Airworthiness Directives; Airbus Airplanes, 8134-8138 [2016-03215]
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Federal Register / Vol. 81, No. 32 / Thursday, February 18, 2016 / Rules and Regulations
Currency in issuing interagency
guidance stating that, depending on the
facts and circumstances, a depository
institution might violate the prohibition
against unfair or deceptive practices in
the FTC Act and the Dodd-Frank Act if
it engages in the practices prohibited by
the former credit practices rules.14
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II. Discussion
Fourteen commenters responded to
the proposed repeal of Regulation AA.
Three individual commenters stated
that Regulation AA was a necessary and
helpful regulation; two of these
commenters stated that the Board’s
reasons for repealing the regulation
were unclear. A comment letter received
from seven consumer advocate
organizations acknowledged that the
Board’s repeal of Regulation AA was
required by the Dodd-Frank Act. In their
letter, these commenters also provided
recommendations to the Bureau
regarding acts or practices that the
Bureau now has to authority to regulate
if it finds they are unfair or deceptive.15
Eight commenters addressed the
interagency guidance that was issued
simultaneously with the proposed
repeal of Regulation AA. One individual
commenter believed the guidance
would discourage banks from engaging
in unfair or deceptive acts or practices,
but seven consumer advocate
commenters recommended
strengthening the guidance language.
The consumer advocate commenters
also recommended that the Board issue
additional guidance regarding other acts
or practices that the commenters believe
should be declared unfair or deceptive
acts or practices.
The Board is finalizing the repeal of
Regulation AA as proposed. As the
Board discussed in the Proposed Rule,
the Dodd-Frank Act eliminated the
Board’s rule writing authority under the
FTC Act, which nullified the regulation.
The Board will continue to monitor
developments with respect to unfair or
deceptive acts or practices and assess
whether to issue additional supervisory
guidance.
The repeal of Regulation AA also
eliminates Subpart A of the regulation,
which generally describes the internal
procedures used by the Board in
handling consumer complaints. The
Board did not receive comment on the
14 ‘‘Interagency Guidance Regarding Unfair or
Deceptive Credit Practices’’ (Aug. 22, 2014).
https://www.federalreserve.gov/newsevents/press/
bcreg/bcreg20140822a2.pdf.
15 One state chartered bank commenter did not
address the proposed repeal, but objected to
examiners’ citations of banks for unfair or deceptive
practices in the supervisory process. Two
individual commenters did not address the
proposed repeal of Regulation AA.
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removal of these internal procedures
from the Code of Federal Regulations.
Information about how the Board
processes consumer complaints is
provided on the Board’s public Web
site.16
III. Final Regulatory Flexibility
Analysis
The Regulatory Flexibility Act 17
(RFA) generally requires an agency to
perform an assessment of the impact a
rule is expected to have on small
entities. Based on its analysis, and for
the reasons stated below, the Board
believes that this final rule will not have
a significant economic impact on a
substantial number of small entities.
1. Statement of the need for, and
objectives of, the final rule. Regulation
AA was issued pursuant to section
18(f)(1) of the FTC Act. As noted above,
the Dodd-Frank Act repealed this
provision of the FTC Act.18
Accordingly, the Board is repealing its
Regulation AA.
2. Summary of issues raised by
comments in response to the initial
regulatory flexibility analysis. The
Board did not receive any comments on
the initial regulatory flexibility analysis.
3. Small entities affected by the final
rule. The final rule repeals Regulation
AA, which was issued pursuant to
section 18(f)(1) of the FTC. As a result
of the FTC Act amendments made by
the Dodd-Frank Act, the Board no
longer has rule writing authority under
section 18(f)(1). The legislative repeal of
the Board’s rulemaking authority
nullified the provisions in Regulation
AA that were issued pursuant to that
authority. Consequently, the Board’s
repeal of the regulation, which no
longer has legal effect, will not affect
any entity, including any small entity.
The repeal of Regulation AA will also
remove information about how the
Board processes consumer complaints
from the Code of Federal Regulations.
This is not expected to have an effect on
small entities because that information
is provided on the Board’s public Web
site.
4. Recordkeeping, reporting, and
compliance requirements. The final rule
repeals Regulation AA and therefore
does not impose any recordkeeping,
reporting, or compliance requirements
on any entities.
5. Significant alternatives to the final
revisions. Because the repeal of
Regulation AA will have no impact,
there are no alternatives that would
16 https://www.federalreserveconsumerhelp.gov/.
17 5
U.S.C. 601 et seq.
section 1092(2) of the Dodd-Frank Act.
18 See
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further minimize the economic impact
of the final rule on small entities.
IV. Paperwork Reduction Act
In accordance with the Paperwork
Reduction Act (PRA) of 1995 (44 U.S.C.
3506; 5 CFR 1320 Appendix A.1), the
Board reviewed the rule under the
authority delegated to the Federal
Reserve by the Office of Management
and Budget (OMB). The final rule
contains no requirements subject to the
PRA.
List of Subjects in 12 CFR Part 227
Banks, Banking, Consumer protection,
Credit, Federal Reserve System,
Finance.
Authority and Issuance
For the reasons set forth in the
preamble, and under the authority of
section 1092(2) of Public Law 111–203,
124 Stat. 1376 (Jul. 21, 2010), the Board
amends 12 CFR chapter II by removing
part 227.
PART 227—[REMOVED]
By order of the Board of Governors of the
Federal Reserve System, February 11, 2016.
Robert deV. Frierson,
Secretary of the Board.
[FR Doc. 2016–03228 Filed 2–17–16; 8:45 am]
BILLING CODE–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–0467; Directorate
Identifier 2016–NM–008–AD; Amendment
39–18395; AD 2016–04–01]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
AGENCY:
We are superseding
Airworthiness Directive (AD) 2015–26–
02 for all Airbus Model A330–200,
A330–200 Freighter, and A330–300
series airplanes; and Airbus Model
A340–200, A340–300, A340–500, and
A340–600 series airplanes. AD 2015–
26–02 required, for certain airplanes,
identification of the part number, serial
number, and standard of the ram air
turbine (RAT) pump, RAT module, RAT
actuator, and RAT lower gearbox
assembly; replacement of the balance
SUMMARY:
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Federal Register / Vol. 81, No. 32 / Thursday, February 18, 2016 / Rules and Regulations
weight screw, modification of the
actuator coil spring, modification of the
actuator, an inspection of the anti-stall
valve for correct installation in the RAT
pump housing; and corrective actions if
necessary. For certain other airplanes,
AD 2015–26–02 required reidentification or replacement of the RAT
module. This new AD requires the same
actions as AD 2015–26–02. This new
AD was prompted by a report of a
typographical error in the regulatory
text of AD 2015–26–02. We are issuing
this AD to prevent loss of the impeller
function and RAT pump pressurization
capability, which, if preceded by a total
engine flame-out, could result in loss of
control of the airplane.
DATES: This AD becomes effective
March 4, 2016.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of February 2, 2016 (80 FR 81174,
December 29, 2015).
We must receive comments on this
AD by April 4, 2016.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, 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 Avenue SE.,
Washington, DC, between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For Airbus service information
identified in this final rule, 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.A330A340@
airbus.com; Internet https://
www.airbus.com.
For Hamilton Sundstrand service
information identified in this final rule,
contact Hamilton Sundstrand, Technical
Publications, Mail Stop 302–9, 4747
Harrison Avenue, P.O. Box 7002,
Rockford, IL 61125–7002; telephone
860–654–3575; fax 860–998–4564; email
tech.solutions@hs.utc.com; Internet
https://www.hamiltonsundstrand.com.
You may view this referenced service
information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue
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SW., Renton, WA. For information on
the availability of this material at the
FAA, call 425–227–1221. It is also
available on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2016–
0467.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2016–
0467; 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 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, WA
98057–3356; telephone 425–227–1138;
fax 425–227–1149.
SUPPLEMENTARY INFORMATION:
Discussion
On December 9, 2015, we issued AD
2015–26–02, Amendment 39–18350 (80
FR 81174, December 29, 2015) (‘‘AD
2015–26–02’’). AD 2015–26–02 applied
to all Airbus Model A330–200, A330–
200 Freighter, and A330–300 series
airplanes; and Airbus Model A340–200,
A340–300, A340–500, and A340–600
series airplanes. AD 2015–26–02 was
prompted by a report indicating that,
during a production flight test, the RAT
did not pressurize the green hydraulic
system. AD 2015–26–02 required for
certain airplanes, identification of the
part number, serial number, and
standard of the RAT pump, RAT
module, RAT actuator, and RAT lower
gearbox assembly; replacement of the
balance weight screw, modification of
the actuator coil spring, modification of
the actuator, an inspection of the antistall valve for correct installation in the
RAT pump housing; and corrective
actions if necessary. For certain other
airplanes, AD 2015–26–02 required reidentification or replacement of the RAT
module. We issued AD 2015–26–02 to
prevent loss of the impeller function
and RAT pump pressurization
capability, which, if preceded by a total
engine flame-out, could result in loss of
control of the airplane.
Since we issued AD 2015–26–02, we
received a report of a typographical
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error in the regulatory text of AD 2015–
26–02. Paragraph (m) of AD 2015–26–02
inadvertently referred to paragraph (n)
and should have referred to paragraph
(o), ‘‘Parts Installation Prohibition.’’
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA Airworthiness
Directive 2013–0274, dated November
15, 2013 (referred to after this as the
Mandatory Continuing Airworthiness
Information, or ‘‘the MCAI’’), to correct
an unsafe condition for all Airbus
Model A330–200, A330–200 Freighter,
and A330–300 series airplanes; and
Airbus Model A340–200, A340–300,
A340–500, and A340–600 series
airplanes. The MCAI states:
During a production flight test of an A330–
300 aeroplane, the Ram Air Turbine (RAT)
did not pressurize the green hydraulic
system. Investigation revealed that the
impeller drive (hex) shaft had a reduced
length of engagement with the pump drive
shaft. This caused the impeller drive shaft to
disengage from the pump and disconnect the
impeller. It was determined that the
disconnection was the result of internal hex
dimensions on the pump impeller shaft,
which had been changed in a manufacturing
drawing. From the investigation analysis, it
was possible to identify a list of affected
parts.
This condition, if not detected and
corrected, could lead to the loss of impeller
function and RAT pump pressurization
capability, possibly resulting, in case of total
engine flame out, to the loss of control of the
aeroplane.
To address this unsafe condition, a new
design RAT pump shaft has been developed
with a decreased hexagonal shaft housing
depth, which increases the hexagonal drive
shaft engagement in the impeller shaft to
carry the impeller torque. Airbus issued
Service Bulletin (SB) A330–29–3122, SB
A340–29–4093 and SB A340–29–5021 to
provide instructions for in-service
replacement of the affected RAT hydraulic
pumps, or re-identification of the RAT pump
and complete RAT module, as applicable.
For the reasons described above, this
[EASA] AD requires identification and
replacement [modification] or reidentification of all affected RAT hydraulic
pumps on A330 and A340–200/300
aeroplanes, and replacement [modification]
of all affected RAT modules on A340–500/
–600 aeroplanes.
For affected pumps, the required
actions also include concurrent actions,
as applicable, including replacement of
the balance weight screw, modification
of the actuator coil spring, modification
of the actuator, an inspection of the antistall valve for correct installation in the
RAT pump housing and re-installation
if necessary. For affected pumps,
corrective actions include replacement
of the RAT hydraulic pump, and reidentification of the part number of the
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RAT module. You may examine the
MCAI on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2016–
0467.
Related Service Information Under 1
CFR Part 51
Airbus has issued the following
service information:
• Airbus Service Bulletin A330–29–
3122, dated October 25, 2012.
• Airbus Service Bulletin A340–29–
4093, dated October 25, 2012.
This service information describes
procedures for identifying the part
number, serial number, and standard of
the RAT pump, RAT module, RAT
actuator, and RAT lower gearbox
assembly; replacing the balance weight
screw, modifying the actuator coil
spring, modifying the actuator, and
doing an inspection of the anti-stall
valve for correct installation; and reidentifying the part numbers of the RAT
hydraulic pump and RAT module.
Airbus also issued Service Bulletin
A330–29–3126, dated June 12, 2014;
and Service Bulletin A340–29–4097,
dated June 12, 2014, which describe
procedures for identifying the part
number and serial number of the RAT
actuator; modifying the RAT actuators;
and re-identifying the part numbers of
the RAT module.
In addition, Airbus issued Service
Bulletin A340–29–5021, dated October
2, 2012; and Service Bulletin A340–29–
5025, dated June 16, 2014, which
describe procedures for replacing
(modifying) the RAT module.
Hamilton Sundstrand has issued
Service Bulletin ERPS06M–29–19, dated
August 6, 2012, which identifies the
serial numbers of the suspect hydraulic
pump.
This service information is reasonably
available because the interested parties
have access to it through their normal
course of business or by the means
identified in the ADDRESSES section.
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FAA’s Determination and Requirements
of This 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 issuing this
AD because we evaluated all pertinent
information and determined the unsafe
condition exists and is likely to exist or
develop on other products of these same
type designs.
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FAA’s Determination of the Effective
Date
We are superseding AD 2015–26–02
to correct a typographical error in the
regulatory text. No other changes have
been made to AD 2015–26–02.
Therefore, we determined that notice
and opportunity for prior public
comment are unnecessary.
Comments Invited
This AD is a final rule that involves
requirements affecting flight safety, and
we did not precede it by notice and
opportunity for public comment. We
invite you to send any written relevant
data, views, or arguments about this AD.
Send your comments to an address
listed under the ADDRESSES section.
Include ‘‘Docket No. FAA–2016–0467;
Directorate Identifier 2016–NM–008–
AD’’ at the beginning of your comments.
We specifically invite comments on the
overall regulatory, economic,
environmental, and energy aspects of
this AD. We will consider all comments
received by the closing date and may
amend this AD because of 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 AD.
Costs of Compliance
We estimate that this AD affects 66
airplanes of U.S. registry.
We also estimate that it will take
about 14 work-hours per product to
comply with the basic requirements of
this AD. The average labor rate is $85
per work-hour. Based on these figures,
we estimate the cost of this AD on U.S.
operators to be $78,540, or $1,190 per
product.
In addition, we estimate that any
necessary follow-on actions will take
about 18 work-hours and require parts
costing up to $427,301, for a cost of
$428,831 per product. We have no way
of determining the number of aircraft
that might need this action.
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
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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 that 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);
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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing airworthiness directive (AD)
2015–26–02, Amendment 39–18350 (80
FR 81174, December 29, 2015), and
adding the following new AD:
■
2016–04–01 Airbus: Amendment 39–18395;
Docket No. FAA–2016–0467; Directorate
Identifier 2016–NM–008–AD.
(a) Effective Date
This AD becomes effective March 4, 2016.
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(b) Affected ADs
(1) This AD replaces AD 2015–26–02,
Amendment 39–18350 (80 FR 81174,
December 29, 2015).
(2) This AD affects AD 2012–21–19,
Amendment 39–17235 (77 FR 65812, October
31, 2012); and AD 2012–21–20, Amendment
39–17236 (77 FR 65799, October 31, 2012).
(c) Applicability
This AD applies to all Airbus airplanes,
certificated in any category, identified in
paragraphs (c)(1) and (c)(2) of this AD, all
manufacturer serial numbers.
(1) Model A330–201, –202, –203, –223,
–223F, –243, –243F, –301, –302, –303, –321,
–322, –323, –341, –342, and –343 airplanes.
(2) Model A340–211, –212, –213, –311,
–312, –313, –541, and –642 airplanes.
(d) Subject
Air Transport Association (ATA) of
America Code 29, Hydraulic Power.
(e) Reason
This AD was prompted by a report
indicating that, during a production flight
test, the ram air turbine (RAT) did not
pressurize the green hydraulic system. We
are issuing this AD to prevent loss of the
impeller function and RAT pump
pressurization capability, which, if preceded
by a total engine flame-out, could result in
loss of control of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
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(g) Identification of RAT Components
For Airbus Model A330–201, –202, –203,
–223, –223F, –243, –243F, –301, –302, –303,
–321, –322, –323, –341, –342, and –343
airplanes; and Model A340–211, –212, –213,
–311, –312, and –313 airplanes: Except as
provided by paragraph (i) of this AD, within
36 months after the effective date of this AD,
identify the part number, serial number, and
standard (through the mod-dots) of the RAT
pump, RAT module, RAT actuator, and RAT
lower gearbox assembly, in accordance with
the Accomplishment Instructions of the
applicable Airbus service information
specified in paragraphs (g)(1) and (g)(2) of
this AD. A review of airplane maintenance
records is acceptable in lieu of this
identification if the part number, serial
number, and standard can be conclusively
determined from that review.
(1) For Airbus Model A330–201, –202,
–203, –223, –223F, –243, –243F, –301, –302,
–303, –321, –322, –323, –341, –342, and –343
airplanes: Airbus Service Bulletin A330–29–
3122, dated October 25, 2012.
(2) For Airbus Model A340–211, –212,
–213, –311, –312, and –313 airplanes: Airbus
Service Bulletin A340–29–4093, dated
October 25, 2012.
(h) Corrective and Concurrent Actions
If the serial number of the RAT hydraulic
pump is included in table 7, ‘‘Suspect
Hydraulic Pump Serial Numbers,’’ of
Hamilton Sundstrand Service Bulletin
ERPS06M–29–19, dated August 6, 2012:
Within 36 months after the effective date of
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this AD, do all applicable corrective actions,
in accordance with the Accomplishment
Instructions of the applicable Airbus service
information specified in paragraphs (g)(1)
and (g)(2) of this AD. Prior to or concurrently
with doing the corrective actions required by
this paragraph, do the actions specified in
paragraphs (h)(1) through (h)(4) of this AD,
in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A330–
29–3122, dated October 25, 2012 (for Model
A330–200, –200 Freighter, and –300 series
airplanes); or Airbus Service Bulletin A340–
29–4093, dated October 25, 2012 (for Airbus
Model A340–211, –212, –213, –311, –312,
and –313 airplanes).
(1) Replace the balance weight screw.
(2) Modify the actuator coil spring.
(3) Modify the actuator.
(4) Do a general visual inspection of the
anti-stall valve for correct installation in the
RAT pump housing, and if any incorrect
installation is found, before further flight,
correctly install the anti-stall valve.
(i) Exception to Service Information
Specifications
Airbus Service Bulletin A330–29–3122,
dated October 25, 2012 (for Model A330–200,
–200 Freighter, and –300 series airplanes),
refers to Hamilton Sundstrand Service
Bulletin ‘‘EPRPS06M–29–13’’ as an
additional source of guidance for doing
certain actions required by paragraph (h) of
this AD. The first ‘‘P’’ in the citation should
have been omitted; the correct reference is to
Hamilton Sundstrand Service Bulletin
‘‘ERPS06M–29–13.’’
(j) Re-Identification of Part Numbers
If the serial number of the RAT hydraulic
pump is not included in table 7, ‘‘Suspect
Hydraulic Pump Serial Numbers,’’ of
Hamilton Sundstrand Service Bulletin
ERPS06M–29–19, dated August 6, 2012:
Within 36 months after the effective date of
this AD, re-identify the part numbers of the
RAT hydraulic pump and RAT module, in
accordance with the Accomplishment
Instructions of the applicable Airbus service
information specified in paragraphs (g)(1)
and (g)(2) of this AD.
(k) Service Information for Optional Actions
Accomplishment of the actions required by
paragraphs (g), (h), and (j) of this AD, in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A330–
29–3126, dated June 12, 2014; or Airbus
Service Bulletin A340–29–4097, dated June
12, 2014, as applicable, constitutes
compliance with the requirements of
paragraphs (g), (h), and (j) of this AD.
(l) RAT Module Replacement (Modification)
For Airbus Model A340–541 and –642
airplanes having RAT module part number
(P/N) 772722D, 772722E, 772722F, or
772722G: Within 36 months after the
effective date of this AD, replace (modify) the
RAT module, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A340–29–5021, dated
October 2, 2012. As an option,
accomplishment of the RAT module
replacement (modification), in accordance
with the Accomplishment Instructions of
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8137
Airbus Service Bulletin A340–29–5025,
dated June 16, 2014, constitutes compliance
with the requirement of this paragraph.
(m) Exception to Paragraphs (g), (h), and (j)
of This AD
The actions required by paragraphs (g), (h),
and (j) of this AD are not required for
airplanes on which Airbus Modification
202537 was embodied in production,
provided it can be determined that, since the
airplane’s first flight, no RAT hydraulic
pump or RAT module having a part number
identified in paragraph (o) of this AD is
installed on that airplane.
(n) Terminating Action for Certain
Requirements of Other ADs
(1) For Airbus Model A330–201, –202,
–203, –223, –223F, –243, –243F, –301, –302,
–303, –321, –322, –323, –341, –342, and –343
airplanes; and Model A340–211, –212, –213,
–311, –312, and –313 airplanes:
Accomplishment of the actions required by
paragraphs (g), (h), and (j) of this AD
constitutes compliance with the
requirements of paragraphs (g)(1) and (g)(2)
of AD 2012–21–19, Amendment 39–17235
(77 FR 65812, October 31, 2012); and
paragraphs (g)(1) and (g)(2) of AD 2012–21–
20, Amendment 39–17236 (77 FR 65799,
October 31, 2012).
(2) For Airbus Model A340–541 and –642
airplanes: Accomplishment of the actions
required by paragraph (l) of this AD
constitutes compliance with the
requirements of paragraphs (h)(1) and (h)(2)
of AD 2012–21–20, Amendment 39–17236
(77 FR 65799, October 31, 2012).
(o) Parts Installation Prohibition
(1) For Airbus Model A330–201, –202,
–203, –223, –223F, –243, –243F, –301, –302,
–303, –321, –322, –323, –341, –342, and –343
airplanes; and A340–211, –212, –213, –311,
–312, and –313 airplanes: After modification
of the RAT module as required by paragraph
(h) of this AD, no person may install any
complete RAT module having a part number
identified in paragraph (o)(1)(i) of this AD, or
any RAT hydraulic pump having the part
number identified in paragraph (o)(1)(ii) of
this AD, on any airplane.
(i) RAT module P/N 766351, 768084,
770379, 770952, 770952A, 770952B,
1702934, 1702934A, or 1702934B.
(ii) RAT hydraulic pump P/N 5909522
(Parker P/N 4207902).
(2) For Airbus Model A340–541 and –642
airplanes: After modification of the RAT
module as required by paragraph (l) of this
AD, no person may install any complete RAT
module having P/N 772722D, 772722E,
772722F, or 772722G, on any airplane.
(p) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
In accordance with 14 CFR 39.19, send your
request to your principal inspector or local
Flight Standards District Office, as
E:\FR\FM\18FER1.SGM
18FER1
8138
Federal Register / Vol. 81, No. 32 / Thursday, February 18, 2016 / Rules and Regulations
appropriate. If sending information directly
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, WA 98057–3356;
telephone 425–227–1138; fax 425–227–1149.
Information may be emailed to: 9-ANM-116AMOC-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) Contacting the Manufacturer: For any
requirement in this AD to obtain corrective
actions from a manufacturer, the action must
be accomplished using a method approved
by the Manager, International Branch, ANM–
116, Transport Airplane Directorate, FAA; or
the European Aviation Safety Agency
(EASA); or Airbus’s EASA Design
Organization Approval (DOA). If approved by
the DOA, the approval must include the
DOA-authorized signature.
wgreen on DSK2VPTVN1PROD with RULES
(q) Related Information
Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2013–0274, dated
November 15, 2013, for related information.
This MCAI may be found in the AD docket
on the Internet at https://www.regulations.gov
by searching for and locating Docket No.
FAA–2016–0467.
(r) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless this AD specifies otherwise.
(3) The following service information was
approved for IBR on February 2, 2016 (80 FR
81174, December 29, 2015).
(i) Airbus Service Bulletin A330–29–3122,
dated October 25, 2012.
(ii) Airbus Service Bulletin A330–29–3126,
dated June 12, 2014.
(iii) Airbus Service Bulletin A340–29–
4093, dated October 25, 2012.
(iv) Airbus Service Bulletin A340–29–
4097, dated June 12, 2014.
(v) Airbus Service Bulletin A340–29–5021,
dated October 2, 2012.
(vi) Airbus Service Bulletin A340–29–
5025, dated June 16, 2014.
(vii) Hamilton Sundstrand Service Bulletin
ERPS06M–29–19, dated August 6, 2012.
(4) For Airbus service information
identified in this 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.A330A340@airbus.com; Internet https://
www.airbus.com.
(5) For Hamilton Sundstrand service
information identified in this AD, contact
Hamilton Sundstrand, Technical
Publications, Mail Stop 302–9, 4747 Harrison
Avenue, P.O. Box 7002, Rockford, IL 61125–
VerDate Sep<11>2014
14:29 Feb 17, 2016
Jkt 238001
7002; telephone 860–654–3575; fax 860–998–
4564; email tech.solutions@hs.utc.com;
Internet https://
www.hamiltonsundstrand.com.
(6) You may view this service information
at the FAA, Transport Airplane Directorate,
1601 Lind Avenue SW., Renton, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
(7) You may view this 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/cfr/ibrlocations.html.
Issued in Renton, Washington, on February
8, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2016–03215 Filed 2–17–16; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–3630; Directorate
Identifier 2014–NM–253–AD; Amendment
39–18397; AD 2016–04–03]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for all The
Boeing Company Model 747–400F
series airplanes. This AD was prompted
by an analysis of the production
methods used to increase fatigue
resistance of the upper closure fittings at
the nose cargo door portal’s C–3 frame,
which showed that cracking could start
too early to be caught in a timely
manner by the inspection or
maintenance program. This AD requires
inspections of the upper closure fitting
and connected strap and doubler at the
nose cargo door portal for cracking, and
related investigative and corrective
actions if necessary. We are issuing this
AD to detect and correct such cracking,
which could result in sudden
decompression and loss of the airplane’s
structural integrity.
DATES: This AD is effective March 24,
2016.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of March 24, 2016.
SUMMARY:
PO 00000
Frm 00006
Fmt 4700
Sfmt 4700
For service information
identified in this final rule, contact
Boeing Commercial Airplanes,
Attention: Data & Services Management,
P.O. Box 3707, MC 2H–65, Seattle, WA
98124–2207; telephone 206–544–5000,
extension 1; fax 206–766–5680; Internet
https://www.myboeingfleet.com. You
may view this referenced service
information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue
SW., Renton, WA. For information on
the availability of this material at the
FAA, call 425–227–1221. It is also
available on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2015–
3630.
ADDRESSES:
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2015–
3630; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this AD, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (phone: 800–647–5527) is
Docket Management Facility, U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590.
FOR FURTHER INFORMATION CONTACT: Bill
Ashforth, Aerospace Engineer, Airframe
Branch, ANM–120S, FAA, Seattle
Aircraft Certification Office (ACO), 1601
Lind Avenue SW., Renton, WA 98057–
3356; phone: 425–917–6432; fax: 425–
917–6590; email: bill.ashforth@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to all The Boeing Company Model
747–400F series airplanes. The NPRM
published in the Federal Register on
September 15, 2015 (80 FR 55273) (‘‘the
NPRM’’). The NPRM was prompted by
a report indicating that an analysis of
the production methods used to
increase fatigue resistance of the upper
closure fittings at the nose cargo door
portal’s C–3 frame showed that cracking
could start too early to be caught in a
timely manner by the inspection or
maintenance program. The upper
closure fittings used in the nose cargo
door portal C–3 frame were shot peened
to increase fatigue resistance. However,
an analysis showed that the increase in
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]]>Agencies
[Federal Register Volume 81, Number 32 (Thursday, February 18, 2016)]
[Rules and Regulations]
[Pages 8134-8138]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-03215]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2016-0467; Directorate Identifier 2016-NM-008-AD;
Amendment 39-18395; AD 2016-04-01]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: We are superseding Airworthiness Directive (AD) 2015-26-02 for
all Airbus Model A330-200, A330-200 Freighter, and A330-300 series
airplanes; and Airbus Model A340-200, A340-300, A340-500, and A340-600
series airplanes. AD 2015-26-02 required, for certain airplanes,
identification of the part number, serial number, and standard of the
ram air turbine (RAT) pump, RAT module, RAT actuator, and RAT lower
gearbox assembly; replacement of the balance
[[Page 8135]]
weight screw, modification of the actuator coil spring, modification of
the actuator, an inspection of the anti-stall valve for correct
installation in the RAT pump housing; and corrective actions if
necessary. For certain other airplanes, AD 2015-26-02 required re-
identification or replacement of the RAT module. This new AD requires
the same actions as AD 2015-26-02. This new AD was prompted by a report
of a typographical error in the regulatory text of AD 2015-26-02. We
are issuing this AD to prevent loss of the impeller function and RAT
pump pressurization capability, which, if preceded by a total engine
flame-out, could result in loss of control of the airplane.
DATES: This AD becomes effective March 4, 2016.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of February 2,
2016 (80 FR 81174, December 29, 2015).
We must receive comments on this AD by April 4, 2016.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, 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 Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
For Airbus service information identified in this final rule,
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.A330A340@airbus.com; Internet
https://www.airbus.com.
For Hamilton Sundstrand service information identified in this
final rule, contact Hamilton Sundstrand, Technical Publications, Mail
Stop 302-9, 4747 Harrison Avenue, P.O. Box 7002, Rockford, IL 61125-
7002; telephone 860-654-3575; fax 860-998-4564; email
tech.solutions@hs.utc.com; Internet https://www.hamiltonsundstrand.com.
You may view this referenced service information at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For
information on the availability of this material at the FAA, call 425-
227-1221. It is also available on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2016-
0467.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2016-
0467; 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 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, WA 98057-3356; telephone 425-227-1138;
fax 425-227-1149.
SUPPLEMENTARY INFORMATION:
Discussion
On December 9, 2015, we issued AD 2015-26-02, Amendment 39-18350
(80 FR 81174, December 29, 2015) (``AD 2015-26-02''). AD 2015-26-02
applied to all Airbus Model A330-200, A330-200 Freighter, and A330-300
series airplanes; and Airbus Model A340-200, A340-300, A340-500, and
A340-600 series airplanes. AD 2015-26-02 was prompted by a report
indicating that, during a production flight test, the RAT did not
pressurize the green hydraulic system. AD 2015-26-02 required for
certain airplanes, identification of the part number, serial number,
and standard of the RAT pump, RAT module, RAT actuator, and RAT lower
gearbox assembly; replacement of the balance weight screw, modification
of the actuator coil spring, modification of the actuator, an
inspection of the anti-stall valve for correct installation in the RAT
pump housing; and corrective actions if necessary. For certain other
airplanes, AD 2015-26-02 required re-identification or replacement of
the RAT module. We issued AD 2015-26-02 to prevent loss of the impeller
function and RAT pump pressurization capability, which, if preceded by
a total engine flame-out, could result in loss of control of the
airplane.
Since we issued AD 2015-26-02, we received a report of a
typographical error in the regulatory text of AD 2015-26-02. Paragraph
(m) of AD 2015-26-02 inadvertently referred to paragraph (n) and should
have referred to paragraph (o), ``Parts Installation Prohibition.''
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA
Airworthiness Directive 2013-0274, dated November 15, 2013 (referred to
after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition for all Airbus Model
A330-200, A330-200 Freighter, and A330-300 series airplanes; and Airbus
Model A340-200, A340-300, A340-500, and A340-600 series airplanes. The
MCAI states:
During a production flight test of an A330-300 aeroplane, the
Ram Air Turbine (RAT) did not pressurize the green hydraulic system.
Investigation revealed that the impeller drive (hex) shaft had a
reduced length of engagement with the pump drive shaft. This caused
the impeller drive shaft to disengage from the pump and disconnect
the impeller. It was determined that the disconnection was the
result of internal hex dimensions on the pump impeller shaft, which
had been changed in a manufacturing drawing. From the investigation
analysis, it was possible to identify a list of affected parts.
This condition, if not detected and corrected, could lead to the
loss of impeller function and RAT pump pressurization capability,
possibly resulting, in case of total engine flame out, to the loss
of control of the aeroplane.
To address this unsafe condition, a new design RAT pump shaft
has been developed with a decreased hexagonal shaft housing depth,
which increases the hexagonal drive shaft engagement in the impeller
shaft to carry the impeller torque. Airbus issued Service Bulletin
(SB) A330-29-3122, SB A340-29-4093 and SB A340-29-5021 to provide
instructions for in-service replacement of the affected RAT
hydraulic pumps, or re-identification of the RAT pump and complete
RAT module, as applicable.
For the reasons described above, this [EASA] AD requires
identification and replacement [modification] or re-identification
of all affected RAT hydraulic pumps on A330 and A340-200/300
aeroplanes, and replacement [modification] of all affected RAT
modules on A340-500/ -600 aeroplanes.
For affected pumps, the required actions also include concurrent
actions, as applicable, including replacement of the balance weight
screw, modification of the actuator coil spring, modification of the
actuator, an inspection of the anti-stall valve for correct
installation in the RAT pump housing and re-installation if necessary.
For affected pumps, corrective actions include replacement of the RAT
hydraulic pump, and re-identification of the part number of the
[[Page 8136]]
RAT module. You may examine the MCAI on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2016-
0467.
Related Service Information Under 1 CFR Part 51
Airbus has issued the following service information:
Airbus Service Bulletin A330-29-3122, dated October 25,
2012.
Airbus Service Bulletin A340-29-4093, dated October 25,
2012.
This service information describes procedures for identifying the
part number, serial number, and standard of the RAT pump, RAT module,
RAT actuator, and RAT lower gearbox assembly; replacing the balance
weight screw, modifying the actuator coil spring, modifying the
actuator, and doing an inspection of the anti-stall valve for correct
installation; and re-identifying the part numbers of the RAT hydraulic
pump and RAT module.
Airbus also issued Service Bulletin A330-29-3126, dated June 12,
2014; and Service Bulletin A340-29-4097, dated June 12, 2014, which
describe procedures for identifying the part number and serial number
of the RAT actuator; modifying the RAT actuators; and re-identifying
the part numbers of the RAT module.
In addition, Airbus issued Service Bulletin A340-29-5021, dated
October 2, 2012; and Service Bulletin A340-29-5025, dated June 16,
2014, which describe procedures for replacing (modifying) the RAT
module.
Hamilton Sundstrand has issued Service Bulletin ERPS06M-29-19,
dated August 6, 2012, which identifies the serial numbers of the
suspect hydraulic pump.
This service information is reasonably available because the
interested parties have access to it through their normal course of
business or by the means identified in the ADDRESSES section.
FAA's Determination and Requirements of This 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 issuing this AD because we
evaluated all pertinent information and determined the unsafe condition
exists and is likely to exist or develop on other products of these
same type designs.
FAA's Determination of the Effective Date
We are superseding AD 2015-26-02 to correct a typographical error
in the regulatory text. No other changes have been made to AD 2015-26-
02. Therefore, we determined that notice and opportunity for prior
public comment are unnecessary.
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety, and we did not precede it by notice and opportunity for public
comment. We invite you to send any written relevant data, views, or
arguments about this AD. Send your comments to an address listed under
the ADDRESSES section. Include ``Docket No. FAA-2016-0467; Directorate
Identifier 2016-NM-008-AD'' at the beginning of your comments. We
specifically invite comments on the overall regulatory, economic,
environmental, and energy aspects of this AD. We will consider all
comments received by the closing date and may amend this AD because of
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 AD.
Costs of Compliance
We estimate that this AD affects 66 airplanes of U.S. registry.
We also estimate that it will take about 14 work-hours per product
to comply with the basic requirements of this AD. The average labor
rate is $85 per work-hour. Based on these figures, we estimate the cost
of this AD on U.S. operators to be $78,540, or $1,190 per product.
In addition, we estimate that any necessary follow-on actions will
take about 18 work-hours and require parts costing up to $427,301, for
a cost of $428,831 per product. We have no way of determining the
number of aircraft that might need this action.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We determined that this AD will not have federalism implications
under Executive Order 13132. This AD will not have a substantial direct
effect on the States, on the relationship between the national
government and the States, or on the distribution of power and
responsibilities among the various levels of government.
For the reasons discussed above, I certify that 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);
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.
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 airworthiness directive (AD)
2015-26-02, Amendment 39-18350 (80 FR 81174, December 29, 2015), and
adding the following new AD:
2016-04-01 Airbus: Amendment 39-18395; Docket No. FAA-2016-0467;
Directorate Identifier 2016-NM-008-AD.
(a) Effective Date
This AD becomes effective March 4, 2016.
[[Page 8137]]
(b) Affected ADs
(1) This AD replaces AD 2015-26-02, Amendment 39-18350 (80 FR
81174, December 29, 2015).
(2) This AD affects AD 2012-21-19, Amendment 39-17235 (77 FR
65812, October 31, 2012); and AD 2012-21-20, Amendment 39-17236 (77
FR 65799, October 31, 2012).
(c) Applicability
This AD applies to all Airbus airplanes, certificated in any
category, identified in paragraphs (c)(1) and (c)(2) of this AD, all
manufacturer serial numbers.
(1) Model A330-201, -202, -203, -223, -223F, -243, -243F, -301,
-302, -303, -321, -322, -323, -341, -342, and -343 airplanes.
(2) Model A340-211, -212, -213, -311, -312, -313, -541, and -642
airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 29, Hydraulic
Power.
(e) Reason
This AD was prompted by a report indicating that, during a
production flight test, the ram air turbine (RAT) did not pressurize
the green hydraulic system. We are issuing this AD to prevent loss
of the impeller function and RAT pump pressurization capability,
which, if preceded by a total engine flame-out, could result in loss
of control of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Identification of RAT Components
For Airbus Model A330-201, -202, -203, -223, -223F, -243, -243F,
-301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes;
and Model A340-211, -212, -213, -311, -312, and -313 airplanes:
Except as provided by paragraph (i) of this AD, within 36 months
after the effective date of this AD, identify the part number,
serial number, and standard (through the mod-dots) of the RAT pump,
RAT module, RAT actuator, and RAT lower gearbox assembly, in
accordance with the Accomplishment Instructions of the applicable
Airbus service information specified in paragraphs (g)(1) and (g)(2)
of this AD. A review of airplane maintenance records is acceptable
in lieu of this identification if the part number, serial number,
and standard can be conclusively determined from that review.
(1) For Airbus Model A330-201, -202, -203, -223, -223F, -243, -
243F, -301, -302, -303, -321, -322, -323, -341, -342, and -343
airplanes: Airbus Service Bulletin A330-29-3122, dated October 25,
2012.
(2) For Airbus Model A340-211, -212, -213, -311, -312, and -313
airplanes: Airbus Service Bulletin A340-29-4093, dated October 25,
2012.
(h) Corrective and Concurrent Actions
If the serial number of the RAT hydraulic pump is included in
table 7, ``Suspect Hydraulic Pump Serial Numbers,'' of Hamilton
Sundstrand Service Bulletin ERPS06M-29-19, dated August 6, 2012:
Within 36 months after the effective date of this AD, do all
applicable corrective actions, in accordance with the Accomplishment
Instructions of the applicable Airbus service information specified
in paragraphs (g)(1) and (g)(2) of this AD. Prior to or concurrently
with doing the corrective actions required by this paragraph, do the
actions specified in paragraphs (h)(1) through (h)(4) of this AD, in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A330-29-3122, dated October 25, 2012 (for Model A330-200, -
200 Freighter, and -300 series airplanes); or Airbus Service
Bulletin A340-29-4093, dated October 25, 2012 (for Airbus Model
A340-211, -212, -213, -311, -312, and -313 airplanes).
(1) Replace the balance weight screw.
(2) Modify the actuator coil spring.
(3) Modify the actuator.
(4) Do a general visual inspection of the anti-stall valve for
correct installation in the RAT pump housing, and if any incorrect
installation is found, before further flight, correctly install the
anti-stall valve.
(i) Exception to Service Information Specifications
Airbus Service Bulletin A330-29-3122, dated October 25, 2012
(for Model A330-200, -200 Freighter, and -300 series airplanes),
refers to Hamilton Sundstrand Service Bulletin ``EPRPS06M-29-13'' as
an additional source of guidance for doing certain actions required
by paragraph (h) of this AD. The first ``P'' in the citation should
have been omitted; the correct reference is to Hamilton Sundstrand
Service Bulletin ``ERPS06M-29-13.''
(j) Re-Identification of Part Numbers
If the serial number of the RAT hydraulic pump is not included
in table 7, ``Suspect Hydraulic Pump Serial Numbers,'' of Hamilton
Sundstrand Service Bulletin ERPS06M-29-19, dated August 6, 2012:
Within 36 months after the effective date of this AD, re-identify
the part numbers of the RAT hydraulic pump and RAT module, in
accordance with the Accomplishment Instructions of the applicable
Airbus service information specified in paragraphs (g)(1) and (g)(2)
of this AD.
(k) Service Information for Optional Actions
Accomplishment of the actions required by paragraphs (g), (h),
and (j) of this AD, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A330-29-3126, dated June 12,
2014; or Airbus Service Bulletin A340-29-4097, dated June 12, 2014,
as applicable, constitutes compliance with the requirements of
paragraphs (g), (h), and (j) of this AD.
(l) RAT Module Replacement (Modification)
For Airbus Model A340-541 and -642 airplanes having RAT module
part number (P/N) 772722D, 772722E, 772722F, or 772722G: Within 36
months after the effective date of this AD, replace (modify) the RAT
module, in accordance with the Accomplishment Instructions of Airbus
Service Bulletin A340-29-5021, dated October 2, 2012. As an option,
accomplishment of the RAT module replacement (modification), in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A340-29-5025, dated June 16, 2014, constitutes compliance
with the requirement of this paragraph.
(m) Exception to Paragraphs (g), (h), and (j) of This AD
The actions required by paragraphs (g), (h), and (j) of this AD
are not required for airplanes on which Airbus Modification 202537
was embodied in production, provided it can be determined that,
since the airplane's first flight, no RAT hydraulic pump or RAT
module having a part number identified in paragraph (o) of this AD
is installed on that airplane.
(n) Terminating Action for Certain Requirements of Other ADs
(1) For Airbus Model A330-201, -202, -203, -223, -223F, -243, -
243F, -301, -302, -303, -321, -322, -323, -341, -342, and -343
airplanes; and Model A340-211, -212, -213, -311, -312, and -313
airplanes: Accomplishment of the actions required by paragraphs (g),
(h), and (j) of this AD constitutes compliance with the requirements
of paragraphs (g)(1) and (g)(2) of AD 2012-21-19, Amendment 39-17235
(77 FR 65812, October 31, 2012); and paragraphs (g)(1) and (g)(2) of
AD 2012-21-20, Amendment 39-17236 (77 FR 65799, October 31, 2012).
(2) For Airbus Model A340-541 and -642 airplanes: Accomplishment
of the actions required by paragraph (l) of this AD constitutes
compliance with the requirements of paragraphs (h)(1) and (h)(2) of
AD 2012-21-20, Amendment 39-17236 (77 FR 65799, October 31, 2012).
(o) Parts Installation Prohibition
(1) For Airbus Model A330-201, -202, -203, -223, -223F, -243, -
243F, -301, -302, -303, -321, -322, -323, -341, -342, and -343
airplanes; and A340-211, -212, -213, -311, -312, and -313 airplanes:
After modification of the RAT module as required by paragraph (h) of
this AD, no person may install any complete RAT module having a part
number identified in paragraph (o)(1)(i) of this AD, or any RAT
hydraulic pump having the part number identified in paragraph
(o)(1)(ii) of this AD, on any airplane.
(i) RAT module P/N 766351, 768084, 770379, 770952, 770952A,
770952B, 1702934, 1702934A, or 1702934B.
(ii) RAT hydraulic pump P/N 5909522 (Parker P/N 4207902).
(2) For Airbus Model A340-541 and -642 airplanes: After
modification of the RAT module as required by paragraph (l) of this
AD, no person may install any complete RAT module having P/N
772722D, 772722E, 772722F, or 772722G, on any airplane.
(p) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
has the authority to approve AMOCs for this AD, if requested using
the procedures found in 14 CFR 39.19. In accordance with 14 CFR
39.19, send your request to your principal inspector or local Flight
Standards District Office, as
[[Page 8138]]
appropriate. If sending information directly 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, WA 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) Contacting the Manufacturer: For any requirement in this AD
to obtain corrective actions from a manufacturer, the action must be
accomplished using a method approved by the Manager, International
Branch, ANM-116, Transport Airplane Directorate, FAA; or the
European Aviation Safety Agency (EASA); or Airbus's EASA Design
Organization Approval (DOA). If approved by the DOA, the approval
must include the DOA-authorized signature.
(q) Related Information
Refer to Mandatory Continuing Airworthiness Information (MCAI)
EASA Airworthiness Directive 2013-0274, dated November 15, 2013, for
related information. This MCAI may be found in the AD docket on the
Internet at https://www.regulations.gov by searching for and locating
Docket No. FAA-2016-0467.
(r) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless this AD specifies otherwise.
(3) The following service information was approved for IBR on
February 2, 2016 (80 FR 81174, December 29, 2015).
(i) Airbus Service Bulletin A330-29-3122, dated October 25,
2012.
(ii) Airbus Service Bulletin A330-29-3126, dated June 12, 2014.
(iii) Airbus Service Bulletin A340-29-4093, dated October 25,
2012.
(iv) Airbus Service Bulletin A340-29-4097, dated June 12, 2014.
(v) Airbus Service Bulletin A340-29-5021, dated October 2, 2012.
(vi) Airbus Service Bulletin A340-29-5025, dated June 16, 2014.
(vii) Hamilton Sundstrand Service Bulletin ERPS06M-29-19, dated
August 6, 2012.
(4) For Airbus service information identified in this 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.
(5) For Hamilton Sundstrand service information identified in
this AD, contact Hamilton Sundstrand, Technical Publications, Mail
Stop 302-9, 4747 Harrison Avenue, P.O. Box 7002, Rockford, IL 61125-
7002; telephone 860-654-3575; fax 860-998-4564; email
tech.solutions@hs.utc.com; Internet https://www.hamiltonsundstrand.com.
(6) You may view this service information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For
information on the availability of this material at the FAA, call
425-227-1221.
(7) You may view this 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/cfr/ibr-locations.html.
Issued in Renton, Washington, on February 8, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2016-03215 Filed 2-17-16; 8:45 am]
BILLING CODE 4910-13-P
