Airworthiness Directives; Airbus Airplanes, 34251-34257 [2017-14923]
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34251
Rules and Regulations
Federal Register
Vol. 82, No. 140
Monday, July 24, 2017
This section of the FEDERAL REGISTER
contains regulatory documents having general
applicability and legal effect, most of which
are keyed to and codified in the Code of
Federal Regulations, which is published under
50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by
the Superintendent of Documents.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–9393; Directorate
Identifier 2014–NM–199–AD; Amendment
39–18935; AD 2017–13–05]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are superseding
Airworthiness Directive (AD) 2013–13–
16 for all Airbus Model A330–200,
A330–200 Freighter, A330–300 series
airplanes; and all Airbus Model A340–
200, –300, –500, and –600 series
airplanes. AD 2013–13–16 required
repetitive inspections for discrepancies
of the ball-screw assembly of the
trimmable horizontal stabilizer actuator
(THSA), repetitive greasing of the THSA
ball-nut, and replacement of the THSA
if necessary; and modification or
replacement (as applicable) of the ballnut assembly, which ends certain
repetitive inspections. This new AD
requires an inspection, corrective
actions if necessary, lubrication of the
ball-nut, modification of the THSA, and
removal of certain airplanes from the
applicability. This AD was prompted by
a determination that a modification that
automatically detects failure of the ballscrew assembly is necessary. We are
issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective August 28,
2017.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of August 28, 2017.
ADDRESSES: For service information
identified in this final rule, contact
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SUMMARY:
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Airbus, Airworthiness Office—EIAS, 1
Rond Point Maurice Bellonte, 31707
Blagnac Cedex, France; telephone +33 5
61 93 36 96; fax +33 5 61 93 44 51; email
account.airworth-eas@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. It is also
available on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2016–
9393.
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–
9393; 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 street address for
the Docket Office (telephone 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:
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
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2013–13–16,
Amendment 39–17504 (78 FR 47537,
August 6, 2013) (‘‘AD 2013–13–16’’). AD
2013–13–16 applied to all Airbus Model
A330–200, A330–200 Freighter, A330–
300 series airplanes, and all Airbus
Model A340–200, –300, –500, and –600
series airplanes. The NPRM published
in the Federal Register on December 19,
2016 (81 FR 91882) (‘‘the NPRM’’).
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA Airworthiness
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Directive 2014–0219, dated September
29, 2014 (referred to after this as the
Mandatory Continuing Airworthiness
Information, or ‘‘the MCAI’’), to correct
an unsafe condition on all Airbus Model
A330 and Model A340 series airplanes.
The MCAI states:
Several cases of transfer tube
disconnection from the ball-nut of the
trimmable horizontal stabilizer actuator
(THSA) part number (P/N) 47172 and 47147–
400 were detected on the ground during
greasing and maintenance. Investigation
results showed that this was caused by water
ingress into the ball-nut, resulting in the
jamming of the ball transfer circuit when the
water froze. If the three (independent) ball
circuits fail, then the THSA operates on a
fail-safe nut (which operates without balls),
which jams after several movements on the
ballscrew of the THSA.
This condition, if not detected and
corrected, could damage the ball screw and
the fail-safe nut, possibly resulting in
jamming of the THSA and consequent
reduced control of the aeroplane.
To detect at an early stage any distortion
or initiation of disconnection, [Directorate
General for Civil Aviation] DGAC France
issued AD 2001–356 and AD 2001–357 to
require repetitive inspections of the transfer
tubes and their collars and, depending on
findings, corrective action(s).
Prompted by another case of transfer tube
disconnection, DGAC France issued AD
2001–356R2 and AD 2001–357R2 to require
additional repetitive greasing and
reinforcement of the ball-nut maintenance
greasing instructions.
Subsequently, DGAC France issued AD
2002–037 and AD 2002–038 to require a
modification that was also terminating action
for the repetitive inspections and greasing
tasks required by DGAC France AD 2001–
356R2 and AD 2001–357R2 for the THSA P/
N 47172 by application of Service Bulletin
(SB) A330–27–3085 or SB A340–27–4089
(equivalent to Airbus production
modification 49590), as applicable, changing
the THSA P/N from 47172 to 47172–300.
Later on, DGAC France issued AD 2002–
414 (later revised to R3) and AD 2002–415
(later revised to R2), which superseded the
DGAC France AD 2001–356R2, AD 2001–
357R2, AD 2002–037, and AD 2002–038,
requiring:
—Repetitive inspections of all THSA P/N in
service,
—repetitive lubrication of some THSA P/N,
and
—replacement of THSA P/N 47172, 47147–
400 and 47147–2XX/–3XX.
In addition, the electrical flight control
computers monitor the operation of the
THSA and the jamming of this actuator could
be detected and indicated by messages on the
maintenance system and on the [electronic
centralized aircraft monitor] ECAM. For that
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reason, DGAC France AD 2002–414 and AD
2002–415 also required inspection of the
THSA after display of such message(s).
After those [DGAC France] ADs were
issued, Airbus introduced 4 new THSA, P/N
47172–500, P/N 47172–510, P/N 47172–520
and P/N 47172–530.
As these new THSA also needed to be
inspected/lubricated, EASA issued AD 2010–
0192 and [EASA] AD 2010–0193 [which
correspond to FAA AD 2013–13–16], which
retained the requirements of DGAC France
AD F–2002–414R3 and AD F–2002–415R2
respectively, which were superseded, to add
required repetitive inspections and
lubrications of the new THSA P/N.
Since those [EASA] ADs were issued, all
requirements of EASA AD 2010–0192 and
[EASA] AD 2010–0193 were transferred into
Airbus Airworthiness Limitations Section
(ALS) Part 4, except the requirement of
paragraph (2.3) of those [EASA] ADs. At this
time, compliance with ALS Part 4 tasks is
required by EASA AD 2013–0268 (A330
aeroplanes) and [EASA] AD 2013–0269
(A340 aeroplanes), respectively [which
correspond to FAA AD 2015–16–02,
Amendment 39–18227 (80 FR 48019, August
11, 2015) (A330 airplanes); and AD 2014–23–
17, Amendment 39–18033 (79 FR 71304,
December 2, 2014) (A340 airplanes);
respectively.]
In addition, Airbus developed a Checkable
Shear Pin (CSP) for the THSA and an
associated additional electrical harness,
which consists of installation of two
Electrical Detection Devices (EDD) on the
lower attachment secondary load path, which
gives an indication to the Flight Control
Primary Computers of secondary load path
engagement.
After embodiment of these modifications
on an aeroplane, the repetitive inspections of
the ballscrew assembly for integrity of the
primary and secondary load paths is no
longer required, because the failure is
detected automatically by this new device.
For the reasons described above, this
[EASA] AD retains only the requirement of
paragraph (2.3) of EASA AD 2010–0192 and
2010–0193 [actions following ECAM fault
messages], which are superseded, and
requires the installation of CSP and
associated additional electrical harness on
the THSA of the aeroplane. This [EASA] AD
also requires, for A340–500/–600 aeroplanes
that are post-SB A340–92–5008 (at Revision
06 or earlier), accomplishment of A340 ALS
Part 3 task 274000–B0002–1–C, providing a
grace period of 3 months for aeroplanes that
have exceeded the applicable threshold or
interval.
The unsafe condition is the degraded
operation of the THSA, which could
result in reduced control of the airplane.
Model A330–223F and A330–243F
airplanes have been removed from the
applicability of this AD to correspond
with the MCAI.
Required actions include a detailed
inspection and corrective actions if an
ECAM fault message is displayed,
repetitive lubrication of the THSA ballnut, and a modification of the THSA by
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installing a CSP and associated
electrical harness.
Required actions also include certain
‘‘Additional Work’’ that is described in
the following service information.
• ‘‘Additional Work’’ in Airbus
Service Bulletin A330–27–3143,
Revision 01, dated July 10, 2012, is
described as removing the closing plug
from the electrical harness 4515VB and
connecting the electrical harness
4515VB to the THSA.
• ‘‘Additional Work’’ in Airbus
Service Bulletin A330–92–3046,
Revision 07, dated January 13, 2017;
and in Airbus Service Bulletin A340–
92–4056, Revision 04, dated December
5, 2013; is described as replacement of
a certain harness item, installation of
placards and cable support,
modification of a certain bracket, and
installation of a certain spacer.
• ‘‘Additional Work’’ in Airbus
Service Bulletin A340–92–5008,
Revision 07, dated February 8, 2013, is
described as replacing a certain wiring
harness, replacing a certain THSA
harness, installing additional placards,
and modifying a certain wire harness
installation order.
You may examine the MCAI in the
AD docket on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2016–
9393.
Comments
We gave the public the opportunity to
participate in developing this AD. We
received no comments on the NPRM or
on the determination of the cost to the
public.
New Service Information
Since we issued the NPRM, we have
reviewed Airbus Service Bulletin A330–
92–3046, Revision 07, dated January 13,
2017 (we referred to Airbus Service
Bulletin A330–92–3046, Revision 06,
dated November 15, 2013, as one of the
appropriate sources of service
information for installing an electrical
harness). Airbus Service Bulletin A330–
92–3046, Revision 07, dated January 13,
2017, includes minor updates to the
procedures and illustrations. We have
revised figure 2 to paragraphs (h) and (i)
of this AD and figure 3 to paragraph (j)
of this AD to refer to Airbus Service
Bulletin A330–92–3046, Revision 07,
dated January 13, 2017. We have also
added paragraph (r)(2) to this AD to give
credit for actions done in accordance
with Airbus Service Bulletin A330–92–
3046, Revision 06, dated November 15,
2013.
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Costs of Compliance Change
The costs of compliance information
in the NPRM included a parts cost of
$14,198. We have revised the costs of
compliance information in this AD
based on receiving updated cost
information from the manufacturer to
include a parts cost of $17,481.
Conclusion
We reviewed the relevant data, and
determined that air safety and the
public interest require adopting this AD
with the changes described previously
and minor editorial changes. We have
determined that these minor changes:
• Are consistent with the intent that
was proposed in the NPRM for
correcting the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM.
We also determined that these
changes will not increase the economic
burden on any operator or increase the
scope of this AD.
Related Service Information Under 1
CFR Part 51
Airbus has issued the following
service information. The service
bulletins having the same document
number are distinct because each
revision contains unique editorial
changes.
The following service information
describes procedures for doing
repetitive inspections for integrity of the
primary and secondary load paths of the
ball-screw assembly of the THSA. These
service bulletins are distinct because
they apply to different airplane models.
• Airbus Service Bulletin A330–27–
3102, Revision 09, dated March 29,
2016.
• Airbus Service Bulletin A340–27–
4107, Revision 09, dated March 29,
2016.
The following service information
describes procedures for installing two
electrical detection devices, also called
CSPs, on the lower attachment
secondary load path of the THSA, and
modifying the THSA. These service
bulletins are distinct because they apply
to different airplane models equipped
with THSAs having different part
numbers.
• Airbus Service Bulletin A330–27–
3137, including Appendix 01, dated
March 20, 2007.
• Airbus Service Bulletin A330–27–
3137, Revision 01, including Appendix
1, dated December 6, 2007.
• Airbus Service Bulletin A330–27–
3137, Revision 02, dated January 18,
2010.
• Airbus Service Bulletin A330–27–
3143, Revision 01, dated July 10, 2012.
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• Airbus Service Bulletin A340–27–
4136, including Appendix 01, dated
March 20, 2007.
• Airbus Service Bulletin A340–27–
4136, Revision 01, including Appendix
1, dated December 6, 2007.
• Airbus Service Bulletin A340–27–
4136, Revision 02, including Appendix
1, dated February 24, 2010.
• Airbus Service Bulletin A340–27–
4143, dated February 21, 2012.
• Airbus Service Bulletin A340–27–
5030, Revision 01, including Appendix
1, dated November 20, 2009.
The following service information
describes procedures for installing
electrical wiring harnesses and brackets
to connect the secondary nut detection
device to the monitoring systems. These
service bulletins are distinct because
they apply to different airplane models.
• Airbus Service Bulletin A330–92–
3046, Revision 04, dated July 16, 2010.
• Airbus Service Bulletin A330–92–
3046, Revision 05, dated November 7,
2011.
• Airbus Service Bulletin A330–92–
3046, Revision 07, dated January 13,
2017.
• Airbus Service Bulletin A340–92–
4056, Revision 03, dated July 16, 2010.
• Airbus Service Bulletin A340–92–
4056, Revision 04, dated December 5,
2013.
• Airbus Service Bulletin A340–92–
5008, Revision 07, dated February 8,
2013.
The following service information
describes system equipment
maintenance requirements (SEMRs) that
refer to preventative maintenance
requirements found necessary to comply
with safety objectives. These documents
are distinct because they apply to
different airplane models.
• Airbus A330 Airworthiness
Limitations Section (ALS) Part 4—
System Equipment Maintenance
Requirements (SEMR), Revision 05,
dated October 19, 2015.
• Airbus A340 Airworthiness
Limitations Section (ALS) Part 4—
System Equipment Maintenance
Requirements (SEMR), Revision 04,
dated October 19, 2015.
Airbus A340 Airworthiness
Limitations Section (ALS) Part 3—
Certification Maintenance Requirements
(CMR), Revision 03, dated October 19,
2015, describes CMRs that are systemrelated periodic tasks established during
type certification.
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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Costs of Compliance
We estimate that this AD affects 33
airplanes of U.S. registry.
The actions required by AD 2013–13–
16, and retained in this AD take about
1 work-hour per product, at an average
labor rate of $85 per work-hour. Based
on these figures, the estimated cost of
the actions that are required by AD
2013–13–16 is $85 per product.
We also estimate that it takes about 67
work-hours per product to comply with
the basic requirements of this AD. The
average labor rate is $85 per work-hour.
Required parts would cost about
$17,481 per product. Based on these
figures, we estimate the cost of this AD
on U.S. operators to be $764,808, or
$23,176 per product.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. ‘‘Subtitle VII:
Aviation Programs,’’ describes in more
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.
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34253
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)
2013–13–16, Amendment 39–17504 (78
FR 47537, August 6, 2013), and adding
the following new AD:
■
2017–13–05 Airbus: Amendment 39–18935;
Docket No. FAA–2016–9393; Directorate
Identifier 2014–NM–199–AD.
(a) Effective Date
This AD is effective August 28, 2017.
(b) Affected ADs
This AD replaces AD 2013–13–16,
Amendment 39–17504 (78 FR 47537, August
6, 2013) (‘‘AD 2013–13–16’’).
(c) Applicability
This AD applies to the airplanes identified
in paragraphs (c)(1) and (c)(2) of this AD,
certificated in any category.
(1) Airbus Model A330–201, –202, –203,
–223, –243, –301, –302, –303, –321, –322,
–323, –341, –342, and –343 airplanes, all
manufacturer serial numbers.
(2) Airbus Model A340–211, –212, –213,
–311, –312, –313, –541, and –642 airplanes,
all manufacturer serial numbers.
(d) Subject
Air Transport Association (ATA) of
America Code 27, Flight Controls.
(e) Reason
This AD was prompted by the
determination that a modification that
automatically detects failure of the ball-screw
assembly is necessary. We are issuing this
AD to detect and correct wear on the
trimmable horizontal stabilizer actuator
(THSA), possibly resulting in damage to the
ball-screw and fail-safe nut, which could jam
the THSA and result in reduced control of
the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Actions for Electronic Centralized
Aircraft Monitor (ECAM) Fault Messages
For airplanes other than those identified in
figure 1 to paragraphs (g), (h), and (q) of this
AD: If, during any flight, one of the ‘‘PRIM
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X PITCH FAULT’’ or ‘‘STAB CTL FAULT’’
messages is displayed on the ECAM
associated with the ‘‘PITCH TRIM ACTR
(1CS)’’ maintenance message, before further
flight after each time the message is
displayed on the ECAM, do the actions
specified in paragraphs (g)(1) and (g)(2) of
this AD.
(1) Do the applicable detailed inspection of
the ball-screw assembly for integrity of the
primary and secondary load path; check the
checkable shear pins (CSP), if installed; and
do all applicable corrective actions; as
specified in paragraph (g)(1)(i), (g)(1)(ii), or
(g)(1)(iii) of this AD. Do all applicable
corrective actions before further flight.
(i) For Model A330 series airplanes: Do the
actions in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A330–27–3102, Revision 09,
dated March 29, 2016, except as required by
paragraph (n)(1) of this AD.
(ii) For Model A340–200 and –300 series
airplanes: Do the actions in accordance with
the Accomplishment Instructions of Airbus
Service Bulletin A340–27–4107, Revision 09,
dated March 29, 2016, except as required by
paragraph (n)(1) of this AD.
(iii) For Model A340–500 and –600 series
airplanes: Do the actions 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).
Note 1 to paragraph (g)(1)(iii) of this AD:
Guidance for the inspection of the ball-screw
assembly can be found in Task 274000–
B0002–1–C, Inspection of the ball-screw
assembly for integrity of the primary and
secondary load paths, of the Airbus A340
Airworthiness Limitations Section (ALS) Part
3—Certification Maintenance Requirements
(CMR), Revision 03, dated October 19, 2015.
(2) Lubricate the THSA ball-nut in
accordance with the applicable service
information specified in paragraph (g)(2)(i),
(g)(2)(ii), or (g)(2)(iii) of this AD.
(i) Task 274400–00002–1–E, Lubrication of
the THSA ball-nut, of Airbus A330 ALS Part
4—System Equipment Maintenance
Requirements (SEMR), Revision 05, dated
October 19, 2015 (for Model A330 series
airplanes).
(ii) Task 274400–00002–1–E, Lubrication
of the THSA ball-nut, of Airbus A340 ALS
Part 4—System Equipment Maintenance
Requirements (SEMR), Revision 04, dated
October 19, 2015 (for Model A340–200 and
–300 series airplanes).
(iii) Task 274000–B0003–1–C, Lubrication
of THS Actuator ball-screw nut, of Airbus
A340 ALS Part 3—Certification Maintenance
Requirements (CMR), Revision 03, dated
October 19, 2015 (for Model A340–500 and
–600 series airplanes).
FIGURE 1 TO PARAGRAPHS (g), (h), AND (q) OF THIS AD—DEFINITION OF AIRPLANE GROUPS
Group
Airplane models
On which the following actions or modifications have been done
Group 1 airplanes ...
Airbus Model A330–200 and –300 series airplanes.
On which the actions specified in Airbus Service Bulletin A330–27–3137, dated
March 20, 2007; or Revision 01, dated December 6, 2007; and Airbus Service Bulletin A330–92–3046, Revision 04, dated July 16, 2010; or Revision 05,
dated November 7, 2011; or Revision 06, dated November 15, 2013; have
been embodied in service.
On which the actions specified in Airbus Service Bulletin A340–27–4136, including Appendix 1, dated March 20, 2007; or Revision 01, including Appendix 1, dated December 6, 2007; and Airbus Service Bulletin A340–92–4056,
Revision 03, dated July 16, 2010; have been embodied in service.
On which Airbus Modifications 55780, 52269, and 56056 have been embodied
in production.
Airbus Model A340–200 and –300 series airplanes.
Group 2 airplanes ...
Group 3 airplanes ...
Airbus Model A330–200 and –300 series airplanes and Model A340–200
and –300 series airplanes.
Airbus Model A340–500 and –600 series airplanes.
Airbus Model A330–200 and –300 series airplanes.
Airbus Model A330–200 and –300 series airplanes.
Airbus Model A340–200 and –300 series airplanes.
Airbus Model A340–200 and –300 series airplanes.
(h) Installation of CSP and Electrical
Harness
For all airplanes, except Group 2 airplanes
specified in figure 1 to paragraphs (g), (h),
and (q) of this AD, and except for airplanes
On which Airbus Modifications 54882, 52191, and 56058 have been embodied
in production.
On which Airbus Service Bulletin A330–27–3137, dated March 20, 2007; or Revision 01, dated December 6, 2007; has been embodied in service and Airbus Modifications 52269 and 56056 have been embodied in production.
On which Airbus Modification 55780 has been embodied in production and Airbus Service Bulletin A330–92–3046 Revision 04, dated July 16, 2010; or Revision 05, dated November 07, 2011; or Revision 06, dated November 15,
2013; has been embodied in service.
On which Airbus Service Bulletin A340–27–4136, including Appendix 1, dated
March 20, 2007; or Revision 01, including Appendix 1, dated December 6,
2007; has been embodied in service and Airbus Modifications 52269 and
56056 have been embodied in production.
On which Airbus Modification 55780 has been embodied in production and Airbus Service Bulletin A340–92–4056, Revision 03, dated July 16, 2010, has
been embodied in service.
identified in paragraphs (i), (j), and (n)(2) of
this AD: Within 12 months after the effective
date of this AD, modify the airplane by
installing a CSP on the THSA and an
additional electrical harness, in accordance
with the Accomplishment Instructions of the
Airbus service information specified in figure
2 to paragraphs (h) and (i) of this AD, as
applicable to the part number of the THSA
installed on the airplane, except as provided
by paragraph (n)(2) of this AD.
srobinson on DSKBC5CHB2PROD with RULES
FIGURE 2 TO PARAGRAPHS (h) AND (i) OF THIS AD—APPLICABLE SERVICE INFORMATION FOR MODIFICATION
THSA Part No.
(P/N)
Service bulletin for CSP installation
Service bulletin for electrical harness installation
47172–300 .......
Airbus Service Bulletin A330–27–3137, Revision 02, dated
January 18, 2010, for Airbus Model A330–200 and –300
series airplanes; and
Airbus Service Bulletin A340–27–4136, Revision 02, including
Appendix 1, dated February 24, 2010, for Airbus Model
A340–200 and –300 series airplanes.
Airbus Service Bulletin A330–92–3046, Revision 07, dated
January 13, 2017, for Airbus Model A330–200 and –300
series airplanes; and
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34255
FIGURE 2 TO PARAGRAPHS (h) AND (i) OF THIS AD—APPLICABLE SERVICE INFORMATION FOR MODIFICATION—Continued
THSA Part No.
(P/N)
Service bulletin for CSP installation
Service bulletin for electrical harness installation
47147–500 .......
Airbus Service Bulletin A330–27–3143, Revision 01, dated
July 10, 2012, for Airbus Model A330–200 and –300 series
airplanes; and
Airbus Service Bulletin A340–27–4143, dated February 21,
2012, for Airbus Model A340–200 and –300 series airplanes.
Airbus Service Bulletin A340–27–5030, Revision 01, including
Appendix 1, dated November 20, 2009, for Airbus Model
A340–541 and –642 airplanes.
Airbus Service Bulletin A340–92–4056, Revision 04, dated
December 5, 2013, for Airbus Model A340–200 and –300
series airplanes.
47175–200,
47175–300.
(i) ‘‘Additional Work’’ on Previously
Modified Airplanes
For airplanes that have already been
modified (installation of CSP on the THSA
and electrical harness) before the effective
date of this AD in accordance with the
Accomplishment Instructions of any
previous revision of an Airbus service
bulletin specified in figure 2 to paragraphs
(h) and (i) of this AD, as applicable: Within
12 months after the effective date of this AD,
do the ‘‘Additional Work’’ specified in, and
in accordance with, the Accomplishment
Instructions of the applicable Airbus service
Airbus Service Bulletin A340–92–5008, Revision 07, dated
February 8, 2013, for Airbus Model A340–541 and –642
airplanes.
information specified in figure 2 to
paragraphs (h) and (i) of this AD.
(j) Installation of Electrical Harness on
Airplanes Equipped With a CSP
For airplanes having one of the THSAs
installed with a part number listed in figure
3 to paragraph (j) of this AD, and which have
been modified by installing a CSP on the
THSA as required by paragraph (h) of this
AD: Within 12 months after the effective date
of this AD, inspect to determine if the
electrical harness identified in the applicable
Airbus service information specified in figure
3 to paragraph (j) of this AD is installed on
the airplane, and if found not to be installed,
modify the airplane by installing an electrical
harness, in accordance with the
Accomplishment Instructions of the Airbus
service information specified in figure 3 to
paragraph (j) of this AD, as applicable to the
part number of the THSA installed on the
airplane. Airplanes having one of the THSAs
installed with a part number listed in figure
3 to paragraph (j) of this AD already have the
CSP installed on the THSA, and only the
electrical harness must be installed on the
airplane.
FIGURE 3 TO PARAGRAPH (j) OF THIS AD—ELECTRICAL HARNESS INSTALLATION
THSA P/N
Service information for electrical harness installation
47172–500, 47172–510, 47172–520, 47172–530, 47147–700, 47147–
710.
Airbus Service Bulletin A330–92–3046, Revision 07, dated January 13,
2017, for Airbus Model A330–200 and –300 series airplanes.
Airbus Service Bulletin A340–92–4056, Revision 04, dated December
5, 2013, for Airbus Model A340–200 and –300 series airplanes.
Airbus Service Bulletin A340–92–5008, Revision 07, dated February 8,
2013, for Airbus Model A340–541 and –642 airplanes.
47175–500, 47175–520, 47175–530 .......................................................
srobinson on DSKBC5CHB2PROD with RULES
(k) Terminating Action for Repetitive
Inspections of Airbus Model A330–200 and
–300 Series Airplanes
Accomplishment of a modification before
the effective date of this AD, using the
Accomplishment Instructions of Airbus
Service Bulletin A330–27–3137, dated March
20, 2007; or Revision 01, dated December 6,
2007; and Airbus Service Bulletin A330–92–
3046, Revision 04, dated July 15, 2010; or
Revision 05, dated November 7, 2011; or
Revision 06, dated November 15, 2013;
terminates the repetitive inspections
specified in paragraphs (k)(1) through (k)(4)
of this AD. Modification of an airplane as
required by this paragraph does not
constitute terminating action for the actions
specified in paragraph (g)(2) of this AD or the
additional work specified in paragraph (i) of
this AD.
(1) Task 274400–00001–1–E, Detailed
inspection of the ball-screw assembly for
integrity of the primary and secondary load
path and check the gap at the secondary nut
trunnion, of Airbus A330 ALS Part 4—
System Equipment Maintenance
Requirements (SEMR), Revision 05, dated
October 19, 2015.
(2) Task 274400–00001–2–E, Detailed
inspection of the ball-screw assembly for
integrity of the primary and secondary load
VerDate Sep<11>2014
16:26 Jul 21, 2017
Jkt 241001
path and check the CSPs, of Airbus A330
ALS Part 4—System Equipment Maintenance
Requirements (SEMR), Revision 05, dated
October 19, 2015.
(3) Task 274400–00001–3–E, Detailed
inspection of the ball-screw assembly for
integrity of the primary and secondary load
path and check the CSPs, of Airbus A330
ALS Part 4—System Equipment Maintenance
Requirements (SEMR), Revision 05, dated
October 19, 2015.
(4) Task 274400–00001–4–E, Detailed
inspection of the ball-screw assembly for
integrity of the primary and secondary load
path and check the CSPs, of Airbus A330
ALS Part 4—System Equipment Maintenance
Requirements (SEMR), Revision 05, dated
October 19, 2015.
(l) Terminating Action for Repetitive
Inspections of Airbus Model A340–200 and
–300 Series Airplanes
Accomplishment of a modification in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A340–
27–4143, dated February 21, 2012; and
Airbus Service Bulletin A340–92–4056,
Revision 03, dated July 16, 2010; terminates
the actions required by paragraph (g)(1) of
this AD for modified Airbus Model A340–
200 and –300 series airplanes only.
Modification of an airplane as specified in
PO 00000
Frm 00005
Fmt 4700
Sfmt 4700
this paragraph does not constitute
terminating action for the actions specified in
paragraph (g)(2) of this AD, or the additional
work specified in paragraph (i) of this AD.
(m) Terminating Action for Repetitive
Inspections of Airbus Model A340–200 and
–300 Series Airplanes
Accomplishment of a modification before
the effective date of this AD using the
Accomplishment Instructions of Airbus
Service Bulletin A340–27–4136, including
Appendix 1, dated March 20, 2007; or
Revision 01, including Appendix 1, dated
December 6, 2007; and Airbus Service
Bulletin A340–92–4056, Revision 03, dated
July 16, 2010; terminates the repetitive
inspections specified in paragraphs (m)(1)
through (m)(4) of this AD. Modification of an
airplane as specified in this paragraph does
not constitute terminating action for the
actions specified in paragraph (g)(2) of this
AD, or the additional work specified in
paragraph (i) of this AD.
(1) Task 274400–00001–1–E, Detailed
inspection of the ball-screw assembly for
integrity of the primary and secondary load
path and gap check at the secondary nut
trunnion, of Airbus A340 ALS Part 4—
System Equipment Maintenance
Requirements (SEMR), Revision 04, dated
October 19, 2015.
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Federal Register / Vol. 82, No. 140 / Monday, July 24, 2017 / Rules and Regulations
(2) Task 274400–00001–2–E, Detailed
inspection of the ball-screw assembly for
integrity of the primary and secondary load
path and CSP check, of Airbus A340 ALS
Part 4—System Equipment Maintenance
Requirements (SEMR), Revision 04, dated
October 19, 2015.
(3) Task 274400–00001–3–E, Detailed
inspection of the ball-screw assembly for
integrity of the primary and secondary load
path and CSP check, of Airbus A340 ALS
Part 4—System Equipment Maintenance
Requirements (SEMR), Revision 04, dated
October 19, 2015.
(4) Task 274400–00001–4–E, Detailed
inspection of the ball-screw assembly for
integrity of the primary and secondary load
path and CSP check, of A340 ALS Part 4—
System Equipment Maintenance
Requirements (SEMR), Revision 04, dated
October 19, 2015.
(n) Exceptions to the Actions in Certain
Service Information and Paragraph (h) of
This AD
(1) Where Airbus Service Bulletin A330–
27–3102, Revision 09, dated March 29, 2016
(for Model A330 series airplanes); or Airbus
Service Bulletin A340–27–4107, Revision 09,
dated March 29, 2016 (for Model A340 series
airplanes); specifies to contact Airbus for a
damage assessment: Before further flight,
accomplish the required actions in
accordance with the procedures specified in
paragraph (s)(2) of this AD.
(2) For airplanes that already had the
electrical harness installed during production
using Airbus Modifications 52269 and 56056
for Airbus Model A330–200 and –300 series
airplanes and Airbus Model A340–200 and
–300 series airplanes, and using Airbus
Modifications 52191 and 56058 for Model
A340–500 and –600 series airplanes: Only
the CSP must be installed on the THSA in
accordance with applicable Airbus service
bulletins and within the compliance time
specified in paragraph (h) of this AD.
srobinson on DSKBC5CHB2PROD with RULES
(o) Terminating Action for Repetitive
Inspections for Airplanes on Which Actions
Required by Paragraph (h), (i), or (j) of This
AD Are Done
Modification of an airplane as required by
paragraph (h), (i), or (j) of this AD, as
applicable, constitutes terminating action for
that airplane for the applicable actions
identified in paragraphs (o)(1) through (o)(4)
of this AD.
(1) For all airplanes: The actions required
by paragraph (g) of this AD.
(2) For Model A340–500 and –600 series
airplanes: Task 274000–B0002–1–C,
Inspection of the ball-screw assembly for
integrity of the primary and secondary load
paths, of Airbus A340 ALS Part 3—
Certification Maintenance Requirements
(CMR), Revision 03, dated October 19, 2015.
(3) For Model A330–200 and –300 series
airplanes: The ALS tasks identified in
paragraphs (k)(1) through (k)(4) of this AD.
(4) For Model A340–200 and –300 series
airplanes: The ALS tasks identified in
paragraphs (m)(1) through (m)(4) of this AD.
VerDate Sep<11>2014
16:26 Jul 21, 2017
Jkt 241001
(p) Ball-Screw Assembly Inspection for
Certain Airplanes
For Model A340–500 and –600 airplanes
that are in post-Airbus Service Bulletin
A340–92–5008, at Revision 06 or earlier,
configuration: Before exceeding the threshold
or interval, as applicable, of Task 274000–
B0002–1–C, Inspection of the ball-screw
assembly for integrity of the primary and
secondary load paths, of Airbus A340 ALS
Part 3—Certification Maintenance
Requirements (CMR), Revision 03, dated
October 19, 2015, or within 3 months after
the effective date of this AD, whichever
occurs later, accomplish Task 274000–
B0002–1–C, Inspection of the ball-screw
assembly for integrity of the primary and
secondary load paths, of Airbus A340 ALS
Part 3—Certification Maintenance
Requirements (CMR), Revision 03, dated
October 19, 2015; and do all applicable
corrective actions. Do all applicable
corrective actions before further flight using
a method approved by the Manager,
International Branch, ANM–116, Transport
Airplane Directorate, FAA; or EASA; or
Airbus’s EASA DOA. Repeat Task 274000–
B0002–1–C, Inspection of the ball-screw
assembly for integrity of the primary and
secondary load paths, thereafter at the
applicable intervals specified in Airbus A340
ALS Part 3—CMRs, Revision 03, dated
October 19, 2015.
(q) Parts Installation Prohibitions
(1) For all airplanes except Group 2
airplanes as identified in figure 1 to
paragraphs (g), (h), and (q) of this AD: After
modification of the airplane as required by
paragraph (h), (i), or (j) of this AD, as
applicable, no person may install any THSA
having part number (P/N) 47172–300, P/N
47147–500, P/N 47175–200, or P/N 47175–
300.
(2) For Group 2 airplanes, as identified in
figure 1 to paragraphs (g), (h), and (q) of this
AD: As of the effective date of this AD, no
person may install on any Group 2 airplane
any THSA having P/N 47172–300, P/N
47147–500, P/N 47175–200, or P/N 47175–
300.
(r) Credit for Previous Actions
(1) This paragraph provides credit for
actions required by paragraph (g)(2) of this
AD, if those actions were performed before
the effective date of this AD using the
applicable service information specified in
paragraphs (r)(1)(i) through (r)(1)(iv) of this
AD.
(i) Task 274400–00002–1–E, Lubrication of
the THSA ball-nut, of Airbus A330 ALS Part
4—Ageing Systems Maintenance, Revision
03, dated September 9, 2011 (for Model A330
series airplanes).
(ii) Task 274400–00002–1–E, Lubrication
of the THSA ball-nut, of Airbus A330 ALS
Part 4—Ageing Systems Maintenance,
Revision 04, dated August 27, 2013 (for
Model A330 series airplanes).
(iii) Task 274400–00002–1–E, Lubrication
of the THSA ball-nut, of Airbus A340 ALS
Part 4—Ageing Systems Maintenance,
Revision 02, dated October 12, 2011 (for
Model A340–200 and –300 series airplanes).
(iv) Task 274400–00002–1–E, Lubrication
of the THSA ball-nut, of Airbus A340 ALS
PO 00000
Frm 00006
Fmt 4700
Sfmt 4700
Part 4—Ageing Systems Maintenance,
Revision 03, dated November 15, 2012 (for
Model A340–200 and –300 series airplanes).
(2) This paragraph provides credit for the
electrical harness installation required by
paragraph (h) of this AD and the inspection
and electrical harness installation required
by paragraph (j) of this AD, if those actions
were performed before the effective date of
this AD using Airbus Service Bulletin A330–
92–3046, Revision 06, dated November 15,
2013.
(s) 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 it to
the attention of the person identified in
paragraph (t)(2) of this AD. Information may
be emailed to: 9-ANM-116-ACO-AMOCREQUESTS@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.
(2) Contacting the Manufacturer: As of the
effective date of this AD, 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
EASA; or Airbus’s EASA DOA. If approved
by the DOA, the approval must include the
DOA-authorized signature.
(t) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2014–0219, dated
September 29, 2014, 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–2016–9393.
(2) For more information about this AD,
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.
(3) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (u)(3) and (u)(4) of this AD.
(u) 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.
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srobinson on DSKBC5CHB2PROD with RULES
Federal Register / Vol. 82, No. 140 / Monday, July 24, 2017 / Rules and Regulations
(i) Airbus A330 Airworthiness Limitations
Section (ALS) Part 4—System Equipment
Maintenance Requirements (SEMR), Revision
05, dated October 19, 2015.
(ii) Airbus A340 Airworthiness Limitations
Section (ALS) Part 3—Certification
Maintenance Requirements (CMR), Revision
03, dated October 19, 2015.
(iii) Airbus A340 Airworthiness
Limitations Section (ALS) Part 4—System
Equipment Maintenance Requirements
(SEMR), Revision 04, dated October 19, 2015.
(iv) Airbus Service Bulletin A330–27–
3102, Revision 09, dated March 29, 2016.
(v) Airbus Service Bulletin A330–27–3137,
including Appendix 01, dated March 20,
2007.
(vi) Airbus Service Bulletin A330–27–
3137, Revision 01, including Appendix 1,
dated December 6, 2007.
(vii) Airbus Service Bulletin A330–27–
3137, Revision 02, dated January 18, 2010.
(viii) Airbus Service Bulletin A330–27–
3143, Revision 01, dated July 10, 2012.
(ix) Airbus Service Bulletin A330–92–
3046, Revision 04, dated July 16, 2010.
(x) Airbus Service Bulletin A330–92–3046,
Revision 05, dated November 7, 2011.
(xi) Airbus Service Bulletin A330–92–
3046, Revision 07, dated January 13, 2017.
(xii) Airbus Service Bulletin A340–27–
4107, Revision 09, dated March 29, 2016.
(xiii) Airbus Service Bulletin A340–27–
4136, including Appendix 01, dated March
20, 2007.
(xiv) Airbus Service Bulletin A340–27–
4136, Revision 01, including Appendix 1,
dated December 6, 2007.
(xv) Airbus Service Bulletin A340–27–
4136, Revision 02, including Appendix 1,
dated February 24, 2010.
(xvi) Airbus Service Bulletin A340–27–
4143, dated February 21, 2012.
(xvii) Airbus Service Bulletin A340–27–
5030, Revision 01, including Appendix 1,
dated November 20, 2009.
(xviii) Airbus Service Bulletin A340–92–
4056, Revision 03, dated July 16, 2010.
(xix) Airbus Service Bulletin A340–92–
4056, Revision 04, dated December 5, 2013.
(xx) Airbus Service Bulletin A340–92–
5008, Revision 07, dated February 8, 2013.
(3) For service information identified in
this AD, contact Airbus, Airworthiness
Office—EIAS, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France;
telephone +33 5 61 93 36 96; fax +33 5 61
93 44 51; email account.airworth-eas@
airbus.com; Internet https://www.airbus.com.
(4) 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.
(5) 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.
VerDate Sep<11>2014
16:26 Jul 21, 2017
Jkt 241001
Issued in Renton, Washington, on June 15,
2017.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2017–14923 Filed 7–21–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–0157; Directorate
Identifier 2016–CE–039–AD; Amendment
39–18965; AD 2017–15–05]
RIN 2120–AA64
Airworthiness Directives; Piper
Aircraft, Inc. Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are superseding
Airworthiness Directive (AD) 69–13–03
for all Piper Aircraft, Inc. Models PA–
23, PA–23–160, PA–23–235, PA–23–
250, PA–E23–250, and PA–30 airplanes.
AD 69–13–03 required inspection of the
heater exhaust extension, replacement
of the extension as necessary, and
overhaul of the combustion heater
assembly. This AD retains the
inspection of the heater exhaust
extension with replacement of the
extension as necessary and removes the
overhaul requirement of the combustion
heater assembly. This AD was prompted
by a recently issued AD that applies to
the Meggitt (Troy), Inc. combustion
heaters, and the combustion heater AD
incorporates corrective actions for the
heater that contradict the overhaul
requirement of AD 69–13–03. We are
issuing this AD to continue to address
the unsafe condition on these products
and avoid potential contradiction of
actions.
SUMMARY:
DATES:
This AD is effective August 28,
2017.
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–2017–
0157; 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 final rule, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (phone: 800–647–5527) is
Document Management Facility, U.S.
PO 00000
Frm 00007
Fmt 4700
Sfmt 4700
34257
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:
Scott Hopper, Aerospace Engineer,
FAA, Atlanta Aircraft Certification
Office, 1701 Columbia Avenue, College
Park, Georgia 30337; phone: (404) 474–
5535; fax: (404) 474–5606; email:
scott.hopper@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 69–13–03,
Amendment 39–785 (34 FR 9748, June
24, 1969) as amended by AD 69–13–03,
Amendment 39–1749 (38 FR 33765,
December 7, 1973), (‘‘AD 69–13–03’’).
AD 69–13–03 applied to certain Piper
Aircraft, Inc. Models PA–23, PA–23–
160, PA–23–235, PA–23–250, PA–E23–
250, and PA–30 airplanes. AD 69–13–03
required inspection of the heater
exhaust extension to determine if it is
mild steel or stainless steel, repetitive
inspections of the mild steel extensions
for deterioration, replacement of the
extension as necessary, and overhaul of
the combustion heater assembly. AD
69–13–03 resulted from the potential of
carbon monoxide entering the airplane
cabin.
The NPRM was prompted by another
AD action that applies to the Meggitt
(Troy), Inc. combustion heaters installed
on the airplanes AD 69–13–03 applied
to. AD 2017–06–03; Amendment 39–
18827 (82 FR 15988, March 31, 2017),
which applies to the Meggitt
combustion heaters incorporates
corrective actions for the heater that
contradict the overhaul requirement of
AD 69–13–03. The NPRM proposed to
retain certain requirements of AD 69–
13–03 and remove the requirement for
overhaul of the heater assembly. We are
issuing this AD continue to address the
unsafe condition on these products and
avoid potential contradiction of actions.
Comments
We gave the public the opportunity to
participate in developing this AD. One
comment was received from Ahmed Ali
who agrees with the AD action. The
following presents the other comment
received on the NPRM and the FAA’s
response to the comment.
Request To Withdraw NPRM
Jeff Aryan stated the AD is not
necessary. The commenter has owned a
Model PA–30 airplane for 25 years and
does not believe heater fumes can enter
the cabin. He has used the heater for
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]]>Agencies
[Federal Register Volume 82, Number 140 (Monday, July 24, 2017)]
[Rules and Regulations]
[Pages 34251-34257]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-14923]
========================================================================
Rules and Regulations
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains regulatory documents
having general applicability and legal effect, most of which are keyed
to and codified in the Code of Federal Regulations, which is published
under 50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by the Superintendent of Documents.
========================================================================
Federal Register / Vol. 82, No. 140 / Monday, July 24, 2017 / Rules
and Regulations
[[Page 34251]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2016-9393; Directorate Identifier 2014-NM-199-AD;
Amendment 39-18935; AD 2017-13-05]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are superseding Airworthiness Directive (AD) 2013-13-16 for
all Airbus Model A330-200, A330-200 Freighter, A330-300 series
airplanes; and all Airbus Model A340-200, -300, -500, and -600 series
airplanes. AD 2013-13-16 required repetitive inspections for
discrepancies of the ball-screw assembly of the trimmable horizontal
stabilizer actuator (THSA), repetitive greasing of the THSA ball-nut,
and replacement of the THSA if necessary; and modification or
replacement (as applicable) of the ball-nut assembly, which ends
certain repetitive inspections. This new AD requires an inspection,
corrective actions if necessary, lubrication of the ball-nut,
modification of the THSA, and removal of certain airplanes from the
applicability. This AD was prompted by a determination that a
modification that automatically detects failure of the ball-screw
assembly is necessary. We are issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective August 28, 2017.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of August 28,
2017.
ADDRESSES: For service information identified in this final rule,
contact Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax
+33 5 61 93 44 51; email account.airworth-eas@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. It is also available on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2016-
9393.
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-
9393; 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 street address for the Docket Office (telephone
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: 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
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2013-13-16, Amendment 39-17504 (78 FR 47537,
August 6, 2013) (``AD 2013-13-16''). AD 2013-13-16 applied to all
Airbus Model A330-200, A330-200 Freighter, A330-300 series airplanes,
and all Airbus Model A340-200, -300, -500, and -600 series airplanes.
The NPRM published in the Federal Register on December 19, 2016 (81 FR
91882) (``the NPRM'').
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA
Airworthiness Directive 2014-0219, dated September 29, 2014 (referred
to after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition on all Airbus Model A330
and Model A340 series airplanes. The MCAI states:
Several cases of transfer tube disconnection from the ball-nut
of the trimmable horizontal stabilizer actuator (THSA) part number
(P/N) 47172 and 47147-400 were detected on the ground during
greasing and maintenance. Investigation results showed that this was
caused by water ingress into the ball-nut, resulting in the jamming
of the ball transfer circuit when the water froze. If the three
(independent) ball circuits fail, then the THSA operates on a fail-
safe nut (which operates without balls), which jams after several
movements on the ballscrew of the THSA.
This condition, if not detected and corrected, could damage the
ball screw and the fail-safe nut, possibly resulting in jamming of
the THSA and consequent reduced control of the aeroplane.
To detect at an early stage any distortion or initiation of
disconnection, [Directorate General for Civil Aviation] DGAC France
issued AD 2001-356 and AD 2001-357 to require repetitive inspections
of the transfer tubes and their collars and, depending on findings,
corrective action(s).
Prompted by another case of transfer tube disconnection, DGAC
France issued AD 2001-356R2 and AD 2001-357R2 to require additional
repetitive greasing and reinforcement of the ball-nut maintenance
greasing instructions.
Subsequently, DGAC France issued AD 2002-037 and AD 2002-038 to
require a modification that was also terminating action for the
repetitive inspections and greasing tasks required by DGAC France AD
2001-356R2 and AD 2001-357R2 for the THSA P/N 47172 by application
of Service Bulletin (SB) A330-27-3085 or SB A340-27-4089 (equivalent
to Airbus production modification 49590), as applicable, changing
the THSA P/N from 47172 to 47172-300.
Later on, DGAC France issued AD 2002-414 (later revised to R3)
and AD 2002-415 (later revised to R2), which superseded the DGAC
France AD 2001-356R2, AD 2001-357R2, AD 2002-037, and AD 2002-038,
requiring:
--Repetitive inspections of all THSA P/N in service,
--repetitive lubrication of some THSA P/N, and
--replacement of THSA P/N 47172, 47147-400 and 47147-2XX/-3XX.
In addition, the electrical flight control computers monitor the
operation of the THSA and the jamming of this actuator could be
detected and indicated by messages on the maintenance system and on
the [electronic centralized aircraft monitor] ECAM. For that
[[Page 34252]]
reason, DGAC France AD 2002-414 and AD 2002-415 also required
inspection of the THSA after display of such message(s).
After those [DGAC France] ADs were issued, Airbus introduced 4
new THSA, P/N 47172-500, P/N 47172-510, P/N 47172-520 and P/N 47172-
530.
As these new THSA also needed to be inspected/lubricated, EASA
issued AD 2010-0192 and [EASA] AD 2010-0193 [which correspond to FAA
AD 2013-13-16], which retained the requirements of DGAC France AD F-
2002-414R3 and AD F-2002-415R2 respectively, which were superseded,
to add required repetitive inspections and lubrications of the new
THSA P/N.
Since those [EASA] ADs were issued, all requirements of EASA AD
2010-0192 and [EASA] AD 2010-0193 were transferred into Airbus
Airworthiness Limitations Section (ALS) Part 4, except the
requirement of paragraph (2.3) of those [EASA] ADs. At this time,
compliance with ALS Part 4 tasks is required by EASA AD 2013-0268
(A330 aeroplanes) and [EASA] AD 2013-0269 (A340 aeroplanes),
respectively [which correspond to FAA AD 2015-16-02, Amendment 39-
18227 (80 FR 48019, August 11, 2015) (A330 airplanes); and AD 2014-
23-17, Amendment 39-18033 (79 FR 71304, December 2, 2014) (A340
airplanes); respectively.]
In addition, Airbus developed a Checkable Shear Pin (CSP) for
the THSA and an associated additional electrical harness, which
consists of installation of two Electrical Detection Devices (EDD)
on the lower attachment secondary load path, which gives an
indication to the Flight Control Primary Computers of secondary load
path engagement.
After embodiment of these modifications on an aeroplane, the
repetitive inspections of the ballscrew assembly for integrity of
the primary and secondary load paths is no longer required, because
the failure is detected automatically by this new device.
For the reasons described above, this [EASA] AD retains only the
requirement of paragraph (2.3) of EASA AD 2010-0192 and 2010-0193
[actions following ECAM fault messages], which are superseded, and
requires the installation of CSP and associated additional
electrical harness on the THSA of the aeroplane. This [EASA] AD also
requires, for A340-500/-600 aeroplanes that are post-SB A340-92-5008
(at Revision 06 or earlier), accomplishment of A340 ALS Part 3 task
274000-B0002-1-C, providing a grace period of 3 months for
aeroplanes that have exceeded the applicable threshold or interval.
The unsafe condition is the degraded operation of the THSA, which
could result in reduced control of the airplane.
Model A330-223F and A330-243F airplanes have been removed from the
applicability of this AD to correspond with the MCAI.
Required actions include a detailed inspection and corrective
actions if an ECAM fault message is displayed, repetitive lubrication
of the THSA ball-nut, and a modification of the THSA by installing a
CSP and associated electrical harness.
Required actions also include certain ``Additional Work'' that is
described in the following service information.
``Additional Work'' in Airbus Service Bulletin A330-27-
3143, Revision 01, dated July 10, 2012, is described as removing the
closing plug from the electrical harness 4515VB and connecting the
electrical harness 4515VB to the THSA.
``Additional Work'' in Airbus Service Bulletin A330-92-
3046, Revision 07, dated January 13, 2017; and in Airbus Service
Bulletin A340-92-4056, Revision 04, dated December 5, 2013; is
described as replacement of a certain harness item, installation of
placards and cable support, modification of a certain bracket, and
installation of a certain spacer.
``Additional Work'' in Airbus Service Bulletin A340-92-
5008, Revision 07, dated February 8, 2013, is described as replacing a
certain wiring harness, replacing a certain THSA harness, installing
additional placards, and modifying a certain wire harness installation
order.
You may examine the MCAI in the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2016-
9393.
Comments
We gave the public the opportunity to participate in developing
this AD. We received no comments on the NPRM or on the determination of
the cost to the public.
New Service Information
Since we issued the NPRM, we have reviewed Airbus Service Bulletin
A330-92-3046, Revision 07, dated January 13, 2017 (we referred to
Airbus Service Bulletin A330-92-3046, Revision 06, dated November 15,
2013, as one of the appropriate sources of service information for
installing an electrical harness). Airbus Service Bulletin A330-92-
3046, Revision 07, dated January 13, 2017, includes minor updates to
the procedures and illustrations. We have revised figure 2 to
paragraphs (h) and (i) of this AD and figure 3 to paragraph (j) of this
AD to refer to Airbus Service Bulletin A330-92-3046, Revision 07, dated
January 13, 2017. We have also added paragraph (r)(2) to this AD to
give credit for actions done in accordance with Airbus Service Bulletin
A330-92-3046, Revision 06, dated November 15, 2013.
Costs of Compliance Change
The costs of compliance information in the NPRM included a parts
cost of $14,198. We have revised the costs of compliance information in
this AD based on receiving updated cost information from the
manufacturer to include a parts cost of $17,481.
Conclusion
We reviewed the relevant data, and determined that air safety and
the public interest require adopting this AD with the changes described
previously and minor editorial changes. We have determined that these
minor changes:
Are consistent with the intent that was proposed in the
NPRM for correcting the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM.
We also determined that these changes will not increase the
economic burden on any operator or increase the scope of this AD.
Related Service Information Under 1 CFR Part 51
Airbus has issued the following service information. The service
bulletins having the same document number are distinct because each
revision contains unique editorial changes.
The following service information describes procedures for doing
repetitive inspections for integrity of the primary and secondary load
paths of the ball-screw assembly of the THSA. These service bulletins
are distinct because they apply to different airplane models.
Airbus Service Bulletin A330-27-3102, Revision 09, dated
March 29, 2016.
Airbus Service Bulletin A340-27-4107, Revision 09, dated
March 29, 2016.
The following service information describes procedures for
installing two electrical detection devices, also called CSPs, on the
lower attachment secondary load path of the THSA, and modifying the
THSA. These service bulletins are distinct because they apply to
different airplane models equipped with THSAs having different part
numbers.
Airbus Service Bulletin A330-27-3137, including Appendix
01, dated March 20, 2007.
Airbus Service Bulletin A330-27-3137, Revision 01,
including Appendix 1, dated December 6, 2007.
Airbus Service Bulletin A330-27-3137, Revision 02, dated
January 18, 2010.
Airbus Service Bulletin A330-27-3143, Revision 01, dated
July 10, 2012.
[[Page 34253]]
Airbus Service Bulletin A340-27-4136, including Appendix
01, dated March 20, 2007.
Airbus Service Bulletin A340-27-4136, Revision 01,
including Appendix 1, dated December 6, 2007.
Airbus Service Bulletin A340-27-4136, Revision 02,
including Appendix 1, dated February 24, 2010.
Airbus Service Bulletin A340-27-4143, dated February 21,
2012.
Airbus Service Bulletin A340-27-5030, Revision 01,
including Appendix 1, dated November 20, 2009.
The following service information describes procedures for
installing electrical wiring harnesses and brackets to connect the
secondary nut detection device to the monitoring systems. These service
bulletins are distinct because they apply to different airplane models.
Airbus Service Bulletin A330-92-3046, Revision 04, dated
July 16, 2010.
Airbus Service Bulletin A330-92-3046, Revision 05, dated
November 7, 2011.
Airbus Service Bulletin A330-92-3046, Revision 07, dated
January 13, 2017.
Airbus Service Bulletin A340-92-4056, Revision 03, dated
July 16, 2010.
Airbus Service Bulletin A340-92-4056, Revision 04, dated
December 5, 2013.
Airbus Service Bulletin A340-92-5008, Revision 07, dated
February 8, 2013.
The following service information describes system equipment
maintenance requirements (SEMRs) that refer to preventative maintenance
requirements found necessary to comply with safety objectives. These
documents are distinct because they apply to different airplane models.
Airbus A330 Airworthiness Limitations Section (ALS) Part
4--System Equipment Maintenance Requirements (SEMR), Revision 05, dated
October 19, 2015.
Airbus A340 Airworthiness Limitations Section (ALS) Part
4--System Equipment Maintenance Requirements (SEMR), Revision 04, dated
October 19, 2015.
Airbus A340 Airworthiness Limitations Section (ALS) Part 3--
Certification Maintenance Requirements (CMR), Revision 03, dated
October 19, 2015, describes CMRs that are system-related periodic tasks
established during type certification.
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.
Costs of Compliance
We estimate that this AD affects 33 airplanes of U.S. registry.
The actions required by AD 2013-13-16, and retained in this AD take
about 1 work-hour per product, at an average labor rate of $85 per
work-hour. Based on these figures, the estimated cost of the actions
that are required by AD 2013-13-16 is $85 per product.
We also estimate that it takes about 67 work-hours per product to
comply with the basic requirements of this AD. The average labor rate
is $85 per work-hour. Required parts would cost about $17,481 per
product. Based on these figures, we estimate the cost of this AD on
U.S. operators to be $764,808, or $23,176 per product.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more 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)
2013-13-16, Amendment 39-17504 (78 FR 47537, August 6, 2013), and
adding the following new AD:
2017-13-05 Airbus: Amendment 39-18935; Docket No. FAA-2016-9393;
Directorate Identifier 2014-NM-199-AD.
(a) Effective Date
This AD is effective August 28, 2017.
(b) Affected ADs
This AD replaces AD 2013-13-16, Amendment 39-17504 (78 FR 47537,
August 6, 2013) (``AD 2013-13-16'').
(c) Applicability
This AD applies to the airplanes identified in paragraphs (c)(1)
and (c)(2) of this AD, certificated in any category.
(1) Airbus Model A330-201, -202, -203, -223, -243, -301, -302, -
303, -321, -322, -323, -341, -342, and -343 airplanes, all
manufacturer serial numbers.
(2) Airbus Model A340-211, -212, -213, -311, -312, -313, -541,
and -642 airplanes, all manufacturer serial numbers.
(d) Subject
Air Transport Association (ATA) of America Code 27, Flight
Controls.
(e) Reason
This AD was prompted by the determination that a modification
that automatically detects failure of the ball-screw assembly is
necessary. We are issuing this AD to detect and correct wear on the
trimmable horizontal stabilizer actuator (THSA), possibly resulting
in damage to the ball-screw and fail-safe nut, which could jam the
THSA and result in reduced control of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Actions for Electronic Centralized Aircraft Monitor (ECAM) Fault
Messages
For airplanes other than those identified in figure 1 to
paragraphs (g), (h), and (q) of this AD: If, during any flight, one
of the ``PRIM
[[Page 34254]]
X PITCH FAULT'' or ``STAB CTL FAULT'' messages is displayed on the
ECAM associated with the ``PITCH TRIM ACTR (1CS)'' maintenance
message, before further flight after each time the message is
displayed on the ECAM, do the actions specified in paragraphs (g)(1)
and (g)(2) of this AD.
(1) Do the applicable detailed inspection of the ball-screw
assembly for integrity of the primary and secondary load path; check
the checkable shear pins (CSP), if installed; and do all applicable
corrective actions; as specified in paragraph (g)(1)(i), (g)(1)(ii),
or (g)(1)(iii) of this AD. Do all applicable corrective actions
before further flight.
(i) For Model A330 series airplanes: Do the actions in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A330-27-3102, Revision 09, dated March 29, 2016, except as
required by paragraph (n)(1) of this AD.
(ii) For Model A340-200 and -300 series airplanes: Do the
actions in accordance with the Accomplishment Instructions of Airbus
Service Bulletin A340-27-4107, Revision 09, dated March 29, 2016,
except as required by paragraph (n)(1) of this AD.
(iii) For Model A340-500 and -600 series airplanes: Do the
actions 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).
Note 1 to paragraph (g)(1)(iii) of this AD: Guidance for the
inspection of the ball-screw assembly can be found in Task 274000-
B0002-1-C, Inspection of the ball-screw assembly for integrity of
the primary and secondary load paths, of the Airbus A340
Airworthiness Limitations Section (ALS) Part 3--Certification
Maintenance Requirements (CMR), Revision 03, dated October 19, 2015.
(2) Lubricate the THSA ball-nut in accordance with the
applicable service information specified in paragraph (g)(2)(i),
(g)(2)(ii), or (g)(2)(iii) of this AD.
(i) Task 274400-00002-1-E, Lubrication of the THSA ball-nut, of
Airbus A330 ALS Part 4--System Equipment Maintenance Requirements
(SEMR), Revision 05, dated October 19, 2015 (for Model A330 series
airplanes).
(ii) Task 274400-00002-1-E, Lubrication of the THSA ball-nut, of
Airbus A340 ALS Part 4--System Equipment Maintenance Requirements
(SEMR), Revision 04, dated October 19, 2015 (for Model A340-200 and
-300 series airplanes).
(iii) Task 274000-B0003-1-C, Lubrication of THS Actuator ball-
screw nut, of Airbus A340 ALS Part 3--Certification Maintenance
Requirements (CMR), Revision 03, dated October 19, 2015 (for Model
A340-500 and -600 series airplanes).
Figure 1 to Paragraphs (g), (h), and (q) of This AD--Definition of
Airplane Groups
------------------------------------------------------------------------
On which the
following actions or
Group Airplane models modifications have
been done
------------------------------------------------------------------------
Group 1 airplanes............. Airbus Model A330- On which the actions
200 and -300 specified in Airbus
series airplanes. Service Bulletin
A330-27-3137, dated
March 20, 2007; or
Revision 01, dated
December 6, 2007;
and Airbus Service
Bulletin A330-92-
3046, Revision 04,
dated July 16, 2010;
or Revision 05,
dated November 7,
2011; or Revision
06, dated November
15, 2013; have been
embodied in service.
Airbus Model A340- On which the actions
200 and -300 specified in Airbus
series airplanes. Service Bulletin
A340-27-4136,
including Appendix
1, dated March 20,
2007; or Revision
01, including
Appendix 1, dated
December 6, 2007;
and Airbus Service
Bulletin A340-92-
4056, Revision 03,
dated July 16, 2010;
have been embodied
in service.
Group 2 airplanes............. Airbus Model A330- On which Airbus
200 and -300 Modifications 55780,
series airplanes 52269, and 56056
and Model A340- have been embodied
200 and -300 in production.
series airplanes.
Airbus Model A340- On which Airbus
500 and -600 Modifications 54882,
series airplanes. 52191, and 56058
have been embodied
in production.
Group 3 airplanes............. Airbus Model A330- On which Airbus
200 and -300 Service Bulletin
series airplanes. A330-27-3137, dated
March 20, 2007; or
Revision 01, dated
December 6, 2007;
has been embodied in
service and Airbus
Modifications 52269
and 56056 have been
embodied in
production.
Airbus Model A330- On which Airbus
200 and -300 Modification 55780
series airplanes. has been embodied in
production and
Airbus Service
Bulletin A330-92-
3046 Revision 04,
dated July 16, 2010;
or Revision 05,
dated November 07,
2011; or Revision
06, dated November
15, 2013; has been
embodied in service.
Airbus Model A340- On which Airbus
200 and -300 Service Bulletin
series airplanes. A340-27-4136,
including Appendix
1, dated March 20,
2007; or Revision
01, including
Appendix 1, dated
December 6, 2007;
has been embodied in
service and Airbus
Modifications 52269
and 56056 have been
embodied in
production.
Airbus Model A340- On which Airbus
200 and -300 Modification 55780
series airplanes. has been embodied in
production and
Airbus Service
Bulletin A340-92-
4056, Revision 03,
dated July 16, 2010,
has been embodied in
service.
------------------------------------------------------------------------
(h) Installation of CSP and Electrical Harness
For all airplanes, except Group 2 airplanes specified in figure
1 to paragraphs (g), (h), and (q) of this AD, and except for
airplanes identified in paragraphs (i), (j), and (n)(2) of this AD:
Within 12 months after the effective date of this AD, modify the
airplane by installing a CSP on the THSA and an additional
electrical harness, in accordance with the Accomplishment
Instructions of the Airbus service information specified in figure 2
to paragraphs (h) and (i) of this AD, as applicable to the part
number of the THSA installed on the airplane, except as provided by
paragraph (n)(2) of this AD.
Figure 2 to Paragraphs (h) and (i) of this AD--Applicable Service Information for Modification
----------------------------------------------------------------------------------------------------------------
Service bulletin for
THSA Part No. (P/N) Service bulletin for CSP installation electrical harness
installation
----------------------------------------------------------------------------------------------------------------
47172-300............................ Airbus Service Bulletin A330-27-3137, Airbus Service Bulletin A330-
Revision 02, dated January 18, 2010, for 92-3046, Revision 07, dated
Airbus Model A330-200 and -300 series January 13, 2017, for Airbus
airplanes; and Model A330-200 and -300
series airplanes; and
Airbus Service Bulletin A340-27-4136,
Revision 02, including Appendix 1, dated
February 24, 2010, for Airbus Model A340-
200 and -300 series airplanes.
[[Page 34255]]
47147-500............................ Airbus Service Bulletin A330-27-3143, Airbus Service Bulletin A340-
Revision 01, dated July 10, 2012, for 92-4056, Revision 04, dated
Airbus Model A330-200 and -300 series December 5, 2013, for Airbus
airplanes; and Model A340-200 and -300
series airplanes.
Airbus Service Bulletin A340-27-4143,
dated February 21, 2012, for Airbus Model
A340-200 and -300 series airplanes.
47175-200, 47175-300................. Airbus Service Bulletin A340-27-5030, Airbus Service Bulletin A340-
Revision 01, including Appendix 1, dated 92-5008, Revision 07, dated
November 20, 2009, for Airbus Model A340- February 8, 2013, for Airbus
541 and -642 airplanes. Model A340-541 and -642
airplanes.
----------------------------------------------------------------------------------------------------------------
(i) ``Additional Work'' on Previously Modified Airplanes
For airplanes that have already been modified (installation of
CSP on the THSA and electrical harness) before the effective date of
this AD in accordance with the Accomplishment Instructions of any
previous revision of an Airbus service bulletin specified in figure
2 to paragraphs (h) and (i) of this AD, as applicable: Within 12
months after the effective date of this AD, do the ``Additional
Work'' specified in, and in accordance with, the Accomplishment
Instructions of the applicable Airbus service information specified
in figure 2 to paragraphs (h) and (i) of this AD.
(j) Installation of Electrical Harness on Airplanes Equipped With a CSP
For airplanes having one of the THSAs installed with a part
number listed in figure 3 to paragraph (j) of this AD, and which
have been modified by installing a CSP on the THSA as required by
paragraph (h) of this AD: Within 12 months after the effective date
of this AD, inspect to determine if the electrical harness
identified in the applicable Airbus service information specified in
figure 3 to paragraph (j) of this AD is installed on the airplane,
and if found not to be installed, modify the airplane by installing
an electrical harness, in accordance with the Accomplishment
Instructions of the Airbus service information specified in figure 3
to paragraph (j) of this AD, as applicable to the part number of the
THSA installed on the airplane. Airplanes having one of the THSAs
installed with a part number listed in figure 3 to paragraph (j) of
this AD already have the CSP installed on the THSA, and only the
electrical harness must be installed on the airplane.
Figure 3 to Paragraph (j) of This AD--Electrical Harness Installation
------------------------------------------------------------------------
Service information for
THSA P/N electrical harness installation
------------------------------------------------------------------------
47172-500, 47172-510, 47172-520, 47172- Airbus Service Bulletin A330-92-
530, 47147-700, 47147-710. 3046, Revision 07, dated
January 13, 2017, for Airbus
Model A330-200 and -300 series
airplanes.
Airbus Service Bulletin A340-92-
4056, Revision 04, dated
December 5, 2013, for Airbus
Model A340-200 and -300 series
airplanes.
47175-500, 47175-520, 47175-530........ Airbus Service Bulletin A340-92-
5008, Revision 07, dated
February 8, 2013, for Airbus
Model A340-541 and -642
airplanes.
------------------------------------------------------------------------
(k) Terminating Action for Repetitive Inspections of Airbus Model A330-
200 and -300 Series Airplanes
Accomplishment of a modification before the effective date of
this AD, using the Accomplishment Instructions of Airbus Service
Bulletin A330-27-3137, dated March 20, 2007; or Revision 01, dated
December 6, 2007; and Airbus Service Bulletin A330-92-3046, Revision
04, dated July 15, 2010; or Revision 05, dated November 7, 2011; or
Revision 06, dated November 15, 2013; terminates the repetitive
inspections specified in paragraphs (k)(1) through (k)(4) of this
AD. Modification of an airplane as required by this paragraph does
not constitute terminating action for the actions specified in
paragraph (g)(2) of this AD or the additional work specified in
paragraph (i) of this AD.
(1) Task 274400-00001-1-E, Detailed inspection of the ball-screw
assembly for integrity of the primary and secondary load path and
check the gap at the secondary nut trunnion, of Airbus A330 ALS Part
4--System Equipment Maintenance Requirements (SEMR), Revision 05,
dated October 19, 2015.
(2) Task 274400-00001-2-E, Detailed inspection of the ball-screw
assembly for integrity of the primary and secondary load path and
check the CSPs, of Airbus A330 ALS Part 4--System Equipment
Maintenance Requirements (SEMR), Revision 05, dated October 19,
2015.
(3) Task 274400-00001-3-E, Detailed inspection of the ball-screw
assembly for integrity of the primary and secondary load path and
check the CSPs, of Airbus A330 ALS Part 4--System Equipment
Maintenance Requirements (SEMR), Revision 05, dated October 19,
2015.
(4) Task 274400-00001-4-E, Detailed inspection of the ball-screw
assembly for integrity of the primary and secondary load path and
check the CSPs, of Airbus A330 ALS Part 4--System Equipment
Maintenance Requirements (SEMR), Revision 05, dated October 19,
2015.
(l) Terminating Action for Repetitive Inspections of Airbus Model A340-
200 and -300 Series Airplanes
Accomplishment of a modification in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A340-27-4143,
dated February 21, 2012; and Airbus Service Bulletin A340-92-4056,
Revision 03, dated July 16, 2010; terminates the actions required by
paragraph (g)(1) of this AD for modified Airbus Model A340-200 and -
300 series airplanes only. Modification of an airplane as specified
in this paragraph does not constitute terminating action for the
actions specified in paragraph (g)(2) of this AD, or the additional
work specified in paragraph (i) of this AD.
(m) Terminating Action for Repetitive Inspections of Airbus Model A340-
200 and -300 Series Airplanes
Accomplishment of a modification before the effective date of
this AD using the Accomplishment Instructions of Airbus Service
Bulletin A340-27-4136, including Appendix 1, dated March 20, 2007;
or Revision 01, including Appendix 1, dated December 6, 2007; and
Airbus Service Bulletin A340-92-4056, Revision 03, dated July 16,
2010; terminates the repetitive inspections specified in paragraphs
(m)(1) through (m)(4) of this AD. Modification of an airplane as
specified in this paragraph does not constitute terminating action
for the actions specified in paragraph (g)(2) of this AD, or the
additional work specified in paragraph (i) of this AD.
(1) Task 274400-00001-1-E, Detailed inspection of the ball-screw
assembly for integrity of the primary and secondary load path and
gap check at the secondary nut trunnion, of Airbus A340 ALS Part 4--
System Equipment Maintenance Requirements (SEMR), Revision 04, dated
October 19, 2015.
[[Page 34256]]
(2) Task 274400-00001-2-E, Detailed inspection of the ball-screw
assembly for integrity of the primary and secondary load path and
CSP check, of Airbus A340 ALS Part 4--System Equipment Maintenance
Requirements (SEMR), Revision 04, dated October 19, 2015.
(3) Task 274400-00001-3-E, Detailed inspection of the ball-screw
assembly for integrity of the primary and secondary load path and
CSP check, of Airbus A340 ALS Part 4--System Equipment Maintenance
Requirements (SEMR), Revision 04, dated October 19, 2015.
(4) Task 274400-00001-4-E, Detailed inspection of the ball-screw
assembly for integrity of the primary and secondary load path and
CSP check, of A340 ALS Part 4--System Equipment Maintenance
Requirements (SEMR), Revision 04, dated October 19, 2015.
(n) Exceptions to the Actions in Certain Service Information and
Paragraph (h) of This AD
(1) Where Airbus Service Bulletin A330-27-3102, Revision 09,
dated March 29, 2016 (for Model A330 series airplanes); or Airbus
Service Bulletin A340-27-4107, Revision 09, dated March 29, 2016
(for Model A340 series airplanes); specifies to contact Airbus for a
damage assessment: Before further flight, accomplish the required
actions in accordance with the procedures specified in paragraph
(s)(2) of this AD.
(2) For airplanes that already had the electrical harness
installed during production using Airbus Modifications 52269 and
56056 for Airbus Model A330-200 and -300 series airplanes and Airbus
Model A340-200 and -300 series airplanes, and using Airbus
Modifications 52191 and 56058 for Model A340-500 and -600 series
airplanes: Only the CSP must be installed on the THSA in accordance
with applicable Airbus service bulletins and within the compliance
time specified in paragraph (h) of this AD.
(o) Terminating Action for Repetitive Inspections for Airplanes on
Which Actions Required by Paragraph (h), (i), or (j) of This AD Are
Done
Modification of an airplane as required by paragraph (h), (i),
or (j) of this AD, as applicable, constitutes terminating action for
that airplane for the applicable actions identified in paragraphs
(o)(1) through (o)(4) of this AD.
(1) For all airplanes: The actions required by paragraph (g) of
this AD.
(2) For Model A340-500 and -600 series airplanes: Task 274000-
B0002-1-C, Inspection of the ball-screw assembly for integrity of
the primary and secondary load paths, of Airbus A340 ALS Part 3--
Certification Maintenance Requirements (CMR), Revision 03, dated
October 19, 2015.
(3) For Model A330-200 and -300 series airplanes: The ALS tasks
identified in paragraphs (k)(1) through (k)(4) of this AD.
(4) For Model A340-200 and -300 series airplanes: The ALS tasks
identified in paragraphs (m)(1) through (m)(4) of this AD.
(p) Ball-Screw Assembly Inspection for Certain Airplanes
For Model A340-500 and -600 airplanes that are in post-Airbus
Service Bulletin A340-92-5008, at Revision 06 or earlier,
configuration: Before exceeding the threshold or interval, as
applicable, of Task 274000-B0002-1-C, Inspection of the ball-screw
assembly for integrity of the primary and secondary load paths, of
Airbus A340 ALS Part 3--Certification Maintenance Requirements
(CMR), Revision 03, dated October 19, 2015, or within 3 months after
the effective date of this AD, whichever occurs later, accomplish
Task 274000-B0002-1-C, Inspection of the ball-screw assembly for
integrity of the primary and secondary load paths, of Airbus A340
ALS Part 3--Certification Maintenance Requirements (CMR), Revision
03, dated October 19, 2015; and do all applicable corrective
actions. Do all applicable corrective actions before further flight
using a method approved by the Manager, International Branch, ANM-
116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA
DOA. Repeat Task 274000-B0002-1-C, Inspection of the ball-screw
assembly for integrity of the primary and secondary load paths,
thereafter at the applicable intervals specified in Airbus A340 ALS
Part 3--CMRs, Revision 03, dated October 19, 2015.
(q) Parts Installation Prohibitions
(1) For all airplanes except Group 2 airplanes as identified in
figure 1 to paragraphs (g), (h), and (q) of this AD: After
modification of the airplane as required by paragraph (h), (i), or
(j) of this AD, as applicable, no person may install any THSA having
part number (P/N) 47172-300, P/N 47147-500, P/N 47175-200, or P/N
47175-300.
(2) For Group 2 airplanes, as identified in figure 1 to
paragraphs (g), (h), and (q) of this AD: As of the effective date of
this AD, no person may install on any Group 2 airplane any THSA
having P/N 47172-300, P/N 47147-500, P/N 47175-200, or P/N 47175-
300.
(r) Credit for Previous Actions
(1) This paragraph provides credit for actions required by
paragraph (g)(2) of this AD, if those actions were performed before
the effective date of this AD using the applicable service
information specified in paragraphs (r)(1)(i) through (r)(1)(iv) of
this AD.
(i) Task 274400-00002-1-E, Lubrication of the THSA ball-nut, of
Airbus A330 ALS Part 4--Ageing Systems Maintenance, Revision 03,
dated September 9, 2011 (for Model A330 series airplanes).
(ii) Task 274400-00002-1-E, Lubrication of the THSA ball-nut, of
Airbus A330 ALS Part 4--Ageing Systems Maintenance, Revision 04,
dated August 27, 2013 (for Model A330 series airplanes).
(iii) Task 274400-00002-1-E, Lubrication of the THSA ball-nut,
of Airbus A340 ALS Part 4--Ageing Systems Maintenance, Revision 02,
dated October 12, 2011 (for Model A340-200 and -300 series
airplanes).
(iv) Task 274400-00002-1-E, Lubrication of the THSA ball-nut, of
Airbus A340 ALS Part 4--Ageing Systems Maintenance, Revision 03,
dated November 15, 2012 (for Model A340-200 and -300 series
airplanes).
(2) This paragraph provides credit for the electrical harness
installation required by paragraph (h) of this AD and the inspection
and electrical harness installation required by paragraph (j) of
this AD, if those actions were performed before the effective date
of this AD using Airbus Service Bulletin A330-92-3046, Revision 06,
dated November 15, 2013.
(s) 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 it to the attention
of the person identified in paragraph (t)(2) of this AD. Information
may be emailed to: 9-ANM-116-ACO-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.
(2) Contacting the Manufacturer: As of the effective date of
this AD, 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 EASA; or Airbus's EASA DOA. If
approved by the DOA, the approval must include the DOA-authorized
signature.
(t) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2014-0219, dated September 29,
2014, 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-2016-9393.
(2) For more information about this AD, 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.
(3) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (u)(3) and (u)(4) of this AD.
(u) 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.
[[Page 34257]]
(i) Airbus A330 Airworthiness Limitations Section (ALS) Part 4--
System Equipment Maintenance Requirements (SEMR), Revision 05, dated
October 19, 2015.
(ii) Airbus A340 Airworthiness Limitations Section (ALS) Part
3--Certification Maintenance Requirements (CMR), Revision 03, dated
October 19, 2015.
(iii) Airbus A340 Airworthiness Limitations Section (ALS) Part
4--System Equipment Maintenance Requirements (SEMR), Revision 04,
dated October 19, 2015.
(iv) Airbus Service Bulletin A330-27-3102, Revision 09, dated
March 29, 2016.
(v) Airbus Service Bulletin A330-27-3137, including Appendix 01,
dated March 20, 2007.
(vi) Airbus Service Bulletin A330-27-3137, Revision 01,
including Appendix 1, dated December 6, 2007.
(vii) Airbus Service Bulletin A330-27-3137, Revision 02, dated
January 18, 2010.
(viii) Airbus Service Bulletin A330-27-3143, Revision 01, dated
July 10, 2012.
(ix) Airbus Service Bulletin A330-92-3046, Revision 04, dated
July 16, 2010.
(x) Airbus Service Bulletin A330-92-3046, Revision 05, dated
November 7, 2011.
(xi) Airbus Service Bulletin A330-92-3046, Revision 07, dated
January 13, 2017.
(xii) Airbus Service Bulletin A340-27-4107, Revision 09, dated
March 29, 2016.
(xiii) Airbus Service Bulletin A340-27-4136, including Appendix
01, dated March 20, 2007.
(xiv) Airbus Service Bulletin A340-27-4136, Revision 01,
including Appendix 1, dated December 6, 2007.
(xv) Airbus Service Bulletin A340-27-4136, Revision 02,
including Appendix 1, dated February 24, 2010.
(xvi) Airbus Service Bulletin A340-27-4143, dated February 21,
2012.
(xvii) Airbus Service Bulletin A340-27-5030, Revision 01,
including Appendix 1, dated November 20, 2009.
(xviii) Airbus Service Bulletin A340-92-4056, Revision 03, dated
July 16, 2010.
(xix) Airbus Service Bulletin A340-92-4056, Revision 04, dated
December 5, 2013.
(xx) Airbus Service Bulletin A340-92-5008, Revision 07, dated
February 8, 2013.
(3) For service information identified in this AD, contact
Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5
61 93 44 51; email account.airworth-eas@airbus.com; Internet https://www.airbus.com.
(4) 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.
(5) 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 June 15, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2017-14923 Filed 7-21-17; 8:45 am]
BILLING CODE 4910-13-P
