Airworthiness Directives; Airbus Airplanes, 7098-7103 [2014-02522]
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Proposed Rules
Federal Register
Vol. 79, No. 25
Thursday, February 6, 2014
This section of the FEDERAL REGISTER
contains notices to the public of the proposed
issuance of rules and regulations. The
purpose of these notices is to give interested
persons an opportunity to participate in the
rule making prior to the adoption of the final
rules.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–0012; Directorate
Identifier 2012–NM–007–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to supersede
Airworthiness Directive (AD) 2004–16–
01, that applies to certain Airbus Model
A330–200 and –300, and Model A340–
200 and –300, series airplanes. AD
2004–16–01 currently requires
repetitive inspections for cracking of the
chromed area of the left and right piston
rods for the main landing gear (MLG)
retraction actuators, and related
investigative and corrective actions if
necessary. Since we issued AD 2004–
16–01, we have determined that the
presence of water in the internal volume
of the piston rod can consequently lead
to propagation of longitudinal cracking
in the body of the piston rod. We have
also determined through sampling that
certain retraction actuator piston rods of
the MLG need to be replaced. This
proposed AD would require repetitive
draining of any fluid from the retraction
actuator piston rod internal volume and
sealing of the vent hole; repetitive
ultrasonic inspections of the upper end
of the piston rods, and corrective
actions if necessary; a one-time
ultrasonic inspection (longitudinal and
circumferential) of the full-length of the
piston rod, and corrective actions if
necessary; and a terminating
modification of the left-hand and righthand MLG retraction actuators. We are
proposing this AD to prevent cracking of
the piston rods for the MLG retraction
actuators, which could result in rupture
of a piston rod, non-damped extension
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of the MLG, high loads on the fully
extended MLG, and consequent reduced
structural integrity of the MLG.
DATES: We must receive comments on
this proposed AD by March 24, 2014.
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 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 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.
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–2014–
0012; 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 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, WA
98057–3356; telephone (425) 227–1138;
fax (425) 227–1149.
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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–2014–0012; Directorate Identifier
2012–NM–007–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
On July 23, 2004, we issued AD 2004–
16–01, Amendment 39–13757 (69 FR
46979, August 4, 2004). AD 2004–16–01
requires actions intended to address an
unsafe condition on the products listed
above.
Since we issued AD 2004–16–01, the
European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, has issued EASA AD 2011–
0178R1, dated March 6, 2012, corrected
March 7, 2012 (for Model A340–200 and
–300 series airplanes); and EASA AD
2011–0179R1, dated March 6, 2012 (for
Model A330–200 and –300 series
airplanes) (both referred to after this as
the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’); to correct an unsafe condition
for the specified products. EASA AD
2011–0178R1, dated March 6, 2012,
corrected March 7, 2012, states:
During an approach phase, the flight crew
of an A330 aeroplane had to perform a freefall extension of the left-hand (LH) MLG.
Rupture of the LH MLG retraction actuator
piston rod was found near the rod attachment
point. The inspection revealed at the location
of the rupture the presence of corrosion
resulting from incorrect application of the
anticorrosion protection, and circumferential
cracks resulting from normal operational
loading effects.
Since the above rupture, new cases of crack
propagation along the length of the piston
rod occurred. These ruptures led to a nondamped extension of the landing gear. Fully
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extended, the landing gear assembly was
submitted to high loads jeopardizing its
structural integrity.
This condition, if not detected and
corrected, could lead to MLG failure during
landing or roll-out and consequent damage to
the aeroplane and injury to occupants.
DGAC France issued AD F–2005–098
(EASA approval 2005–5887) [and AD F–
2005–099 (EASA approval 2005–5888)] to
address this unsafe condition [the FAA
issued AD 2004–16–01, Amendment 39–
13757 (69 FR 46979, August 4, 2004)]. Since
that [DGAC France] AD was issued, the
results of extensive investigation determined
that the presence of water in the internal
volume of the piston rod can lead to the
formation of ice which represents a potential
source of high magnitude tensile hoop
stresses in the material of the rod, leading to
propagation of longitudinal crack in the body
of the piston rod.
Prompted by these findings, EASA issued
AD 2006–0301, partially retaining the
requirements of DGAC France AD F–2005–
099, which was superseded, and to revise the
inspection requirements as follows:
a. Extend the repetitive inspections
interval for the removal of fluid from the
internal volume of the piston rod using flight
cycles in lieu of flight hours as this better
represents the mechanism for the
accumulation of water within the piston rod.
b. Remove the preliminary visual
inspection from the ultrasonic longitudinal
inspection of the upper end of the piston rod.
c. Add a new one-time ultrasonic
longitudinal and circumferential inspection
of the full piston rod length to eliminate any
parts that exhibit severe corrosion along the
internal length of the piston rod.
d. Require installation of new design
hollow piston rod Part Number (P/N)
114256328 (Airbus mod. 52980—SB A340–
32–4222 Revision 01) without a vent hole,
thus eliminating moisture ingress as the
terminating action.
EASA AD 2006–0301 was later revised:
—at revision 01, to correct a number of
typographical errors and to add reference
to Airbus SB A340–32–4212 Revision 04,
and
—at revision 02 to extend the inspections
threshold from 3 to 6 years in service usage
for retraction actuator piston rod P/N
114256321 issue 06 which was reidentified to P/N 114256326 issue 01 in
accordance with the instructions of Airbus
SB A340–32–4260.
More recently, the sampling of piston rod
P/N 114256326 issue 1 and P/N 114256321
issue 06 have confirmed the need to replace
all retraction actuator piston rods with a
piston rod P/N114256328.
For the reasons described above, this
[EASA] AD at original issue retained the
requirements of EASA AD 2006–0301R2
(https://ad.easa.europa.eu/blob/easa_ad_
2006_0301_R2_superseded.pdf/AD_20060301R2_1), which is superseded, and
required the replacement of all retraction
actuator piston rods with a piston rod P/N
114256328, which constitutes terminating
action to the repetitive requirements of this
AD.
This [EASA] AD is revised to clarify that
aeroplanes on which Airbus mod. 52980 has
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been embodied in production are not
required to accomplish the reidentification of
MLG retraction actuator P/N 114256002–055
which is mentioned in the accomplishment
instructions of Airbus SB A340–32–4222
Revision 03.
This [EASA] AD has been republished to
correct a typographical mistake of the
applicable Airbus SB number in the
Applicability (in the Note) and in the Reason
sections of this [EASA] AD.
You may examine the MCAI in the AD
docket on the Internet at https://
www.regulations.gov by searching for
and locating it in Docket No. FAA–
2014–0012.
Relevant Service Information
Airbus has issued the following
service bulletins.
• Airbus Mandatory Service Bulletin
A330–32–3173, Revision 05, dated
September 26, 2008.
• Airbus Mandatory Service Bulletin
A330–32–3180, Revision 03, dated
January 28, 2011.
• Airbus Mandatory Service Bulletin
A340–32–4212, Revision 05, dated
September 26, 2008.
• Airbus Mandatory Service Bulletin
A340–32–4222, Revision 03, dated
January 28, 2011.
The actions described in this service
information are intended to correct the
unsafe condition identified in the
MCAI.
FAA’s Determination and Requirements
of This Proposed AD
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
bilateral agreement with the State of
Design Authority, we have been notified
of the unsafe condition described in the
MCAI and service information
referenced above. We are proposing this
AD because we evaluated all pertinent
information and determined an unsafe
condition exists and is likely to exist or
develop on other products of the same
type design.
Differences Between This Proposed AD
and the MCAI or Service Information
EASA AD 2011–0178R1, dated March
6, 2012, corrected March 7, 2012 (for
Model A340–200 and –300 series
airplanes); and AD 2011–0179R1, dated
March 6, 2012 (for Model A330–200 and
–300 series airplanes); require
replacement of the retraction actuator
within 10 flight cycles if the findings of
the ultrasonic inspection of the
retraction actuator piston rod end are
between 75% and 90% FSH (full screen
height) and between 5 and 7 in time
base. However, paragraph (n) of this
proposed AD would require
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replacement of the retraction actuator
before further flight if the findings of the
ultrasonic inspection of the retraction
actuator piston rod end are higher than
75% and between 5 and 7 in time base.
EASA AD 2011–0178R1, dated March
6, 2012, corrected March 7, 2012 (for
Model A340–200 and –300 series
airplanes); and AD 2011–0179R1, dated
March 6, 2012 (for Model A330–200 and
–300 series airplanes); require
replacement of the retraction actuator
within 10 landings if the findings of the
one-time ultrasonic circumferential
inspection of the full-length chromed
part of the piston rod give an indication
between 75% and 90% FSH and
between 7 and 9.5 in time base.
However, paragraph (p)(2) of this
proposed AD would require
replacement of the retraction actuator
before further flight if inspection
findings are higher than 75% FSH and
between 7 and 9.5 in time base.
We have determined that, because of
the safety implications and
consequences associated with those
findings, the actuator must be replaced
before further flight. These differences
have been coordinated with EASA.
Costs of Compliance
We estimate that this proposed AD
affects 24 Model A330–200 and –300
series airplanes of U.S. registry. There
are no Model A340–200 and –300 series
airplanes of U.S. registry.
We estimate that it would take about
67 work-hours per product to comply
with the basic requirements of this
proposed AD. The average labor rate is
$85 per work-hour. Required parts
would cost about $56,000 per product (2
actuators). Based on these figures, we
estimate the cost of this proposed AD on
U.S. operators to be $1,480,680, or
$61,695 per product.
In addition, we estimate that any
necessary follow-on actions would take
about 38 work-hours and require parts
costing $56,000 (2 actuators), for a cost
of $59,230 per product. We have no way
of determining the number of aircraft
that might need these actions.
According to the manufacturer, some
of the costs of this proposed AD may be
covered under warranty, thereby
reducing the cost impact on affected
individuals. We do not control warranty
coverage for affected individuals. As a
result, we have included all costs in our
cost estimate.
Paperwork Reduction Act
A federal agency may not conduct or
sponsor, and a person is not required to
respond to, nor shall a person be subject
to penalty for failure to comply with a
collection of information subject to the
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requirements of the Paperwork
Reduction Act unless that collection of
information displays a current valid
OMB control number. The control
number for the collection of information
required by this proposed AD is 2120–
0056. The paperwork cost associated
with this proposed AD has been
detailed in the Costs of Compliance
section of this document and includes
time for reviewing instructions, as well
as completing and reviewing the
collection of information. Therefore, all
reporting associated with this proposed
AD is 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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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 proposed
regulation is within the scope of that
authority because it addresses an unsafe
condition that is likely to exist or
develop on products identified in this
rulemaking action.
Regulatory Findings
We determined that this proposed AD
would not have federalism implications
under Executive Order 13132. This
proposed AD would not have a
substantial direct effect on the States, on
the relationship between the national
Government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify this proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in
Alaska; and
4. Will not have a significant
economic impact, positive or negative,
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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.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing airworthiness directive (AD)
2004–16–01, Amendment 39–13757 (69
FR 46979, August 4, 2004), and adding
the following new AD:
■
Airbus: Docket No. FAA–2014–0012;
Directorate Identifier 2012–NM–007–AD.
(a) Comments Due Date
We must receive comments by March 24,
2014.
(b) Affected ADs
This AD supersedes AD 2004–16–01,
Amendment 39–13757 (69 FR 46979, August
4, 2004).
(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; and Model A340–211, –212, and
–213, –311, –312, and –313 airplanes;
certificated in any category; all manufacturer
serial numbers, except for those airplanes
that have had Airbus Modification 52980
incorporated in production on both main
landing gear (MLG) units, or airplanes that
have had Airbus Modification 54500
incorporated in production.
(d) Subject
Air Transport Association (ATA) of
America Code 32, Landing Gear.
(e) Reason
This AD was prompted by reports of the
piston rods for the MLG retraction actuators
rupturing during flight. We are issuing this
AD to prevent cracking of the piston rods for
the MLG retraction actuators, which could
result in rupture of a piston rod, non-damped
extension of the MLG, high loads on the fully
extended MLG, and consequent reduced
structural integrity of the MLG.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
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(g) Repetitive Detailed Inspections
At the applicable time specified in
paragraph (g)(1) or (g)(2) of this AD: Do a
detailed inspection for cracking of the visible
chromed area of the MLG retraction actuator
piston rods in the fully extended position, in
accordance with the Accomplishment
Instructions of Airbus Mandatory Service
Bulletin A330–32–3173, Revision 05, dated
September 26, 2008 (for Model A330 series
airplanes); or Airbus Mandatory Service
Bulletin A340–32–4212, Revision 05, dated
September 26, 2008 (for Model A340–200
and –300 series airplanes). Repeat the
inspection thereafter at intervals not to
exceed 8 days until the actions required by
paragraphs (j) and (o) of this AD are
accomplished.
(1) For MLG retraction actuator piston rods
that have not had a detailed inspection
accomplished as of the effective date of this
AD, as described in any applicable service
information specified in paragraph (h)(1) or
(h)(2) of this AD: At the applicable time
specified in paragraph (g)(1)(i) or (g)(1)(ii) of
this AD.
(i) For MLG retraction actuator piston rods
having part number (P/N) 114256309, or
P/N 114256321 issue 03: Do the inspection
within 60 days after the effective date of this
AD, or before the MLG retraction actuator has
been in service 36 months, whichever occurs
later.
(ii) For MLG retraction actuator piston rods
having P/N 114256326 issue 01, or P/N
114256321 issue 06: Do the inspection within
60 days after the effective date of this AD, or
before the MLG retraction actuator has been
in service 72 months, whichever occurs later.
(2) For MLG retraction actuator piston rods
having P/N 114256309, P/N 114256321 issue
03, P/N 114256326 issue 01, or P/N
114256321 issue 06, that have had a detailed
inspection accomplished as of the effective
date of this AD, as described in the
applicable service information specified in
paragraph (h)(1) or (h)(2) of this AD: Inspect
within 8 days after the effective date of this
AD.
(h) Service Information To Determine
Airplane Configuration for Paragraph (g) of
This AD
(1) For Model A330 airplanes:
(i) Airbus Mandatory Service Bulletin
A330–32–3173, Revision 01, dated June 16,
2004;
(ii) Airbus Mandatory Service Bulletin
A330–32–3173, Revision 02, dated May 11,
2005;
(iii) Airbus Mandatory Service Bulletin
A330–32–3173, Revision 03, dated March 13,
2006;
(iv) Airbus Mandatory Service Bulletin
A330–32–3173, Revision 04, dated June 12,
2006; or
(v) Airbus Mandatory Service Bulletin
A330–32–3173, Revision 05, dated
September 26, 2008.
(2) For Model A340–200 and –300 series
airplanes:
(i) Airbus Mandatory Service Bulletin
A340–32–4212, Revision 01, dated June 16,
2004;
(ii) Airbus Mandatory Service Bulletin
A340–32–4212, Revision 02, dated May 11,
2005;
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(iii) Airbus Mandatory Service Bulletin
A340–32–4212, Revision 03, dated March 13,
2006;
(iv) Airbus Mandatory Service Bulletin
A340–32–4212, Revision 04, dated June 12,
2006; or
(v) Airbus Mandatory Service Bulletin
A340–32–4212, Revision 05, dated
September 26, 2008.
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(i) Corrective Action for Cracking
If any cracking is found during any
inspection required by paragraph (g) of this
AD: Before further flight, replace the MLG
retraction actuator with a new or serviceable
part, in accordance with the
Accomplishment Instructions of Airbus
Mandatory Service Bulletin A330–32–3173,
Revision 05, dated September 26, 2008 (for
Model A330 series airplanes); or Airbus
Mandatory Service Bulletin A340–32–4212,
Revision 05, dated September 26, 2008 (for
Model A340–200 and –300 series airplanes).
(j) Repetitive Fluid Draining and Vent Hole
Sealing
At the applicable time specified in
paragraph (j)(1) or (j)(2) of this AD: Drain any
fluid from the retraction actuator piston rod
internal volume and seal the vent hole, in
accordance with the Accomplishment
Instructions of Airbus Mandatory Service
Bulletin A330–32–3173, Revision 05, dated
September 26, 2008 (for Model A330 series
airplanes); or Airbus Mandatory Service
Bulletin A340–32–4212, Revision 05, dated
September 26, 2008 (for Model A340–200
and –300 series airplanes). Repeat the
draining and sealing thereafter at intervals
not to exceed 1,000 flight cycles or 24
months, whichever occurs first.
(1) For MLG retraction actuator piston rods
that have not been inspected and have not
had the fluid drained as of the effective date
of this AD, as described in the applicable
service information specified in paragraph
(k)(1) or (k)(2) of this AD: At the applicable
time specified in paragraph (j)(1)(i) or
(j)(1)(ii) of this AD.
(i) For MLG retraction actuator piston rods
having P/N 114256309, or P/N 114256321
issue 03: Do the draining and sealing within
60 days after the effective date of this AD or
before the MLG retraction actuator has been
in service 36 months, whichever occurs later.
(ii) For MLG retraction actuator piston rods
having P/N 114256326 issue 01, or P/N
114256321 issue 06: Do the draining and
sealing within 60 days after the effective date
of this AD or before the MLG retraction
actuator has been in service 72 months,
whichever occurs later.
(2) For MLG retraction actuator piston rods
having P/N 114256309, P/N 114256321 issue
03, P/N 114256326 issue 01, or P/N
114256321 issue 06, that have been inspected
and the fluid drained as of the effective date
of this AD, as described in the applicable
service information specified in paragraph
(k)(1) or (k)(2) of this AD: Do the draining
and sealing at the later of the times specified
in paragraphs (j)(2)(i) and (j)(2)(ii) of this AD.
(i) Within 1,000 flight cycles or 24 months,
whichever occurs first, from the last
inspection and fluid drainage accomplished
in accordance with the actions required in
paragraph (j) of this AD.
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(ii) Within 60 days after the effective date
of this AD.
(k) Service Information To Determine
Configuration for Paragraph (j) of This AD
(1) For Model A330 airplanes:
(i) Airbus Mandatory Service Bulletin
A330–32–3173, Revision 02, dated May 11,
2005;
(ii) Airbus Mandatory Service Bulletin
A330–32–3173, Revision 03, dated March 13,
2006;
(iii) Airbus Mandatory Service Bulletin
A330–32–3173, Revision 04, dated June 12,
2006; or
(iv) Airbus Mandatory Service Bulletin
A330–32–3173, Revision 05, dated
September 26, 2008.
(2) For Model A340–200 and –300 series
airplanes:
(i) Airbus Mandatory Service Bulletin
A340–32–4212, Revision 02, dated May 11,
2005;
(ii) Airbus Mandatory Service Bulletin
A340–32–4212, Revision 03, dated March 13,
2006;
(iii) Airbus Mandatory Service Bulletin
A340–32–4212, Revision 04, dated June 12,
2006; or
(iv) Airbus Mandatory Service Bulletin
A340–32–4212, Revision 05, dated
September 26, 2008.
(l) Ultrasonic Inspection
At the applicable time specified in
paragraph (l)(1) or (l)(2) of this AD: Do an
ultrasonic longitudinal inspection for
cracking of the retraction actuator piston rod
end, in accordance with the Accomplishment
Instructions of Airbus Mandatory Service
Bulletin A330–32–3173, Revision 05, dated
September 26, 2008 (for Model A330 series
airplanes); or Airbus Mandatory Service
Bulletin A340–32–4212, Revision 05, dated
September 26, 2008 (for Model A340–200
and -300 series airplanes).
(1) For MLG retraction actuator piston rods
that have not had a non-destructive test
(NDT) inspection as of the effective date of
this AD, as described in the applicable
service information specified in paragraph
(m)(1) or (m)(2) of this AD: At the applicable
time specified in paragraph (l)(1)(i) or
(l)(1)(ii) of this AD.
(i) For MLG retraction actuator piston rods
having P/N 114256309, or P/N 114256321
issue 03: Do the inspection within 60 days
after the effective date of this AD, or before
the MLG retraction actuator has been in
service 36 months, whichever occurs later.
(ii) For MLG retraction actuator piston rods
having P/N 114256326 issue 01, or P/N
114256321 issue 06: Do the inspection within
60 days after the effective date of this AD, or
before the MLG retraction actuator has been
in service 72 months, whichever occurs later.
(2) For MLG retraction actuator piston rods
having P/N 114256309, P/N 114256321 issue
03, P/N 114256326 issue 01, or P/N
114256321 issue 06, that have had an NDT
inspection as of the effective date of this AD,
as described in the applicable service
information specified in paragraph (m)(1) or
(m)(2) of this AD: Do the inspection at the
later of the times specified in paragraphs
(l)(2)(i) and (l)(2)(ii) of this AD.
PO 00000
Frm 00004
Fmt 4702
Sfmt 4702
7101
(i) Within 1,400 flight hours, 250 flight
cycles, or 4 months, whichever occurs first
after the date of the last ultrasonic
longitudinal inspection performed as
described in the applicable service
information specified in paragraph (m)(1) or
(m)(2) of this AD.
(ii) Within 60 days after the effective date
of this AD.
(m) Service Information To Determine
Configuration for Paragraph (l) of This AD
(1) For Model A330 airplanes:
(i) Airbus Mandatory Service Bulletin
A330–32–3173, dated December 17, 2003;
(ii) Airbus Mandatory Service Bulletin
A330–32–3173, Revision 01, dated June 16,
2004;
(iii) Airbus Mandatory Service Bulletin
A330–32–3173, Revision 02, dated May 11,
2005;
(iv) Airbus Mandatory Service Bulletin
A330–32–3173, Revision 03, dated March 13,
2006;
(v) Airbus Mandatory Service Bulletin
A330–32–3173, Revision 04, dated June 12,
2006; or
(vi) Airbus Mandatory Service Bulletin
A330–32–3173, Revision 05, dated
September 26, 2008.
(2) For Model A340–200 and –300 series
airplanes:
(i) Airbus Mandatory Service Bulletin
A340–32–4212, dated December 17, 2003;
(ii) Airbus Mandatory Service Bulletin
A340–32–4212, Revision 01, dated June 16,
2004;
(iii) Airbus Mandatory Service Bulletin
A340–32–4212, Revision 02, dated May 11,
2005;
(iv) Airbus Mandatory Service Bulletin
A340–32–4212, Revision 03, dated March 13,
2006;
(v) Airbus Mandatory Service Bulletin
A340–32–4212, Revision 04, dated June 12,
2006; or
(vi) Airbus Mandatory Service Bulletin
A340–32–4212, Revision 05, dated
September 26, 2008.
(n) Corrective Action for Ultrasonic
Inspection; Repetitive Interval
(1) If the finding of the inspection required
by paragraph (l) of this AD gives an
indication of 75% or higher of full screen
height (FSH) and between 5 and 7 in time
base: Before further flight, replace the MLG
retraction actuator with a new or serviceable
part, in accordance with the
Accomplishment Instructions of Airbus
Mandatory Service Bulletin A330–32–3173,
Revision 05, dated September 26, 2008 (for
Model A330 series airplanes); or Airbus
Mandatory Service Bulletin A340–32–4212,
Revision 05, dated September 26, 2008 (for
Model A340–200 and –300 series airplanes).
(2) If the finding of the inspection required
by paragraph (l) of this AD gives an
indication of less than 75% FSH and between
5 and 7 in time base: Repeat the inspection
required by paragraph (l) of this AD
thereafter at intervals not to exceed 1,400
flight hours, 250 flight cycles, or 4 months,
whichever occurs first.
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Federal Register / Vol. 79, No. 25 / Thursday, February 6, 2014 / Proposed Rules
tkelley on DSK3SPTVN1PROD with PROPOSALS
(o) One-Time Ultrasonic Inspections of the
Full-Length of the Piston Rod
At the applicable time specified in
paragraph (o)(1) or (o)(2) of this AD: Do a
full-length ultrasonic longitudinal and a fulllength circumferential inspection of the
chromium-plated area of the piston rod for
cracking, in accordance with the
Accomplishment Instructions of Airbus
Mandatory Service Bulletin A330–32–3173,
Revision 05, dated September 26, 2008 (for
Model A330 series airplanes); or Airbus
Mandatory Service Bulletin A340–32–4212,
Revision 05, dated September 26, 2008 (for
Model A340–200 and –300 series airplanes).
(1) For MLG retraction actuator piston rods
having P/N 114256309, or P/N 114256321
issue 03: Inspect at the later of the times
specified in paragraphs (o)(1)(i) and (o)(1)(ii)
of this AD.
(i) Within 1,750 flight hours, 315 flight
cycles, or 5 months after the effective date of
this AD, whichever occurs first.
(ii) Before the MLG retraction actuator has
been in service 36 months.
(2) For MLG retraction actuator piston rods
having P/N 114256326 issue 01, or P/N
114256321 issue 06: Inspect at the later of the
times specified in paragraphs (o)(2)(i) and
(o)(2)(ii) of this AD.
(i) Within 1,750 flight hours, 315 flight
cycles, or 5 months after the effective date of
this AD, whichever occurs first.
(ii) Before the MLG retraction actuator has
been in service 72 months.
(p) Corrective Action for One-time
Ultrasonic Inspections of the Full-Length of
the Piston Rod
(1) If the finding of the full-length
ultrasonic longitudinal inspection required
by paragraph (o) of this AD gives an
indication of 75% or higher FSH and
between 5 and 7 in time base: Before further
flight, replace the MLG retraction actuator
with a new or serviceable part, in accordance
with the Accomplishment Instructions of
Airbus Mandatory Service Bulletin A330–32–
3173, Revision 05, dated September 26, 2008
(for Model A330 series airplanes); or Airbus
Mandatory Service Bulletin A340–32–4212,
Revision 05, dated September 26, 2008 (for
Model A340–200 and –300 series airplanes).
(2) If the finding of the full-length
ultrasonic circumferential inspection
required by paragraph (o) of this AD gives an
indication of 75% or higher FSH and
between 7 and 9.5 in time base: Before
further flight, replace the MLG retraction
actuator with a new or serviceable part, in
accordance with the Accomplishment
Instructions of Airbus Mandatory Service
Bulletin A330–32–3173, Revision 05, dated
September 26, 2008 (for Model A330 series
airplanes); or Airbus Mandatory Service
Bulletin A340–32–4212, Revision 05, dated
September 26, 2008 (for Model A340–200
and –300 series airplanes).
(q) Reporting Requirement
Report the results (regardless of findings)
of the detailed inspection, the fluid drain/
seal of the retraction actuator piston rod, the
one-time ultrasonic longitudinal inspection
of the upper end of the piston rod, and the
one-time full-length ultrasonic
VerDate Mar<15>2010
16:49 Feb 05, 2014
Jkt 232001
circumferential inspection required by this
AD, and the findings of the actions required
by this AD that cause an actuator to be
replaced, in accordance with the
Accomplishment Instructions of Airbus
Mandatory Service Bulletin A330–32–3173,
Revision 05, dated September 26, 2008 (for
Model A330 series airplanes); or Airbus
Mandatory Service Bulletin A340–32–4212,
Revision 05, dated September 26, 2008 (for
Model A340–200 and –300 series airplanes).
Submit the report to Airbus Customer
Services Directorate, Attention: SEDCC1
Technical Data and Documentation Services
fax: (+33) 5 61 93 28 06; email: sb.reporting@
airbus.com, or via your resident customer
support office. Submit the report at the
applicable time specified in paragraph (q)(1)
or (q)(2) of this AD.
(1) If the actions requiring reporting, as
specified in paragraph (q) of this AD, are
done on or after the effective date of this AD:
Submit the report within 90 days after those
actions have been done.
(2) If the actions requiring reporting, as
specified in paragraph (q) of this AD, were
done before the effective date of this AD:
Submit the report within 90 days after the
effective date of this AD.
(r) Terminating Actions for Repetitive
Detailed Inspections
Accomplishment of the initial drainage of
the fluid from the piston, as required by
paragraph (j) of this AD, the full-length
ultrasonic longitudinal inspection, and the
full-length circumferential inspection, as
required by paragraph (o) of this AD,
constitutes terminating action for the
repetitive detailed inspections required by
paragraph (g) of this AD, provided no crack
is found during the inspections.
(s) Terminating Modification
Within 48 months after the effective date
of this AD: Modify the left-hand and righthand MLG retraction actuators, in accordance
with the Accomplishment Instructions of
Airbus Mandatory Service Bulletin A330–32–
3180, Revision 03, dated January 28, 2011
(for Model A330 series airplanes); or Airbus
Mandatory Service Bulletin A340–32–4222,
Revision 03, dated January 28, 2011 (for
Model A340–200 and –300 series airplanes).
Accomplishment of the modification
required by this paragraph terminates the
repetitive requirements of this AD for the
MLG retraction actuator that is modified.
(t) Exception to Re-Identification of the MLG
Retraction Actuator
The re-identification of the MLG retraction
actuator having P/N 114256002–055, which
is described in Airbus Mandatory Service
Bulletin A330–32–3180, Revision 03, dated
January 28, 2011 (for Model A330 series
airplanes); or Airbus Mandatory Service
Bulletin A340–32–4222, Revision 03, dated
January 28, 2011 (for Model A340–200 and
–300 series airplanes); is not required on
airplanes that have Airbus modification
52980 embodied in production.
(u) Optional Parts Installation
Installation of retraction actuator piston
rod having P/N 114256323, in accordance
with the Accomplishment Instructions of
PO 00000
Frm 00005
Fmt 4702
Sfmt 4702
Airbus Service Bulletin A330–32–3174,
Revision 02, dated September 16, 2005 (for
Model A330 series airplanes); or Airbus
Service Bulletin A340–32–4213, Revision 01,
dated September 16, 2005 (for Model A340–
200 and –300 series airplanes); constitutes an
acceptable method of compliance with the
requirements of paragraphs (g), (j), (l), and (o)
of this AD for that installed MLG retraction
actuator.
(v) Parts Installation Limitation
As of the effective date of this AD, no
person may install a piston rod having P/N
114256309, or 114256321, or 114256326
issue 01 for the MLG retraction actuator on
any airplane, unless the part meets the
applicable requirements of this AD at the
specified times and intervals.
(w) Credit for Previous Actions
(1) This paragraph provides credit for the
actions required by paragraphs (g), (j), (l), and
(o) of this AD, if those actions were
performed before the effective date of this AD
using the service information specified in
paragraphs (w)(1)(i) through (w)(1)(ix) of this
AD.
(i) Airbus Mandatory Service Bulletin
A330–32–3173, dated December 17, 2003;
(for Model A330 series airplanes).
(ii) Airbus Mandatory Service Bulletin
A330–32–3173, Revision 01, dated June 16,
2004 (for Model A330 series airplanes).
(iii) Airbus Mandatory Service Bulletin
A330–32–3173, Revision 02, dated May 11,
2005 (for Model A330 series airplanes).
(iv) Airbus Mandatory Service Bulletin
A330–32–3173, Revision 03, dated March 13,
2006 (for Model A330 series airplanes).
(v) Airbus Mandatory Service Bulletin
A330–32–3173, Revision 04, dated June 12,
2006 (for Model A330 series airplanes).
(vi) Airbus Mandatory Service Bulletin
A340–32–4212, dated December 17, 2003 (for
Model A340–200 and –300 series airplanes).
(vii) Airbus Mandatory Service Bulletin
A340–32–4212, Revision 01, dated June 16,
2004 (for Model A340–200 and –300 series
airplanes).
(viii) Airbus Mandatory Service Bulletin
A340–32–4212, Revision 02, dated May 11,
2005; Revision 03, dated March 13, 2006 (for
Model A340–200 and –300 series airplanes).
(ix) Airbus Mandatory Service Bulletin
A340–32–4212, Revision 04, dated June 12,
2006 (for Model A340–200 and –300 series
airplanes).
(2) This paragraph provides credit for the
actions required by paragraph (s) of this AD,
if the modification was done before the
effective date of this AD using the service
bulletins specified in paragraphs (u)(2)(i)
through (u)(2)(iv) of this AD.
(i) Airbus Service Bulletin A330–32–3180,
Revision 01, dated August 15, 2005 for Model
A330 series airplanes).
(ii) Airbus Mandatory Service Bulletin
A330–32–3180, Revision 02, dated April 4,
2007 (for Model A330 series airplanes).
(iii) Airbus Service Bulletin A340–32–
4222, Revision 01, dated August 15, 2005 (for
Model A340–200 and –300 series airplanes).
(iv) Airbus Mandatory Service Bulletin
A340–32–4222, Revision 02, dated April 4,
2007 (for Model A340–200 and –300 series
airplanes).
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Federal Register / Vol. 79, No. 25 / Thursday, February 6, 2014 / Proposed Rules
(3) This paragraph provides credit for the
actions required by paragraph (s) of this AD,
if the modification was done before the
effective date of this AD using Airbus Service
Bulletin A340–32–4222, dated September 20,
2004; and re-identified using Airbus Service
Bulletin A340–32–4222, Revision 01, dated
August 15, 2005, or Airbus Mandatory
Service Bulletin A340–32–4222, Revision 02,
dated April 4, 2007.
tkelley on DSK3SPTVN1PROD with PROPOSALS
(x) 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
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: 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, or the DAH with a
State of Design Authority’s design
organization approval). For a repair method
to be approved, the repair approval must
specifically refer to this AD. 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.
VerDate Mar<15>2010
16:49 Feb 05, 2014
Jkt 232001
(y) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) European
Aviation Safety Agency Airworthiness
Directive 2011–0178R1, dated March 6, 2012
(corrected March 7, 2012); and 2011–0179R1,
dated March 6, 2012; for related information.
These MCAIs may be found in the AD docket
on the Internet at https://www.regulations.gov
by searching for and locating Docket No.
FAA–2014–0012.
(2) For 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. 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.
Issued in Renton, Washington, on January
29, 2014.
John P. Piccola,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2014–02522 Filed 2–5–14; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
[Docket No. FAA–2014–0053; Directorate
Identifier 2013–NM–174–AD]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for certain
The Boeing Company Model 777
airplanes. This proposed AD was
prompted by reports of corroded,
migrated, or broken spring pins of the
girt bar floor fitting; in one case the
broken pins prevented a door escape
slide from deploying during a
maintenance test. This proposed AD
would require replacing the existing
spring pins at each passenger entry door
at both girt bar floor fittings with new
spring pins. We are proposing this AD
to prevent broken or migrated spring
pins of the girt bar floor fittings, which
could result in improper deployment of
the escape slide/raft and consequent
delay and injury during evacuation of
passengers and crew from the cabin in
the event of an emergency.
SUMMARY:
Frm 00006
Fmt 4702
We must receive comments on
this proposed AD by March 24, 2014.
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: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this proposed AD, 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, Washington. For information on
the availability of this material at the
FAA, call 425–227–1221.
DATES:
Examining the AD Docket
14 CFR Part 39
PO 00000
7103
Sfmt 4702
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2014–
0053; 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 proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Office
(phone: 800–647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT: Ana
Martinez Hueto, Aerospace Engineer,
Cabin Safety and Environmental
Systems Branch, ANM–150S, FAA,
Seattle Aircraft Certification Office
(ACO), 1601 Lind Avenue SW., Renton,
WA 98057–3356; phone: 425–917–6592;
fax: 425–917–6591; email:
ana.m.hueto@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposal. Send your comments to
an address listed under the ADDRESSES
section. Include ‘‘Docket No. FAA–
E:\FR\FM\06FEP1.SGM
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]]>Agencies
[Federal Register Volume 79, Number 25 (Thursday, February 6, 2014)]
[Proposed Rules]
[Pages 7098-7103]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-02522]
========================================================================
Proposed Rules
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.
========================================================================
Federal Register / Vol. 79, No. 25 / Thursday, February 6, 2014 /
Proposed Rules
[[Page 7098]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2014-0012; Directorate Identifier 2012-NM-007-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to supersede Airworthiness Directive (AD) 2004-16-
01, that applies to certain Airbus Model A330-200 and -300, and Model
A340-200 and -300, series airplanes. AD 2004-16-01 currently requires
repetitive inspections for cracking of the chromed area of the left and
right piston rods for the main landing gear (MLG) retraction actuators,
and related investigative and corrective actions if necessary. Since we
issued AD 2004-16-01, we have determined that the presence of water in
the internal volume of the piston rod can consequently lead to
propagation of longitudinal cracking in the body of the piston rod. We
have also determined through sampling that certain retraction actuator
piston rods of the MLG need to be replaced. This proposed AD would
require repetitive draining of any fluid from the retraction actuator
piston rod internal volume and sealing of the vent hole; repetitive
ultrasonic inspections of the upper end of the piston rods, and
corrective actions if necessary; a one-time ultrasonic inspection
(longitudinal and circumferential) of the full-length of the piston
rod, and corrective actions if necessary; and a terminating
modification of the left-hand and right-hand MLG retraction actuators.
We are proposing this AD to prevent cracking of the piston rods for the
MLG retraction actuators, which could result in rupture of a piston
rod, non-damped extension of the MLG, high loads on the fully extended
MLG, and consequent reduced structural integrity of the MLG.
DATES: We must receive comments on this proposed AD by March 24, 2014.
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 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 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.
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-2014-
0012; 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 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, WA 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-2014-0012;
Directorate Identifier 2012-NM-007-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
On July 23, 2004, we issued AD 2004-16-01, Amendment 39-13757 (69
FR 46979, August 4, 2004). AD 2004-16-01 requires actions intended to
address an unsafe condition on the products listed above.
Since we issued AD 2004-16-01, the European Aviation Safety Agency
(EASA), which is the Technical Agent for the Member States of the
European Community, has issued EASA AD 2011-0178R1, dated March 6,
2012, corrected March 7, 2012 (for Model A340-200 and -300 series
airplanes); and EASA AD 2011-0179R1, dated March 6, 2012 (for Model
A330-200 and -300 series airplanes) (both referred to after this as the
Mandatory Continuing Airworthiness Information, or ``the MCAI''); to
correct an unsafe condition for the specified products. EASA AD 2011-
0178R1, dated March 6, 2012, corrected March 7, 2012, states:
During an approach phase, the flight crew of an A330 aeroplane
had to perform a free-fall extension of the left-hand (LH) MLG.
Rupture of the LH MLG retraction actuator piston rod was found
near the rod attachment point. The inspection revealed at the
location of the rupture the presence of corrosion resulting from
incorrect application of the anticorrosion protection, and
circumferential cracks resulting from normal operational loading
effects.
Since the above rupture, new cases of crack propagation along
the length of the piston rod occurred. These ruptures led to a non-
damped extension of the landing gear. Fully
[[Page 7099]]
extended, the landing gear assembly was submitted to high loads
jeopardizing its structural integrity.
This condition, if not detected and corrected, could lead to MLG
failure during landing or roll-out and consequent damage to the
aeroplane and injury to occupants.
DGAC France issued AD F-2005-098 (EASA approval 2005-5887) [and
AD F-2005-099 (EASA approval 2005-5888)] to address this unsafe
condition [the FAA issued AD 2004-16-01, Amendment 39-13757 (69 FR
46979, August 4, 2004)]. Since that [DGAC France] AD was issued, the
results of extensive investigation determined that the presence of
water in the internal volume of the piston rod can lead to the
formation of ice which represents a potential source of high
magnitude tensile hoop stresses in the material of the rod, leading
to propagation of longitudinal crack in the body of the piston rod.
Prompted by these findings, EASA issued AD 2006-0301, partially
retaining the requirements of DGAC France AD F-2005-099, which was
superseded, and to revise the inspection requirements as follows:
a. Extend the repetitive inspections interval for the removal of
fluid from the internal volume of the piston rod using flight cycles
in lieu of flight hours as this better represents the mechanism for
the accumulation of water within the piston rod.
b. Remove the preliminary visual inspection from the ultrasonic
longitudinal inspection of the upper end of the piston rod.
c. Add a new one-time ultrasonic longitudinal and
circumferential inspection of the full piston rod length to
eliminate any parts that exhibit severe corrosion along the internal
length of the piston rod.
d. Require installation of new design hollow piston rod Part
Number (P/N) 114256328 (Airbus mod. 52980--SB A340-32-4222 Revision
01) without a vent hole, thus eliminating moisture ingress as the
terminating action.
EASA AD 2006-0301 was later revised:
--at revision 01, to correct a number of typographical errors and to
add reference to Airbus SB A340-32-4212 Revision 04, and
--at revision 02 to extend the inspections threshold from 3 to 6
years in service usage for retraction actuator piston rod P/N
114256321 issue 06 which was re-identified to P/N 114256326 issue 01
in accordance with the instructions of Airbus SB A340-32-4260.
More recently, the sampling of piston rod P/N 114256326 issue 1
and P/N 114256321 issue 06 have confirmed the need to replace all
retraction actuator piston rods with a piston rod P/N114256328.
For the reasons described above, this [EASA] AD at original
issue retained the requirements of EASA AD 2006-0301R2 (https://ad.easa.europa.eu/blob/easa_ad_2006_0301_R2_superseded.pdf/AD_2006-0301R2_1), which is superseded, and required the replacement
of all retraction actuator piston rods with a piston rod P/N
114256328, which constitutes terminating action to the repetitive
requirements of this AD.
This [EASA] AD is revised to clarify that aeroplanes on which
Airbus mod. 52980 has been embodied in production are not required
to accomplish the reidentification of MLG retraction actuator P/N
114256002-055 which is mentioned in the accomplishment instructions
of Airbus SB A340-32-4222 Revision 03.
This [EASA] AD has been republished to correct a typographical
mistake of the applicable Airbus SB number in the Applicability (in
the Note) and in the Reason sections of this [EASA] AD.
You may examine the MCAI in the AD docket on the Internet at https://www.regulations.gov by searching for and locating it in Docket No. FAA-
2014-0012.
Relevant Service Information
Airbus has issued the following service bulletins.
Airbus Mandatory Service Bulletin A330-32-3173, Revision
05, dated September 26, 2008.
Airbus Mandatory Service Bulletin A330-32-3180, Revision
03, dated January 28, 2011.
Airbus Mandatory Service Bulletin A340-32-4212, Revision
05, dated September 26, 2008.
Airbus Mandatory Service Bulletin A340-32-4222, Revision
03, dated January 28, 2011.
The actions described in this service information are intended to
correct the unsafe condition identified in the MCAI.
FAA's Determination and Requirements of This Proposed AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all pertinent information and determined an unsafe condition
exists and is likely to exist or develop on other products of the same
type design.
Differences Between This Proposed AD and the MCAI or Service
Information
EASA AD 2011-0178R1, dated March 6, 2012, corrected March 7, 2012
(for Model A340-200 and -300 series airplanes); and AD 2011-0179R1,
dated March 6, 2012 (for Model A330-200 and -300 series airplanes);
require replacement of the retraction actuator within 10 flight cycles
if the findings of the ultrasonic inspection of the retraction actuator
piston rod end are between 75% and 90% FSH (full screen height) and
between 5 and 7 in time base. However, paragraph (n) of this proposed
AD would require replacement of the retraction actuator before further
flight if the findings of the ultrasonic inspection of the retraction
actuator piston rod end are higher than 75% and between 5 and 7 in time
base.
EASA AD 2011-0178R1, dated March 6, 2012, corrected March 7, 2012
(for Model A340-200 and -300 series airplanes); and AD 2011-0179R1,
dated March 6, 2012 (for Model A330-200 and -300 series airplanes);
require replacement of the retraction actuator within 10 landings if
the findings of the one-time ultrasonic circumferential inspection of
the full-length chromed part of the piston rod give an indication
between 75% and 90% FSH and between 7 and 9.5 in time base. However,
paragraph (p)(2) of this proposed AD would require replacement of the
retraction actuator before further flight if inspection findings are
higher than 75% FSH and between 7 and 9.5 in time base.
We have determined that, because of the safety implications and
consequences associated with those findings, the actuator must be
replaced before further flight. These differences have been coordinated
with EASA.
Costs of Compliance
We estimate that this proposed AD affects 24 Model A330-200 and -
300 series airplanes of U.S. registry. There are no Model A340-200 and
-300 series airplanes of U.S. registry.
We estimate that it would take about 67 work-hours per product to
comply with the basic requirements of this proposed AD. The average
labor rate is $85 per work-hour. Required parts would cost about
$56,000 per product (2 actuators). Based on these figures, we estimate
the cost of this proposed AD on U.S. operators to be $1,480,680, or
$61,695 per product.
In addition, we estimate that any necessary follow-on actions would
take about 38 work-hours and require parts costing $56,000 (2
actuators), for a cost of $59,230 per product. We have no way of
determining the number of aircraft that might need these actions.
According to the manufacturer, some of the costs of this proposed
AD may be covered under warranty, thereby reducing the cost impact on
affected individuals. We do not control warranty coverage for affected
individuals. As a result, we have included all costs in our cost
estimate.
Paperwork Reduction Act
A federal agency may not conduct or sponsor, and a person is not
required to respond to, nor shall a person be subject to penalty for
failure to comply with a collection of information subject to the
[[Page 7100]]
requirements of the Paperwork Reduction Act unless that collection of
information displays a current valid OMB control number. The control
number for the collection of information required by this proposed AD
is 2120-0056. The paperwork cost associated with this proposed AD has
been detailed in the Costs of Compliance section of this document and
includes time for reviewing instructions, as well as completing and
reviewing the collection of information. Therefore, all reporting
associated with this proposed AD is 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.
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 proposed regulation is
within the scope of that authority because it addresses an unsafe
condition that is likely to exist or develop on products identified in
this rulemaking action.
Regulatory Findings
We determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify this proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979);
3. Will not 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.
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
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)
2004-16-01, Amendment 39-13757 (69 FR 46979, August 4, 2004), and
adding the following new AD:
Airbus: Docket No. FAA-2014-0012; Directorate Identifier 2012-NM-
007-AD.
(a) Comments Due Date
We must receive comments by March 24, 2014.
(b) Affected ADs
This AD supersedes AD 2004-16-01, Amendment 39-13757 (69 FR
46979, August 4, 2004).
(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; and Model A340-211, -212, and -213, -311, -312, and -313
airplanes; certificated in any category; all manufacturer serial
numbers, except for those airplanes that have had Airbus
Modification 52980 incorporated in production on both main landing
gear (MLG) units, or airplanes that have had Airbus Modification
54500 incorporated in production.
(d) Subject
Air Transport Association (ATA) of America Code 32, Landing
Gear.
(e) Reason
This AD was prompted by reports of the piston rods for the MLG
retraction actuators rupturing during flight. We are issuing this AD
to prevent cracking of the piston rods for the MLG retraction
actuators, which could result in rupture of a piston rod, non-damped
extension of the MLG, high loads on the fully extended MLG, and
consequent reduced structural integrity of the MLG.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Repetitive Detailed Inspections
At the applicable time specified in paragraph (g)(1) or (g)(2)
of this AD: Do a detailed inspection for cracking of the visible
chromed area of the MLG retraction actuator piston rods in the fully
extended position, in accordance with the Accomplishment
Instructions of Airbus Mandatory Service Bulletin A330-32-3173,
Revision 05, dated September 26, 2008 (for Model A330 series
airplanes); or Airbus Mandatory Service Bulletin A340-32-4212,
Revision 05, dated September 26, 2008 (for Model A340-200 and -300
series airplanes). Repeat the inspection thereafter at intervals not
to exceed 8 days until the actions required by paragraphs (j) and
(o) of this AD are accomplished.
(1) For MLG retraction actuator piston rods that have not had a
detailed inspection accomplished as of the effective date of this
AD, as described in any applicable service information specified in
paragraph (h)(1) or (h)(2) of this AD: At the applicable time
specified in paragraph (g)(1)(i) or (g)(1)(ii) of this AD.
(i) For MLG retraction actuator piston rods having part number
(P/N) 114256309, or P/N 114256321 issue 03: Do the inspection within
60 days after the effective date of this AD, or before the MLG
retraction actuator has been in service 36 months, whichever occurs
later.
(ii) For MLG retraction actuator piston rods having P/N
114256326 issue 01, or P/N 114256321 issue 06: Do the inspection
within 60 days after the effective date of this AD, or before the
MLG retraction actuator has been in service 72 months, whichever
occurs later.
(2) For MLG retraction actuator piston rods having P/N
114256309, P/N 114256321 issue 03, P/N 114256326 issue 01, or P/N
114256321 issue 06, that have had a detailed inspection accomplished
as of the effective date of this AD, as described in the applicable
service information specified in paragraph (h)(1) or (h)(2) of this
AD: Inspect within 8 days after the effective date of this AD.
(h) Service Information To Determine Airplane Configuration for
Paragraph (g) of This AD
(1) For Model A330 airplanes:
(i) Airbus Mandatory Service Bulletin A330-32-3173, Revision 01,
dated June 16, 2004;
(ii) Airbus Mandatory Service Bulletin A330-32-3173, Revision
02, dated May 11, 2005;
(iii) Airbus Mandatory Service Bulletin A330-32-3173, Revision
03, dated March 13, 2006;
(iv) Airbus Mandatory Service Bulletin A330-32-3173, Revision
04, dated June 12, 2006; or
(v) Airbus Mandatory Service Bulletin A330-32-3173, Revision 05,
dated September 26, 2008.
(2) For Model A340-200 and -300 series airplanes:
(i) Airbus Mandatory Service Bulletin A340-32-4212, Revision 01,
dated June 16, 2004;
(ii) Airbus Mandatory Service Bulletin A340-32-4212, Revision
02, dated May 11, 2005;
[[Page 7101]]
(iii) Airbus Mandatory Service Bulletin A340-32-4212, Revision
03, dated March 13, 2006;
(iv) Airbus Mandatory Service Bulletin A340-32-4212, Revision
04, dated June 12, 2006; or
(v) Airbus Mandatory Service Bulletin A340-32-4212, Revision 05,
dated September 26, 2008.
(i) Corrective Action for Cracking
If any cracking is found during any inspection required by
paragraph (g) of this AD: Before further flight, replace the MLG
retraction actuator with a new or serviceable part, in accordance
with the Accomplishment Instructions of Airbus Mandatory Service
Bulletin A330-32-3173, Revision 05, dated September 26, 2008 (for
Model A330 series airplanes); or Airbus Mandatory Service Bulletin
A340-32-4212, Revision 05, dated September 26, 2008 (for Model A340-
200 and -300 series airplanes).
(j) Repetitive Fluid Draining and Vent Hole Sealing
At the applicable time specified in paragraph (j)(1) or (j)(2)
of this AD: Drain any fluid from the retraction actuator piston rod
internal volume and seal the vent hole, in accordance with the
Accomplishment Instructions of Airbus Mandatory Service Bulletin
A330-32-3173, Revision 05, dated September 26, 2008 (for Model A330
series airplanes); or Airbus Mandatory Service Bulletin A340-32-
4212, Revision 05, dated September 26, 2008 (for Model A340-200 and
-300 series airplanes). Repeat the draining and sealing thereafter
at intervals not to exceed 1,000 flight cycles or 24 months,
whichever occurs first.
(1) For MLG retraction actuator piston rods that have not been
inspected and have not had the fluid drained as of the effective
date of this AD, as described in the applicable service information
specified in paragraph (k)(1) or (k)(2) of this AD: At the
applicable time specified in paragraph (j)(1)(i) or (j)(1)(ii) of
this AD.
(i) For MLG retraction actuator piston rods having P/N
114256309, or P/N 114256321 issue 03: Do the draining and sealing
within 60 days after the effective date of this AD or before the MLG
retraction actuator has been in service 36 months, whichever occurs
later.
(ii) For MLG retraction actuator piston rods having P/N
114256326 issue 01, or P/N 114256321 issue 06: Do the draining and
sealing within 60 days after the effective date of this AD or before
the MLG retraction actuator has been in service 72 months, whichever
occurs later.
(2) For MLG retraction actuator piston rods having P/N
114256309, P/N 114256321 issue 03, P/N 114256326 issue 01, or P/N
114256321 issue 06, that have been inspected and the fluid drained
as of the effective date of this AD, as described in the applicable
service information specified in paragraph (k)(1) or (k)(2) of this
AD: Do the draining and sealing at the later of the times specified
in paragraphs (j)(2)(i) and (j)(2)(ii) of this AD.
(i) Within 1,000 flight cycles or 24 months, whichever occurs
first, from the last inspection and fluid drainage accomplished in
accordance with the actions required in paragraph (j) of this AD.
(ii) Within 60 days after the effective date of this AD.
(k) Service Information To Determine Configuration for Paragraph (j) of
This AD
(1) For Model A330 airplanes:
(i) Airbus Mandatory Service Bulletin A330-32-3173, Revision 02,
dated May 11, 2005;
(ii) Airbus Mandatory Service Bulletin A330-32-3173, Revision
03, dated March 13, 2006;
(iii) Airbus Mandatory Service Bulletin A330-32-3173, Revision
04, dated June 12, 2006; or
(iv) Airbus Mandatory Service Bulletin A330-32-3173, Revision
05, dated September 26, 2008.
(2) For Model A340-200 and -300 series airplanes:
(i) Airbus Mandatory Service Bulletin A340-32-4212, Revision 02,
dated May 11, 2005;
(ii) Airbus Mandatory Service Bulletin A340-32-4212, Revision
03, dated March 13, 2006;
(iii) Airbus Mandatory Service Bulletin A340-32-4212, Revision
04, dated June 12, 2006; or
(iv) Airbus Mandatory Service Bulletin A340-32-4212, Revision
05, dated September 26, 2008.
(l) Ultrasonic Inspection
At the applicable time specified in paragraph (l)(1) or (l)(2)
of this AD: Do an ultrasonic longitudinal inspection for cracking of
the retraction actuator piston rod end, in accordance with the
Accomplishment Instructions of Airbus Mandatory Service Bulletin
A330-32-3173, Revision 05, dated September 26, 2008 (for Model A330
series airplanes); or Airbus Mandatory Service Bulletin A340-32-
4212, Revision 05, dated September 26, 2008 (for Model A340-200 and
-300 series airplanes).
(1) For MLG retraction actuator piston rods that have not had a
non-destructive test (NDT) inspection as of the effective date of
this AD, as described in the applicable service information
specified in paragraph (m)(1) or (m)(2) of this AD: At the
applicable time specified in paragraph (l)(1)(i) or (l)(1)(ii) of
this AD.
(i) For MLG retraction actuator piston rods having P/N
114256309, or P/N 114256321 issue 03: Do the inspection within 60
days after the effective date of this AD, or before the MLG
retraction actuator has been in service 36 months, whichever occurs
later.
(ii) For MLG retraction actuator piston rods having P/N
114256326 issue 01, or P/N 114256321 issue 06: Do the inspection
within 60 days after the effective date of this AD, or before the
MLG retraction actuator has been in service 72 months, whichever
occurs later.
(2) For MLG retraction actuator piston rods having P/N
114256309, P/N 114256321 issue 03, P/N 114256326 issue 01, or P/N
114256321 issue 06, that have had an NDT inspection as of the
effective date of this AD, as described in the applicable service
information specified in paragraph (m)(1) or (m)(2) of this AD: Do
the inspection at the later of the times specified in paragraphs
(l)(2)(i) and (l)(2)(ii) of this AD.
(i) Within 1,400 flight hours, 250 flight cycles, or 4 months,
whichever occurs first after the date of the last ultrasonic
longitudinal inspection performed as described in the applicable
service information specified in paragraph (m)(1) or (m)(2) of this
AD.
(ii) Within 60 days after the effective date of this AD.
(m) Service Information To Determine Configuration for Paragraph (l) of
This AD
(1) For Model A330 airplanes:
(i) Airbus Mandatory Service Bulletin A330-32-3173, dated
December 17, 2003;
(ii) Airbus Mandatory Service Bulletin A330-32-3173, Revision
01, dated June 16, 2004;
(iii) Airbus Mandatory Service Bulletin A330-32-3173, Revision
02, dated May 11, 2005;
(iv) Airbus Mandatory Service Bulletin A330-32-3173, Revision
03, dated March 13, 2006;
(v) Airbus Mandatory Service Bulletin A330-32-3173, Revision 04,
dated June 12, 2006; or
(vi) Airbus Mandatory Service Bulletin A330-32-3173, Revision
05, dated September 26, 2008.
(2) For Model A340-200 and -300 series airplanes:
(i) Airbus Mandatory Service Bulletin A340-32-4212, dated
December 17, 2003;
(ii) Airbus Mandatory Service Bulletin A340-32-4212, Revision
01, dated June 16, 2004;
(iii) Airbus Mandatory Service Bulletin A340-32-4212, Revision
02, dated May 11, 2005;
(iv) Airbus Mandatory Service Bulletin A340-32-4212, Revision
03, dated March 13, 2006;
(v) Airbus Mandatory Service Bulletin A340-32-4212, Revision 04,
dated June 12, 2006; or
(vi) Airbus Mandatory Service Bulletin A340-32-4212, Revision
05, dated September 26, 2008.
(n) Corrective Action for Ultrasonic Inspection; Repetitive Interval
(1) If the finding of the inspection required by paragraph (l)
of this AD gives an indication of 75% or higher of full screen
height (FSH) and between 5 and 7 in time base: Before further
flight, replace the MLG retraction actuator with a new or
serviceable part, in accordance with the Accomplishment Instructions
of Airbus Mandatory Service Bulletin A330-32-3173, Revision 05,
dated September 26, 2008 (for Model A330 series airplanes); or
Airbus Mandatory Service Bulletin A340-32-4212, Revision 05, dated
September 26, 2008 (for Model A340-200 and -300 series airplanes).
(2) If the finding of the inspection required by paragraph (l)
of this AD gives an indication of less than 75% FSH and between 5
and 7 in time base: Repeat the inspection required by paragraph (l)
of this AD thereafter at intervals not to exceed 1,400 flight hours,
250 flight cycles, or 4 months, whichever occurs first.
[[Page 7102]]
(o) One-Time Ultrasonic Inspections of the Full-Length of the Piston
Rod
At the applicable time specified in paragraph (o)(1) or (o)(2)
of this AD: Do a full-length ultrasonic longitudinal and a full-
length circumferential inspection of the chromium-plated area of the
piston rod for cracking, in accordance with the Accomplishment
Instructions of Airbus Mandatory Service Bulletin A330-32-3173,
Revision 05, dated September 26, 2008 (for Model A330 series
airplanes); or Airbus Mandatory Service Bulletin A340-32-4212,
Revision 05, dated September 26, 2008 (for Model A340-200 and -300
series airplanes).
(1) For MLG retraction actuator piston rods having P/N
114256309, or P/N 114256321 issue 03: Inspect at the later of the
times specified in paragraphs (o)(1)(i) and (o)(1)(ii) of this AD.
(i) Within 1,750 flight hours, 315 flight cycles, or 5 months
after the effective date of this AD, whichever occurs first.
(ii) Before the MLG retraction actuator has been in service 36
months.
(2) For MLG retraction actuator piston rods having P/N 114256326
issue 01, or P/N 114256321 issue 06: Inspect at the later of the
times specified in paragraphs (o)(2)(i) and (o)(2)(ii) of this AD.
(i) Within 1,750 flight hours, 315 flight cycles, or 5 months
after the effective date of this AD, whichever occurs first.
(ii) Before the MLG retraction actuator has been in service 72
months.
(p) Corrective Action for One-time Ultrasonic Inspections of the Full-
Length of the Piston Rod
(1) If the finding of the full-length ultrasonic longitudinal
inspection required by paragraph (o) of this AD gives an indication
of 75% or higher FSH and between 5 and 7 in time base: Before
further flight, replace the MLG retraction actuator with a new or
serviceable part, in accordance with the Accomplishment Instructions
of Airbus Mandatory Service Bulletin A330-32-3173, Revision 05,
dated September 26, 2008 (for Model A330 series airplanes); or
Airbus Mandatory Service Bulletin A340-32-4212, Revision 05, dated
September 26, 2008 (for Model A340-200 and -300 series airplanes).
(2) If the finding of the full-length ultrasonic circumferential
inspection required by paragraph (o) of this AD gives an indication
of 75% or higher FSH and between 7 and 9.5 in time base: Before
further flight, replace the MLG retraction actuator with a new or
serviceable part, in accordance with the Accomplishment Instructions
of Airbus Mandatory Service Bulletin A330-32-3173, Revision 05,
dated September 26, 2008 (for Model A330 series airplanes); or
Airbus Mandatory Service Bulletin A340-32-4212, Revision 05, dated
September 26, 2008 (for Model A340-200 and -300 series airplanes).
(q) Reporting Requirement
Report the results (regardless of findings) of the detailed
inspection, the fluid drain/seal of the retraction actuator piston
rod, the one-time ultrasonic longitudinal inspection of the upper
end of the piston rod, and the one-time full-length ultrasonic
circumferential inspection required by this AD, and the findings of
the actions required by this AD that cause an actuator to be
replaced, in accordance with the Accomplishment Instructions of
Airbus Mandatory Service Bulletin A330-32-3173, Revision 05, dated
September 26, 2008 (for Model A330 series airplanes); or Airbus
Mandatory Service Bulletin A340-32-4212, Revision 05, dated
September 26, 2008 (for Model A340-200 and -300 series airplanes).
Submit the report to Airbus Customer Services Directorate,
Attention: SEDCC1 Technical Data and Documentation Services fax:
(+33) 5 61 93 28 06; email: sb.reporting@airbus.com, or via your
resident customer support office. Submit the report at the
applicable time specified in paragraph (q)(1) or (q)(2) of this AD.
(1) If the actions requiring reporting, as specified in
paragraph (q) of this AD, are done on or after the effective date of
this AD: Submit the report within 90 days after those actions have
been done.
(2) If the actions requiring reporting, as specified in
paragraph (q) of this AD, were done before the effective date of
this AD: Submit the report within 90 days after the effective date
of this AD.
(r) Terminating Actions for Repetitive Detailed Inspections
Accomplishment of the initial drainage of the fluid from the
piston, as required by paragraph (j) of this AD, the full-length
ultrasonic longitudinal inspection, and the full-length
circumferential inspection, as required by paragraph (o) of this AD,
constitutes terminating action for the repetitive detailed
inspections required by paragraph (g) of this AD, provided no crack
is found during the inspections.
(s) Terminating Modification
Within 48 months after the effective date of this AD: Modify the
left-hand and right-hand MLG retraction actuators, in accordance
with the Accomplishment Instructions of Airbus Mandatory Service
Bulletin A330-32-3180, Revision 03, dated January 28, 2011 (for
Model A330 series airplanes); or Airbus Mandatory Service Bulletin
A340-32-4222, Revision 03, dated January 28, 2011 (for Model A340-
200 and -300 series airplanes). Accomplishment of the modification
required by this paragraph terminates the repetitive requirements of
this AD for the MLG retraction actuator that is modified.
(t) Exception to Re-Identification of the MLG Retraction Actuator
The re-identification of the MLG retraction actuator having P/N
114256002-055, which is described in Airbus Mandatory Service
Bulletin A330-32-3180, Revision 03, dated January 28, 2011 (for
Model A330 series airplanes); or Airbus Mandatory Service Bulletin
A340-32-4222, Revision 03, dated January 28, 2011 (for Model A340-
200 and -300 series airplanes); is not required on airplanes that
have Airbus modification 52980 embodied in production.
(u) Optional Parts Installation
Installation of retraction actuator piston rod having P/N
114256323, in accordance with the Accomplishment Instructions of
Airbus Service Bulletin A330-32-3174, Revision 02, dated September
16, 2005 (for Model A330 series airplanes); or Airbus Service
Bulletin A340-32-4213, Revision 01, dated September 16, 2005 (for
Model A340-200 and -300 series airplanes); constitutes an acceptable
method of compliance with the requirements of paragraphs (g), (j),
(l), and (o) of this AD for that installed MLG retraction actuator.
(v) Parts Installation Limitation
As of the effective date of this AD, no person may install a
piston rod having P/N 114256309, or 114256321, or 114256326 issue 01
for the MLG retraction actuator on any airplane, unless the part
meets the applicable requirements of this AD at the specified times
and intervals.
(w) Credit for Previous Actions
(1) This paragraph provides credit for the actions required by
paragraphs (g), (j), (l), and (o) of this AD, if those actions were
performed before the effective date of this AD using the service
information specified in paragraphs (w)(1)(i) through (w)(1)(ix) of
this AD.
(i) Airbus Mandatory Service Bulletin A330-32-3173, dated
December 17, 2003; (for Model A330 series airplanes).
(ii) Airbus Mandatory Service Bulletin A330-32-3173, Revision
01, dated June 16, 2004 (for Model A330 series airplanes).
(iii) Airbus Mandatory Service Bulletin A330-32-3173, Revision
02, dated May 11, 2005 (for Model A330 series airplanes).
(iv) Airbus Mandatory Service Bulletin A330-32-3173, Revision
03, dated March 13, 2006 (for Model A330 series airplanes).
(v) Airbus Mandatory Service Bulletin A330-32-3173, Revision 04,
dated June 12, 2006 (for Model A330 series airplanes).
(vi) Airbus Mandatory Service Bulletin A340-32-4212, dated
December 17, 2003 (for Model A340-200 and -300 series airplanes).
(vii) Airbus Mandatory Service Bulletin A340-32-4212, Revision
01, dated June 16, 2004 (for Model A340-200 and -300 series
airplanes).
(viii) Airbus Mandatory Service Bulletin A340-32-4212, Revision
02, dated May 11, 2005; Revision 03, dated March 13, 2006 (for Model
A340-200 and -300 series airplanes).
(ix) Airbus Mandatory Service Bulletin A340-32-4212, Revision
04, dated June 12, 2006 (for Model A340-200 and -300 series
airplanes).
(2) This paragraph provides credit for the actions required by
paragraph (s) of this AD, if the modification was done before the
effective date of this AD using the service bulletins specified in
paragraphs (u)(2)(i) through (u)(2)(iv) of this AD.
(i) Airbus Service Bulletin A330-32-3180, Revision 01, dated
August 15, 2005 for Model A330 series airplanes).
(ii) Airbus Mandatory Service Bulletin A330-32-3180, Revision
02, dated April 4, 2007 (for Model A330 series airplanes).
(iii) Airbus Service Bulletin A340-32-4222, Revision 01, dated
August 15, 2005 (for Model A340-200 and -300 series airplanes).
(iv) Airbus Mandatory Service Bulletin A340-32-4222, Revision
02, dated April 4, 2007 (for Model A340-200 and -300 series
airplanes).
[[Page 7103]]
(3) This paragraph provides credit for the actions required by
paragraph (s) of this AD, if the modification was done before the
effective date of this AD using Airbus Service Bulletin A340-32-
4222, dated September 20, 2004; and re-identified using Airbus
Service Bulletin A340-32-4222, Revision 01, dated August 15, 2005,
or Airbus Mandatory Service Bulletin A340-32-4222, Revision 02,
dated April 4, 2007.
(x) 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 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) 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, or the DAH with a State of Design
Authority's design organization approval). For a repair method to be
approved, the repair approval must specifically refer to this AD.
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.
(y) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) European Aviation Safety Agency Airworthiness Directive 2011-
0178R1, dated March 6, 2012 (corrected March 7, 2012); and 2011-
0179R1, dated March 6, 2012; for related information. These MCAIs
may be found in the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-
2014-0012.
(2) For 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. 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.
Issued in Renton, Washington, on January 29, 2014.
John P. Piccola,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2014-02522 Filed 2-5-14; 8:45 am]
BILLING CODE 4910-13-P
