State of
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Design Authority, we have been notified
of the unsafe condition described in the
MCAI and service information
referenced above. We are proposing this
AD because we evaluated all pertinent
information and determined an unsafe
condition exists and is likely to exist or
develop on other products of the same
type design.
Costs of Compliance
Based on the service information, we
estimate that this proposed AD would
affect about 29 products of U.S. registry.
We also estimate that it would take
about 22 work-hours per product to
comply with the basic requirements of
this proposed AD. The average labor
rate is $85 per work-hour. Based on
these figures, we estimate the cost of the
proposed AD on U.S. operators to be
$54,230, or $1,870 per product.
In addition, we estimate that any
necessary follow-on actions would take
about 6 work-hours and require parts
costing $21,222, for a cost of $21,732
per product. We have no way of
determining the number of products
that may need these actions.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. ‘‘Subtitle VII:
Aviation Programs,’’ describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in ‘‘Subtitle VII,
Part A, Subpart III, Section 44701:
General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
We determined that this proposed AD
would not have federalism implications
under Executive Order 13132. This
proposed AD would not have a
substantial direct effect on the States, on
the relationship between the national
Government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify this proposed regulation:
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1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in
Alaska; and
4. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared a regulatory evaluation
of the estimated costs to comply with
this proposed AD and placed it in the
AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
Airbus: Docket No. FAA–2012–0111;
Directorate Identifier 2011–NM–089–AD.
(a) Comments Due Date
We must receive comments by March 26,
2012.
(b) Affected ADs
None.
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(c) Applicability
This AD applies to Airbus Model A330–
201, –202, –203, –223, –243, –301, –302,
–303, –321, –322, –323, –341, –342, and –343
airplanes; Model A340–211, –212, and –213
airplanes; Model A340–311, –312, and –313
airplanes; Model A340–541 airplanes; and
Model A340–642 airplanes; certificated in
any category; all manufacturer serial
numbers, except those on which Airbus
modification 54500 has been embodied in
production.
(d) Subject
Air Transport Association (ATA) of
America Code 32: Landing Gear.
(e) Reason
This AD was prompted by reports of cracks
in the bogie pivot pin caused by material
heating due to friction between the bogie
pivot pin and bush. We are issuing this AD
to correct and detect cracks and damage to
the main and central landing gear, which
could result in the collapse of the landing
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gear and adversely affect the airplane’s
continued safe flight and landing.
(f) Compliance
You are responsible for having the actions
required by this AD performed within the
compliance times specified, unless the
actions have already been done.
(g) Inspection
Within 26 months after the effective date
of this AD or within 26 months after the first
flight of the airplane, whichever occurs later;
but no earlier than 12 months after the first
flight of the airplane: Do a detailed
inspection for degradation of the bogie pivot
pins and pivot pin bushes of the main and
central landing gear, for any cracks and
damage (i.e., loss of chromium plate, loose
chromium, sharp edges), in accordance with
the Accomplishment Instructions of the
applicable service bulletin specified in
paragraph (g)(1), (g)(2), or (g)(3) of this AD.
(1) Airbus Mandatory Service Bulletin
A330–32–3240, including Appendix 1, dated
December 8, 2010 (for Model A330–200
series airplanes and Model A330–300 series
airplanes).
(2) Airbus Mandatory Service Bulletin
A340–32–4281, including Appendix 1, dated
December 8, 2010 (for Airbus Model A340–
200 series airplanes and Model A340–300
series airplanes).
(3) Airbus Mandatory Service Bulletin
A340–32–5096, including Appendix 1, dated
December 8, 2010 (for Model A340–541
airplanes and A340–642 airplanes).
(h) Corrective Action
If, during the inspection specified in
paragraph (g) of this AD, any pivot pin bush
is found cracked or damaged: Before further
flight, record all findings (both positive and
negative), as required by paragraph (k) of this
AD, and repair or replace the pivot pin bush
with a new or serviceable pivot pin bush, in
accordance with the Accomplishment
Instructions of the applicable service bulletin
specified paragraph (h)(1), (h)(2), or (h)(3) of
this AD.
(1) Airbus Mandatory Service Bulletin
A330–32–3240, including Appendix 1, dated
December 8, 2010 (for Model A330–200
series airplanes and Model A330–300 series
airplanes).
(2) Airbus Mandatory Service Bulletin
A340–32–4281, including Appendix 1, dated
December 8, 2010 (for Airbus Model A340–
200 series airplanes and Model A340–300
series airplanes).
(3) Airbus Mandatory Service Bulletin
A340–32–5096, including Appendix 1, dated
December 8, 2010 (for Model A340–541
airplanes and A340–642 airplanes).
(i) Record Findings and Inspection
If, during the inspection specified in
paragraph (g) of this AD, degraded chrome
plating on any bogie pivot pin is found:
Before further flight, record findings (both
positive and negative), as required by
paragraph (k) of this AD, and do a nondestructive test (magnetic particle inspection)
of the affected bogie pivot pin for corrosion
and base metal cracks, in accordance with
the Accomplishment Instructions of the
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applicable service bulletin specified
paragraph (i)(1), (i)(2), or (i)(3) of this AD.
(1) Airbus Mandatory Service Bulletin
A330–32–3240, including Appendix 1, dated
December 8, 2010 (for Model A330–200
series airplanes and Model A330–300 series
airplanes).
(2) Airbus Mandatory Service Bulletin
A340–32–4281, including Appendix 1, dated
December 8, 2010 (for Airbus Model A340–
200 series airplanes and Model A340–300
series airplanes).
(3) Airbus Mandatory Service Bulletin
A340–32–5096, including Appendix 1, dated
December 8, 2010 (for Model A340–541
airplanes and A340–642 airplanes).
(j) Repair or Replacement
If, during the non-destructive test
(magnetic particle inspection) specified in
paragraph (i) of this AD, the bogie pivot pin
is found corroded or the base metal is
cracked: Before further flight, repair or
replace the bogie pin with a new or
serviceable bogie pin, in accordance with the
Accomplishment Instructions of the
applicable service bulletin specified
paragraph (j)(1), (j)(2), or (j)(3) of this AD.
(1) Airbus Mandatory Service Bulletin
A330–32–3240, including Appendix 1, dated
December 8, 2010 (for Model A330–200
series airplanes and Model A330–300 series
airplanes.
(2) Airbus Mandatory Service Bulletin
A340–32–4281, including Appendix 1, dated
December 8, 2010 (for Airbus Model A340–
200 series airplanes and Model A340–300
series airplanes).
(3) Airbus Mandatory Service Bulletin
A340–32–5096, including Appendix 1, dated
December 8, 2010 (for Model A340–541
airplanes and A340–642 airplanes).
(k) Reporting Requirement
Submit a report of the findings (both
positive and negative) of the inspections
required by paragraphs (g) and (i) of this AD
to Airbus, Customer Services Directorate, 1
Rond Point Maurice Bellonte, 31707 Blagnac
Cedex France, ATTN: SDC32 Technical Data
and Documentation Services; fax (+33) 5 61
93 28 06; email sb.reporting@airbus.com; at
the applicable time specified in paragraph
(k)(1) or (k)(2) of this AD. The report must
include the inspection results and
description of any discrepancies found.
(1) If the inspection was done on or after
the effective date of this AD: Submit the
report within 90 days after the inspection.
(2) If the inspection was done before the
effective date of this AD: Submit the report
within 90 days after the effective date of this
AD.
(l) Other FAA AD Provisions
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
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Federal Register / Vol. 77, No. 28 / Friday, February 10, 2012 / Proposed Rules
to the International Branch, send it to ATTN:
Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, Washington 98057–
3356; telephone (425) 227–1138; fax (425)
227–1149. Information may be emailed to: 9ANM-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.
(3) Reporting Requirements: A federal
agency may not conduct or sponsor, and a
person is not required to respond to, nor
shall a person be subject to a penalty for
failure to comply with a collection of
information subject to the requirements of
the Paperwork Reduction Act unless that
collection of information displays a current
valid OMB Control Number. The OMB
Control Number for this information
collection is 2120–0056. Public reporting for
this collection of information is estimated to
be approximately 5 minutes per response,
including the time for reviewing instructions,
completing and reviewing the collection of
information. All responses to this collection
of information are mandatory. Comments
concerning the accuracy of this burden and
suggestions for reducing the burden should
be directed to the FAA at: 800 Independence
Ave. SW., Washington, DC 20591, Attn:
Information Collection Clearance Officer,
AES–200.
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(m) Related Information
Refer to MCAI European Aviation Safety
Agency Airworthiness Directive 2011–0040,
dated March 8, 2011, and the service
information specified in paragraphs (m)(1)
through (m)(3) of this AD, for related
information.
(1) Airbus Mandatory Service Bulletin
A330–32–3240, including Appendix 1, dated
December 8, 2010.
(2) Airbus Mandatory Service Bulletin
A340–32–4281, including Appendix 1, dated
December 8, 2010.
(3) Airbus Mandatory Service Bulletin
A340–32–5096, including Appendix 1, dated
December 8, 2010.
Issued in Renton, Washington on February
3, 2012.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2012–3105 Filed 2–9–12; 8:45 am]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 135
[Docket No. FAA 2011–1397]
Clarification of Policy Regarding
Approved Training Programs;
Correction
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of availability;
Correction.
AGENCY:
The FAA is correcting a
notice published on December 27, 2011
(76 FR 80831). In that notice of
availability the FAA announced the
availability of an FAA Notice that
would require FAA inspectors to review
policy regarding approved training
programs as well as to identify and
correct those training programs which
erroneously issued credit for previous
training or checking. The Notice also
provided guidance on constructing
reduced hour training programs based
on previous experience. Upon review of
the comments and any necessary
revision, the Notice would cancel and
replace FAA Order 8900.1, Volume 3,
Chapter 19, Paragraph 3–1111. This
document corrects an incorrect
comment due date.
DATES: Written comments must be
received on or before February 27, 2012.
ADDRESSES: Send comments identified
by docket number FAA–2011–1397
using any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov and follow
the online instructions for sending your
comments electronically.
• Mail: Send comments to Docket
Operations, M–30; U.S. Department of
Transportation (DOT), 1200 New Jersey
Avenue SE., Room W12–140, West
Building Ground Floor, Washington, DC
20590–0001.
• Hand Delivery or Courier: Take
comments to Docket Operations in
Room W12–140 of the West Building
Ground Floor at 1200 New Jersey
Avenue SE., Washington, DC, between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays.
• Fax: Fax comments to Docket
Operations at 202–493–2251.
Privacy: The FAA will post all
comments it receives, without change,
to https://www.regulations.gov, including
any personal information the
commenter provides. Using the search
function of the docket web site, anyone
can find and read the electronic form of
SUMMARY:
PO 00000
Frm 00006
Fmt 4702
Sfmt 4702
all comments received into any FAA
dockets, including the name of the
individual sending the comment (or
signing the comment for an association,
business, labor union, etc.). DOT’s
complete Privacy Act Statement can be
found in the Federal Register published
on April 11, 2000 (65 FR 19477–19478),
as well as at https://DocketsInfo.dot.gov.
Docket: Background documents or
comments received may be read at
https://www.regulations.gov at any time.
Follow the online instructions for
accessing the docket or Docket
Operations in Room W12–140 of the
West Building Ground Floor at 1200
New Jersey Avenue SE., Washington,
DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
FOR FURTHER INFORMATION CONTACT:
Robert Burke, Air Carrier Training
Branch, Air Transportation Division,
Flight Standards Service, Federal
Aviation Administration, 800
Independence Avenue SW.,
Washington, DC 20591; telephone: 202–
267–8262; facsimile: 202–267–5229;
email: robert.burke@faa.gov.
Background
On December 27, 2011, the FAA
published a notice of availability
entitled, ‘‘Clarification of Policy
Regarding Approved Training
Programs’’ (76 FR 80831).
The FAA Order 8900.1, Flight
Standards Information Management
System, was issued on September 13,
2007. This order consolidated and
replaced FAA Orders 8300.1, 8400.1,
and 8700.1, the FAA’s guidance to
inspectors. There have been numerous
inquiries by part 135 certificate holders
regarding the acceptance of training/
evaluations previously completed by a
crewmember while in the employment
of another certificate holder.
Regulations do not permit the crediting
of such training (with the specific
exception of CRM and DRM training).
Additionally, some training centers
have distributed a training program
template that provides credit for
training/evaluations conducted by
another operator. Such provisions are
contrary to the intent as well as the
technical provisions of part 135 and are
not appropriate for inclusion in a
certificate holder’s approved training
program.
Part 135 certificate holders may
develop and submit for approval
multiple curriculums for a particular
crewmember position and aircraft make/
model/variant. For example, a part 135
certificate holder may have a an initial
new-hire curriculum designed to meet
the requirements of new hire
crewmembers that have minimal flight
E:\FR\FM\10FEP1.SGM
10FEP1
]]>Agencies
[Federal Register Volume 77, Number 28 (Friday, February 10, 2012)]
[Proposed Rules]
[Pages 7007-7010]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-3105]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2012-0111; Directorate Identifier 2011-NM-089-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to adopt a new airworthiness directive (AD) for
certain Airbus Model A330-200 series airplanes; Model A330-300 series
airplanes, Model A340-200 series airplanes; Model A340-300 series
airplanes; Model A340-541 airplanes; and Model A340-642 airplanes. This
proposed AD was prompted by reports of cracks in the bogie pivot pin
caused by material heating due to friction between the bogie pivot pin
and bush. This proposed AD would require performing a detailed
inspection for degradation of the bogie pivot pins and pivot pin bushes
of the main and central landing gear for any cracks and damage, and
repairing or replacing bogie pivot pins and pivot pin bushes, if
necessary. We are proposing this AD to correct and detect cracks and
damage to the main and central landing gear, which could result in the
collapse of the landing gear and adversely affect the airplane's
continued safe flight and landing.
DATES: We must receive comments on this proposed AD by March 26, 2012.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: (202) 493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey
[[Page 7008]]
Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through
Friday, except Federal holidays.
For service information identified in this proposed AD, contact
Airbus SAS--Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61
93 45 80; email airworthiness.A330-A340@airbus.com; Internet https://www.airbus.com. You may review copies of the referenced service
information at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue SW., Renton, Washington. For information on the availability of
this material at the FAA, call (425) 227-1221.
Examining the AD Docket
You may examine the AD docket on the Internet at 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 this proposed AD, the regulatory
evaluation, any comments received, and other information. The street
address for the Docket Operations office (telephone (800) 647-5527) is
in the ADDRESSES section. Comments will be available in the AD docket
shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, Washington 98057-3356; telephone (425)
227-1138; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2012-0111;
Directorate Identifier 2011-NM-089-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD based on those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued EASA
Airworthiness Directive 2011-0040, dated March 8, 2011 (referred to
after this as ``the MCAI''), to correct an unsafe condition for the
specified products. The MCAI states:
During removals of A330/340 Main Landing Gear Bogie Beams and
A340-500/600 Centre Landing Gear Bogie Beams, cracks in the Bogie
Pivot Pin (BPP) have been found.
Investigations indicated that the main root cause is material
heating due to friction between bogie pivot pin and bush.
Consequences of that heating are chrome detachment and stress
corrosion cracking (SCC).
This situation, if not corrected, could result in the collapse
of the main or central landing gear.
As a precautionary measure, this [EASA] AD requires a one-time
[detailed] inspection of the main landing gear (all types of A330
and A340) and central landing gear (A340-500/600 only) to detect
degradation * * * of the BPP [and cracks and damages of the bushes],
as applicable to aeroplane model, and the reporting of inspections
results.
Required actions also include, for certain airplanes, a magnetic
particle inspection of the bogie pivot pin for corrosion and base metal
cracks. The corrective actions include replacing any cracked or damaged
pivot pin bush with a new or serviceable pivot pin bush, and replacing
any corroded or cracked bogie pin with a new bogie pin. You may obtain
further information by examining the MCAI in the AD docket.
Relevant Service Information
Airbus has issued the following service bulletins:
Airbus Mandatory Service Bulletin A330-32-3240, including
Appendix 1, dated December 8, 2010 (for Model A330-200 series airplanes
and Model A330-300 series airplanes);
Airbus Mandatory Service Bulletin A340-32-4281, including
Appendix 1, dated December 8, 2010 (for Model A340-200 series airplanes
and Model A340-300 series airplanes); and
Airbus Mandatory Service Bulletin A340-32-5096, including
Appendix 1, dated December 8, 2010 (for Model A340-541 airplanes and
A340-642 airplanes).
The actions described in this service information are intended to
correct the unsafe condition identified in the MCAI.
FAA's Determination and Requirements of This Proposed AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all pertinent information and determined an unsafe condition
exists and is likely to exist or develop on other products of the same
type design.
Costs of Compliance
Based on the service information, we estimate that this proposed AD
would affect about 29 products of U.S. registry. We also estimate that
it would take about 22 work-hours per product to comply with the basic
requirements of this proposed AD. The average labor rate is $85 per
work-hour. Based on these figures, we estimate the cost of the proposed
AD on U.S. operators to be $54,230, or $1,870 per product.
In addition, we estimate that any necessary follow-on actions would
take about 6 work-hours and require parts costing $21,222, for a cost
of $21,732 per product. We have no way of determining the number of
products that may need these actions.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify this proposed
regulation:
[[Page 7009]]
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in Alaska; and
4. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this proposed AD and placed it in the AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. The FAA amends Sec. 39.13 by adding the following new AD:
Airbus: Docket No. FAA-2012-0111; Directorate Identifier 2011-NM-
089-AD.
(a) Comments Due Date
We must receive comments by March 26, 2012.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Airbus Model A330-201, -202, -203, -223, -
243, -301, -302, -303, -321, -322, -323, -341, -342, and -343
airplanes; Model A340-211, -212, and -213 airplanes; Model A340-311,
-312, and -313 airplanes; Model A340-541 airplanes; and Model A340-
642 airplanes; certificated in any category; all manufacturer serial
numbers, except those on which Airbus modification 54500 has been
embodied in production.
(d) Subject
Air Transport Association (ATA) of America Code 32: Landing
Gear.
(e) Reason
This AD was prompted by reports of cracks in the bogie pivot pin
caused by material heating due to friction between the bogie pivot
pin and bush. We are issuing this AD to correct and detect cracks
and damage to the main and central landing gear, which could result
in the collapse of the landing gear and adversely affect the
airplane's continued safe flight and landing.
(f) Compliance
You are responsible for having the actions required by this AD
performed within the compliance times specified, unless the actions
have already been done.
(g) Inspection
Within 26 months after the effective date of this AD or within
26 months after the first flight of the airplane, whichever occurs
later; but no earlier than 12 months after the first flight of the
airplane: Do a detailed inspection for degradation of the bogie
pivot pins and pivot pin bushes of the main and central landing
gear, for any cracks and damage (i.e., loss of chromium plate, loose
chromium, sharp edges), in accordance with the Accomplishment
Instructions of the applicable service bulletin specified in
paragraph (g)(1), (g)(2), or (g)(3) of this AD.
(1) Airbus Mandatory Service Bulletin A330-32-3240, including
Appendix 1, dated December 8, 2010 (for Model A330-200 series
airplanes and Model A330-300 series airplanes).
(2) Airbus Mandatory Service Bulletin A340-32-4281, including
Appendix 1, dated December 8, 2010 (for Airbus Model A340-200 series
airplanes and Model A340-300 series airplanes).
(3) Airbus Mandatory Service Bulletin A340-32-5096, including
Appendix 1, dated December 8, 2010 (for Model A340-541 airplanes and
A340-642 airplanes).
(h) Corrective Action
If, during the inspection specified in paragraph (g) of this AD,
any pivot pin bush is found cracked or damaged: Before further
flight, record all findings (both positive and negative), as
required by paragraph (k) of this AD, and repair or replace the
pivot pin bush with a new or serviceable pivot pin bush, in
accordance with the Accomplishment Instructions of the applicable
service bulletin specified paragraph (h)(1), (h)(2), or (h)(3) of
this AD.
(1) Airbus Mandatory Service Bulletin A330-32-3240, including
Appendix 1, dated December 8, 2010 (for Model A330-200 series
airplanes and Model A330-300 series airplanes).
(2) Airbus Mandatory Service Bulletin A340-32-4281, including
Appendix 1, dated December 8, 2010 (for Airbus Model A340-200 series
airplanes and Model A340-300 series airplanes).
(3) Airbus Mandatory Service Bulletin A340-32-5096, including
Appendix 1, dated December 8, 2010 (for Model A340-541 airplanes and
A340-642 airplanes).
(i) Record Findings and Inspection
If, during the inspection specified in paragraph (g) of this AD,
degraded chrome plating on any bogie pivot pin is found: Before
further flight, record findings (both positive and negative), as
required by paragraph (k) of this AD, and do a non-destructive test
(magnetic particle inspection) of the affected bogie pivot pin for
corrosion and base metal cracks, in accordance with the
Accomplishment Instructions of the applicable service bulletin
specified paragraph (i)(1), (i)(2), or (i)(3) of this AD.
(1) Airbus Mandatory Service Bulletin A330-32-3240, including
Appendix 1, dated December 8, 2010 (for Model A330-200 series
airplanes and Model A330-300 series airplanes).
(2) Airbus Mandatory Service Bulletin A340-32-4281, including
Appendix 1, dated December 8, 2010 (for Airbus Model A340-200 series
airplanes and Model A340-300 series airplanes).
(3) Airbus Mandatory Service Bulletin A340-32-5096, including
Appendix 1, dated December 8, 2010 (for Model A340-541 airplanes and
A340-642 airplanes).
(j) Repair or Replacement
If, during the non-destructive test (magnetic particle
inspection) specified in paragraph (i) of this AD, the bogie pivot
pin is found corroded or the base metal is cracked: Before further
flight, repair or replace the bogie pin with a new or serviceable
bogie pin, in accordance with the Accomplishment Instructions of the
applicable service bulletin specified paragraph (j)(1), (j)(2), or
(j)(3) of this AD.
(1) Airbus Mandatory Service Bulletin A330-32-3240, including
Appendix 1, dated December 8, 2010 (for Model A330-200 series
airplanes and Model A330-300 series airplanes.
(2) Airbus Mandatory Service Bulletin A340-32-4281, including
Appendix 1, dated December 8, 2010 (for Airbus Model A340-200 series
airplanes and Model A340-300 series airplanes).
(3) Airbus Mandatory Service Bulletin A340-32-5096, including
Appendix 1, dated December 8, 2010 (for Model A340-541 airplanes and
A340-642 airplanes).
(k) Reporting Requirement
Submit a report of the findings (both positive and negative) of
the inspections required by paragraphs (g) and (i) of this AD to
Airbus, Customer Services Directorate, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex France, ATTN: SDC32 Technical Data and
Documentation Services; fax (+33) 5 61 93 28 06; email
sb.reporting@airbus.com; at the applicable time specified in
paragraph (k)(1) or (k)(2) of this AD. The report must include the
inspection results and description of any discrepancies found.
(1) If the inspection was done on or after the effective date of
this AD: Submit the report within 90 days after the inspection.
(2) If the inspection was done before the effective date of this
AD: Submit the report within 90 days after the effective date of
this AD.
(l) Other FAA AD Provisions
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
[[Page 7010]]
to the International Branch, send it to ATTN: Vladimir Ulyanov,
Aerospace Engineer, International Branch, ANM-116, Transport
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, Washington
98057-3356; telephone (425) 227-1138; 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.
(3) Reporting Requirements: A federal agency may not conduct or
sponsor, and a person is not required to respond to, nor shall a
person be subject to a penalty for failure to comply with a
collection of information subject to the requirements of the
Paperwork Reduction Act unless that collection of information
displays a current valid OMB Control Number. The OMB Control Number
for this information collection is 2120-0056. Public reporting for
this collection of information is estimated to be approximately 5
minutes per response, including the time for reviewing instructions,
completing and reviewing the collection of information. All
responses to this collection of information are mandatory. Comments
concerning the accuracy of this burden and suggestions for reducing
the burden should be directed to the FAA at: 800 Independence Ave.
SW., Washington, DC 20591, Attn: Information Collection Clearance
Officer, AES-200.
(m) Related Information
Refer to MCAI European Aviation Safety Agency Airworthiness
Directive 2011-0040, dated March 8, 2011, and the service
information specified in paragraphs (m)(1) through (m)(3) of this
AD, for related information.
(1) Airbus Mandatory Service Bulletin A330-32-3240, including
Appendix 1, dated December 8, 2010.
(2) Airbus Mandatory Service Bulletin A340-32-4281, including
Appendix 1, dated December 8, 2010.
(3) Airbus Mandatory Service Bulletin A340-32-5096, including
Appendix 1, dated December 8, 2010.
Issued in Renton, Washington on February 3, 2012.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2012-3105 Filed 2-9-12; 8:45 am]
BILLING CODE 4910-13-P
